rdr-2000 inst

INSTALLATION MANUAL

RDR 2000COLOR WEATHER RADAR

SYSTEM

MANUAL NUMBER 006-00643-0007REVISION 7, July, 2002

WARNINGPrior to the Export of this Document, review for export license requirements is needed.

COPYRIGHT NOTICE

©2001,2002 Honeywell International Inc.

Reproduction of this publication or any portion thereof by any means without the express writtenpermission of Honeywell is prohibited. For further information contact the Manager, TechnicalPublications, Honeywell, One Technology Center, 23500 West 105th Street Olathe KS 66061Telephone: (913) 782-0400.

BENDIX/KING RDR 2000

Rev 7, July/2002 00643I05.TDC Page i

SECTION IGENERAL INFORMATION

1.1 INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1

1.2 EQUIPMENT DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1

1.2.1 ART 2000 ANTENNA/RECEIVER/TRANSMITTER . . . . . . . . . . 1-2

1.2.2 IN 182A COLOR RADAR INDICATOR . . . . . . . . . . . . . . . . . . . . 1-2

1.2.3 AA2010V/H AND AA2012V/H ANTENNAS. . . . . . . . . . . . . . . . . 1-3

1.2.4 CM 2000 CONFIGURATION MODULE . . . . . . . . . . . . . . . . . . . 1-3

1.3 TECHNICAL CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . 1-3

1.3.1 ARINC 429 INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3

1.3.2 UNIT INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4

1.4 UNITS AND ACCESSORIES SUPPLIED . . . . . . . . . . . . . . . . . . 1-9

1.4.1 ART 2000 ANTENNA/RECEIVER/TRANSMITTER . . . . . . . . . . 1-9

1.4.2 IN 182A COLOR RADAR INDICATOR . . . . . . . . . . . . . . . . . . . . 1-9

1.4.3 ANTENNAS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9

1.4.4 CM 2000 CONFIGURATION MODULE . . . . . . . . . . . . . . . . . . . 1-9

1.4.5 INSTALLATION KITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9

1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED . . . . . . . . 1-11

1.5.1 STABILIZATION REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . 1-11

1.5.2 QUADRAXIAL CABLE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11

1.5.3 +14/28 VDC CONVERTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11

1.5.4 RADOME. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11

1.5.5 CONFIGURATION MODULE PROGRAMMER KIT . . . . . . . . . 1-11

1.6 OPTIONAL ACCESSORIES . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11

1.6.1 INSTALLATIONS WITH EFIS . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11

1.6.2 GC 360A RADAR GRAPHICS COMPUTER. . . . . . . . . . . . . . . 1-12

1.6.3 GC 362A TCAS GRAPHICS PROCESSOR . . . . . . . . . . . . . . . 1-12

1.6.4 GC 381A RADAR GRAPHICS COMPUTER. . . . . . . . . . . . . . . 1-12

1.6.5 CC 2024 CHECKLIST UNIT . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-12

1.6.6 CC 2024B CHECKLIST CONTROLLER . . . . . . . . . . . . . . . . . . 1-12

1.6.7 IU 2023B RADAR GRAPHICS COMPUTER. . . . . . . . . . . . . . . 1-12

1.7 LICENSE REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-12

SECTION IIINSTALLATION

2.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1


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2.2 UNPACKING AND INSPECTING EQUIPMENT . . . . . . . . . . . . . 2-1

2.3 EQUIPMENT INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1

2.3.1 COOLING CONSIDERATIONS. . . . . . . . . . . . . . . . . . . . . . . . . . 2-1

2.3.2 INSTALLATION PLANNING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1

2.3.3 INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2

DIP SWITCH (Access and settings) . . . . . . . . . . . . . . . . . . . . . . 2-3

2.3.4 IN 182A COLOR RADAR INDICATOR INSTALLATION. . . . . . . 2-6

2.3.5 INSTALLATION OF CABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6

2.4 POST-INSTALLATION SYSTEM CONFIG AND CALIBRATION 2-7

2.4.1 CONFIGURATION PROCEDURE USING RADAR INDICATOR 2-7

2.4.2 CONFIGURATION PROCEDURE USING EFIS 10, 40/50

(Software 08 or earlier) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8

2.4.3 CONFIGURATION PROCEDURE USING EFIS 40/50

(Software 09 or higher) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10

2.4.4 STABILIZATION CALIBRATION. . . . . . . . . . . . . . . . . . . . . . . . 2-21

2.5 PRE-FLIGHT TEST PROCEDURES. . . . . . . . . . . . . . . . . . . . . 2-38

2.5.1 RF OPERATION CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38

2.5.2 INTERFERENCE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39

2.5.3 PREFLIGHT CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39

2.6 FLIGHT TEST PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . 2-40

2.6.1 STABILIZATION CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-41

2.6.2 VERTICAL PROFILE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . 2-41

SECTION IIIOPERATION

3.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

3.2 CONTROLS AND DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

3.2.1 IN182A CONTROLS AND DISPLAY . . . . . . . . . . . . . . . . . . . . . 3-1

3.2.2 ART 2000 FAULT CODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4

3.2.3 OPERATING PROCEDURES. . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5

LIST OF ILLUSTRATIONS

2-1 RDR HIDDEN PAGE MENU . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8

2-2 RDR R-T CALIBRATION DATA PAGE . . . . . . . . . . . . . . . . . . . . 2-8

2-3 EFIS MAINT FUNCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9


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2-4 SUBSYSTEM MENU. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10

2-5 R-T CALIBRATION DATA PAGE . . . . . . . . . . . . . . . . . . . . . . . 2-10

2-6 EFIS 40/50 MAINTENANCE MENUS LEADING TO RADAR

CONFIGURATION MENUS . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12

2-7 MENUS FOR OPERATION CONFIGURATION . . . . . . . . . . . . 2-13

2-8 MENUS FOR EQUIPMENT CONFIGURATION . . . . . . . . . . . . 2-15

2-9 DIAGNOSTICS MENUS FOR SYSTEM CHECK . . . . . . . . . . . 2-18

2-10 GAIN KNOB CALIBRATION FUNCTION . . . . . . . . . . . . . . . . . 2-23

2-11 TILT KNOB CALIBRATION FUNCTION . . . . . . . . . . . . . . . . . . 2-24

2-12 MENUS FOR STABILIZATION CALIBRATION . . . . . . . . . . . . 2-34

2-13 REF GAIN ADJUST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34

2-14 PITCH GAIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35

2-15 PITCH OFFSET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35

2-16 ROLL GAIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36

2-17 ROLL OFFSET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36

2-18 AHRS PITCH OFFSET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-37

2-19 AHRS ROLL OFFSET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-37

2-20 SAVE CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38

2-21 LEVEL FLIGHT, SAT. STAB. AS SEEN ON RADAR IND . . . . 2-42

2-22 ROLL STAB. INOPERATIVE AS SEEN ON RADAR IND. . . . . 2-42

2-23 ROLL RIGHT, ROLL GAIN ERROR AS SEEN ON RADAR IND2-43

2-24 5° PITCH UP, PITCH GAIN ERROR SEEN ON RADAR IND. . 2-44

2-25 CRIMP TOOLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-45

2-26 ART 2000 PINOUT DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . 2-46

2-27 IN 182A PINOUT DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-48

2-28 CONFIGURATION MODULE PINOUT DIAGRAM . . . . . . . . . . 2-50

2-29 ART 2000 OUTLINE AND MOUNTING DRAWING

(HORIZONTALLY POLARIZED ANTENNA) . . . . . . . . . . . . . . . 2-51

2-30 ART 2000 OUTLINE AND MOUNTING DRAWING

(VERTICALLY POLARIZED ANTENNA). . . . . . . . . . . . . . . . . . 2-53

2-31 IN 182A RADAR INDICATOR OUTLINE AND MTG DRAWING 2-55

2-32 CONFIGURATION MODULE OUTLINE AND MTG DRAWING 2-57

2-33 10-INCH FLAT PLATE ANTENNA OUTLINE AND MOUNTING

DRAWING (VERTICALLY POLARIZED) . . . . . . . . . . . . . . . . . 2-59


DRAWING (VERTICALLY POLARIZED) . . . . . . . . . . . . . . . . . 2-61


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DRAWING (HORIZONTALLY POLARIZED). . . . . . . . . . . . . . . 2-63


DRAWING (HORIZONTALLY POLARIZED). . . . . . . . . . . . . . . 2-65

2-37 AIRCRAFT POWER AND GROUND INTERCONNECT. . . . . . 2-67

2-38 CONFIGURATION MODULE INTERCONNECT . . . . . . . . . . . 2-69

2-39 SINGLE RDS INDICATOR INTERCONNECT . . . . . . . . . . . . . 2-71

2-40 ART INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-75

2-41 ANALOG STABILIZATION INTERCONNECT . . . . . . . . . . . . . 2-77

2-42 AHRS STABILIZATION INTERCONNECT . . . . . . . . . . . . . . . . 2-85

2-43 EFIS 40/50 INTERCONNECT (2 SG, 1 INDICATOR). . . . . . . . 2-87

2-44 EFIS 40/50 INTERCONNECT (3 SG, 1 CONTROL PANEL) . . 2-89

2-45 EFIS 40/50 INTERCONNECT (3 SG, 3 CONTROL PANELS) . 2-91

2-46 EFIS 40/50 INTERCONNECT (2 SG, 1 INDICATOR, 2 CONTROL

PANELS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-93

2-47 EFIS 10 INTERCONNECT (1 INDICATOR, 2 CTRL PANELS) 2-95

2-48 EFIS 10 INTERCONNECT, MFD DISPLAY, 2 CTRL PANELS 2-97

2-49 RS 181A/811A TO ART 2000 HARNESS CONNECTOR

REPLACEMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-99

3-1 IN 182A OPERATING CONTROLS AND DISPLAYS . . . . . . . . . 3-2

3-2 IN 182A ADDITIONAL CONTROLS AND DISPLAYS. . . . . . . . . 3-2

3-3 TYPICAL TEST PATTERN DISPLAY . . . . . . . . . . . . . . . . . . . . . 3-7

3-4 TYPICAL WEATHER DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . 3-8

LIST OF TABLES

2-1 ART 2000 DIPSWITCH SETTINGS . . . . . . . . . . . . . . . . . . . . . . 2-3

2-2 CALIBRATION PARAMETERS IN AZIMUTH COUNT FIELD . 2-23

3-1 IN 182A CONTROL FUNCTIONS. . . . . . . . . . . . . . . . . . . . . . . . 3-3

3-2 IN 182A FUNCTION SELECTOR SWITCH POSITIONS . . . . . . 3-4

3-3 ART 2000 FAULT CODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4

3-4 PUSHBUTTON TYPES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5


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GENERAL INFORMATION

1.1 INTRODUCTION This manual contains information relative to the physical, mechanical and electrical characteristics and installation procedures for the BENDIX/KING RDR 2000 Color Weather Radar System.

1.2 EQUIPMENT DESCRIPTION The RDR 2000 Color Weather Radar System consists of three pieces of equipment. The ART 2000 Antenna/Receiver/Transmitter, KMD 850 MFD, or an IN 182A Radar Indicator with Vertical Profile capability, and the Configuration Module (included in the Installation Kit). A 10 or 12 inch antenna must be installed on the ART 2000.The ART 2000 can be installed as a replacement (with a connector change) for the RS 181A or the RS 811A in an existing RDS 81 or RDS 82 installation. If installed with an existing IN 812A, however, Vertical Profile and tracking are not supported by the IN 812A. If using an IN 182A that is not Vertical Profile compatible, the Vertical Profile feature of the ART will not be supported. IN 182A indicators with part numbers of 066-3084-10 and 066-3084-11 are not compatible with the RDR 2000 system.

NOTE:Some part numbers may not be currently available.Consult the current Honeywell catalog or contactyour Honeywell representative for equipment avail-ability.

The ART 2000 can accommodate up to three ARINC 429 control inputs, however, only two can be actively controlling the system at one time and display #3 must be EFIS 40/50 software level 9 or higher. It can also output information to a maximum of three displays by using SDI bits on the ARINC 453 bus.The RDR 2000 system will also interface with the EFS 10 and the EFIS 40/50. In EFIS (Electronic Flight Instrument System) installations, weather is displayed on the EFIS display with a radar con-trol panel providing radar control. No radar indicator is necessary, however, one may be used in combination with EFIS displays.The control/display used enables selection of basic weather, ground mapping and self-test func-tions. Also, image display optimization is made possible by the use of controls for range selection, display intensity and antenna tilt angle. All these functions are multiplexed on the ARINC 429 con-trol bus. Alphanumerics are displayed on-screen for selected mode of operation and the selected range along with the interval (nautical miles) between the displayed range rings. All controls for the system are mounted on the perimeter of the IN 182A screen. In EFIS installations, the radar is controlled through the Radar Control Panel.The optional IU 2023B DataNav can be used to interface numerous navigation systems to an RDR 2000 system by means of an ARINC 429 data bus. The panel mounted CC 2024B Checklist Con-troller can be used with the RDR 2000 to display pilot selectable checklist information and can be used with or without the IU 2023B DataNav. Refer to the IU 2023B Installation Manual (006-00934-0001) or the CC 2024B Installation Manual (006-00935-0001). For checklist capability with EFS 10 the RDR 2000 must interface through the CP 123 Radar Control Panel.The optional GC 381A Radar Graphics Unit can be used to interface the RDR 2000 with the KNS 81 RNAV or the KNR 634 NAV equipment. When the RDR 2000 system is used with a GC 381A, the indicator will provide several pages of alphanumerical checklist data and waypoint information for display on the screen. The waypoint information is supplied by the KNS 81 (10 waypoints) or the KNR 634 (1 waypoint). Refer to the GC 381A Installation Manual for details of the interfacing.


