NEOAV 500 ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) … · 9967-0041 REV F RECORD OF TEMPORARY REVISIONS ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 RTR-1 All

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 COVER-1

403 S. Raymond Avenue Pasadena, CA 91109 USA

NEOAV 500 ELECTRONIC FLIGHT INSTRUMENT SYSTEM

(EFIS) 500/520 (P/N 160E015; 160E030; 160E046; 160E049; 160E050, -1)

INSTALLATION MANUAL 9967-0041

© Copyright 2002 Rogerson Aircraft, Inc. All rights reserved.

Proprietary Notice: The content of this publication is the property of, and contains information proprietary to, Rogerson Aircraft Corporation. In order to minimize the possibility of obsolete information being used for

maintenance, overhaul and repair of our equipment, it is made available for the exclusive use of owners/operators of applicable aircraft. This manual may not be reproduced in whole or in part, nor distributed to others, without explicit

written permission of Rogerson Aircraft Corporation.

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 COVER-2

NOTICES This manual applies to the following equipment:

UNIT MODEL ROGERSON KRATOS P/N 5 ATI EFIS (Rotorcraft) EFIS 500 160E015-X 5 ATI EFIS (Rotorcraft /NVG) EFIS 500 NVG 160E030-X 5 ATI EFIS (Fixed Wing and Rotorcraft)

EFIS 520 160E046-X

5 ATI EFIS (Fixed and Rotor) NVG

EFIS 520 NVG 160E049-X

5 ATI EFIS (Fixed and Rotor) SAR / NVG

EFIS 520 SAR / SAF 160E050-X

NOTICE: FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905) This document and the information disclosed herein are proprietary data of Rogerson Aircraft, Inc., and is provided in confidence by Rogerson Aircraft, Inc. Neither this document nor the information contained herein shall be used, reproduced, or disclosed without the express written consent of Rogerson Aircraft, Inc., except to the extent required for the installation or maintenance of the recipient's equipment. The information disclosed in this document falls within exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905. SOFTWARE COPYRIGHT NOTICE All software resident in this equipment is protected by copyright. © Copyright 2002 Rogerson Aircraft, Inc. All rights reserved. Every effort has been made to ensure the accuracy and completeness of this document at the time of publication. However, some errors may occur. Please describe any problems as specifically as possible, and include the manual part number, the page number, and the paragraph or figure number. Comments should be sent to:

ROGERSON KRATOS 403 S. Raymond Avenue

Pasadena, CA 91109 USA Attn: Technical Publications

(626) 449-3090

9967-0041 Rev F

RECORD OF REVISIONS

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 RR-2

All information on this page is subject to the restrictions of the proprietary notice of this document.

THIS PAGE INTENTIONALLY BLANK

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RECORD OF TEMPORARY REVISIONS

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 RTR-1


TEMPORARY REV. NO. PAGE NO. DATE ISSUED BY DATE REMOVED BY

On receipt of a temporary revision, insert revised pages in the manual and enter temporary revision number, page number, date issued, date inserted and initial. When temporary revisions are removed, enter the date of removal and initial.

9967-0041 REV F

RECORD OF TEMPORARY REVISIONS

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 RTR-2



9967-0041 Rev F

SERVICE BULLETIN LIST

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 SBL-1


SERVICE BULLETIN NO. SUBJECT

MANUAL REVISION NUMBER

MANUAL REVISION DATE

On receipt of a service bulletin, insert the service bulletin number, date, date inserted and initial.

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SERVICE BULLETIN LIST

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 SBL-2



9967-0041 Rev F

LIST OF EFFECTIVE PAGES

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 LEP-1


SUBJECT PAGE DATE Cover COVER-1 APR 2/07 COVER-2 APR 2/07 Record of RR-1 MAR 23/04 Revisions RR-2 SEP 10/02 Record of RTR-1 SEP 10/02 Temporary RTR-2 SEP 10/02 Revisions Service Bulletin SBL-1 SEP 10/02 List SBL-2 SEP 10/02 List of Effective LEP-1 APR 2/07 Pages LEP-2 APR 2/07 Table of TOC-1 MAR 23/04 Contents TOC-2 MAR 23/04 TOC-3 MAR 23/04 TOC-4 MAR 23/04 Introduction INTRO-1 APR 2/07 INTRO-2 OCT 25/05 INTRO-3 MAR 23/04 INTRO-4 APR 2/07 INTRO-5 SEP 10/02 INTRO-6 SEP 10/02 Description and 1 MAR 23/04 Operation 2 OCT 25/05 3 APR 2/07 4 APR 2/07 5 MAR 23/04 6 MAR 23/04 F 7/8 MAR 23/04 9 MAR 23/04 10 APR 2/07 11 APR 2/07 12 MAR 23/04 13 MAR 23/04 14 MAR 23/04 15 MAR 23/04 16 MAR 23/04 17 MAR 23/04 18 MAR 23/04 19 MAR 23/04 20 APR 2/07 21 MAR 23/04 22 MAR 23/04 23 MAR 23/04 24 MAR 23/04 25 MAR 23/04 26 MAR 23/04

SUBJECT PAGE DATE 27 OCT 25/05 28 MAR 23/04 29 MAR 23/04 30 MAR 23/04 31 MAR 23/04 32 MAR 23/04 Testing and Fault 101 MAR 23/04 Isolation 102 MAR 23/04 Installation/ 201 MAR 23/04 Removal 202 MAR 23/04 203 MAR 23/04 204 MAR 23/04 205 MAR 23/04 206 MAR 23/04 207 MAR 23/04 208 MAR 23/04 209 MAR 23/04 210 MAR 23/04 Wiring Harness 301 MAR 23/04 Requirements and 302 MAR 23/04 Options 303 MAR 23/04 304 APR 2/07 305 MAR 23/04 306 APR 2/07 307 OCT 25/05 308 OCT 25/05 309 APR 2/07 310 OCT 25/05 311 OCT 25/05 312 OCT 25/05 313 OCT 25/05 314 OCT 25/05 315 OCT 25/05 316 APR 2/07 317 OCT 25/05 318 MAR 23/04 319 APR 2/07 320 MAR 23/04 F 321/322 MAR 23/04 F 323/324 MAR 23/04 F 325/326 MAR 23/04 F 327/328 MAR 23/04 F 329/330 MAR 23/04 F 331/332 MAR 23/04 F 333/334 MAR 23/04 F 335/336 MAR 23/04 F 337/338 MAR 23/04 F 339/340 MAR 23/04 F 341/342 MAR 23/04 F 343/344 MAR 23/04

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LIST OF EFFECTIVE PAGES

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 LEP-2


SUBJECT PAGE DATE F 345/346 MAR 23/04 F 347/348 MAR 23/04 F 349/350 MAR 23/04 351 MAR 23/04 352 MAR 23/04 353 APR 2/07 354 MAR 23/04 F 355/356 MAR 23/04 F 357/358 MAR 23/04 F 359/360 MAR 23/04 F 361/362 MAR 23/04 F 363/364 MAR 23/04 F 365/366 MAR 23/04 F 367/368 MAR 23/04 F 369/370 MAR 23/04 F 371/372 MAR 23/04 373 MAR 23/04 374 MAR 23/04 375 MAR 23/04 376 MAR 23/04 Configuration/ 401 OCT 25/05 Installation 402 APR 2/07 Checkout 403 OCT 25/05 404 OCT 25/05 405 APR 2/07 406 APR 2/07 407 APR 2/07 408 OCT 25/05 409 OCT 25/05 410 MAR 23/04 411 MAR 23/04 412 MAR 23/04 413 OCT 25/05 414 OCT 25/05 Inspection/ 501 SEP 10/02 Check 502 SEP 10/02 Cleaning/ 601 SEP 10/02 Painting 602 SEP 10/02 Repairs 701 SEP 10/02 702 SEP 10/02

"F" indicates a fold-out page

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TABLE OF CONTENTS

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 TOC-1


INTRODUCTION .................................................................................................................. 1 1. General ...................................................................................................................... 1 2. Manufacturing ............................................................................................................ 1 3. Manual Format........................................................................................................... 1 4. Revision Service ........................................................................................................ 2 5. Technical Questions .................................................................................................. 2 6. Abbreviations/Acronyms ............................................................................................ 2

DESCRIPTION AND OPERATION ...................................................................................... 1 1. Data Sheet ................................................................................................................. 1 2. Certification Statements............................................................................................. 2 3. General ...................................................................................................................... 3

A. Overview of Operation........................................................................................................................ 3 B. Physical Description ........................................................................................................................... 4 C. Failure Notification and Comparison Monitoring ................................................................................ 5 D. Data Retrieval ..................................................................................................................................... 6

4. Product Operation.................................................................................................... 10 A. Controls (5XX Series)....................................................................................................................... 10 B. EFIS 5XX Operation ......................................................................................................................... 10 C. HSI MODE........................................................................................................................................ 24 D. External Selection of EGPWS Terrain and TCAS Traffic (EFIS 520 Only)...................................... 25 E. Self-Test Mode ................................................................................................................................. 27 F. Maintenance Mode ........................................................................................................................... 30 G. LNAV Configuration Page ................................................................................................................ 31 H. Diagnostic Pages.............................................................................................................................. 31 I. WXR Calibration Pages ................................................................................................................... 31

TESTING AND FAULT ISOLATION ................................................................................ 101 1. General .................................................................................................................. 101 2. Manual BIT Initiation .............................................................................................. 101 3. Limitations.............................................................................................................. 101

INSTALLATION/REMOVAL............................................................................................. 201 1. General .................................................................................................................. 201 2. Advisories .............................................................................................................. 202 3. Installation Considerations ..................................................................................... 203 4. Initial Installation .................................................................................................... 203

A. Aircraft Preparation......................................................................................................................... 203 B. Equipment Preparation................................................................................................................... 204

5. Mounting Requirements......................................................................................... 205 A. EFIS 5XX Flat Panel Indicator........................................................................................................ 205

6. Mechanical Removal/Replacement........................................................................ 211 A. Removal.......................................................................................................................................... 211 B. Replacement .................................................................................................................................. 211

WIRING HARNESS REQUIREMENTS AND OPTIONS .................................................. 301 1. General .................................................................................................................. 301

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2. Wiring Harness Connectors and Signal Standards.................................................301 A. Wiring Harness Connectors ...........................................................................................................302 B. Wiring Harness Signal Standards ..................................................................................................302

3. Wiring Harness Options and Interfaces ..................................................................303 A. Configuration Options.....................................................................................................................303 B. External Switches or Control Panel................................................................................................305

CONFIGURATION/INSTALLATION CHECKOUT............................................................401 1. General...................................................................................................................401 2. Configuration Procedures .......................................................................................401

A. EFIS 500 Configuration Procedures...............................................................................................401 B. EFIS 520 Configuration ..................................................................................................................401

3. Installation Checkout Procedure.............................................................................407 A. Entering Diagnostic mode: (EFIS 520 Only) ..................................................................................408 B. Entering Operator initiated BIT .......................................................................................................409

4. Maintenance Port....................................................................................................413 A. Ground Support Equipment (GSE) Operation................................................................................413 B. Software Data Loading ...................................................................................................................414

INSPECTION/CHECK.......................................................................................................501 1. General...................................................................................................................501 2. Inspection/Check Procedure...................................................................................501

CLEANING/PAINTING......................................................................................................601 1. General...................................................................................................................601 2. Cleaning Procedure ................................................................................................601

A. General Assembly Cleaning Procedures .......................................................................................601 B. EFIS Unit Monitor Screen Cleaning ...............................................................................................601

3. Painting Procedure .................................................................................................602

REPAIRS ..........................................................................................................................701 1. General...................................................................................................................701

LIST OF FIGURES Figure 1—EFIS Outline Drawing (all P/Ns covered in this document) ................................................................ 9 Figure 2—EFIS (EADI Configuration), Typical Physical Appearance ................................................................. 9 Figure 3—EFIS (EHSI Configuration), Typical Physical Appearance ................................................................. 9 Figure 4—ADI Collective Cue and ILS Mode .................................................................................................... 11 Figure 5—ADI Format (EFIS 500) ..................................................................................................................... 13 Figure 6—ADI Collective Cue, ILS Mode (EFIS 500)........................................................................................ 15 Figure 7—EHSI Normal Mode (EFIS 520)......................................................................................................... 18 Figure 8—HSI Map Mode (EFIS 500)................................................................................................................ 18 Figure 9—HSI ARC Map Mode (EFIS 500) ....................................................................................................... 19 Figure 10—HSI ARC Map and Wx Mode (EFIS 520)........................................................................................ 19 Figure 11—Vertical Profile Mode (EFIS 520) .................................................................................................... 20 Figure 12—EHSI Composite Mode (EFIS 500) ................................................................................................. 20

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Figure 13—HSI Format (EFIS 500) ................................................................................................................... 23 Figure 14—EFIS 520 Map + Traffic + TAWS Display ....................................................................................... 25 Figure 15—EFIS 520 TCAS Traffic Data........................................................................................................... 26 Figure 16—EFIS 520 SAR Doppler Hover Mode .............................................................................................. 27 Figure 17—ADI Self-Test Mode, Phase 1(EFIS 500)........................................................................................ 28 Figure 18—ADI Self-Test Mode, Phase 2 (EFIS 500)....................................................................................... 29 Figure 19—EHSI Self-Test Mode, Phase 1 (EFIS 500) .................................................................................... 29 Figure 20—EHSI Self-Test Mode, Phase 2 (EFIS 500) .................................................................................... 30 Figure 21—Typical EFIS 5XX Installation Procedure...................................................................................... 201 Figure 22—Clamp Configuration 1 .................................................................................................................. 209 Figure 23—Clamp Configuration 2 .................................................................................................................. 209 Figure 24—Adapter Plate Configuration.......................................................................................................... 210 Figure 25—Typical EFIS 500 System Functional Block Diagram ................................................................... 318 Figure 26—LNAV Interface Block Diagram ..................................................................................................... 319 Figure 27—VOR/DME Interface Block Diagram.............................................................................................. 320 Figure 28—Attitude/Heading Interface Block Diagram.................................................................................... 321 Figure 29—ADF/Radio ALT Interface Block Diagram ..................................................................................... 322 Figure 31—EFIS 5XX Wiring Diagram, Sheet 1 of 15..................................................................................... 323 Figure 32—EFIS 5XX Wiring Diagram, Sheet 2 of 15..................................................................................... 325 Figure 33—EFIS 5XX Wiring Diagram, Sheet 3 of 15..................................................................................... 327 Figure 34—EFIS 5XX Wiring Diagram, Sheet 4 of 15..................................................................................... 329 Figure 35—EFIS 5XX Wiring Diagram, Sheet 5 of 15..................................................................................... 331 Figure 36—EFIS 5XX Wiring Diagram, Sheet 6 of 15..................................................................................... 333 Figure 37—EFIS 5XX Wiring Diagram, Sheet 7 of 15..................................................................................... 335 Figure 38—EFIS 5XX Wiring Diagram, Sheet 8 of 15..................................................................................... 337 Figure 39—EFIS 5XX Wiring Diagram, Sheet 9 of 15..................................................................................... 339 Figure 40—EFIS 5XX Wiring Diagram, Sheet 10 of 15................................................................................... 341 Figure 41—EFIS 5XX Wiring Diagram, Sheet 11 of 15................................................................................... 343 Figure 42—EFIS 5XX Wiring Diagram, Sheet 12 of 15................................................................................... 345 Figure 43—EFIS 5XX Wiring Diagram, Sheet 13 of 15................................................................................... 347 Figure 44—EFIS 5XX Wiring Diagram, Sheet 14 of 15................................................................................... 349 Figure 45—EFIS 5XX Wiring Diagram, Sheet 15 of 15................................................................................... 351 Figure 46—EFIS 500 Wiring Diagram, Sheet 1 of 3........................................................................................ 355 Figure 47—EFIS 500 Wiring Diagram, Sheet 2 of 3........................................................................................ 357 Figure 48—EFIS 500 Wiring Diagram, Sheet 3 of 3........................................................................................ 359 Figure 49—EFIS 520 Wiring Diagram, Sheet 1 of 7........................................................................................ 361 Figure 50—EFIS 520 Wiring Diagram, Sheet 2 of 7........................................................................................ 363 Figure 51—EFIS 520 Wiring Diagram, Sheet 3 of 7........................................................................................ 365 Figure 52—EFIS 520 Wiring Diagram, Sheet 4 of 7........................................................................................ 367 Figure 53—EFIS 520 Wiring Diagram, Sheet 5 of 7........................................................................................ 369 Figure 54—EFIS 520 Wiring Diagram, Sheet 6 of 7........................................................................................ 371 Figure 55—EFIS 520 Wiring Diagram, Sheet 7 of 7........................................................................................ 373 Figure 56—EFIS 520 Maintenance Page........................................................................................................ 404 Figure 57—EFIS 520 Configuration Page 1 .................................................................................................... 405 Figure 58—EFIS 520 Configuration Page 2 .................................................................................................... 406 Figure 59—EFIS 520 Configuration Page 3 .................................................................................................... 407 Figure 60—EFIS 520 Diagnostic Mode Discrete Ground/Open Inputs........................................................... 410 Figure 61—EFIS 520 Diagnostic Mode Discrete 28 Volt/Open Inputs............................................................ 410 Figure 62—EFIS 520 Diagnostic Mode Variable DC Inputs............................................................................ 411 Figure 63—EFIS 520 Diagnostic Mode Synchro Inputs .................................................................................. 411 Figure 64—EFIS 520 Diagnostic Mode Discrete Outputs ............................................................................... 412 Figure 65—EFIS 520 Diagnostic Mode Variable Outputs ............................................................................... 412 Figure 66—EFIS 520 Diagnostic Mode ARINC 429 HS and LS Inputs .......................................................... 413

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TABLE OF CONTENTS



LIST OF TABLES

Table 1—P/N Effectivity ....................................................................................................................................... 1 Table 2—Data Sheet ........................................................................................................................................... 1 Table 3—Bezel Mode Button Control Descriptions ........................................................................................... 10 Table 4—FD Mode Annunciations..................................................................................................................... 12 Table 5—Lateral and Vertical Transitions.......................................................................................................... 12 Table 6—Radio Altitude Range/Resolution ....................................................................................................... 13 Table 7—Decision Height Range/Resolution .................................................................................................... 13 Table 8—Marker Beacon Colors ....................................................................................................................... 15 Table 9—Comparison Monitor Signals and Symbols ........................................................................................ 16 Table 10—Recommended Wire Types for Aircraft Wire Bundles ...................................................................204 Table 11—Mounting Kits..................................................................................................................................208 Table 12—Clamp Configuration 1 ...................................................................................................................208 Table 13—Clamp Configuration 2 ...................................................................................................................209 Table 14—Adapter Plate Configuration ...........................................................................................................210 Table 15—EFIS 500 Specific Wiring Configurations .......................................................................................305 Table 16—Pin List for EFIS 5XX and EFIS 520 ..............................................................................................315 Table 17—EFIS 500 Configurable Settings.....................................................................................................353 Table 18—EFIS 5XX Switching Table .............................................................................................................354 Table 19—EFIS 520 Only Configurable Settings ............................................................................................375

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INTRODUCTION

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 INTRO-1


1. TC "Introduction" \l1General

This manual provides the general description, specifications and instructions required for the proper installation and operation of the Rogerson Kratos NEOAV 500 Series Electronic Flight Instrument System (EFIS) 5XX (see for effectivity). Instructions are also provided for performing routine maintenance functions such as testing and cleaning. System inputs and outputs are also described in this manual.

