CMA9000 Manual

INSTALLATION/

FLIGHT LINE MANUAL

FLIGHT MANAGEMENT SYSTEM

CMA-9000

H/W 100-601951-VAR

S/W 169-614876-010

CMC Electronics Inc.

600 DR. FREDERIK PHILIPS BOULEVARD VILLE ST-LAURENT, QUEBEC, CANADA H4M 2S9

INSTALLATION/

FLIGHT LINE MANUAL

FLIGHT MANAGEMENT SYSTEM

CMA-9000

H/W 100-601951-VAR

S/W 169-614876-010

CMC Electronics Inc.

600 DR. FREDERIK PHILIPS BOULEVARD VILLE ST-LAURENT, QUEBEC, CANADA H4M 2S9 TEL: (514) 748-3148, TELEX: 05-827822, FAX: (514) 748-3100

Publication No. 9000-GEN-0840

34-61-14

May 10, 2007

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Electronics

Inc.

CUSTOMER SUPPORT

600 DR. FREDERIK PHILIPS BOULEVARD VILLE ST. LAURENT, QUEBEC,

CANADA H4M 2S9

FOLD BACK

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LIST OF EFFECTIVE PAGES

NOTE

The portion of the text affected by the latest change is indicated by a vertical line in the margin of the page. Changes to illustrations are indicated by miniature pointing hands or black vertical lines.

Original... 0... May 10, 2007

THE TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 400 CONSISTING OF THE FOLLOWING

SUBJECT PAGE DATE SUBJECT PAGE DATE

Title T-1 May 10/07

T-2 Blank

List of Effective Pages LEP-1 May 10/07

LEP-2 May 10/07

LEP-3 May 10/07

LEP-4 May 10/07

LEP-5 May 10/07

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Record of Revisions RR-1 May 10/07

RR-2 Blank

Service Bulletin List SB-1 May 10/07

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Electrostatic Discharge ED-1 May 10/07

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Abbreviations INTRO-1 May 10/07

INTRO-2 May 10/07

INTRO-3 May 10/07

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Table of Contents TC-1 May 10/07

TC-2 May 10/07

TC-3 May 10/07

TC-4 May 10/07

TC-5 May 10/07

TC-6 May 10/07

Description and Operation 1 May 10/07

2 May 10/07 3 May 10/07 4 May 10/07 5 May 10/07 6 May 10/07 7 May 10/07 8 May 10/07 9 May 10/07 10 May 10/07 11 May 10/07 12 May 10/07 13 May 10/07 14 May 10/07 15 May 10/07 16 May 10/07 17 May 10/07 18 May 10/07 19 May 10/07 20 May 10/07 21 May 10/07 22 May 10/07 23 May 10/07 24 May 10/07 25 May 10/07 26 May 10/07 27 May 10/07 28 May 10/07 29 May 10/07 30 May 10/07 31 May 10/07 32 May 10/07 33 May 10/07 34 May 10/07 35 May 10/07 36 May 10/07 37 May 10/07 38 May 10/07 39 May 10/07

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LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

Description and Operation 40 May 10/07

(cont’d) 41 May 10/07 42 May 10/07 43 May 10/07 44 May 10/07 45 May 10/07 46 May 10/07 47 May 10/07 48 May 10/07 49 May 10/07 50 May 10/07 51 May 10/07 52 May 10/07 53 May 10/07 54 May 10/07 55 May 10/07 56 May 10/07 57 May 10/07 58 May 10/07 59 May 10/07 60 May 10/07 61 May 10/07 62 May 10/07 63 May 10/07 64 May 10/07 65 May 10/07 66 May 10/07 67 May 10/07 68 May 10/07 69 May 10/07 70 May 10/07 71 May 10/07 72 May 10/07 73 May 10/07 74 May 10/07 75 May 10/07 76 May 10/07 77 May 10/07 78 May 10/07 79 May 10/07 80 May 10/07 81 May 10/07 82 May 10/07 83 May 10/07 84 May 10/07 85 May 10/07 86 May 10/07 87 May 10/07 88 May 10/07 89 May 10/07 90 May 10/07 91 May 10/07 92 May 10/07 93 May 10/07 94 May 10/07 95 May 10/07 96 May 10/07 Installation 101 May 10/07 102 May 10/07 103 May 10/07 104 May 10/07 105 May 10/07 106 May 10/07 107 May 10/07 108 May 10/07 109 May 10/07 110 May 10/07 111 May 10/07 112 May 10/07 113 May 10/07 114 May 10/07 115 May 10/07 116 May 10/07 117 May 10/07 118 May 10/07 119 May 10/07 120 Blank Post-Installation Test 201 May 10/07

202 May 10/07 203 May 10/07 204 May 10/07 205 May 10/07 206 May 10/07 207 May 10/07 208 May 10/07 209 May 10/07 210 May 10/07 211 May 10/07 212 May 10/07 213 May 10/07 214 May 10/07 215 May 10/07

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LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

Post-Installation Test 216 May 10/07

(cont'd) 217 May 10/07 218 May 10/07 219 May 10/07 220 May 10/07 221 May 10/07 222 May 10/07 223 May 10/07 224 May 10/07 225 May 10/07 226 Blank Flight Line Test/ 301 May 10/07 Troubleshooting 302 May 10/07 303 May 10/07 304 May 10/07 305 May 10/07 306 May 10/07 307 May 10/07 308 May 10/07 309 May 10/07 310 May 10/07 311 May 10/07 312 May 10/07 313 May 10/07 314 May 10/07 315 May 10/07 316 May 10/07 317 May 10/07 318 May 10/07 319 May 10/07 320 May 10/07 321 May 10/07 322 May 10/07 323 May 10/07 324 May 10/07 325 May 10/07 326 May 10/07 327 May 10/07 328 May 10/07 329 May 10/07 330 May 10/07 331 May 10/07 332 May 10/07 333 May 10/07 334 Blank 335 May 10/07 336 Blank 337 May 10/07 338 Blank 339 May 10/07 340 Blank 341 May 10/07 342 Blank 343 May 10/07 344 Blank 345 May 10/07 346 Blank 347 May 10/07 348 Blank 349 May 10/07 350 May 10/07 351 May 10/07 352 Blank Maintenance Practices 401 May 10/07

402 Blank Servicing 501 May 10/07 502 Blank Removal/Installation 601 May 10/07 602 May 10/07 Cleaning/Painting 701 May 10/07 702 Blank Approved Repairs 801 May 10/07

802 Blank Configuration Selection 901 May 10/07

902 May 10/07 903 May 10/07 904 May 10/07 905 May 10/07 906 May 10/07 907 May 10/07 908 May 10/07 909 May 10/07 910 May 10/07 911 May 10/07 912 May 10/07 913 May 10/07 914 May 10/07 915 May 10/07 916 May 10/07

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LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

Configuration Selection 917 May 10/07

(cont'd) 918 May 10/07 919 May 10/07 920 May 10/07 921 May 10/07 922 May 10/07 923 May 10/07 924 May 10/07 925 May 10/07 926 May 10/07 927 May 10/07 928 May 10/07 929 May 10/07 930 May 10/07 931 May 10/07 932 May 10/07 933 May 10/07 934 May 10/07 935 May 10/07 936 May 10/07 937 May 10/07 938 May 10/07 939 May 10/07 940 May 10/07 941 May 10/07 942 May 10/07 943 May 10/07 944 May 10/07 945 May 10/07 946 May 10/07 947 May 10/07 948 May 10/07 949 May 10/07 950 May 10/07 951 May 10/07 952 May 10/07 953 May 10/07 954 May 10/07 955 May 10/07 956 May 10/07 957 May 10/07 958 May 10/07 959 May 10/07 960 May 10/07 961 May 10/07 962 May 10/07 963 May 10/07 964 May 10/07 965 May 10/07 966 May 10/07 967 May 10/07 968 May 10/07 969 May 10/07 970 May 10/07 971 May 10/07 972 May 10/07 973 May 10/07 974 May 10/07 975 May 10/07 976 May 10/07 977 May 10/07 978 May 10/07 979 May 10/07 980 May 10/07 981 May 10/07 982 May 10/07 983 May 10/07 984 May 10/07 985 May 10/07 986 May 10/07 Data Loader Unit (DLU) 1001 May 10/07