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The GC 360A Radar Graphics Computer interfaces with Bendix/King RDR 2000 RDS81, 82, 84 or 86 Radar systems. It receives navigation data from a Bendix/King KNS 660, KLN 88, KLN 90, KLN 90B, KLN 900, or GNS-XLS Long Range Navigation System. A second LNAV, or a Bendix/King KNR634A, KDM706A or DM441B combination may be added to the system. The GC 362A TCAS Graphics Processor can be used to interface TCAS with the RDR 2000 sys-tem.

1.2.1 ART 2000 ANTENNA/RECEIVER/TRANSMITTER

The ART 2000 consists of a radar receiver and a radar transmitter (with applicable antenna) con-structed as a single unit with a single mounting facility. The RDR 2000 system provides for radar stabilization input for combined pitch, roll and tilt angles of up to ± 30°. In the Vertical Profile mode, the antenna stabilization only responds to pitch inputs.The antenna array is attached to the microwave assembly on the ART 2000 and the two are moved together as the radar scans. The base of the ART 2000 contains the receiver and all pro-cessing and control circuits.

The antenna scan angle can be configured for a 90° or a 100° scan.In EFIS installations with software level 09 or later, the system can be configured with a strut switch. This configuration puts the system in standby mode when the aircraft is on the ground and will not allow the ART to transmit unless the override function is enabled.Upon installation, the system can be configured to include a Target Alert feature. In this configu-ration, if the ART detects a red intensity target with a minimum size of 2 NM in range and 2° in azimuth that is beyond 80 NM and the selected range is 80 NM or less, two red arcs separated by a black arc are displayed at the top of the display centered on the aircraft heading.

1.2.2 IN 182A COLOR RADAR INDICATOR

The IN 182A Color Radar Indicator provides a five color display (black, green, yellow, red, and magenta) of weather and a three color display of ground targets within the area scanned by the radar. Internally generated range marks appear as evenly spaced blue segmented concentric cir-cles (arcs) on the display to assist in determining range of the targets.Video display is accomplished by digital techniques, resulting in a continuous bright display of vid-eo information. The indicator stores a large amount of video information which is read out at rel-atively high rates (about 60 frames per second). The display continuously updates as the antenna scans.The IN 182A has special inputs provided for direct external control of the CRT color guns. This feature allows an external graphics unit such as a GC 360A or GC 381A or an external remote graphics unit such as a IU 2023B to control the display. The CC 2024B Checklist Controller can be used to view a checklist. The IU 2023B and CC 2024B can be used separately or together if the option for a checklist and NAV graphics is desired.The indicator mode (Wx, WxA, VP, NAV, or MAP) is selected by push- buttons. The TST mode is selected by the function switch. Placing the function switch in the TST position causes a pre-determined test pattern to appear on the indicator. In the TST position the transmitter is not op-erational. Range and tracking are controlled by pushbutton switches.A yellow track cursor may be moved either right or left by pressing the track buttons. This assists in determining azimuth bearing of targets. The cursor moves slowly at about 15° per second (in 1° steps to 45° or 50° left or right, depending on the scan angle configured and the type and soft-ware level of the indicator). The deviation from the aircraft heading will be indicated in the upper left corner of the display.



Within 15 seconds after the button is released, the track cursor and the numerics will disappear from the display. The track cursor is also used to select the location of the vertical slice to be viewed in the Vertical Profile mode.IN 182A P/N 066-3084-00 through -03 will not support the Vertical Profile feature of the RDR 2000.

1.2.3 AA2010V/H AND AA2012V/H ANTENNAS

These are aluminum alloy, slotted, flat plate antennas. The AA2010V and AA2012V are vertically polarized. The AA2010H and AA2012H are horizontally polarized. The AA2010V/H are 10" di-ameter antennas and the AA2012V/H are 12" diameter antennas.

1.2.4 CM 2000 CONFIGURATION MODULE

The Configuration Module stores the configuration and calibration data for the RDR 2000 system. The module can be programmed with configuration data in the system if installed in conjunction with EFIS that has software level 09 or higher.In all other installations, the Configuration Module must be programmed with configuration data outside the system using the KPA 900 Configuration Module Programmer Kit (P/N 050-03311-0000) along with a personal computer.All calibration data is programmed with the module in the system, regardless of the type of instal-lation.

1.3 TECHNICAL CHARACTERISTICS

1.3.1 ARINC 429 INFORMATION

The following are serial digital input labels to the ART 2000:

The following are serial digital outputs from the ART 2000:

LABEL INFORMATION CONTAINED IN LABEL FORMAT SPEED

270 Radar Control Word #1 DSC Low Speed

271 Radar Control Word #2 DSC Low Speed

273 Vertical Profile Control Word DSC Low Speed

275 RDR Control Word #3 DSC Low Speed

276 Radar Control Panel Control Word DSC Low Speed

324 Pitch Angle BNR High Speed

325 Roll Angle BNR High Speed

177 Time/Temp Recorder Data Request Low Speed

LABEL INFORMATION CONTAINED IN LABEL FORMAT SPEED

177 Time/Temperature Recorder Data Low Speed



1.3.2 UNIT INFORMATION

ART 2000 ANTENNA/RECEIVER/TRANSMITTERS

TSO COMPLIANCE: See Appendix E

TEMPERATURE RANGE: -55° C to +70° C with antenna

ALTITUDE: 55,000 ft. unpressurized

WEIGHT: 9.9 lbs. (4.49 kg.)

OVERALL DIMENSIONS:

Base: 10.00 in. (25.40 cm)

INPUT POWER REQUIREMENTS: 2.0 amps. at 28 Vdc.2.5 amps. at 17 Vdc.

RADAR TRANSMITTER:

RF Power Output: 2.5 kW to 6.0 kW.3.3 kW nominal.

Frequency (X-band): 9375 MHz ± 30 MHz

Pulse Repetition Freq: 106.5 Hz ± 5 Hz

Pulse Width: 4 µsec. nominal (GMAP and WX modes)

Weather Avoidance Range Capability: 279 NM max. with 10" antenna305 NM max. with 12" antenna

RADAR RECEIVER:

Sensitivity: -110 dBm typical.

STC: Effective 0 to 30 NM with 10" antennaEffective 0 to 35 NM with 12" antenna

Weather Compensation (Wx mode only): 0 to 240 NM

Extended STC: Effective 40 to 240 NM.

Manual Gain Control: Greater than 16 dB at normal room tempera-ture

Gain Reduction Greater than 14 dB from -55° to +70°C



ART 2000 ANTENNA/RECEIVER/TRANSMITTERS (cont.)

STABILIZATION REQUIREMENTS:

Reference: 400 - 5000 Hz

Inputs: 26 Vrms, 400 Hz Sine Wave

115 Vrms, 400 Hz Sine Wave

20 Vp-p, 400 Hz Sine Wave

20 Vp-p, 400 Hz Square Wave

10.7 Vp-p, 400 Hz Square Wave

28 Vp-p, 5 kHz Square Wave

ARINC 429

Pitch and Roll Scaling: 30mV to 220mV/degree, 400 Hz or 5000 Hz

Pitch HI in phase with gyro exc. on pitch up.

Roll HI in phase with gyro exc. on right roll.

STABILIZATION RATE: 25° sec (pitch and roll)

SCAN ANGLE: 90° or 100° (configurable)

SCAN PHYSICAL RADIUS: 10 inch antenna (vert. polarized) - 5.31 inch

10 inch antenna (horiz. polarized) - 5.22 inch

12 inch antenna (vert. polarized) - 6.28 inch

12 inch antenna (horiz. polarized) - 6.20 inch

SCAN RATE: 25°/second

VERTICAL PROFILE: ± 30°

TILT ANGLE: ± 15°

PERFORMANCE INDEX:

10" Flat Plate Antenna: 209.9 dB ± 2.5 dB

12" Flat Plate Antenna: 212.7 dB ± 2.5 dB



CM 2000 CONFIGURATION MODULE (Included in Installation Kit)

KMD 540 MULTI-FUNCTION DISPLAY


PHYSICAL DIMENSIONS:

Height: 2.10 in. (5.33 cm)

Width: 1.60 in. (4.05 cm)

Length (w/connector): 2.10 in. (5.33 cm)

Length (w/o connector): 0.85 in. (2.16 cm)

WEIGHT: 0.10 lb. (.046 kg)

TEMPERATURE: -55° to +70° C.

ALTITUDE RANGE: 0ft to 55,000 ft.

POWER REQUIREMENTS: Supplied by ART 2000

TSO COMPLIANCE: TSO C113Display functionality of C110a

ENVIRONMENTAL CERTIFICATION: See TSO Appendix, EnvironmentalQualification Forms

TEMPERATURE RANGE: -20° C to +70° C

ALTITUDE: 35,000 ft.

PHYSICAL DIMENSIONS: Refer to KMD 550/850 Installation Manual (P/N 006-10608-XXXX)

WEIGHT: Refer to KMD 550/850 Installation Manual (P/N 006-10608-XXXX)

COOLING REQUIREMENTS: No external forced air cooling needed. All re-quired cooling provided by internal fan.

INPUT POWER REQUIREMENTS: 10 to 33 V DC,20 watts nominal, 40 watts maximum

LIGHTING POWER +28 VDC or +14 VDC or + 5 VDC or 5 VAC

MOUNTING Panel mounted with Honeywell supplied mounting rack.



KAC 501 WEATHER RADAR MODULE

IN 182A COLOR RADAR INDICATOR

TSO COMPLIANCE: Display functionality of C63c

ENVIRONMENTAL CERTIFICATION: See TSO Appendix, EnvironmentalQualification Forms

PHYSICAL DIMENSIONS: Length: Width:

7.474 in. (18.983 cm.)5.047 in. (12.819 cm.)

WEIGHT: Included in unit weight per installation draw-ing, figure 2-42

POWER REQUIREMENTS: Supplied by KMD 540 base unit

TSO COMPLIANCE: TSO C63b, Class 7, DO-173

DO-160A Env Cat

A1B1/A/PKS/XXXXXXABABA

TEMPERATURE RANGE: -20° C to +55° C


WEIGHT:

Indicator: 8.9 lb. (4.0 kg.)

Mounting Tray: 0.4 lb. (0.18 kg.)

Connector Kit (RS 181A/IN 182A): 0.3 lb. (0.14 kg.)

OVERALL DIMENSIONS:

Height: 4.11 in. (10.44 cm.)

Width: 6.41 in. (16.28 cm.)

Length (including connector): 12.75 in. (32.38 cm.)

POWER REQUIREMENTS: 28 Vdc @ 2.0 amps continuous

Panel Lighting: 14 Vdc @ 1mA

28 Vdc @ 264mA5 Vac @ 1mA



METAL FLAT PLATE ANTENNAS

WEATHER DISPLAY COLORS:

Black: No Return

Green: Rainfall up to 0.16 in./hr. (4mm./hr.)

Yellow: Rainfall from 0.16 to 0.48 in./hr. (4 to 12mm./hr.)

Red: Rainfall from 0.48 to 2 in./hr. (12 to 50mm./hr.)

Magenta: Rainfall of 2 in./hr. (50mm./hr.) and over

DISPLAY RANGE/RANGE MARKS: (NM) 10/2.5, 20/5, 40/10, 80/20, 160/40 and 240/60

DISPLAY STORAGE: Digital Memory

DISPLAY TYPE: X-Y raster scan

SELF TEST CAPABILITY: TST position on indicator selects test pattern.

WEATHER DATA INPUT: ARINC 453 bus, ARINC 708 data word

CONTROL DATA OUTPUTS: ARINC 429 characteristic



WEIGHT:

10-inch antenna: 0.66 lb. (0.30 kg.)

12-inch antenna: 0.95 lb. (0.43 kg.)

OVERALL DIMENSIONS:

10-inch antenna 9.90 in. (25.15 cm.)

12-inch antenna 11.88 in. (30.18 cm.)

GAIN (min.):

10-inch antenna: 25.7 dB

12-inch antenna: 26.7 dB

VSWR (max.): 1.4:1

BEAMWIDTH:

10-inch antenna: 10°

12-inch antenna: 8.1°



1.4 UNITS AND ACCESSORIES SUPPLIED

NOTE:Some part numbers may not be currently available.Consult the current Honeywell catalog or contactyour Honeywell representative for equipment avail-ability.

1.4.1 ART 2000 ANTENNA/RECEIVER/TRANSMITTER

P/N 071-01519-0101 (to be used in the RDR 2000 system or a replacement in the RDS 81/82 sys-tem).

1.4.2 IN 182A COLOR RADAR INDICATOR

The IN 182A (P/N 066-3084-XX) is available in the following configurations for use in the RDR 2000 system:

The following versions of the IN 182A are not currently available for use with the RDR 2000system: 066-3084-0000 / -0001 / -0002 / -0003 / -0010 / -0011 / -9000 / -9001.

1.4.3 ANTENNAS The antennas are available in the following configurations:

1.4.4 CM 2000 CONFIGURATION MODULE

The Configuration Module is included in the ART 2000 Installation Kit.

