NEOAV 500 ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS

Transcription

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-1
NOTICES
This manual applies to the following equipment:
UNIT
MODEL
5 ATI EFIS (Rotorcraft)
EFIS 500
5 ATI EFIS (Rotorcraft /NVG) EFIS 500 NVG
5 ATI EFIS (Fixed Wing and
EFIS 520
Rotorcraft)
5 ATI EFIS (Fixed and Rotor) EFIS 520 NVG
NVG
5 ATI EFIS (Fixed and Rotor) EFIS 520 SAR / SAF
SAR / NVG
ROGERSON KRATOS P/N
160E015-X
160E030-X
160E046-X
160E049-X
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
COVER-2
9967-0041
Rev F
RECORD OF REVISIONS
THIS PAGE INTENTIONALLY BLANK
All information on this page is subject to the restrictions of the proprietary notice of this document.
RR-2
9967-0041
REV F
RECORD OF TEMPORARY REVISIONS
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.
RTR-1
9967-0041
REV F
RECORD OF TEMPORARY REVISIONS
RTR-2
9967-0041
Rev F
SERVICE BULLETIN LIST
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.
SBL-1
9967-0041
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SERVICE BULLETIN LIST
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LIST OF EFFECTIVE PAGES
SUBJECT
Cover
PAGE
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DATE
OCT 25/05
MAR 23/04
MAR 23/04
MAR 23/04
MAR 23/04
MAR 23/04
Testing and Fault
Isolation
101
102
MAR 23/04
MAR 23/04
Installation/
Removal
201
202
203
204
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Description and
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Operation
2 OCT 25/05
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Record of
Revisions
DATE
APR 2/07
APR 2/07
RR-1
RR-2
MAR 23/04
SEP 10/02
Record of
Temporary
Revisions
RTR-1
RTR-2
SEP 10/02
SEP 10/02
Service Bulletin
List
SBL-1
SBL-2
SEP 10/02
SEP 10/02
List of Effective
Pages
LEP-1
LEP-2
APR 2/07
APR 2/07
Table of
Contents
TOC-1
TOC-2
TOC-3
TOC-4
MAR 23/04
MAR 23/04
MAR 23/04
MAR 23/04
INTRO-1
INTRO-2
INTRO-3
INTRO-4
INTRO-5
INTRO-6
APR 2/07
OCT 25/05
MAR 23/04
APR 2/07
SEP 10/02
SEP 10/02
Introduction
SUBJECT
Wiring Harness
Requirements and
Options
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LIST OF EFFECTIVE PAGES
SUBJECT
PAGE
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DATE
MAR 23/04
MAR 23/04
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APR 2/07
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Configuration/
Installation
Checkout
401
402
403
404
405
406
407
408
409
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414
OCT 25/05
APR 2/07
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MAR 23/04
MAR 23/04
MAR 23/04
OCT 25/05
OCT 25/05
Inspection/
Check
501
502
SEP 10/02
SEP 10/02
Cleaning/
Painting
601
602
SEP 10/02
SEP 10/02
Repairs
701
702
SEP 10/02
SEP 10/02
"F" indicates a fold-out page
LEP-2
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TABLE OF CONTENTS
INTRODUCTION .................................................................................................................. 1
1.
2.
3.
4.
5.
6.
General ...................................................................................................................... 1
Manufacturing ............................................................................................................ 1
Manual Format........................................................................................................... 1
Revision Service ........................................................................................................ 2
Technical Questions .................................................................................................. 2
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.
2.
3.
4.
General .................................................................................................................. 201
Advisories .............................................................................................................. 202
Installation Considerations ..................................................................................... 203
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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TABLE OF CONTENTS
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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TABLE OF CONTENTS
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 40—EFIS 5XX Wiring Diagram, Sheet 10 of 15................................................................................... 341
Figure 46—EFIS 500 Wiring Diagram, Sheet 1 of 3........................................................................................ 355
Figure 56—EFIS 520 Maintenance Page ........................................................................................................ 404
Figure 57—EFIS 520 Configuration Page 1 .................................................................................................... 405
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
TOC-4
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INTRODUCTION
1.
{ TC "Introduction" \l1}General
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
5 ATI EFIS (Rotorcraft)
5 ATI EFIS (Rotorcraft /NVG)
5 ATI EFIS (Fixed Wing and
Rotorcraft)
5 ATI EFIS (Fixed and Rotor)
NVG
5 ATI EFIS (Fixed and Rotor)
SAR / NVG
MODEL
EFIS 500
EFIS 500 NVG
EFIS 520
ROGERSON KRATOS P/N
160E015-X
160E030-X
160E046-X
EFIS 520 NVG
160E049-X
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
INTRO-1
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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:
•
•
•
•
•
•
•
•
6.