1002 May 10/07 1003 May 10/07 1004 May 10/07 1005 May 10/07 1006 May 10/07 1007 May 10/07 1008 Blank

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LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

Appendix A T-A1 May 10/07

T-A2 Blank TC-A1 May 10/07 TC-A2 Blank A-1 May 10/07 A-2 May 10/07 A-3 May 10/07 A-4 May 10/07 A-5 May 10/07 A-6 May 10/07 A-7 May 10/07 A-8 May 10/07 A-9 May 10/07 A-10 May 10/07 A-11 May 10/07 A-12 May 10/07 A-13 May 10/07 A-14 May 10/07 A-15 May 10/07 A-16 May 10/07 A-17 May 10/07 A-18 May 10/07 A-19 May 10/07 A-20 May 10/07 A-21 May 10/07 A-22 May 10/07 A-23 May 10/07 A-24 May 10/07 Appendix B T-B1 May 10/07 T-B2 Blank TC-B1 May 10/07 TC-B2 Blank B-1 May 10/07 B-2 May 10/07 B-3 May 10/07 B-4 May 10/07 B-5 May 10/07 B-6 May 10/07 B-7 May 10/07 B-8 May 10/07 B-9 May 10/07 B-10 May 10/07 B-11 May 10/07 B-12 May 10/07 B-13 May 10/07 B-14 May 10/07 B-15 May 10/07 B-16 May 10/07 B-17 May 10/07 B-18 May 10/07 B-19 May 10/07 B-20 May 10/07 B-21 May 10/07 B-22 Blank Appendix C T-C1 May 10/07 T-C2 Blank TC-C1 May 10/07 TC-C2 Blank C-1 May 10/07 C-2 May 10/07 C-3 May 10/07 C-4 May 10/07 C-5 May 10/07 C-6 May 10/07 C-7 May 10/07 C-8 May 10/07 C-9 May 10/07 C-10 May 10/07 C-11 May 10/07 C-12 May 10/07 C-13 May 10/07 C-14 May 10/07 C-15 May 10/07 C-16 May 10/07

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RECORD OF REVISIONS

date inserted and initial.

ASSIGNED TO (JOB TITLE) LOCATION

REV. NO. REVISION DATE INSERTION DATE BY REV. NO. REVISION DATE INSERTION DATE BY

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SERVICE BULLETIN LIST

SERVICE BULLETIN NO. SUBJECT MANUAL REVISION NUMBER MANUAL REVISION DATE

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ELECTROSTATIC DISCHARGE

This equipment contains components which are sensitive to damage by electrostatic discharge (ESD). Modules containing components sensitive to ESD are identified on the module by a label bearing the following marking.

"CAUTION-THIS EQUIPMENT CON-TA I N S PA R T S S E N S I T I V E T O D A M A G E B Y E L E C T R O S TAT I C D I S C H A R G E ( E S D ) . U S E E S D PRECAUTIONARY PROCEDURES WHEN TOUCHING, REMOVING, OR INSERTING PARTS OR ASSEMBLIES."

When these modules have to be replaced and returned for service the following precautions should be observed:

1. Handle the modules as little as possible. Do not touch the leads, pin or tracks while handling. 2. Keep spare modules in the ESD protective packing until ready for use.

3. Discharge static before handling modules (removal or replacement) by touching a grounded metallic surface such as rack or cabinet hardware. Use of wrist strap grounded through a one megohm resistor is preferred when handling modules. (This ground should be the same as the equipment ground). 4. Do not slide static-sensitive modules over any surface.

5. Clothing must not come in contact with components or assemblies. Short sleeves are preferred; if long sleeves are worn then should be rolled up.

6. Package parts properly for storage or transportation. Modules which are removed from the equipment should be placed into ESD protective packing immediately. Do not place any paper, card or other plastic inside the ESD protective packing.

7. When packing these modules for storage or transportation, keep them in the bag. Fold over and seal the mouth of the bag to keep out any static generating packing material (eg, foamed polystyrene). Pack around the bag firmly to prevent motion which could generate static.

WARRANTY

In the case of any ESD sensitive module bearing the marking described above which is received by CMC not in ESD protective packing, other than the initially reported fault, all warranty, present or future, is voided for failure related to ESD sensitive components.

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Monitoring

AC - Alternative Current

A/C - Aircraft

ACARS - Aircraft Communications Addressing and Reporting

System ACCUR - Accuracy

ACMS - Aircraft Condition Monitoring System

ACT - Active

ADC - Air Data Computer

ADF - Automatic Direction Finder AFCS - Automatic Flight Control System AFM - Aircraft Flight Manual

AGL - Above Ground Level

AHCAS - Advanced Helicopter Cocpkpit Avionics System

AHRS - Attitude and Heading Reference

System

ALT - Altitude

AMLCD - Active Matrix Liquid Crystal Display

AMU - Audio Management Unit ANP - Actual Navigation Performance ANS - Answer (HCS text message) APIRS - Aircraft Piloting Inertial Reference

System

APPR - Approach

APU - Auxiliary Power Unit

ARINC - Aeronautical Radio Incorporated

ARR - Arrival

ATC - Air Traffic Control

ATP - Acceptance Test Procedure AWG - American Wire Gauge BCD - Binary Coded Decimal BIT - Built-In-Test

BITE - Built-In-Test Equipment

BNR - BiNaRy

BRT - Brightness

BUF - Buffer

CDU - Control Display Unit CFG - Configuration CHAR - Character CHN/CHAN - Channel CLR - Clear CMC - CMC Electronics Inc. COMM - Communication COORD - Coordinate CP - Control Panel

CPU - Central Processor Unit CRC - Cyclic Redundant Check CRP - Centrale Reference Primaire

DA - Drift Angle dB - deciBel DBASE - Database DC - Direct Current DEGR - Degradation DEP - Departure DIG - Digital DISC - Discrete

DITS - Digital Information Transfer System

DLU - Data Loader Unit DMAP - Digital Map

DME - Distance Measurement Equipment

DOP - Discrete Output

DR - Dead Reckoning

DTK - Desired Track DTW - Distance To Waypoint

DTO - Direct-To

DVS - Doppler Velocity Sensor EADI - Electronics Atttiude Display

Indicator

ECD - Eurocopter Deutschland EFIS - Electronic Flight Instrumentation

System

EGI - Embedded GPS/INS

EHSI - Electronic Horizontal Situation Indicator

EICAS - Engine Instrument Crew Alerting System

EIS - Electrical Instrument System EMI - ElectroMagnetic Integration EOT - End Of Transmission

ELT - Emergency Locator Transmitter

ERR - Error

ESD - Electro Static Discharge ETA - Estimated Time of Arrival

EQP - Equipment

EXEC - Execute

FAA - Federal Aviation Authority FAF - Final Approach Fix

FC - Fuel Computer

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LIST OF STANDARD AND NONSTANDARD ABBREVIATIONS (cont’d)

FMC - Flight Management Computer FMS - Flight Management System FPU - Floating Point unit