1.4.5 INSTALLATION KITS

PART NUMBER BEZEL PANEL LIGHTING

066-3084-30 VP/EFS BLK 5 V, 14 V, OR 28 V

066-3084-31 VP/EFS GRY 5 V, 14 V, OR 28 V

066-3084-32 VP/EFS/GC/BLK 5 V, 14 V, OR 28 V

066-3084-33 VP/EFS/GC/GRY 5 V, 14 V, OR 28 V

UNIT PART NUMBER SIZE POLARIZATION

AA2010V 071-01549-0100 10 INCH VERTICAL

AA2010H 071-01528-0100 10 INCH HORIZONTAL

AA2012V 071-01549-0200 12 INCH VERTICAL

AA2012H 071-01528-0200 12 INCH HORIZONTAL



1.4.5.1 ART 2000 Installation Kit

The Installation Kit (050-03088-0000) for the ART 2000 Antenna/ Receiver/Transmitter contains the following parts:

1.4.5.2 IN 182A Installation Kit

When installing the IN 182A, it is necessary to use a connector kit (050-03291-0000) and a mount-ing tray (047-07535-0000). The contents of connector kit is as follows:

1.4.5.3 KPA 900 Configuration Module Programmer Kit

When installing the RDR 2000 with The KMD 850, Radar indicator, EFS 10 or an EFIS 40/50 in-stallation with software 08 or lower, it is necessary to use the KPA 900 Configuration Module Pro-grammer Kit (P/N 050-03311-0002) to program the Configuration Module with the desired param-eters for that installation. To obtain the programmer kit and software, order the following kit which contains the items listed:

P/N DESCRIPTION UM QTY VENDOR PART NUMBER

030-01157-0011 SOCKET CRMP 20G EA 60 Positronic FC6020D-14

030-01171-0000 CONNECTOR S‘UB-D HSG 9S EA 1 Positronic RD09F00000-782.0

030-01176-0010 CONNECTOR SUB-D HSG 50S EA 1 Positronic RD50F0000X-782.0

030-01428-0006 EMI HOOD W/LOCK 50P EA 1 Positronic D50000GVLO-923.15

030-02351-0000 HOOD/LVR ASSY ST E EA 1 Positronic D9000JVLO-476

071-00097-0100 CM 2000 CONFIG MODULE EA 1 Honeywell

089-06494-0005 SCR SHC 8-32X5/16 EA 6 Honeywell

P/N DESCRIPTION UM QTY VENDOR PART NUMBER

030-01157-0011 SOCKET CRMP 20G EA 37 Positronic FC6020D-14

030-01175-0000 CONNECTOR S‘UB-D HSG 37S EA 1 Positronic RD37F00000-782.0

030-01428-0004 EMI HOOD W/LOCK 37P EA 1 Positronic D37000GVLO-923.15

P/N DESCRIPTION UM -0000 -0001 VENDOR PART NUMBER

006-05392-0000 OPERATOR’S GUIDE EA 1 1 Honeywell

050-03281-0000 CONFIG MODULE PROGRAMMER EA 1 1 Honeywell

222-00366-0002 KPA 900 PROGRAM EA - 1 Honeywell



1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED

1.5.1 STABILIZATION REQUIREMENTS

A vertical gyro (see Analog Stabilization Inputs drawing) or AHRS system (see AHRS Stabilization Inputs drawing) must be used to fully stabilize the RDR 2000 Radar System. The gyro provides excitation and pitch and roll signals for the stabilization circuits in the ART 2000. It is recommend-ed that isolation transformers be used for pitch and roll inputs when the ART 2000 is installed with a gyro that does not have isolated outputs for radar stabilization. Isolation Transformer P/N (019-05098-0001)is the recommended part.

1.5.2 QUADRAXIAL CABLE

Quadraxial cable (024-00064-0000) shield is required for transmission of ARINC 453 data from the ART 2000 to the IN 182A. Refer to the System Interconnect Drawings for details. A specific length must be determined prior to placing an order.

1.5.3 +14/28 VDC CONVERTER

A +14/28 Vdc converter (068-01016-0003) is required when the RDR 2000 is installed in a +14 Vdc aircraft system to supply +28 Vdc to the radar. Refer to installation manual P/N 006-00578-0000 for details.

1.5.4 RADOME

Radome kits and installation directions must be ordered directly from radome manufacturers or supplied by the aircraft manufacturer. The radome provides a radar window for the radar signal while retaining the original nose configuration of the aircraft.The ART 2000 is mounted directly behind the radome. The radome must have a transmissivity of 90% or better for proper radar operation.

1.5.5 CONFIGURATION MODULE PROGRAMMER KIT

The KPA 900 Configuration Module Programmer Kit (P/N 050-03311-0000), is necessary to input configuration data to the Configuration Module before the module is installed in a radar indicator only (or EFIS 40/50 with software level 08 or lower and EFS 10) installation.

1.6 OPTIONAL ACCESSORIES

1.6.1 INSTALLATIONS WITH EFIS

When the ART 2000 is installed in the EFS 40/50 system, the KMD 540 or IN 182A Radar Indicator does not have to be installed. In this case, the CP 466A Radar Control Panel is used to operate the weather radar. When the ART 2000 is to be installed with the EFS-10 system the IN 182A Radar Indicator is not required. However, either the CP 113N or the CP 123J Radar Control Pan-els must be installed to control the radar.



NOTE

The following are only used with the IN 182A/842A/862A.

1.6.2 GC 360A RADAR GRAPHICS COMPUTER (071-1313-XX) Refer to the GC360A Install Manual for version applicable.

Special versions of GC 360A’s are used to interface the KNS 660 Flight Management System with the special versions of IN 182A (066-3084-02, -03, -32, -33). The GC 360A provides the radar graphics presentation and the checklist presentation on the IN 182A Radar Indicator. The instal-lation kit for the GC 360A is available under P/N 050-02354-0000.

1.6.3 GC 362A TCAS GRAPHICS PROCESSOR

Special versions of the GC 362A are used to interface TCAS I or TCAS II to the RDR 2000 radar system. The processor provides graphics information to the radar indicator. Refer to the CAS 66A/67A System Installation Manual for more information.

1.6.4 GC 381A RADAR GRAPHICS COMPUTER (071-1359-10, -11, -12 and -13 onlyused with IN 182A)

Special versions of GC 381A’s are used to interface the KNS 81 RNAV System with the special versions of IN 182A (066-3084-02, -03, -32, -33). The GC 381A provides the radar graphics pre-sentation and the checklist presentation on the IN 182A Radar Indicator. The installation kit for the GC 381A is available under P/N 050-02354-0001.

1.6.5 CC 2024 CHECKLIST UNIT

When a CC-2024 is installed alone with a RDR 2000 system, the installation kit required is avail-able under P/N 050-02381-0000.When a CC-2024 is installed with a IU-2023B in the RDR 2000 system, the installation kit required is available under P/N 050-02383-0000.When a CC-2024 is installed with a IU-2023C in the RDR 2000 system, the installation kit required is available under P/N 050-02508-0000.

1.6.6 CC 2024B CHECKLIST CONTROLLER

The CC 2024B is used to give a pilot selectable checklist presentation in the RDR 2000 system. The installation kit for the CC 2024B is available under P/N 050-02380-0000.

1.6.7 IU 2023B RADAR GRAPHICS COMPUTER

The IU 2023B is used to interface the KNS 660 Flight Management System with the RDR 2000 Weather Radar System. The IU 2023B provides the Radar Graphics presentation and the CC 2024B provides a checklist presentation on the IN 182A Radar Indicator. The installation kit for the IU 2023B is available under P/N 050-02385-0000.

1.7 LICENSE REQUIREMENTS

An Aircraft Radio Station License is required to operate this system when installed in an aircraft. The Federal Communications Commission has type-accepted and entered this equipment as "Honeywell Avionics Inc." FCC ID# ASYART2000. When completing Form 404, Station License Application, the exact description must be used.



SECTION IIINSTALLATION

2.1 GENERAL This section provides general information for installing the RDR 2000 Color Weather Radar Sys-tem. The cable harness will be fabricated by the installing agency to fit these various require-ments. This section contains interconnect diagrams, mounting dimensions and information per-taining to installation.The conditions and tests required for TSO approval of this unit are minimum performance stan-dards. It is the responsibility of those desiring to install this unit either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO standards. The unit may be installed only if further evaluation by the applicant documents an acceptable in-stallation and is approved by the Administrator.

2.2 UNPACKING AND INSPECTING EQUIPMENT Exercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for damage is to be made, save the ship-ping container to substantiate the claim. The claim should be promptly filed with the transportation company.It would be advisable to retain the container and packaging material after all equipment has been removed in the event that equipment storage or reshipment should become necessary.

2.3 EQUIPMENT INSTALLATION The ART 2000 should be installed in accordance with standards established by the customer’s in-stalling agency, and existing conditions as to unit location and type of installation. However, the following suggestions should be considered before installing the system. Close adherence to these suggestions will assure a more satisfactory performance from the equipment. The installing agency will supply and fabricate all external cables. The connectors required are supplied by Hon-eywell.

2.3.1 COOLING CONSIDERATIONS

The greatest single contributor to increased reliability of all modern day avionics is to limit the max-imum operating temperature of the individual units, whether panel or remote mounted. While modern day circuit designs consume far less electrical energy, the watts per cubic inch dissipated within the avionics units still remains much the same due to high density packaging techniques utilized. Consequently, the importance of providing avionics cooling is essential to the life span of the unit.While each individual unit may or may not require forced air cooling, the combined heat load of several units operating in a typical avionics location will significantly degrade the reliability of the avionics if provisions for cooling are not incorporated in the initial installation. Failure to provide cooling will certainly lead to increased avionics maintenance costs and may void the warranty.

2.3.2 INSTALLATION PLANNING

The locations chosen for units of the RDR 2000 Color Weather Radar System, and the method of installation, will vary with each particular type of aircraft. The units should be installed in a conve-nient location for ease of operation and accessibility for inspection and maintenance. The area should be free from excessive vibration, heat, and noise generating sources.

In addition, since all weather radar receiver-transmitter units are high-power pulse-generating de-vices, they are potential sources of radio-frequency interference (RFI); consequently, consider-ation should be given to this factor when selecting a location for the ART 2000 Antenna/Receiver/Transmitter unit. The cable should not be bundled with automatic-direction-finder (ADF) wiring or antenna lines.



NOTEWhen the transmitter is on, a magnetic field is creat-ed by the heavy DC current drawn. The indicatorcontains a magnetic shield that encloses the bulb ofthe cathode ray tube to eliminate this type of interfer-ence.

The RDR 2000 system operates primarily from the aircraft’s 28 Vdc power system. Refer to the System Interconnect Diagrams. Both the ART 2000 and the IN 182A/812A in the system are op-erated from the +28 Vdc aircraft power through their own circuit breaker. The KMD 540 will oper-ate with an input voltage of 10 to 33 VDC; however, front panel lighting must be +5 VDC, 5 VAC, +14 VDC, or +28 VDC depending on the aircraft lighting bus.

Figure 2-43 is the Outline and Mounting Drawing for the IN 182A. Cable assemblies will be fabri-cated by the installing agency. Installation kits containing the mounting hardware and the unit con-nectors for various systems are available. Consult paragraph 1.4 in Section 1 of this manual.

2.3.3 INSTALLATION

The ART 2000 is a high power digital weather radar. Precautionary measures are necessary dur-ing the installation and operation of this unit to avoid damaging it and/or degrading its perfor-mance.

Precautionary measures:

The ART 2000 is specified to have a operating VSWR of up to 2:1. To prevent loss of performance, the following precautions are recommended:

Lightning diverter strips installed on the bottom of the radome may cause problems with the ART 2000 Contact Honeywell Business and General Aviation Customer Service Product Sup-port before operating the ART 2000.Avoid using lead or metallic flake paints on the radome.Avoid operating the radar near steel buildings.

Installation Guidelines:

Gyro accuracy and calibration at installation are key elements of radar stabilization. Each gyro is unique, so the ART 2000 stabilization calibration procedure has been designed to compensate for a wide variety of gyro sources.

Installation tips:• Pin 8 on the IN182A must be grounded when wired to the ART 2000 as side 1.• The ART 2000 minimum equipment list is addressed in its Installation Manual P/N 066-

00643-0005The ART 2000 has a dipswitch with eight settings for factory and installation functions. The dipswitch MUST have the proper configuration for the radar to perform properly. Note that a set-ting is on when it is positioned facing the center of the unit.



Table 2-1ART 2000 dipswitch settings

2.3.3.1 Antenna

Either a 10-inch or 12-inch flat plate antenna must be attached to the radar receiver-transmitter. See figures 2-33, 2-34, 2-35, and 2-36.

A vertically polarized antenna will give the best radar performance. However, clearance restric-tions in specific applications may necessitate the use of one of the other antenna options. See figures 2-29, and 2-30, ART 2000 Outline and Mounting Drawing.The ART 2000 is shipped with a cover plate over the port opening on the microwave assembly. This cover plate must be removed and discarded. A 9/64" ball end Allen driver is needed for in-stallation and removal of the antenna on all ART’s. Proceed as follows to install the antenna.

NOTE:Before installing the ART 2000 antenna (071-01519-0101), a sticker on the radar’s microwave assemblymust be removed. Once this sticker is been removedthe surface must be cleaned. Cleaning must be donewith Isopropyl alcohol and a cotton cloth to insurethat all adhesive is removed from the radar’s micro-wave assembly. Caution must be given not to allowdebris to enter the microwave assembly cavity. Thiscleaning process must be followed every time theprotective sticker is removed and just before installa-tion of the antenna.

