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FOLD BACK ……………………………………………………………………………………….......................................................................................................................................
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
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
Title
T-1 T-2
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List of Effective Pages
LEP-1 LEP-2 LEP-3 LEP-4 LEP-5 LEP-6
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Record of Revisions
RR-1 RR-2
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Service Bulletin List
SB-1 SB-2
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Electrostatic Discharge
ED-1 ED-2
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Abbreviations
INTRO-1 INTRO-2 INTRO-3 INTRO-4
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Table of Contents
TC-1 TC-2 TC-3 TC-4 TC-5 TC-6
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DATE May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07 May 10/07
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LIST OF EFFECTIVE PAGES SUBJECT Configuration Selection (cont'd)
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1001 1002 1003 1004 1005 1006 1007 1008
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SUBJECT
Appendix C
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B-17 B-18 B-19 B-20 B-21 B-22
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RECORD OF REVISIONS ASSIGNED TO (JOB TITLE)
REV. NO.
REVISION DATE
INSERTION DATE
On receipt of revisions, insert pages and record date inserted and initial. LOCATION
BY
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REVISION DATE
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SERVICE BULLETIN LIST SERVICE BULLETIN NO.
SUBJECT
MANUAL REVISION NUMBER
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MANUAL REVISION DATE
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FORWARD 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 CONTA 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 DISCHARGE (ESD). USE ESD 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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LIST OF STANDARD AND NONSTANDARD ABBREVIATIONS AAIM
-
ACCUR ACMS
-
ACT ADC ADF AFCS AFM AGL AHCAS
-
AHRS
-
ALT AMLCD
-
AMU ANP ANS APIRS
-
APPR APU ARINC ARR ATC ATP AWG
-
Aircraft Autonomous Integrity Monitoring Alternative Current Aircraft Aircraft Communications Addressing and Reporting System Accuracy Aircraft Condition Monitoring System Active Air Data Computer Automatic Direction Finder Automatic Flight Control System Aircraft Flight Manual Above Ground Level Advanced Helicopter Cocpkpit Avionics System Attitude and Heading Reference System Altitude Active Matrix Liquid Crystal Display Audio Management Unit Actual Navigation Performance Answer (HCS text message) Aircraft Piloting Inertial Reference System Approach Auxiliary Power Unit Aeronautical Radio Incorporated Arrival Air Traffic Control Acceptance Test Procedure American Wire Gauge
Control Display Unit Configuration Character Channel Clear CMC Electronics Inc. Communication Coordinate
CP CPU CRC CRP
-
Control Panel Central Processor Unit Cyclic Redundant Check Centrale Reference Primaire
DA dB DBASE DC DEGR DEP DIG DISC DITS
-
DLU DMAP DME
-
DOP DR DTK DTW DTO DVS
-
Drift Angle deciBel Database Direct Current Degradation Departure Digital Discrete Digital Information Transfer System Data Loader Unit Digital Map Distance Measurement Equipment Discrete Output Dead Reckoning Desired Track Distance To Waypoint Direct-To Doppler Velocity Sensor
EADI
-
ECD EFIS
-
EGI EHSI
-
EICAS
-
EIS EMI EOT ELT ERR ESD ETA EQP EXEC
-
Electronics Atttiude Display Indicator Eurocopter Deutschland Electronic Flight Instrumentation System Embedded GPS/INS Electronic Horizontal Situation Indicator Engine Instrument Crew Alerting System Electrical Instrument System ElectroMagnetic Integration End Of Transmission Emergency Locator Transmitter Error Electro Static Discharge Estimated Time of Arrival Equipment Execute
FAA FAF FC FLT
-
Federal Aviation Authority Final Approach Fix Fuel Computer Flight
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LIST OF STANDARD AND NONSTANDARD ABBREVIATIONS (cont’d) FMC FMS FPU FREQ FTE
-
Flight Management Computer Flight Management System Floating Point unit Frequency Fliht Technical Error
GAMA
-
GDOP GMT GND GNSSU
-
GPP
-
GPS GPU G/S GS GSM
-
General Aviation Manufucturers Association Geometric Dilution of Precision Greenwich Mean Time Ground Global Navigation System Sensor Unit Gessellschaft Fur Prozessrechner Programmierung mbH ( German company that makes HCS) Global Positioning System Ground Power unit Ground Speed Glide Slope Global System for Mobile Telecommunication
HCS
-
HDG HDOP HF HFOM HIL HSI H/W
-
Helicopter Communication System Heading Horizontal Dilution of Precision High Frequency Horizontal Figure Of Merit Horizontal Integration Limit Horizontal Situation Indicator Hardware
IDT I/F IFDS IFR I/O I/P ILS INIT INS INT IRS
-
Ident Interface Integrated Flight Display System Instrument Flight Regulations Input/Output Input Instrument Landing System Initial Inertial Navigation System Integrity Inertial Reference Sensor
JAA
-
Joint Aeronautical Authority
KG KT(s)
-
Kilograms Knot(s)
L LAT LB LCD LEGCHG LNAV LONG LRU LSK LSW
-
Left Latitude Pound Liquid Crystal Display Leg Change Lateral Navigation Longitude Line Replaceable Unit Line Select Key Least Significant Word
MAG MCDU MLS MOD MSL MSW MSG MTBF
-
Magnetic Multipurpose Control Display Unit Microwave Landing System Modified Mean Sea Level Mist Signficant Word Message Mean Time Between Failure
N/A NAS NAV NMI NMS NPA NVG
-
Not Applicable National Air Space NAVigation Nautical Miles Navigation Management System Non-Precision Approach Night Vision Goggle
Portable Data Loader Packet Data Protocol Primary Field Display Page Personnel Locator System Part Number Phase Of Flight Position Predefined Previous Progress Programmable Read Only Memory
QTY
-
Quantity
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LIST OF STANDARD AND NONSTANDARD ABBREVIATIONS (cont’d) R RAIM
-
REC REF REPE RF RMS RNP RTCA
-
RTE RTN RX
-
Right Receiver Autonomous Integrity Monitoring Recorder Reference Repeater Radio Frequency Radio Management System Required Navigation Performance Radio Technical Commission for Aeronautics Route Return Receive
SDI SMC SP SQK SSM STBY
-
Source Data Information System Management Computer Space Squawk Sign/Status Matrix Standby
TACAN TAS TAWS
-
TCAS
-
TCN TDN TK TKE TOGA TRK TSO TX TX1 TX2
-
TACtical Air Navigation system True Air Speed Terrain Awareness and Warning Systems Traffic Alert Collision Avoidance System TACAN Transition DowN Track Track Angle Error Take Off Go Around Track Technical Standard Order Transmit V/UHF radio #1 transmitting V/UHF radio #2 transmitting
UHF UTC UTM
-
Ultra High Frequency Universal Time Coordinate Universal Transverse Mercator
VAR VDOP VER VFR VHF VOR VSI VUHF
-
WOW WPT WXR
-
Weight On Wheel Waypoint Weather Radar System
XMIT XPDR XTK
-
Transmit ATC Transponder Cross Track
Variation Vertical Dilution of Precision Vertical Visual Flight Regulations Very High Frequency VHF Omni-directional Radio range Vertical Situation Indicator Very & Ultra High Frequency
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TABLE OF CONTENTS 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. HH. II. JJ. KK. LL. MM. NN. OO.
Radio Altimeter (ARINC 429)................................................................................. 78 LN-100GT Embedded GPS/INS Sensor (ARINC 429).......................................... 78 SIGMA50H Embedded GPS/INS Sensor (ARINC 429) ........................................ 80 Weather Radar (ARINC 429)................................................................................. 82 Doppler Velocity Sensor DVS (ARINC 429) .......................................................... 82 Personnel Locator System (ARINC 429).............................................................. 83 Thomson NC-12B TACAN (ARINC 429) ............................................................... 84 Data Loader unit Targa (RS-422) .......................................................................... 84 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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TABLE OF CONTENTS (cont'd) Section
Title
Page
SECTION IV FLIGHT LINE TEST/TROUBLESHOOTING .......................................................................... 301 1. 2. 3. 4.
GENERAL.................................................................................................................... 301 ALERT MESSAGES .................................................................................................... 301 TROUBLESHOOTING PHILOSOPHY ........................................................................ 301 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 APPENDIX B APPENDIX C
Ground Functional Test Procedures for CMC Electronics Inc. CMA-9000 S/W 169-614876-0XX ................................................................................. T-A Flight Functional Test Procedures & Report for CMC Electronics Inc. CMA-9000 S/W 169-614876-0XX ................................................................................. T-B Procedures for Obtaining Civil Authorities Approval - IFR/VFR Operations For Follow-on FMS/GPS Equipment Installations CMC Electronics Inc. CMA-9000 S/W 169-614876-0XX ................................................................................. T-C
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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
Table 1 ARINC 429 Equipment Supported by the CMA-9000......................................................................... 33
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SECTION I 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 CMA-9000. Different hardware variations of the CMA-9000 are available. Figure 1 illustrates CMA9000 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
Figure 1 CMA-9000 Flight Management System variation 100-601951-030
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Waypoint and computed navigation and guidance information is generated in both geographic and 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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(1)
Global Positioning System (GPS) (Option) 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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(5)
Hybrid INS/DVS 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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(8)
DVS 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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1
3
2
FAIL
5
4
MSG
POS
6
NPA
TX1
7
8
9
TX2
CMC ELECTRONICS
10
10
18 16 11
32
INIT REF
DEP ARR
RTE
RADIO TPDR
LEGS
PROG
EXEC
MARK HOLD
MSG
BRT
12
31
1
2
3
30
4
5
6
A
B
C
D
E
F
G
13
7
8
9
H
I
J
K
L
M
N
14
.
0
+/ -
O
P
Q
R
S
T
U
17
/
SP
V
W
X
Y
Z
CLR
29 28 27
26
25
24
23 22
21
20
33
19
15
0611006
Figure 2A Annunciators and Keys of CMA-9000 variation 100-601951-030
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FAIL
MSG
POS
NPA
GSM
SMS
CMC ELECTRONICS
INIT REF
RTE
DEP ARR
LEGS
PROG
EXEC
RADIO
ANS
SQK IDT
HOLD
FIX
BRT
1
2
3
4
5
6
A
B
C
D
E
F
G
7
8
9
H
I
J
K
L
M
N
.
0
+/ -
O
P
Q
R
S
T
U
/
SP
V
W
X
Y
Z
CLR 0610006
Figure 2B Annunciators and Keys of CMA-9000 variation 100-601951-VAR 001/101/301
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FAIL
MSG
POS
NPA
GSM
SMS
CMC ELECTRONICS
INIT REF
RTE
RADIO FUEL
DEP ARR
LEGS
MARK HOLD
PROG
EXEC
FIX
BRT
1
2
3
4
5
6
A
B
C
D
E
F
G
7
8
9
H
I
J
K
L
M
N
.
0
+/ -
O
P
Q
R
S
T
U
/
SP
V
W
X
Y
Z
CLR 0610007
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
CMC ELECTRONICS
INIT REF
RTE
DEP ARR
LEGS
PROG
EXEC
RADIO FMC
VNAV
HOLD
FIX
BRT
1
2
3
4
5
6
A
B
C
D
E
F
G
7
8
9
H
I
J
K
L
M
N
.
0
+/ -
O
P
Q
R
S
T
U
/
SP
V
W
X
Y
Z
CLR 0611003
Figure 2D Annunciators and Keys of CMA-9000 variation 100-601951-VAR 040
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FAIL
MSG
RNP
IND
ATC
CMC ELECTRONICS
INIT REF
RTE
DEP ARR
LEGS
PROG
EXEC
RADIO TACT
VNAV
HOLD
ATC
BRT
1
2
3
4
5
6
A
B
C
D
E
F
G
7
8
9
H
I
J
K
L
M
N
.
0
+/ -
O
P
Q
R
S
T
U
/
SP
V
W
X
Y
Z
CLR 0610005
Figure 2E Annunciators and Keys of CMA-9000 variation 100-601951-VAR 050
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The item numbers mentioned in the first column are used for referencing to annunciators and keys of Figures 2A, 2B, 2C, 2D and 2E. ITEM
DESCRIPTION
FUNCTION
1 2
LCD Display Screen FAIL Annunciator (NVIS AMBER)
Provides 14 lines of 24 characters. Illuminates at maximum brightness with the display blank upon detection of a FMS failure.
3
MSG Annunciator (NVIS AMBER)
4
POS Annunciator (NVIS AMBER) OFST Annunciator (NVIS GREEN) NPA Annunciator (NVIS GREEN) TX1 Annunciator - VAR 030 only (NVIS GREEN) GSM Annunciator (NVIS GREEN) TX2 Annunciator - VAR 030 only (NVIS GREEN) SMS Annunciator (NVIS GREEN)
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. Illuminates when system is in dead reckoning navigation mode. Illuminates during offset (parallel track) navigation.
5 6 7
8
9
LDR Sensor
Illuminates when Non-Precision Approach is initiated. Illuminates when the configured V/UHF unit #1 emits RF power (radio is transmitting). Illuminates for incoming call on the GSM network. Illuminates when the configured V/UHF unit #2 emits RF power (radio is transmitting). Illuminates when the Short Message Service text message has been received. Detects ambient light conditions in order to perform autobrightness 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.
Figure 2F Annunciators and Keys (Sheet 1 of 5)
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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. Figure 2F Annunciators and Keys (Sheet 2 of 5)
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ITEM 14
DESCRIPTION MSG Key - VAR 030 only
FUNCTION 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.
FIX Key (all other variations)
15
CLR Key
16
PROG Key
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. 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. 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
18
HOLD Key
LEGS 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. 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. Figure 2F Annunciators and Keys (Sheet 3 of 5)
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ITEM 19
DESCRIPTION DEP ARR Key
FUNCTION 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
Provides access to the ATC radio control page. This page allows the pilot to control the operation of the ATC Transponder.
ANS - VAR 001/101/301 only
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.
FUEL - VAR 002/003/005/102/103/302/303 only
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 25
SP Key Plus-Minus [+/-] Key
26
Slash (/) Key
Provides a "space" character for separation of words. Pressing the [+/-] will first display the "-" (minus) symbol. Pressing it a second time will display the "+" (plus) symbol. Separates data fields in scratchpad data entry.
27
Decimal (.) Key
Provides decimal point for numeric data entries. Figure 2F Annunciators and Keys (Sheet 4 of 5)
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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
Provides a quick access function to Squawk ident of the active ATC transponder.
MARK (all other variations)
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
9000-GEN-0101 with appropriate software 930-600052-000
Interface Specification for Flight Management System CMA-9000
408-A14876-XXX
Installation/Flight Line Manual for GNSSU CMA-3012
3012-GEN-0801A 924-990400-100
Component Maintenance Manual for GNSSU CMA-3012
3012-GEN-1202 924-990445-000
Installation/Flight Line Manual for GNSSU CMA-3024
3024-GEN-0801 929-600043-000
Targa PDP/3-DOS protocol
32001328 - Revision A Figure 3 Related Publications
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H.
Equipment Identification The equipment identification is listed in Figure 4.
EQUIPMENT NOMENCLATURE CMA-9000 Flight Management System (FMS)
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
EQUIPMENT NOMENCLATURE CMA-9000 Flight Management System (FMS)
CMA-9000 Flight Management System (FMS)
CMA-3024 Global Navigator System Sensor Unit (GNSSU MKII) CMA-3012 Global Navigator System Sensor Unit (GNSSU MKI) Trimble TA-12
Honeywell Global Navigator System Sensor Unit (GNSSU MKII)
NAME FMS: Note: variation supplied FMS: Note: variation supplied GPS Note: not supplied GPS Note: not supplied GPS Note: not supplied GPS Note: not supplied
Honeywell Global Navigator System Sensor Unit (GNSSU MKI)
GPS
CMA-3112 GPS Sensor Module (embedded in the CMA-900 FMS)
GPS/ FMS:
Note: not supplied
Not supplied
HW PART NUMBER 100-601951302
SW PART NUMBER Operational= 169-614876-001 Boot = 169615065-X01
PANEL TYPE
100-601951303
Operational= 169-614876-001 Boot = 169615065-X01
100-6019440XX/1XX
Operational = 169-614788-001
100-601600201,302,405, 504,702
Operational = 169-613751007,207,115,402, 305
ARINC 743A
-
24835-10
Operational = TA12-CX-0129
TA_12
-
HG2021GD0 3 (same as CMC 100601944-0XX) HG2021GD0 2 (same as CMC 100601600-3XX) P/N 245-601 650-1XX or – 2XX
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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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
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
APPLICABLE DOCUMENTS/ AEEC ARINC 424
SPECIFICATION
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 TSO-C115b (See NOTE 1)
Airborne Multipurpose Electronic Displays; FAA Standard Orders 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.
Figure 5 Equipment Specification (Sheet 1 of 3)
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
CHARACTERISTIC
SPECIFICATION
TSO-C129a (See NOTE 2)
TSO-C115b AC 20-130A AC 20-138
AC 90-94
Airborne Supplemental Navigation Using Global Positioning System (GPS) NOTE 2: TSO-C129a (a)(3)(xix), Vertical Navigation (VNAV) is not implemented. Area Navigation Equipment using Multi-Sensor Inputs Airworthiness Approval of Navigation or Flight Management Systems integrating Multiple Navigation Sensors Airworthiness Approval of Global Positioning System (GPS) Navigation Equipment for use as a VFR and IFR Supplemental Navigation System 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 Standards for Aeronautical Information Minimum Operational Performance Standards for Airborne Supplemental Navigation Equipment Using Global Poaitioning System (GPS)
Minimum Aviation System Performance Specification Required Navigation Performance for Area Navigation Minimum Operational Performance Standards for Required Navigation Performance for Area Navigation
DO-283A ED-79
Certification Considerations for Highly-Integrated or Complex Aircraft Systems Figure 5 Equipment Specification (Sheet 2 of 3)
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
CHARACTERISTIC
SPECIFICATION
SAE AMS2521A
Reflection-Reducing Coatings for Instrument Glasses
ARP 1068B
Flight Deck and Instrumentation, Display Criteria and Associated Controls for Transport Aircraft Design Objectives for Liquid Crystal Displays for Part 25 (Transport) Aircraft Certification Considerations for Highly-Integrated or Complex Aircraft Systems
ARP 4256 ARP-4754/ED-79 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 Interim Guidance on GPS as a Supplementary Navigation System, 1 July 1996
Leaflet No. 3 INT/POL/27/29/1
Protection from the effects of HIRF, Issue 1, 01-10-96
TGL-10 (P-RNAV)
Airworthiness and operational approval operations in designated european airspace
for
Precision
RNAV
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 MIL-C-14806A MIL-L-85762A
Markings Anti-Reflection Coating 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 Figure 5 Equipment Specification (Sheet 3 of 3)
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
PHYSICAL PHYSICAL SPECIFICATION Size
Weight
SPECIFICATION 147.57 mm (5.81 in) depth, 146.05 mm (5.75 in) wide, 171.45 mm (6.75 in) high 3.86 kg (8.5 lb) maximum
ELECTRICAL SPECIFICATIONS POWER REQUIREMENTS Power Dissipation
Power Interrupt and BIT Timer
+28 Vdc, 45.0W typical at ambient, 75.0W typical during cold temperature startup Integral lighting, 12.0W maximum at 5.0 Vdc (included in power specified in the sentence above) NOTE: CMC recommends a 5 Amp circuit breaker for the +28 Vdc power supply source. DO-160E, Section 16.0 Cat. A 200msec power interrupt No interrupt < 0.200 seconds Warm start 0.200 < t < 7 or 0.200 < t < 90 seconds (depending on the configuration.) Cold start t > 7 seconds or t > 90 seconds (depending on the configuration.) BIT duration 10.0 seconds maximum (Cold start only) NOTE: The power interruption duration, when the aircraft is on the ground, is software configurable to either 7 or 90 seconds. Figure 6 Physical Specification
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
ENVIRONMENTAL ENVIRONMENTAL SPECIFICATIONS Temperature
SPECIFICATION In accordance with Radio Technical Commission for Aeronautics (RTCA) Document No. DO-160E. However, only major characteristics are listed. DO-160E Section 4.5 Cat. A4B4 Non-operating high temperature 85°C (185°F) Non-operating low temperature -55°C (-67°F) Operating high temperature (see Note below) see note below Operating low temperature -40°C(-40°F) Forced cooling air required None
Decompression
NOTE: - At +55 °C, fully operational (tested for 2 hours). - At +70°C, fully operational for 30 minutes. - At +70°C, fully operational for 2 hours if display is initially set at 80 fL. (Display may dim. This specification is made in order to protect the lamp at high temperature. DO-160E Section 4.6 Cat. A4B4 2h at 40,000 ft. 45,000 ft. in 15 sec.