FREQ - Frequency

FTE - Fliht Technical Error

GAMA - General Aviation Manufucturers Association

GDOP - Geometric Dilution of Precision GMT - Greenwich Mean Time

GND - Ground

GNSSU - Global Navigation System Sensor Unit

GPP - Gessellschaft Fur Prozessrechner Programmierung mbH ( German company that makes HCS) GPS - Global Positioning System GPU - Ground Power unit

G/S - Ground Speed

GS - Glide Slope

GSM - Global System for Mobile Telecommunication

HCS - Helicopter Communication System

HDG - Heading

HDOP - Horizontal Dilution of Precision

HF - High Frequency

HFOM - Horizontal Figure Of Merit HIL - Horizontal Integration Limit HSI - Horizontal Situation Indicator H/W - Hardware

IDT - Ident

I/F - Interface

IFDS - Integrated Flight Display System IFR - Instrument Flight Regulations

I/O - Input/Output

I/P - Input

ILS - Instrument Landing System

INIT - Initial

INS - Inertial Navigation System

INT - Integrity

IRS - Inertial Reference Sensor JAA - Joint Aeronautical Authority

KG - Kilograms

KT(s) - Knot(s)

L - Left

LAT - Latitude

LB - Pound

LCD - Liquid Crystal Display LEGCHG - Leg Change

LNAV - Lateral Navigation LONG - Longitude

LRU - Line Replaceable Unit LSK - Line Select Key LSW - Least Significant Word

MAG - Magnetic

MCDU - Multipurpose Control Display Unit MLS - Microwave Landing System

MOD - Modified

MSL - Mean Sea Level MSW - Mist Signficant Word

MSG - Message

MTBF - Mean Time Between Failure N/A - Not Applicable NAS - National Air Space

NAV - NAVigation

NMI - Nautical Miles

NMS - Navigation Management System NPA - Non-Precision Approach

NVG - Night Vision Goggle OEI - One Engine Inoperative

OFST - Offset

OP - Operational

O/P - Output

PDL - Portable Data Loader PDP - Packet Data Protocol PFD - Primary Field Display

PG - Page

PLS - Personnel Locator System

P/N - Part Number

POF - Phase Of Flight

POS - Position

PREDEF - Predefined PREV - Previous PROG - Progress

PROM - Programmable Read Only

Memory

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RAIM - Receiver Autonomous Integrity Monitoring

REC - Recorder

REF - Reference

REPE - Repeater

RF - Radio Frequency

RMS - Radio Management System RNP - Required Navigation Performance RTCA - Radio Technical Commission for

Aeronautics

RTE - Route

RTN - Return

RX - Receive

SDI - Source Data Information SMC - System Management Computer

SP - Space

SQK - Squawk

SSM - Sign/Status Matrix

STBY - Standby

TACAN - TACtical Air Navigation system TAS - True Air Speed

TAWS - Terrain Awareness and Warning Systems

TCAS - Traffic Alert Collision Avoidance System

TCN - TACAN

TDN - Transition DowN TK - Track

TKE - Track Angle Error TOGA - Take Off Go Around

TRK - Track

TSO - Technical Standard Order

TX - Transmit

TX1 - V/UHF radio #1 transmitting TX2 - V/UHF radio #2 transmitting UHF - Ultra High Frequency UTC - Universal Time Coordinate UTM - Universal Transverse Mercator VAR - Variation

VDOP - Vertical Dilution of Precision

VER - Vertical

VFR - Visual Flight Regulations VHF - Very High Frequency

VOR - VHF Omni-directional Radio range VSI - Vertical Situation Indicator

VUHF - Very & Ultra High Frequency

WOW - Weight On Wheel

WPT - Waypoint

WXR - Weather Radar System XMIT - Transmit

XPDR - ATC Transponder XTK - Cross Track

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Section Title Page SECTION I DESCRIPTION AND OPERATION ... 1

1. GENERAL... 1 A. Purpose of Manual... 1 B. Function of Equipment... 1 C. Reliability and Maintainability... 1 D. External Interface Capabilities ... 2 E. Description of the Primary Modes of Navigation ... 4 F. Annunciators and Keys... 7 G. Related Publications ... 18 H. Equipment Identification ... 19 2. EQUIPMENT SPECIFICATIONS ... 21 3. DIGITAL EQUIPMENT... 33 A. Aircraft Condition Monitoring System (ACMS) ... 34 B. Air Data Computer (ARINC 429) ... 35 C. Air Data Computer (ARINC 575) ... 36 D. Attitude and Heading Reference System (ARINC 429)... 36 E. Automatic Flight Control System ... 37 F. Checker (ARINC 429)... 38 G. Collins DME-442/DME-4000 Distance Measuring Equipment Receiver (ARINC

429)... 38 H. Collins 700 Distance Measuring Equipment Receiver (ARINC 429)... 39 I. Chelton DM-441B Distance Measuring Equipment Receiver (ARINC ... 40 J. ARINC 615 Data Loader Unit (ARINC 429)... 40 K. GAMA EFIS Interface Description ... 40 L. IFDS and AHCAS/AHCAS2 EFIS Interface Description ... 50 M. ARINC 702 EFIS Interface Description ... 54 N. Fuel Computer ... 62 O. GPS Sensor ... 62 P. Flight Recorder ... 67 Q. Repeater ... 67 R. System Management Computer ... 68 S. Chelton VN-411B, Collins VIR-432, Collins NAV-4500 NAV (VOR/ILS) RECEIVER (ARINC 429) ... 68 T. VOR RECEIVER (ARINC 579) ... 69 U. X-FMS for cross-talk (ARINC 429) ... 69 V. Emergency Locator Transmitter ARTEX ELT-110-406HM/GPS (ARINC 429) ... 70 W. Bendix King MST67A ATC Transponder (ARINC 429) ... 70 X. Collins TDR 94D ATC Transponder (ARINC 429)... 71 Y. Chelton VC-401B VHF COM radio (ARINC 429) ... 72 Z. Chelton VC-401C VHF Comm (ARINC 429) ... 72 AA. Chelton ADF-431B, Collins ADF-462 ADF (ARINC 429) ... 73 BB. Marconi Selenia SRT-651/N-A V/UHF radio (ARINC 429)... 73 CC. TEAM Audio Management Unit AMU (ARINC 429) ... 74 DD. Aircraft Piloting Inertial Reference System (APIRS SFIM) ... 75 EE. Digital Map System... 75 FF. Data Concentrator ... 77

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TABLE OF CONTENTS (cont'd)

Section Title Page

GG. Radio Altimeter (ARINC 429)... 78 HH. LN-100GT Embedded GPS/INS Sensor (ARINC 429)... 78 II. SIGMA50H Embedded GPS/INS Sensor (ARINC 429) ... 80 JJ. Weather Radar (ARINC 429)... 82 KK. Doppler Velocity Sensor DVS (ARINC 429) ... 82 LL. Personnel Locator System (ARINC 429)... 83 MM.Thomson NC-12B TACAN (ARINC 429) ... 84 NN. Data Loader unit Targa (RS-422) ... 84 OO. Helicopter Communication System (HCS) Software Protocol (RS-422) Future

Growth ... 85 PP. Radio Interface Box (RIB) equipment (RS-422) Future Growth ... 88 QQ. Inertial Reference System (ARINC 429)... 89

SECTION II INSTALLATION... 101

1. GENERAL... 101 2. EQUIPMENT LOCATION ... 101 A. General ... 101 B. Location of the FMS... 101 C. Selection and location of the GPS receiver and related GPS Antenna... 101 D. Active Antenna Installations (CMA-3012 and CMA-3024) ... 103 3. INTERWIRING AND OUTLINE DRAWING ... 105 4. HARNESS VOLTAGE CHECKOUT ... 117 5. EGI INSTALLATION ... 117 6. DOPPLER INSTALLATION ... 118 7. ANNUNCIATOR INSTALLATION... 119