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
Abbreviations/Acronyms
ABBREVIATION/
ACRONYM
ABS
ABV
ADF
ADI
AFCS
AHRS
ALT
AMLCD
ARINC
ATI
ATT
DESCRIPTION
Absolute
Above
Automatic Direction Finder
Attitude Direction Indicator
Automatic Flight Control System
Attitude Heading Reference System
Altitude
Active Matrix Liquid Crystal Display
Aeronautical Radio, Incorporated
Air Transport Indicator
Attitude
INTRO-2
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INTRODUCTION
ABBREVIATION/
ACRONYM
AWG
BC
BIT
BLW
BRG
CAP
CCW
COL
CRS
CW
DF
DG
DG/VG
DH
DME
DR
DTK
EADI
EFIS
EGPWS
EHSI
EMI
ESD
EX-LOC
FCC
FCS
FD
FDC
FMS
GA
GMAP
GND
GPS
GS
GSE
GSPD
HDG
HSI
HZN
IAS
ILS
IM
DESCRIPTION
American Wire Gauge
Back Course
Built-in Test
Below
Bearing
Capture
Counterclockwise
Collective
Course
Clockwise
Direction Finder
Direction Gyro
Direction Gyro/Vertical Gyro
Decision Height
Distance Measurement Equipment
Dead Reckoning
Desired Track
Electronic Attitude Direction Indicator
Electronic Flight Instrument System
Enhanced Ground Proximity Warning System
Electronic Horizontal Situation Indicator
Electromagnetic Interference
Electrostatic Sensitive Device
Expanded Localizer
Flight Control Computer
Flight Control System
Flight Director
Flight Director Computer
Flight Management System
Go Around
Ground Map
Ground
Global Positioning System
Glideslope
Ground Support Equipment
Ground Speed
Heading
Horizontal Situation Indicator
Horizon
Indicated Airspeed
Instrument Landing System
Inner Marker
INTRO-3
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INTRODUCTION
ABBREVIATION/
ACRONYM
INS
IRS
LMT
LNAV
LOC
MAG
MB
MFD
MM
MON
MSG
NAV
NCD
NM
NVM
OBS
OM
PELS
PIT
PROF
RA
REV
RFI
RID
RK
RNAV
ROL
SAF
SAR
STAB
STBY
TACAN
TBD
TCAS
TCN
TTL
TTS
VAPP
VG
VOR
VORTAC
VS
DESCRIPTION
Inertial Navigation System
Inertial Reference System
Limit
Long Range Navigation
Localizer
Magnetic
Marker Beacon
Multi-function Display
Middle Marker
Monitor
Message
Navigational
No Computed Data
Nautical Miles
Non-Volatile Memory
Omni Bearing Select
Outer Marker
Pixel Element Light Segments
Pitch
Profile
Radio Altimeter, Resolution Advisory
Reversionary
Radio Frequency Interference
Rotary Input Device
Rogerson Kratos
Area Navigation
Roll
Swedish Air Force
Search and Rescue
Stabilization
Standby
Tactical Air Navigation
To Be Defined (or Determined)
Traffic Alert and Collision Avoidance System
Tactical Air Navigation
Tuned To Localizer
Time to Station
VOR Approach
Vertical Gyro
Very-High-Frequency Omnirange
VOR/TACAN
Vertical Speed
INTRO-4
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INTRODUCTION
ABBREVIATION/
ACRONYM
VSI
WOW
WPT
WX
WXA
WXR
XTK
DESCRIPTION
Vertical Speed Indicator
Weight on Wheels
Waypoint
Weather
Weather Alert
Weather Radar
Cross Track
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INTRODUCTION
INTRO-6
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DESCRIPTION AND OPERATION
1.
{ TC "Description and Operation" \l1}Data Sheet
CHARACTERISTIC
Dimensions
SPECIFICATION
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]
(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
4.2 X 4.2 inch [106.68mm X 106.68mm] square AMLCD, 719 X 719 PELS
Motorola 68020 processor
7.8 lbs. [3.538kg] max.
Passive, natural convection, No forced air cooling required.