Overpressure
DO-160E Section 4.6.2 At –15,000 ft, 10 minutes, off
Temperature Variation
DO-160E Section 5.0 Cat. B
Humidity
DO-160E Section 6.0 Cat. A
Shock
Explosion proofness Waterproofness
DO-160E Section 7.0 Cat. B: DO-160E Section 7.2 operational shock DO-160E Section 7.3.1 impulse test DO-160E Section 7.3.2 sustained test DO-160E Section 8.0 Cat. H(R), S (M, B, B3) fixed wing DO-160E Section 8.0 Cat. R(G) rotor configuration (not applicable to VAR 030) DO-160E Section 9.0 Cat. X. No test required. DO-160E Section 10.0 Cat. W
Fluids Susceptibility
DO-160E Section 11.0 Cat. X. No test required.
Sand and Dust
DO-160E Section 12.0 Cat. D
Fungus Resistance
DO-160E Section 13.0 Cat. F
Salt Spray
DO-160E Section 14.0 Cat. X No test required.
Altitude
Vibration
Figure 7 Environmental Specification (Sheet 1 of 2)
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
ENVIRONMENTAL
SPECIFICATION
ELECTROMAGNETIC INTERFERENCE (cont’d) Magnetic Effect
DO-160E Section 15.0 Cat. Z
Power Input
DO-160E Section 16.0 Cat. A Momentary Power Interrupt (200 ms)
Voltage Spike conducted Audio Frequency conducted susceptibility
DO-160E Section 17.0 Cat. A DO-160E Section 18.0 Cat. R
Induced Signal susceptibility
DO-160E Section 19.0 Cat. ZC
RF Susceptibility
DO-160E Section 20.0 Cat. WW and RR
Emission of Radio Frequency Energy
DO-160E Section 21.0 Cat. M
Lighting Induced transient susceptibility
DO-160E Section 22.0 Cat. A3E3X The bonding resistance of the CMA-9000 is less than 2.5 mOhm.
Lightning Direct Effects Test
DO-160E Section 23.0 Cat. X.
Icing
DO-160E Section 24.0 Cat X.
Electrostatic Discharge (ESD)
DO-160E Section 25.0 Cat. A
Fire, Flammability
DO-160E Section 26.0 Cat. X.
Bench Handling
MIL-STD-810E, Method 516.4. Drop of 4 inches and at 45 degrees edge
Solar radiation
MIL-STD-810E, Procedure II Method 505.3
Figure 7 Environmental Specification (Sheet 2 of 2)
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
J1 J1 2 8 V D C IN T L IG H T IN G 0 1 66 67 O N /O F F C O N T R O L IR S A 4 2 9 I/P 1 5 I/P H I 78 I/P H I 79 6 8 I/P L O A D C A 4 2 9 I/P 1 6 69 I/P L O 72 A R IN C 4 2 9 O /P 5 IR S A 4 2 9 O /P 8 X -T A L K A 4 2 9 O /P 4 H S 73 A R IN C 4 2 9 I/P 1 H S 0 .5 -5 V d c A M L C D D IM M IN G 1 2 6 A M L C D D IM M IN G R E T U R N 0 2 A R IN C 4 2 9 I/P 2 L S 76 A R IN C 4 2 9 O /P 7 77 A R IN C 4 2 9 I/P 5 H S 0 .5 -5 V d c IN T L IG H T (P A N E L ) 0 8 IN T E G R A L L IG H T R E T U R N 0 9 C H A S S IS G N D 80 D IS C R E T E I/P 9 D IS C R E T E I/P 1 4 A R IN C 4 2 9 O /P 3 L S 4 3 D IS C R E T E I/P 1 5 44 A R IN C 4 2 9 I/P 6 L S M A S T E R C A U T IO N O /P (1 ) 3 9 31 G P S IN T W A R N O /P (4 ) 29 A R IN C 4 2 9 I/P 3 L S U /V H F 2 A 4 2 9 I/P 8 30 D IS C R E T E O /P 5 8 7 A R IN C 4 2 9 I/P 7 L S D IS C R E T E O /P 6 8 8 D IS C R E T E O /P 7 8 9 A R IN C 4 2 9 O /P 1 L S D IS C R E T E O /P 8 9 0 91 A R IN C 4 2 9 O /P 2 H S RS422 RX3 92 D IS C R E T E R E T U R N 4197 X -T A L K A 4 2 9 I/P 9 H S U /V H F 1 A 4 2 9 I/P 4 18 D IS C R E T E I/P 1 2 D IS C R E T E I/P 1 3 95 R S 2 3 2 /4 2 2 R X 1 D IS C R E T E I/P 1 6 96 M C F A IL (6 ) 97 R S 2 3 2 /4 2 2 T X 1 98 RS422 R X2 E M E R G E N C Y D IS C I/P (2 ) 48 101 RS422 TX2 RS 422 RX4 110023 RS 232 G ND 104 RS 422 TX 4 D IS C R E T E O /P 2 105 D IS C R E T E I/P 4 106 A R IN C 4 2 9 I/P 1 7 D IS C R E T E I/P 5 107 D IS C R E T E I/P 1 0 A R IN C 4 2 9 I/P 1 8 1 0 8 D IS C R E T E I/P 1 1 109 L A M P T E S T D IS C R E T E (3 ) 110 A R IN C 4 2 9 I/P 1 9 D IS C R E T E O /P 3 56 T O G A (D IS I/P 1 ) 57 V O L F B C K F C (I/P 1 0 ) RS422 TX3 113 114 A R IN C 4 2 9 I/P 2 1 S Y N C R E F I/P L O 117 G P S T IM E M A R K H I A R IN C 4 2 9 I/P 2 3 H I 58 G P S T IM E M A R K L O 59 A R IN C 4 2 9 I/P 1 1 118 W O W (8 ) 111189 A R IN C 4 2 9 I/P 2 3 L O S H IE L D R E T U R N 120 S H IE L D R E T U R N A R IN C 4 2 9 I/P 2 4 60 A R IN C 4 2 9 I/P 2 0 61 A R IN C 4 2 9 I/P 1 2 123 A R IN C 4 2 9 I/P 2 2 S Y N C O /P 1 Z 124 S Y N C R E F I/P H I 64 D A T A L O A D A 6 1 5 I/P 1 3 F U E L A 4 2 9 I/P 1 4 65 S Y N C O /P 1 X 27 S Y N C O /P 1 Y 1 1 5 V a c,4 0 0 H z P O W 1 128 D A Y /N IG H T D IS C R E T E (7 ) 1 1 5 V a c ,4 0 0 H z R T N A R IN C 4 2 9 O /P 6
RD GN
POW ER +28VDC +28VDC +28VDC +28VDC
J1
28 29 J1
RD GN
RD GN RD GN
J2 15
B rig h tn e s s C o n tro l D is p la y
RD GN
38 39
RD GN
ADC
FR ON T FMS (J 1P 6 8/6 9)
J1
J1
80
78 79
RD GN
J1 RD GN
18 27
J 11
B C
RD GN
RD GN
R a d io 8 1 In te rfa c e 1
J1 1 RD GN
AHRS
36 37 J1
RD GN
J1 29
U /V H F 1
A E
RD GN
REAR FM S (J 1 P 1 7 /1 8 )
R a d io E m e rg e n cy
J2
78 79
RD GN
REAR FM S (J 1 P 2 9/3 0 ) RD GN
U /V H F 2
JB 8E
RD GN
8F
O S M C (J 1 P 5 0/ 51 )
AMU JB RD GN
B 1 1A
RD GN
JB
B 1 1B
7A 7B
JB
RD GN
R EAR FMS (J 1P 25 /2 6)
B 1 0A
RD GN
B 1 0B
J2 A V IO N IC S C A T 2 (J 9 P 1 5 /1 6 )
46 Fuel 47 C o m p u te r
C3 C1
C2
RD GN
R EAR FMS (J 1P 6 4/6 5)
X1
X2
D A Y /N IG H T 3 FR ON T R ELAY
S e co n d F M S BATT BATT
FRONT FMS (J1P 4)
J1
10 11
G P S re ce ive r
J1
24 25
RD GN
FRONT FMS (J1P 10/11) RD GN
REAR FMS (J1P 34,37)
RD GN
RD GN RD GN RD GN
J1
V O R /IL S 1
15 16 J1
05 06 J1
05 06
V O R /IL S 2
J1
21 22
RD GN FRONT FMS (J1P 12/13)
RD GN RD GN
RD GN
RD GN
OSMC, FPFD, RPFD, CAT, HSG FRONT FMS (J1P 19/20)
RD GN RD GN RD GN
RD GN OSMC, FPFD, RPFD, HSG
FRONT FMS (J1P 70,71)
FRONT FMS (J1P 38)
RD GN
C1
J2
ATC T ran sp o n d e r
19 20 J2 21 22 J1
DME
01 02 J1 21 22
C2
FRONT FMS (J1P 21/22) RD GN
C3
X2
X1
M C F A IL 2 R E LA Y AMU
RD GN
FRONT FMS (J1P 23/24) RD GN
R E A R LA M P T E S T S W IT C H FRONT FMS (J1P 16) D3
RD GN
D1
D2
C A T 2(J9P 11/12)
J1
E F IS
44 45 J1 33 34
X2
X1
W O W 2 R E LA Y
RD GN
RD GN
RD GN
C O C K P IT C A T (J502 P 27, 28) C O C K P IT C A T (J502 P 36, 37)
J1 01 66 67 68 69 78 79 72 73 A R IN C 4 2 9 I/P 1 H S 0 .5 -5 V d c A M L C D D IM M IN G 1 2 6 A M L C D D IM M IN G R E T U R N 0 2 76 A R IN C 4 2 9 I/P 2 L S A R IN C 42 9 O /P 7 77 A R IN C 4 2 9 I/P 5 H S0 .5 -5 V d c IN T L IG H T (P A N E L ) 0 8 09 IN T E G R A L L IG H T R E T U R N C H A S S IS G N D 80 D IS C R E T E I/P 9 4 3 D IS C R E T E I/P 1 4 A R IN C 4 2 9 O /P 3 L S D IS C R E T E I/P 1 5 44 A R IN C 4 2 9 I/P 6 L S M A S T E R C A U T IO N O /P (1 ) 3 9 31 G P S IN T W A R N 0 /P (4 ) 29 A R IN C 4 2 9 I/P 3 L S U /V H F 2 A 4 2 9 I/P 8 3 0 D IS C R E T E O /P 5 8 7 A R IN C 4 2 9 I/P 7 L S D IS C R E T E O /P 6 8 8 89 D IS C R E T E O /P 7 A R IN C 4 2 9 O /P 1 L S D IS C R E T E O /P 8 9 0 91 A R IN C 4 2 9 O /P 2 H S R S 42 2 R X 3 92 D IS C R E T E R E T U R N 49 X -T A L K A 4 2 9 I/P 9 H S 17 U /V H F 1 A 42 9 I/P 4 D IS C R E T E I/P 1 2 18 D IS C R E T E I/P 1 3 95 R S 2 3 2 /4 22 R X 1 D IS C R E T E I/P 1 6 96 M C F A IL (6 ) 97 R S 2 3 2 /42 2 T X 1 98 RS422 RX2 E M E R G E N C Y D IS C I/P (2 ) 48 101 RS422 TX2 RS422 RX4 102 1 03 RS232 GND RS422 TX4 104 D IS C R E T E O /P 2 D IS C R E T E I/P 4 105 A R IN C 4 29 I/P 1 7 1 0 6 D IS C R E T E I/P 5 D IS C R E T E I/P 1 0 A R IN C 42 9 I/P 1 8 1 0 7 D IS C R E T E I/P 1 1 108 L A M P T E S T D IS C R E T E (3 ) 109 A R IN C 42 9 I/P 1 9 1 D IS C R E T E O /P 3 10 T O G A (D IS I/P 1 ) 56 V O L F B C K R C (I/P 1 0 ) 57 RS422 TX3 113 A R IN C 4 2 9 I/P 2 1 114 S Y N C R E F I/P L O 117 A R IN C 4 2 9 I/P 2 3 H I G P S T IM E M A R K H I 58 G P S T IM E M A R K L O A R IN C 4 2 9 I/P 1 1 59 W O W (8 ) 118 A R IN C 4 2 9 I/P 2 3 L O S H IE L D R E T U R N 119 S H IE L D R E T U R N A R IN C 4 29 I/P 2 4 120 A R IN C 4 2 9 I/P 2 0 60 A R IN C 4 2 9 I/P 1 2 61 A R IN C 4 2 9 I/P 2 2 123 S Y N C O /P 1 Z S Y N C R E F I/P H I 1 2 4 D A T A L O A D A 61 5 I/P 1 3 64 F U E L A 42 9 I/P 1 4 6 5 S Y N C O /P 1 X S Y N C O /P 1 Y 1 1 5 V a c,4 0 0 H z P O W 1 2 7 D A Y /N IG H T D IS C R E T E (7 ) 1 1 5 V a c,4 0 0 H z R T N 1 2 8
FRONT FMS (J1P 66/67)
J1
2 8 V D C IN T LIG H T IN G
A R IN C 4 2 9 O /P 6
RD GN
P O W E R O N /O FF C O N T R O L IR S A 4 29 I/P 1 5 +2 8 V D C I/P H I A D C A 42 9 I/P 1 6 +2 8 V D C I/P H I +2 8 V D C I/P L O A R IN C 42 9 O /P 8 +2 8 V D C I/P L O A R IN C 42 9 O /P 5 X -T A L K A 4 2 9 O /P 4 H S
FRONT FMS (J1P 68/69)
J1 29
J2 15 RD GN
28 29
RD GN
RD GN
B righ tn e ss C o n tro l D isp la y
38 39
RD GN
78 79
J1 RD GN
ADC
J1
J1
RD GN
AHRS
J1
80
RD GN
R a d io 8 1 In te rfa ce 2
18 27
J1 RD GN
B C
RD GN
U /V H F 1
REAR FMS (J1P 17/18)
R a d io E m e rg e n cy
J2
REAR FMS (J1P 29/30) RD GN
J1
78 79
RD GN
RD GN
U /V H F 2
A E
RD GN
JB 9E 9F
O S M C (J1P 54/ 55)
AMU JB RD GN
10A 10B
JB RD GN
7A 7B
RD GN FRONT FMS (J1P 25/26)
JB 11A 11B
RD GN
J2 A V IO N IC C A T 2(J9P 17/19) D3 D2
X2
D1
46 Fuel 47 C o m p u ter
RD GN
FRONT FMS (J1P 64/65)
X1
D A Y /N IG H T 3 R E A R R E LA Y
Figure 8E Dual FMS installation with radio tuning and suggested pins allocation (courtesy of Pilatus Aircraft Switzerland)
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
3.
DIGITAL EQUIPMENT Table 1 shows a list of ARINC 429 equipment which may be connected to each CMA-9000 system (in a dual FMS installation). The digital inputs and outputs can be configured for high or low speed. QUANTITY 1
1 Up to 2 1 1 Up to 2 1 Up to 2 1 1 1 1 1 Up to 2 1 Up to 2 1 Up to 2
EFIS EHSI EGI ELT FC GPS CONC PLS PRI REC REPE SIMUL NAV TACAN VUHF WXR XPDR
DESCRIPTION Aircraft Communication Addressing and Reporting System (Future Growth) Aircraft Condition Monitoring System Audio Management Unit Air Data Computer Automatic Direction Finder Aircraft Flight Control System Attitude and Heading Reference System Aircraft Piloting Inertial Reference System ARINC 429 I/F Checker Digital Map System Data Loader Unit Distance Measuring Equipment Doppler Velocity Sensor* Electronic Flight Instrument System Electronic Horizontal Situation Indicator Embedded GPS INS (1)* Emergency Locator Transmitter (use REC o/p) Fuel Computer Global Positioning System (ARINC 743A) Data Concentrator Personnel Locator System Printer (Future Growth) Flight Recorder Repeater Simulator (Future Growth) VOR/ILS Receiver Tactical Air Navigation Receiver V/UHF Communication Radio Weather rader
ATC Transponder
I/O Both O/P Both I/P Both O/P I/P I/P Both Both (Note 1) Both Both I/P for RDN-85 Both for ANV-353 Both (Note 2) Both Both O/P I/P Both I/P I/P O/P O/P Both Both Both I/P Both I/P Both
NOTE 1: The FMS transmits output data to the DMAP unit via the EFIS output A429 bus. NOTE 2: The FMS receives and decodes input data from EFIS IFDS, AHCAS and AHCAS2 unit types only. *The installation of an EGI, DVS are not allowed with an approved FMS. Table 1 ARINC 429 Equipment Supported by the CMA-9000
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
A.
Aircraft Condition Monitoring System (ACMS) (1)
FMS to Digital ACMS Link Summary This section provides information on the ARINC 429 outputs that are supplied by the FMS to the Aircraft Condition Monitoring System (ACMS).
DESCRIPTION Distance to the TO waypoint Time to go to the "TO" waypoint Ground Speed ETA at Destination Dep/Dest airports (dep123) Dep/Dest airports (dep4/dest1) Dep/Dest airports (dest234) Zero Fuel Weight (Aircraft Gross Weight - Aircraft Fuel Weight) Aircraft Gross Weight Selected Altitude Target Vertical Speed Desired track Waypoint bearing Cross-track (lateral deviation) Vertical deviation Range to target altitude Roll/steering command Greenwich Mean Time Vertical deviation UTC (Time) (Pilot Entered) MDA (Minimum Descent Altitude) Pressure altitude Baro Corrected Altitude Mach Number CAS/IAS True Airspeed Vertical Rate Static Air Temperature Flight number (char1/char2) Flight number (char3/char4) Flight number (char5/char6) Flight number (char7/char8) Flight number (char9/char10) Distance to Go Time to Go Date FMS status word 1 FMS failure word FMS sub-system validity word FMS status word 2
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
LABEL-EQUIP ID 310-002 311-002 312-002 313-002 314-002 315-002 316-002 317-002 320-002 321-002 325-002 335-002 354-002b 361-004 365-002 B.