SECTION III POST-INSTALLATION TEST ... 201

1. GENERAL... 201 2. CONDITIONS ... 201 3. SYSTEM TEST PREPARATION ... 201 A. Built-In Test... 201 B. Front panel brightness control ... 203 C. Configuration Selection... 204 D. Navigation Database Loading... 204 4. PROCEDURE ... 205 A. Power On ... 205 B. Annunciator Test and RADIO Page... 205 C. Heading Input Verification... 208 D. True Airspeed Verification ... 209 E. GPS Sensor Unit ... 210 F. DME Status... 215 G. VOR/DME/TCN Status ... 216 H. Radio Test... 217 I. Discrete Output Test... 217 J. EFIS Interface Test... 218 K. Electromagnetic Compatibility Test ... 221 L. IRS to FMS to IRS Ground Check ... 225

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Section Title Page

SECTION IV FLIGHT LINE TEST/TROUBLESHOOTING ... 301

1. GENERAL... 301 2. ALERT MESSAGES ... 301 3. TROUBLESHOOTING PHILOSOPHY ... 301 4. FAULT LOG ... 302 A. SYSTEM ALERT MESSAGES ... 302 B. MAINTENANCE ALERT MESSAGES... 312 C. MAINTENANCE ADVISORY MESSAGES... 314 D. STATUS ADVISORY MESSAGES... 321

SECTION V MAINTENANCE PRACTICES ... 401

1. GENERAL... 401

SECTION VI SERVICING ... 501

1. GENERAL... 501

SECTION VII REMOVAL/INSTALLATION ... 601

1. GENERAL... 601 2. REMOVAL PROCEDURES ... 601 A. General ... 601 B. Flight Management System (FMS) ... 601 3. PRE-INSTALLATION INSPECTION... 601 4. INSTALLATION OF UNITS... 601 5. POST-INSTALLATION INSPECTION ... 602 6. POST-INSTALLATION TESTS... 602

SECTION VIII CLEANING/PAINTING... 701

1. GENERAL... 701 A. Cleaning and Painting of Surfaces ... 701 B. Display Glass Cleaning... 701

SECTION IX APPROVED REPAIRS ... 801

1. GENERAL... 801

SECTION X CONFIGURATION SELECTION... 901

1. GENERAL... 901 2. CONFIGURATION CAPABILITIES OF THE CMA-9000: FOUR CONFIGURATIONS901 3. FMS Configuration Selection Procedure ... 901 A. FMS Configuration Procedure Using Configuration Diskette ... 903 B. Manual FMS Configuration Procedure ... 904

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TABLE OF CONTENTS (cont'd)

Section Title Page

SECTION XI DATA LOADER UNIT (DLU) ... 1001

1. GENERAL... 1001 2. DATA LOADER DESCRIPTION... 1001 A. ARINC 615 Data Loader Unit (DLU)... 1001 B. Loading a database or FMS configuration with an ARINC 615 DLU ... 1003 3. RS422 DLU... 1004 A. Loading a database or FMS configuration with the RS 422 DLU... 1004 B. Saving the User database or the FMS configuration into the RS422 DLU ... 1006

APPENDIX A Ground Functional Test Procedures for CMC Electronics Inc.

CMA-9000 S/W 169-614876-0XX ... T-A APPENDIX B Flight Functional Test Procedures & Report for CMC Electronics Inc.

CMA-9000 S/W 169-614876-0XX ... T-B APPENDIX C Procedures for Obtaining Civil Authorities Approval - IFR/VFR Operations For

Follow-on FMS/GPS Equipment Installations CMC Electronics Inc.

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LIST OF FIGURES

Figure Title Page

Figure 1 CMA-9000 Flight Management System variation 100-601951-030 ... 3 Figure 2A Annunciators and Keys of CMA-9000 variation 100-601951-030... 8 Figure 2B Annunciators and Keys of CMA-9000 variation 100-601951-VAR 001/101/301 ... 9 Figure 2C Annunciators and Keys of CMA-9000 variation 100-601951-VAR 002/003/005/102/103/302/30310 Figure 2D Annunciators and Keys of CMA-9000 variation 100-601951-VAR 040 ... 11 Figure 2E Annunciators and Keys of CMA-9000 variation 100-601951-VAR 050 ... 12 Figure 2F Annunciators and Keys (Sheet 1 of 5)... 13 Figure 3 Related Publications ... 18 Figure 5 Equipment Specification (Sheet 1 of 3) ... 21 Figure 6 Physical Specification ... 24 Figure 7 Environmental Specification (Sheet 1 of 2) ... 25 Figure 8A Single Basic System with Radio Tuning... 27 Figure 8B Single Basic System without Radio Tuning... 28 Figure 8C Dual System ... 29 Figure 8D System Block Diagram Dual System ... 30 Figure 8E Dual FMS installation with radio tuning and suggested pins allocation (courtesy of Pilatus Aircraft Switzerland) ... 31 Figure 9 FMS Viewing Envelope... 32 Figure 10 Triple FMS/Triple-LTN-92 IRS Interconnections ... 93 Figure 11 FMU to LTN-92 INU Source Select (All Relays Shown Energized) ... 94 Figure 12 Heading Sources for Triple FMS/Triple LTN-92 IRS/Dual Compass Couplers ... 95 Figure 101A Typical CMA-9000 Location (for a helicopter)... 104 Figure 101B Typical CMA-9000 Location (for an aircraft) ... 104 Figure 102A CMA-9000 Outline Drawing... 105 Figure 102B CMA-9000 J1 Connector... 106 Figure 104 Interwiring Specifications (Sheet 1 of 5) ... 112 Figure 105 Input Wiring Checks for CMA-9000 hardware variation 100-601951-XXX... 117 Figure 201. Integral Lighting 5V Curve ... 204 Figure 202. Typical Map Mode Display... 220 Figure 203. Typical ARC Mode Display ... 220 Figure 204 EMC Matrix Chart ... 224 Figure 301 System Alert Messages (Sheet 1 of 10) ... 302 Figure 302 Maintenance Alert Messages (Sheet 1 of 2) ... 312 Figure 303 Maintenance Advisory Messages (Sheet 1 of 7) ... 314 Figure 304 Status Advisory Messages (Sheet 1 of 5) ... 321 Figure 305 Testing/Troubleshooting Flow Chart (Sheet 1 of 7)... 326 Figure 306 Maintenance Pages (Sheet 1 of 7) ... 333 Figure 307 Maintenance Test 1 ... 347 Figure 308 Maintenance Test 2 ... 347 Figure 309 Typical Full Rose Map Display (Sheet 1 of 2) ... 348 Figure 310 Typical ARC NAV Display... 349 Figure 311 Typical Plan Mode ... 350 Figure 312 Label 271 Maintenance Action FMS Status ... 351 Figure 901 FMS Configuration Pages (Sheet 1 of 60)... 909 Figure 902 Configuration Selections (Sheet 1 of 18)... 969

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LIST OF TABLES

Table Title Page

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DESCRIPTION AND OPERATION 1. GENERAL

A. Purpose of Manual

The purpose of this manual is to provide installation instructions and flight line maintenance for the 9000. Different hardware variations of the 9000 are available. Figure 1 illustrates CMA-9000 hardware variation 030. Figures 2 illustrates the other variations.

B. Function of Equipment

The CMA-9000 is a self-contained cockpit mounted radio and flight management system. It provides the user with a color display of moderate resolution for alphanumeric data and a keyboard for data entry, data editing, and system control. Its display, background lighting and annunciators are compatible with Night Vision Goggles (NVG) for use in a tactical environment.