UNIT MODEL ROGERSON KRATOS P/N 5 ATI EFIS (Rotorcraft) EFIS 500 160E015-X 5 ATI EFIS (Rotorcraft /NVG) EFIS 500 NVG 160E030-X 5 ATI EFIS (Fixed Wing and Rotorcraft)

EFIS 520 160E046-X

5 ATI EFIS (Fixed and Rotor) NVG

EFIS 520 NVG 160E049-X

5 ATI EFIS (Fixed and Rotor) SAR / NVG

EFIS 520 SAR / SAF 160E050-X

Table 1—P/N Effectivity

2. Manufacturing

The EFIS is manufactured by:

Rogerson Kratos 403 South Raymond Avenue Pasadena, CA 91109 USA Telephone: (626) 449-3090 FAX: (626) 795-0322

3. Manual Format

This manual is divided into the following sections:

• Introduction • Description and Operation • Testing and Fault Isolation • Installation/Removal • Wiring Harness Requirements and Options • Configuration/Installation Checkout • Inspection/Check • Cleaning/Painting • Repairs

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INTRODUCTION



Within each of these sections, information common to the entire 5XX series is presented first. In those situations where additional detail is necessary, information specific to the EFIS 500 is then presented, followed by information specific to the NEOAV 520 series.

4. Revision Service

The manual is revised as necessary in order to reflect current and revised information. However, service bulletins may be issued independently and separately. Their effect on the manual will be made evident and reflect incorporation into the manual by a reissue of the service bulletin list as appropriate.

5. Technical Questions

Technical questions relating to the EFIS products or specific questions relating to installing and interfacing the system and components should be directed to Rogerson Kratos Customer Service at 949-442-2352, Fax 949-442-2301, or e-mail [email protected].

Please have the following information available when you call Rogerson Kratos Customer Support:

• Aircraft type and model • Location of unit • EFIS model number (part number and serial number) • Software version and revision • Systems interfaced to the EFIS • EFIS Diagnostic page listings • Description of problem • Efforts made to troubleshoot the problem

6. Abbreviations/Acronyms

ABBREVIATION/ ACRONYM DESCRIPTION ABS Absolute ABV Above ADF Automatic Direction Finder ADI Attitude Direction Indicator AFCS Automatic Flight Control System AHRS Attitude Heading Reference System ALT Altitude AMLCD Active Matrix Liquid Crystal Display ARINC Aeronautical Radio, Incorporated ATI Air Transport Indicator ATT Attitude

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INTRODUCTION



ABBREVIATION/ ACRONYM DESCRIPTION AWG American Wire Gauge BC Back Course BIT Built-in Test BLW Below BRG Bearing CAP Capture CCW Counterclockwise COL Collective CRS Course CW Clockwise DF Direction Finder DG Direction Gyro DG/VG Direction Gyro/Vertical Gyro DH Decision Height DME Distance Measurement Equipment DR Dead Reckoning DTK Desired Track EADI Electronic Attitude Direction Indicator EFIS Electronic Flight Instrument System EGPWS Enhanced Ground Proximity Warning System EHSI Electronic Horizontal Situation Indicator EMI Electromagnetic Interference ESD Electrostatic Sensitive Device EX-LOC Expanded Localizer FCC Flight Control Computer FCS Flight Control System FD Flight Director FDC Flight Director Computer FMS Flight Management System GA Go Around GMAP Ground Map GND Ground GPS Global Positioning System GS Glideslope GSE Ground Support Equipment GSPD Ground Speed HDG Heading HSI Horizontal Situation Indicator HZN Horizon IAS Indicated Airspeed ILS Instrument Landing System IM Inner Marker

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INTRODUCTION



ABBREVIATION/ ACRONYM DESCRIPTION INS Inertial Navigation System IRS Inertial Reference System LMT Limit LNAV Long Range Navigation LOC Localizer MAG Magnetic MB Marker Beacon MFD Multi-function Display MM Middle Marker MON Monitor MSG Message NAV Navigational NCD No Computed Data NM Nautical Miles NVM Non-Volatile Memory OBS Omni Bearing Select OM Outer Marker PELS Pixel Element Light Segments PIT Pitch PROF Profile RA Radio Altimeter, Resolution Advisory REV Reversionary RFI Radio Frequency Interference RID Rotary Input Device RK Rogerson Kratos RNAV Area Navigation ROL Roll SAF Swedish Air Force SAR Search and Rescue STAB Stabilization STBY Standby TACAN Tactical Air Navigation TBD To Be Defined (or Determined) TCAS Traffic Alert and Collision Avoidance System TCN Tactical Air Navigation TTL Tuned To Localizer TTS Time to Station VAPP VOR Approach VG Vertical Gyro VOR Very-High-Frequency Omnirange VORTAC VOR/TACAN VS Vertical Speed

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INTRODUCTION



ABBREVIATION/ ACRONYM DESCRIPTION VSI Vertical Speed Indicator WOW Weight on Wheels WPT Waypoint WX Weather WXA Weather Alert WXR Weather Radar XTK Cross Track

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INTRODUCTION




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DESCRIPTION AND OPERATION

ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 Page 1


1. TC "Description and Operation" \l1Data Sheet

CHARACTERISTIC SPECIFICATION Dimensions Behind the bezel for mounting: 4.875”W X 4.978”T X 9.71”L [123.83mm X

126.44mm X 246.63mm] plus 0.80” connectors [20.32mm] Bezel: 5.080”W X 5.080”T X 0.238”L [129.03mm X 129.03mm X 6.05mm] (knob 1.1” from mount) [27.94mm]

Mechanical Controls (2) Software programmable RID Knob with push buttons (1) Dimmer knob with programmable push button (4) Software Programmable push buttons (1) Photo detection Ambient light sensor

Display Type 4.2 X 4.2 inch [106.68mm X 106.68mm] square AMLCD, 719 X 719 PELS Central Processor Motorola 68020 processor Weight 7.8 lbs. [3.538kg] max. Cooling Passive, natural convection, No forced air cooling required. Connectors /Mating Connectors – J1

Mil-C-38999 Series III 79 pin: D38999/2ING35PN Mating: D38999/26FG35SN, RK P/N 2115-0119

Connectors /Mating Connectors – J2

Mil-C-38999 Series III 79 pin: D38999/2ING35PA Mating: D38999/26FG35SA, RK P/N 2115-0120

Connectors /Mating Connectors – J3

Mil-C-38999 Series III 79 pin: D38999/2ING35PB Mating: D38999/26FG35SB, RK P/N 2115-0121

Electrical – Power +28VDC, +12V to 32VDC. Electrical – Power Consumption

50 Watts max with heaters on 38 Watts max with full brightness 5 Watts max +5VDC bezel lighting

Electrical – Power Interrupt

0 – 50 mS: recovery within 500 msec after interrupt completion

Interface - Synchro Each unit: (6) ARINC 407 Synchro inputs, (2) Resolver outputs Interface – ARINC 429 Each unit: (8) ARINC 429 inputs. (4) ARINC 429 outputs Interface – ARINC 453 Each unit: (1) ARINC 453 inputs compatible to ARINC 708 Weather Radar Interface – ARINC 568 Each unit: (1) ARINC 568 DME input Interface – RS 232 Each unit: (1) RS-422/232 input and output for Ground Support and Data loading Interface – Variable voltage / Current

(12) variable current or voltage inputs, 2 variable DC outputs

Interface – Discrete (16) 28 V / open inputs, (8) 28 V outputs, (32) Gnd/Open inputs, (8) Gnd/Open outputs, (8) EFIS reserved Gnd/Open discretes

Software DO-178B Levels A and B Environmental – Category

B1BANXXXXXSAZAZZYZA3E3XX

Environmental - Temp RTCA/DO-160C, Sec. 5, Cat. B Environmental - Humidity RTCA/DO-160C, Sec. 6, Cat. A Environmental - Shock RTCA/DO-160C, Sec. 7 Environmental - Vibration

RTCA/DO-160C, Sec. 8, Cat. N

Table 2—Data Sheet

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2. Certification Statements

The EFIS Model EFIS 5XX is designed and tested to meet DO-178B level A, DO-160C Environmental (no change from previous TSO baseline), and the following incomplete systems TSO standards listed below. This document specifies the interface connectivity to qualified sensor sources to complete the system requirements of the TSO.

TSO Standards Comment

C3d AS 8004 Mechanical Slip Ball, On-screen Rate of Turn indicator when combined with C3d compatible sensor source.

C4c AS 396 Displays C4c compatible Bank and Pitch information when combined with C4c compatible sensor sources.

C5e SAE 8021 Displays C5e compatible Heading information when combined with C5e compatible sensor sources.

C6d AS 8013 Displays C6d compatible Heading (Mag) information when combined with C6d compatible sensor sources.

C8d SAE 8016 Displays C8d compatible Vertical Velocity information when combined with compatible C8d air data sensor sources

C9c AS 402 Displays annunciations and performs C9c compatible Autopilot functions when combined with AS 402 compatible Autopilots.

C34e RTCA DO-192 Displays C34e compatible indicators when combined with C34e compatible ILS receiver radios.

C35d RTCA DO-143 Displays C35d compatible indicators when combined with C35d compatible Marker Beacon Radio source

C36e RTCA DO-195 Displays C36e compatible indicators when combined with C36e compatible ILS radio sources

C40c RTCA DO-196 Displays C40c compatible indicators when combined with C40c compatible VOR radio sources

C41d RTCA DO-179 Displays C41d compatible indicators when combined with C41d compatible ADF radio source

C52b AS 8008 Displays C52b Flight Direction/annunciation when combined with AS 8008 compatible Flight Director source

C63c RTCA DO-173 Displays C63c compatible WX information when combined with compatible Do-173 weather radar source.

C66c RTCA DO-189 Displays C66c compatible DME information when combined with C66c compatible DME source

C87 TSO-C87 Displays C87 compatible Rad Altitude when combined with C87 compatible radio altimeter source

C92c RTCA DO-161A Displays C92c compatible Terrain Map when combined with compatible C92c GPWS source with Terrain Map.

C105 RTCA DO-174 Displays C105 compatible Wx and Ground Map information when combined with compatible DO-174 WX Computer / sensor.

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C117a TSO-C117a Provides C117a Windshear annunciations when combined with C117a compatible sensor source

C118 RTCA DO-197a Provides C118 compatible traffic display when combined with a C118 compatible TCAS I computer.

C119b RTCA DO-185a Provides C119b Traffic and Resolution Advisory display when combined with C119a compatible TCAS II computer.

C129a RTCA DO-208 Displays C129a GPS map and information when combined with a C129a compatible GPS source.

C151b TSO C151b Provides compatible C151b Terrain Display when combined with a C151b compatible EGPWS.

Current TSOs :The EFIS Model EFIS 520 is designed and tested to meet DO-178B level A, DO-160C Environmental (no change from previous TSO baseline), and the following TSO standards listed below:


C113 AS 8034 Provides C113 compatable Airborne Multipurpose Electronic Display

3. General

A. Overview of Operation

The EFIS 5XX systems provide the flight crew with all primary ADI and HSI functionality on an easy-to-understand high-contrast ratio 5 ATI AMLCD display. In addition, the EFIS 5XX also provides the flight crew with MFD functions that include graphical FMS routing, nearest airports, nearest NAV aids, waypoint information and routing information such as windspeed and direction, ETA, TCAS and EGPWS terrain display (actual features depend on the EFIS 5XX P/N installed). The EFIS 520 also provides the installer with advanced configuration pages and settings, and diagnostic pages to aid in maintenance, installation and support.

(1) EFIS 500

Designed for use in helicopters, the EFIS 500 provides the flight crew with all primary ADI and HSI functionality on a clear, easy-to-understand 5 ATI AMLCD display. The EFIS provides weather radar display in combination with routing information for graphic weather avoidance, Wx profile mode, and BIT (test and results).

(2) EFIS 520

The EFIS 520 includes the same functions as the EFIS 500, and adds additional digital (ARINC 429) interfacing options, EGPWS terrain display, as

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well as TCAS I and TCAS II with resolution advisory capability. In addition, configuration and diagnostic pages aid installation and checkout. The EFIS 520 can be configured for either fixed wing aircraft or rotorcraft.

(3) EFIS 520 SAR

The EFIS 520 SAR includes the same functions as the EFIS 520, and adds additional interfacing and display options to handle doppler radar input and Search and Rescue hover operations. The EFIS 520 can be configured for either fixed wing aircraft or rotorcraft. The EFIS 520 SAF is a variant of the EFIS 520 SAR and references to SAR apply to the SAF version as well unless otherwise noted.

B. Physical Description

The EFIS 5XX is a self-contained unit that can be utilized in multiple locations in the cockpit. The EFIS 500 can be configured for single or dual EFIS. The EFIS 520 can be configured for single MFD or EHSI, dual EHSI, single EFIS (one EADI, one EHSI), dual EFIS, or combinations of each with separate MFDs.

NOTE: The terms “on-side” and “off-side” used in this manual refer to the EFIS installation location relative to dual sensors. Thus, co-pilot VOR selection of VOR 2 is on-side and co-pilot selection of VOR1 is off-side. Sensor designators can be configured by maintenance personnel upon installation of the EFIS system. When the Pilot Reference Designator is set to 2 (PILOT REF DSG on configuration page 3), reference designators are changed (i.e. VOR 1 becomes VOR 2) in all instances and modes.

The EADI and EHSI use the same bezel configuration; each bezel is split into two sections: a vertical section and a horizontal section. The vertical section contains four softkeys ("M", "N", "B" and "R") and a rotary/push-button switch ("DIM", part of the bezel-mounted rotary push-button “DIM” - “TST/REF” control). The horizontal section contains two rotary push-button switches ("CRS SEL" and "DH/HDG SEL") and an inclinometer on the EADI (see Figure 2). On the EHSI, a cover is provided on the chassis for the inclinometer (see Figure 3).

See

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Figure 1 for additional physical dimensions and data.

C. Failure Notification and Comparison Monitoring

The EFIS is also able to display any internal failures for crew notification and maintenance purposes; records of these failures are stored in NVM. External equipment failures are displayed and recorded into NVM as well.

In addition, comparison monitoring is used to determine any possible display of misleading information when a dual EADI/EHSI installation is deployed. The heading comparison is disabled when the on-side and off-side sources do not match

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(i.e., MAG vs. TRUE). The LOC/GS comparison monitoring is only active when both NAV receivers are tuned to the same frequency.

The comparison monitoring function does not adversely affect the display of information in case of discrepancy. That is, the display of a parameter and/or data is provided along with the miscompare annunciations. No comparison is made on invalid parameters.

D. Data Retrieval

The EFIS provides sufficient information on the display to isolate box-level maintenance. In addition, the EFIS interfaces to GSE to allow data retrieval for component-level maintenance.

NOTE: This interface is not required for aircraft installation or test, and is used by RK field personnel or the factory, only.

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ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 Pages 9/8


Figure 1—EFIS Outline Drawing (all P/Ns covered in this document)

M

N

B

R

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Figure 2—EFIS (EADI Configuration), Typical Physical Appearance

(EFIS 520 SAR & EFIS 500 shown) NOTE: Note the inclinometer on the horizontal bezel.

Figure 3—EFIS (EHSI Configuration), Typical Physical Appearance

(EFIS 520 & EFIS 500 shown)

NOTE: Note the inclinometer cover on the horizontal bezel.

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4. Product Operation

A. Controls (5XX Series)

The controls located on the vertical indicator bezel (see Figure 2 and Figure 3) are described in Table 3.

MODE BEZEL

BUTTON ADI HSI COMPOSITE

FORCED

M ADI =

COMPOSITE MODE SELECT DH SELECT

N INACTIVE NAV SOURCE

SELECT NAV SOURCE

SELECT B INACTIVE BEARING SELECT BEARING SELECT R INACTIVE RANGE SELECT INACTIVE

Table 3—Bezel Mode Button Control Descriptions

B. EFIS 5XX Operation

(1) EADI Bezel Functions (see Figure 2)

(a) DIM and TST

The DIM and TST control is a combined display brightness and display test control. Rotate this knob to adjust the display brightness. Push the knob for a least 4 seconds to initiate the display self-test. When the test is selected, normal symbology and failure flags are displayed. The self-test is terminated automatically after approximately 10 seconds.

NOTE: The self-test cannot be performed if the EFIS is in composite mode.

(b) RA Test

Momentarily push the RA Test button to send a discrete signal to the radio altimeter to enter self-test mode.

(c) HZN SYNC

If the aircraft straight and level flight presents a steady non-zeroed pitch attitude, activation of this control brings the horizon line back to the middle of the display. However, two yellow marks remain, indicating the true horizon position. An additional activation of “HZN SYNC” or selection of composite mode causes the horizon sync mode to end.

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(d) "M" Button

Press this button to toggle between normal ADI and composite mode.

(e) "N," "B" and "R" Buttons

These controls are inactive in operator-entered composite mode, and revert to HSI functionality when the ADI enters forced (or automatic) composite mode.

(2) EADI Function and Display Format Structure

ADI collective cue and ILS mode is illustrated in Figure 4.

Figure 4—ADI Collective Cue and ILS Mode

(EFIS 520 & EFIS 500 shown)

(a) FD Mode Annunciations

Valid FD mode annunications are shown in Table 4.

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COLLECTIVE CUE LATERAL CUE VERTICAL CUE Capture (Green)

Arm (White)

Capture (Green)

Arm (White)

Capture (Green)

GA NAV VAPP LNV LOC BC

NAV VAPP LNV LOC BC HDG

GS ALT GS IAS VS GA

Table 4—FD Mode Annunciations

NOTE: Since only the NAV input is provided by the FD to the EFIS, the EFIS changes the “NAV” legend to “LNV” or “LOC” according to the nav type selected.