Function Function when on Function when off

1. Transmit enable Transmitter is enabled Transmitter is displayed “Tx Flt” displayed

2. Antenna scan enable Antenna scans normally Antenna motors are disabled

3. Factory Calibration Factory calibration Normal operation

4. Antenna size used in con-nection with (5)

(4) on (5) on 10” slotted or 12” microstrip antenna

(4) off (5) on 12” slotted antenna

5. Antenna size used in con-nection with (4)

(4) on (5) off 18” slotted antenna (future expansion)

(4) off(5) off 10” microstrip antenna

6. TTR request Factory diagnostics Normal operation

7. Quiet startup enable Antenna motion initiated using sensors

Antenna hall sensors are not used and attempt to recali-brate

8. Factory Calibration Factory calibration Normal operation



A. Lay the antenna on a clean, smooth, table top, with mounting holes and port opening fac-ing up.

CAUTIONAVOID DENTING OR SCRATCHING THE ANTEN-NA RADIATING SURFACE.

B. Place the receiver-transmitter on the antenna with the holes aligned. Attach the antenna plate with the screws (089-06494-0005) provided with the Honeywell Installation Kit.

C. Carefully pivot the base of the receiver-transmitter to one side and tighten the exposed screws. Pivot the unit to the other side and tighten the remaining screws.

D. Access the DIP switches through the access port on the ART 2000 and set to the appro-priate antenna (see Table 2-1). The switch is ON when pushed toward the center of the ART 2000.

1. For a 10" antenna, set switch #4 to the ON position and switch #5 to the ONposition.

2. For a 12" antenna, set switch #4 to the OFF position and switch #5 to the ONposition.

2.3.3.2 Installation of ART 2000 Antenna/Receiver/Transmitter

The Antenna/Receiver/Transmitter is designed for mounting to the forward bulkhead in the nose section or a wing pod of an aircraft, behind a radome fabricated for the operating frequency of the radar system. Check all mounting surfaces before mounting the ART 2000 to the bulkhead to en-sure a good electrical bond to the airframe.After base metal has been exposed, treat the surface with Alumiprep #33 (016-01127-0000). Alu-miprep #33 removes light deposits of oil and grease, mill markings and corrosion products as well as natural oxides.After the surface is dry, treat it with Alodine #1001 (016-01128-0000). Alodine #1001 chemically stabilizes aluminum, provides increased corrosion resistance and does not change the appear-ance of the aluminum.Both Alumiprep and Alodine should be wiped off with a clean damp rag to remove any excess.The total space required for the radar antenna can be determined from the dimensional informa-tion contained on the ART 2000 Outline and Mounting Drawing, figures 2-29, and 2-30.

CAUTIONBE CERTAIN THAT THE ANTENNA IS FREE TOMOVE IN AZIMUTH PRIOR TO APPLYING POW-ER.

The forward bulkhead should contain a bolt hole (1/4" dia.) pattern which agrees with the mounting hole pattern of the ART 2000. See figure 2-29. Due to the limited area for bolt heads, socket-head cap screws should be used for mounting.For installations where the cable must come through the bulkhead behind the base of the ART 2000 (such as in a Wing Pod), the cable may be flattened to pass behind the base. Add 1/4" diameter (.071" thick) flat washers or similar spacers between the ART 2000 base isolators and the aircraft bulkhead to increase clearance for the flattened cable.To obtain optional stabilization analog inputs for the radar, the pitch, roll and gyro excitation sig-nals must be connected as shown in the figure 2-41, Analog Stabilization Interconnect. See figure 2-42 for AHRS Stabilization Interconnect.No connections are required if the stabilization inputs are not desired.



Use a light lubricant on the self tapping screw for the connector hood. This allows easier installa-tion of the screw.For proper operation of the radar in stabilized flight, the unit mounting surface should be perpen-dicular to the level-attitude flight path. This may be checked with a spirit level while the gyro is indicating level flight.If the bulkhead mounting surface is not accurate, the ART 2000 may be mounted in a correct at-titude by placing shims between the unit and the bulkhead.

For example, if the bulkhead was tilted back 1/2°, the unit could be corrected by placing 1/16-inch shims between the unit and the bulkhead at the top only (for 1° add 1/8-inch shims, etc.).

A. Ventilation

The ART 2000 is designed to operate in the unpressurized nose section of the aircraft and ventilation is not important.

B. Pressurization

The antenna is designed to operate within ambient air pressures ranging from sea level (and below) to an altitude of 55,000 feet, without pressurization.The ART 2000 is installed in the nose section of the aircraft or wing pod, which is not normally pressurized.

C. Orientation

The ART 2000 must be mounted to within 1° of level in both the vertical and horizontal planes and near the longitudinal (fore-aft) centerline of aircraft.The ART may also be mounted inverted if necessary. This may be desirable if the ART 2000 is being installed in an existing RDS system. Unit orientation will be noted when performing the antenna configuration.

D. Water and Humidity

The installer must insure that the radome is properly sealed against water ingression and ac-cumulation of condensation.

E. Radome

To allow the most satisfactory radar beam radiation, the nose section (radome) in front of the ART 2000 should be fabricated for X-band signals.A radome having less than 90% transmissivity, at all incidence angles defined by the scan and tilt coverage, will result in degradation of system performance and should not be used. A good radome will have a transmissivity greater than 90%.When the radome is installed it should allow the widest possible angle of useful beam radiation (120°, 60° to each side of aircraft heading). Radar range, in terms of that attainable without a radome, is equal to the square of the radome transmissivity percentage.Follow good radome grounding practices to guard against static charges building up and af-fecting the performance of the RDR 2000 system.If there is doubt of the quality of radome material, a flight test should be performed to evaluate the performance over the anticipated ranges and tilt angles that will be required for that type of aircraft. See FAA Advisory Circular 43-14 for additional radome information.

2.3.3.3 KMD 540 Installation

Please refer to the KMD 550/850 Multi-function Display System Installation Manual (P/N 006-10608-XXXX) for KMD 540 Installation.



2.3.4 IN 182A COLOR RADAR INDICATOR INSTALLATION The color radar indicator is installed in a mounting tray in the instrument panel of the aircraft. The total space required for the radar indicator can be determined from the outline and mounting dia-gram, figure 2-31.

CAUTIONBEFORE THE COLOR RADAR INDICATOR ISPERMANENTLY INSTALLED IN A SELECTED LO-CATION, DETERMINE BY ACTUAL OPERATIONTHAT NO MAGNETIC INTERFERENCE EXISTSBETWEEN THE COLOR RADAR AND OTHER AIR-CRAFT INSTRUMENTS.

The mounting tray for the color radar indicator is designed for front loading. Clean all mounting surfaces before installing the mounting tray to ensure a good electrical bond to the airframe. The mounting tray is secured to the instrument panel and airframe with four screws, two on each side.To install the color radar indicator, pull the electrical cables far enough out of the mounting tray to engage the cable to the connector on the rear of the color radar indicator. Slide the color radar indicator into its mounting tray.Press on the front of the color radar indicator with one hand while using an 3/32" Allen wrench to engage the locking pawls. The locking pawl’s access holes are located near the lower left and right corners on the front panel of the IN 182A.When a second (optional) indicator is installed in the system, it must be connected as shown in the interconnect wiring diagram. Observe that the control bus from the second indicator is wired to a second port on the ART 2000. The same data output from the ART 2000 will be supplied to both indicators. The second indicator must also be wired to the aircraft’s +28 Vdc power bus and to the panel lighting voltage. The second indicator must use its own circuit breaker that has the same rating as the first indicator’s breaker.2.3.5 INSTALLATION OF CABLES The cables should be supported firmly enough to prevent movement. They should be carefully protected wherever one may chafe against another or against some other object. Extra protection should be provided in all locations where the cables may be subject to abuse. Shields on shielded wires should be grounded as shown on the System Interconnect Diagrams.Shields should be carried through any obstruction via a thru-bulkhead connector. If shielding can-not be carried through by use of a bulkhead/connector pin, precautions should be taken to ensure each segment of the shielded lead be grounded at only one point. A ground connection of not more than two inches in length should be used. The preceding discussion does not apply to co-axial and quadraxial cable.The connector J5001 has internal ceramic RFI protection circuitry. Because of this, any undue lat-eral strain placed on the pins will fracture that part of the connector, which will result in failure. To minimize this problem, we recommend that enough length be allowed in the wiring harness to cre-ate a service loop. This allows the connectors to mated straight and true, and reduces the damage caused to the connector pins. Make certain that the connectors mate straight and true, and that the locking pawls engage correctly.If the unit is being installed with the connector on top, we recommend that a moisture shield be constructed over the connector. This helps prevent moisture from entering the connector, which causes the unit to fail immediately, and also reduces corrosion on the connector, which eventually causes a failed condition.If corrosion is found on the housing portion of the aircraft connector, this could be a result of a chemical reaction between dissimilar metals in the R/T connector and the connector housing. Re-place the connector housing on the aircraft harness with a new housing, P/N 030-01176-0010. It is not necessary to replace the pins.



2.4 POST-INSTALLATION SYSTEM CONFIGURATION AND CALIBRATION If the system is installed in a radar indicator or KMD 850 MFD installation refer to Section 2.4.1. If the system is installed with EFS 10 or EFIS 40/50 with software level 08 or earlier, refer to Sec-tion 2.4.2. If the system is installed in an EFIS 40/50 system with software level 09 or higher, refer to Section 2.4.3.

2.4.1 CONFIGURATION PROCEDURE USING RADAR INDICATOR

If the system is installed in a radar indicator or KMD 850 MFD refer to Section 2.4.1.The Configu-ration Module must be configured for the specific aircraft installation using the KPA 900 Configu-ration Module Programmer Kit (Part Number 050-03311-0000) in conjunction with a personal computer. Follow the instructions for the programmer.The following guidelines will help insure correct configuration of the CM 2000 module.

1. Make sure the 9v radio battery in the KPA-900 is fully charged and that the KPA-900 is connected to your PC printer port.

2. The DOS program wil only work with Windows up to 98 version, it will not work with later windows software or windows NT.

3. Boot up your PC in DOS and work solely in DOS using the 3.5" floppy.

4. When you have entered the configuration page, go to Hardware, and select write. This puts "default" settings into the Config Module.

5. Go to Memory and select View. Select each Item and ensure a check mark appears to the left of that item. If you do not have EFIS ignore the EFIS items.

6. When you have selected all items required, depress the "Esc" button on your PC keyboard.

7. Go to Hardware and select write. When the program has finished writing and verified itself, select Exit.

8. Remove config module from KPA-900 and install it to the aircraft.

Note: For antenna clearance check and radar stabili-zation using the KMD 550, refer to the KMD 550/850 System Installation Manual (P/N 006-10608-XXXX)

The following steps are performed by utilizing the GAIN knob, RANGE buttons and the mode but-tons on the radar indicator.

2.4.1.1 Antenna Clearance Check

Enter the maintenance mode by performing Steps A and B.

A. Set the radar function selector to TEST. Turn the GAIN knob to minimum.

B. Set the antenna tilt to full up and select 240 NM range.

C. Simultaneously press the Wx and WxA or Wx/WxA and VP buttons (depending on which indicator is in the system) to display the maintenance menu.

D. Press the RANGE UP button to display the RT CALIBRATION DATA page. See figure 2-2.

E. Upon display of the RT CALIBRATION DATA page with the system in calibration mode, all fault fields will flash briefly. This verifies calibration mode is entered. XMITTER should be the only fault displayed. If other faults are shown, further investigation is necessary.

F. Rotate the GAIN knob to obtain a value of -26.5 to -28 in the GAIN POT %2 field. This will initiate the antenna clearance scan. The antenna will move to each of the extreme posi-tions to determine that there is no interference with antenna movement and all scan motors are working properly.



FIGURE 2-1 RDR HIDDEN PAGE MENU

FIGURE 2-2 RDR R-T CALIBRATION DATA PAGE

2.4.2 CONFIGURATION PROCEDURE USING EFS 10, EFIS 40/50 (Software 08 or earlier)

If the system is installed in an EFS 10 or EFIS 40/50 (software 08 or earlier) installation, the Con-figuration Module must be configured for the specific installation using the KPA 900 Configuration Module Programmer Kit (P/N 050-03281-0000) in conjunction with a personal computer. Follow the instructions for the programmer.The following steps are performed by utilizing the pointer buttons on the EFIS Control Panel, plus, the GAIN knob, RANGE buttons and the mode buttons on the Radar Control Panel.2.4.2.1 Antenna Clearance CheckEnter the maintenance mode by performing Steps A and B.





C. Press and hold the TST/REF button. This places the EFIS system in self test mode.

D. When the display shows SELF TEST PASS, simultaneously press the HSI and ARC but-tons. This must be done within five seconds of SELF TEST PASS being displayed. The EFS 40/50 MAINTENANCE page should now be displayed.

E. Press the RANGE DOWN button on the Radar Control Panel to display the EFIS MAINT FUNCTION page. See figure 2-3.

F. Press the #2 bearing pointer button on the EFIS Control Panel to move the select pointer on the display down to SUBSYSTEM MENU.

G. Press the RANGE DOWN button to display SUBSYSTEM MENU page. See figure 2-4.

H. Press the #2 bearing pointer button to move the select pointer on the display down to RA-DAR ALIGNMENT.

I. Press the RANGE DOWN button to display the R-T CALIBRATION DATA page. See figure 2-5.

J. Upon display of the RT CALIBRATION DATA page with the system in calibration mode, the fault fields will flash briefly. This verifies calibration mode is entered. XMITTER should be the only fault displayed. If other faults are shown, further investigation is necessary.

K. Rotate the GAIN knob to obtain a value of -26.5 to -28 in the GAIN POT %2 field. This will initiate the antenna clearance scan.

The antenna will move to each of the extreme positions to determine that there is no interfer-ence with antenna movement and all scan motors are working properly.