DESCRIPTION Present position latitude Present position longitude Ground speed Track angle true True heading Wind Speed Wind Angle Track Angle Magnetic Magnetic Heading Drift angle Roll angle Track angle rate TO WPT name Baro Inertial Altitude Inertial vertical speed
Digital ADC to FMS Link Summary The Air Data Computer (ADC) provides True Air Speed (TAS), Pressure Altitude (P.ALT.) and Baro Corrected Altitude to the FMS following ARINC 429 specifications. LABEL-EQUIP ID 102-002 203-006 204-006 205-002 206-002 210-006 212-002 213-002 234-006 237-025
DESCRIPTION Mode Control Panel Selected Altitude Pressure Altitude Baro Corrected Altitude Mach Number Corrected Airspeed Or Indicated Airspeed True Air Speed Vertical Rate Static Air Temperature Baro Correction Barometric Correction
When a Rockwell, Barco or AHCAS2 EFIS is installed, the crew selected altitude type (barocorrected or standard) is also provided via label 170. LABEL-EQUIP ID 170-006
DESCRIPTION DH Selected
TX RATE 100 msec
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INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
C.
Air Data Computer (ARINC 575) (1)
Digital ADC to FMS Link Summary The Air Data Computer (ADC) provides True Air Speed (TAS), Pressure Altitude (P.ALT.) and Baro Corrected Altitude to the FMS following ARINC 575 specifications. LABEL-EQUIP ID 210-575 203-575 204-575
D.
DESCRIPTION True Air Speed Pressure Altitude Barometric Altitude
TX RATE 500 msec 500 msec 500 msec
Attitude and Heading Reference System (ARINC 429) (1)
Digital AHRS to FMS Link Summary The Attitude And Heading Reference System (AHRS) provides True & Magnetic Heading, to the FMS following the ARINC 429 specifications. The FMS gives priority to the TRUE heading when both labels are available. LABEL-EQUIP ID 314-005 320-005
DESCRIPTION True Heading Magnetic Heading
TX RATE 50 msec 50 msec
When a Rockwell or Barco EFIS is installed, the heading source selection is also provided via label 275. LABEL-EQUIP ID 275-025 (2)
DESCRIPTION EFIS status
TX RATE 200 msec
Central Reference Primaire (CRP) AHRS to FMS Link Summary This section identifies the labels received by the FMS from an AHRS of type CRP LABEL-EQUIP ID 350-005 320-005
DESCRIPTION AHRS status Magnetic Heading
TX RATE 80 msec 20 msec
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E.
Automatic Flight Control System (1)
AFCS to FMS Link Summary This section provides information on the ARINC 429 outputs that are supplied by the Automatic Flight Control System (AFCS) to the FMS. NOTE: LABEL 300 is always valid, regardless of the SSM value. It is used to compute tail deformation compensation value on helicopter. LABEL-EQUIP ID 300-025
(2)
DESCRIPTION Engines Hinge Moment
TX RATE 200 msec
FMS to Digital AFCS Link Summary This section provides information on the ARINC 429 outputs that are supplied by the FMS to the Automatic Flight Control System (AFCS). LABEL-EQUIP ID 121-002 214-002a* (see note) 216-002a* (see note)
NOTE:
DESCRIPTION Horizontal Command Track Angle Error For Steering Control Cross-Track Distance For Steering Control
TX RATE 100 msec 100 msec 100 msec
Labels 214 and 216 are installation configurable through the A429 GENERAL EQP 1/6 page
(a) Horizontal Command Output Characteristics The Horizontal Command to the AFCS has the following characteristics: Refresh rate = 100 msec Maximum bank angle = +/- 10 to 30 degrees based on configuration Maximum roll rate = 2.5 degrees/sec to 4.0 degrees/sec The "Status Matrix" should be interpreted as follows: NOTE: When the "NO COMPUTED DATA" status is set, the data should not be used for flight guidance.
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Normal: No Computed Data:
F.
- Valid roll command - System failures - Heading failure when not in GPS navigation mode or when flying a heading leg (heading to altitude, ...) - TAS failure when navigating in DR mode. - Aircraft airborne and speed below minimum speed. - Undefined active waypoint (Disco, end of route, no route) - Aircraft is not on intercept heading/course (installation configurable). - Unable to meet approach criteria 2 nm inbound to FAF.
Checker (ARINC 429) This equipment is used for testing purposes, it allows the user to monitor and transmit ARINC labels from a Maintenance page (A429 I/O CHECKER page) NOTE: The checker (CHK) is configured on a single ARINC 429 input bus and/or on a single ARINC 429 output bus.
Digital DME to FMS Link Summary The COLLINS 442 or COLLINS 4000 Distance Measuring Equipment (DME) Receiver provides the frequency of the DME station tuned, the distance to the DME station and the DME station identifier to the FMS. This is done in accordance with the GAMA specifications. LABEL-EQUIP ID 035-009 202-009
DESCRIPTION DME Frequency Distance from Station
TX RATE 100 msec 100 msec
The FMS is expecting these labels from the DME receiver, in the following sequence: CH 1 - FREQ(035), DIST(202) CH 2 - FREQ(035), DIST(202) CH 3 - FREQ(035), DIST(202) CH 1 - FREQ(035), DIST(202), IDENT(300), IDENT(300) CH 2 - FREQ(035), DIST(202), IDENT(300), IDENT(300) CH 3 - FREQ(035), DIST(202), IDENT(300), IDENT(300) NOTE:
The CMA-9000 is not using the DME station identifier ARINC 429 label 300-009 at this stage (Future Growth).
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(2)
FMS to Digital DME Link Summary This section provides information on the ARINC 429 RADIO TUNING output, supplied by the FMS to the COLLINS 442 or COLLINS 4000 DME receiver. The FMS sends an output of the next frequency to be tuned by the DME receiver. The frequency identifies a particular DME station. LABEL-EQUIP ID 035-002
Digital DME to FMS Link Summary The COLLINS 700 DISTANCE MEASURING EQUIPMENT (DME) RECEIVER provides the frequency of the DME station tuned and the distance to the DME station to the FMS. This is done in accordance with the ARINC specifications. LABEL-EQUIP ID 035-009a
DESCRIPTION DME Frequency
TX RATE 200 msec
202-009a
Distance From Station
167 msec
The FMS is expecting these labels from the DME receiver, in the following sequence: CH 1 - FREQ(035), DIST(202) CH 2 - FREQ(035), DIST(202) CH 3 - FREQ(035), DIST(202) CH 1 - FREQ(035), DIST(202), IDENT(300), IDENT(300) CH 2 - FREQ(035), DIST(202), IDENT(300), IDENT(300) CH 3 - FREQ(035), DIST(202), IDENT(300), IDENT(300) NOTE:
(2)
The CMA-9000 is not using the DME station identifier ARINC 429 label 300-009 at this stage (Future Growth).
FMS to Digital DME Link Summary This section provides information on the ARINC 429 RADIO TUNING output, supplied by the FMS to the COLLINS 700 DME receiver. The FMS sends an output of the next frequency to be tuned by the DME receiver. The frequency identifies a particular DME station. LABEL-EQUIP ID 035-002a
DESCRIPTION DME Frequency
TX RATE 100 msec
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I.
Chelton DM-441B Distance Measuring Equipment Receiver (ARINC The Chelton DM-441B used to be known as the Bendix King DME receiver 441B. (1)
Digital FMS to Digital DME Link Summary The DME requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the DME are listed below. NOTE:
Output for hold mode channel only when in hold mode. NAV radio paired channels may be tuned directly by the NAV radio output or by using the FMS output.
The outputs listed below are formatted in accordance with the General Aviation Manufacturers Association (GAMA) specifications. LABEL-EQUIP ID 035-002
(2)
DESCRIPTION DME Frequency
TX RATE 100 msec, Burst
REMARKS Output on CH 3 for Navigator, CH4, 5 for Hold mode (burst), CH1, 2 when paired with NAV receiver.
Digital DME to FMS Link Summary This section describes the ARINC 429 data words and transmission protocol of the inputs to the FMS from the DME radio. LABEL-EQUIP ID 035-009 202-009
J.
DESCRIPTION DME Frequency DME Distance
RATE 150 msec 150 msec
ARINC 615 Data Loader Unit (ARINC 429) The ARINC 615 capable data loader unit sends/receives data to/from the FMS. The communication between the DLU and FMS takes place over the ARINC high speed data link using label 226 as per the ARINC 615-3 specification.
K.
GAMA EFIS Interface Description This section provides information on the ARINC 429 outputs that are supplied by the FMS to an EIS. The outputs are formatted to follow the GAMA specifications (General Aviation Manufacturers Association).
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(1)
FMS to Digital Sperry EIS (Airline Version) Link Summary The FMS transmits the following labels according to the table below. LABEL-EQUIP ID 001-002 056-002 114-002 115-002 116-002a 117-002a 121-002 125-002 147-002 251-002 252-002 261-002 275-002a 310-002 311-002 312-002 313-002 314-002 315-002 316-002 321-002 326-002 352-002 371-002
DESCRIPTION Distance To The "To" Waypoint Estimated GMT At End Of Route Desired Track (True) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Greenwich Meantime Magnetic Variation Distance To Go Time To Go GPS Discrete Word FMS Status Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code
This table provides the list of labels transmitted for route and navaid output and their rate of transmission. LABEL-EQUIP ID 074-002 075-002a 113-002 300-002 301-002 302-002 303-002 304-002 305-002 306-002 307-002 *
DESCRIPTION Data Record Header Active WPT From/To Message Checksum Station Type/Class Message Character 7-9 Message Character 10-12 Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude
1/ Fixed rate at 10 seconds. 2/ Continuous rate depending on number of waypoints.
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(2)
FMS to Digital Sperry EIS (General Aviation Version) Link Summary The FMS will transmit the following labels according to the table below. LABEL-EQUIP ID 001-002 056-002 114-002a 115-002 116-002 117-002a 121-002 125-002 147-002 251-002 252-002 261-002 275-002 310-002 311-002 312-002 313-002 314-002 315-002 316-002 321-002 326-002 352-002 371-002
DESCRIPTION Distance To The "To" Waypoint Estimated GMT At End Of Route Desired Track (Magnetic) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Greenwich Meantime Magnetic Variation Distance To Go Time To Go GPS Discrete Word FMS Status Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code
This table provides the list of labels transmitted for route and navaid output and their rate of transmission. LABEL-EQUIP ID 074-002 075-002a 113-002 300-002 301-002 302-002 303-002 304-002 305-002 306-002 307-002 *
DESCRIPTION Data Record Header Active WPT From/To Message Checksum Station Type/Class Message Character 7-9 Message Character 10-12 Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude
1/ Fixed rate at 10 seconds. 2/ Continuous rate depending on number of waypoints.
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(3)
FMS to Digital EIS (GAMA compliant) Link Summary The FMS transmits the following labels according to the table below. LABEL-EQUIP ID 100-002 114-002 115-002 116-002 117-002a 121-002 147-002 150-002 251-002 252-002 261-002 275-002b 310-002 311-002 312-002 313-002 314-002 315-002 316-002 321-002 326-002 352-002 371-002
DESCRIPTION Selected Intercept Course (True/Mag) Desired Track (True) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Magnetic Variation Greenwich Mean Time Distance To Go Time To Go GPS Discrete Word FMS Status Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code
This table provides the labels transmitted at for route and navaid output and their rate of transmission. LABEL-EQUIP ID 074-002 075-002a 113-002 300-002 301-002 302-002 303-002 304-002 305-002 306-002 307-002 *
DESCRIPTION Data Record Header Active WPT From/To Message Checksum Station Type/Class Message Character 7-9 Message Character 10-12 Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude
1/ Fixed rate at 10 seconds. 2/ Continuous rate depending on number of waypoints.
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(4)
FMS to Sextant Digital EIS (GAMA compliant, Avionique Nouvelle) Link Summary This table provides the labels transmitted at a fixed rate and their rate of transmission.
DESCRIPTION Selected Intercept Course (True/Mag) Desired Track (True) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Magnetic Variation Greenwich Mean Time ACK Of DMAP WPT TXFR Distance To Go Time To Go GPS Discrete Word FMS Status FMS Status Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code
This table provides the labels transmitted at for route and navaid output and their rate of transmission. LABEL-EQUIP ID DESCRIPTION TX RATE 074-002 Data Record Header * 075-002a Active WPT From/To 100 msec 113-002 Message Checksum 100 msec 300-002 Station Type/Class 100 msec 301-002 Message Character 7-9 100 msec 302-002 Message Character 10-12 100 msec 303-002c Message Control Word 100 msec 304-002 Message Character 1-3 100 msec 305-002 Message Character 4-6 100 msec 306-002 Waypoint Latitude 100 msec 307-002 Waypoint Longitude 100 msec * 1/ Fixed rate at 10 seconds. 2/ Continuous rate depending on number of waypoints.
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(5)
FMS to Rockwell/Rockwell2/AHCAS2 Custom EIS (GAMA Compliant) Link Summary This table provides the labels transmitted and their rate of transmission. LABEL-EQUIP ID 074-002 075-002 076-002 113-002 114-002 115-002 116-002 117-002a 121-002 140-002 147-002 150-002 164-002 172-002a 203-002 204-002 210-002 216-002 220-002 251-002 252-002 260-all except 002c 270-002b 271-002 275-002a 300-002 303-002d 304-002 305-002 306-002 307-002 310-002 311-002 312-002 313-002a 314-002 315-002 316-002 321-002a 326-002 352-002 371-002
DESCRIPTION Data Record Header Active WPT From/To Msl Altitude (From GPS) Message Checksum Desired Track (True) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Roll Steering Magnetic Variation Time Utc Radio Height ACK Of DMAP WPT TXFR Standard ALT Corrected ALT True Airspeed Cross Track Offset INS/GPS Altitude Distance To Go Time To Go Date (D/M/Y) Status Word FMS Failure Word FMS Status Word Station Type/Class Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
NOTE:
(6)
Fixed rate at 10 seconds. Continuous Rate Depending on Number of Waypoints.
Rockwell/Rockwell2 EFIS to FMS Summary The FMS will receive from the Rockwell/Rockwell2 EFIS units the following input ARINC 429 labels and decode them via the input EFIS (EFI) equipment:
DESCRIPTION Data Record Header Active WPT From/To MSL Altitude (From GPS) Message Checksum Desired Track (True) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Roll Steering Magnetic Variation Time UTC Standard ALT Corrected ALT True Airspeed Cross Track Offset Distance To Go Time To Go Date (D/M/Y) Status Word FMS Failure Word FMS Status Word Station Type/Class Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code
TX RATE 10 sec less See NOTE 1 100 msec 200 msec See NOTE 3 100 msec See NOTE 4 100 msec 100 msec 200 msec 100 msec 100 msec 100 msec 1 sec 300 msec 200 msec See NOTE 2 200 msec See NOTE 2 200 msec See NOTE 2 1 sec 200 msec 1 sec 1 sec 333 msec 1 sec 333 msec 100 msec See NOTE 4,5 100 msec See NOTE 4 100 msec See NOTE 4 100 msec See NOTE 4 100 msec See NOTE 4 100 msec See NOTE 4 200 msec 200 msec 200 msec 100 msec 50 msec 333 msec 333 msec 100 msec 333 msec 1 sec 1 sec
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NOTES: 1. Label 113 transmission rate depends on the following: • Fixed rate at 10 seconds. • Continuous rate depends on number of waypoints, navaids, and airports to be transmitted. The resulting rate may be faster than once every 10 seconds. 2. Labels 203, 204, and 210 are repeated from the air data computer. 3. Label 076 GPS MSL Altitude is repeated from the GPS Sensor. 4. Each label in a record is sent 10 times per second. 5. Station type, class is only sent for NAVAID records. 6. Transmission of these labels is optional depending on the length of the ident. They may be transmitted with NUL characters even if the ident is less than 7 characters long. (8)
BARCO EFIS to FMS Summary The FMS will receive from the BARCO EFIS units the following input ARINC 429 labels and decode them via the input EFIS (EFI) equipment:
LABEL-EQUIP ID 271-025
DESCRIPTION PFD Configuration
RATE 200 ms
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(9)
FMS to Meggit EIS (GAMA Compliant) Link Summary This table provides the labels transmitted and their rate of transmission. LABEL-EQUIP ID 001-002 012-002 074-002 075-002 100-002 113-002 114-002 115-002 116-002 117-002a 121-002 125-002 147-002 251-002 252-002 260-All 261-002 275-002a 300-002 303-002e 304-002 305-002 306-002 307-002 310-002 311-002 312-002 313-002 314-002 315-002 316-002 317-002 320-002 321-002a 326-002 352-002 371-002 377-002 NOTE 1:
DESCRIPTION Distance To The "To" Waypoint Ground Speed Data Record Header Active WPT From/To Selected Intercept Course Message Checksum Desired Track (True) Bearing To Waypoint (True) Cross Track Distance Vertical Deviation Horizontal Command Greenwich Mean Time Magnetic Variation Distance To Go Time To Go Date (D/M/Y) GPS Discrete Word FMS Status Word Station Type/Class Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude Present Position Latitude Present Position Longitude Ground Speed Track Angle (True) True Heading Wind Speed Wind Angle (From) (True) Track Angle (Magnetic) Magnetic Heading Angle Drift Angle Lateral Scale Factor Estimated Time To Destination Manufacturer Ident Code Equipment Hex ID
- Fix rate at 4 sec. - Continuous rate depending on number of waypoints.
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L.
IFDS and AHCAS/AHCAS2 EFIS Interface Description (1)
IFDS/AHCAS/AHCAS2 to FMS Summary The FMS will receive from the IFDS or AHCAS2 units the following input ARINC 429 labels and decode them via the input EFIS (EFI) equipment:
AHCAS Joystick Discrete Word 1 AHCAS Joystick Discrete Word 2 Aircraft gross weight Hover height Roll/Yaw Active mode Return Armed mode (Automatic Hover mode) Heading Angle AHCAS Heading Angle AHRS Status Word AHCAS Joystick Latitude AHCAS Joystick Longitude
25 ms 25 ms 200 ms 40 ms 200 ms 40 ms 20 ms 25 ms 80 ms 150 ms 150 ms
FMS to IFDS/AHCAS Link Summary (a) Navigation Sub-frame Except for labels 124 and 125, all other labels are sent with SDI=00 for this sub-frame. Labels 124 and 125 will be sent with SDI 00 (used by the Plan sub-frame) and 10 (used by the Preparation sub-frame). The FMS will transmit the following ARINC 429 labels over the Navigation sub-frame at specific rates as defined in the table below.