Mil-C-38999 Series III 79 pin: D38999/2ING35PN
Mating: D38999/26FG35SN, RK P/N 2115-0119
Mil-C-38999 Series III 79 pin: D38999/2ING35PA
Mating: D38999/26FG35SA, RK P/N 2115-0120
Mil-C-38999 Series III 79 pin: D38999/2ING35PB
Mating: D38999/26FG35SB, RK P/N 2115-0121
+28VDC, +12V to 32VDC.
50 Watts max with heaters on
38 Watts max with full brightness
5 Watts max +5VDC bezel lighting
0 – 50 mS: recovery within 500 msec after interrupt completion
Mechanical Controls
Display Type
Central Processor
Weight
Cooling
Connectors /Mating
Connectors – J1
Connectors /Mating
Connectors – J2
Connectors /Mating
Connectors – J3
Electrical – Power
Consumption
Interrupt
Interface - Synchro
Interface – ARINC 429
Interface – RS 232
Interface – Variable
voltage / Current
Interface – Discrete
Each unit: (6) ARINC 407 Synchro inputs, (2) Resolver outputs
Each unit: (8) ARINC 429 inputs. (4) ARINC 429 outputs
Each unit: (1) ARINC 453 inputs compatible to ARINC 708 Weather Radar
Each unit: (1) ARINC 568 DME input
Each unit: (1) RS-422/232 input and output for Ground Support and Data loading
(12) variable current or voltage inputs, 2 variable DC outputs
Software
Environmental –
Category
Environmental - Temp
Environmental - Humidity
Environmental - Shock
Environmental Vibration
(16) 28 V / open inputs, (8) 28 V outputs, (32) Gnd/Open inputs, (8) Gnd/Open
outputs, (8) EFIS reserved Gnd/Open discretes
DO-178B Levels A and B
B1BANXXXXXSAZAZZYZA3E3XX
RTCA/DO-160C, Sec. 5, Cat. B
RTCA/DO-160C, Sec. 6, Cat. A
RTCA/DO-160C, Sec. 7
RTCA/DO-160C, Sec. 8, Cat. N
Table 2—Data Sheet
Page 1
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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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TSO
Standards
Comment
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:
3.
TSO
Standards
Comment
C113
AS 8034
Provides C113 compatable Airborne Multipurpose Electronic
Display
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).
S
e
e
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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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M
N
B
R
Figure 1—EFIS Outline Drawing (all P/Ns covered in this document)
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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
M
N
B
R
B.
ADI
ADI =
COMPOSITE
HSI
COMPOSITE
FORCED
MODE SELECT
DH SELECT
NAV SOURCE
NAV SOURCE
INACTIVE
SELECT
SELECT
INACTIVE
BEARING SELECT
BEARING SELECT
INACTIVE
RANGE SELECT
INACTIVE
Table 3—Bezel Mode Button Control Descriptions
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 selftest is terminated automatically after approximately 10 seconds.
NOTE:
(b)
The self-test cannot be performed if the EFIS is in composite
mode.
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
Capture
(Green)
GA
LATERAL CUE
VERTICAL CUE
Arm
Capture
Arm
Capture
(White)
(Green)
(White)
(Green)
NAV
NAV
GS
ALT
VAPP
VAPP
GS
LNV
LNV
IAS
LOC
LOC
VS
BC
BC
GA
HDG
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
NAV ARM
⇒ NAV CAP
LOC ARM
⇒ LOC CAP
BC ARM
⇒ BC CAP
VAPP ARM ⇒ VAPP CAP
VERTICAL TRANSITIONS
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
5 feet
≤ 200 feet
10 feet
> 200 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
1 foot
≤ 200 feet
10 feet
> 200 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:
(3)
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.
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
DISPLAYED
SIGNALS
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:
(c)
These comparisons are active only when both NAV receivers
are tuned to the same ILS frequency.
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)
1200
VS
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:
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:
6
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.
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:
7
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.
DH select while in Composite Mode is only applicable
during forced composite operations (i.e. EFIS same
side unit has failed).
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:
(3)
Use the digital heading select display next to the HDG SEL knob
when setting the heading bug.
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.
Page 28
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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
Page 29
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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. Selftest 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. Selftest 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
Page 30
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Rev F
•
•
•
•
G.
Digital I/O board version
Display generator version
An alert that NVM error information is present
M-net status
LNAV Configuration Page
(1)
EFIS 500
•
•
•
•
(2)
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.
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" \l1}General
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
•
•
3.
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.