FIGURE 2-3 EFIS MAINT FUNCTIONS



FIGURE 2-4 SUBSYSTEM MENU

FIGURE 2-5 R-T CALIBRATION DATA PAGE

2.4.3 CONFIGURATION PROCEDURE USING EFIS 40/50 (Software 09 or higher)

If the Radar Indicator (IN-182/812) is part of an EFIS/RADAR System, it is recommended to follow the procedure in Section 2.4.3.Menus and menu items not discussed in the following procedures are not needed for installation and setup and will not be addressed in this installation manual. To access the ASCII text pages pertaining to the radar system configuration, perform the following procedure. The buttons re-ferred to in this procedure are found on the EFIS control panel or on the EHSI if no control panel is installed.



NOTEThe EFIS symbol Generator (SG-465) must be thecorrect configuration to operate with the ART 2000.Below is a summary of equipment configuration.PLEASE CONSULT THE EFIS MANUAL FORMORE INFORMATION.

EQUIPMENT CONFIGURATION EFIS EquipmentConfiguration - Selection for the ART 2000 Radar Type - RDS 81/82/RDR 2000 Radar CTL PNL - CP 466A or CP 466B (Set as appropriate)

OPERATIONAL CHARACTERISTICS CONFIGURATION EFIS Configuration - Selection for the ART 2000 Max Radar Scan Angle -1 = 100 Degrees

Radar SDI* -1 = Side 1 or -2 = Side 2 or -3 = Side 3 * This setting will be different for EACH SG-465 connected to the Radar.

2.4.3.1 Initial Procedures

The following procedures are accomplished by utilizing the controls on the EFIS Control Panel and the Radar Control Panel.

A. Set the radar function selector to the TEST position. Press and hold the TST/REF button. This places the EFIS system in self test mode.

B. When the display shows SELF TEST PASS, simultaneously press the HSI and ARC but-tons. This must be done within five seconds of SELF TEST PASS being displayed. The EFS 40/50 MAINTENANCE page should now be displayed. See figure 2-6A.

C. Press the RANGE DOWN button to display the EFIS MAINT FUNCTION page. See figure 2-6B.

D. Press the #2 bearing pointer button to move the select pointer on the display down to ASCII TEXT PAGE.

E. Press the RANGE DOWN button to display the ASCII TEXT PAGE MENU. See figure 2-6C.

F. Press the #2 bearing pointer button (NEXT ITEM) to move the select pointer on the display down to RADAR BUS.

G. Press the RANGE DOWN button to display the ART 2000 MAINTENANCE page. See fig-ure 2-6D.



FIGURE 2-6 EFIS 40/50 MAINTENANCE MENUSLEADING TO RADAR CONFIGURATION MENUS



2.4.3.2 Operation Configuration Procedure

The buttons referred to in the following procedure are located on the radar control panel or radar indicator.

A. Press the WxA button to display the MAINT FUNCTIONS menu. See figure 2-7A.

B. Press the GND MAP button to move the select pointer on the display to OPERATION CONFIG.

C. Press the WxA button to display the OPERATION CONFIG options. See figure 2-7B.

D. Press the GND MAP button to select each displayed option. Press the WxA button to se-lect T (true) or F (false) in the bracket of the selected option. Set each option to the con-dition that satisfies the installation.

FIGURE 2-7 MENUS FOR OPERATION CONFIGURATION



2.4.3.3 Equipment Configuration Procedure


A. Press the Wx button until the MAINT FUNCTIONS menu is again displayed. See figure 2-8A.

B. Press the GND MAP button to move the select pointer on the display to EQUIPMENT CONFIG.

C. Press the WxA button to display the EQUIP CONFIG menu. See figure 2-8B.

D. Press the GND MAP button to move the select pointer on the display to ANTENNA CON-FIG.

E. Press the WxA button to display the ANTENNA CONFIG options. See figure 2-8C.

F. Press the GND MAP button to select each displayed option. Press the WxA button to se-lect the desired setting in the bracket of the selected option. Set each option to the condi-tion that satisfies the installation.

G. Press the Wx button until the EQUIP CONFIG menu is again displayed. See figure 2-8D.

H. Press the GND MAP button to move the select pointer on the display to CONTROLLER CONFIG.

I. Press the WxA button to display the CONTROLLER CONFIG options. See figure 2-8E.

J. Press the GND MAP button to select each displayed option. Press the WxA button to se-lect the desired setting in the bracket of the selected option. Set each option to the condi-tion that satisfies the installation.

K. Press the Wx button until the EQUIP CONFIG menu is again displayed. See figure 2-8F.

L. Press the GND MAP button to move the select pointer on the display to SENSOR CON-FIG.

M. Press the WxA button to display the SENSOR CONFIG options. See figure 2-8G.

N. Press the GND MAP button to select each displayed option. Press the WxA button to se-lect T (true) or F (false) in the bracket of the first three selected options. The REF LEVEL must set to the proper gyro reference voltage level which corresponds to the gyro installed in the aircraft.

Select NONE for no analog input, 26 V for a 26 V input, 115 V for a 115 V input, and 10 V for all other voltage ranges. Set each option to the condition that satisfies the installation.



FIGURE 2-8 MENUS FOR EQUIPMENT CONFIGURATION



FIGURE 2-8 MENUS FOR EQUIPMENT CONFIGURATION (Cont’d)



2.4.3.4 System Check


A. Press the Wx button until the MAINT FUNCTIONS menu is again displayed. See figure 2-9A.

B. Press the GND MAP button to move the select pointer on the display to DIAGNOSTICS.

C. Press the WxA button to display the DIAGNOSTICS menu. See figure 2-9B.

D. Press the GND MAP button to move the select pointer on the display to ANTENNA CLEARANCE.

E. Press the WxA button to display the ANTENNA CLEARANCE option. See figure 2-9C.

F. Press the WxA button to start the antenna scan. The antenna will move to each of the ex-treme positions to determine that there is no interference with antenna movement and all scan motors are working properly.

If there are any scan motor problems or DIP switch #2 is in the off position, this will be annun-ciated on the display as in figure 2-9D.

G. Press the Wx button until the DIAGNOSTICS menu is again displayed. See figure 2-9E.

H. Press the GND MAP button to move the select pointer on the display to BUILT IN TEST.

I. Press the WxA button to display the BUILT IN TEST menu. See figure 2-9F.

J. Press the GND MAP button to move the select pointer on the display to POWER LEVELS.

K. Press the WxA button to display the POWER LEVELS page. See figure 2-9G. All voltages shown in the right column should be within 10% of the values shown in the left column.

L. Press the Wx button to return to the BUILT IN TEST menu.

M. Press the GND MAP button to move the select pointer to MEMORY STATUS. See figure 2-9H.

N. Press the WxA button to display the MEMORY STATUS page. See figure 2-9I.

O. Verify each item shows PASS under the STATUS column. If an item shows FAIL, this in-dividual test can rerun by pressing the GND MAP button to move the pointer to that item. Pressing the WxA button will initiate the test. If FAIL is still displayed, further investigation is necessary.

P. Press the Wx button until the DIAGNOSTICS menu is again displayed. See figure 2-9J.

Q. Press the GND MAP button to move the select pointer on the display to FAULT HISTORY.

R. Press the WxA button to display the FAULT HISTORY page. See figure 2-9K. No faults should be displayed. If any are shown, further investigation is necessary.

S. Save Configuration

1. Press the Wx button until the MAINT FUNCTIONS menu is displayed.

2. Press the GND MAP button to move the select pointer to SAVE SETUP DATA. See figure 2-19.



3. Press the WxA button to display the save option page. See figure 2-20A. Press the WxA button again to initiate the save process.

If the save process is successful, COPY PASS will be displayed for five seconds before the display returns to the ART 2000 MAINTENANCE page. See figure 2-6D.

If the save process is unsuccessful, COPY FAIL will be displayed. Try again.

FIGURE 2-9 DIAGNOSTICS MENUS FOR SYSTEM CHECK



FIGURE 2-9 DIAGNOSTICS MENUS FOR SYSTEM CHECK (Cont’d)




2.4.4 STABILIZATION CALIBRATION

Before stabilization can be calibrated, the radar stabilization source must be removed from the air-craft and mounted on a tilt table. Mount the gyro on a suitable tilt table at 0° pitch and 0° roll. Put the radar into calibration mode. Rock the gyro on its pitch axis approximately 5° up to 5° down. Repeat on the roll axis. (This causes the radar to look for the lowest AC voltage the gyro is pro-ducing.)When aligning the ART 2000 with the KI-256 Gyro, vibrate the gyro during the alignment. (This may be accomplished by simply rolling a screwdriver across the tilt table.)

NOTE

It is recommended that isolation transformers be used forpitch and roll inputs when the ART 2000 is installed with agyro that does not have isolated outputs for radar stabilization.Isolation Transformer P/N 019-05098-0001 is the recom-mended part.

NOTEWhen the radar is in the test mode, stab off will be

displayed in the upper left corner of the display.



The radar antenna may be observed from the front of the aircraft during the following procedures because the radar is not transmitting while in the TEST mode. However, the MPEL boundary should always be observed when the radar is operational.

If the ART 2000 is installed in a EFS 10 or EFIS 40/50 system with software level 08 or earlier, proceed to Section 2.4.4.2.

If the ART 2000 is installed in an EFIS 40/50 system with software level 09 or above, proceed to Section 2.4.4.3.

2.4.4.1 Stabilization Calibration with Radar Indicator

The following procedure assumes that either analog or ARINC 429 stabilization inputs are present. The following procedures may also be used if an IN 812A Radar Indicator is used in the system.

The following procedures are performed by utilizing the GAIN knob, RANGE buttons and the mode buttons on the radar indicator.

Enter the maintenance mode by performing the following procedure.



NOTEFailure to perform Steps A and B will prevent theART from entering calibration mode. If more thanone radar indicator is installed in the system, all butone indicator must be in the OFF or SBY position inorder for the system to enter the calibration mode.

C. Simultaneously press the Wx and WxA or Wx/WxA and VP buttons (depending on whether Vertical Profile is supported by the indicator) to display the maintenance menu. See figure 2-3.

D. Press the RANGE UP button to display the RT CALIBRATION DATA page. See figure 2-5.

E. Upon display of the RT CALIBRATION DATA page with the system in calibration mode, the fault fields will flash briefly. No faults should be displayed when the fields stop flashing. This verifies calibration mode is entered. Adjust Roll Trim for 0°.

F. 400 Hz REF GAIN

If an ARINC 429 gyro is being used, proceed to Step K.

1. Set the tilt table to 0° pitch and roll.

2. Adjust the GAIN knob for a GAIN POT setting between -28 and -30 (see figure2-10). An 01 should be displayed in the AZIMUTH COUNT field (see table 2-2).



TABLE 2-2 CALIBRATION PARAMETERS IN AZIMUTH COUNT FIELD

FIGURE 2-10 GAIN KNOB CALIBRATION FUNCTION

DIGIT IN AZIMUTH COUNT FIELD CALIBRATION PARAMETER

00 NONE

01 400 HZ REFERENCE

02 PITCH GAIN

03 ROLL GAIN

04 PITCH OFFSET

05 ROLL OFFSET

06 AHRS ARINC 429 PITCH OFFSET

07 AHRS ARINC 429 ROLL OFFSET

08 SAVE CONFIGURATION



FIGURE 2-11 TILT KNOB CALIBRATION FUNCTION

3. Adjust the TILT SETTING between 5 and 10 UP to increment the 400 HZ REF field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching the desired setting, quickly adjust the TILT SETTING to above 10° to lock in the setting. See figure 2-11.

4. Proceed to Step G.

NOTEIf the 400 Hz REF field is zero (0), and will notchange when the TILT knob is adjusted, check thatthe correct gyro has been selected when program-ming the Configuration Module.

G. PITCH OFFSET

1. Adjust the GAIN knob for a GAIN POT setting between -17.5 and -19.5 (see figure 2-10). An 04 should be displayed in the AZIMUTH COUNT field (see table 2-2).

2. Check that the tilt table is set for 0° pitch.

3. Adjust the TILT SETTING between 5° and 10° UP to increment the PITCH ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5° and 10° DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10° to lock in the setting. See figure 2-11.

4. Set the tilt table to 10° PITCH UP. The value should be 10.0 up ± 1.0°.

5. Set the tilt table to 10° PITCH DOWN. The value should be 10.0 down ± 1.0°.

6. Set the tilt table to 0° PITCH. The value should be 0.0 ± 1.0°.

7. Proceed to Step H.

H. ROLL OFFSET




2. Check that the tilt table is set for 0° roll.

3. Adjust the TILT SETTING between 5° and 10° UP to increment the ROLL ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5° and 10° DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10° to lock in the setting. See figure 2-11.

4. Set the tilt table to 10° roll right. The value should be 10.0R ± 1.0°.

5. Set the tilt table to 10° roll left. The value should be 10.0L ± 1.0°.

6. Set the tilt table to 0° roll. The value should be 0.0 ± 1.0°.

7. Proceed to Step I.

I. PITCH GAIN

1. Set the tilt table for 5° PITCH UP.


3. Adjust the TILT SETTING between 5° and 10° UP to increment the PITCH ANGLE field to 5.0 ± 1.0° (adjusting the TILT SETTING between 5° and 10° DOWN will dec-rement the numbers).

Upon reaching the desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set for 5° PITCH DOWN. Repeat steps 2 and 3.


6. Proceed to Step J.

J. ROLL GAIN

1. In determining the tilt for the table use the standard rate turn for the aircraft being aligned.


3. Adjust the TILT SETTING between 5° and 10° UP to increment the ROLL ANGLEfield to Standard Rate Turn (SRT) for the aircraft (adjusting the TILT SETTING be-tween 5° and 10° DOWN will decrement the numbers). Upon reaching the desired setting, quickly adjust the TILT SETTING to above 10° to lock in the setting. See figure 2-11.