The CMA-9000 contains ARINC 429, RS-422 RS232, and Discrete interfaces for integration with other avionics and communication systems for control and/or monitoring via the display and keyboard. The CMA-9000 can be used with an optional external Radio Interface Board (RIB) (Future Growth) to interface with analogue radios.

C. Reliability and Maintainability

The CMA-9000 exhibits a robust design in the environmental conditions specified in this document. System mean time between failures (MTBF) is 9,499 hours at 30° C ambient temperature in the airborne inhabited cargo (AIC) environment. In the airborne rotary wing (ARW) environment, system MTBF is 6,500 hours. The AMLCD Backlight Module is not considered in the MTBF calculations. It is noted that the CMA-9000 FMS is fitted with a lithium battery that is only used to maintain the real-time clock. Refer to Section VI, Servicing for Lamp and Battery replacement. The CMA-9000 incorporates provisions for Built-In-Test (BIT) of the installed equipment with no additional test equipment. The end-to-end test is capable of detecting faults with a 95% probability. The BIT monitors the integrity of the navigation database at least once every 15 minutes while powered, and announces any corruption of data.

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D. External Interface Capabilities

The CMA-9000 is capable of receiving information from external navigation sensors, including: • GPS Global Positioning System

• EGI Embedded GPS/INS*

• DME Distance Measuring Equipment • NAV VHF Omni-directional Radio range • ADF Automatic Direction Finder

• ADC Air Data Computer • DVS Doppler Velocity Sensor*

• AHRS Attitude Heading Reference System • APIRS Aircraft Piloting Inertial Reference System • TACAN TACtical Air Navigation system

• IRS Inertial Reference System

The CMA-9000 accepts true (EGI) or magnetic (AHRS or compass) heading inputs and True Air Speed (TAS), pressure or barometric corrected altitude from an ADC.

The CMA-9000 is capable of exchanging information with other external equipment such as XPDR (ATC Transponder), COM and V/UHF (radios), EHSI (Electronic Horizontal Situation Indicator), DMAP (Digital Map), PLS (Personnel Locator System),ACMS (Aircraft Condition Monitoring System), AMU (Audio Management Unit), Electronic Flight Instrument System (EFIS), Flight Data Recorder (REC), Weather Radar (WXR), Emergency Locator Transmitter (ELT) and FC (Fuel Computer). The FMS is configurable to operate with the equipment if installed.

The CMA-9000 is capable of transmitting and receiving information to/from external communication and navigation radios, including HF, VHF, UHF, VUHF, NAV, TACAN and ADF equipment when used with the optional external RIB unit (Future Growth). The CMA-9000 is also capable of receiving and transmitting information from other external equipment such as Data Loader Unit (DLU).

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0611007

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track-related reference frames for display to the pilot and for output to external aircraft display systems, including an Electronic Flight Instrument System (EFIS), EHSI (Electronic Horizontal Situation Indicator), or Digital Map Display System (DMAP).

The CMA-9000 outputs on the ARINC 429 interface suitably formatted lateral steering signals (roll command or heading error) for use by the Automatic Flight Control System (AFCS) for aircraft flight guidance in the horizontal plane. In addition the CMA-9000 is capable of generating output to drive an Aircraft Condition Monitoring System (ACMS) or a Flight Data Recorder (REC) for in flight recording of FMS information.

The FMS has the built-in capability to hold the following databases: navigation database, custom database, user database, radios tuning libraries, Fly Away and OEI cruise function parameters and a phone book. The above databases, the dimming curves (for external brightness dimming control), the unit configuration file and the magnetic variation model are updated as a CMA-9000 maintenance task via an ARINC 615 or Targa PDP/3-DOS DLU based on configuration. The unit software upgrades are updated as a CMA-9000 maintenance task via an ARINC 615 DLU or an RS-422 Xmodem loader. The pilot or maintenance crew may initiate the upload and download of the user database from the CMA-9000 pages. The databases that are handled by the FMS are configured to match the functions configured into the CMA-9000.

E. Description of the Primary Modes of Navigation

The CMA-9000 can be configured to one of two distinct modes: the civil mode and the military mode. Integrity monitoring and resulting consequences as required by TSO-C115b, AC20-130A, and DO-236A are the main differences between the two options.

When in the military navigation configuration option, the sensor navigation solutions will be assumed to have integrity unless proven otherwise. The navigation modes selection logic is geared to accuracy performance and the FMS will not necessarily force mode transitions based on integrity. Some integrity monitoring is nevertheless performed to raise alarms. The pilot is expected to consider navigation mode alarms and force navigation sensor selections if judged necessary. When in the civil navigation configuration option, the sensor navigation solutions will be assumed not to have integrity unless proven otherwise. The navigation modes selection logic is geared to safety (integrity) and the FMS may force mode transitions to remain in a navigation mode with integrity, thereby also preventing unnecessary alarms from being raised. This configuration option is intended to fully comply with TSO-C115, AC20-130A, and the integrity requirements of DO-236A. The CMA-9000 has several navigation modes. In sequence of priority, they are: Hybrid INS/GPS (military), GPS (civil), DME (civil), VOR/DME (civil) /TCN (military), Hybrid INS/DVS (military), Inertial (military), DVS (military), Kalman (civil) and Dead Reckoning (DR) (civil and military modes).

While in operation the CMA-9000 continuously computes the independent sensor positions. Each sensor output is monitored and compared against validity criteria. Any sensor which is declared as failed or has degraded sufficiently will automatically be deselected and will be restored to inventory only when restored to its criteria levels.

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GPS is the highest priority navigation mode of the FMS, and will be used when sufficient satellite coverage exists in the Phase Of Flight (POF) for which it is approved. The sensor continuously monitors the integrity of the satellites by using a Receiver Autonomous Integrity Monitor (RAIM).

The GPS will remain selected for navigation when it’s RAIM function computes a Horizontal Integrity Limit (HIL) value that is less than the GPS Integrity alert limit, which is a function of the current POF and Required Navigation Performance (RNP). When the HIL exceeds the alert limit, or if the GPS loses it’s RAIM function then the first secondary mode is selected. (2) Hybrid INS/GPS (EGI)

When an EGI is configured and the hybrid solution is available and valid, it will have priority over a non-certified GPS. When the hybrid solution becomes invalid but the GPS solution remains valid, the GPS solution will be used. When both the hybrid and GPS solutions become invalid but the INS solution is valid, it will not be used. The INS solution will only be used if any radio (DME/VOR) solution fails.

(3) DME/DME

DME is the secondary navigation mode and will be used in areas with sufficient DME coverage and for which the appropriate navigation database is installed. In this mode the FMS automatically tunes the on-board DME equipment to acquire distance data from up to six DME ground stations to determine aircraft position. The position is updated once every 10 seconds from measured sensor data. In addition a velocity rate and heading based update is computed at least once every second.

For DME sensors, the raw information received is compared with the predicted position and signals rejected if a discrepancy between the predicted position and DME slant range information exceeds the applicable tolerances.

(4) VOR/DME or VOR/DME/TACAN (if TACAN installed)

VOR/DME or VOR/DME/TACAN navigation is a reversionary navigation mode which is used in areas with sparse DME coverage where there are two or less VOR/DME/TACAN stations. This mode combines co-located DME distances and VOR bearing to determine position. The position is updated once every 10 seconds.

For VOR, DME or TACAN sensors, the raw information received is compared with the predicted position. Signals will be rejected if the discrepancy between the predicted position and DME/VOR or TACAN information exceeds the applicable tolerances.

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When a SAGEM SIGMA50H EGI is configured and the hybrid INS/DVS position and velocities provided by the EGI are available and valid, a hybrid INS/DVS navigation becomes available.