DESCRIPTION Ground speed (BCD) Active route ident (first 7, 8 and 9) Active route ident (first 10, 11 and 12) Active route ident (characters 1, 2 and 3) Active route ident (characters 4, 5 and 6) GPS altitude Selected radial – magnetic Desired track DTK – magnetic Bearing next waypoint Cross track distance XTK VERTICAL DEVIATION FMS Latitude Fine FMS Longitude Fine TO waypoint number and Destination type Pattern type & starting waypoint number Roll command
RATE 333.33 ms 1000 ms 1000 ms 1000 ms 1000 ms 200 ms 333.33 ms 333.33 ms 200 ms 100 ms 100 msec 200 ms 200 ms 1000 ms 1000 ms 200 ms
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DESCRIPTION GMT Time Track Angle Error TKE Radio height Distance to go (BCD) Pressure Altitude (FMS) Baro Corrected Altitude Cross Track Offset ALT INS/GPS Distance to go (BNR) Time to go Date H/C Delta Mass FMS Status (IFDS) FMS Status (AHCAS) FMS Status word 2 ACK of DMAP wpt xfer / True/Mag Magnetic variation FMS Latitude Coarse FMS Longitude Coarse Ground speed (BNR) True Heading Wind speed Track angle – magnetic Drift angle HIS scale PLS Waypoint Latitude PLS Waypoint Longitude DMAP Center Waypoint Latitude DMAP Center Waypoint Longitude Wind direction – magnetic
RATE 1000 ms 333.33 ms 200 ms 333.33 ms 200 ms 200 ms 1000 ms 200 ms 100 ms 1000 ms 1000 ms 333.33 ms 200 ms 200 ms 333.33 ms 200 ms 1000 ms 200 ms 200 ms 200 ms 200 ms 1000 ms 200 ms 333.33 ms 333.33 ms 200 ms 200 ms 1000 ms 1000 ms 1000 ms
(b) Waypoint Data Sub-frames 1
Sector Sub-frame This sub-frame will contain all the parameters defining an active flight plan or pattern. The FMS will transmit this sub-frame all the time with all the parameters having SDI=00 and a refresh rate of 1800 ms (which makes this sub-frame distinct of the "navigation" sub-frame). The parameters that are not used are sent with SSM NCD. The parameters of this frame are listed in the table above. The transmission order of this sub-frame is as follows: FROM, TO, TO+1, …, TO+9. For a Hover procedure the sector sub-frame will contain the TDN and MRK waypoints in the last but one and respectively last position of the transmission.
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Plan Sub-frame
2
This sub-frame will contain all the parameters necessary to define an active flight plan or pattern. The FMS will transmit this sub-frame all the time with all parameters having SDI = 01 and a refresh rate of 1800 ms. The parameters that are not used are sent with SSM NCD. The sub-frame update is done in increasing order starting with the CENTER waypoint and finishing with waypoint (TO+9). The parameters of this sub-frame are listed in the table above. In order to properly display the Plan sub-frame information, the IFDS will use the information sent in the ARINC labels 124-00 and 125-00 of the navigation sub-frame. For a Hover procedure the plan sub-frame will contain the TDN and MRK waypoints always in the (TO+8) and (TO+9) positions. 3
Preparation Sub-frame This sub-frame will contain all the parameters necessary to define a flight plan or a pattern that is being prepared (see NOTE 1). This sub-frame is sent all the time. All the parameters are sent with SDI = 10 and a refresh rate of 1800 ms. Unused parameters are sent with SSM NCD. Patterns are transmitted in the Preparation sub-frame only when there is no active hover procedure, holding pattern and search pattern in the Active route. In the particular case of waypoint identifiers, the waypoint ident parameters will always be sent NCD, except when the Inactive route is transmitted in the Preparation sub-frame, in which case the waypoint ident parameters are sent with SSM NORM only for those waypoints defined in the Inactive route. This sub-frame will contain all the parameters necessary to transmit the information related to one of the procedures or route selected according to the priority logic defined below: • • • • • • • • •
an offset leg if one is defined in the Active route; else a holding pattern if a holding pattern waypoint is defined in the Active route or modified Active route and is located in the route before any discontinuity (if one exists) and before any search waypoint (if one exists) which was not created off-route (see NOTE 2); else a search pattern if a search pattern waypoint is defined in the Active route or modified Active route and is located in the route before any discontinuity (if one exists); else the Inactive route, if one is defined.
NOTE 1:
In order to display correctly the Preparation sub-frame, the IFDS uses the information sent in the navigation sub-frame on the ARINC labels 124-10 and 125-10.
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NOTE 2:
4
A holding pattern waypoint always has priority over a search pattern waypoint created off-route. Off-route search pattern waypoints are created from the CDU SAR pages using a search waypoint Ident or a search waypoint Reference Ident and are always inserted as the first waypoint of the route. It is important to clarify that Off-route SAR waypoints are actually part of the route. The term "Off route" relates to their nature fof being created outside of the planned route, e.g. they are "Off route".
Waypoint Data For a pattern other than hover, the FMS will send the waypoint identifier as NCD. For a hover procedure, waypoint identifiers are sent only for TRANSDOWN (TDN) and MARK ON TOP (MRK) waypoints; NCD for others. Within each sub-frame and at every 100ms, the FMS will transmit all data related to each waypoint in the following order: LAT, LON, and ident (4 ARINC labels). Each sub-frame is refreshed every 1800ms. NOTE: The transmission of all 11 waypoints for each sub-frame requires 1100ms. Therefore, 7 additional empty transmission slots of 100ms are required to make up the 1800ms sub-frame refresh rate. The FMS will transmit to the IFDS EFIS the Active route waypoints (via Sector and Plan sub-frames) or Inactive route waypoints (via Preparation sub-frame) with the '/' character appended followed by the attribute 'H' for a holding pattern or 'O' for overfly or 'S' for a search pattern,. T' for a Tactical DTO and 'R' for Radial-To.
(c) Holding pattern For a holding pattern in order to display on the IFDS EFIS the same active leg in both plan and sector sub-frames, the FMS will compute a supplementary leg of zero length that is super-imposed on the holding fix. (d) DME arcs and Fix Radius turns (arc legs) When legs of types "Arc to a Fix" and "Radius to a Fix" are encountered in the Active route or when a Hover procedure becomes active in the Active route, the FMS will compute intermediate arc waypoints in order to draw the desired arc (Sector and Plan sub-frames only). No identifiers are provided for those intermediate arc waypoints. When legs of types "Arc to a Fix" and "Radius to a Fix" are encountered in the Inactive route (Preparation sub-frame only), no intermediate arc waypoints are computed.
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(e) Tactical DTO waypoint When a route waypoint with a Tactical DTO qualifier ("/T") becomes the Active TO waypoint, then the FMS will replace on IFDS EFIS the display of any existing legs leading to the Tactical DTO waypoint by an initial leg starting from aircraft present position to the waypoint. Once the waypoint is overflown, the FMS will no longer connect aircraft present position to the waypoint. If the Tactical DTO qualifier is removed from the Active TO waypoint before it is overflown, then the FMS will display back on IFDS EFIS the original leg as specified by the attributes of the active FROM/TO waypoints. (f)
Active Leg Backwards Extension Upon engaging specific leg types for which the displayed leg course on IFDS EFIS does not match the desired course (e.g. CF, CI, VI, CA, VA, CD, VD, CR, VR, FA, FC, FD legs and downpath DF leg), the FMS will re-draw on IFDS EFIS, in lieu of the active leg and any existing previous legs, a new active leg whose course matches the desired course and which extends backwards from the active waypoint.
(g) Search pattern In order to display a search pattern on the IFDS & AHCAS EFIS types, the FMS will transmit, via the Sector, Plan and Preparation sub-frames, a maximum of 10 search pattern waypoints at a time out of the total 80 search pattern waypoints (including the search pattern origin). The origin identifier will be transmitted over the Sector and Plan sub-frames only. In addition, for the AHCAS EFIS type only, search pattern waypoints (excluding the origin) will be transmitted, via the Sector, Plan and Preparation subframes, with valid identifiers of the form "nn", where nn is a number whose range is [01, 79]. M.
ARINC 702 EFIS Interface Description This section provides information on the ARINC 429 outputs supplied to an EHSI. The outputs are transmitted in alternating blocks of dynamic and background data, according to the ARINC 702A specification. (1)
ARINC 702 EFIS to FMS Link Summary The data sent from the EHSI to the FMS consists of the map mode, scale and symbol option selections made by the flight crew on the EHSI control panel. These selections are encoded into the discrete words listed below. LABEL-EQUIP ID 272-002a 273-002
DESCRIPTION EFIS Discrete #1 EFIS Discrete #2
TX RATE 200 msec 200 msec
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FMS to ARINC 702 EFIS Link Summary FMS to Smiths Industries 5-ATI EHSI: DYNAMIC DATA LABEL-EQUIP ID
DESCRIPTION
TX RATE (MSEC)
001-002
FMS Distance to Waypoint
1000
012-002
FMS Ground Speed (BCD)
1000
056-002a
Estimated Time of Arrival
1000
116-002
Cross-Track Distance
100
117-002
VERTICAL DEVIATION
100
126-002
Vertical Deviation
100
120-002
Range to Altitude
100
210-002
True Airspeed
100
271-002a
FMC Discrete Word 1
500
303-002b
Start of Dynamic Data
50
310-002
FMC Present Position - Latitude
100
311-002
FMC Present Position - Longitude
100
312-002
FMS Ground Speed
200
313-002
Track Angle True
50
315-002
Wind speed
1000
316-002
Wind Direction
200
317-002
Track Angle Magnetic
50
354-002
Alpha Numeric Text
1000
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BACKGROUND DATA OCTAL LABEL
BIT POSITION
PARAMETER
0
1
2
3
4
5
6
7
301
1
1
0
0
0
0
0
1
START OF TRANSMISSION (SOT) (BACKGROUND)
303
1
1
0
0
0
0
1
1
START OF TRANSMISSION (SOT) (DYNAMIC)
100
0
1
0
0
0
0
0
0
VECTOR - Active Flight Plan
300
1
1
0
0
0
0
0
0
VECTOR - Active Flight Plan Changes
040
0
0
1
0
0
0
0
0
VECTOR - Inactive Flight Plan
140
0
1
1
0
0
0
0
0
VECTOR - Radial
020
0
0
0
1
0
0
0
0
VECTOR - Offset Path
160
0
1
1
1
0
0
0
0
VECTOR IDENTIFIERS
250
1
0
1
0
1
0
0
0
SYMBOL: VORTAC + Identifier
150
0
1
1
0
1
0
0
0
SYMBOL: TUNED VORTAC (Astronautics only)
350
1
1
1
0
1
0
0
0
SYMBOL: VOR + Identifier
030
0
0
0
1
1
0
0
0
SYMBOL: TUNED VOR (Astronautics only)
230
1
0
0
1
1
0
0
0
SYMBOL: DME/TACAN + Identifier
130
0
1
0
1
1
0
0
0
SYMBOL: TUNED DME/TACAN (Astronautics)
330
1
1
0
1
1
0
0
0
SYMBOL: Waypoint + Identifier
070
0
0
1
1
1
0
0
0
SYMBOL: Active Waypoint + Identifier
270
1
0
1
1
1
0
0
0
SYMBOL: Airfield + Identifier
170
0
1
1
1
1
0
0
0
SYMBOL: Origin/Destination Airfield + Identifier
004
0
0
0
0
0
1
0
0
SYMBOL: Altitude Profile Point + Identifier
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BACKGROUND DATA (Cont'd) OCTAL LABEL
BIT POSITION
PARAMETER
0
1
2
3
4
5
6
7
104
0
1
0
0
0
1
0
0
SYMBOL: Conditional Waypoint (Astronautics Only)
304
1
1
0
0
0
1
0
0
SYMBOL: Active Conditional Waypoint (Astronautics Only)
204
1
0
0
0
0
1
0
0
SYMBOL: Selected Reference Point
244
1
0
1
0
0
1
0
0
SYMBOL: Selected Reference Point + Distance
224
1
0
0
1
0
1
0
0
TEXT: Type 1 - Navigation Advisory
264
1
0
1
1
0
1
0
0
MAP REFERENCE GROUP - Latitude
164
0
1
1
1
0
1
0
0
MAP REFERENCE GROUP - Longitude
364
1
1
1
1
0
1
0
0
DISCRETE WORD - Map Mode
014
0
0
0
0
1
1
0
0
DISCRETE WORD - Range
054
0
0
1
0
1
1
0
0
ROTATED SYMBOLS: Runway + Ident
254
1
0
1
0
1
1
0
0
ROTATED SYMBOLS: Airport + Runway + Ident
354
1
1
1
0
1
1
0
0
ROTATED SYMBOLS: Holding Pattern - R
034
0
0
0
1
1
1
0
0
ROTATED SYMBOLS: Holding Pattern - L
234
1
0
0
1
1
1
0
0
ROTATED SYMBOLS: Procedure Turn - R
134
0
1
0
1
1
1
0
0
ROTATED SYMBOLS: Procedure Turn - L
302
1
1
0
0
0
0
1
0
END OF TRANSMISSION (EOT)
000
0
0
0
0
0
0
0
0
FILL-IN WORDS
NOTE: The labels are shown in the order of transmission. (3)
Map Data Updating The FMS outputs map data to the EFIS every 50 msec, in alternating blocks of background data (64 words) and dynamic data, until a complete map background data block of 512 words are transmitted. After completion of the map background data transmission, the dynamic data continues to be updated at 20 Hz until a new map background data block is transmitted. Map background data is updated and transmitted once every 3 seconds, except on a mode, scale or option change, when the FMS updates and transmits new map background data within 1 second.
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(4)
Dynamic Data Format The first word of each dynamic data transmission is a Start of Dynamic Data (SOD) word, label 303.
(5)
Background Data Format (a) Start of Transmission Word The first word of each 64-word data block is a Start Of Transmission (or SOT) word, label 301. Each SOT word contains a field indicating the position of the block in the sequence of such blocks into which the transmission is divided. This count is from 1 to 8. Each SOT word also contains a binary count of the total number of usable background data words to be contained in the transmission. This count does not include the SOT, EOT and fill-in words, hence the maximum is 496. This count is set to zero in subsequent background data blocks. (b) End of Transmission Word The last word of each 64-word data block is an End Of Transmission (EOT), label 302. (c) Fill-in Word The 62 usable data words of each map background data block contain the positional, character and control information used by the EHSI to construct the map background. If the final block of the transmission contains less than 62 useful words, it is padded with fill-in words, label 000, and terminated with the End of Transmission word at position 64. (d) Data Types Seven types of data are transmitted as part of the EFIS background data: Control Words (SOT, EOT, Filler), Position, Distance, Length, Angular, and Discrete. (e) Data Type Word Groups Three types of background data word groups may be transmitted: vector word groups, symbol word groups, and map reference word groups. Word groups are formatted as a sequence of data labels where the label field is used to encode the data type and the sign/status matrix is used to designate the start and end of the group, as well as to identify special control words, as follows:
31 0 0 1 1
BIT 30 1 0 1 0
WORD DESCRIPTION First word of data type group Intermediate position or character words Control word, symbol rotation or vector conic data Last word of data type group
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1
Vector Word Groups
VECTOR WORD GROUP
OCTAL LABEL
DATA FORMATS POSITION
ANGULAR
DISTANCE
CHARACTER
Active Flight Plan
100
Lat, Long
Inbound course, course change
Turn Radius
-
Inactive Flight Plan
040
Lat, Long
Inbound course, course change
Turn Radius
-
Active Flight Plan Changes
300
Lat, Long
Inbound course, course change
Turn Radius
-
Offset Flight Plan
020
Lat, Long
Inbound course, course change
Turn Radius
-
Vector Identifiers
160
-
-
-
Offset Distance + Direction
Vector Radial
140
Lat, Long
-
-
-
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2
Symbol Word Groups
SYMBOL WORD GROUPS
OCTAL LABEL
DATA FORMATS POSITION
ANGULAR
LENGTH
CHARACTER
VORTAC (VOR/DME)
250
Lat, Long
-
-
Identifier
VOR
350
Lat, Long
-
-
Identifier
DME/TACAN
230
Lat, Long
-
-
Identifier
Airport
270
Lat, Long
-
-
Identifier
Origin/Dest Airport
170
Lat, Long
-
-
Identifier
Flight Plan Waypoint
330
Lat, Long
-
-
Identifier + Constraints
Conditional Waypoint
104
Lat, Long
-
-
Identifier
Active Waypoint
070
Lat, Long
-
-
Identifier + Constraints
Active Conditional Waypoint
304
Lat, Long
-
-
Identifier
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SYMBOL WORD GROUPS
OCTAL LABEL
DATA FORMATS POSITION
ANGULAR
LENGTH
CHARACTER
Rotated Airport
254
Lat, Long
Runway Heading
-
Airport ID Runway ID
Runway
054
Lat, Long
Runway Heading
Paved Length
Airport ID Runway ID
Altitude Profile Point
004
Lat, Long
-
-
Identifier
Selected Reference Point
204
Lat, Long
-
-
-
SRP Distance
244
Lat, Long
Distance
Displayed Distance
Holding Pattern Left
034
Lat, Long
Inbound Course
-
-
Holding Pattern Right
354
Lat, Long
Inbound Course
-
-
Proc Turn Left
134
Lat, Long
Inbound Course
-
-
Proc Turn Right
234
Lat, Long
Inbound Course
-
-
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3
Map Reference Word Groups
MAP REFERENCE WORD GROUP
N.
OCTAL LABEL
DATA FORMAT POSITION
ANGULAR
LENGTH
CHARACTER
Plan Mode Ref Pt Lat
264
Lat
-
-
-
Plan Mode Ref Pt Long
164
Long
-
-
-
Discrete Word 1
364
-
-
-
-
Discrete Word 2
014
-
-
-
-
Fuel Computer The Fuel Computer (FC) provides fuel contents and/or fuel flow to the FMS following the ARINC 429 specifications. The FMS is configurable for single, dual or no FC inputs. The FMS is configurable for fuel inputs displayed either in kilograms or pounds. The FMS is configurable for 1 or 2 labels type for both fuel quantity and fuel flow. The FMS has a configuration item for the value of the most significant bit of the fuel quantity and a separate configuration item for the value of the most significant bit of the fuel flow. The FMS has a configuration item for Source Destination Identifier (SDI OFF/ON) for both fuel quantity and fuel flow.
O.
GPS Sensor (1)
ARINC 743A Standard GPS Receiver which includes CMA-3024, CMA-3012 and CMA-3112 (a) Digital GPS to FMS Link Summary
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The FMS decodes the GPS sensor unit the labels listed in the following table, according to the ARINC 743A specifications. LABEL-EQUIP ID 273-00B 076-00B 101-00B 102-00B 103-00B 110-00B 120-00B 111-00B 121-00B 112-00B 130-00B 133-00B 136-00B 140-00B 165-00B 166-00B 174-00B 247-00B 260-00B 150-00B 162-00B 343-00B 370-00B
DESCRIPTION GPS Sensor Status GPS Altitude GPS HDOP GPS VDOP GPS Track Angle GPS Latitude GPS Latitude Fine GPS Longitude GPS Longitude Fine GPS Ground Speed GPS HIL (Integrity) GPS VIL (Integrity) GPS Vertical Fom GPS UTC Fine GPS Vertical Velocity GPS N/S Velocity GPS E/W Velocity GPS Horizontal Fom GPS Date GPS UTC GPS Destination WPT ETA GPS Destination WPT HIL GPS Height
NOTE: The labels are shown in their transmission order. This order must be respected by the GPS receiver. Labels 162 and 343 are sent when applicable.
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(b) FMS to Digital GPS Link Summary This section provides information on the ARINC 429 outputs that are supplied by the FMS to the GPS sensor. The outputs are formatted to follow the ARINC 743A specifications. LABEL-EQUIP ID 041-002 042-002 143-002 144-002 146-002 150-002 152-002 170-002 203-002 210-002 260-002 310-002 311-002 312-002 313-002 314-002
DESCRIPTION Initialize Latitude Initialize Longitude Destination WPT Long. Destination WPT Lat. SV Deselect A GMT (UC) Destination WPT ETA SV Deselect B Pressure Altitude True Air Speed Date Latitude Longitude Ground Speed Track Angle True True Heading
NOTES: 1. These words are transmitted in burst of 2 seconds duration on power-up and when a new position is entered. 2. These words are transmitted in burst of 3 seconds duration when doing a predictive RAIM request. (c) GPS Time Mark input (d) The GPS time mark discrete provides for the GPS to be synchronized with other aircraft systems.