4. Set the tilt table for SRT roll left. Repeat Steps 2 and 3 of this section.


6. Proceed to Step M.



K. AHRS ARINC 429 PITCH OFFSET



3. Adjust the TILT SETTING between 5° and 10° UP to increment the PITCH ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5° and 10° DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10° to lock in the setting. See figure 2-11.

4. Set the tilt table to 5° pitch up. The value should be 5° ± 1.0°. If the value is out of range, repeat Steps 1, 2, and 3 of this section.

5. Set the tilt table to 5° pitch down. The value should be 5° ± 1.0°. If the value is out of range, repeat Steps 1, 2, 3, and 4 of this section.

6. Set the tilt table to 0° pitch. The value should be 0.0 ± 1.0°.

7. Proceed to Step L.

L. AHRS ARINC 429 ROLL OFFSET



3. Adjust the TILT SETTING between 5° and 10° UP to increment the ROLL ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5° and 10° DOWN will dec-rement the numbers). Upon reaching 0.0 ± 1.0°, quickly adjust the TILT SETTING to above 10° to lock in the setting. See figure 2-11.





M. SAVE CONFIGURATION


2. Set the TILT SETTING to 15.0 DOWN. The fault fields will flash indicating the save procedure is beginning. If the save procedure is successful, the GYRO fault will disappear and the azimuth count will step.

3. If the GYRO remains unchanged, TILT to 0° and repeat Step 2.



2.4.4.2 Stabilization Calibration with EFS 10 and EFIS 40/50 (Software 08 or earlier)

The following procedure assumes that either analog or ARINC 429 stabilization inputs are present. If one or the other inputs are not available, that particular option need not be calibrated.The following procedures are performed by utilizing the pointer buttons on the EFIS Control Panel, plus, the GAIN knob, RANGE buttons and the mode buttons on the Radar Control Panel.Enter the maintenance mode by performing the following procedure.



NOTEFailure to perform Steps A and B will prevent theART from entering calibration mode. If more thanone radar indicator is installed in the system, all butone indicator must be in the OFF or SBY position inorder for the system to enter the calibration mode.

C. Press and hold the TST/REF button. This places the EFIS system in self test mode.

D. When the display shows SELF TEST PASS, simultaneously press the HSI and ARC but-tons. This must be done within five seconds of SELF TEST PASS being displayed. The EFS 40/50 MAINTENANCE page should now be displayed.

E. Press the RANGE DOWN button on the Radar Control Panel to display the EFIS MAINT FUNCTION page. See figure 2-3.

F. Press the #2 bearing pointer button on the EFIS Control Panel to move the select pointer on the display down to SUBSYSTEM MENU.

G. Press the RANGE DOWN button to display the SUBSYSTEM MENU page. See figure 2-4.

H. Press the #2 bearing pointer button to move the select pointer on the display down to RA-DAR ALIGNMENT.

I. Press the RANGE DOWN button to display the R-T CALIBRATION DATA page. See fig-ure 2-5.

J. Upon display of the RT CALIBRATION DATA page with the system in calibration mode, the fault fields will flash briefly. No faults should be displayed when the fields stop flashing. This verifies calibration mode is entered. Adjust Roll Trim for 0°.

If an ARINC 429 gyro is being used, proceed to Step P.

K. 400 Hz REF GAIN


2. Adjust the GAIN knob for a GAIN POT setting between -28 and -30 (see figure 2-10). An 01 should be displayed in the AZIMUTH COUNT field (see table 2-2).

3. Adjust the TILT SETTING between 5 and 10 UP to increment the 400 HZ REF field to 0.0 ± 1.0 (adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching the desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.



NOTEIf the 400 Hz REF field is zero (0), and will notchange when the TILT knob is adjusted, check thatthe correct gyro has been selected when program-ming the Configuration Module.

4. Proceed to Step L.

L. PITCH OFFSET



3. Adjust the TILT SETTING between 5 and 10 UP to increment the PITCH ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set the tilt table to 10° pitch up. The value should be 10.0U ± 1.0°.

5. Set the tilt table to 10° pitch down. The value should be 10.0D ± 1.0°.



M. ROLL OFFSET



3. Adjust the TILT SETTING between 5 and 10 UP to increment the ROLL ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set the tilt table to 10° roll right. The value should be 10.0R ± 1.0°. If the value is out of range, repeat Step O.

5. Set the tilt table to 10° roll left. The value should be 10.0L ± 1.0°. If the value is out of range, repeat Step O.

6. Set the tilt table to 0° roll. The value should be 0.0 ± 1.0°. If the value is out of range, repeat Step P.

7. Proceed to Step N.

N. PITCH GAIN

1. Set the tilt table for 5° pitch up.




3. Adjust the TILT SETTING between 5 and 10 UP to increment the PITCH ANGLE field to 10.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will dec-rement the numbers). Upon reaching the desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set to 5° PITCH DOWN and repeat steps 2 and 3 of this section.


6. Proceed to Step O.

O. ROLL GAIN

1. In determining the tilt for the table use the standard rate turn for the aircraft being aligned.


3. Adjust the TILT SETTING between 5 and 10 UP to increment the ROLL ANGLE field to 10.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will dec-rement the numbers). Upon reaching the desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set to 10° roll left. Repeat steps 2 and 3 of this section.


6. Proceed to Step R.

P. AHRS ARINC 429 PITCH OFFSET



3. Adjust the TILT SETTING between 5 and 10 UP to increment the PITCH ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set the tilt table to 10° pitch up. The value should be 10.0U ± 1.0°. If the value is out of range, repeat Steps 1, 2, and 3 of this section.

5. Set the tilt table to 10° pitch down. The value should be 10.0D ± 1.0°. If the value is out of range, repeat Steps 1, 2, 3, and 4 of this section.




7. Proceed to Step Q.

Q. AHRS ARINC 429 ROLL OFFSET



3. Adjust the TILT SETTING between 5 and 10 UP to increment the ROLL ANGLE field to 0.0 ± 1.0° (adjusting the TILT SETTING between 5 and 10 DOWN will dec-rement the numbers). Upon reaching 0° ± 1.0°, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11.

4. Set the tilt table to 10° roll right. The value should be 10.0R ± 1.0°. If the value is out of range, repeat Steps 1, 2, and 3 of this section.

5. Set the tilt table to 10° roll left. The value should be 10.0L ± 1.0°. If the value is out of range, repeat Steps 1, 2, 3, and 4 of this section.



R. SAVE CONFIGURATION


2. Set the TILT SETTING to 15.0D. The fault fields will flash indicating the save pro-cedure is beginning. If the save procedure is successful, the GYRO fault will dis-appear and the azimuth count field will step.

3. If the GYRO remains unchanged, TILT to 0° then repeat Step 2.

2.4.4.3 Stabilization Calibration with EFIS 40/50 Software Level 09 or Above

The following procedure assumes that both analog and ARINC 429 stabilization inputs are present. If one or the other inputs are not available, this situation will be annunciated on the ap-propriate page. No adjustments can be made on a page displaying no inputs available.The following procedures are accomplished by utilizing the controls on the EFIS Control Panel and the Radar Control Panel.

A. Set the radar function selector to the TEST position. Press and hold the TST/REF button. This places the EFIS system in self test mode.

B. When the display shows SELF TEST PASS, simultaneously press the HSI and ARC but-tons. This must be done within five seconds of SELF TEST PASS being displayed. The EFS 40/50 MAINTENANCE page should now be displayed. See figure 2-6A.

C. Press the RANGE DOWN button to display the EFIS MAINT FUNCTION page. See figure 2-6B.



D. Press the #2 bearing pointer button (NEXT ITEM) to move the select pointer on the display down to ASCII TEXT PAGE.

E. Press the RANGE DOWN button to display the ASCII TEXT PAGE MENU. See figure 2-6C.

F. Press the #2 bearing pointer button (NEXT ITEM) to move the select pointer on the display down to RADAR BUS.

G. Press the RANGE DOWN button to display the ART 2000 MAINTENANCE page. See fig-ure 2-6D.

H. Press the WxA button to display the MAINT FUNCTIONS menu. See figure 2-7A.

I. Press the GND MAP button to move the select pointer on the display to STAB CALIBRA-TION. See figure 2-12

J. Press the WxA button to display the STAB CALIBRATION options. See figure 2-12.

K. Press the GND MAP button to select PASSIVE CALIBRATION.

If an ARINC 429 gyro is being used, Proceed to Step Q.

L. REF GAIN ADJUST

1. Press the WxA button to display the REF GAIN ADJUST page (see figure 2-13). Set the TILT knob for a value of 0.0 as shown in the upper right portion of the dis-play.

2. Press the WxA button again to display brackets around the REF value. This allows the TILT knob to change the REF value when turned. Adjust for a reading of 0.0 1.0° in the REF field.

3. Check that the tilt table containing the stabilization source is level and set the table to 0° pitch and roll.

NOTEIf the 400 Hz REF field is 0, and will not change whenthe TILT knob is adjusted, check that the correctgyro has been selected when programming the Con-figuration Module.


M. PITCH OFFSET

1. Set the tilt table for 0° pitch and roll. Press the GND MAP button to display the PITCH OFFSET page (see figure 2-15).

2. Press the WxA to display brackets around the PITCH value. Adjust the TILT knob for a PITCH value of 0.0 ± 1.0°. Press the WxA button to deselect the brackets.

3. Set the tilt table to 10° pitch up. The value should be 10.0U ± 1.0°.

4. Set the tilt table to 10° pitch down. The value should be 10.0D ± 1.0°.




6. Proceed to Step N.

N. ROLL OFFSET

1. Set the tilt table for 0° pitch and roll. Press the GND MAP button to display the ROLL OFFSET page (see figure 2-17).

2. Press the WxA to display brackets around the ROLL value. Adjust the TILT knob for a ROLL value of 0.0 ± 1.0°. Press the WxA button to deselect the brackets.




6. Proceed to Step O.

O. PITCH GAIN

1. Press the GND MAP button to obtain the PITCH GAIN page on the display (see figure 2-14). Set the TILT knob for a value of 0.0.

2. Set the tilt table for 5° pitch up.

3. Press the WxA button again to display brackets around the PITCH value. Adjust the TILT knob for a reading of 10.0U ± 1.0° in the PITCH field. Pressing the WxA button again will remove the brackets.

4. Set the tilt for 5° PITCH DOWN. Repeat Step 3.

5. Proceed to Step P.

P. ROLL GAIN

1. Set the tilt table to 0° pitch and roll. Press the GND MAP button to obtain the ROLL GAIN page on the display (see figure 2-16). Set the TILT knob for a value of 0.0.

2. In determining the tilt of the table use the standard rate turn for the aircraft being aligned.

3. Press the WxA button again to display brackets around the ROLL value. Adjust the TILT knob for a reading of 10.0R ± 1.0° in the ROLL field. Pressing the WxA button again will remove the brackets.

4. Set the tilt table for a standard rate turn for the aircraft being aligned. Repeat Step 3.

5. Proceed to Step S.

Q. ARINC 429 PITCH OFFSET

1. Set the tilt table for 0° pitch and roll. Press the GND MAP button to display the 429 PITCH OFFSET page (see figure 2-18).

2. Press the WxA to display brackets around the PITCH value. Adjust the TILT knob for a PITCH value of 0.0 ± 1.0°. Press the WxA button to deselect the brackets.



3. Set the tilt table to 10° pitch up. The value should be 10.0U ± 1.0°. If the value is out of range, repeat Steps 1 and 2 of this section.

4. Set the tilt table to 10° pitch down. The value should be 10.0D ± 1.0°. If the value is out of range, repeat Steps 1 and 2 of this section.



R. ARINC 429 ROLL OFFSET

1. Set the tilt table for 0° pitch and roll. Press the GND MAP button to display the 429 ROLL OFFSET page (see figure 2-19).

2. Press the WxA to display brackets around the ROLL value. Adjust the TILT knob for a ROLL value of 0.0 ± 1.0°. Press the WxA button to deselect the brackets.

3. Set the tilt table to 10° roll right. The value should be 10.0R ± 1.0°. If the value is out of range, repeat Steps 1 and 2 of this section.

4. Set the tilt table to 10° roll left. The value should be 10.0L ± 1.0°. If the value is out of range, repeat Steps 1 and 2 of this section.


6. Proceed to Step S.

S. Save Configuration

1. Press the Wx button until the MAINT FUNCTIONS menu is displayed.

2. Press the GND MAP button to move the select pointer to SAVE SETUP DATA. See figure 2-20A.

3. Press the WxA button to display the save option page. See figure 2-20B. Press the WxA button again to initiate the save process.

If the save process is successful, COPY PASS will be displayed for five seconds before the display returns to the ART 2000 MAINTENANCE page. See figure 2-20B.

If the save process is unsuccessful, COPY FAIL will be displayed. Try again.



FIGURE 2-12 MENUS FOR STABILIZATION CALIBRATION

FIGURE 2-13 REF GAIN ADJUST



FIGURE 2-14 PITCH GAIN

FIGURE 2-15 PITCH OFFSET



FIGURE 2-16 ROLL GAIN

FIGURE 2-17 ROLL OFFSET



FIGURE 2-18 AHRS PITCH OFFSET

FIGURE 2-19 AHRS ROLL OFFSET



FIGURE 2-20 SAVE CONFIGURATION

2.5 PRE-FLIGHT TEST PROCEDURES

2.5.1 RF OPERATION CHECK

WARNINGWHENEVER THE FUNCTION SWITCH IS IN THE"ON" POSITION, RF ENERGY IS BEING RADIAT-ED. DO NOT ALLOW PERSONNEL TO STANDWITHIN 15 FEET OF THE AREA BEING SCANNEDBY THE ANTENNA. TESTS INVOLVING THE RA-DIATION OF RF ENERGY MUST NOT BE MADE INTHE VICINITY OF REFUELING OPERATIONS.ALWAYS USE "TEST" OR "STANDBY" POSI-TIONS, AS APPLICABLE.