As the modes transition from arm to capture, the green capture annunciation flashes for five seconds (see Table 5 for transition detail).

LATERAL TRANSITIONS VERTICAL TRANSITIONSNAV ARM ⇒ NAV CAP LOC ARM ⇒ LOC CAP BC ARM ⇒ BC CAP VAPP ARM ⇒ VAPP CAP

ALT ARM GS ARM ⇒ GS CAP

Table 5—Lateral and Vertical Transitions

(b) Radio Altimeter (RA) Display

A cyan four-digit display is located at the upper right corner of the screen with the white “RA” legend located beside the radio altitude value (see Figure 5).

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Figure 5—ADI Format (EFIS 500)

The radio altitude range is from –20 feet to a maximum value selected in the configuration page with the resolution shown in Table 6:

RANGE RESOLUTION≤ 200 feet 5 feet > 200 feet 10 feet

Table 6—Radio Altitude Range/Resolution

The display is removed for altitudes greater than the maximum value selected in the configuration page.

(c) Decision Height (DH) Display

A cyan 3-digit display indicates the DH value. The set range is from 0 to 2500 feet with the following resolution:

RANGE RESOLUTION≤ 200 feet 1 foot > 200 feet 10 feet

Table 7—Decision Height Range/Resolution

The DH display is only shown when the radio altitude displayed. The display may be removed by adjusting the set control to less than 0 feet. When radio altitude decreases to or moves below the DH value set, a yellow “DH” is displayed in the middle of the upper half of the ADI sphere.

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(d) Rate of Turn Display (optional)

A white-filled “T” shaped pointer displays the rate of turn and a scale with 3 unfilled white rectangles (indexes) is placed under the expanded localizer. The rate of turn of the aircraft is indicated by the position of the pointer against scale indexes (left or right), representing a standard rate of turn (two minutes or three degrees per second turn rate).

If the turn deviation exceeds any limit of the scale (left or right), the pointer stops moving after the last index and shows half its full width.

The rate of turn indicator is removed in composite mode.

(e) Inclinometer

The inclinometer consists of a hardware subassembly mounted in the lower part of the bezel. The inclinometer gives the pilot a conventional display on aircraft slip or skid to be used as an aid to coordinated maneuvers. It contains a white ball with white indexes and operates smoothly with a minimum roll rate of six degrees per second. Adjustment slots on the mount provide a means for leveling the inclinometer.

NOTE: The inclinometer is only used on the EADI unit. Although physically present on the EHSI unit, a cover is provided to shield the inclinometer from view.

(3) EADI Approach Mode

When the TTL input is active GS and localizer data are displayed on the EADI (see Figure 6). When an LNV source that provides approach mode pseudo glideslope or vertical navigation data is selected for primary navigation, this scale is presented as above except the pointer is cyan with the text “VN” inside and with a white annunciator of “FT” or “AN” above. "FT" indicates ENROUTE/TERMINAL mode and "AN" indicates APPROACH mode. In addition, the rising runway displays absolute reference above the terrain when the aircraft is below 200 feet.

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Figure 6—ADI Collective Cue, ILS Mode (EFIS 500)

(a) Rising Runway

The green rising runway appears at 1500 feet, begins rising toward the aircraft symbol at 200 feet, and contacts the bottom of the symbolic aircraft at touchdown. The rising runway is centered on the localizer pointer.

The rising runway is removed when the radio altitude validity input is not present or the BC input is active.

(b) Marker Beacon (MB) Display

MB information is displayed at the upper left side of the screen just below the FD annunciation position. The MB annunciation consists of dual letters enclosed in an unfilled white-outlined hexagonal box. Marker colors are as follows in Table 8:

MARKER COLOR Outer Marker (OM) Cyan Middle Marker (MM) Yellow Inner Marker (IM) White

Table 8—Marker Beacon Colors

(4) EADI Monitors Fault Annunciations

The EADI presents the following fault annunciations as appropriate:

(a) Same Attitude Source (dual EFIS).

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If the pilot and copilot have selected the same attitude source (ATT1 or ATT2), the attitude source is annunciated in yellow. If the pilot and copilot are using their normal attitude source, there is no attitude source annunciation.

(b) Comparison Monitor (dual EFIS).

Selected pilot and copilot input data is compared in each EADI. If the difference between the data exceeds predetermined threshold levels, a miscompare annunciation is displayed. Initially, this annunciation flashes at 1Hz for five seconds. The miscompare indications (see Table 9) are annunciated with a yellow-filled box and black lettering. When the compared pitch and roll attitude or GS and LOC signals are out of tolerance, the system displays a combined label (ATT or ILS).

COMPARED SIGNALS

DISPLAYED SYMBOL

Pitch Attitude PIT Roll Attitude ROL Pitch and Roll Attitude ATT Heading HDG Localizer LOC (See note) Glideslope GS (See note) Localizer and Glideslope ILS (See note) Radio Altitude RA

Table 9—Comparison Monitor Signals and Symbols

NOTE: These comparisons are active only when both NAV receivers are tuned to the same ILS frequency.

(c) Attitude Failure

If there is attitude failure, the sphere is painted entirely sky blue, and a red-filled box with white “ATT” legend is displayed in the upper half of the sphere.

(d) Glideslope, Expanded Localizer and Rate of Turn Failures

If any of these systems fail, the affected indicator is removed and replaced with a yellow box and the appropriate text in black letters.

(e) Radio Altitude Failure Annunciation

If the radio altimeter fails, a yellow box with a black “RA” replaces the numerical values and the rising runway, and any DH displays are

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removed from the screen. Localizer information is not removed,

(f) FD Failure Annunciation

If the FD computer fails, a black “FD” is displayed in a yellow box in the center of the display just below the ATT failure indication position. In addition, the FD command bars and mode annunciations are removed from the screen.

(g) Internal Failure

In the event of an internal failure, the screen displays a yellow box with black “FAIL”, or may be completely blank (depending upon the type of failure).

(5) EHSI Bezel and Display Definition

(a) Display Brightness and Display Test (DIM and TST)

The DIM and TST control is a combined display brightness and display test control. Rotate this knob to adjust the display brightness. Push the knob to initiate the display self-test. When the test is selected, normal symbology and failure flags are displayed. The self-test is terminated automatically after approximately 10 seconds.

(b) Course (CRS Select)

Use the “CRS” select knob to set the course pointer and associated digital readout to the desired course. Momentarily press the “CRS” knob to provide direct to function.

(c) Heading (HDG) Select

Use the “HDG” select knob set the heading bug and associated digital readout to the desired heading. A momentary press of the HDG knob causes the heading bug and digital readout to “sync” to the present aircraft heading.

(d) Bezel Button Configurations

1 Mode Selection (“M” button) (EFIS 500)

Momentary pressing the “M” button on the EFIS 500 cycles through the following modes:

• Normal HSI Mode (default mode) (see Figure 7)

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• Full MAP (see Figure 8) • ARC (120° compass card) (see Figure 9) • ARC MAP (see Figure 9) • ARC WX (see Figure 10) • ARC MAP + Wx (see Figure 10) • Wx Vertical Profile (see Figure 11) • Composite Mode (see Figure 12)

On the next button push, the display returns to normal HSI mode.

Figure 7—EHSI Normal Mode (EFIS 520 SAR)

Figure 8—HSI Map Mode (EFIS 500)

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Figure 9—HSI ARC Map Mode (EFIS 500)

Figure 10—HSI ARC Map and Wx Mode (EFIS 520)

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Figure 11—Vertical Profile Mode (EFIS 520)

VS1200

Figure 12—EHSI Composite Mode (EFIS 500)

2 Mode Selection (“M” button) (EFIS 520)

Momentary pressing the “M” button on the EFIS 520 cycles through the following modes:

• Full Rose • Full Rose + MAP • ARC (90° compass card) • ARC MAP • ARC MAP + Wx • Wx Vertical Profile

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• Composite Mode

On the next button push, the display returns to normal HSI mode.

3 Primary Nav Source select (“N” button) (EFIS 5XX)

Momentary pressing the “N” button cycles through the available NAV sensors as follows:

• VOR1/TCN1 or LOC1 (if tuned) • VOR2/TCN2 or LOC2 (if tuned) • LNV 1 (or LNV if single) • LNV 2 (if installed)

The sequence begins again with the next button push. Each change of the navigation source results in sending a NAV pulse discrete of one-second duration to the FD system. Changing from VOR1 to VOR2 toggles the DME transfer discrete to the VOR; this allows the VOR to detect which DME function to use.

4 Bearing Pointer #1/#2 Select (“B” button) (EFIS 5XX)

Push the “B” button on the EHSI. The current bearing 1 source identifier is boxed in magenta and a “BRG 1” legend is shown in lieu of “HDG” and its readout. Rotate the HDG SEL knob (CW or CCW) until the desired bearing source is shown.

Push the “B” button to advance to bearing 2 selection. Rotate the HDG SEL knob (CW or CCW) until the desired bearing source is known.

Push the “B” button to exit bearing selection.

NOTE: The beginning selection mode is exited after five seconds of button knob inactivity. If the “B” is pushed after exiting, the selection process starts with bearing 1. If no changes are desired for a bearing source, press “B” again to proceed to the next phase.

The bearing 1 source can be selected as OFF, VOR/TCN, LNV, ADF, DF (if installed), REPEAT (LNV/VOR/TCN are depicted as LNV1/VOR1/TCN1, if two sources of that type are configured).

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The bearing 2 source can be selected as OFF, VOR/TCN, LNV, ADF, DF (if installed), REPEAT (LNV/VOR/TCN are depicted as LNV2/VOR2/TCN2 if two sources of that type are configured).

NOTE: Sensor designators can be configured by maintenance personnel upon installation of the EFIS system. When the Pilot Reference Designator is set to 2 (PILOT REF DSG on configuration page 3), reference designators are changed (i.e. VOR 1 becomes VOR 2) in all instances and modes.

5 Range Function (“R” button) (EFIS 5XX)

• Push the “R” key on the EHSI. The current mid-range value is boxed in magenta and a RNG legend is shown in lieu of HDG and its readout.

• Rotate the HDG SEL knob (CW or CCW) until the desired mid-range value is shown.

• Push the “R” button to exit the range selection process. The yellow box is removed from the display.

NOTE: The range selection mode is exited after five seconds of button/knob inactivity. Also, the full range value is boxed for the vertical profile WX format.

6 To select the DH value while in Composite Mode:

• Push the “M” button on the healthy indicator. The current DH value is boxed in magenta and the readout also changes to yellow.

• Rotate the DH knob (CW or CCW) until the desired value is shown.

• Push the “M” key to exit DH selection mode. The yellow box is removed and the readout turns to cyan.

NOTE: DH select while in Composite Mode is only applicable during forced composite operations (i.e. EFIS same side unit has failed).

7 DME or LNAV Reference Data

If an LNAV source is installed and selected, ground speed (GSPD) or time to station (TTS) are alternatively displayed by pressing the TST/REF button. GSPD (knots) and TTS (minutes)

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are displayed in green on the top right of the screen (see Figure 13).

Figure 13—HSI Format (EFIS 500)

When DME hold is selected, the distance displayed is white and a yellow “H” is added to the left of the held distance information.

NOTE: In the case of a primary NAV source failure other than LNAV, the DME HOLD information remains displayed in the HSI upper-right corner.

Three yellow dashed lines replace the DME digital readout when the DME is invalid (fail) or missing.

8 LNAV Annunciations

• “WPT” is annunciated in yellow to alert an upcoming waypoint passage.

• “MSG” is annunciated in yellow to indicate there is a message to be viewed on the GPS unit message page.

• “MSG” (message) “DR” (Dead Reckoning) and“WPT” (waypoint) annunciations are displayed at the right hand side of the lubber line; the annunciations flash for five seconds and are then solid.

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C. HSI MODE

(1) Magnetic/True Heading Annunciation

When the primary source is an LNAV system, reference can be either magnetic or true heading. When the compass card is in true mode, a yellow “T” is displayed near the heading fore lubber line. Magnetic heading is displayed by default with no additional annunciation indicating magnetic heading.

(2) Heading Select Bug and Heading Select Display

Use the HDG SEL knob to position the notched magenta (cyan for 520 SAR) heading select bug on the rotating compass card and to display a preselected compass heading. The bug spans 10° and rotates with the compass card. The difference between the bug and the lubber line index is the amount of heading error applied to the FD computer.

NOTE: Use the digital heading select display next to the HDG SEL knob when setting the heading bug.

(3) Course Select Pointer

The green course pointer is positioned on the rotating heading dial by the CRS knob to select the desired VOR radial or localizer course. The course pointer rotates with the rotating compass card. The difference between the arrow head and the heading lubber line is the amount of course error sent to the FD computer. The CRS select pointer is linked on both EHSIs when the same NAV source is selected.

When a long range navigation (LNAV) sensor is installed and selected, the course pointer is replaced by a cyan desired track (DTK) pointer. The position of the DTK pointer is controlled by the LNAV system. A digital display of DTK replaces the CRS readout.

In approach mode, the runway course is selected using the CRS selection. Setting the CRS selection 105 deg from the heading will put the unit in Back Course mode. This inverts the Localizer indicator on the ADI and lights the BC annunciator in place of the Glide Slope indicator.

(4) Not in Command Indicator

A green arrow is placed underneath the heading select or course select readout on the EHSI not in command. The green arrow is controlled by the EFIS in command discrete and points at the EFIS in command.

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D. External Selection of EGPWS Terrain and TCAS Traffic (EFIS 520 Only)

The EFIS 520 has the capability to display EGPWS terrain data, and TCAS I and TCAS II traffic data and resolution advisories.

(1) EGPWS Terrain Displays

Selection of the exterior EGPWS terrain button displays EGPWS ARINC 453 terrain data in an ARC format (see Figure 14).

Figure 14—EFIS 520 Map + Traffic + TAWS Display

A secondary push of the Terrain button deselects terrain data and reverts to Wx mode.

The EFIS 520 also supports EGPWS Terrain Pop-up mode. The EFIS 520 senses the discrete EGPWS discrete input then pops-up to the ARC format with terrain data. The EGPWS system and control panel handles all annunciations. The EFIS 520 only provides annunciation that the terrain mode is selected (“TERR” as in seen in Figure 14).

(2) TCAS I or TCAS II Displays

The EFIS 520 supports both TCAS I and TCAS II systems. Traffic is selected via the exterior TRAFFIC selection, or by the optional pop-up mode. Selection of traffic data sends EFIS to the next MAP format in the mode sequence and displays TCAS Traffic data in standard TCAS symbology (see Figure 15).

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Figure 15—EFIS 520 TCAS Traffic Data

The installer can also select to have TCAS traffic data pop-up when a resolution advisory is received from TCAS. This is deselected in the EFIS 520 configuration pages. If pop-up mode is enabled, the display pops up TCAS traffic data in a rose map format (see Figure 15) when a resolution advisory is received from TCAS.

(3) TCAS Resolution Advisories

The EFIS 520 also supports TCAS II resolution advisories. The vertical speed indicator (VSI) is shown on the EHSI in tape with moving pointer format. TCAS resolution advisories are displayed with red “don’t fly” and green “fly to” bands on the VSI. TCAS II configuration enables the resolution capability. Resolution Advisories are unaffected by the TRAFFIC selection.

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(4) Doppler Hover Mode.

Figure 16—EFIS 520 SAR Doppler Hover Mode

The EFIS 520 SAR supports configuration for the display of a Doppler Radar Hover mode as a sub-mode of the Rose Map. The display shows magenta velocity cue bars in both the X (Forward and Aft) and Y (Right and Left) around the helicopter symbol and includes a cyan velocity cue scale. In Hover Mode, the Half range scale in MAP mode is removed and replaced by a full scale range annunciated on top left side compass rose.

E. Self-Test Mode

When the TEST button is pressed and held for four seconds, a test flag (black “TEST” in a yellow box for 500, black “TEST” in a cyan box for 520) appears in the upper left quadrant of the screen and the following information is displayed:

(1) EADI

(a) Phase 1

Pitch is at 10° up, roll is at 20° right, FD pitch roll centered, expanded localizer and glideslope are centered and radio altitude is at 100 feet (see Figure 17).

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Figure 17—ADI Self-Test Mode, Phase 1(EFIS 500)

(b) Phase 2

EFIS 500: Attitude is flagged with a red box and "ATT" in white letters. If configured, flight director is flagged with a red box and "FD in white letters. Glideslope is flagged with a red box and "GS" in white letters. If configured, radio altimeter is flagged with a red box and "RA" in white letters and localizer is flagged with a red box and white "LOC" letters.

EFIS 520: Attitude is flagged with a red box and "ATT" in white letters. If configured, flight director is flagged with a yellow box and "FD in black letters. Glideslope is flagged with a yellow box and "GS" in black letters. If configured, radio altimeter is flagged with a yellow box and "RA" in black letters and localizer is flagged with a yellow box and black "LOC" letters.

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Figure 18—ADI Self-Test Mode, Phase 2 (EFIS 500)

(2) EHSI Self-Test Mode

(a) Phase 1

Heading is at 0°, selected course is at 0°, selected heading is at 0°, distance to go is at 0.0 NM, glideslope deviation is centered (see Figure 19).

Figure 19—EHSI Self-Test Mode, Phase 1 (EFIS 500)

(b) Phase 2

EFIS 500: Selected navigation source is flagged with a red box and white letters (VOR, VOR1, VOR2 or GPS). Selected bearing pointers

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are flagged with a red box with white letters (VOR, VOR1, VOR2 or DF). Glideslope is flagged with a red box and white letters “GS”. Heading is flagged with a red box and white letters “HDG”. Weather radar is flagged with a red box and white letters “WX” if the current configuration indicates WX is present (see Figure 20). Any existing failure of the specified functions remains failed when the self-test is completed. Self-test is not allowed when composite mode is selected.

EFIS 520: Selected navigation source is flagged with a yellow box and black letters (VOR, VOR1, VOR2 or GPS). Selected bearing pointers are flagged with a yellow box with black letters (VOR, VOR1, VOR2 or DF). Glideslope is flagged with a yellow box and black letters “GS”. Heading is flagged with a red box and white letters “HDG”. Weather radar is flagged with a yellow box and black letters “WX” if the current configuration indicates WX is present. Any existing failure of the specified functions remains failed when the self-test is completed. Self-test is not allowed when composite mode is selected.