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" \l1}General
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 mounting
location of system
components
Check wire harness
Determine other
avionics suite and
EFIS configuration
Apply power to
system
Construct and install
wire harness
Check software and
hardware
configuration
selections
Install EFIS 5XX
using instrument
mounting clamp
Perform checkout
procedure
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.
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•
3.
Do not handle ESDs unnecessarily or remove them from their packages until actually
used or tested.
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:
•
•
•
•
•
•
•
•
4.
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
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.
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•
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
Serial data bus
Analog discrete signal
Analog synchro/resolver
Strapping pin
WIRE TYPE
#22 AWG, twisted shield pair, Teflon insulated wire
#22 AWG, Teflon insulated wire
#22 AWG, triple-shielded, Teflon insulated wire
#22 AWG, Teflon insulated wire
#22 AWG, Teflon insulated wire, 3-inch [76.2mm]
Shield ground wires
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.
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(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
U
s
e
t
h
e
E
F
I
S
5
X
X
o
u
t
l
i
n
e
a
Page 205
9976-0041
Rev F
n
d
m
o
u
n
t
i
n
g
d
i
a
g
r
a
m
(
s
e
e
Page 206
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.
Page 207
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Rev F
RK Kit P/N
Description
SP-0624-0003
0 angle mount w/
MS24693BB52 mount screws
SP-0624-0004
0 angle mount w/ MS35214-44
mount screws
SP-0624-0005
3.5 deg angle mount w/
MS5214-46 mount screws
SP-0624-0006
SP-0624-0007
6.0 deg spacer
SP-0624-0008
SP-0624-0009
3.0 deg spacer
SP-0624-0010
Mooring Plate
SP-0624-0011
Adapter Plate
SP-0624-0012
4" Flush mount (nonpreferred)
w/ MS24693BB276 mount
screws
SP-0624-0013
4" Flush mount (nonpreferred)
w/ MS35215-57 mount screws
CONTENTS
Connector
Connector
(qty)
(qty)
RK P/N
RK P/N
2115-0120
2115-0121
Mount
(qty)
Connector
(qty)
RK P/N
2115-0119
Backshell
(qty)
RK P/N
2151-0033
Installation
Manual
Ref.
4
4
4
4
12
1
Table 12
Figure 22
4
4
4
4
12
1
Table 12
Figure 22
4
4
4
4
12
1
Table 12
Figure 22
4
4
4
4
12
1
4
---
---
---
---
1
4
4
4
4
12
1
4
---
---
---
---
---
4
---
---
---
---
---
4
---
---
---
---
---
Table 12
Figure 22
Table 12
Figure 22
Table 12
Figure 22
Table 14
Figure 24
4
4
4
4
12
1
Table 13
Figure 23
4
4
4
4
12
1
Table 13
Figure 23
Table 12
Figure 22
Table 12
Figure 22
Table 11—Mounting Kits
(2)
Mounting Options
Clamp and adapter plate mounting options provide additional aids for simple
installation.
(a)
RK P/N
2803-0048
2803-0049
2803-0052
2803-0050
2803-0014
2803-0051
2803-0015
2803-0002
ARINC #408
SPEC
5ATI-S
5ATI-S
5ATI-S
5ATI-S
SPACER
5ATI-S
SPACER
MOORING
PLATE
Clamp Configuration 1
A
±.010
4.975
4.975
4.975
4.975
5.010
4.975
5.010
B
±.010
4.975
4.975
4.975
4.975
5.010
4.975
5.010
5.175
5.175
Figure 22 REF
C
D
±.005
±.005
4.810
4.810
4.810
4.810
4.810
4.819
4.810
4.810
4.810
4.810
4.810
4.810
4.810
4.810
4.810
4.810
E
±.010
0.476
0.476
0.576
0.428
0.488
0.428
0.488
F
REF.