A. Rotate the function switch to the ON position after the system has been in SBY or TST for at least 60 seconds.

B. Check for target reflections of local weather (if any) by indexing the range to each range position while tilting the antenna upward above the horizon, using the TILT control.

C. Select each of the range positions. Note that the corresponding range and range mark in-tervals appear in the alphanumeric area of the display. Note that targets on display (if any) shift their relative position.

D. Rotate the function switch to SBY (standby).



2.5.2 INTERFERENCE CHECK

WARNINGWHENEVER THE FUNCTION SWITCH IS IN THE"ON" POSITION, RF ENERGY IS BEING RADIAT-ED. DO NOT ALLOW PERSONNEL TO STANDWITHIN 15 FEET OF THE AREA BEING SCANNEDBY THE ANTENNA. TESTS INVOLVING THE RA-DIATION OF RF ENERGY MUST NOT BE MADE INTHE VICINITY OF REFUELING OPERATIONS.ALWAYS USE "TEST" OR "STANDBY" POSI-TIONS, AS APPLICABLE.

A. Operate the system on all functions and check that this does not affect other electronic equipment in the aircraft.

B. Operate the system on all functions and check that it is not affected by any of the functions of the other electronic or electrical equipment in the aircraft.

C. Upon successful completion of the foregoing post-installation tests, install the radome pre-paratory to preflight checkout of the system.

2.5.3 PREFLIGHT CHECK

NOTEThe preflight check assumes the system has suc-cessfully completed post-installation check, that theaircraft is pointed toward a non-reflective area, andthat fuel trucks or personnel are not close to the ra-dar line-of-sight.

A. Energize the radar bus and vertical gyro reference bus. Ensure that +28 Vdc and the 400 Hz, 5 kHz power (10, 26, or 115 Vac), 14/28 VP-P or ARINC 429 stabilization inputs are being supplied to the system. Check that the vertical (stabilization) gyro is erected. Allow the gyro a minimum of 3 minutes to erect and stabilize before commencing with the align-ment.

B. Vary the external panel lighting voltage (dim control) for maximum panel brightness. Cov-er the indicator mask and check the white panel markings for even light distribution. Re-duce the lighting voltage. The panel lighting should dim.

C. Set the radar indicator or radar control panel function switch to TST. The antenna scans in the TEST mode.

D. Set the brightness (BRT) control to midrange; set the antenna control to any tilt position with antenna stabilization on. The range will be automatically set to 80 miles.

E. The test pattern should appear on the indicator screen. Adjust BRT again, as required.



1. The test pattern should display four colored bands. Starting with the closest band to the origin, the bands will be green, yellow, red, and magenta. The magenta band represents the most intense level. All range marks will be visible and displayed in blue letters (an EFIS indicator will display only one range ring).

2. The "update" action may be observed as a "ripple" moving along the outer band.

F. Set the function switch to the SBY position, then taxi the aircraft to a clear-ahead area where metal buildings, aircraft, etc., are not in the line-of-sight within 600 yards minimum.

WARNINGTESTS INVOLVING RADIATION OF RF ENERGYBY THE RADAR ANTENNA MUST NOT BE MADEIN THE VICINITY OF REFUELING OPERATIONS,OR WHEN PERSONNEL ARE STANDING DI-RECTLY IN FRONT OF THE RADAR ANTENNA.RF ENERGY IS GENERATED IN ALL MODES EX-CEPT STANDBY AND TEST. DO NOT ALLOWPERSONNEL WITHIN THE MPEL BOUNDARY BE-ING SCANNED BY ANTENNA WHEN THE SYS-TEM IS TRANSMITTING. A SAFE DISTANCE OF15 FEET IS RECOMMENDED.

G. Rotate the function switch to the ON position. The indicator should automatically be in the Wx mode and in the 80-mile range. When connected to an EFIS system the RT will come on in the mode and range that the EFIS was shut off in. Make sure that the antenna sta-bilization is connected.

H. Adjust the antenna tilt control up (clockwise) in small increments until a clear picture de-velops of any local weather. Close-in ground targets may also appear in the display. At maximum up (+15°), no ground targets should appear on the display.

I. Repeat antenna tilt control adjustments to check remaining ranges.

J. Rotate the function switch to SBY prior to taxi maneuvers.

2.6 FLIGHT TEST PROCEDURES

NOTEVertical gyro precession may be experienced duringtakeoff or a prolonged aircraft maneuver.

Rotate the function switch to TST. Adjust the brightness (BRT) control as necessary to evaluate the test pattern. Basically, check that update is occurring and that the colored bands are correct.2.6.1 STABILIZATION CHECK

NOTEThe analog pitch and roll output levels from the ver-tical gyro are governed by the 10, 26, or 115 Vac,400 Hz/5 kHz or 14/28 Vdc excitation, the linearity ofthe gyro, plus the ability of the gyro the follow the mo-tion of the aircraft. The accuracy contributed by theantenna is its ability to respond to the gyro outputs.



As a result of these factors, the stabilization system accuracy can vary up to ±10% of the pitch or roll angle of the aircraft. This accuracy can be tested in flight by performing the following proce-dure.A. Fly the aircraft being tested to 6,000 feet AGL or to the aircraft’s normal cruise altitude,

whichever is most convenient.B. Select the MAP mode and set range on radar indicator to 20 miles. Set manual GAIN con-

trol to maximum gain (full clockwise on gain knob).

C. While flying with wings level (0° roll) and minimum pitch to maintain altitude, adjust the an-tenna tilt control on the radar indicator to obtain the video pattern shown in figure 2-21. Then note the antenna tilt control setting.This tilt angle should be about 2.0° down, but will vary with aircraft type, antenna size and al-titude. The terrain band (for open and dry land) should be displayed above the range mark as shown.If the inner ring of video is not parallel to the range mark (figure 2-21), the error is caused by mechanical displacement of the antenna about the roll axis of the aircraft. Follow the applica-ble stabilization calibration procedures in Section 2.4.4 to obtain the proper display.

NOTEMinor corrections may be made with the Roll TrimAdjustment on the Radar Indicator/Controller.

D. Roll the aircraft gradually 20° to the right (the gentle maneuver will minimize gyro preces-sion). For perfect stabilization, the terrain band shown in figure 2-21 should not change.

E. If the terrain band changes in Step E to a display as shown in figures 2-23A or 2-23B the roll gain must be increased or decreased, as indicated by the illustration. Adjust the roll gain accordingly.

F. Make a gentle 20° left turn and repeat the observations in Step E.G. If the roll stabilization is inoperative, an image similar to figure 2-22 will be observed.

H. With wings level, pitch the aircraft up 5°. The display should appear as in figure 2-21. If the display appears as in figure 2-24A or 2-24B, the pitch gain is set too high or too low, as indicated by the illustration. Adjust the pitch gain accordingly.

I. If the center of the display changes by exactly 5° in Step I, the pitch circuit is inoperative.

2.6.2 VERTICAL PROFILE CHECK (if system is so equipped)

A. Press the VP button with the system in Wx or WxA mode.B. A short period of time will elapse before the vertical picture is "painted". This is because

the radar continues to scan normally after the VP is pressed, until it reaches the selected azimuth position.

C. Adjust the TRACK cursor with the TRACK buttons to obtain a vertical "slice" at the position the TRACK cursor is positioned.

D. Push the Wx/WxA button to return to horizontal weather scan. A TRACK line will remain on the screen for 15 seconds to indicate the location of the last profiling azimuth angle.



FIGURE 2-21 LEVEL FLIGHT,SATISFACTORY STABILIZATION AS SEEN ON RADAR INDICATOR

FIGURE 2-22 ROLL STABILIZATION INOPERATIVE AS SEEN ON RADAR INDICATOR



FIGURE 2-23 ROLL RIGHT,ROLL GAIN ERROR AS SEEN ON RADAR INDICATOR



FIGURE 2-24 5° PITCH UP,PITCH GAIN ERROR AS SEEN ON RADAR INDICATOR



FIGURE 2-25 CRIMP TOOLS



FIGURE 2-26 ART 2000 PINOUT DIAGRAM

P5001 I/O SIGNAL NAME

1 I STRUT SWITCH IN

2 I CONTROL 1 429 RECEIVER A

3 I CONTROL 1 429 RECEIVER B





8 I ARINC 429 STABILIZATION (A)

9 I ARINC 429 STABILIZATION (B)

10 NO CONNECTION

11 NO CONNECTION

12 O TIME/TEMP OUT (A) (MAINTENANCE ONLY)

13 O TIME/TEMP OUT (B) (MAINTENANCE ONLY)

14 DETECTOR CAL (MAINTENANCE ONLY)

15 CALIBRATION INC (MAINTENANCE ONLY)

16 AFC ADJUST (MAINTENANCE ONLY)

17 NO CONNECTION

18 I PITCH STABILIZATION LO

19 I PITCH STABILIZATION HI

20 I ROLL STABILIZATION LO

21 I ROLL STABILIZATION HI

22 NO CONNECTION

23 NO CONNECTION



FIGURE 2-26 ART 2000 PINOUT DIAGRAM (CONT).


24 NO CONNECTION

25 NO CONNECTION

26 NO CONNECTION

27 NO CONNECTION

28 NO CONNECTION

29 NO CONNECTION

30 NO CONNECTION

31 I RT #1 ON/OFF (ON=GND)



34 I +28 VDC AIRCRAFT POWER

35 I +28 VDC AIRCRAFT POWER

36 POWER AND CHASSIS GROUND

37 POWER AND CHASSIS GROUND

38 CALIBRATION LIGHT (MAINTENANCE ONLY)

39 SPARE

40 I GYRO REFERENCE HI

41 GYRO REFERENCE COMMON

42 O ARINC 453 DATA (A)

43 O ARINC 453 DATA (B)

44 O +5 VDC CONFIGURATION MODULE VOLTAGE

45 O CONFIGURATION MODULE CLOCK

46 O CONFIGURATION MODULE CHIP SELECT 1

47 O CONFIGURATION MODULE CHIP SELECT 2

48 O DATA TO CONFIGURATION MODULE

49 I DATA FROM CONFIGURATION MODULE

50 CONFIGURATION MODULE GROUND



FIGURE 2-27 IN 182A PINOUT DIAGRAM


1 I 453 DATA IN (A)

2 O 429 CONTROL BUS 1B

3 I EXT DRIVE CONTROL INPUT, BLUE CNT -

4 I EXT DRIVE INPUT, RED -

5 I EXT DRIVE CONTROL INPUT, BLUE CNT +

6 I EXT DRIVE INPUT, RED +

7 I EXT DRIVE INPUT, GREEN +

8 I IND STRAP

9 MAINT. (FOR FACTORY USE ONLY)

10 I EXT DRIVE CONTROL INPUT, GREEN CNT -

11 I +5 VAC LIGHTING

12 I +14 VDC LIGHTING

13 I CHECKLIST

14 I IU DATA

15 I IU CLOCK

16 POWER GROUND

17 POWER GROUND

18 I SB BUFF

19 I +28 VDC POWER IN

20 I 453 DATA IN (B)

21 I EXT DRIVE INPUT, BLUE -

22 I EXT DRIVE CONTROL INPUT, RED CNT -



FIGURE 2-27 IN 182A PINOUT DIAGRAM (CONT).


23 I EXT DRIVE INPUT, BLUE +

24 I EXT DRIVE CONTROL INPUT, RED CNT +

25 I EXT DRIVE CONTROL INPUT, GREEN CNT +

26 I EXT DRIVE CONTROL INPUT, EN EXT

27 O 429 CONTROL BUS 1A

28 I EXT DRIVE INPUT, GREEN -

29 LIGHTING RETURN LO

30 I +28 VDC LIGHTING

31 O RT ON/OFF

32 I CM/NAV SENSE

33 I IU ENABLE

34 I IU LOAD

35 I EXT DRIVE CONTROL INPUT, SHLD GND

36 I LB BUFF

37 I +28 VDC POWER IN



FIGURE 2-28 CONFIGURATION MODULE PINOUT DIAGRAM


1 POWER GROUND

2 I CHIP SELECT 1

3 NO CONNECTION

4 O DATA OUT

5 I +5 VDC POWER

6 I CLOCK

7 NO CONNECTION

8 I DATA IN

9 I CHIP SELECT 2



FIGURE 2-29 ART 2000 OUTLINE AND MOUNTING DRAWING (HORIZONTALLY POLARIZED ANTENNA)(Dwg. No. 155-05816-0000 R-AA)



FIGURE 2-30 ART 2000 OUTLINE AND MOUNTING DRAWING (VERTICALLY POLARIZED ANTENNA)(Dwg. No. 155-05816-0000 R-AA)



FIGURE 2-31 IN 182A RADAR INDICATOR OUTLINE AND MOUNTING DRAWING(Dwg. No. 300-04240-0000 R-BA)



FIGURE 2-32 CONFIGURATION MODULE OUTLINE AND MOUNTING DRAWING(Dwg. No. 155-06016-0000 R-2)



FIGURE 2-33 10-INCH FLAT PLATE ANTENNA OUTLINE AND MOUNTING DRAWING(VERTICALLY POLARIZED)(Dwg. No. 071-01549-0100 R-AA)



FIGURE 2-34 12-INCH FLAT PLATE ANTENNA OUTLINE AND MOUNTING DRAWING(VERTICALLY POLARIZED)(Dwg. No. 071-01549-0200 R-AA)