The FMS is computing an INS/DVS Navigation solution if all of the following are true:

a) The FMS receives valid INS status, INS/DVS position, velocity, and Quality Factor data (e.g. navigation labels are received with SSM NORMAL and values are within the required range) from the EGI sensor.

b) The INS status indicates Navigation mode. c) The INS is not declared Fail.

(6) Inertial

An Inertial navigation becomes available when an EGI is configured. In the INS navigation mode, the FMS is using the raw INS position and velocities provided by the EGI for navigation.

(7) Kalman Filter (Optional)

The CMA-9000 uses the Attitude and Heading Reference System (AHRS), and the GPS to provide a Kalman Filter navigation mode. In this mode, the primary navigation sensor is a GPS receiver. The AHRS is made into a dead-reckoning navigation system by emulating an INS navigator with a Kalman filter performing closed-loop GPS correction and alignment. Each sensor has specific performance characteristics and behavior which when combined provide for continuous navigation. The GPS receiver has bounded but noisy positioning and velocity errors and the GPS navigation solution is subject to the availability of the GPS satellite constellation. The AHRS exhibits steady error growth which when converted to a dead-reckoning system will yield steady error growth in the position and velocity navigation solution. However, the AHRS-based inertial navigation solution is always available.

The Kalman Filter provides the means to combine both navigation modes so that accurate navigation can continue for some time after the GPS is lost. The GPS and the AHRS are integrated via a Kalman Filter to continuously correct and align the AHRS-based inertial navigation solution, as if the inertial navigation solution were static at a known position point. The inertial navigation solution based on the AHRS measurements offer short-term navigation when the GPS or other approved navigation sensor cannot provide navigation data. The inertial navigator uses measurements from the AHRS and corrections from the Kalman Filter when GPS is available. Once GPS is lost, the AHRS inertial navigation solution is provided until its error bounds have been exceeded. The CMA-9000 calculates these drift errors and makes the navigation solution unavailable when this error exceeds a limit. When exceeding the error the number will be 300 m 95% of the time which is equivalent to 400 m 99% of the time. The Kalman navigation mode typically lasts about 3-4 minutes. The GPS LOST discrete output is activated as soon as GPS data is not available and the Master Caution discrete output is activated when the 300 meter limit is exceeded.

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The navigation mode based solely on Doppler is the less accurate FMS navigation mode based on sensor. It has priority over the Dead Reckoning mode only.

When a RDN85 or ANV353 DVS is configured, the CMA-9000 can compute a navigation solution if all of the following criteria is verified:

a) The FMS receives valid Doppler velocities and mode indication (e.g. labels are received with SSM NORMAL and values are within the required range) from the DVS;

b) The Doppler mode is LAND, SEA or CALM SEA for the RDN85 or in OPER for the ANV353 DVS;

c) The FMS receives valid heading data (e.g. labels are received with SSM NORMAL and values are within the required range) from an external sensor (refer to Section Heading Sources for possible heading inputs and selection logic).

The navigation solution computed by the CMA-9000 is based on the following data: • Doppler velocities (longitudinal, lateral and vertical)

• FMS System Selected Attitude (pitch and roll) • FMS System Selected Heading

(9) Dead Reckoning (DR)

When the external sensor data inputs become insufficient to maintain the normal navigation modes, the FMS reverts to the dead reckoning mode of navigation. The FMS must now rely on the last known aircraft position, combined with heading and TAS inputs, and the last valid computed wind, for its aircraft position calculation. Prolonged DR operation will result in decreased position accuracy. Alerts are provided when the estimated position accuracy exceeds the requirements for each phase of flight.

The FMS will automatically recover its normal modes of operation and position accuracy upon restoration of the external sensor inputs.

F. Annunciators and Keys

The FMS contains a full alphanumeric keyboard with special function keys. There are six line select keys (LSK) on each side of the display area. The functions of the LSKs are specific to each screen page. Figure 2A thru 2D describes the annunciators and FMS keys.

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INIT DEP

REF RTE ARR RADIO TPDR SP MSG CLR BRT LEGS HOLD PROG EXEC

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INIT DEP

REF RTE ARR RADIO ANS SP FIX CLR BRT LEGS HOLD PROG EXEC

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INIT DEP

REF RTE ARR RADIO FUEL SP FIX CLR BRT LEGS HOLD PROG EXEC

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Figure 2C Annunciators and Keys of CMA-9000 variation 100-601951-VAR 002/003/005/102/103/302/303

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FAIL MSG RNP IND ATC

INIT DEP

REF RTE ARR

RADIO VNAV SP FIX CLR BRT LEGS HOLD PROG EXEC

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FAIL MSG RNP IND ATC

INIT DEP

REF RTE ARR

RADIO TACT VNAV

SP ATC CLR BRT LEGS HOLD PROG EXEC

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2A, 2B, 2C, 2D and 2E.

ITEM DESCRIPTION FUNCTION

1 LCD Display Screen Provides 14 lines of 24 characters. 2 FAIL Annunciator

(NVIS AMBER)

Illuminates at maximum brightness with the display blank upon detection of a FMS failure.

3 MSG Annunciator (NVIS AMBER)

Illuminates when a System Alert message appears in the scratchpad field of the FMS display. The annunciator stays illuminated as long as the condition causing the System Alert message remains, or until the message is acknowledged by pressing the CLR key, or until the System Alert message is viewed on the MESSAGE RECALL page accessed via the INIT REF key or the MSG key. New System Alert messages also cause illumination of the remote MSG annunciator on the instrument panel in the pilot's field of view (if installed). Any acknowledged alert message is available for recall on the MESSAGE RECALL page as long as the condition causing it remains.

4 POS Annunciator (NVIS AMBER)

Illuminates when system is in dead reckoning navigation mode.

5 OFST Annunciator (NVIS GREEN)

Illuminates during offset (parallel track) navigation. 6 NPA Annunciator

(NVIS GREEN)

Illuminates when Non-Precision Approach is initiated. 7 TX1 Annunciator - VAR 030

only

(NVIS GREEN)

Illuminates when the configured V/UHF unit #1 emits RF power (radio is transmitting).

GSM Annunciator

(NVIS GREEN)

Illuminates for incoming call on the GSM network. 8 TX2 Annunciator - VAR 030

only

(NVIS GREEN)

Illuminates when the configured V/UHF unit #2 emits RF power (radio is transmitting).

SMS Annunciator (NVIS GREEN)

Illuminates when the Short Message Service text message has been received.

9 LDR Sensor Detects ambient light conditions in order to perform auto-brightness control of display screen and annunciators. The brightness of the screen and annunciators of the FMS can also be controlled by an external unit (e.g. CLDU). This item is configurable. The LDR sensor is not functional when the brightness is controlled by the 0-5 VDC external source.

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ITEM DESCRIPTION FUNCTION

10 Line Select Keys (LSK) There are twelve LSKs on the FMS panel, six on either side of the display. LSKs are identified by their location from top to bottom of the screen and as left or right, e.g. LSK 1L, LSK 6R. Entry of data from the scratchpad into the selected field is accomplished by pressing the adjacent LSK which moves the data from the scratchpad to the selected field. Data entries are permitted only on lines adjacent to the LSKs. Data can also be duplicated from a data field into the scratchpad by pressing the LSK adjacent to the desired data line. Inward pointing arrow symbols indicate that an option may be selected in that field. Outward point arrow symbols indicate that a new page will be displayed when the adjacent LSK is pressed, or that an action will be initiated.

11 EXEC Annunciator (NVIS GREEN)

Illuminates when a modification to the active route is in process but has not been executed. When the EXEC annunciator is lit, the impact of the data displayed on the LEGS page may be reviewed on other FMS pages, except the PROGRESS pages, and may be made active for guidance of the aircraft by pressing the EXEC key.