6.360
6.360
6.360
6.430
6.395
6.430
6.395
ANGLE
±1°
MOUNTING
SCREWS
ADJUSTING
SCREW
RK KIT P/N
REF
0
0
3.5
6.0
6.0
3.0
3.0
MS24693BB52
MS35214-44
MS35214-46
MS35214-41
--MS35214-47
---
MS35214-50
MS35214-50
MS35214-50
MS35214-50
--MS35214-50
---
SP-0624-0003
SP-0624-0004
SP-0624-0005
SP-0624-0006
SP-0624-0007
SP-0624-0008
SP-0624-0009
5.010
5.010
0.488
---
---
SP-0624-0010
Table 12—Clamp Configuration 1
Page 208
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Figure 22—Clamp Configuration 1
(b)
RK P/N
2803-0046
2803-0047
RK SPEC
5ATI-S
4"DEEP
5ATI-S
4"DEEP
Clamp Configuration 2
A
Figure 23 REF
B
C
D
T
RK
SCREW
ADJUSTING
SCREW
RK KIT P/N
REF
4.975
4.810
6.360
4.00
0.050
MS24693BB276 MS51957-75 SP-0624-0012
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
Page 209
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(c)
Adapter Plate
Figure 24 REF
OTHER
A
B
C
D
E
F
G
H
I
J
K
L
M
RK P/N
P/N
±.010 ±.010 ±.005 ±.005 ±.010 ±.00 ±.010 ±.010 ±.010 ±.010 REF. REF. ±.003
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
RK KIT
P/N REF
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.
Page 210
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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).
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Page 212
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WIRING HARNESS REQUIREMENTS AND OPTIONS
1.
{ TC "Wiring Harness Requirements and Options" \l1}General
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
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.
Page 301
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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
Page 302
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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:
(2)
Ensure CPUDGND jumper straps are only connected to
CPUDGND_COM RETURNS (J1-31 or J1-47)
EFIS 5XX System Configuration
NOTE:
(a)
Ensure DGND jumper straps are only connected to DGND SIGNAL
COM RETURNS (J1-39/41, or J3-56/58).
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.
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(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:
(3)
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.
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).
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PIN
DGND03 J3-74
DGND04 J3-72
DGND05 J3-70
DGND06 J3-68
DGND08 J3-64
DGND09 J3-62
DGND10 J3-60
DGND11 J1-5
CONFIGURATION EFFECT
Single or dual VOR sources
Single or ADF and DF sources
Single or dual LNAV / FMS sources
1/2 or no LNAV / FMS sources
Single or dual radio altimeter sources
1/2 or no radio altimeter sources
Flight director or no flight director
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:
(2)
Ensure that +28VDC discrete jumper straps are only connected to
+28VDC-COM returns (J1-52/73, or J3-45/48).
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.
Page 305
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 j135). 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.
Page 306
9976-0041
Rev F
EFIS 5XX
PIN
SIGNAL
NAME
J116 DCPWR_LO
J216 DCPWR_LO
J113 DCPWR1_HI
J213 DCPWR2_HI
J16
HTRPWR
J133
J115
J215
J315
J143
HTRRTN
CHASSISGND
CHASSISGND
CHASSISGND
ACLITING
J118 ACLITINGRTN
J123 CPUDGND1
J125 CPUDGND2
J149 CPUDGND3
J127
J129
J11
J13
J325
PILOT
ADI
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Hi
+28 VDC
Power Input
Hi
+28 VDC
POWER IN
Hi
+28 VDC
POWER IN
LO
Chassis
Ground
Chassis
Ground
Chassis
Ground
+ 5 VAC
Lighting Hi
+5 VAC
Lighting
Com
Strap to
Pilot ADI
J1-31 or 47
PILOT
HSI
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Hi
+28 VDC
Power Input
Hi
+28 VDC
POWER IN
Hi
+28 VDC
POWER IN
LO
Chassis
Ground
Chassis
Ground
Chassis
Ground
+ 5 VAC
Lighting Hi
+5 VAC
Lighting
Com
N/C
Strap to
Pilot HSI
N/C
J1-31 or 47
Strap to
Strap to
Pilot HSI
Pilot ADI
J1-31 or 47 J1-31 or 47
CO-PILOT
ADI
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Hi
+28 VDC
Power Input
Hi
+28 VDC
POWER IN
Hi
+28 VDC
POWER IN
LO
Chassis
Ground
Chassis
Ground
Chassis
Ground
+ 5 VAC
Lighting Hi
+5 VAC
Lighting
Com
Strap to
Copilot ADI
J1-31 or 47
N/C
EFIS 520 ONLY
CO-PILOT
HSI
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Lo
+28 VDC
Power Input
Hi
+28 VDC
Power Input
Hi
+28 VDC
POWER IN
Hi
+28 VDC
POWER IN
LO
Chassis
Ground
Chassis
Ground
Chassis
Ground
+ 5 VAC
Lighting Hi
+5 VAC
Lighting
Com
N/C
CPUDGND5
Reserved
GSE
Enable
Reserved
GSE
Enable
Reserved
GSE
Enable
Reserved
GSE
Enable
Reserved
reprogram
enable
CPU
STRAP
COM
CPU
STRAP
COM
Reserved
reprogram
enable
CPU
STRAP
COM
CPU
STRAP
COM
Reserved
reprogram
enable
CPU
STRAP
COM
CPU
STRAP
COM
Reserved
reprogram
enable
CPU
STRAP
COM
CPU
STRAP
COM
Reserved
J1-69
MNETPC
ALL EFIS
J1-77
MNETPH
ALL EFIS
J1-7
MNETSC
ALL EFIS
Reserved
J1-69
MNETPC
ALL EFIS
J1-77
MNETPH
ALL EFIS
J1-7
MNETSC
ALL EFIS
Reserved
J1-69
MNETPC
ALL EFIS
J1-77
MNETPH
ALL EFIS
J1-7
MNETSC
ALL EFIS
Reserved
J1-69
MNETPC
ALL EFIS
J1-77
MNETPH
ALL EFIS
J1-7
MNETSC
ALL EFIS
CPUDLCTRL
J131 CPUDGND_COM
J147 CPUDGND_COM
J326 CPU_SPARE
J169 MNETPC
J177 MNETPH
J17
MNETSC
PILOT
HSI
CO-PILOT CO-PILOT
ADI
HSI
Note Ref.