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(2)
ARINC 743 Standard GPS Receiver which includes HONEYWELL, HG2021GD02, HG2021GD03 and TRIMBLE TASMAN TA-12. (a) Digital GPS to FMS Link Summary The GPS sensor unit provides the labels listed in the following table to the FMS, with respect to the ARINC 743 specification. LABEL-EQUIP ID 273-00B 076-00B 101-00B 102-00B 103-00B 110-00B 120-00B 111-00B 121-00B 112-00B 130-00Ba 136-00B 165-00B 166-00B 177-00B 247-00B 260-00B 150-00B 140-00B 162-00B 343-00B
DESCRIPTION GPS Sensor Status GPS Altitude GPS HDOP GPS VDOP GPS Track Angle GPS Latitude GPS Latitude Fine GPS Longitude GPS Longitude Fine GPS Ground Speed GPS HIL (Integrity) GPS Vertical Fom GPS Vertical Velocity GPS N/S Velocity GPS E/W Velocity GPS Horizontal Fom GPS Date GPS UTC GPS UTC Fine GPS Destination WPT ETA GPS Destination WPT HIL
NOTE: The labels are shown in their transmission order. This order must be respected by the GPS receiver. Labels 162 and 343 are sent when applicable.
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(b) FMS to Digital GPS Link Summary This section provides information on the ARINC 429 outputs that are supplied by the FMS to the GPS sensor. The outputs are formatted to follow the ARINC 743 specifications. LABEL-EQUIP ID 041-002 042-002 125-002 126-002 127-002 143-002 144-002 150-002 152-002 203-002 210-002 260-002 310-002 311-002 312-002 313-002 314-002
DESCRIPTION Initialize Latitude Initialize Longitude Gmt (UC) SV Deselect A SV Deselect B Destination WPT Long. Destination WPT Lat. GMT (UC) Destination WPT ETA Pressure Altitude True Air Speed Date Latitude Longitude Ground Speed Track Angle True True Heading
These words are transmitted in burst of 2 seconds duration on power-up and when a new position is entered.
2. These words are transmitted in burst of 3 seconds duration when doing a predictive RAIM request. (c) GPS Time Mark input The GPS time mark discrete provides for the GPS to be synchronized with other aircraft systems.
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P.
Flight Recorder When configured, this equipment transmits data for the ACMS and the lables defined below: LABEL-EQUIP ID 44-002 45-002 45-002 276-002a 347-002a 350-002a 351-002a 352-002a 353-002a 355-002a 356-002a 357-002a 362-002a 363-002
Q.
DESCRIPTION First 2 characters of Approach Procedure Name 3rd and 4th characters of Approach Procedure Name Last 4 characters of Approach Procedure Name FMS VNAV Status discrete word Maintenance VOR/DME latitude Maintenance GPS latitude Maintenance GPS longitude Maintenance DME latitude Maintenance DME longitude Maintenance VOR/DME longitude Maintenance Inertial latitude Maintenance Inertial longitude Desired vertical path angle for approach VNAV Target altitude
Repeater This equipment relays data from selected input port to selected output port. NOTE:
The ARINC 429 labels received from a single ARINC 429 input bus (e.g. Single interface equipment) can be configured to be repeated. The Reapeater can be configured to any ARINC 429 output bus.
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R.
System Management Computer (1)
Digital SMC to FMS Link Summary The SYSTEM MANAGEMENT COMPUTER (SMC) provides TOTAL FUEL CONTENTS and FUEL FLOW RATE to the FMS following the ARINC 429 specifications. LABEL-EQUIP ID 247-048 347-048
The Chelton VN-411B used to be known as the Bendix King NAV receiver 411B. The Collins NAV-45000 combines a VOR/ILS/MB and an ADF receiver in the same enclosure. The same interface protocol is compatible with Chelton VN411B and Collins VIR-432 and NAV-4500.
(1)
Digital NAV to FMS Link Summary The NAV or VOR RECEIVER provides the frequency of the VOR station tuned, the VOR omni bearing to the FMS following the ARINC specifications. LABEL-EQUIP ID 034-011 222-011
(2)
DESCRIPTION VOR/ILS Frequency VOR Bearing Word
TX RATE 200 ms 200 ms
Digital FMS to NAV Link Summary The NAV requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the NAV are listed below. The outputs listed below are formatted in accordance with the General Aviation Manufacturers Association (GAMA) specifications.
LABEL-EQUIP ID 034-002
DESCRIPTION VOR/ILS Frequency
TX RATE Burst/200 MS
REMARKS Burst when backup CP installed
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T.
VOR RECEIVER (ARINC 579) (1)
Digital VOR to FMS Link Summary The VOR RECEIVER provides the VOR omni bearing to the FMS following the ARINC 579 specifications. LABEL-EQUIP ID 222-579
U.
DESCRIPTION VOR Bearing Word
TX RATE 200 ms
X-FMS for cross-talk (ARINC 429) (1)
Digital X-FMS to FMS Link Summary In multiple-FMS installations, the FMS will transmit/accept the following labels to/from the offside FMS(s), in accordance with proprietary protocol specifications for cross-talk. LABEL-EQUIP ID 010-002x 011-002x 013-002x 014-002x 015-002x 016-002x 017-002x 020-002x 021-002x 022-002x 060-002x 061-002x 062-002x 063-002x 064-002x 065-002x 066-002x 067-002x 102-002x 205-002x 206-002x 212-002x 213-002x 226-002x 274-002x 277-002x 330-002a
DESCRIPTION Best Sensor Latitude Best Sensor Longitude Best Sensor Track Angle Best Sensor Ground Speed True Air Speed Heading ADC Altitude Best Sensor Latitude Fine Best Sensor Longitude Fine QNH Block Transfer Data Word Block Transfer Data Word Best Sensor Accuracy (MS) GPS HIL (Integrity) Inbound Holding Course INS Time In NAV INS Actual Navigation Performance (ANP) Best Sensor Accuracy (LS) Selected Altitude Mach Number Computed Air Speed/Indicated Air Speed Vertical Speed Static Air Temperature Block Transfer Control Word Cross-Talk Control/Status Word EFIS Status Word System Altitude
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EXPECTED RATE 1sec 1sec 1sec 1sec 100 msec 50 msec 100 msec 1sec 1sec 50 msec as required as required 1sec 1sec 1sec (1) 5-10 sec 50 msec 1sec 1sec 1sec 1sec 1sec 1sec as required 50 ms 50 ms 100 msec
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(a) This word is received only when the cross-side FMS is performing an entry procedure into a holding pattern or is on a flight plan leg terminated by a holding fix. (2)
FMS to Digital X-FMS Link Summary The ARINC 429 labels are the same as listed in (1) above.
Digital FMS to ELT Link Summary The ELT requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the ELT are listed below. The outputs listed below are formatted in accordance with the General Aviation Manufacturers Association (GAMA) specifications. LABEL-EQUIP ID 310-002x 311-002x
DESCRIPTION Present Position Latitude Present Position Longitude
TX RATE 100 msec 100 msec
W. Bendix King MST67A ATC Transponder (ARINC 429) (1)
Digital FMS to XPDR Link Summary The transponder requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the transponder are listed below. LABEL-EQUIP ID 031-002
DESCRIPTION ACTRBS
TX RATE 100 - 200 msec or Burst
In addition to the above label, the CMA-9000 outputs the following labels to the ATC to support the Elementary Surveillance (ELS) (flight identification) requirement. LABEL-EQUIP ID 233-002 234-002 235-002 236-002
DESCRIPTION Flight ID (Char1/Char2) Flight ID (Char3/Char4) Flight ID (Char5/Char6) Flight ID (Char7/Char8)
TX RATE 1 sec 1 sec 1 sec 1 sec
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(2)
Digital XPDR to FMS Link Summary This section describes the ARINC 429 data words and transmission protocol of the inputs to the CMA-9000 from the transponder.
LABEL-EQUIP ID 350-018
X.
DESCRIPTION Mode S BIT Automatic Message Mode
TX RATE 500 – 1000 msec
Collins TDR 94D ATC Transponder (ARINC 429) (1)
Digital FMS to XPDR Link Summary The transponder requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the transponder are listed below. The CMA-900 will transmit transponder labels in either continuous or burst tuning modes (installation configurable).
LABEL-EQUIP ID 031-002
DESCRIPTION ACTRBS
TX RATE 100 - 200 msec or Burst
In addition to the above label, the CMA-9000 outputs the following labels to the ATC. LABEL-EQUIP ID 233-002 234-002 235-002 236-002 (2)
DESCRIPTION Flight ID (Char1/Char2) Flight ID (Char3/Char4) Flight ID (Char5/Char6) Flight ID (Char7/Char8)
TX RATE 1 sec 1 sec 1 sec 1 sec
Digital XPDR to FMS Link Summary This section describes the ARINC 429 data words and transmission protocol of the inputs to the FMS from the transponder.
LABEL-EQUIP ID 031-018b 350-018b
DESCRIPTION Transponder Reply Word Transponder diagnostics Word
TX RATE 500 – 1000 msec 500 – 1000 msec
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Y.
Chelton VC-401B VHF COM radio (ARINC 429) The Chelton VC-401B used to be known as the Bendix-King VC-401B VHF COM radio. The Chelton VC-401B supports only a frequency step of 25kHz. (1)
Digital FMS to VHF Link Summary The VHF radio requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the VHF radio are listed below.
LABEL-EQUIP ID 030-002
(2)
DESCRIPTION VHF COM Frequency (25 kHz Frequency Steps)
TX RATE 100 - 200 msec or Burst
Digital VHF to FMS Link Summary This section describes the ARINC 429 data words and transmission protocol of the inputs to the FMS from the VHF radio. LABEL-EQUIP ID 030-016
Z.
DESCRIPTION VHF COM Frequency (25 kHz steps)
TX RATE 100 – 200 msec
Chelton VC-401C VHF Comm (ARINC 429) The Chelton VC-401C used to be known as the Bendix-King VC-401C VHF COM radio. The Chelton VC-401C supports both frequency steps of 25kHz and 8.33 kHz. (1)
Digital FMS to VHF Link Summary The VHF radio requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the VHF radio are listed below.
LABEL-EQUIP ID 030-002 047-002
DESCRIPTION VHF COM Frequency (25 kHz Steps) VHF COM Frequency (8.33 kHz Steps)
TX RATE 100 - 200 msec or Burst 100 - 200 msec or Burst
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(2)
Digital VHF to FMS Link Summary This section describes the ARINC 429 data words and transmission protocol of the inputs to the FMS from the VHF radio. LABEL-EQUIP ID 030-016 047-016
DESCRIPTION VHF COM Frequency (25 kHz frequency steps)
Digital FMS to ADF Link Summary The ADF requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the ADF are listed below.
(2)
LABEL-EQUIP ID 032-002
DESCRIPTION ADF Frequency
TX RATE 200 msec
320-002
Magnetic Heading
50 msec
Digital ADF to FMS Link Summary This section describes the ARINC 429 data words and transmission protocol of the inputs to the FMS from the ADF radio. LABEL-EQUIP ID 032-012 162-012
DESCRIPTION ADF Frequency Relative Bearing
TX RATE 200 msec 67.5 msec
REMARKS echo
BB. Marconi Selenia SRT-651/N-A V/UHF radio (ARINC 429) Either a single or no V/UHF is installation configurable via maintenance pages. After a V/UHF is configured, the output can be moved to any ARINC 429 output bus. (1)
Digital FMS to V/UHF Link Summary The V/UHF requires only a portion of the data available on the ARINC 429 link to which it is attached. The labels of interest to the V/UHF are listed below.
LABEL-EQUIP ID 271-002b 272-002b 273-002b
DESCRIPTION V/UHF Command Word 1 V/UHF Command Word 2 V/UHF Command Word 3
MAX TX RATE 200 msec 200 msec 200 msec
REMARKS Tuning and mode setting Tuning and mode setting Tuning and mode setting
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(2)
Digital V/UHF to FMS Link Summary This section describes the ARINC 429 data words and the transmission protocol of the inputs to the FMS from the V/UHF radio.
LABEL-EQUIP ID 271-017 272-017 273-017 274-017
DESCRIPTION V/UHF Status Word 1 V/UHF Status Word 2 V/UHF Status Word 3 V/UHF Status Word 4
CC. TEAM Audio Management Unit AMU (ARINC 429) (1)
Digital FMS to AMU Link Summary The labels of interest to the AMU are listed below. NOTE: These labels are only output to the AMU when the FMS is in control of the AMU.
LABEL-EQUIP ID 051-002b 053-002b 055-002b 155-002b 160-002b 275-002b
(2)
DESCRIPTION COM 1/2 Volume NAV 1/2 Volume Intercom Volume DME 1/2 or TACAN 1/2 Volume ACM CFM
MAX TX RATE 300 ms 300 ms 300 ms 300 ms 300 ms 300 ms
REMARKS Volume setting Volume setting Volume setting Volume setting Aircraft configuration settings Common Frequency mode
Digital AMU to FMS Link Summary This section describes the ARINC 429 data words and the transmission protocol of the inputs to the FMS from the AMU.
LABEL-EQUIP ID 051-136 053-136 055-136 155-136 270-136
DESCRIPTION COM 1/2 Volume NAV 1/2 Volume Intercom Volume DME 1/2 or TACAN 1/2 Volume AMU Status
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
DD. Aircraft Piloting Inertial Reference System (APIRS SFIM) (1)
Digital (APIRS SFIM) to FMS Link Summary This input is for the purpose of Kalman Filtered navigation mode only, normal AHRS input requires heading only (magnetic, true). The labels processing on this input will synchronize the APIRS labels with the GPS Time Mark signal for use by the Kalman Filter. LABEL-EQUIP ID 006-005 273-005 320-005 324-005 325-005 326-005 327-005 330-005 331-005 332-005 333-005
DESCRIPTION Major/Minor Cycle # General Operating Mode Status Heading Angle Pitch Angle Roll Angle Pitch Rate Roll Rate Yaw Rate Longitudinal Acceleration Lateral Accelleration Normal Acceleration
Digital DMAP to FMS Link Summary The data input to the FMS from the DMAP comprises multi-waypoint flight plans, or singlewaypoint (direct-to) flight plans. The inputs are formatted in accordance with the General Aviation Manufacturers Association (GAMA) specifications.
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DESCRIPTION Data Record Header Message Checksum Message Character 7-9 Message Character 10-12 Message Control Word Message Character 1-3 Message Character 4-6 Waypoint Latitude Waypoint Longitude Manufacturer Ident Code
Transmitted once at the start of each route transmission.
NOTE 2:
The set of labels (303, 304, 305, 301, 302, 306, 307 and 113) specify the first navigation point are transmitted immediately after Label 074. Each set of labels specifying successive navigation points will follow at intervals of 100 milliseconds.
NOTE 3: 5
Not transmitted by the DMAP ELBIT unit.
(a)
Example of Transmission The transmission of a normal or Direct-To flight plan from the DMAP to the FMS will follow the example below. A Direct-To flight plan will consist of a single waypoint as follows: T = 0.0 SECONDS (DIRECT-TO WAYPOINT, NO IDENTIFIER) 074 DATA RECORD HEADER 303 MESSAGE CONTROL WORD 304 WPT IDENT CHAR 1-3 (CHAR 1, 2, 3 = NUL) 305 WPT IDENT CHAR 4-6 (CHAR 4, 5, 6 = NUL) 301 WPT IDENT CHAR 7-9 (CHAR 7, 8, 9 = NUL) 302 WPT IDENT CHAR 10-12 (CHAR 10, 11, 12 = NUL) 306 WPT LATITUDE 307 WPT LONGITUDE 113 MESSAGE CHECKSUM
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FF. Data Concentrator (1)
Digital FMS to Data Concentrator Link Summary The Data Concentrator will receive data from the ARINC 429 link of the FMS but does not use any data itself. The inputs needed will be configured on the input port connected to the Data Concentrator. The labels received are described in the sections for those individual equipment types. NOTE: The Data Concentrator only receives data. If some equipment configured for the Data Concentrator has outputs, those must be configured onto output busses in the normal manner.
(2)
Digital Data Concentrator to FMS Link Summary The FMS receives data from the Data Concentrator via up to two dedicated ARINC 429 links.
The labels listed below assume ADF, DME, NAV and ADC are installed on the Data Concentrator, this is for example only, the actual labels expected will depend on the equipment configuration. LABEL-EQUIP ID
DESCRIPTION
032-012
ADF Frequency
TX RATE MAX RATE ALLOWED 135 msec
034-011
VOR/ILS Frequency
150 msec
035-009
DME Frequency
135 msec
162-012 202-009 203-006 204-006 210-006 222-011
ADF Bearing DME Distance Standard Altitude 1013.25 Baro Corrected Altitude True Airspeed VOR Omnibearing
45 msec 135 msec 20 Hz 20 Hz 20 Hz 100 msec
REMARKS
radio feedback radio feedback radio feedback, NOTE 1 NOTE 1 NOTE 2 NOTE 2 NOTE 2
NOTE 1:
DME is a special equipment and can be installed only on one side of the Data Concentrator (per equipment). All others may have redundant input on both sides.
NOTE 2:
These parameters are transmitted or not depending on the ADC connected.
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GG. Radio Altimeter (ARINC 429) (1)
Radio Altimeter to FMS Link Summary The RADIO ALTIMETER provides RADIO ALTITUDE to the FMS following the ARINC 429 specifications. LABEL-EQUIP ID 164-007
Digital EGI to FMS Link Summary This section describes the ARINC 429 data words and the transmission protocol of the inputs to the FMS from the LN-100GT EGI. LABEL-EQUIP ID 010-00Be 011-00Be 076-00Be 103-00Be 110-00Be 111-00Be 112-00Be 120-00Be 121-00Be 150-00Be 163-004e 166-00Bf 171-004e 172-004e 174-00Bf 214-004e 220-004e 240-004e 240-00Be 243-004e 250-00Be 251-00Be 260-00Be 265-00Be 270-004e 270-004e 270-00Be 271-00Be
DESCRIPTION GPS SA/AS Key Status GPS Integrity GPS Altitude Mean Sea Level GPS Ground Track GPS Latitude (MSW) GPS Longitude (MSW) GPS Ground Speed GPS Latitude (LSW) GPS Longitude (LSW) GMT Time UTC Navigation Time North South GPS Speed Hybrid Quality Factor Pure Inertial Quality Factor East West GPS Speed Alignment Counter Baro Inertial Altitude Latitude, Ppos Hyb GPS (LSW) GPS Est Horizontal Position Error Longitude, Ppos Hyb GPS (LSW) GPS Discrete Data #2 GPS Discrete Data #3 GPS Date GPS Vertical Velocity INS Output Status Label Maintenance Label GPS Discrete Data No 1 GPS Satellite Used 1-16
DESCRIPTION GPS Satellite Used 17-32 GPS Dilution Factor, VDOP HDOP GPS Dilution Factor, PDOP GDOP Velocity North, Hybrid GPS Velocity East, Hybrid GPS Latitude, Ppos Hyb GPS (MSW) Longitude, Ppos Hyb GPS (MSW) Latitude Pure Inertial Longitude Pure Inertial True Heading Wind speed Wind direction Drift Angle Pitch Angle Roll Angle Satellites visible X Lever Arm to GPS Antenna (+ Forward) Z Lever Arm to GPS Antenna (+ Down) Yaw Boresight Pitch Boresight Roll Boresight Y Lever Arm to GPS Antenna (+ Right) RAIM integrity AAIM integrity Velocity Vertical, Pure Inertial Velocity North, Pure Inertial Velocity East, Pure Inertial
Digital FMS to EGI Link Summary This section describes the ARINC 429 data words and the transmission protocol of the outputs from the FMS to the LN-100GT EGI. LABEL-EQUIP ID 005-002s 006-002s 041-002 042-002 054-002s 055-002s 150-002 203-002 210-002 260-002s 270-002b 271-002a 304-002s 306-002
DESCRIPTION Set Latitude WGS84, (LSW) Set Longitude WGS84, (LSW) Set Latitude WGS84, (MSW) Set Longitude WGS84, (MSW) Delta Latitude Update/ Pure INS Delta Longitude Update/ Pure INS GMT Time, UTC Pressure Altitude (standard) True Airspeed Date Discrete Data Input Status Discrete Data Input Status Magnetic variation Latitude INI/END
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
LABEL-EQUIP ID 307-002 340-002s 342-002s 343-002s 344-002s 345-002s 346-002s II.