FIGURE 2-35 10-INCH FLAT PLATE ANTENNA OUTLINE AND MOUNTING DRAWING(HORIZONTALLY POLARIZED)(Dwg. No. 071-01528-0100 R-1)



FIGURE 2-36 12-INCH FLAT PLATE ANTENNA OUTLINE AND MOUNTING DRAWING(HORIZONTALLY POLARIZED)(Dwg. No. 071-01528-0200 R-1)



FIGURE 2-37 AIRCRAFT POWER AND GROUND INTERCONNECT(Dwg. No. 155-01636-0067 R-1)



FIGURE 2-38 CONFIGURATION MODULE INTERCONNECT(Dwg. No. 155-01636-0032 R-1)



FIGURE 2-39 SINGLE RDS INDICATOR INTERCONNECT(Dwg. No. 155-01636-0002 R-AB)

Sheet 1 of 2



FIGURE 2-39 SINGLE RDS INDICATOR INTERCONNECT(Dwg. No. 155-01636-0002 R-AB)

Sheet 2 of 2



FIGURE 2-40 ART INTERFACE(Dwg. No. 155-01636-0001 R-1)



FIGURE 2-41 ANALOG STABILIZATION INTERCONNECT(Dwg. No. 155-01636-0068 R-2)

Sheet 1 of 4




Sheet 2 of 4




Sheet 3 of 4



FIGURE 2-41 ANALOG STABILIZATION INTERCONNECT(Dwg. No. 155-01636-0071 R-AA)

Sheet 4 of 4



FIGURE 2-42 AHRS STABILIZATION INTERCONNECT(Dwg. No. 155-01636-0008 R-0)



FIGURE 2-43 EFIS 40/50 INTERCONNECT (2 SG, 1 INDICATOR)(Dwg. No. 155-01636-0061 R-AB)



FIGURE 2-44 EFIS 40/50 INTERCONNECT (3 SG, 1 CONTROL PANEL)(Dwg. No. 155-01636-0059 R-2)



FIGURE 2-45 EFIS 40/50 INTERCONNECT (3 SG, 3 CONTROL PANELS)(Dwg. No. 155-01636-0060 R-2)



FIGURE 2-46 EFIS 40/50 INTERCONNECT(2 SG, 1 INDICATOR, 2 CONTROL PANELS)(Dwg. No. 155-01636-0062 R-AB)



FIGURE 2-47 EFIS 10 INTERCONNECT (1 INDICATOR, 2 CONTROL PANELS)(Dwg. No. 155-01636-0012 R-AB)



FIGURE 2-48 EFIS 10 INTERCONNECT (MFD DISPLAY, 2 CONTROL PANELS)(Dwg. No. 155-01636-0011 R-1)



FIGURE 2-49 RS 181A/811A TO ART 2000

HARNESS CONNECTOR REPLACEMENT

BENDIX/KING ART 2000




SECTION IIIOPERATION

3.1 GENERAL This section describes the controls and displays of the RDR 2000 Color Weather Radar System when the system uses a IN 182A Color Radar Indicator. When the system is installed in conjunc-tion with EFIS, radar functions may be accessed using the radar control panel. A more thorough explanation of the operation and controls of the RDR 2000 can be found in the RDR 2000 Pilots Guide P/N 006-08755-0000.

3.2 Controls and displays 3.2.1 IN 182A CONTROLS AND DISPLAY All controls used to operate the RDR 2000 Color Weather Radar System are contained on the ra-dar indicator or radar control panel. These controls and the display features are identified in figure 3-1 and figure 3-2 and described in this paragraph.



FIGURE 3-1 OPERATING CONTROLS AND DISPLAYS,IN 182A COLOR RADAR INDICATOR

FIGURE 3-2 ADDITIONAL CONTROLS AND DISPLAYS,IN 182A WITH VERTICAL PROFILE



TABLE 3-1 IN 182A CONTROL FUNCTIONS(reference Figures 3-1 & 3-2)

CONTROL/DISPLAY FUNCTION

BRT control Adjusts brightness of the display for varying cockpit light conditions.

Wx pushbutton Selects the weather mode (Wx) when pressed. Wx appears in display.

WxA pushbutton Selects weather alert mode (WxA) when pressed. Magenta area flashes. WxA appears in the display.

Wx/WxA pushbutton Toggles between Weather and Weather Alert mode in units with Vertical Profile option.

VP pushbutton Selects and deselects the Vertical Profile mode of operation on units containing this op-tion.

MAP pushbutton Selects ground mapping mode (MAP) when pressed. MAP appears in the display. Red color is not used in the MAP mode.

NAV pushbutton Selects Navigation mode and displays preprogrammed waypoints when system is used with optional radar graphics unit and Flight Management System.

TILT control

Turn the knob to adjust antenna tilt. Adjusts the antenna to move the radar beam up to a maximum of +15° above the horizontal, or to a maximum of -15° below the horizontal position. The horizontal position is indicated as 0° on the control. The tilt angle is dis-played in the upper right corner of the indicator. Pulling this knob out disables stabilization. If the system is in a non-stabilized installation, "STAB OFF" will appear in the upper left corner of the screen.

RANGE increase

Clears the display and advances the pushbuttonindicator to the next higher range each time the pushbutton is pressed (eg: 20 to 40, 40 to 80, etc.), until 240 mile range is reached. The range selected is displayed in the upper right corner on the last range mark, and the distance to each of the other range mark circles is displayed along the right edge of the circles (arcs).

RANGE decreaseClears the display and places the indicator pushbutton in the next lower range each time the pushbutton is pressed (eg: 40 to 20), until the minimum range of 10 mile is reached at the outermost range mark or ring.

TRACK leftMoves azimuth line to the left in 1° steps pushbuttonuntil 45° is displayed when button is pushed. Also, used to select the vertical "slice" to be displayed when in Vertical Profile mode on units with this option and increments in 2° steps after each horizontal scan.

TRACK rightMoves azimuth line to the right in 1° steps pushbuttonuntil 45° is displayed when button is pushed. Also, used to select the vertical "slice" to be displayed when in Vertical Profile mode on units with this option and increments in 2° steps after each horizontal scan.

GAIN control Varies the radar receiver gain when in the MAP mode. Gain and STC are preset in the Wx, WxA and VP modes.

ROLL TRIM

Adjust for a mechanical error of 2° or less if the radar sensor is not mounted parallel to the wings. If the error is greater than 2° , the radar sensor must be removed and mechan-ically aligned as close to 0° as possible.



TABLE 3-2 IN 182A FUNCTION SELECTOR SWITCH POSITIONS(reference Figures 3-1 & 3-2)

3.2.2 ART 2000 FAULT CODES

TABLE 3-3 ART 2000 FAULT CODES

POSITION FUNCTION

OFF OFF position removes primary power from the system.

SBY (standby)

SBY position places system in the standby condition during warm-up period and when the system is not in use. The screen is blank with word STBY displayed in the lower left corner. NAV mode may be selected while in standby. No transmission exists in the SBY condition.

TST (test)TST position selects test function to determine operability of the system. A test pattern is displayed and the 80 mile range is automatically selected, but can be changed. No transmission exists in the TST condition.

ONON position selects the condition for normal operation. Radar transmission exists in the ON position. The Wx mode and 80 mile range are automatically selected when turned on.

LOG

LOG position is used only when a Bendix/King IU 2023 series radar graphics unit is in-stalled with a compatible long range navigation system. This mode lists the latitudes and longitudes of selected waypoints, selected VOR frequencies and bearings and distances to waypoints. No radar transmission occurs in this mode.

Error Code Description

IN FLT 6: Indicator is transmitting 429 control word. No 453 Radar word.

STB LMT: Unit has exceeded 30° combined pitch and roll deflection.

TX FLT/ANT FLT: These faults, when alternately displayed in the fault field, indicate that the RT unit (ART 2000) is unable to communicate with the configuration module (CM 2000)

ANT FLT: Indicates a problem with either the drive or sensor systems on the antenna drive system.

TX FLT: Indicates a problem on the TX or RX circuits of the ART 2000.(TX FLT is always present when the ART 2000 is in the test mode.)

WX FLT: Indicates that the information transmitted to the indicator, on the 453 bus, does not reflect the 429 control sent by the indicator to the RT. This will be apparant in a three indicator system if the third indicator controls are not set identical to No.1 or No.2 indi-cator.

429 FLT: This indicates the 429 control bus is not fuctioning correctly.

STAB OFF: Indicates that the 400 Hz. reference is missing or incorrect for the configuration programmed. Indicates that the tilt knob may be in the stab off position (Outer position).



3.2.3 OPERATING PROCEDURES

3.2.3.1 General

There are several system functions that the operator can perform or select by using the controls on the indicator. The basic operational procedures are described in the following paragraphs.Some of the control functions are unique to the color radar indicators. Operation of GAIN and TILT controls is similar to the controls on other airborne radar systems. In the Wx, WxA, VP, and TEST modes, the gain is preset to obtain a calibrated (magenta display) function at a predetermined storm-cell level.In the GND MAP mode, the GAIN control setting can be an operator function (depending if the option is selected OPERATION CONFIGURATION). This feature can be important in obtaining a definitive picture during varying topographic conditions.Operation of the TILT control is covered in the pilots’ manual. This control is important. Improper use can allow a potentially dangerous storm to remain undetected. For additional information, re-fer to Bendix publication ACS-927, Airborne Weather Radar Antenna Stabilization Criteria.

Momentary pushbutton controls are used on the indicator. The momentary switches return when the pushbutton is released. By function, the pushbutton types are as follows:

Table 3-4 Pushbutton Types

3.2.3.2 Turn on Procedure

A. Turn the function switch from the OFF to the TST position. After seven to eight seconds, a test pattern should appear on the indicator display.

B. Check the indicator display. The test pattern displayed is for the test mode, 80-mile range, and contains all the alphanumerical information for mode, range, and range marks. The word TEST appears in the lower left corner.

C. Adjust BRT controls for desired screen brightness. Observe test pattern illustrated in figure3-3.

D. When safe conditions exist (see operating precautions in previous paragraph), place function switch in the ON position to activate the radar system. The indicator display automatically ap-pears in the Wx mode.

Pushbutton Control Function Type

Wx (Weather) Momentary

WxA (Weather Alert) Momentary

Wx/WxA Momentary

VP Momentary

MAP Momentary

NAV Momentary

TRACK (left and right) Momentary

RANGE (up and down) Momentary



NOTEIf the function selector is placed in the ON positionduring the warm-up period, the display will be stan-dard black with a white or blue growing signal untilthe 80 NM range, as the radar sweeps the black isstripped away. Just before the system is ready tofire, the display will turn completely black again for acouple of seconds. Weather will now be displayedand the system is operational.

3.2.3.3 Primary Mode Selection (Wx, WxA, VP, MAP)

A. Observe the existing mode indicated on the display (see figure 3-4).

NOTEWhen the indicator is first turned ON, the Wx modeis displayed.

B. To change the existing mode to one of the other primary modes, press the desired mode push-button.

3.2.3.4 Range Selection

A. Momentarily press the RANGE increase pushbutton to increase the maximum range dis-played by one increment, (e.g., 20 to 40).

NOTEDisplay erases completely and rewrites on the newlyselected range.

B. Observe that the range selected is shown in the upper right corner of the display and along the last range mark.

C. Observe that the distance to each of the other three range marks is shown at the right side of each concentric range circle.

D. To decrease the maximum range displayed, momentarily press the RANGE decrease button.

E. Repeat Step A or D as necessary to obtain the desired range.

3.2.3.5 Track Position

A. Press and hold the TRACK left button and a yellow track line will appear. The position of the track line in degrees relative to the nose of the aircraft is displayed in the upper left corner of the screen. As the button is held down the line will move to the left in 1° steps.

B. Press and hold the TRACK right button and the track line will move to the right in 1° steps.

C. If neither button has been pressed for 15 seconds, the track line will disappear.

D. In the Vertical Profile mode, if the unit is so equipped, the Profiled "slice" will be taken at the position of the track line. If the TRACK buttons are pressed the vertical scan will change po-sition with the track line and is changed in 2° steps at the end of each horizontal scan.



3.2.3.6 Test Pattern Selection

A. Initially, turn function switch from OFF to TST position.

B. Check the indicator display. The test pattern appears 7 or 8 seconds after the indicator func-tion switch was rotated from the OFF position to the TST position. The exact point of test pat-tern termination or range duration of each color is shown in figure 3-3. The presence of four distinct colors, in the proper order, is important.

C. If indicator function switch is already in the ON position, move to the TST position and observe that the test pattern reflects the range selected before the function switch was moved; e.g., if range was set for 160 miles, the test pattern will extend only to about 50 miles on the 160-mile range. set the range to 80 miles for the best test pattern presentation.

3.2.3.7 Turn-off Procedure (on the ground)

The ART 2000 Antenna/Receiver/Transmitter will tilt the antenna down, for increased radar re-ceiver protection, when the indicator is switched to SBY and OFF position.Always turn the indicator function switch to SBY or OFF before disengaging the avionics master switch in the aircraft. The system will power-down in about 5 seconds after switched to the OFF position, to allow time for the antenna to move to the down position (-25°).

FIGURE 3-3 TYPICAL TEST PATTERN DISPLAYNOTE: STAB OFF will be displayed in TEST MODE



FIGURE 3-4 TYPICAL WEATHER DISPLAY


Rev 7, July/2002 00643I05.TDC Page E-1

APPENDIX EENVIROMENTAL QUALIFICATION FORMS


Page E-2 00643I05.TDC Rev 7, July/2002

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