EFIS 520
USE
Power
Unit Power
See note R
Power
Unit Power
See note R
Power
Unit Power
See note R
Power
Unit Power
See note R
Power
LCD Heater
Power
LCD Heater
Power
GND
Power
GND
Power
Power
GND
Bezel
Lighting
Power
Bezel
Lighting
N/C
N/C
ADI/HSI
Strap to
Strap to
Copilot ADI Copilot HSI
J1-31 or 47 J1-31or 47 ADI/HSI
N/C
CPUDGND7
PILOT
ADI
N/C
ADI/HSI
Strap to
Copilot HSI
J1-31 or 47 ADI/HSI
CPUDGND4
CPUDGND6
EFIS
500
USE
Config
See note S
Config
See note S
Config
See note S
Config
See note S
Data
Load
See note T
Data Load
See note T
ADI/HSI
Cofig Com
See note S
ADI/HSI
Cofig Com
See note S
ADI/HSI
EFIS Bus
See note AD
ADI/HSI
EFIS Bus
See note AD
ADI/HSI
EFIS Bus
See note AD
Page 307
9976-0041
Rev F
EFIS 5XX
PIN
SIGNAL
NAME
J19
MNETSH
J151 28VIN01
J153 28VIN02
J155 28VIN03
J157 28VIN04
J172 28VIN05
J174 28VIN06
J176 28VIN07
J168 28VIN08
J320 28VIN09
J344 28VIN10
J321 28VIN11
J322 28VIN12
J323 28VIN13
EFIS 520 ONLY
EFIS
500
USE
PILOT
PILOT
CO-PILOT CO-PILOT
ADI
HSI
ADI
HSI
J1-9
J1-9
J1-9
J1-9
MNETSH
MNETSH
MNETSH
MNETSH
ALL EFIS ALL EFIS ALL EFIS ALL EFIS ADI/HSI
+28 V =
+28 V =
+28 V =
+28 V =
ATT1 Valid ATT2 Valid ATT2 Valid ATT1 Valid
Gyro
HDG SYNC HDG SYNC HDG SYNC HDG SYNC
+28 V =
VOR/LOC 2
Valid
+28 V =
Glideslope
2 Valid
+28 V =
DME Valid
+28 V =
Rad Alt 1
Valid
+28 V =
ADF 2 Valid
+28 V =
EFIS in
Command
+28 V =
VOR/LOC 1
Valid
+28 V =
Glideslope1
Valid
+28 V =
DME Valid
+28 V =
Rad Alt 2
Valid
+28 V =
ADF 1 Valid
+28 V =
EFIS in
Command
+28 V =
VOR/LOC 1
Valid
+28 V =
Glideslope
1 Valid
+28 V =
DME Valid
+28 V =
Rad Alt 2
Valid
+28 V =
ADF 1 Valid
+28 V =
EFIS in
Command
Switch
+28 V =
VOR/LOC 2
Valid
VOR
+28 V =
Glideslope
2 Valid
VOR
+28 V =
DME Valid
DME
+28 V =
Rad Alt 1
Valid
Rad Alt
+28 V =
ADF 2 Valid ADF
+28 V =
EFIS in
Command Switch
+28 V = RA +28 V = RA
1, Open = 1, Open =
RA 2
RA 2
+28 V =
+28 V =
Pilot ADI
Pilot HSI
Valid,
Valid,
Open=Fail Open=Fail