DESCRIPTION Longitude INI/END X Lever Arm to GPS (+Fwd) Z Lever Arm to GPS Antenna (+Dwn) Yaw Boresight Entry Pitch Boresight Entry Roll Boresight Entry Y Lever Arm to GPS Antenna (+Rt)
Digital EGI to FMS Link Summary This section describes the ARINC 429 data words and the transmission protocol of the inputs to the FMS from the SIGMA50H EGI. LABEL-EQUIP ID 010-00Bf 011-00Bf 076-00Bf 103-00Bf 110-00Bf 111-00Bf 112-00Bf 120-00Bf 121-00Bf 150-00Bf 163-004f 166-00Bf 171-004f 172-004f 174-00Bf 214-004f 220-004f 240-004f 240-00Bf 243-004f 260-00Bf 265-00Bf 270-004f 270-004f 270-00Bf 271-00Bf 276-00Bf 277-00Bf 301-004f 302-004f 306-004f
DESCRIPTION GPS SA/AS Key Status GPS Integrity GPS Altitude Mean Sea Level GPS Ground Track GPS Latitude (MSW) GPS Longitude (MSW) GPS Ground Speed GPS Latitude (LSW) GPS Longitude (LSW) GMT Time UTC Navigation Time North South GPS Speed Hybrid/GPS Quality Factor Hybrid/DVS Quality Factor East West GPS Speed Alignment Counter Baro Inertial Altitude Latitude, Ppos Hyb GPS (LSW) GPS Est Horizontal Position Error Longitude, Ppos Hyb GPS (LSW) GPS Date GPS Vertical Velocity INS Output Status Label Maintenance Label GPS Discrete Data No 1 NB. GPS Satellite Used GPS Dilution Factor, VDOP HDOP GPS Dilution Factor, PDOP GDOP Velocity North, Hybrid GPS Velocity East, Hybrid GPS Latitude, Ppos Hyb GPS (MSW)
Latitude Pure INS/DVS Longitude Pure INS/DVS True Heading Wind Speed
40 msec 40 msec 40 msec 160 msec
Wind Direction
160 msec
Drift Angle Pitch Angle Roll Angle X Lever Arm to GPS Antenna (+ Forward) Z Lever Arm to GPS Antenna (+ Down) Yaw Boresight Pitch Boresight Roll Boresight Y Lever Arm to GPS Antenna (+ Right) RAIM Integrity AAIM Integrity Velocity Vertical, INS/DVS Velocity North, INS/DVS Velocity East, INS/DVS
Digital FMS to EGI Link Summary This section describes the ARINC 429 data words and the transmission protocol of the outputs from the FMS to the LN-100GT EGI. LABEL-EQUIP ID 007-002 054-002s 055-002s 270-002b 271-002a 306-002 307-002 340-002s 342-002s 343-002s 344-002s 345-002s 346-002s
DESCRIPTION Initial Altitude Delta Latitude Update/ Pure INS Delta Longitude Update/ Pure INS Discrete Data Input Status Discrete Data Input Status Latitude INI/END Longitude INI/END X Lever Arm to GPS (+ Forward) Z Lever Arm to GPS (+ Down) Yaw Boresight Entry Pitch Boresight Entry Roll Boresight Entry Y Lever Arm to GPS Antenna (+ Right)
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
JJ. Weather Radar (ARINC 429) (1)
Weather Radar to FMS Link Summary This section describes the transmission protocol of the inputs to the FMS from the weather radar via ARINC 429.
LABEL-EQUIP ID 360-008 361-008
DESCRIPTION WXR joystick Lat (BNR) WXR joystick Lon (BNR)
MAX RATE 160 msec 160 msec
REMARKS Latitude +/-90 deg Longitude +/-180 deg
KK. Doppler Velocity Sensor DVS (ARINC 429) NOTE: The installation of a DVS is not allowed with an approved FMS. (1)
Doppler Velocity Sensor (RDN85 and ANV353 DVS) to FMS Link Summary This section describes the inputs to the FMS from the Doppler Velocity Sensor (DVS) via ARINC 429.
LABEL-EQUIP ID 050-025
DESCRIPTION DVS Longitudinal speed (BNR)
051-025
DVS Lateral speed (BNR)
052-025
DVS Vertical speed (BNR)
343-025 344-025 345-025 353-025
DVS Boresight YAW (BNR) DVS Boresight PITCH (BNR) DVS Boresight ROLL (BNR) DVS status word
LL. Personnel Locator System (ARINC 429) The FMS decodes the range and the steering of the PLS waypoint from the labels in table below. (1) Cubic AN/ARS6 PLS LABEL-EQUIP ID 202-(300) 222-(300)
DESCRIPTION PLS range PLS steering
Rate 200 msec 200 msec
NOTE: 1. PLS Range is the distance between the aircraft and the PLS position. 2. PLS Bearing (steering) is the bearing to the PLS position with the heading of the aircraft as reference (+- 90 degrees). (2)
NOTE: 1. PLS Range is the distance between the aircraft and the PLS position. 2. PLS Bearing is the bearing to the PLS position with the heading of the aircraft as reference (+- 180 degrees).
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MM. Thomson NC-12B TACAN (ARINC 429) This section describes the ARINC 429 data words and the transmission protocol of the outputs from the NC 12B Thomson TACAN used by the FMS. LABEL-EQUIP ID
DESCRIPTION
033 201 222
TACAN Channel TACAN Distance TACAN Omni bearing
Rate (msec) 50 msec 50 msec 50 msec
NN. Data Loader unit Targa (RS-422) This section describes the RS-422 data words and the transmission protocol of the interface Targa data loader and CMA-9000 FMS. When the Targa DLU is configured, the data loader unit sends/receives data to/from the FMS. The communication between the DLU and FMS takes place over the RS422 serial link at 38.4 kbps using the Packet Data Protocol PDP/3-DOS. In order to load files from the Targa DLU to the FMS, the following file extension convention shall be used (otherwise, file transfer is not performed): DATA TYPE USER_DATA NAV_DATA CUSTOM_DATA RADIO_DATA CONFIG_0 CONFIG_1 CONFIG_2 CONFIG_3 PRECAN _MSG MAGVAR_MODEL OEI_MODEL
DESCRIPTION User database Navigation database Custom database Radio Tuning libraries and GSM library OP CSCI configuration file OP CSCI configuration file OP CSCI configuration file OP CSCI configuration file Precanned Messages Magnetic variation model database OEI model data tables
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
OO. Helicopter Communication System (HCS) Software Protocol (RS-422) Future Growth This section describes the RS-422 data words and the transmission protocol of the HCS interface and CMA-9000 FMS. (1)
HCS Software Protocol (a) Transmission of Data Frames The information interchange is based on simple data frames that start with the ASCII character STX and end with an ETX. The maximum frame length including ETX and STX is 512 characters. Data can be sent without delay between the characters. The receiving system has to read in the complete frame as fast as the data are sent. There is no flow control mechanism to stop the sending station. (b) Polling The FMS polls the Helicopter Communication System periodically. That means a Command or Request Frame is sent by the FMS and the HCS answers in an Answer Frame. Serial Message Frame Types between the HCS and the FMS: FRAME TYPE Command/Request Frame Answer Frame
DESCRIPTION The FMS sends a Command or Request Frame to the HCS. The HCS answers in an Answer Frame
(c) Command / Request Frame If the FMS sends a Command Frame to the HCS, the HCS will respond with an Answer Frame that consists of STX, Status Code (0,1,A,B,@), Attention Code, Checksum and ETX. The FMS can decide whether the command has been accepted depending on the Status Code. If the FMS sends a Request Frame, the HCS responds with an Answer Frame that may have the result of a previous command of this type in the Answer Area. If not, the Status Code informs the FMS that the Command is not yet processed. Command/Request Frame Message Format from the HCS to the FMS
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BYTE NO. 0 1 2 to 1+PL
2+PL to 3+PL 4+PL
CONTENTS OF THE COMMAND/REQUEST FRAME STX Command/Request Parameter Area
Checksum ETX
DESCRIPTION Start of Text Command Code ( '@','A'-'Z') or Request Code ('a'-'z') The Parameter Frame contains the necessary parameters of a command. (Parameter Length (PL) is the length of the Parameter Area) A checksum transmitted in character 2+PL and 3+PL of the Command/Request Frame. End of text
(d) Answer Frame The Answer Frame contains a Status Code that informs the Display Unit about data transmission problems and availability of an answer. Additionally, the FMS gets the information, whether the previously transmitted command could be stored. If an answer is available the Answer Area contains the requested answer data. Every Answer Frame contains an Attention Code. If the character is '@' there is no further answer available in the HCS. If the Character is between 'a' and 'z', it tells the FMS that an answer is available. This answer can be requested by a Request Frame with a Request Code that is equal to the previously received Attention Code. Answer Frame Message Format from the FMS to the HCS: BYTE NO.
0 1
CONTENTS OF THE ANSWER FRAME STX Status Code
2 to 1+AF
Answer Area
2+AF
Attention Code
3+AF 4+AF 5+AF
Checksum ETX
DESCRIPTION
Start of text The Status Character contains one of the following: - command is stored and will be processed ('0') - command refused ('1') - new answer available ('2') - answer available (‘3’) - no answer available ('4') - transmission error occured ('A') - input buffer overflow ('B') - ‘@’ command received (‘@’) The Answer Frame contains the necessary parameters of a command. (Answer Frame (AF) is the length of the Parameter Frame) If an answer has become available, the Attention Code contains the value of the Request Code that can be used to order the Answer Frame. Otherwise, a '@' is inserted. A checksum transmitted in character 3+AF and 4+AF of the Answer Frame. End of text
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(e) Calculation of Checksum In addition to the parity bit that will be transmitted with each character, at the end of a frame a Checksum is inserted. The Checksum is calculated over all characters (7 bit codes) of the data frame excluding STX and ETX. The resulting Checksum is the least 8 significant bits value of the sum over the character codes. The Checksum is transmitted as a two character wide hexadecimal number. As hexadecimal digits the characters '0' to '9' and 'A' to 'F' should be used. The most significant digit is transmitted first. (f)
High Level Software Protocol between HCS and Display Unit 1
Commands and requests sent to the HCS by the FMS:
Commands and requests consist of several information units, which depend on the type of command, request or answer. 2
Format of the Application Data:
In this chapter the format of the application messages is described, which are sent from the FMS to the DC and vice versa. The application messages are inserted in the parameter area of the command ‘S’= ‘ Send a normal message’, when sending a message from the FMS to the DC or inserted in the answer area of the request ‘r’ = ‘Receive a message’, when a message has been received from the DC. The length of the complete message is restricted for Short Messages to 140 bytes. The length of the application messages can be up to 108 characters in direction from the DC to the FMS and up to 66 characters from the FMS to the DC. The last direction is restricted to the length of 66 characters, because the HCS adds to each message characters with information, got by the ‘P’ command, about geographical position, date, time, altitude and remaining flight time according the fuel level. The application data exchanged between DC and FMS and vice versa are passed through by the HCS unchanged. 3
Information Flow:
The following information flows demonstrate examples for the main functions of the communication between the HCS and FMS. As examples only the exchanged application data is shown without STX, Checksum and ETX. The requests shown in the following should be repeated by the CDU until the answer frame indicates a valid answer.
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4
Polling of the CDU-Driver on the HCS by the FMS:
The CDU-driver on the HCS is polled by the FMS about every 100 msec. That means every time the FMS sends a command or a request, the HCS sets up the corresponding answer and sends it to the FMS. Whenever a command is received, outstanding answers for this command type are erased. Answers are erased after having been read. The ‘Send Status’ command and the null command can be sent always by the FMS. In general the null command can be replaced by the ‘Send Status’ command to provide the HCS continuously with the latest status. Whenever the FMS-driver on the HCS receives a message, that means a string of characters beginning with STX and ending with ETX, the following activities will be performed at the HCS: It is checked whether the command/request format code is valid. If so the corresponding answer will be set up with status code and answer area, if available. It will be checked whether any different answer is available. If this is so, the next available answer is announced by the corresponding attention code. The answer frame is sent to the FMS. The delay between reception of a frame and answer to this frame is less than 50 msec. PP. Radio Interface Box (RIB) equipment (RS-422) Future Growth (1) This section describes the RS-422 data words and the transmission protocol of the RIB interface and CMA-9000 FMS. The FMS shall communicate with the RIB in accordance to the protocol listed below. (a) Serial Port Radio Equipment The RIB has the capability to control the following serial radio equipment: • • • •
AN/ARC-164 UHF AM Radio; AN/ARC-186 VHF FM Radio; AN/ARC-182 UHF/VHF AM/FM Radio; and AN/ARN-118 TACAN Radio.
(b) Parallel Port Radio Equipment The RIB has the capability to control the following parallel radio equipment: • •
ADF-206 Radio; and VIR-31 NAV Radio.
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QQ. Inertial Reference System (ARINC 429) (1) LTN-92 INS Interface. (a) FMU To/From INU (LTN-92) (See Figure 11, 12 and 13). Figure 11 illustrates the FMU-INU interconnections. The INU high-speed ARINC 429 data bus (HS429) is connected to all three FMUs. This provides ARINC 704 IRS data, including navigation, attitude, acceleration, baro-inertial altitude, true and synthetic magnetic heading, status and maintenance data. The FMU processes the IRS alerts and status messages, which are output on the highspeed data bus, to generate MCDU scratchpad alert messages. The INU CDU bus output provides CDU character data labels, which the FMU processes for the creation of emulated IRS display pages on the MCDU. Under normal operations, the general output bus from each FMU is connected in parallel to the CDU and FMS input ports of its onside INU. The FMU transmits on the general output bus serial data containing both MCDU keystroke and INS initialization data labels. These data labels are automatically recognized by the appropriate INU port without label conflict. Emulated INS-CDU keystrokes are transmitted by the FMU using label 030. The FMU also outputs a status word on label 151 to the INU at a rate of greater than 2 Hz (nominally 10 Hz). The CDU Valid discrete input of the INU is connected to a source of 28 VDC. (b) Primary/Backup FMU-INU Source Switching To enable continued control of an INU in the event of its onside FMU failure, an automatic source select capability is provided to allow the INU CDU and FMS input ports to be switched to a backup FMU (see Figures 10-12). Each INU FMS source select function is controlled by the system valid discrete output of its onside FMU as illustrated in Figures 135 and 136. This source select function is implemented by the Flight Interface Unit (FIU).
INU INU #1 INU #2 INU #3
Primary FMU FMU #1 FMU #2 FMU #3
Backup FMU FMU #2 FMU #3 FMU #1
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(2) ADIRU/ laseref V/LTN-101 (a) The FMS outputs the following labels to the ADIRU: LABEL NUMBER 041-002 042-002 043-002 For ADIRU and laseref V 125-002 For LTN-101 150-002 203-002 210-002 260-002 NOTE:
DESCRIPTION Initial latitude Initial longitude Initial Magnetic Heading UTC
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
MP-9C, 9D MP-11A, 11B, 11C INU2
I/P 11
INU3
I/P 12
MP-9C, 9D MP-11A, 11B, 11C
FMU 1
FMU 3
I/P 9
I/P 12 TP 15C, 15D
INU 1
J1-B 49, 50
MP-9C, 9D MP-11A, 11B, 11C
I/P 9
INU1
I/P 11
INU2
FMU 2 I/P 11
TP 1C, 1D
INU1
I/P 12
INU3
MP 1A, 1B
FMU2
FMU1
FMU1
FMU3
FMU2
FMU3
COMPASS
I/P 9
J1-B 49, 50
INU 3
COUPLER 1
COMPASS
J1-B 49, 50
INU 2
COUPLER 2
HS 429 TRUE & MAG HDG SYNCHRO MAG HDG APFD A
APFD C
APFD B 929-600008-000 056
Figure 12 Heading Sources for Triple FMS/Triple LTN-92 IRS/Dual Compass Couplers (2) ADIRS ( LTN-101, Laseref V or Honeywell ADIRU) interface. (d) FMU To/From ADIRS The ADIRU Nav data bus is fed to all FMUs. The FMS extracts from this bus the INS position, heading, velocities, status data. The FMS configuration pages expects the following physical interconnections when configuring the FMS ARINC 429 input ports receiving ADIRU data: FMU FMU #1 FMU #2 FMU #3
Primary ADIRS (pIRS) ADIRU #1 ADIRU #2 ADIRU #3
Secondary ADIRS (xIRS) ADIRU #2 ADIRU #1 ADIRU #2
Tertiary ADIRS (tIRS) ADIRU #3 ADIRU #3 ADIRU #1
Under normal operations, the ADIRS expects initialization data from its onside FMS. To enable continued control of an ADIRS in the event of its onside FMU failure, the initialization data of all FMUs is sent to all ADIRSs. ADIRS ADIRS #1 ADIRS #2 ADIRS #3
Primary FMU FMU #1 FMU #2 FMU #3
Secondary FMU FMU #3 FMU #1 FMU #2
Tertiary FMU FMU #2 FMU #3 FMU #1
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(e) Initialization Data from FMU to ADIRS Each ADIRS Remote Test Discrete Input is connected to its onside FMS. The user can initiate an ADIRS Remote TEST via the FMS/MCDU IRS DATA page. The FMS accepts the following labels from the ADIRS: Label For Honeywell ADIRU and Laseref V: 126-004b, d For LTN-101: 160-004a 270-004 271-004b, d 310-004 311-004 312-004 313-004 314-004 317-004 320-004 321-004 322-004 324-004 325-004 335-004 350-004b, d 361-004 365-004 366-004 367-004
Description Time In NAV
Expected Rate 640 msec
Time In NAV
1000 msec
IRS discrete status #1 IRS discrete status #2 Inertial position latitude Inertial position longitude Inertial Ground speed Track Angle True True Heading Track angle magnetic Magnetic heading Drift angle Flight path angle Pitch angle Roll angle Track angle rate IRS Maintenance Word Inertial altitude Inertial vertical speed North-South velocity East-West velocity
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
SECTION II INSTALLATION 1.