Figure 20—EHSI Self-Test Mode, Phase 2 (EFIS 500)

F. Maintenance Mode

To enter Maintenance mode, push the dimmer button until self test engages, then push and hold the “R” and “B” buttons. The following information is displayed in this mode:

• Software title, version number and build date • Analog I/O board version

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• Digital I/O board version • Display generator version • An alert that NVM error information is present • M-net status

G. LNAV Configuration Page

(1) EFIS 500

• The LNAV configuration page is accessed from the Maintenance Page menu. Push the “N” button while the maintenance page is displayed to display the LNAV configuration page.

• With the LNAV configuration page is displayed, push the “N” button to scroll through the selection options.

• Push “R” to select the highlighted selection. • Press “M” to return to the Maintenance Page.

(2) EFIS 520

The EFIS 520 provides more extensive configuration pages than the EFIS 500 allowing the installer to select from a variety of input sensors/radios and configuration settings. In addition, the EFIS 520 allows the user to configure only one display (pilot EHSI) then update the configuration on the other displays. See the Configuration/Installation Checkout section (page 401) for additional information about the EFIS 520 configuration options.

H. Diagnostic Pages

The EFIS 520 provides the installer and maintenance personnel with diagnostic pages allowing the user to see real-time input values. This greatly aids diagnosing problems in the system installation or operation. See the Configuration/Installation Checkout section (page 401) for additional information on diagnostic procedures.

I. WXR Calibration Pages

The WXR calibration pages will be entered from the System Status page via the ‘B’ and ‘R’ keys and will display the information provided by Bendix/King.

Bezel button "B" initiates WX R/T calibration display mode, which displays various operational parameters of the WX R/T such as gain, pitch angle, roll angle, tilt, azimuth, and faults.

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Bezel button "R" initiates WX maintenance display mode, which displays without interpretation 12 rows of twenty characters (ASCII subset) each, as provided by the WX R/T.

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TESTING AND FAULT ISOLATION



1. TC "Testing and Fault Isolation" \l1General

WARNING: This unit exhibits a high degree of functional reliability. Nevertheless, users must know that it is not practical to monitor for all conceivable system failures and that, however unlikely, it is possible that erroneous operation could occur without a fault indication. The pilot has the responsibility to find such an occurrence by means of cross-checks with redundant or correlated data available in the cockpit.

The configurable EFIS 5XX uses built-in test (BIT) to test the operational integrity of the system. Monitoring occurs automatically at power-up, and is continuous during operation.

2. Manual BIT Initiation

• Press and hold the display TEST button (on the bezel control panel) for five seconds to place the EFIS unit into BIT mode. The unit will return to normal mode after it completes the self-test process.

• To stop a manual BIT, press the “M” button.

3. Limitations

Testing and fault isolation of the configurable EFIS 5XX is dependent upon the type of aircraft installation involved.

See the Configuration/Installation Checkout section of this manual (page 401) for an installation checkout procedure.

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TESTING AND FAULT ISOLATION




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INSTALLATION/REMOVAL



1. TC "Installation/Removal" \l1General

This section describes the general mounting options and diagrams and the general mechanical installation and removal procedure for the unit. Refer to Wiring Harness Requirements and Options (page 301) and Configuration/Installation Checkout (page 401) for additional configuration options and installation checkout procedures.

The flow of a typical installation is shown in Figure 21.

Determine mountinglocation of system

components

Determine otheravionics suite andEFIS configuration

Construct and installwire harness

Install EFIS 5XXusing instrumentmounting clamp

Check wire harness

Apply power tosystem

Check software andhardware

configurationselections

Perform checkoutprocedure

Installation Complete

Figure 21—Typical EFIS 5XX Installation Procedure

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2. Advisories

WARNING: Service personnel are to follow standard safety precautions, such as wearing safety glasses, to prevent personal injury while installing or maintaining this unit. This unit may have piece parts that contain materials (such as beryllium oxide, acids, lithium, radioactive material, mercury, etc.) that can be hazardous to your health. If the piece part enclosure is broken, handle the piece part in accordance with OSHA Requirements 29CFR 1910.1000 or superseding documents to prevent personal contact with or inhalation of hazardous materials. Since it is virtually impossible to determine which piece parts do or do not contain such hazardous materials, do not open or disassemble piece parts for any reason.

CAUTION: Before handling any unit or unit component, ground the repair operator through a conductive wrist strap or other device that uses a 470k92 or 1MΩ series resistor to prevent personnel injury. Turn off power before disconnecting any unit from wiring. Disconnecting the unit without turning power off may cause voltage transients that can damage the unit.

CAUTION: ESDs are subject to damage by excessive levels of voltage and/or current, just as are more conventional semiconductor devices. However, the precautions normally used to protect semiconductors are not sufficient for the protection of ESDs because of their very high electrical resistance. The low-energy source that most commonly destroys ESDs is the human body which, in conjunction with nonconductive garments and floor coverings, generates and retains static electricity. In order to adequately protect ESDs, the device and everything that contacts it must be brought to ground potential by providing a conductive surface and discharge paths. The following precautions must be followed:

• De-energize or disconnect all power and signal sources and loads. • Place the unit on grounded conductive surface. • Ground the repair operator through a conductive wrist strap or other device using a

470KW or 1MW series resistor to prevent unit or unit component damage. • When ESDs and assemblies are not in the unit, they should be kept on the

conductive work surface or in conductive containers. When a device or assembly is inserted or removed from a container, the operator should maintain contact with the conductive portion of the container. Do not use plastic bags unless they have been impregnated with a conductive material.

9976-0041 Rev F




• Do not handle ESDs unnecessarily or remove them from their packages until actually used or tested.

3. Installation Considerations

The EFIS 5XX is highly configurable and supports many installation options that depend on the aircraft type, sensor suite, and navigation suite. To support this, the EFIS 5XX system offers more interfaces and configurations than are required for a single application.

Factors to consider while determining the best configuration for your specific application include:

• Number of EFIS, EHSI, or MFD: MFD or EHSI, Dual EHSI, Single EFIS, Dual EFIS, combinations of MFD.

• Aircraft type: Helicopter or Fixed Wing • Aircraft sensors (AHRS, DG/VG, Rad Alt) Digital (ARINC 429) or Analog Synchro • Nav sources (VOR, ADF, DF, TACAN, FMS), number of each and signal type (analog

– synchro or Digital –ARINC 429) • Weather Radar • TCAS (TCAS I or TCAS II), Display Resolution Advisory or not • EGPWS • Vertical Speed Indicator

4. Initial Installation

A. Aircraft Preparation

(1) Cabling

Observe the following precautions when preparing interconnect wiring cables.

• Keep the connecting cables away from circuits/wires carrying heavy current, equipment transmitting pulses or other sources of interference.

• Bond and shield all parts of the aircraft electrical system such as generators and ignition systems.

• Use 3-inch [76.2mm] #22 AWG wire for connection of ARINC 429 bus ground shields to aircraft ground. Connections are at both ends of the shielded wires. If a 3-inch [76.2mm] length cannot be met, keep length as short as possible.

• Make all external connections to the equipment through designated connectors listed in the data sheet (see Table 2).

• Leave slack in cables to allow for free sway of the equipment. • Avoid long wire runs.

9976-0041 Rev F




• Connect primary power to indicated components through airframe circuit breakers.

• For all wires indicated as twisted and shielded, make shield grounds at the electronics rack shelf-interconnect points (when applicable), and at production breaks.

• Provide separate alternating current and direct current grounds. Direct current grounds may be individual local grounds.

• For ease of R&R operation, leave enough slack in the cable set to allow the unit to slide forward to gain access to the connector with hand.

(2) Wire Type

The wire types designated in Table 10 are recommended for use in the aircraft wire bundles.

FUNCTION WIRE TYPE Serial data bus #22 AWG, twisted shield pair, Teflon insulated wire Analog discrete signal #22 AWG, Teflon insulated wire Analog synchro/resolver #22 AWG, triple-shielded, Teflon insulated wire Strapping pin #22 AWG, Teflon insulated wire

Shield ground wires #22 AWG, Teflon insulated wire, 3-inch [76.2mm] length

Table 10—Recommended Wire Types for Aircraft Wire Bundles

B. Equipment Preparation

(1) Mechanical Check

As shipped from the factory, the EFIS 5XX is ready for installation in the aircraft.

(a) Carefully unpack the equipment and inspect for possible shipping damage. All claims for damage should be filed with the transportation company involved. If claims for damage are to be filed, save the original packing carton and materials.

(b) Ensure that screws securing subassemblies and cover to the chassis have not vibrated loose in shipment. Tighten any loose screws, one turn at a time, until all are tight.

CAUTION: Do not use excessive force when tightening screws. To do so may cause damage to the assemblies or cover.

9976-0041 Rev F




(2) EHSI Unit Preparation

Remove the inclinometer cover located on the case of the unit and install over the slip ball indicator.

(3) EADI Unit Preparation

Make sure that the slip ball indicator is visible and do not remove the inclinometer cover on the case of the unit.

(4) Preinstallation and Postinstallation Checkout

Preinstallation and postinstallation checkout procedures are presented in the Configuration/Installation Checkout section of this manual (see page 401).

5. Mounting Requirements

A. EFIS 5XX Flat Panel Indicator

Use the EFIS 5XX outline a

9976-0041 Rev F




nd mounting diagram (see

9976-0041 Rev F




Figure 1) to determine mounting requirements for your installation.

(1) Mounting Kits

EFIS 5XX installation kits are available from Rogerson Kratos and can be ordered from the part number listed in Table 11.

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CONTENTS

RK Kit P/N Description

Mount (qty)

Connector (qty)

RK P/N 2115-0119

Connector (qty)

RK P/N 2115-0120

Connector (qty)

RK P/N 2115-0121

Backshell (qty)

RK P/N 2151-0033

Installation Manual Ref.

SP-0624-0003 0 angle mount w/ MS24693BB52 mount screws 4 4 4 4 12 1

Table 12 Figure 22

SP-0624-0004 0 angle mount w/ MS35214-44 mount screws 4 4 4 4 12 1

Table 12 Figure 22

SP-0624-0005 3.5 deg angle mount w/ MS5214-46 mount screws 4 4 4 4 12 1

Table 12 Figure 22


Table 12 Figure 22

SP-0624-0007 6.0 deg spacer 4 --- --- --- --- 1

Table 12 Figure 22


Table 12 Figure 22

SP-0624-0009 3.0 deg spacer 4 --- --- --- --- ---

Table 12 Figure 22

SP-0624-0010 Mooring Plate 4 --- --- --- --- ---

Table 12 Figure 22

SP-0624-0011 Adapter Plate 4 --- --- --- --- ---

Table 14 Figure 24

SP-0624-0012 4" Flush mount (nonpreferred) w/ MS24693BB276 mount screws 4 4 4 4 12 1

Table 13 Figure 23

SP-0624-0013 4" Flush mount (nonpreferred) w/ MS35215-57 mount screws 4 4 4 4 12 1

Table 13 Figure 23

Table 11—Mounting Kits

(2) Mounting Options

Clamp and adapter plate mounting options provide additional aids for simple installation.

(a) Clamp Configuration 1

Figure 22 REF

RK P/N ARINC #408

SPEC A

±.010 B

±.010 C

±.005 D

±.005 E

±.010 F

REF. ANGLE

±1° MOUNTING SCREWS

ADJUSTING SCREW

RK KIT P/N REF

2803-0048 5ATI-S 4.975 4.975 4.810 4.810 0.476 6.360 0 MS24693BB52 MS35214-50 SP-0624-00032803-0049 5ATI-S 4.975 4.975 4.810 4.810 0.476 6.360 0 MS35214-44 MS35214-50 SP-0624-00042803-0052 5ATI-S 4.975 4.975 4.810 4.819 0.576 6.360 3.5 MS35214-46 MS35214-50 SP-0624-00052803-0050 5ATI-S 4.975 4.975 4.810 4.810 0.428 6.430 6.0 MS35214-41 MS35214-50 SP-0624-00062803-0014 SPACER 5.010 5.010 4.810 4.810 0.488 6.395 6.0 --- --- SP-0624-00072803-0051 5ATI-S 4.975 4.975 4.810 4.810 0.428 6.430 3.0 MS35214-47 MS35214-50 SP-0624-00082803-0015 SPACER 5.010 5.010 4.810 4.810 0.488 6.395 3.0 --- --- SP-0624-0009

2803-0002 MOORING

PLATE 5.175 5.175 4.810 4.810 5.010 5.010 0.488 --- --- SP-0624-0010

Table 12—Clamp Configuration 1

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Figure 22—Clamp Configuration 1

(b) Clamp Configuration 2

Figure 23 REF RK P/N RK SPEC A B C D T

RK SCREW

ADJUSTING SCREW

RK KIT P/N REF

2803-0046 5ATI-S 4"DEEP 4.975 4.810 6.360 4.00 0.050 MS24693BB276 MS51957-75 SP-0624-0012

2803-0047 5ATI-S 4"DEEP 4.975 4.810 6.360 4.00 0.050 MS35215-57 MS51957-75 SP-0624-0013

Table 13—Clamp Configuration 2

Figure 23—Clamp Configuration 2

9976-0041 Rev F




(c) Adapter Plate

Figure 24 REF

RK P/N OTHER

P/N A

±.010 B

±.010 C

±.005 D

±.005E

±.010F

±.00 G

±.010H

±.010I

±.010J

±.010K

REF.L

REF. M

±.003 RK KIT

P/N REF 2153-0001 5ATI-S 5.175 5.175 4.810 4.810 5.010 5.010 5.095 5.095 0.513 0.488 6.480 6.395 0.196 SP-0624-0011

Table 14—Adapter Plate Configuration

Figure 24—Adapter Plate Configuration

(3) Cooling Requirements

The EFIS 5XX is passively cooled by natural convection and does not require forced-air cooling. Additionally, holes in the instrument-mounting clamp allow for airflow.

(4) Location

The EFIS 5XX is designed for mounting in existing spaces in the aircraft cockpit that currently hold electromechanical configurable 5ATI-size ADI or HSI indicators.

NOTE: In some installations, the spaces may have to be enlarged from size 4ATI to size 5ATI.

9976-0041 Rev F




6. Mechanical Removal/Replacement

A. Removal

(1) Remove power to the system through the aircraft power circuit breaker or other means.

(2) Loosen the four screws holding the unit in the mounting clamp.

(3) Slide the unit out far enough to reach the rear connectors.

(4) Unscrew the three Mil-C-D38999 mating connectors.

(5) Remove the unit.

Leave mating connectors/harness connections extended from the clamp for easy access with the replacement unit.

B. Replacement

(1) Screw all three mating connectors to the replacement unit.

NOTE: Connectors are keyed to ensure proper connections.

(2) Slide the replacement unit into place and tighten the four mounting screws.

(3) Follow the configuration and check procedure in the Configuration/Installation Checkout section of this document prior to powering up (see page 401).

9976-0041 Rev F





9976-0041 Rev F

WIRING HARNESS REQUIREMENTS AND OPTIONS



1. TC "Wiring Harness Requirements and Options" \l1General

The EFIS 5XX is highly configurable and supports many installation options that depend on the aircraft type, sensor suite, and navigation suite. To support this, the EFIS 5XX system offers more interfaces and configurations than are required for a single application.

Factors to consider while determining the best configuration for your specific application include:

• Number of EFIS, EHSI, or MFD: MFD or EHSI, Dual EHSI, Single EFIS, Dual EFIS, combinations of MFD.

• Aircraft type: Helicopter or Fixed Wing • Aircraft sensors (AHRS, DG/VG, Rad Alt) Digital (ARINC 429) or Analog Synchro • Nav sources (VOR, ADF, DF, TACAN, FMS), number of each and signal type (analog

– synchro or Digital –ARINC 429) • Weather Radar • TCAS (TCAS I or TCAS II), Display Resolution Advisory or not • EGPWS • Vertical Speed Indicator

NOTE: Review the initial installation instructions located in the Installation/Removal section of this document (page 201).

2. Wiring Harness Connectors and Signal Standards

Due to the above installation options and configurations, the wiring harness will vary for each aircraft installation. Because of this, typical wiring diagrams are provided that can be used for understanding a typical installation of the specific interface.

NOTE: Since combinations of each optional configuration are possible, information in the following paragraphs is for reference.

9976-0041 Rev F




A. Wiring Harness Connectors

The EFIS 5XX uses three Mil-C-38999 79-pin connectors. Although the signal types and names are the same for various EFIS 5XX unit configurations, the use of the signal may vary depending on the series number. Pay close attention to ensure that the EFIS 5XX series and RK part number matches the pin list (see Table 16).

B. Wiring Harness Signal Standards

Following are definitions for the EFIS 5XX standard discrete signal interfaces.

(1) Standard Open

The standard open signal is a resistance of 100,000 ohms or more with respect to signal common or a voltage level of +18.5VDC to +36VDC if a pull-up resistor is used in the circuitry.

(2) Standard Ground

The standard ground signal is generated by either a solid state or mechanical switch. For mechanical switch-type circuitry, a resistance of 10 ohms or less to signal common represents the ground condition. Semiconductor circuitry exhibits a voltage of +3.5VDC or less with respect to signal common in the ground condition.

(3) Standard Applied Voltage Output

The standard applied voltage is a nominal value of +27.5VDC. This signal is applied when the voltage level is +18.5VDC to +36VDC. The signal is not applied when the voltage level is less than +3.5VDC.

(4) Standard Discrete Input

A standard discrete input recognizes incoming signals having two possible states: open and ground. The ground state is when the circuit senses a low resistance or a voltage of less than +3.5VDC. The open state is when the circuit senses a voltage level between +18.5VDC to +36VDC, or a resistance of greater than 100,000 ohms connected to the input.

(5) Standard Discrete Output

A standard discrete output exhibits two states: open and ground. The open state is a voltage of +18.5VDC to +36VDC, or a resistance of greater than 100,000 ohms between the input pin and airframe direct current ground. The ground state is a voltage of 0 to +3.5VDC between the unit pin and airframe

9976-0041 Rev F




direct current ground. The discrete output can sink up to 20mA when in the ground state.

(6) Standard Annunciator Output

A standard annunciator output exhibits two states: open and ground. The open state is a voltage of +18.5VDC to +36VDC, or a resistance of greater than 100,000 ohms between the unit pin and the airframe direct current ground. The ground state is a voltage of 0 to +3.5VDC between the unit pin and airframe direct current ground. The annunciator output can sink up to 200mA when in the ground state.

3. Wiring Harness Options and Interfaces

Critical signals on the EFIS 5XX are configured with configuration straps in the wiring harness. See the configuration table in the wiring diagram schematics to determine configuration option for specific application.

NOTE: Block diagrams (see Figure 25 through Figure 29) and wiring diagrams (see Figure 30 through Figure 54) are provided for the installer's reference and begin on page 317.