FD
FD
Decouple
Decouple
+28 V = RA
1, Open =
RA 2
+28 V =
Copilot HSI
Valid,
Open=Fail
FD
Decouple
DH ALERT DH ALERT DH ALERT DH ALERT
MB
28VIN16
28VIN_COM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
+28 VIN
COMM
Signal
Com
Signal
Com
Signal
Com
Signal
Com
28VOUT1
ADI Valid
HSI Valid
ADI Valid
HSI Valid
ADI/HSI
28VIN_COM
28VOUT2
28VOUT3
28VOUT4
28VOUT5
HDG SYNC HDG SYNC HDG SYNC HDG SYNC
/
/
/
/
+28V =
+28V =
+28V =
+28V =
Rate Gyro
Doppler
Rate Gyro
Doppler
Valid
Valid
Valid
Valid
+28 V =
+28 V =
+28 V =
+28 V =
VOR/LOC VOR/LOC VOR/LOC VOR/LOC
2/TCN
1/TCN
1/TCN
2/TCN
Valid
Valid
Valid
Valid
Rad Alt
J346 28VIN15
28VIN_COM
CO-PILOT CO-PILOT
ADI
HSI
+28 V = RA
1, Open =
RA 2
Rad Alt
+28 V =
Copilot ADI
Valid,
Open=Fail ADI/HSI
FD
Decouple
FCS
MB
28VIN_COM
PILOT
HSI
+28 V = AP +28 V = AP +28 V = AP +28 V = AP
Coupled
Coupled
Coupled
Coupled
J324 28VIN14
J347
J152
J173
J345
J348
J179
J154
J333
J335
J337
PILOT
ADI
Reserved
Reserved
Reserved
GS VALID
HDG ERR
Valid
GS VALID
HDG ERR
Valid
GS VALID
HDG ERR
Valid
VOR/TCN 1 VOR/TCN 1 VOR/TCN 1 VOR/TCN 1
Primary
Primary
Primary
Primary
Reserved
NAV VALID NAV VALID NAV VALID NAV VALID
GS VALID
HDG ERR
Valid
Terrain
Terrain
Select =
Select =
Fast/Slow
Fast/Slow
28V
28V
Valid = 28V
Valid = 28V
Windshear Windshear Windshear Windshear
Caution = Caution = Caution = Caution =
28V
28V
28V
28V
Windshear Windshear Windshear Windshear
Warning = Warning = Warning = Warning =
28V
28V
28V
28V
EFIS Bus
See note AD
Att Gyro
See note K
Gyro /
doppler
See note AI
VOR/TCN
See note K
ILS
See note K
DME
See note K
RADALT
See note K
ADF
See note K
Cockpit
Switch
See note C
FCS
RA Select
Switch
See note D
EFIS Valid
See note I
FCS
See note E
DH/RADALT
See note F
FS/EGPWS
See note G
WX
WX
Signal Com
See note A
Signal Com
See note A
Signal Com
See note A
Signal Com
See note A
EFIS Valid
See note I
FCS
See note J
FCS
FCS
FCS
FCS
FCS
FCS
Note Ref.