12 EXEC Key Is used to accept modifications to the active route (flight plan) performed on the LEGS, RTE (route) or HOLD pages. Modifications to the active flight plan will turn on the EXEC annunciator and display in reverse video a MOD status in the page title line and also an ERASE prompt. When data entries have been made active (by pressing the EXEC key), the title MOD status will revert to ACT (active). Until the MOD status is made active, the FMS will continue to use the previous active data for navigation and guidance even though it is not displayed. Any modification can be erased (cancelled) prior to EXECution by pressing the ERASE LSK. 13 BRT Key When the internal brightness mode of the FMS is configured,

this key controls the brightness of the screen and annunciators. After an elapsed time of 5 seconds, the first press of this key will always increase brightness; each depression of the BRT key alternately brightens or dims the display. The brightness of the screen and annunciators of the FMS can also be controlled by an external unit (e.g. CLDU). This item is configurable. It is not functional when the brightness is controlled by the 0-5 VDC external source.

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ITEM DESCRIPTION FUNCTION

14 MSG Key - VAR 030 only

FIX Key

(all other variations)

Accesses the MESSAGE RECALL page for display of System Alert messages.

NOTE: This key can also be configured to act as a NEXT key to access successive MESSAGE RECALL

pages.

Provides access to FIX page for all fix and abeam waypoint functions.

NOTE: The MSG key provides access to the MSG RECALL page. This page provides flight crew awareness of any FMS ALERTS by displaying the active alert scratchpad messages. The MSG RECALL page can be accessed though other functions keys. Even though, this particular key can be software or hardware (e.g. different variations) configured to another purpose, CMC recommends to retain the MSG key as part of one of the front panel rapid page access keys.

15 CLR Key Clears one character to the left during scratchpad data entry. When pressed and held for more than 1 second, it clears the entire scratchpad. The CLR key also clears alert and advisory messages from the scratchpad. The DELETE message can be cleared by a single press of the CLR key. Pressing the CLR key with the scratchpad empty will display DELETE in the scratchpad. The delete process is completed by pressing the LSK next to the data to be removed.

16 PROG Key Accesses the PROGRESS pages for display of current flight and navigation status information.

NOTE: This key can also be configured to act as a NEXT key to access successive PROGRESS pages.

17 HOLD Key Provides access to the HOLD page for the definition of HOLDING procedures at a designated waypoint or present position.

NOTE: This key can also be configured to act as a NEXT key to access successive HOLD pages.

18 LEGS Key Displays LEGS pages containing detailed data concerning each leg of the flight plan.

NOTE: This key can also be configured to act as a NEXT key to access successive LEGS pages.

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ITEM DESCRIPTION FUNCTION

19 DEP ARR Key Provides access to the DEP/ARR page for the definition of departure and arrival procedures and runways.

NOTE: This key can also be configured to act as a NEXT key to access successive DEPARTURES or

ARRIVALS pages. 20 TPDR Key - VAR 030 only

ANS - VAR 001/101/301 only

FUEL - VAR

002/003/005/102/103/302/303 only

Provides access to the ATC radio control page. This page allows the pilot to control the operation of the ATC Transponder.

SMS annunciator active: displays the newest message of the short message service on its dedicated page.

GSM annunciator active: accepts the phone call when pressed the first time, hangs up when pressed a second time. Priority is given to GSM.

Provides a quick access function to Fuel estimation and status pages.

NOTE: This key can also be configured to act as a NEXT key to access successive pages, when applicable.

21 RTE Key Provides access to the ROUTE page for the definition of routes entered into the FMS.

NOTE: This key can also be configured to act as a NEXT key to access successive ROUTE pages.

22 RADIO Key Provides access to RADIO tuning functions.

NOTE: This key can also be configured to act as a NEXT key to access successive RADIO pages.

23 INIT REF Key Provides access to pages of data required for initialization and various categories of reference data.

NOTE: This key can also be configured to act as a NEXT key to access successive INIT REF pages.

24 SP Key Provides a "space" character for separation of words.

25 Plus-Minus [+/-] Key Pressing the [+/-] will first display the "-" (minus) symbol. Pressing it a second time will display the "+" (plus) symbol. 26 Slash (/) Key Separates data fields in scratchpad data entry.

27 Decimal (.) Key Provides decimal point for numeric data entries.

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ITEM DESCRIPTION FUNCTION

28 Alpha-Numeric Keyboard Allows entry of alpha-numeric data.

29 NEXT Key When multiple-page displays are indicated in the page title line, pressing the NEXT key advances the display to the next higher page number or to page 1 if presently on the last page.

30 PREV Key When multiple-page displays are indicated in the page title line, pressing the PREV key backs up the display to the previous page or to the last page if presently on page 1. 31 MENU Key Displays the system menu for access to other ARINC 739

subsystems connected to the CMA-9000. (ARINC 739 MCDU is a Future Growth capability of the CMA-9000) 32 MENU Annunciator

(NVIS GREEN)

Illuminates when a remote subsystem is connected (e.g. ARINC 739 MCDU) to the CMA-9000 and requires attention (Future Growth)

33 SQK_IDT - VAR 001/101/301 only

MARK (all other variations)

Provides a quick access function to Squawk ident of the active ATC transponder.

Provides access to the MARK-ONTOP page and stores the present position on this page and on the PREDEF WPT page.

Figure 2F Annunciators and Keys (Sheet 5 of 5)

NOTE: Variations in above figure are in reference to the 100-601951-0xx hardware part number.

NOTE: Items 16 to 19 and 20 to 23 already stated in description may also be configured to act as a NEXT key when displaying an applicable page.

e.g.: When this option is selected and a page like the LEGS 1/X page is displayed, pressing LEGS again will provide access to the second LEGS page (e.g. LEGS 2/X page).

NOTE: Items 14, 17, 20, 22 and 33 are software configurable:

• For hardware variation 030, the five push-button keys located on the second row of function keys

are labeled: RADIO, TPDR, MARK, HOLD and MSG as illustrated in Figure 2A.

• For hardware variation 001/101/301, the five push-button keys located on the second row of

function keys are labeled: RADIO, ANS, SQK/IDT, HOLD and MSG as illustrated in Figure 2B.

• For hardware variation 002/003/005/102/103/302/303, the five push-button keys located on the

second row of function keys are labeled: RADIO, TPDR, MARK, HOLD and MSG as illustrated in Figure 2C.

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G. Related Publications

The related publications are listed in Figure 3.

PUBLICATION NAME PUBLICATION NUMBER

Operators Manual for Flight Management System CMA-9000

Interface Specification for Flight Management System CMA-9000

Installation/Flight Line Manual for GNSSU CMA-3012

Component Maintenance Manual for GNSSU CMA-3012

Installation/Flight Line Manual for GNSSU CMA-3024

Targa PDP/3-DOS protocol

9000-GEN-0101 with appropriate software 930-600052-000 408-A14876-XXX 3012-GEN-0801A 924-990400-100 3012-GEN-1202 924-990445-000 3024-GEN-0801 929-600043-000 32001328 - Revision A

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H. Equipment Identification

The equipment identification is listed in Figure 4.