GENERAL The installation of a CMA-9000 Flight Management System (FMS) in an aircraft requires the approval of the appropriate air/radio division of the government of the country issuing the aircraft certificate of airworthiness. Contact with the appropriate government authority prior to the installation and during the system planning is highly recommended in order to minimize approval problems. If installation assistance is required contact CMC's Avionics Field Engineering Department at the telephone/telex/FAX numbers on the title page of this manual.
2.
EQUIPMENT LOCATION A.
General (1)
The location of a Flight Management System within an aircraft varies with the type of aircraft in which it is installed. A typical location of a single FMS installation is illustrated in Figure 101.
(2) System planning is necessary since the FMS must be correctly interfaced with other aircraft system and instrumentation. (3) The FMS is installed in the cockpit area, located either in the instrument panel or in the pedestal. (4) The FMS is secure with four captive Dzus fasteners. B.
Location of the FMS (1)
C.
Where the FMS is to be used as a flight instrument in the guidance and control of the aircraft, it should be located where it is clearly visible to the pilot with the least possible deviation from his normal position and from his line of vision when he is looking forward along the flight path. Where a dual FMS is to be used as flight instrument in the guidance and control of the aircraft, one unit should be located where it is clearly visible to the pilot and the other to the co-pilot. A typical location of the second co-pilot FMS could be right next to the pilot FMS on the center pedestal.
Selection and location of the GPS receiver and related GPS Antenna (1)
Recommendation of GPS receiver and antenna selection CMC Electronics currently offers three types of GPS receiver: the CMA-3012, the CMA-3112 (embedded in the CMA-900 FMS) and the CMA-3024. The CMA-9000 is certified to work with any of these GPS receivers. The latest generation, the CMA-3024 offers growth capability to WAAS and EGNOS. CMC Electronics recommends the selection of the CMA-3024 GPS receiver and an active GPS antenna.
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(2)
GPS receiver location With all avionic equipment, if at all possible, the GPS receiver should be installed in a pressurized and temperature-controlled area with low levels of humidity and moisture in order to reduce environmental stresses. If necessary, it can be installed in an un-pressurized location. The GPS receiver location is dependent upon the location of the GPS antenna. When using a passive antenna, the GPS receiver should be located on the inside of the aircraft near to the GPS antenna to minimize the RF losses in the interconnecting RF cable. This is particularly important in this case since cables longer than a few meters will quickly degrade the sensitivity and the performance of the GPS receiver. Using active antennas allows much longer cable runs, thus more flexibility in installation.
(3)
GPS antenna selection and location When installed with CMA-3012 or CMA-3024 GPS receiver, the GPS antenna must comply with the requirements of RTCA DO-228 change 1. The GPS antenna should be installed on the outer aircraft skin, nominally along the aircraft centerline and upward in a horizontal attitude in normal flight. Typically the antenna will be installed on the forward topside portion of the aircraft fuselage to minimize the shadowing effect of the vertical stabilizer and wings. Proper antenna separation from RF sources is required to provide the RF isolation necessary to minimize the risks of RF interference. It is recommended to install GPS antennas at least one meter away from other transmitting antennas, and at least one hundred and sixty (160) inches (4.064 meters) from SATCOM and GLOBALSTAR antennas. The two antennas in dual GPS receiver antenna installations should be separated by a minimum of twelve (12) inches (0.3048 meter).
Refer to CMA-3012 Installation Manual GNSSU (3012-GEN-1202) for information related to GPS receiver and antenna installation. Refer to CMA-3024 GNSSU MKII CMC Installation Manual 3024-GEN-0801 publication 929600043-XXX for additional information on GPS receiver and related GPS antenna installation information.
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D.
Active Antenna Installations (CMA-3012 and CMA-3024) Recommended Active Antenna Types
PART NUMBER
DESCRIPTION & NOMINAL RF POWER GAIN
S67-1575-132
GPS antenna, active, 29.5 dB gain
S67-1575-133
GPS antenna, active, 33 dB gain
AT575-143W-TNCF000-RG-29.5-NM
GPS antenna, active, DO-228, 29.5 dB gain
MAXIMUM GAIN OF ANTENNA
MANUFACTURER
32.5 dB
Sensor Systems
36 dB
Sensor Systems
32.5 dB
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Figure 101A Typical CMA-9000 Location (for a helicopter)
0607001
Figure 101B Typical CMA-9000 Location (for an aircraft)
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3.
INTERWIRING AND OUTLINE DRAWING The following figures provide dimensional, mounting, connector pin assignments and other data required to correctly install the CMA-9000.
1.87 ±.05
D38999/20FJ35AN MAITING WITH D38999/26FJ35SN NOTES: (UNLESS OTHERWISE SPECIFIED) 1. APPLICABLE STANDARDS/SPECIFICATIONS: ASME Y14.5M-1994. 2. WEIGHT OF UNIT: 8.5 LBS MAX (3.86 Kg). 3. INPUT POWER : 75W TYP, (98W MAX) WITH HEATER : 45W TYP, (67W MAX) WITHOUT HEATER 4. POWER FOR INTEGRAL LIGHTNING: 8W TYP, (12W MAX) (INCLUDED IN INPUT POWER, NOTE 3. FOR VARIATION WITH SENSE CONFIGURATION, REFER TO FIGURE 4) 5. COLOR OF CONTROL PANEL: MATT BLACK. COLOR OF HOUSING: CHEMICAL FILM, CLEAR.
5.02 ±.05
6. CONTROL PANEL DIMENSIONS PER MS25212 AND AS SHOWN. 7. MOUNTING HARDWARE: DZUS FASTENER 1/4 TURN PF35-53RB. 8. NEOPRENE RUBBER GASKET MAY EXCEED MAXIMUM DIMENSIONS.
5.365
6.75 MAX
5.73 ±.05
6.645 REF
6.375
.215 .200
5.75 MAX .762 ±.020
5.82 ±.02 0612006
Figure 102A CMA-9000 Outline Drawing
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CMC PART NUMBER 230-990123-702 702-990121-803 230-990304-647 230-990304-648
FCI INTERNATIONAL PART NUMBER N/A N/A 805-25F35SN 8D-109F02
N/A
8D-109F03
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PLUG/PIN NO.
SIGNAL NAME
REMARKS
POWER INPUT J1-4 J1-5
+28 VDC I/P HI
Connect to positive side of aircraft +28 Vdc power supply
J1-6 J1-7
+28 VDC I/P LO
Connect to negative side of aircraft +28 Vdc power supply
J1-3
SPARE
Future Growth - On/Off switch (see note below)
J1-53
CHASSIS GROUND
Connect to good aircraft ground plane
J1-54 J1-55
SHIELD RETURN
Internal Ground Connection
J1-127
SPARE
Future Growth - Connect to HOT side of aircraft 115 Vac power supply
J1-128
SPARE
Future Growth - Connect to COLD side of aircraft 115 Vac power supply
IMPORTANT INSTALLATION NOTES: 1) Discrete I/P 1 to 16 supports either open/ground or 0/28 VDC type of discrete signal. The open is defined as >100 Kohms and the ground is defined as <10 ohms. The impedance range between 100 Ohms and 100 kOhms is indeterminate. The 0Vdc is any voltage of less than 3.5 Vdc and the 28 Vdc is any voltage in between 18.5 Vdc and 30.5 Vdc. A remote discrete input tolerates a ground voltage mismatch of up to 2.5 Volts in magnitude measured as the difference in the ground potential between the FMS ground (either Chassis Ground pin 53 or Discrete Input Return pin 49) and the remote grounding point of the discrete input. 2) Discrete O/P 1 to 6 will be able to sink 200 mA each. Discrete O/P 7 and 8 will be able to sink 500 mA each. 3) There is a future growth capability for the CMA-9000 to offer four 28V/Open discrete input type of signal. This will accommodate older installations for which 28V/Open discrete are required (e.g. older LNAV_ON signal). The current plan for this future variation is to have Discrete input #1 to #4 configured as 28V/Open. 4) Future Growth - Pin J1-03 provides the capability for an ON/OFF internal switch on the CMA-9000 FMS. The CMA-9000 is activated (power and display are ON) when appropriate 28VDC circuit breaker is set and the aircraft power bus is energized, providing power to pins 4/5/6/7, and this pin J1-3 is in an Open state (e.g. not connected).This specific discrete accepts only Open/Ground type of signal. The definition of Open state for this pin (this pin only) is a resistivity greater than 1 MOhms. The definition of Ground state for this pin (this pin only) is a resistivity of less than 2 Ohms. Figure 103 FMS Pin Assignments (Sheet 1 of 5)
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PLUG/PIN NO.
SIGNAL NAME
REMARKS
DIMMING INPUTS J1-1
28 VDC Integral Lighting
Connects to cockpit integral lighting potentiometer for 28 VDC Integral Lighting Configuration. Refer to Figure 4 Equipment Identification for appropriate hardware variation.
J1-8
5 VDC Integral Lighting
Connects to cockpit integral lighting potentiometer for 5 VDC Integral Lighting Configuration. Refer to Figure 4 Equipment Identification for appropriate hardware variation.
J1-9
Integral Lighting Return
Connects to cockpit integral lighting potentiometer return (for both 5 VDC and 28VDC Integral Lighting Configuration)
0.5 to 5 VDC AMLCD AMLCD Display Dimming
Connects to cockpit display brightness dimming potentiometer
(Refer to Note 1, Figure 103 Sheet 1 of 5) Discrete inputs 1 through 16 can be configured to one of the following options: TOGA_ON, LAMP_TEST, NAV_COM_CP, SEL_CAPHSI, SEL_FOHSI, ADF_ATC_CP, EMERGENCY, NVG_MODE, NIGHT_MODE, OLEO_AIR, LNAV_ON, TRUE_MAG, (Internal Ground Connection) CENTRAL_CLEAR, APPROACH_ARMED, SDI_1, SDI_2, CFG_SEL_1, CFG_SEL_2, ZEROIZE_1, ZEROIZE_2, MC_FAILED,
Figure 103 FMS Pin Assignments (Sheet 2 of 5)
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Master Caution* (CMC recommendation) Discrete outputs 1 through 8 can be configured to one of the following options : APPR_ARMED, APPR_CAP, GPS_INT, HDG_VALID, LEGCHG, LNAV_VALID, MSG, OFFSET, SYS_VALID, TRUE_ANG, VNAV_VALID, WPT, MCAUTION, pATC, xATC, AMU_CTRL NOTE: Even though the discrete output #1 can be configured, CMC strongly recommends configuring the Discrete Output #1 to Master Caution as the discrete output is also internally connected to the CPU SYSTEM_FAIL signal.
RS-422 ports 2 through 4 can be configured to DLU.
RS-232 RX1 or RS-422 RX1-B RS-422 RX1-A RS-232 TX1 or RS-422 TX1-B RS-422 TX1-A RS-232 GND
This first serial port can be configured to either RS-232 or RS-422 protocol. The port can be configured to one of the following options: DLU or MAINT.
GPS Time Mark Hi GPS Time Mark Lo
GPS Time Mark Pulse High GPS Time Mark Pulse Low
J1-98 J1-99 RS-422 GPS TIME MARK J1-51 J1-52
Figure 103 FMS Pin Assignments (Sheet 3 of 5)
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ARINC Output port 1 through 8 can be configured to one of the equipment listed in Section I sub-section 3.
Figure 103 FMS Pin Assignments (Sheet 5 of 5)
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The following figure illustrates the interwiring specifications.
PIN NO.
SIGNAL NAME
PIN AMERICAN WIRE GAUGE
J1-1
28 VDC INTEGRAL LIGHTING HOT (Sense or Power) 28 VDC INTEGRAL LIGHTING RETURN (Sense or Power)
22
0.1/2 or 0.6/2
22
0.1/2 or 0.6/2
5 VDC AMLCD Display dimming RETURN (hot on J-126)
22
0.1/2
+28 VDC I/P HI +28 VDC I/P LO
22 22
2.0/1 (PER WIRE) 2.0/1 (PER WIRE)
5 VDC INTEGRAL LIGHTING HOT 5 VDC INTEGRAL LIGHTING RETURN
22 22
0.1/2 0.1/2
INPUT CURRENT/ RESISTANCE RATING (Amps/Ohms) See note on Sheet 5 of 5
J1-9
NOTE: Refer to Figure 4 Equipment Identification for appropriate hardware variation and Integral Lighting Configuration. J1-2 J1-4,5 J1-6,7 J1-8 J1-9
NOTE: Refer to Figure 4 Equipment Identification for appropriate hardware variation and Integral Lighting Configuration. J1-10 J1-11
ARINC 429 I/P NO. 1 HI ARINC 429 I/P NO. 1 LO
22 22
0.1/2 0.1/2
J1-12 J1-13
ARINC 429 I/P NO. 2 HI ARINC 429 I/P NO. 2 LO
22 22
0.1/2 0.1/2
J1-14 J1-15
ARINC 429 I/P NO. 5 HI ARINC 429 I/P NO. 5 LO
22 22
0.1/2 0.1/2
J1-16
DISCRETE I/P NO. 8
22
0.01/2
J1-17 J1-18
ARINC 429 I/P NO. 4 HI ARINC 429 I/P NO. 4 LO
22 22
0.1/2 0.1/2
J1-19 J1-20
ARINC 429 I/P NO. 6 HI ARINC 429 I/P NO. 6 LO
22 22
0.1/2 0.1/2
J1-21 J1-22
ARINC 429 I/P NO. 3 HI ARINC 429 I/P NO. 3 LO
22 22
0.1/2 0.1/2
J1-23 J1-24
ARINC 429 I/P NO. 7 HI ARINC 429 I/P NO. 7 LO
22 22
0.1/2 0.1/2
J1-25 J1-26
ARINC 429 O/P NO. 1 HI ARINC 429 O/P NO. 1 LO
22 22
0.1/2 0.1/2
Figure 104 Interwiring Specifications (Sheet 1 of 5)
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PIN NO.
SIGNAL NAME
PIN AMERICAN WIRE GAUGE
INPUT CURRENT/ RESISTANCE RATING (Amps/Ohms) See note on Sheet 5 of 5
J1-27 J1-28
ARINC 429 O/P NO. 2 HI ARINC 429 O/P NO. 2 LO
22 22
0.1/2 0.1/2
J1-29 J1-30
ARINC 429 I/P NO. 8 HI ARINC 429 I/P NO. 8 LO
22 22
0.1/2 0.1/2
J1-31
DISCRETE O/P NO. 4
22
0.3/2
J1-32 J1-33
RS-422 I/P NO. 2 HI RS-422 O/P NO. 2 HI
22 22
0.1/2 0.1/2
J1-34 J1-35
ARINC 429 I/P NO. 9 HI RS-422 I/P NO.2 LO
22 22
0.1/2 0.1/2
J1-36 J1-37
RS-422 O/P NO. 2 LO ARINC 429 I/P NO. 9 LO
22 22
0.1/2 0.1/2
J1-38
DISCRETE I/P NO. 6
22
0.01/2
J1-39
DISCRETE O/P NO. 1
22
0.3/2
J1-40
DISCRETE I/P NO. 3
22
0.01/2
J1-41
DISCRETE I/P NO. 4
22
0.01/2
J1-42
DISCRETE I/P NO. 5
22
0.01/2
J1-43
ARINC 429 O/P NO. 3 HI
22
0.1/2
J1-44
ARINC 429 O/P NO. 3 LO
22
0.1/2
J1-45
DISCRETE O/P NO. 2
22
0.3/2
J1-46
DISCRETE O/P NO. 3
22
0.3/2
J1-47
DISCRETE I/P NO. 1
22
0.01/2
J1-48
DISCRETE I/P NO. 2
22
0.01/2
J1-49
DISCRETE RETURN
22
0.25/1
J1-50
DISCRETE I/P NO. 7
22
0.01/2
J1-51
GPS TIME MARK HI
22
0.01/2
J1-52
GPS TIME MARK LO
22
0.01/2
J1-53
CHASSIS GROUND
22
1.0/10
SHIELD RTN
22
N/A
J1-56
ARINC 429 I/P NO. 10 HI
22
0.1/2
J1-57
ARINC 429 I/P NO. 10 LO
22
0.1/2
J1-58
ARINC 429 I/P NO. 11 HI
22
0.1/2
J1-54,55
Figure 104 Interwiring Specifications (Sheet 2 of 5)
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PIN NO.
SIGNAL NAME
PIN AMERICAN WIRE GAUGE
INPUT CURRENT/ RESISTANCE RATING (Amps/Ohms) See note on Sheet 5 of 5
J1-59
ARINC 429 I/P NO. 11 LO
22
0.1/2
J1-60
ARINC 429 I/P NO. 12 HI
22
0.1/2
J1-61
ARINC 429 I/P NO. 12 LO
22
0.1/2
J1-62
ARINC 429 I/P NO. 13 HI
22
0.1/2
J1-63
ARINC 429 I/P NO. 13 LO
22
0.1/2
J1-64
ARINC 429 I/P NO. 14 HI
22
0.1/2
J1-65
ARINC 429 I/P NO. 14 LO
22
0.1/2
J1-66
ARINC 429 I/P NO. 15 HI
22
0.1/2
J1-67
ARINC 429 I/P NO. 15 LO
22
0.1/2
J1-68
ARINC 429 I/P NO. 16 HI
22
0.1/2
J1-69
ARINC 429 I/P NO. 16 LO
22
0.1/2
J1-70
ARINC 429 O/P NO. 4 HI
22
0.1/2
J1-71
ARINC 429 O/P NO. 4 LO
22
0.1/2
J1-72
ARINC 429 O/P NO. 5 HI
22
0.1/2
J1-73
ARINC 429 O/P NO. 5 LO
22
0.1/2
J1-74
ARINC 429 O/P NO. 6 HI
22
0.1/2
J1-75
ARINC 429 O/P NO. 6 LO
22
0.1/2
J1-76
ARINC 429 O/P NO. 7 HI
22
0.1/2
J1-77
ARINC 429 O/P NO. 7 LO
22
0.1/2
J1-78
ARINC 429 O/P NO. 8 HI
22
0.1/2
J1-79
ARINC 429 O/P NO. 8 LO
22
0.1/2
J1-80
DISCRETE I/P NO. 9
22
0.01/2
J1-81
DISCRETE I/P NO. 10
22
0.01/2
J1-82
DISCRETE I/P NO. 11
22
0.01/2
J1-83
DISCRETE I/P NO. 12
22
0.01/2
J1-84
DISCRETE I/P NO. 13
22
0.01/2
J1-85
DISCRETE I/P NO. 14
22
0.01/2
Figure 104 Interwiring Specifications (Sheet 3 of 5)
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PIN NO.