A. Configuration Options

(1) EFIS 5XX Location Configuration

The CPUDGND 1 through 4 discrete sets the EFIS location configuration.

NOTE: Ensure CPUDGND jumper straps are only connected to CPUDGND_COM RETURNS (J1-31 or J1-47)

(2) EFIS 5XX System Configuration

NOTE: Ensure DGND jumper straps are only connected to DGND SIGNAL COM RETURNS (J1-39/41, or J3-56/58).

(a) EFIS 500 System Configuration

EFIS 500 can be configured for single or dual EFIS. If EFIS 500 is installed as dual EHSI or single EHSI, the unit MON flag will be set; this indicates a cross bus failure. The units can be used in this configuration with a pilot's manual notice, but it is not recommended (see DGND07 J3-66).

EFIS 500 is configured for helicopter symbology only.

9976-0041 Rev F




(b) EFIS 520 System Configuration

EFIS 520 can be configured for single, dual EFIS, or single and dual EHSI, or MFD only. EHSI-only is the same configuration as MFD. Refer to the DGND discrete logic in the wiring diagrams for pin connections (see DGND07 J3-66 and DGND13 J1-70).

EFIS 520 can be configured for helicopter or fixed wing symbology (see DGND04 J3-72 on EFIS 520).

NOTE: EFIS installation should be performed as per wiring diagram (i.e. Pilot’s VOR to pilot side) regardless of desired pilot sensor data reference selection 1 or 2. The Pilot Reference Designator effects display properties only.

(3) EFIS 5XX Attitude and Heading System Configuration

(a) EFIS 500 Attitude and Heading System Configuration

EFIS 500 can be configured for single or dual analog vertical gyros/directional gyros (see DGND01 J3-78, DGND02 J3-76).

(b) EFIS 520 Attitude and Heading System Configuration

EFIS 520 can be configured for single or dual analog or digital AHRS/INS inputs (see DGND01 J3-78, DGND02 J3-76, AHRS selection DGND05 J3-70).

EFIS 520 SAR (160E050 or greater) can be configured to display an expanded pitch attitude indication of +/-15° instead of the standard +/-25° (see DGND10 J3-60).

(4) EFIS 5XX Specific Wiring Configurations

(a) EFIS 500 Specific Wiring Configurations

EFIS 500 has specific discrete configurations that have been incorporated into a configuration page in the EFIS 520. These are described in Table 15.

NOTE: If only one sensor source is selected, the sensor information should be routed to both on-side and off-side inputs. For example, when choosing only one VOR source, the installer should route the VOR to both VOR 1 and VOR 2 inputs (see wiring diagrams).

9976-0041 Rev F




PIN CONFIGURATION EFFECT DGND03 J3-74 Single or dual VOR sources DGND04 J3-72 Single or ADF and DF sources DGND05 J3-70 Single or dual LNAV / FMS sources DGND06 J3-68 1/2 or no LNAV / FMS sources DGND08 J3-64 Single or dual radio altimeter sources DGND09 J3-62 1/2 or no radio altimeter sources DGND10 J3-60 Flight director or no flight director DGND11 J1-5 Weather radar or no weather radar

Table 15—EFIS 500 Specific Wiring Configurations

(b) EFIS 520 Specific Wiring Configurations

EFIS 520 has specific discrete configurations that are not available in the EFIS 500 units. Please refer to the wiring diagrams and configuration tables.

B. External Switches or Control Panel

(1) EFIS 5XX Cockpit Switching Wiring Configurations

The following items are switched inputs to the EFIS 5XX:

• +28 VDC08 J1-68 EFIS in Command: informs EFIS which side is coupled to the autopilot.

• DGND22 J1-44 Attitude source (ATT1 or ATT2) select. There is one switch to both on-side EFIS units.

• DGND23 J1-21 Heading source (HDG1 or HDG2) select. There is one switch to both on-side EFIS units.

NOTE: Ensure that +28VDC discrete jumper straps are only connected to +28VDC-COM returns (J1-52/73, or J3-45/48).

(2) EFIS 500 Cockpit Switching Wiring Configurations

There is no cockpit switching wiring configuration unique to the EFIS 500 units.

(3) EFIS 520 Cockpit Switching Wiring Configurations

The following items are switched inputs to the EFIS 520:

• DGND08 J3-64 Traffic Selection. There is one switch for each EHSI, and the discrete selects TCAS traffic display or declutter.

9976-0041 Rev F




• DGND09 J3-62 ABV/BLW/ABS Selection. There is one switch to each EHSI and the discrete selects Above, Below, ALL, or absolute altitude mode for TCAS traffic display formats.

• +28VDC14 J3-24 Terrain Selection (EHSI Function ONLY). There is one switch for each EHSI and the discrete selects EGPWS terrain display or terrain declutter. This input discrete must also switch the 453 data from WX data to EGPWS data and the control data output to EGPWS for range selection.

• DGND03 J3-74 Airdata source (ADC1 or ADC2) select. There is one switch to both on-sides EFIS units.

• EFIS 520 SAR also includes a Doppler Mode Enable Switch to enable Doppler radar velocity cues and readouts in Rose Map Mode. DGND17 (J1-37)

• EFIS 520 SAF includes a True/Magnetic heading select switch to allow either display reference when the IRS heading is selected (DFND14 j1-35). There is one switch to both on-side EFIS units.

The following items are used for switching exterior relays for data flow:

• DGNDOUT1 J1-65 TA/RA Display Failure discrete. EFIS 520 sets this discrete to indicate it is unable to display resolution advisories.

• DGNDOUT6 J3-11 Display in Composite Mode. EFIS 520 sets this discrete to indicate it is in composite mode. The discrete is used in a single EFIS installation to switch radio altimeter data into the EHSI on ARINC A429I6 J1-4/32.

• DGNDOUT5 J3-9 DME Transfer. This sends a ground signal with pilot off-side VOR selection to switch in off-side DME information in the ARINC 568 inputs.

9976-0041 Rev F




EFIS 5XX EFIS 520 ONLY

PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J1-16 DCPWR_LO

+28 VDC Power Input

Lo

+28 VDC Power Input

Lo

+28 VDC Power Input

Lo

+28 VDC Power Input

Lo Power Unit Power See note R

J2- 16 DCPWR_LO

+28 VDC Power Input

Lo

+28 VDC Power Input

Lo

+28 VDC Power Input

Lo

+28 VDC Power Input

Lo Power Unit Power See note R

J1- 13 DCPWR1_HI

+28 VDC Power Input

Hi

+28 VDC Power Input

Hi

+28 VDC Power Input

Hi

+28 VDC Power Input

Hi Power Unit Power See note R

J2- 13 DCPWR2_HI

+28 VDC Power Input

Hi

+28 VDC Power Input

Hi

+28 VDC Power Input

Hi

+28 VDC Power Input

Hi Power Unit Power See note R

J1- 6 HTRPWR

+28 VDC POWER IN

Hi

+28 VDC POWER IN

Hi

+28 VDC POWER IN

Hi

+28 VDC POWER IN

Hi Power LCD Heater

J1- 33 HTRRTN

+28 VDC POWER IN

LO

+28 VDC POWER IN

LO

+28 VDC POWER IN

LO

+28 VDC POWER IN

LO Power LCD Heater J1- 15 CHASSISGND

Chassis Ground

Chassis Ground

Chassis Ground

Chassis Ground Power GND

J2- 15 CHASSISGND

Chassis Ground

Chassis Ground

Chassis Ground


J3- 15 CHASSISGND

Chassis Ground

Chassis Ground

Chassis Ground


J1- 43 ACLITING

+ 5 VAC Lighting Hi

+ 5 VAC Lighting Hi

+ 5 VAC Lighting Hi

+ 5 VAC Lighting Hi Power

Bezel Lighting

J1- 18 ACLITINGRTN

+5 VAC Lighting

Com

+5 VAC Lighting

Com

+5 VAC Lighting

Com

+5 VAC Lighting

Com Power Bezel

Lighting

J1- 23 CPUDGND1

Strap to Pilot ADI

J1-31 or 47 N/C

Strap to Copilot ADI J1-31 or 47 N/C ADI/HSI Config See note S

J1- 25 CPUDGND2 N/C

Strap to Pilot HSI

J1-31 or 47 N/C

Strap to Copilot HSI J1-31 or 47 ADI/HSI Config See note S

J1- 49 CPUDGND3

Strap to Pilot ADI

J1-31 or 47

Strap to Pilot HSI

J1-31 or 47 N/C N/C ADI/HSI Config See note S

J1- 27 CPUDGND4 N/C N/C

Strap to Copilot ADI J1-31 or 47

Strap to Copilot HSI J1-31or 47 ADI/HSI Config See note S

J1- 29 CPUDGND5 Reserved Reserved Reserved Reserved J1- 1 CPUDGND6

GSE Enable

GSE Enable

GSE Enable

GSE Enable

Data Load See note T

J1- 3 CPUDGND7 Reserved Reserved Reserved Reserved J3- 25 CPUDLCTRL

reprogram enable

reprogram enable

reprogram enable

reprogram enable Data Load See note T

J1- 31 CPUDGND_COM

CPU STRAP COM

CPU STRAP COM

CPU STRAP COM

CPU STRAP COM ADI/HSI Cofig Com See note S

J1- 47 CPUDGND_COM

CPU STRAP COM

CPU STRAP COM

CPU STRAP COM

CPU STRAP COM ADI/HSI Cofig Com See note S

J3- 26 CPU_SPARE Reserved Reserved Reserved Reserved

J1- 69 MNETPC

J1-69 MNETPC ALL EFIS



J1-69 MNETPC ALL EFIS ADI/HSI EFIS Bus See note AD

J1- 77 MNETPH

J1-77 MNETPH ALL EFIS



J1-77 MNETPH ALL EFIS ADI/HSI EFIS Bus See note AD

J1- 7 MNETSC

J1-7 MNETSC ALL EFIS



J1-7 MNETSC ALL EFIS ADI/HSI EFIS Bus See note AD

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J1- 9 MNETSH

J1-9 MNETSH ALL EFIS



J1-9 MNETSH ALL EFIS ADI/HSI EFIS Bus See note AD

J1- 51 28VIN01

+28 V = ATT1 Valid

+28 V = ATT2 Valid

+28 V = ATT2 Valid

+28 V = ATT1 Valid Gyro Att Gyro See note K

J1- 53 28VIN02 HDG SYNC HDG SYNC HDG SYNC HDG SYNC Switch

HDG SYNC /

+28V = Rate Gyro

Valid

HDG SYNC /

+28V = Doppler

Valid

HDG SYNC /

+28V = Rate Gyro

Valid

HDG SYNC /

+28V = Doppler

Valid Gyro /

doppler See note AI

J1- 55 28VIN03

+28 V = VOR/LOC 2

Valid

+28 V = VOR/LOC 1

Valid

+28 V = VOR/LOC 1

Valid

+28 V = VOR/LOC 2

Valid VOR

+28 V = VOR/LOC

2/TCN Valid

+28 V = VOR/LOC

1/TCN Valid

+28 V = VOR/LOC

1/TCN Valid

+28 V = VOR/LOC

2/TCN Valid VOR/TCN See note K

J1- 57 28VIN04

+28 V = Glideslope

2 Valid

+28 V = Glideslope1

Valid

+28 V = Glideslope

1 Valid

+28 V = Glideslope

2 Valid VOR ILS See note K J1- 72 28VIN05

+28 V = DME Valid

+28 V = DME Valid

+28 V = DME Valid

+28 V = DME Valid DME DME See note K

J1- 74 28VIN06

+28 V = Rad Alt 1

Valid

+28 V = Rad Alt 2

Valid

+28 V = Rad Alt 2

Valid

+28 V = Rad Alt 1

Valid Rad Alt RADALT See note K J1- 76 28VIN07

+28 V = ADF 2 Valid

+28 V = ADF 1 Valid

+28 V = ADF 1 Valid

+28 V = ADF 2 Valid ADF ADF See note K

J1- 68 28VIN08

+28 V = EFIS in

Command

+28 V = EFIS in

Command

+28 V = EFIS in

Command

+28 V = EFIS in

Command Switch Cockpit Switch See note C

J3- 20 28VIN09

+28 V = AP Coupled

+28 V = AP Coupled

+28 V = AP Coupled

+28 V = AP Coupled FCS

J3- 44 28VIN10

+28 V = RA 1, Open =

RA 2

+28 V = RA 1, Open =

RA 2

+28 V = RA 1, Open =

RA 2

+28 V = RA 1, Open =

RA 2 Rad Alt RA Select

Switch See note D

J3- 21 28VIN11

+28 V = Pilot HSI

Valid, Open=Fail

+28 V = Pilot ADI

Valid, Open=Fail

+28 V = Copilot HSI

Valid, Open=Fail

+28 V = Copilot ADI

Valid, Open=Fail ADI/HSI EFIS Valid See note I

J3- 22 28VIN12

FD Decouple

FD Decouple

FD Decouple

FD Decouple FCS FCS See note E

J3- 23 28VIN13 DH ALERT DH ALERT DH ALERT DH ALERT Rad Alt DH/RADALT See note F

J3- 24 28VIN14 MB

Fast/Slow Valid = 28V

Terrain Select =

28V Fast/Slow

Valid = 28V

Terrain Select =

28V FS/EGPWS See note G

J3- 46 28VIN15 MB

Windshear Caution =

28V

Windshear Caution =

28V

Windshear Caution =

28V

Windshear Caution =

28V WX

J3- 47 28VIN16

Windshear Warning =

28V

Windshear Warning =

28V

Windshear Warning =

28V

Windshear Warning =

28V WX J1- 52 28VIN_COM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM

Signal Com Signal Com See note A

J1- 73 28VIN_COM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM


J3- 45 28VIN_COM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM


J3- 48 28VIN_COM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM

+28 VIN COMM


J1- 79 28VOUT1 ADI Valid HSI Valid ADI Valid HSI Valid ADI/HSI EFIS Valid See note I J1- 54 28VOUT2 Reserved Reserved Reserved Reserved

VOR/TCN 1 Primary

VOR/TCN 1 Primary

VOR/TCN 1 Primary

VOR/TCN 1 Primary FCS See note J

J3- 33 28VOUT3 NAV VALID NAV VALID NAV VALID NAV VALID FCS FCS J3- 35 28VOUT4 GS VALID GS VALID GS VALID GS VALID FCS FCS J3- 37 28VOUT5

HDG ERR Valid

HDG ERR Valid

HDG ERR Valid

HDG ERR Valid FCS FCS

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J3- 39 28VOUT6 Reserved Reserved Reserved Reserved

VOR/TCN 2 Primary

Nav

VOR/TCN 2 Primary

Nav

VOR/TCN 2 Primary

Nav

VOR/TCN 2 Primary

Nav FCS See note J


LNV 1 Primary

Nav

LNV 1 Primary

Nav

LNV 1 Primary

Nav

LNV 1 Primary

Nav FCS See note J


LNV 2 Primary

Nav

LNV 2 Primary

Nav

LNV 2 Primary

Nav

LNV 2 Primary

Nav FCS See note J J1- 75 28VOUT_COM

+28 V Out Signal Com



+28 V Out Signal Com Common See note H

J3- 14 28VOUT_COM




+28 V Out Signal Com See note H

J3- 19 28VOUT_COM





J3- 55 28VOUT_COM





J3- 78 DGND01

GND = Dual ATT OPEN =

Single ATT


Single ATT


Single ATT


Single ATT Strap Config single

or dual

J3- 76 DGND02

GND = Dual HDG OPEN =

Single HDG


Single HDG


Single HDG


Single HDG Strap Config single

or dual

J3- 74 DGND03

GND = Dual VOR OPEN =

Single VOR


Single VOR


Single VOR


Single VOR Strap

OPEN = onside ADCGND = offside ADC

OPEN = onside ADCGND = offside ADC

OPEN = onside ADC GND = offside ADC

OPEN = onside ADC GND = offside ADC

ADC Select Switch

J3- 72 DGND04

GND = ADF & DF OPEN =

ADF


ADF


ADF


ADF Strap

GND = Rotary, Open = Fixed Wing



GND = Rotary, Open = Fixed Wing Config

J3- 70 DGND05

GND = LNAV1

&LNAV2 OPEN=LN

V

GND = LNAV1

&LNAV2 OPEN=LN

V

GND = LNAV1

&LNAV2 OPEN=LN

V

GND = LNAV1

&LNAV2 OPEN=LN

V Strap

Gnd=A429, AHRS, Opn =

Synchro


Synchro


Synchro


Synchro Analog / Digital

J3- 68 DGND06

GND = LNAV

OPEN=NO LNV

GND = LNAV

OPEN=NO LNV

GND = LNAV

OPEN=NO LNV

GND = LNAV

OPEN=NO LNV Strap

GND = Weight on

Wheels

GND = Weight on

Wheels

GND = Weight on

Wheels

GND = Weight on

Wheels WOW

J3- 66 DGND07

GND = DUAL EFIS

OPEN= SINGLE

GND = DUAL EFIS

OPEN= SINGLE

GND = DUAL EFIS

OPEN= SINGLE

GND = DUAL EFIS

OPEN= SINGLE Strap

GND= DUAL EFIS

OPN= SINGLE

GND= DUAL EFIS

OPN= SINGLE

GND= DUAL EFIS

OPN= SINGLE

GND= DUAL EFIS

OPN= SINGLE

Single or dual

configuration

J3- 64 DGND08

GND = RA1 & RA2

OPEN=RA

GND = RA1 & RA2

OPEN=RA

GND = RA1 & RA2

OPEN=RA

GND = RA1 & RA2

OPEN=RA Strap VNAV ARM

GND = Traffic Select VNAV ARM

GND = Traffic Select FCS/TCAS See note W

J3- 62 DGND09

GND = RA OPEN=NO

RA

GND = RA OPEN=NO

RA

GND = RA OPEN=NO

RA

GND = RA OPEN=NO

RA Strap VNAV CAP

GND = ABV/BLW/ABS toggle VNAV CAP

GND = ABV/BLW/ABS toggle FCS/TCAS See note W

J3- 60 DGND10

GND = FD Avail

OPEN = NO FD

GND = FD Avail

OPEN = NO FD

GND = FD Avail

OPEN = NO FD

GND = FD Avail

OPEN = NO FD Strap

GND = expanded

pitch

GND = expanded

pitch

GND = expanded

pitch

GND = expanded

pitch ADI pitch

scale See note B

J1- 5 DGND11

GND = WX OPEN=NO

WX

GND = WX OPEN=NO

WX

GND = WX OPEN=NO

WX

GND = WX OPEN=NO

WX Wx ALT ARM

GND = Terrain Pop-Up ALT ARM

GND = Terrain Pop-Up

FCS/ EGPWS See note W

J1- 78 DGND12 TTL 2 TTL 1 TTL 1 TTL 2 VOR ILS/VOR

J1- 70 DGND13 Reserved Reserved Reserved Reserved Strap

GND=EFIS,OPEN = EHSI only

GND=EFIS, OPEN = EHSI only

EHSI only configuration

J1- 35 DGND14 ALT ALT ALT ALT FCS

True/Mag select (SAF

only)


only)


only)


only) FCS

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J1- 8 DGND15 HDG HDG HDG HDG FCS FCS J1- 10 DGND16 VS VS VS VS FCS FCS