EQUIPMENT NOMENCLATURE NAME HW PART NUMBER SW PART NUMBER

PANEL TYPE REMARKS INTEGRAL

LIGHTING CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-030 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS green B RADIO, TPDR, MARK, HOLD, MSG keys 5 VDC sense see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-001 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS green B RADIO, ANS, SQK/IDT, HOLD, FIX keys 5 VDC sense see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-101/301 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS green B RADIO, ANS, SQK/IDT, HOLD, FIX keys 28 VDC power see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-002 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS Saturn Yellow RADIO, FUEL, MARK, HOLD, FIX keys 5 VDC sense see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-102/302 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS Saturn Yellow RADIO, FUEL, MARK, HOLD, FIX keys 28 VDC power see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-003/005 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS green B RADIO, FUEL, MARK, HOLD, FIX keys 5 VDC sense see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-103/303 Operational= 169-614876-001 Boot = 169-615065-X01 MIL-L-85762A Type I Class B NVIS green B RADIO, FUEL, MARK, HOLD, FIX keys 28 VDC power see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-301 Operational= 169-614876-001 Boot = 169-615065-X01

Non NVIS RADIO, ANS, SQK/IDT, HOLD, FIX keys 28 VDC power see note

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PANEL TYPE REMARKS INTEGRAL

LIGHTING CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-302 Operational= 169-614876-001 Boot = 169-615065-X01

Non NVIS RADIO, FUEL, MARK, HOLD, FIX keys 28 VDC power see note CMA-9000 Flight Management System (FMS) FMS: Note: variation supplied 100-601951-303 Operational= 169-614876-001 Boot = 169-615065-X01

Non NVIS RADIO, FUEL, MARK, HOLD, FIX keys 28 VDC power see note CMA-3024 Global Navigator System Sensor Unit (GNSSU MKII) GPS Note: not supplied 100-601944-0XX/1XX Operational = 169-614788-001 ARINC 743A - CMA-3012 Global Navigator System Sensor Unit (GNSSU MKI) GPS Note: not supplied 100-601600-201,302,405, 504,702 Operational = 169-613751-007,207,115,402, 305 ARINC 743A - Trimble TA-12 GPS Note: not supplied 24835-10 Operational = TA12-CX-0129 TA_12 - Honeywell Global Navigator System Sensor Unit (GNSSU MKII) GPS Note: not supplied HG2021GD0 3 (same as CMC 100-601944-0XX) Operational = 169-614788-001 ARINC 743 - Honeywell Global Navigator System Sensor Unit (GNSSU MKI) GPS Note: not supplied HG2021GD0 2 (same as CMC 100-601600-3XX) Operational = 169-613751-207 ARINC 743 - CMA-3112 GPS Sensor Module (embedded in the CMA-900 FMS) GPS/ FMS: Not supplied P/N 245-601 650-1XX or – 2XX Operational = 169-613850-5XX ARINC 743 -

Figure 4 Equipment Identification (Sheet 2 of 2)

NOTE: "Sense" means that the energy needed to illuminate the keyboard is retrieved from the FMS aircraft power 28VDC on pins J1-4/5/6/7.

"Power" means that the energy needed to illuminate the keyboard is retrieved from the Integral Lighting pins on pins J1-8/9/1.

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2. EQUIPMENT SPECIFICATIONS

Equipment specification of the CMA-9000 are listed in Figure 5. The interconnection of an integrated unit is illustrated in Figure 6 and is included as an aid to better understanding the relationship of the FMS to other aircraft systems.

CHARACTERISTIC SPECIFICATION APPLICABLE DOCUMENTS/

AEEC

ARINC 424 Navigation System Database

ARINC 429 Mark 33 Digital Information Transfer System (DITS) ARINC 545 Subsonic Air Data Computer System

ARINC 561 Air Transport Inertial Navigation Systems (INS) ARINC 565 Mark 3 Subsonic Air Data System

ARINC 610A Guidance for Use of Avionics Equipment and Software in Simulators ARINC 615 Airborne Computer High Speed Data Loader

ARINC 702A Advanced Flight Management Computer System (FMS) ARINC 704 Inertial Reference Systems

ARINC 716 Airborne VHF Communication Transceiver ARINC 739 Multi-Purpose Control and Display Unit ARINC 743A Airborne Global Positioning System Receiver ARINC 601 Control/Display Interfaces

FEDERAL AVIATION ADMINISTRATION (FAA)

TSO-C113 Airborne Multipurpose Electronic Displays; FAA Standard Orders TSO-C115b (See NOTE 1) Area Navigation Equipment using Multi-Sensor Inputs

NOTE 1: TSO-C115b (a)(1), with respect to RTCA DO-187 para 2.3, Vertical Navigation is not implemented.

TSO-C115b (a)(2)(xii), Standalone VOR/DME approaches are not implemented.

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CHARACTERISTIC SPECIFICATION

TSO-C129a (See NOTE 2) Airborne Supplemental Navigation Using Global Positioning System (GPS)

NOTE 2: TSO-C129a (a)(3)(xix), Vertical Navigation (VNAV) is not implemented.

TSO-C115b Area Navigation Equipment using Multi-Sensor Inputs

AC 20-130A Airworthiness Approval of Navigation or Flight Management Systems integrating Multiple Navigation Sensors

AC 20-138 Airworthiness Approval of Global Positioning System (GPS) Navigation Equipment for use as a VFR and IFR Supplemental Navigation System

AC 90-94 Guidelines for Using Global Positioning System Equipment for IFR En Route and Terminal Operations and for Non-Precision Instrument Approaches in the U.S. National Airspace System

RTCA/EUROCAE

DO-160E Environmental Conditions and Test Procedures for Airborne Equipment

DO-178B Software Considerations in Airborne Systems and Equipment Certification

DO-187A Minimum Operational Performance Standards for Airborne Area Navigation Equipment Using Multi-Sensor Inputs

DO-201A Standards for Aeronautical Information

DO-208 Minimum Operational Performance Standards for Airborne Supplemental Navigation Equipment Using Global Poaitioning System (GPS)

DO-212 Minimum Operational Performance Standards for Airborne Automatic Dependent Surveillance (ADS) Equipment

DO-217 MASP, DGNSS Instrument Approach System: SCAT-I

DO-236B/ED-75 Minimum Aviation System Performance Specification Required Navigation Performance for Area Navigation

DO-283A Minimum Operational Performance Standards for Required Navigation Performance for Area Navigation

ED-79 Certification Considerations for Highly-Integrated or Complex Aircraft Systems

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CHARACTERISTIC SPECIFICATION SAE

AMS2521A Reflection-Reducing Coatings for Instrument Glasses

ARP 1068B Flight Deck and Instrumentation, Display Criteria and Associated Controls for Transport Aircraft

ARP 4256 Design Objectives for Liquid Crystal Displays for Part 25 (Transport) Aircraft

ARP-4754/ED-79 Certification Considerations for Highly-Integrated or Complex Aircraft Systems

AS8034 Minimum Performance Standard for Airborne Multipurpose Electronic Displays

JAA (Joint Aeronautical Authority)

Leaflet No. 2 AMJ-20X2 - Advisory Material for the Airworthiness Approval of Navigation Systems for Use in European Airspace Designated for Basic RNAV Operations, 1 July 1996

Leaflet No. 3 Interim Guidance on GPS as a Supplementary Navigation System, 1 July 1996

INT/POL/27/29/1 Protection from the effects of HIRF, Issue 1, 01-10-96

TGL-10 (P-RNAV) Airworthiness and operational approval for Precision RNAV operations in designated european airspace

MILITARY SPECIFICATION

MS25212C (ASG) Control Panel Console Type, Aircraft Equipment, Basic Dimensions

MILITARY STANDARD

MIL-C-14806A Coating, Reflection Reducing, for Instrument Cover Glasses and Lighting Wedges

MIL-STD-810C Environmental Test Methods and Engineering Guidelines

MIL-M-13231C Markings

MIL-C-14806A Anti-Reflection Coating

MIL-L-85762A Lighting, Aircraft, Interior, Night Vision Imaging System (NVIS) Compatible

CMC

408-A14876-XXX Interface specification for the CMA-9000 FMS

ECD

SP L330 M0901 E01 EC135 NVG Cockpit, Issue C, 2nd Draft, Date