SIGNAL NAME
PIN AMERICAN WIRE GAUGE
INPUT CURRENT/ RESISTANCE RATING (Amps/Ohms) See note on Sheet 5 of 5
J1-86
DISCRETE I/P NO. 15
22
0.01/2
J1-87
DISCRETE O/P NO. 5
22
0.3/2
J1-88
DISCRETE O/P NO. 6
22
0.3/2
J1-89
DISCRETE O/P NO. 7
22
0.6/2
J1-90
DISCRETE O/P NO. 8
22
0.6/2
J1-91 J1-92
RS-422 I/P NO. 3 HI RS-422 I/P NO. 3 LO
22 22
0.1/2 0.1/2
J1-93 J1-94
RS-422 O/P NO. 3 HI RS-422 O/P NO. 3 LO
22 22
0.1/2 0.1/2
J1-95
RS-422 or RS-232 I/P NO. 1 LO
22
0.1/2
J1-96
RS-422 I/P NO. 1 HI
22
0.1/2
J1-97
RS-422 or RS-232 O/P NO. 1 LO
22
0.1/2
J1-98
RS-422 O/P NO. 1 HI
22
0.1/2
J1-99
RS-232 Ground NO 1
22
N/A
J1-100
DISCRETE I/P NO. 16
22
0.01/2
J1-101 J1-102
RS-422 I/P NO. 4 HI RS-422 I/P NO. 4 LO
22 22
0.1/2 0.1/2
J1-103 J1-104
RS-422 O/P NO. 4 HI RS-422 O/P NO. 4 LO
22 22
0.1/2 0.1/2
J1-105
ARINC 429 I/P NO. 17 HI
22
0.1/2
J1-106
ARINC 429 I/P NO. 17 LO
22
0.1/2
J1-107
ARINC 429 I/P NO. 18 HI
22
0.1/2
J1-108
ARINC 429 I/P NO. 18 LO
22
0.1/2
J1-109
ARINC 429 I/P NO. 19 HI
22
0.1/2
J1-110
ARINC 429 I/P NO. 19 LO
22
0.1/2
J1-111
ARINC 429 I/P NO. 20 HI
22
0.1/2
J1-112
ARINC 429 I/P NO. 20 LO
22
0.1/2
J1-113
ARINC 429 I/P NO. 21 HI
22
0.1/2
J1-114
ARINC 429 I/P NO. 21 LO
22
0.1/2
Figure 104 Interwiring Specifications (Sheet 4 of 5)
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PIN NO.
SIGNAL NAME
PIN AMERICAN WIRE GAUGE
INPUT CURRENT/ RESISTANCE RATING (Amps/Ohms) See note on Sheet 5 of 5
J1-115
ARINC 429 I/P NO. 22 HI
22
0.1/2
J1-116
ARINC 429 I/P NO. 22 LO
22
0.1/2
J1-117
ARINC 429 I/P NO. 23 HI
22
0.1/2
J1-118
ARINC 429 I/P NO. 23 LO
22
0.1/2
J1-119
ARINC 429 I/P NO. 24 HI
22
0.1/2
J1-120
ARINC 429 I/P NO. 24 LO
22
0.1/2
J1-121
RESERVED (SYNCHRO407)
N/A
Future Growth
J1-122
RESERVED (SYNCHRO407)
N/A
Future Growth
J1-123
RESERVED (SYNCHRO407)
N/A
Future Growth
J1-124
RESERVED (SYNCHRO407)
N/A
Future Growth
J1-125
RESERVED (SYNCHRO407)
N/A
Future Growth
J1-126
0.5V to 5VDC AMLCD Display dimming
22
0.1/2
J1-127
RESERVED (115 VAC, 400 Hz)
N/A
Future Growth
J1-128
RESERVED (115 VAC, 400 Hz)
N/A
Future Growth
Figure 104 Interwiring Specifications (Sheet 5 of 5) NOTE: Use twisted and shielded cables for all digital interfacing. Wire gauge current and resistance rating are per above information. American Wire Gauge size 22 specifies a 16 ohms for a 1000 ft cable length. The resistance above is provided for a 100 ft cable length.
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4.
HARNESS VOLTAGE CHECKOUT Before installing equipment, perform a point-to-point resistance check on the cable harness and the voltage checks given in Figure 105. Connector pin numbers refer to the aircraft side of the FMS connector. Also make certain that circuit breakers are correctly identified for +28 Vdc. Set the appropriate circuit breaker (DC) to on. FMS interwiring is shown in Figure 104. CONNECTOR PINS HI/HOT/LOW/COLD J1-4,5
J1-6,7
J1-53 J1-8 J1-1
J1-9 J1-9
INDICATION
FUNCTION
+28 Vdc
Primary Power
0Vdc/0 ohms
Aircraft Ground
0 to 5.0 VDC 0 to 28.0 VDC
Integral Lighting NOTE: Refer to Figure 4 Equipment Identification for appropriate hardware variation and Integral Lighting Configuration.
J1-126
J1-2
0 to 5.0 VDC
J1-38
ON = >18.5 VDC OFF = <3.5 VDC
J1-16
GROUND/OPEN
AMLCD Display Dimming if supported Remote Lamp Test (Configure LAMP_TEST on discrete I/P No. 6)* Weight on Wheels (Determined by Configuration)
Figure 105 Input Wiring Checks for CMA-9000 hardware variation 100-601951-XXX * Refer to Section X, Configuration Selection of this Manual. 5.
EGI INSTALLATION If an EGI is installed with the CMA-9000 FMS, then lever arm and boresight corrections are required. These corrections are entered after the FMS is configured. Please refer to Section X for FMS configuration procedure. To enter the lever arm corrections: (1)
Press in sequence [INIT/REF] [NEXT] and . Enter maintenance password (normally 1) and MAINTENANCE 1/2 page will appear.
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(2)
Press and . The EGI must be configured in the ARINC 429 SENSOR before having accessed to the EGI setting page.
(3)
On the FMS parameters (e.g. left side of the display), enter, for each axis, the distance (in meters) between the CG of the EGI and the CG of the aircraft. Please note that X is positive forward, Y is positive right, and Z is positive down.
(4)
Press and . After few seconds, the EGI parameters (right side of the display) should be updated with the entered values.
To enter the boresight corrections:
6.
(1)
Press in sequence [INIT/REF] [NEXT] and . Enter maintenance password (normally 1) and MAINTENANCE 1/2 page will appear.
(2)
Press and . The EGI must be configured in the ARINC 429 SENSOR before having accessed to the EGI setting page.
(3)
On the FMS parameters (e.g. left side of the display), enter, for roll, pitch, and yaw, the angle (in degrees) between the center line of the EGI and the body center line of the aircraft. Please note that roll is positive on right turn, pitch is positive climbing and yaw is positive clockwise.
(4)
Press and . After few seconds, the EGI parameters (right side of the display) should be updated with the entered values.
DOPPLER INSTALLATION If a Doppler Velocity Sensor (DVS) is installed with the CMA-9000 FMS, then boresight corrections are required. These corrections will be entered after the FMS is configured. Please refer to Section X for FMS configuration procedure. To enter the boresight corrections: (1)
Press in sequence [INIT/REF] [NEXT] and . Enter maintenance password (normally 1) and MAINTENANCE 1/2 page will appear.
(2)
Press and . The DVS must be configured in the ARINC 429 SENSOR before having accessed to the DVS setting page.
(3)
On the FMS parameters (e.g. left side of the display), enter, for roll, pitch, and yaw, the angle (in degrees) between the centerline of the DVS and the body centerline of the aircraft. Please note that roll is positive on right turn, pitch is positive climbing and yaw is positive clockwise.
(4)
Press . After few seconds, the DVS parameters (right side of the display) should be updated with the entered values.
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7.
ANNUNCIATOR INSTALLATION For a certified installation: (1)
A Non-Precision Approach mode annunciator shall be installed in the pilot’s primary field of view. Either a dedicated remote NPA annunciator, or an appropriate EFIS annunciation must be installed. (2) A GPS integrity annunciator shall be installed in the pilot’s primary field of view. Either a dedicated remote GPS integrity annunciator, or an appropriate EFIS annunciation must be installed.
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SECTION III POST-INSTALLATION TEST 1.
GENERAL This section contains the necessary information and procedures to test the installation of the CMA-9000 containing software variations S/W 169-614876-001 and its interfaces to other associated aircraft systems.
2.
CONDITIONS The aircraft should be located in an area where the Ground Power Unit (GPU) or Auxiliary Power Unit (APU) and later engines may be run to supply aircraft power to the avionics and hydraulic systems. For normal operation of the system use the procedures as given in the appropriate Operator’s Manual. To verify and record the sensor tests it is necessary to position the aircraft in an area clear of surrounding obstructions and electromagnetic interference. Refer to Operator's Manual for the proper procedures to access the pages required for many of the following tests. The FMS should be configured for the installation and navigation database loaded. (Refer to sections X and XI).
3.
SYSTEM TEST PREPARATION A.
Built-In Test The system has a Built-In Test (BIT) capability that consists of an automatic test at Power-up, periodic tests during operation and operator requested tests while in Maintenance mode. The power-up test monitors the operational status of the internal circuitry and generates a message when a malfunction is detected. The following operations are tested on power-up: • • • • • • • • • • • •
RAM test CPU test FPU test Operational code FEPROM CRC Bootstrap code FEPROM CRC Database test (PSA) Non volatile memory corruption tests Loop tests of the ARINC 429 receivers/transmitters Loop tests of RS 422 receivers/transmitters Non volatile memory test Real Time Clock test Battery Test (monitors the battery capacity and gives at least a month warning of impending failure
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The continuous BIT checks the following operations: • • • • • • • •
Validity of digital inputs Operational code FEPROM CRC Bootstrap code FEPROM PSA CRC CRC checksum of installation configurable items ACTIVE Navigation Database test (FEPROM PSA) 429 inputs (external equipment validation/availability) Discrete I/O tests Magnetic Variation Table CRC check
The Maintenance Mode Manually Activated BIT performs self-test upon operator request as follows: • • • • • • • • • • • • • • •
429 receivers/transmitters loop tests 422 receivers/transmitters loop tests Discrete I/O tests Keyboard tests Time Mark input test Annunciator activation tests AMLCD/Video Generator functional/performance tests Characters Font Test (Size 9*9 and 9*13) Battery Voltage Level Checker Non-Volatile data and DATABASE FEPROM sectors Test Keyboard Test Internal Annunciators Test (Individually or All in Sequence) Colors Test Video Test Contrast Test
The Automatic tests will be part of the Acceptance Test Procedures (extensive tests performed prior to FMS delivery) and the CMA-9000 will provide manual triggers for the following test: • • • • • • • •
ARINC 429 Bus Loopback Test (ARINC LOOP) AMLCD Colors Test (All in Sequence) LDR tests (enable/disable) UART Loopback Test (UART LOOP) Time Mark Loop Test (TIME MARK LOOP) Discretes test (DISC O/P with DIP and DOP fields) Radio Interface Board test Colour Display test
Perform system testing of the FMS as follows:
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B.
Front panel brightness control The front panel of the CMA-9000 is composed of three items: the display, 9 annunciators, and integral lighting. The brightness range supported by each component is nominally: (1)
Display: In DAY mode: 1.5 to 120 fL In NIGHT mode: 0.25 to 3.0 fL. In NVG mode: 0.25 to 3.0 fL. The brightness for the display can be controlled by either the combination of the BRT front panel function key and the photosensitive Light Dependent Resistor (LDR) sensor or by the combination of dimming curve and external 0-5 VDC external power DC voltage source. A configuration option allows selecting the control source (e.g. BRT key + LDR or external DC voltage ratio). The BRT key /LDR sensor are disabled while operating in the EXTERNAL mode where the display brightness is controlled by an external voltage source and that source is valid (e.g. > 0.3 VDC). When configured to, the FMS can use a default dimming curve, hard-coded in the FMS software, or use a pre-loaded dimming curve (through data loading capability). Refer to the configuration options of the DIMMING 1/1 configuration page.
(2)
Annunciators: In DAY mode: constant at 110 fL. In NIGHT mode: constant at 3.0 fL. In NVG mode: constant at 1.0 fL.
(3)
Integral Lighting: In DAY mode: Integral lighting turned off by the external 5VDC/28VDC voltage source In NIGHT mode: controlled by the external 5VDC/28VDC voltage source. In NVG mode: Integral lighting turned off by the external 5VDC/28VDC voltage source The brightness of the keyboard (integral lighting) in NIGHT mode is to be supplied from an external 5VDC/28VDC voltage source. The curve of the specification SP L330 M0901 Issue C Annex A2, Dimming curve for 5V (the voltage is scaled down by a factor of 28VDC/5VDC = 5.3 for the 28VDC configuration in order to use the same curve) Components, dimming curve down to 0 fL. is used. The keyboard brightness luminescence is switched off when an invalid DC voltage signal is detected (less than 0.3VDC).
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Luminance vs Control Voltage (LED’s reproduce incandescent lamp response curve) 100% 90% 80%
Brightness
70% 60% 50% 40% 30% 20%
5.00
4.75
4.50
4.25
4.00
3.75
3.50
3.25
3.00
2.75
2.50
2.25
2.00
1.75
1.50
1.25
1.00
0.75
0.50
0.25
0.00
10%
Control Voltage (0-5V)
Figure 201 Integral Lighting 5V Curve
C.
Configuration Selection Configure the FMS (if the configuration for the aircraft was not previously done). The configuration identification CFG NO is displayed on the FMSx IDENT 1/2 page. It is essential that the FMS include the proper configuration for a specific installation. The methods of configuration are described in Section X.
D.
Navigation Database Loading Load the navigation, customer, and/or the user databases. The methods for loading the databases are detailed in Section XI. NOTE: In a dual installation: • For synchronized operation, the operator must ensure that the same navigation and user databases are entered in each FMS.
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4.
PROCEDURE The purpose of this test procedure is to ensure the installation of the CMA-9000 is operating correctly and in no way affects the operation of other aircraft systems. NOTE:
A.
In the key sequences shown to display pages, square brackets “[ ]” indicates a function key, angle brackets “< >” indicates a line select key (left and right softkeys). Omit any test or portion of a test which is not applicable to installation.
Power On NOTE:
B.
Future Growth - Pin J1-03 provides the capability for an ON/OFF switch on CMA-9000 FMS. The CMA-9000 is activated (power is ON) when appropriate 28VDC circuit breaker is set and this pin is left Open. See note in Section II Figure 103 of this manual.
(1)
Verify all relevant circuit breakers for the FMS and associated systems are set to ON.
(2)
If the display dimming is configured to internal control (DIMMING page software configuration set to INTERNAL), pressing and holding the BRT key will adjust the display intensity. Adjust to a comfortable level.
Annunciator Test and RADIO Page (1)
During the start up sequence verify that an all white screen is displayed and the annunciators (as selected by configuration) MENU, FAIL, MSG, POS, OFST, NPA, TX1, TX2 and EXEC illuminate in sequence starting with MENU and proceeding left to right until the EXEC annunciator is illuminated.
(2)
Verify that the FAIL annunciator remains extinguished. Depending on the configuration, the RADIO 1/4 or the FMSx IDENT 1/2 MCDU page appears.
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(3)
If the FMS is to interface with radios as a radio control unit (ADF, ATC NAV, COM…configured) the RADIO 1/4 page appears. Otherwise the FMSx IDENT 1/2 appears as illustrated in (7).
INSTALLATION/FLIGHT LINE MANUAL CMA-9000 FLIGHT MANAGEMENT SYSTEM
(5)
Press . The IDENT 1/2 page appears:
FMS1 IDENT
1/2
5L
NAV DATABASE ACTIVE K L M W W 0 6 9 7 OCT10-NOV06/03 SECOND KLMWW0697 NOV07-DEC04/03 OP PROGRAM CFG NO 614876-xxx xx 23253 CUSTOM DATABASE DATE EC-RTEST MAR21/04 USER DATABASE DATE EC-UDTEST MAR21/04
6L
1L 2L 3L 4L
POS INIT>
1R 2R 3R 4R 5R 6R
(6)
Verify and record the software and configuration identifications. These are as specified in the Aircraft Flight Manual Supplement. Press .
(7)
The POS INIT 1/2 page appears.
POS INIT/REF
1/2
FMS POS DR 1L 2L 3L
N47o26.28 W122o18.67
REF WAYPOINT KBFI N 4 7 o3 1 . 8 0 W 1 2 2 o1 8 . 0 0 INS MODE SET ALT -----F T STANDBY ALIGN SET INS POS o
4L
>GND
5L
1757:04z
6L
UTC
.
o
.
DATE
1R 2R 3R 4R
OCT20/04
5R
START ALIGN>
6R
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(8)
Press [RTE], the ACT ROUTE 1/X page appears:
ACT
C.
1/2 DEST
RUNWAY
FLT NO
1L
KSEA
2L
-----
3L
>OFF
4L
5L
6L
(9)
RTE 1
ORIGIN
DMAP APPEND
PANC
KL007
ROUTE
1R 2R
KSEAPANC1
3R
CO ROUTES>
4R
USER ROUTES>
5R
OFFSET
R0.0N M
6R
This completes the initialize sequence and from this point on the operator may access any of the screens necessary for this test procedure. Ensure there are at least four waypoints in the active route to enable the discrete output tests.
Heading Input Verification (1)
Press [PROG], [PREV]. PROGRESS 4/4 page appears. NOTE: PROGRESS 3/3 might appear depending on the configuration.
ACT PROGRESS HEADWIND
1L 2L 3L
027K T
HDG/DA 290o/ L11o MAGVAR E019.9o
4L
ALT (GPS)
5L
0
6L
QNH SET 28.63
FT
4/4
CROSSWIND
R44K T
TAS 240K T
1R 2R 3R 4R 5R 6R
(2)
Verify the Heading as displayed on the HDG/DA line and HSI or EFIS agree within ±2 degrees.
(3)
Slew the compass system in 30 degrees increment and verify the HDG/DA readout changes in the same direction and remains within 2 degrees at each stop.
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(4)
Fail the compass system (by pulling applicable circuit breaker) and verify the FMS indicates a heading failure. The MSG annunciator and one of the following scratchpad message will appear: • if no heading information is available: HEADING INPUT LOST. • if only the AHRS was unpowered : AHRS FAILED. The message will also be displayed on MESSAGE RECALL 1/1 page. This page may be displayed by pressing [INIT REF], or by pressing [MSG] or by pressing and maintaining [INIT/REF] for more than one second.
FMS1 MESSAGE RECALL 1/1 1L 2L 3L
*VUHF1 CONTROL LOST1 *TACAN NAV LOST 1 DATABASE OUT OF DATE1 VUHF2 CONTROL LOST 1 INDEPENDENT OP 1
2R 3R
4L
4R
5L
5R
6L
D.
1R
MAINT MSG>
6R
(5)
Re-activate the compass system and verify the heading failure message disappears and the MSG annunciator extinguishes.
(6)
Repeat above test if dual Heading System is installed.
True Airspeed Verification When no TAS inputs are available, Manual TAS may be entered if TAS source in configuration is set to Manual. (Refer to AIRCRAFT CONFIG 2/2 page). (1)
Connect a Pilot/Static test set to the aircraft. Input values of Airspeed of 50, 150, 200 knots.
(3)
Verify that the TAS reads within ±4 knots.
(4)
Fail the ADC system and verify the FMS indicates an ADC failure. AIR DATA LOST or ADC1 FAILED or ADC2 FAILED for digital type ADC will appear on the scratchpad and the MSG annunciator is illuminated (for the AIR DATA LOST System Alert message only). The message will also be displayed on the FMS MESSAGE RECALL 1/1 page accessed as above.
(5)
Re-activates the ADC system and verify the MSG annunciator extinguishes and the message disappears from the scratchpad and MESSAGE RECALL page.
(6)
Repeat above test if dual TAS System is installed.
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E.
GPS Sensor Unit NOTE: There are two options available which are selectable by Configuration entry. One option is using an external ARINC 743A compatible GPS receiver (CMA-3012 or CMA-3024 or CMA-3112) or an external ARINC 743 compatible GPS receiver (HONEYWELL, HG2021GD02, HG2021GD03 and TRIMBLE TASMAN TA-12) or the embedded GPS in the EGI (LN_100GT, SIGMA50H). The displays are different but overall the same information is available. (1)
EGI (If LN_100GT is installed) (a) Press [INIT REF],