J1- 37 DGND17 Reserved Reserved Reserved Reserved TURB

GND = Doppler mode enable TURB

GND = Doppler mode enable

FCS /

DOPPLER See note X J1- 12 DGND18 GA GA GA GA FCS FCS

J1- 14 DGND19

GND = Slave, Open =Free



GND = Slave, Open =Free Heading HDG Gyro

J1- 17 DGND20

GND = HDG Valid

GND = HDG Valid

GND = HDG Valid

GND = HDG Valid Gyro

GND = HDG / HDG

2 Valid

GND = HDG / HDG

1 Valid

GND = HDG / HDG

1 Valid

GND = HDG / HDG

2 Valid HDG Gyro See note K J1- 19 DGND21

Open = DME Hold

Open = DME Hold

Open = DME Hold

Open = DME Hold DME DME

J1- 44 DGND22

OPEN=ATT / ATT 1,

GND=ATT2

OPEN=ATT / ATT 1,

GND=ATT2

OPEN = ATT 2,

GND = ATT 1

OPEN=ATT 2,

GND=ATT 1 Switch Att Select See note D

J1- 21 DGND23

OPN=HDGor HDG1,

GND=HDG2

OPN=HDGor HDG1,

GND=HDG2

OPN = HDG2, GND = HDG1

OPN = HDG2, GND = HDG1 Switch Hdg Select See note D

J1- 64 DGND24 IAS IAS IAS IAS FCS FCS J1- 63 DGND25 ILS ARM ILS ARM ILS ARM ILS ARM FCS FCS J1- 62 DGND26 GS CAP GS CAP GS CAP GS CAP FCS FCS J1- 61 DGND27 NAV ARM NAV ARM NAV ARM NAV ARM FCS FCS J1- 59 DGND28 NAV CAP NAV CAP NAV CAP NAV CAP FCS FCS J1- 71 DGND29 BC ARM BC ARM BC ARM BC ARM FCS FCS J1- 56 DGND30 BC CAP BC CAP BC CAP BC CAP FCS FCS J3- 18 DGND31 VAPP ARM VAPP ARM VAPP ARM VAPP ARM FCS FCS J3- 27 DGND32 VAPP CAP VAPP CAP VAPP CAP VAPP CAP FCS FCS J1- 39 DGND_COM

DGND Signal Com

DGND Signal Com

DGND Signal Com

DGND Signal Com

Signal GND Sig Com See note A

J1- 41 DGND_COM

DGND Signal Com

DGND Signal Com

DGND Signal Com

DGND Signal Com


J3- 56 DGND_COM

DGND Signal Com

DGND Signal Com

DGND Signal Com

DGND Signal Com


J3- 58 DGND_COM

DGND Signal Com

DGND Signal Com

DGND Signal Com

DGND Signal Com


J1- 65 DGNDOUT1 N/C Reserved N/C Reserved

TA/RA Display Status =

OK

TA/RA Display Status =

OK TCAS J1- 67 DGNDOUT2

RAD ALT 1 Test

RAD ALT 2 Test

RAD ALT 2 Test

RAD ALT 1 Test Rad Alt Rad Alt

J3- 5 DGNDOUT3 TTL TO FD TTL TO FD TTL TO FD TTL TO FD FCS To FCS See note Y J3- 7 DGNDOUT4 DH ALERT DH ALERT DH ALERT DH ALERT Rad Alt

To Panel light See note Z

J3- 9 DGNDOUT5

DME XFR =GND

DME XFR =GND

DME XFR =GND

DME XFR =GND

DME Rev DME Switch See note AA

J3- 11 DGNDOUT6 Reserved Reserved Reserved Reserved

Display in Comp Mode



Display in Comp Mode ADI/HSI See note AB

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J3- 13 DGNDOUT7 Reserved Reserved Reserved Reserved J3- 16 DGNDOUT8 Nav Pulse Nav Pulse Nav Pulse Nav Pulse FDC FCS See note AC

J1- 46 A429I1-

Reserved for

AHRS B HS

Reserved for

AHRS B HS

Reserved for

AHRS B HS

Reserved for

AHRS B HS

AHRS/IRS/INS 1B HS

A429

AHRS/IRS/INS 1B HS

A429

AHRS/IRS/ INS 2B HS

A429

AHRS/IRS/ INS 2B HS

A429 AHRS See note K &

P

J1- 22 A429I1+

Reserved for

AHRS A HS

Reserved for

AHRS A HS

Reserved for

AHRS A HS

Reserved for

AHRS A HS

AHRS/IRS/INS 1A HS

A429

AHRS/IRS/INS 1A HS

A429

AHRS/IRS/ INS 2A HS

A429

AHRS/IRS/ INS 2A HS

A429 AHRS See note K &

P J1- 48 A429I2-

TCAS B HS A429

TCAS B HS A429 TCAS

J1- 24 A429I2+

TCAS A HS A429

TCAS A HS A429 TCAS

J1- 66 A429I3-

LNAV 1 ARINC 429

in B LS

LNAV 1 ARINC 429

in B LS

LNAV 1 ARINC 429

in B LS

LNAV 1 ARINC 429 input B LS LNAV

FMS 1 B LS A429

FMS 1 B LS A429

FMS 2 B LS A429

FMS 1 B LS A429 FMS See note K

J1- 26 A429I3+

LNAV 1 ARINC 429 input A LS



LNAV 1 ARINC 429 input A LS LNAV

FMS 1 A LS A429

FMS 1 A LS A429

FMS 2 A LS A429

FMS 1 A LS A429 FMS See note K

J1- 50 A429I4-

LNAV 2 ARINC 429 input B LS



LNAV 2 ARINC 429 input B LS LNAV

RAD ALT 1 B LS A429

FMS 2 B LS

A429/RA RAD ALT 2 B LS A429

FMS 2 B LS

A429/RA FMS / RA See note N

J1- 28 A429I4+




LNAV 2 ARINC 429 input A LS LNAV

RAD ALT 1 A LS A429

FMS 2 A LS

A429/RA RAD ALT 2 A LS A429

FMS 2 A LS

A429/RA FMS / RA See note N J1- 30 A429I5-

ADF 2 B LS A429

ADF 1 B LS A429

ADF 1 B LS A429

ADF 2 B LS A429 ADF/RCP

See note K & L

J1- 2 A429I5+

ADF 2 A LS A429

ADF 1 A LS A429

ADF 1 A LS A429

ADF 2 A LS A429 ADF/RCP

See note K & L

J1- 32 A429I6-

Wx 429 B LS

Wx 429 B LS Wx

DFCC B LS A429

Wx B LS A429

DFCC B LS A429

Wx B LS A429 DFCC/ Wx See note M

J1- 4 A429I6+

Wx 429 A LS

Wx 429 A LS Wx

DFCC A LS A429

Wx A LS A429 (RCP)

DFCC A LS A429

Wx A LS A429 (RCP) DFCC/ Wx See note M

J3- 42 A429I7-

VOR 2 B LS A429

VOR 1 B LS A429

VOR 1 B LS A429

VOR 2 B LS A429 VOR See note K

J3- 17 A429I7+

VOR 2 A LS A429

VOR 1 A LS A429

VOR 1 A LS A429

VOR 2 A LS A429 VOR See note K

J3- 63 A429I8-

ADC or ADC 1 B LS A429



ADC or ADC 2 B LS A429 ADC See note O

J3- 61 A429I8+

ADC or ADC 1 A LS A429



ADC or ADC 2 A LS A429 ADC See note O

J1- 36 A429O1-

Wx 429 B LS out

Wx 429 B LS out Wx

Wx / EGPWS B LS A429 (Range)

Wx / EGPWS B LS A429 (Range) Wx/EGPWS See note M

J1- 34 A429O1+

Wx 429 A LS out

Wx 429 A LS out Wx

Wx / EGPWS A LS A429 (Range)

Wx / EGPWS A LS A429 (Range) Wx/EGPWS See note M

J3- 12 A429O2-

LNAV 1 ARINC 429

B

LNAV 1 ARINC 429

B

LNAV 1 ARINC 429

B

LNAV 1 ARINC 429

B LNAV FMS 1 B LS A429

FMS 1 B LS A429

FMS 2 B LS A429

FMS 1 B LS A429 FMS

See note K & Q

J3- 10 A429O2+

LNAV 1 ARINC 429

A

LNAV 1 ARINC 429

A

LNAV 1 ARINC 429

A

LNAV 1 ARINC 429

A LNAV FMS 1 A LS A429

FMS 1 A LS A429

FMS 2 A LS A429

FMS 1 A LS A429 FMS

See note K & Q

J3- 38 A429O3-

LNAV 2 ARINC 429

B

LNAV 2 ARINC 429

B

LNAV 2 ARINC 429

B

LNAV 2 ARINC 429

B LNAV FMS 2 B LS A429

FMS 2 B LS A429 FMS

See note K & Q

J3- 36 A429O3+

LNAV 2 ARINC 429

A

LNAV 2 ARINC 429

A

LNAV 2 ARINC 429

A

LNAV 2 ARINC 429

A LNAV FMS 2 A LS A429

FMS 2 A LS A429 FMS

See note K & Q

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J3- 59 A429O4-

DFCC B LS A429

DFCC B LS A429

DFCC B LS A429

DFCC B LS A429 DFCC

J3- 57 A429O4+

DFCC A LS A429

DFCC A LS A429

DFCC A LS A429

DFCC A LS A429 DFCC

J1- 38 DME568_CLK-

DME568 CLK-

DME568 CLK-

DME568 CLK-

DME568 CLK- DME DME

J1- 11 DME568_CLK+

DME568 CLK+

DME568 CLK+

DME568 CLK+

DME568 CLK+ DME DME

J1- 40 DME568_DAT-

DME568 BCD-

DME568 BCD-

DME568 BCD-

DME568 BCD- DME DME See note AA

J1- 58 DME568_DAT+

DME568 BCD+

DME568 BCD+

DME568 BCD+

DME568 BCD+ DME DME See note AA

J1- 42 DME568_SYN-

DME568 SYNC-

DME568 SYNC-

DME568 SYNC-

DME568 SYNC- DME DME

J1- 60 DME568_SYN+

DME568 SYNC+

DME568 SYNC+

DME568 SYNC+

DME568 SYNC+ DME DME

J2- 18 S1A PITCH 1 X PITCH 2 X PITCH 2 X PITCH 1 X Gyro Gyro (Pitch)

See note K & P

J2- 19 S1BD PITCH 1 Z PITCH 2 Z PITCH 2 Z PITCH 1 Z Gyro Gyro (Pitch)

See note K & P

J2- 20 S1C PITCH 1 Y PITCH 2 Y PITCH 2 Y PITCH 1 Y Gyro Gyro (Pitch)

See note K & P

J2- 63 DEMOD1-

Pitch 1 Ref - (+26 VAC

Com)


Com)


Com)


Com) Gyro Gyro (Pitch)See note K &

V

J2- 62 DEMOD1+

Pitch 1 Ref + (+26 VAC

Hi)


Hi)


Hi)


Hi) Gyro Gyro (Pitch)See note K &

V J2- 21 S2A ROLL 1 X ROLL 2 X ROLL 2 X ROLL 1 X Gyro Gyro (Roll)

See note K & P

J2- 22 S2BD ROLL 1 Z ROLL 2 Z ROLL 2 Z ROLL 1 Z Gyro Gyro (Roll)

See note K & P

J2- 23 S2C ROLL 1 Y ROLL 2 Y ROLL 2 Y ROLL 1 Y Gyro Gyro (Roll)

See note K & P

J2- 65 DEMOD2-

Roll 1 Ref - (+26 VAC

Com)


Com)


Com)


Com) Gyro Gyro (Roll) See note K &

V

J2- 64 DEMOD2+

Roll 1 Ref + (+26 VAC

Hi)


Hi)


Hi)


Hi) Gyro Gyro (Roll) See note K &

V J2- 24 S3A HDG 2 X HDG 1 X HDG 1 X HDG 2 X Gyro Gyro (HDG)

See note K & P

J2- 25 S3BD HDG 2 Z HDG 1 Z HDG 1 Z HDG 2 Z Gyro Gyro (HDG)

See note K & P

J2- 26 S3C HDG 2 Y HDG 1 Y HDG 1 Y HDG 2 Y Gyro Gyro (HDG)

See note K & P

J2- 51 DEMOD3-

HDG 2 Ref - (+26 VAC

Com)


Com)


Com)


Com) Gyro Gyro (HDG)See note K &

V

J2- 66 DEMOD3+

HDG 2 Ref + (+26 VAC

Hi)


Hi)


Hi)


Hi) Gyro Gyro (HDG)See note K &

V J2- 49 S4A VOR 2 SIN VOR 1 SIN VOR 1 SIN VOR 2 SIN VOR

VOR 2 / TCN SIN

VOR 2 / TCN SIN

VOR 2 / TCN SIN

VOR 2 / TCN SIN VOR / TCN See note K

J2- 48 S4BD VOR 2 RTN VOR 1 RTN VOR 1 RTN VOR 2 RTN VOR

VOR 2 / TCN RTN

VOR 2 / TCN RTN

VOR 2 / TCN RTN

VOR 2 / TCN RTN VOR / TCN See note K

J2- 47 S4C

VOR 2 COS

VOR 1 COS

VOR 1 COS

VOR 2 COS VOR

VOR 2 / TCN COS

VOR 2 / TCN COS

VOR 2 / TCN COS

VOR 2 / TCN COS VOR / TCN See note K

J2- 76 DEMOD4-

VOR 2 Ref - (+26 VAC

Com)


Com)


Com)


Com) VOR

VOR2/TCN Ref

(26VAC Com)

VOR1/TCN Ref

(26VAC Com)

VOR1/TCN Ref

(26VAC Com)

VOR2/TCN Ref

(26VAC Com) VOR/TCN

See note K & V

J2- 67 DEMOD4+

VOR 2 Ref + (+26 VAC

Hi)


Hi)


Hi)


Hi) VOR

VOR2/TCN Ref +

(+26 VAC Hi)

VOR1/TCN Ref +

(+26 VAC Hi)

VOR1/TCN Ref +

(+26 VAC Hi)

VOR2/TCN Ref +

(+26 VAC Hi) VOR/TCN

See note K & V

J2- 46 S5A

ADF 2 /DF X ADF 1 X ADF 1 X

ADF 2 /DFX ADF ADF See note K

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J2- 45 S5BD

ADF 2 /DF Z ADF 1 Z ADF 1 Z

ADF 2 /DF Z ADF ADF See note K

J2- 44 S5C

ADF 2 /DF Y ADF 1 Y ADF 1 Y

ADF 2 /DF Y ADF ADF See note K

J2- 74 DEMOD5-

ADF 2 Ref - (+26 VAC

Com)


Com)


Com)

ADF 2 Ref -(+26 VAC

Com) ADF ADF See note K &

V

J2- 75 DEMOD5+

ADF 2 Ref + (+26 VAC Hi)



ADF 2 Ref + (+26 VAC Hi) ADF ADF

See note K & V

J2- 60 S6A N/C N/C N/C N/C J2- 43 S6BD N/C N/C N/C N/C J2- 61 S6C N/C N/C N/C N/C J2- 79 DEMOD6- Reserved Reserved Reserved Reserved J2- 77 DEMOD6+ Reserved Reserved Reserved Reserved J2- 17 RESOUT1_H Reserved Reserved Reserved Reserved J2- 28 RESOUT1_JP Reserved Reserved Reserved Reserved J2- 53 RESOUT1_JS N/C N/C N/C N/C J2- 50 RESOUT1_L Reserved Reserved Reserved Reserved J2- 42 RESOUT2_H Reserved Reserved Reserved Reserved J2- 29 RESOUT2_JP Reserved Reserved Reserved Reserved J2- 78 RESOUT2_JS Reserved Reserved Reserved Reserved J2- 30 RESOUT2_L Reserved Reserved Reserved Reserved J2- 41 RESOUT3_H

HDG ERROR Hi

HDG ERROR Hi

HDG ERROR Hi

HDG ERROR Hi FCS FCS See note AE

J2- 2 RESOUT3_JP

JUMP TO J2-73

JUMP TO J2-73

JUMP TO J2-73

JUMP TO J2-73 Jumper Jumper

J2- 73 RESOUT3_JS

JUMP TO J2-2

JUMP TO J2-2

JUMP TO J2-2


J2- 32 RESOUT3_L

HDG ERROR Lo

HDG ERROR Lo

HDG ERROR Lo

HDG ERROR Lo FCS FCS See note AE

J2- 59 RESOUT4_H

CRS DATUM Hi

CRS DATUM Hi

CRS DATUM Hi

CRS DATUM Hi FCS FCS See note AE

J2- 31 RESOUT4_JP

JUMP TO J2-68

JUMP TO J2-68

JUMP TO J2-68


J2- 68 RESOUT4_JS

JUMP TO J2-31

JUMP TO J2-31

JUMP TO J2-31


J2- 54 RESOUT4_L

CRS DATUM Lo

CRS DATUM Lo

CRS DATUM Lo

CRS DATUM Lo FCS FCS See note AE

J3- 6 30HZ_INPUT_H Reserved Reserved Reserved Reserved J3- 34 30HZ_RTN_C Reserved Reserved Reserved Reserved J3- 8 30HZ_STRAP1 Reserved Reserved Reserved Reserved

J2- 27 DC_OUT 1 +

Lateral Deviation 1

Hi

Lateral Deviation 1

Hi

Lateral Deviation 2

Hi

Lateral Deviation 2

Hi FCS FCS See note K &

AH

J2- 1 DC_OUT 2 +

Vertical Deviation 1

Hi


Hi


Hi


Hi FCS FCS See note K &

AH J2- 3 DC_OUT 3 + Reserved Reserved Reserved Reserved

9976-0041 Rev F





PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J2- 52 DC_OUT 4 + Reserved Reserved Reserved Reserved J3- 69 DC34_STRAP3 Reserved Reserved Reserved Reserved J2- 34 VDCC1-

FD Pitch Command -

FD Pitch Command -

FD Pitch Command -

FD Pitch Command - FCS

J2- 33 VDCC1+

FD Pitch Command

+

FD Pitch Command

+

FD Pitch Command

+

FD Pitch Command

+ FCS J2- 36 VDCC2-

FD Roll Command -

FD Roll Command -

FD Roll Command -

FD Roll Command - FCS

J2- 35 VDCC2+

FD Roll Command

+

FD Roll Command

+

FD Roll Command

+

FD Roll Command

+ FCS J2- 38 VDCC3-

VOR/LOC DEV 2-

VOR/LOC DEV 1-

VOR/LOC DEV 1-

VOR/LOC DEV 2- VOR VOR/ILS See note K

J2- 37 VDCC3+

VOR/LOC DEV 2+

VOR/LOC DEV 1+

VOR/LOC DEV 1+

VOR/LOC DEV 2+ VOR VOR/ILS See note K

J2- 12 VDCC4- GS DEV 2 - GS DEV 1 - GS DEV 1 - GS DEV 2 - VOR VOR/ILS See note K J2- 39 VDCC4+

GS DEV 2 +

GS DEV 1 +

GS DEV 1 +

GS DEV 2 + VOR VOR/ILS See note K

J2- 5 VDCV1-

RAD ALT 1 Signal -

RAD ALT 2 Signal -

RAD ALT 2 Signal -

RAD ALT 1 Signal - Rad Alt Rad Alt See note K

J2- 4 VDCV1+

RAD ALT 1 Signal +

RAD ALT 2 Signal +

RAD ALT 2 Signal +

RAD ALT 1 Signal + Rad Alt Rad Alt See note K

J2- 7 VDCV2-

Turn Rate Signal -

DOPPLER X-

VELOCITYTurn Rate Signal -

DOPPLER X-

VELOCITY

Gyro /

DOPPLER See note AG

J2- 6 VDCV2+

Turn Rate Signal +

DOPPLER X+

VELOCITYTurn Rate Signal +

DOPPLER X+

VELOCITY

Gyro /

DOPPLER See note AG

J2- 9 VDCV3-

Fast / Slow Signal -

DOPPLER Y-

VELOCITYFast / Slow

Signal -

DOPPLER Y-

VELOCITY

FS /

DOPPLER See note AG

J2- 8 VDCV3+

Fast / Slow Signal +

DOPPLER Y+

VELOCITYFast / Slow

Signal +

DOPPLER Y+

VELOCITY

FS /

DOPPLER See note AG

J2- 11 VDCV4-

>1.4 V = FD Valid, <1.4 V =

FD Invalid

>1.4 V = FD Valid, <1.4 V =

FD Invalid

>1.4 V = FD Valid, <1.4 V =

FD Invalid

>1.4 V = FD Valid, <1.4 V =

FD Invalid FDC FDC

J2- 10 VDCV4+

>1.4 V = FD Valid, <1.4 V =

FD Invalid

>1.4 V = FD Valid, <1.4 V =

FD Invalid

>1.4 V = FD Valid, <1.4 V =

FD Invalid

>1.4 V = FD Valid, <1.4 V =

FD Invalid FDC FDC

J2- 57 VDC5-

+5 VDC INPUT (IM)

-

+5 VDC INPUT (IM)

-

+5 VDC INPUT (IM)

-

+5 VDC INPUT (IM)

- MB MB

J2- 58 VDC5+

+5 VDC INPUT (IM)

+

+5 VDC INPUT (IM)

+

+5 VDC INPUT (IM)

+

+5 VDC INPUT (IM)

+ MB MB

J2- 56 VDC6-

+5 VDC INPUT (MM) -

+5 VDC INPUT (MM) -

+5 VDC INPUT (MM) -

+5 VDC INPUT (MM) - MB MB

J2- 55 VDC6+

+5 VDC INPUT (MM) +

+5 VDC INPUT (MM) +

+5 VDC INPUT (MM) +

+5 VDC INPUT (MM) + MB MB

J2- 70 VDC7-

+5 VDC INPUT (OM) -

+5 VDC INPUT (OM) -

+5 VDC INPUT (OM) -

+5 VDC INPUT (OM) - MB MB

J2- 69 VDC7+

+5 VDC INPUT (OM) +

+5 VDC INPUT (OM) +

+5 VDC INPUT (OM) +

+5 VDC INPUT (OM) + MB MB

J2- 72 VDC8-

FD COLLECTIVE -

FD COLLECTIVE -

FD COLLECTIVE -

FD COLLECTIVE - FDC FDC

J2- 71 VDC8+

FD COLLECTIVE +

FD COLLECTIVE +

FD COLLECTIVE +

FD COLLECTIVE + FDC FDC

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PIN SIGNAL NAME

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOTHSI

EFIS 500 USE

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI

EFIS 520USE

Note Ref.

J2- 40 SIGNALGND Signal Gnd Signal Gnd Signal Gnd Signal Gnd

Signal GND

Tie to AC GND

J1- 45 WX453- N/C WX453- N/C WX453- Wx WX/EGPWS See note AFJ1- 20 WX453+ N/C WX453+ N/C WX453+ Wx WX/EGPWS See note AFJ3- 75 AIORS232_RX Reserved Reserved Reserved Reserved J3- 73 AIORS232_TX Reserved Reserved Reserved Reserved J3- 79 DIORS232_RX Reserved Reserved Reserved Reserved J3- 77 DIORS232_TX Reserved Reserved Reserved Reserved J3- 2 RS232/422_GND Reserved Reserved Reserved Reserved

Data Load Data Load See note T

J3- 3 RS232/422_RX_HI Reserved Reserved Reserved Reserved


J3- 31 RS232/422_RX_LO Reserved Reserved Reserved Reserved J3- 1 RS232/422_TX_HI Reserved Reserved Reserved Reserved


J3- 71 AC12_STRAP2 Reserved Reserved Reserved Reserved J3- 4 AIO_SPARE01 Reserved Reserved Reserved Reserved J3- 32 AIO_SPARE02 Reserved Reserved Reserved Reserved J3- 53 AIO_SPARE03 Reserved Reserved Reserved Reserved J3- 54 AIO_SPARE04 Reserved Reserved Reserved Reserved J3- 49 AIO_SPARE05 Reserved Reserved Reserved Reserved J3- 50 AIO_SPARE06 Reserved Reserved Reserved Reserved J3- 51 AIO_SPARE07 Reserved Reserved Reserved Reserved J3- 67 AIO_SPARE08 Reserved Reserved Reserved Reserved J3- 52 AIO_SPARE09 Reserved Reserved Reserved Reserved J2- 14 AIO_SPARE10 Reserved Reserved Reserved Reserved J3- 28 UIC_SPARE1 Reserved Reserved Reserved Reserved J3- 30 UIC_SPARE2 Reserved Reserved Reserved Reserved J3- 65 UIC_SPARE3 Reserved Reserved Reserved Reserved J3- 40 UIC_SPARE4 Reserved Reserved Reserved Reserved

Table 16—Pin List for EFIS 5XX and EFIS 520

Interface pin notes: a) Tie a minimum of two (2) signal common input to aircraft ground. b) Expanded pitch is available only in EFIS 520 SAR (160E050 or greater). c) Cockpit transfer switch to select EFIS in control. Switch should provide either +28V to Pilot

EHSI & EADI or +28V to Copilot EHSI & EADI (J1-68).

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d) Cockpit switch on both Pilot and Copilot panels to select on-side or off-side sensor source, however ATT1/ATT2 select must also switch in AHRS 429 input data relay as well as toggle discrete.

e) +28VDC removes FD and Flight Director Bars from view. f) Sets “DH” flag on EFIS, tie into existing RA DH setting if old system is still utilized. g) +28VDC terrain from EGPWS is displayed in Arc + Map + WX/EGPWS mode, open WX data is

displayed. h) Tie a minimum of two (2) +28VDC out common to aircraft ground. i) Tie Pilot ADI valid (J1-79) to Pilot HSI (J3-21) ADI valid in.

Tie Pilot HSI valid (J1-79) to Pilot ADI (J3-21) HSI valid in. Tie Copilot ADI valid (J1-79) to Copilot HSI (J3-21) ADI valid in. Tie Copilot HSI valid (J1-79) to Copilot ADI (J3-21) HSI valid in.

j) Function available in EFIS 520 SAR (160E050 or greater) only. Provides autopilot with +28VDC output when indicated primary navigation source is selected on EFIS. For single system VOR or LNV with pilot side designator set to 2, the sensor 2 discrete will be activated.

k) For single source connect to both port 1 & 2 on all units directly (see L & P). For mixed navigation radios (i.e. digital VOR1, analog VOR2) connect digital to all units and analog to all units.

l) If remote EFIS control panel (RCP) is used, connect digital ADF1&2 and digital doppler to control panel (RCP) and direct connect remote control panel to EFIS ADF ports (J1-2/30).

m) If dual FMS and dual digital radio altimeters are used, switch in on-side radio altimeter to the HSI port J1-4/32 when the HSI enters composite mode DGNDOUT6 (J3-11).

For the EFIS 520 SAR (160E050 or greater), Wx 429 data is not required if WXRT Control for range is selected. WX 429 from the control head is required for EFIS to control range.

n) If single FMS and dual digital radio altimeters are used connect on-side radio altimeter to HSI port J1-28/50.

o) Reversion switch ADC1/ADC2 should also switch ADC input to EFIS. p) Attitude/Heading must be purely digital (AHRS) or purely analog (gyro). No mixing of AHRS

and Gyro is allowed. The SAF version may mix a single DG/VG pair with a digital system. q) LNAV output is only used on CMA-9000, KLN90B and Garmin FMS. r) Use both Hi and Lo +28 aircraft power pins to distribute power to unit. Each unit should be on

its own 5-amp circuit breaker. s) CPUGND_COM pins J1-31/47 should not be connected to aircraft GND. They are used to

strap CPUGND1-7 pins (J1-23, 25, 49, 27, 29, 1 and 3) only. t) CPUGND6 and the RS-232 bus are used for maintenance mode only – software upload and the

debugger. J3-1 (Tx) carries data from the EFIS unit to the PC (pin 2 of a DB-9 connector), J3-3 (Rx) carries data from the PC to the EFIS unit (pin 3 of a DB-9 connector). The ground is pin 9 of a DB-9 connector. J3-25 (CPUDLCTRL) must be grounded to re-program a unit.

u) <REMOVED>: v) Ensure gyro reference is sourced from the same power bus as the gyro otherwise phase errors

could occur. w) Traffic select ABV/BLW/ALL/ABS and terrain pop-up are momentary GND closures and should

open after pilot has released the button push. x) When Doppler enable is grounded, the EFIS will display Doppler cues in Rose Map mode.

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y) TTL to FD (J3-5) used to notify AP/FD of approach mode or power an indicator. z) DH alert (J3-7) output is used to notify AP/FD of decision height. aa) DME XFR (J3-9) provides a GND out on all four units when:

1. EFIS in command is selected to pilot off-side VOR source (see C). 2. EFIS not in command is selected to pilot off-side VOR and EFIS in command is selected

to a non-VOR primary navigation. Installer should daisy chain the HSI DME XFR to DME relay. The DME relay should switch DME data to all EFIS units, i.e. open for pilot on-side DME, GND for pilot off-side DME.

ab) Display in composite mode (J3-11) provides a ground when composite mode is selected. ac) Nav pulse (J3-6) provides a ground pulse of approximately 0.7 seconds while pilot is changing

primary nav selection. This is used to notify AP/FD of nav changes (usually used to go into heading hold until new primary nav is selected).

ad) High speed dual redundant EFIS interconnect bus. Connect all units in parallel. ae) Follow jumper indications. HDG error/ CRS datum can be configured to 393mV/Deg or

200mV/Deg on the configuration screen (EFIS 520 SAR only). af) WX453+/- (J1-20/45) is a relay switched input for EGPWS or WX data, controlled by the terrain

select discrete 28vin14 (J3-24). ag) Doppler velocity inputs available on EFIS 520 SAR only. ah) J2- 27/01 are not differential but swing +/- 200 ma into 1 K ohms using J2-40 as signal ground. ai) 28vin2 is Heading Sync on the 520, Rate Gyro valid (ADI) or Doppler valid (HSI) on the 520

SAR.

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EADI2

EADI1

EHSI2

EHSI1

M-net

M-net

TAWS

WX R/TARINC 429 ARINC 429

ARINC 453 ARINC 453

ARINC 453 ARINC 453

FDC

HDG ERRCRSDATUMLat DevVert DevFlags, TTL




TCAS

ADF

D. VOR 1

VOR 1

D. ADF 1

DME

LNV 2

LNV 1

RADALT 2

Heading 1

AHRS 1

AHRS 2

Airdata 1

Airdata 2

D. RADALT 1

AHRS 1

AHRS 2

Airdata 1

Airdata 2

D. RADALT 1

D. RADALT 2

ADF

D. VOR 1

VOR 1

D. ADF 1

DME

Attitude 2

LNV 2

RADALT 2

Heading 1

AHRS 1

AHRS 2

Airdata 1

Airdata 2

D. RADALT 1

D. RADALT 2

DF

D. VOR 2

VOR 2

D. ADF 2

DME

Attitude 1

LNV 1

RADALT 1

Heading 2

TCAS

DF

D. VOR 2

VOR 2

D. ADF 2

DME

LNV 2

LNV 1

RADALT 1

Heading 2

AHRS 1

AHRS 2

Airdata 1

Airdata 2

D. RADALT 2

Copilot Pilot

WX CP WX CP

ARINC 429 ARINC 429D. = digital (ARINC 429)

Figure 25—Typical EFIS 520 System Functional Block Diagram

NOTE: The area within the dashed line illustrates a single EFIS configuration.

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LNAV INTERFACE

LNAV 1ADI J1-21

J1-50J1-2

J1-30

J3-10J3-12J3-36J3-38

LNV1 ALNV1 BLNV2 ALNV2 B

LNAV1 CNTL ALNAV1 CNTL BLNAV2 CNTL ALNAV2 CNTL B

HSI J3-10J3-12J3-36J3-38

J1-21J1-50

J1-2J1-30

LNV1 CNTL ALNV1 CNTL BLNV2 CNTL ALNV2 CNTL B

LNAV1 ALNAV1 BLNAV2 ALNAV2 B

TO COPILOT LNAV REVERSIONARY RELAY

+28 VDC

EFIS IN COMMAND

EFIS INCOMMANDRELAY

+28 VDC

EFIS IN COMMAND

EFIS INCOMMANDRELAY

LNAV 2

TO COPILOT LNAV REVERSIONARY RELAY

+28 VDCHSI VALID

REV. RELAY

WX INTERFACE Figure 26—LNAV Interface Block Diagram

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Figure 27—VOR/DME Interface Block Diagram

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ATTITUDE / HEADINGINTERFACE

ATT1GYRO

DIRGYRO

1

DIRGYRO

2

ATT 2GYRO

Pitch 2XPitch 2ZPitch 2YRoll 2XRoll 2ZRoll 2YHDG 1XHDG 1ZHDG 1Y

ADI 2 J2-18J2-19J2-20J2-21J2-22J2-23J2-24J2-25J2-26J1-51J1-17

J2-18J2-19J2-20J2-21J2-22J2-23J2-24J2-25J2-26J1-51J1-17

Pitch 1XPitch 1ZPitch 1YRoll 1XRoll 1ZRoll 1Y

HDG 2XHDG 2ZHDG 2Y

J2-18J2-19J2-20J2-21J2-22J2-23J2-24J2-25J2-26J1-51J1-17

Pitch 2XPitch 2ZPitch 2YRoll 2XRoll 2ZRoll 2Y

HDG 1XHDG 1ZHDG 1Y

Pitch 1XPitch 1ZPitch 1YRoll 1XRoll 1ZRoll 1YHDG 2XHDG 2ZHDG 2Y

HSI 2J2-18J2-19J2-20J2-21J2-22J2-23J2-24J2-25J2-26J1-17

ATT 2 Valid

ATT 2 Valid

Att 1 Valid

J1-51

HDG 1 Valid

HDG1 Valid

HDG2 Valid

HDG 2 Valid

J2-62, J2-64, J2-66

J2-63, J2-65, J2-51

On all units

+26 VAC

+26 VAC Com

ADI 1

HSI 1

ATT REVATT REV

Figure 28—Attitude/Heading Interface Block Diagram

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ADF / RADIO ALT INTERFACE

J2-46J2-45J2-44J1-76

J1-67J3-07J2-04J2-05J1-74J3-23

ADF2 X

ADF2/DF

ADI

RAD ALT 1

ADF2 ZADF2 YADF Valid

RAD ALT TESTDH OUTRAD ALT+RAD ALT-RAD ALT ValidDH IN

J2-75J2-74J2-67J2-76

ADF2 REF+ADF2 REF-VOR2 REF+VOR2 REF-

26VAC 400HZ

26VAC COM

J2-46J2-45J2-44J1-76

ADF1 X

ADF1ADF1 ZADF1 YADF Valid

J1-67J3-07J2-04J2-05J1-74J3-23

RAD ALT 2

RAD ALT TESTDH OUTRAD ALT+RAD ALT-RAD ALT ValidDH IN

J2-75J2-74J2-67J2-76

ADF1 REF+ADF1 REF-VOR1 REF+VOR1 REF-

26VAC 400HZ

26VAC COM

HSI

Figure 29—ADF/Radio ALT Interface Block Diagram

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ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 Page 323/324


Figure 30—EFIS 5XX Wiring Diagram, Sheet 1 of 15

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Figure 3-17—EFIS 5XX Wiring Diagram, Sheet 4 of 15

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SIGNAL NAME

PIN NO.

PILOT ADI

PILOT HSI

COPILOT ADI

COPILOT HSI COMMENTS

DGND01 J3-78 GND = ATT1 & ATT2

OPEN = ATT GND = ATT1 & ATT2



OPEN = ATT Configure for one or two attitude sources

DGND02 J3-76 GND = HDG1&HDG2

OPEN = HDG GND = HDG1&HDG2



OPEN = HDG Configure for one or two heading sources

DGND03 J3-74 GND = VOR1&VOR2

OPEN = VOR GND = VOR1&VOR2



OPEN = VOR Configure for one or

two VOR sources

DGND04 J3-72 GND = ADF & DF

OPEN = ADF GND = ADF & DF



OPEN = ADF

Configure for one or two ADF or DF

sources

DGND05 J3-70

GND = LNAV1&LNAV2 OPEN = LNV




Configure for one or two LNAV sources

DGND06 J3-68 GND = LNAV

OPEN = NO LNV GND = LNAV



OPEN = NO LNV Configure for some or

no LNAV sources

DGND07 J3-66 GND = DUAL EFIS OPEN = SINGLE

GND = DUAL EFIS OPEN = SINGLE



Configure for single EFIS (2-panel) or

dual EFIS (4-panel)

DGND08 J3-64 GND = RA1 & RA2

OPEN = RA GND = RA1 & RA2



OPEN = RA Configure for one or

two RA sources

DGND09 J3-62 GND = RA

OPEN = NO RA GND = RA



OPEN = NO RA Configure for some or

no RA sources

DGND10 J3-60 GND = FD Aval OPEN = NO FD

GND = FD Aval OPEN = NO FD



Configure for flight director available or

no flight director

DGND11 J1-05 GND = WX

OPEN = NO WX GND = WX



OPEN = NO WX Configure for weather or no weather radar

Table 17—EFIS 500 Configurable Settings

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SIGNAL NAME

PIN NO. PILOT ADI PILOT HSI

COPILOT ADI

COPILOT HSI COMMENTS

DGND22 J1-44 OPEN=ATT2 or ATT1

GND = ATT2

OPEN=ATT 2 or ATT1

GND = ATT2

OPEN=ATT2GND = ATT1

OPEN=ATT2GND = ATT1

Cockpit switch to select EFIS attitude source. Switch must switch both on-side ADI and HSI.

DGND23 J1-21 OPEN=HDG1 GND=HDG2

OPEN=HDG1 GND=HDG2

OPEN=HDG2GND=HDG1

OPEN=HDG2GND=HDG1

Cockpit switch to select EFIS heading source. Switch must switch both on-side ADI and HSI.

28VIN10 J3-44 +28VDC=RA1

OPEN = RA 2

+28VDC=RA1

OPEN = RA 2

+28VDC=RA1

OPEN = RA 2

+28VDC=RA1

OPEN = RA 2

Cockpit switch to select EFIS RA source. Switch must switch both on-side ADI and HSI.

DGND03 J3-74 OPN = onside ADC

GND = offside ADC

OPN = onside ADC

GND = offside ADC

OPN = onside ADC

GND = offside ADC

OPN = onside ADC

GND = offside ADC

Cockpit switch to select airdata source. Switch must switch both onside ADI and HSI (520 only).

DGND08 J3-64 TCAS select TCAS select GND = toggle TCAS display (momentary).

DGND09 J3-62 TCAS mode TCAS mode GND = cycle to next TCAS display mode (momentary).

DGND14 J1-35 Mag/True Heading

Mag/True Heading

Mag/True Heading

Mag/True Heading

Applies to digital heading (SAF only).

DGND17 J1-37 Activate Doppler

Activate Doppler

Enable Doppler symbols when the full map page is active (SAR only).

28VIN08 J1-68 EFIS in command

EFIS in command

EFIS in command

EFIS in command

28V = this side in command, 0V this side not in command.

28VIN14 J3-24 Terrain select Terrain select 28V = Terrain displayed, OPN = WX displayed.

Table 18—EFIS 5XX Switching Table

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Figure 45—EFIS 500 Wiring Diagram, Sheet 1 of 3

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SIGNAL NAME

PIN No.

PILOT ADI

PILOT HSI

CO-PILOT ADI

CO-PILOT HSI COMMENTS

DGND01 J3-78

GND = ATT1 & ATT2

OPEN = ATT

GND = ATT1 & ATT2

OPEN = ATT

GND = ATT1 & ATT2

OPEN = ATT

GND = ATT1 & ATT2

OPEN = ATT

Configure for one or two

attitude sources

DGND02 J3-76

GND = HDG1&HDG2 OPEN = HDG




Configure for one or two heading sources

DGND04 J3-72

GND = ROTOR OPEN = FIXED

WING


WING


WING


WING

Configure for rotor or fixed

wing

DGND05 J3-70

GND = A429 AHRS OPEN =

SYNCHRO

GND = A429 AHRSOPEN =

SYNCHRO

GND = A429 AHRSOPEN =

SYNCHRO

GND = A429 AHRS OPEN =

SYNCHRO AHRS or

VG/DG inputs

DGND07 J3-66 GND = DUAL EFIS OPEN = SINGLE

GND = DUAL EFISOPEN = SINGLE

GND = DUAL EFISOPEN = SINGLE


Configure for single EFIS (2-panel) or dual EFIS (4-panel)

DGND10 J3-60

GND = EXPANDED

OPEN = NORMAL

GND = EXPANDED

OPEN = NORMAL

GND = EXPANDED

OPEN = NORMAL

GND = EXPANDED

OPEN = NORMAL

EXPANDED ADI PITCH

SCALE

DGND13 J1-70 RESERVED

GND= EFIS OPEN = EHSI

ONLY RESERVED

GND= EFIS OPEN = EHSI

ONLY ---

Table 19—EFIS 520 Only Configurable Settings

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CONFIGURATION/INSTALLATION CHECKOUT



1. TC "Configuration/Installation Checkout" /l 1 General

This section contains the procedures to configure and test the EFIS 5XX display system installation. Adjustment or repair of any subsystem component must be performed according to the instructions in the applicable Component Maintenance Manual.

2. Configuration Procedures

A. EFIS 500 Configuration Procedures

(1) Ensure that the equipment is properly installed and cabled.

(2) Apply power to the EFIS 500 system and all equipment interfacing with the EFIS system.

(3) Press and hold the TEST/REF button to enter self-test.

(4) While in self-test (indicated by the yellow TEST box on screen), push the two “B” and “R” buttons simultaneously to enter maintenance mode.

(5) Verify that the displayed hardware and software part numbers are correct for the application.

(6) Select “Configuration Page” by pressing the "N" bezel button.

(7) Select the desired LNAV or FMS and exit.

(8) Perform step (1) through step (7) for each display.

B. EFIS 520 Configuration

(1) EFIS 520 Configuration Procedure

(a) Ensure that the equipment is properly installed and cabled.

(b) Apply power to the EFIS 520 system and all equipment interfacing with the EFIS 520 system. The EFIS units must be connected via their standard M-Net connections for all units to be updated with a new configuration.

(c) On the Pilot’s HSI unit press and hold the TEST/REF button to enter self-test. The Pilot HSI must have its weight on wheels discrete grounded to update the configuration.

(d) While in self-test (indicated by the cyan TEST box on screen), push the “B” and “R” bezel buttons simultaneously to enter identification mode.

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(e) Verify that the displayed hardware and software part numbers are correct for the application.

(f) While in identification mode push the “N” bezel button to enter maintenance mode.

(g) Select “CONFIGURATION SET-UP”. If “CONFIGURATION REVIEW” is displayed the unit is not the pilot HSI or the weight on wheels discrete is not grounded.

(h) Verify/Update the configuration settings per the desired installation configuration by referring to the configuration pages (see Figure 55 through Figure 57). Note that the figures here apply generally to the 520 and 520 SAR. Not all parameters/options will be available on each type.

(i) When the desired configuration is achieved select “SAVE” on the bottom of the page, press the RID, and wait for the text to cycle from magenta back to white. If “SAVE” is not visible no configuration changes were made. When the RID is pressed the changes will be saved in non-volatile memory on all connected units.

(j) After the pilot HSI has been updated, exit the configuration pages by selecting "EXIT." Perform a warm start on all units.

(k) The configuration may be verified on all units.

(2) EFIS 520 Configuration Page Settings

• Air data configuration and number of sources • VOR/TCN source select and number of sources • DME type and number • ADF/DF source type and number of sources (no more than 2 can be

configured) • FMS source type and number of sources • TCAS I, TCAS II or no TCAS • TCAS pop-up mode enable or disable • EGPWS or No EGPWS • Flight Director or No Flight Director type (collective cue only on

helicopter configuration) • FD command bars/ADI aircraft symbol type (delta or bull’s eye) • Fast /Slow (only available on fixed wing configuration) • Doppler may be configured for either a 20 knot or 40 knot full range

(520 SAR only)

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• Vertical Speed Indicator select (available only with AIRDATA selected) • ADF angle sense (whether the signal is a “from” or a “to” bearing) (520

only) • Radio Altitude scaling and bend/declutter points (for RAs with positive

voltages for above-ground altitudes, swap the + and – connections, 520 SAR only)

• Pilot Reference Designator 1 or 2 (pilot is considered “side 1” or “side 2,” 520 SAR only)

• Decision Height enabled or disabled (disable for installations with an independent radio altimeter with decision height capability, 520 SAR only)

• Weather radar can be configured for non-beacon or beacon type (non-beacon only for 520)

• Weather radar vertical profile format is only available if the IVSI is disabled

• Weather radar control data (429) source (WX control panel or WX indicator, 520 SAR only)

(3) EFIS 520 TCAS I or TCAS II Configuration

• Airdata must be connected and configured to the unit in order to display the vertical speed indicator, resolution advisories and absolute mode on the traffic display.

• Selecting TCAS I configures the system as a traffic display only. • Selecting TCAS II configures the system as a traffic and resolution

advisory display. • TCAS traffic pop-up mode can be configured as an option. If

configured, the display will pop up TCAS traffic information in rose map mode with a five-mile range when an alert or advisory is detected.

NOTE: Traffic select/declutter button has no effect on the resolution advisory display.

NOTE: TCAS traffic information and resolution advisories are not available and inhibited if the EHSI is in composite mode; in this case, the RA discrete is set as RA FAIL. In a two EFIS configuration, the off-side EHSI will provide redundant resolution and traffic display.

(4) EFIS 520 EGPWS Terrain Display configuration:

Selection of the EGPWS terrain display configures the EFIS 520 to accept ARINC 453 data from the EGPWS (see the Wiring Harness Requirements and Options section on page 301 to ensure proper connection). External switches

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for all EGPWS are a requirement. EFIS 520 only uses the terrain select input discrete to annunciate “TERR” and display the ARINC 453 data.

NOTE: EGPWS pop-up mode takes priority over TCAS traffic pop-up mode. However, the TCAS resolution advisories are still present.

Figure 55—EFIS 520 Maintenance Page

NOTE: HDG SEL rotates selection cursor. HDG SYNC selects option. Diagnostics leads to Installation Check-out pages.

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Figure 56—EFIS 520 Configuration Page 1

NOTE: HDG SEL rotates selection cursor. HDG SYNC selects parameter. HDG SEL rotates through options in magenta. HDG SYNC selects new parameter option (returns to white) — this is only available if WOW = TRUE and Pilot HSI.

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NOTE: HDG SEL rotates selection cursor. HDG SYNC selects parameter. HDG SEL rotates through options in magenta. HDG SYNC selects parameter option (returns to white) — this is only available if WOW = TRUE and Pilot HSI.

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NOTE: HDG SEL rotates selection bar. HDG SYNC selects parameter. HDG SEL rotates through options in magenta. HDG SYNC selects parameter option (returns to white) — this is only available if WOW = TRUE and Pilot HSI.

(5) Radio Altimeter Configuration Procedure:

1. Determine Rad Alt input voltage/foot scaling factor.

2. Set Scale1 for mV/Ft (low end through bend point).

3. Set Bend at top of first scale.

4. Set Scale2 for mV/Ft (bend point through top end).

5. Set Declutter AGL height in Ft.

Scaling and bend points only apply to analog RAs. The declutter point may be set for both types. RAs with a single scaling factor (no bend), set the bend point to the declutter point and use the same scaling factor for scales 1 and 2.

3. Installation Checkout Procedure

NOTE: Diagnostic pages are not available on the EFIS 500. Proper interface connection and operation is determined through operational display, test set stimulus, and results. The built in debugger may also be used (see section 4).

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CAUTION: Installation checkout is performed using the EFIS 520 maintenance mode diagnostic pages the while the aircraft is on the ground only.

A. Entering Diagnostic mode: (EFIS 520 Only)

(1) Apply power to the EFIS 520 system and all equipment interfacing with the EFIS 520 system.

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(2) Ensure that all displays are properly configured by using the pilot EHSI.

• Press and hold the TEST/REF button to enter self-test.

• While in self-test (indicated by the cyan TEST box on screen), push the “B” and “R” bezel buttons simultaneously to enter identification mode.

• While in identification mode push the “N” bezel button to enter maintenance mode.

• Select “CONFIGURATION SET-UP” and verify the proper configuration and exit.

(3) Select “DIAGNOSTICS.” While in diagnostic mode the current input values are displayed for each type of signal. See Figure 59 through Figure 65 for diagnostic page detail.

(4) Make corrections or configuration changes according to the Wiring Harness Requirements and Options section, or Configuration Settings as described above.

(5) Exit and return to normal operation.

B. Entering Operator-Initiated BIT

(1) Push and hold the “TEST/REF” button until the unit enters BIT as indicated by the yellow or cyan “TEST” annunciation. This BIT is merely a symbology familiarity presentation for the pilot.

(2) Verify that the unit displays valid flight symbology followed by failed sensor symbology, then returns to normal operation.

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Figure 59—EFIS 520 Diagnostic Mode Discrete Ground/Open Inputs

Figure 60—EFIS 520 Diagnostic Mode Discrete 28 Volt/Open Inputs

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Figure 61—EFIS 520 Diagnostic Mode Variable DC Inputs

Figure 62—EFIS 520 Diagnostic Mode Synchro Inputs

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Figure 63—EFIS 520 Diagnostic Mode Discrete Outputs

Figure 64—EFIS 520 Diagnostic Mode Variable Outputs

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Figure 65—EFIS 520 Diagnostic Mode ARINC 429 HS and LS Inputs

4. Maintenance Port

EFIS indicators provide, through the main connector, an RS-232C port to Ground Support Equipment (GSE) for maintenance purposes. This port can be used when enabled via a ground strap on an input discrete (CPUDGND6).

EFIS 5XX RS-232 COMMANDS Initial Command

Secondary Command

Action

AIO Display AIO status. DIO Display DIO status. ARINC429 Display ARINC status.

SHO

FAIL Display unit failure history. CLEARFAIL Clears unit failure history. CONFIG Display current unit configuration DNLD Download new EFIS operating software. ?

n/a

Display available menu options. HELP various Display help information on selected subject. For

example, “HELP DNLD” will display help information for the DNLD command.

A. Ground Support Equipment (GSE) Operation.

Accessing the RS-232 Maintenance functions is accomplished through grounding the GSE enable discrete (CPUDGND6) and connecting a COM port of a PC running a communications program (QMODEM, for example) to the RS-232 Rx, Tx, and ground outputs (RS232/422_RX_HI, RS232/422_TX_HI and RS232/422_GND). This

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interface provides access to the EFIS failure history, the configuration state, the download function, and other debugging functions. The PC’s communications program must be set for 9600 baud, 8 bits of data, no parity, and 1 stop bit.

B. Software Data Loading

Enabling the software data load function will be accomplished through the RS-232 Maintenance functions as described above.

The EFIS equipment allows for software data-loading. The EFIS contains a root kernel of code that is loaded whenever it is programmed in the factory. This root kernel of code contains the code necessary to ensure proper download of code in the field utilizing a PC with a RS 232 Tx/RX port. Connector pin J3-25 must be grounded to enable software download. Individual record checksums and an overall 32 bit Cyclic Redundancy Check (CRC) code are used to ensure proper download.

If a failure occurs during the reprogramming process, the unit may not allow further S/W download. The unit must be returned to the factory for initial code reload in this case.

The results of the re-programming will be displayed on the PC monitor controlling the process. When download is finished, the EFIS must be restarted with a cold start. Final verification of the download will be depicted on the display configuration page. The operator will verify that the proper S/W version number matches the displayed version number.

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INSPECTION CHECK



1. TC "Inspection/Check" \l 1 General

This section provides instruction to verify the mechanical condition of the display while installed in the aircraft.

2. Inspection/Check Procedure

• Verify that the display is not chipped or cracked, and that the knobs and buttons are in working order.

• Verify that the display connections are properly mated and tightened. • Verify that the unit is properly secured and mounted in the aircraft panel.

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INSPECTION CHECK




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CLEANING/PAINTING



1. TC "Cleaning/Painting" General

This section describes the procedures for cleaning and painting the exterior of the EFIS 5XX units.

2. Cleaning Procedure

A. General Assembly Cleaning Procedures

WARNING: Isopropyl alcohol is flammable and toxic to skin, eyes, and respiratory tract. Skin and eye protection required. Avoid repeated or prolonged contact. Good general ventilation is normally adequate.

CAUTION: Do not use chlorinated solvents or metal pick to clean parts. Do not use silicone grease on components. Use a solution of 75% isopropyl alcohol and 25% ionized water, and wet only the cotton swab. Do not wet the glass directly.

(1) Clean electrical connector(s) with a cotton swab soaked in isopropyl alcohol solution.

(2) Clean outer surface of unit using commercially available cleaning solvents and a lint free cloth.

(3) Parts must be free of corrosion, dirt, grease, oil and other contaminants.

B. EFIS Unit Monitor Screen Cleaning

Use the following procedure whenever the aircraft is in flight or in preparation for flight and dirt, dust, contaminants or other factors prevent a clear view of the EFIS display on the monitor.

CAUTION: Do not spray any cleaning solution, solvent or fluid of any kind directly on the EFIS unit screen or elsewhere on the face of the unit. The spraying process can cause fluids or moisture to be drawn between the inner and outer screens of the unit requiring repair action.

CAUTION: Avoid touching any other part of the front surface of the unit with the cleaning cloth.

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CLEANING/PAINTING



(1) Apply mild glass-cleaning solution (as above) to a soft lint-free cloth and, using extreme care, clean away any dirt, dust or contaminant on the unit video screen. Avoid using pressure and if necessary, use repeated applications of the solution to clear away the substance.

(2) Allow the screen to air dry, or if there is any streaking or dampness, use a clean, dry, lint-free cloth to dry the screen of any residual cleaning solution.

(3) Inspect the unit screen for evidence of any residual contaminants and request maintenance action if unable to clean the surface of the screen completely,

3. Painting Procedure

CAUTION: Ensure that paint is applied to exterior surfaces only, and that paint is not applied to the AMLCD or lighted bezel characters.

Touchup painting may be performed on any of the system equipment.

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REPAIRS



1. TC "Repairs" General

CAUTION: Repair of the EFIS 5XX unit by unauthorized personnel will void your warranty and may impair the performance of the EFIS 5XX unit.

If the EFIS 5XX unit fails to perform to specification, contact Rogerson Kratos Customer Support (see page 2) for troubleshooting assistance or return procedures.

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REPAIRS




Documents

NEOAV 500 ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) … · 9967-0041 REV F RECORD OF TEMPORARY REVISIONS ROGERSON KRATOS · 403 SOUTH RAYMOND AVENUE · PASADENA, CA 91109 RTR-1 All