EFIS 520
USE
Page 308
9976-0041
Rev F
EFIS 5XX
SIGNAL
NAME
EFIS 520 ONLY
PILOT
ADI
PILOT
HSI
J339 28VOUT6
Reserved
Reserved
Reserved
Reserved
J341 28VOUT7
Reserved
Reserved
Reserved
Reserved
Reserved
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
GND =
Dual ATT
OPEN =
Single ATT
GND =
Dual HDG
OPEN =
Single HDG
GND =
Dual VOR
OPEN =
Single VOR
GND =
ADF & DF
OPEN =
ADF
GND =
LNAV1
&LNAV2
OPEN=LN
V
GND =
LNAV
OPEN=NO
LNV
GND =
DUAL EFIS
OPEN=
SINGLE
GND = RA1
& RA2
OPEN=RA
GND = RA
OPEN=NO
RA
GND = FD
Avail
OPEN =
NO FD
GND = WX
OPEN=NO
WX
Reserved
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
GND =
Dual ATT
OPEN =
Single ATT
GND =
Dual HDG
OPEN =
Single HDG
GND =
Dual VOR
OPEN =
Single VOR
GND =
ADF & DF
OPEN =
ADF
GND =
LNAV1
&LNAV2
OPEN=LN
V
GND =
LNAV
OPEN=NO
LNV
GND =
DUAL EFIS
OPEN=
SINGLE
GND = RA1
& RA2
OPEN=RA
GND = RA
OPEN=NO
RA
GND = FD
Avail
OPEN =
NO FD
GND = WX
OPEN=NO
WX
Reserved
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
GND =
Dual ATT
OPEN =
Single ATT
GND =
Dual HDG
OPEN =
Single HDG
GND =
Dual VOR
OPEN =
Single VOR
GND =
ADF & DF
OPEN =
ADF
GND =
LNAV1
&LNAV2
OPEN=LN
V
GND =
LNAV
OPEN=NO
LNV
GND =
DUAL EFIS
OPEN=
SINGLE
GND = RA1
& RA2
OPEN=RA
GND = RA
OPEN=NO
RA
GND = FD
Avail
OPEN =
NO FD
GND = WX
OPEN=NO
WX
TTL 2
TTL 1
TTL 1
PIN
J343
J175
J314
J319
J355
28VOUT8
28VOUT_COM
28VOUT_COM
28VOUT_COM
28VOUT_COM
J378 DGND01
J376 DGND02
J374 DGND03
J372 DGND04
J370 DGND05
J368 DGND06
J366 DGND07
J364 DGND08
J362 DGND09
J360 DGND10
J15
DGND11
J178 DGND12
CO-PILOT CO-PILOT
ADI
HSI
EFIS
500
USE
PILOT
PILOT
CO-PILOT CO-PILOT
ADI
HSI
ADI
HSI
VOR/TCN 2 VOR/TCN 2 VOR/TCN 2 VOR/TCN 2
Primary
Primary
Primary
Primary
Nav
Nav
Nav
Nav
LNV 1
LNV 1
LNV 1
LNV 1
Primary
Primary
Primary
Primary
Nav
Nav
Nav
Nav
LNV 2
LNV 2
LNV 2
LNV 2
Primary
Primary
Primary
Primary
Nav
Nav
Nav
Nav
Reserved
+28 V Out
Signal Com Common
+28 V Out
Signal Com
+28 V Out
Signal Com
+28 V Out
Signal Com
GND =
Dual ATT
OPEN =
Single ATT Strap
GND =
Dual HDG
OPEN =
Single HDG Strap
OPEN =
OPEN =
GND =
onside ADC onside ADC
Dual VOR
GND =
GND =
OPEN =
Single VOR Strap offside ADC offside ADC
GND =
GND =
GND =
Rotary,
Rotary,
ADF & DF
Open =
Open =
OPEN =
ADF
Strap Fixed Wing Fixed Wing
GND =
Gnd=A429, Gnd=A429,
LNAV1
AHRS,
AHRS,
&LNAV2
Opn =
Opn =
OPEN=LN
Synchro
Synchro
V
Strap
GND =
GND =
GND =
LNAV
Weight on Weight on
OPEN=NO
Wheels
Wheels
LNV
Strap
GND=
GND=
GND =
DUAL EFIS DUAL EFIS
DUAL EFIS
OPN=
OPN=
OPEN=
SINGLE
SINGLE
SINGLE
Strap
GND =
GND = RA1
Traffic
& RA2
Select
OPEN=RA
Strap VNAV ARM
GND =
GND = RA
ABV/BLW/
OPEN=NO
RA
Strap VNAV CAP ABS toggle
GND = FD
GND =
GND =
Avail
expanded expanded
OPEN =
pitch
pitch
NO FD
Strap
GND =
GND = WX
Terrain
OPEN=NO
Pop-Up
WX
Wx
ALT ARM
TTL 2
Reserved
Reserved
Reserved
Reserved
Strap
J135 DGND14
ALT
ALT
ALT
ALT
FCS
FCS
See note J
FCS
See note J
FCS
See note J
See note H
See note H
See note H
See note H
Config single
or dual
Config single
or dual
OPEN =
onside ADC
GND =
offside ADC
GND =
Rotary,
Open =
Fixed Wing
OPEN =
onside ADC
GND =
ADC Select
offside ADC
Switch
GND =
Rotary,
Open =
Fixed Wing
Config
Gnd=A429, Gnd=A429,
AHRS,
AHRS,
Opn =
Opn =
Synchro
Synchro
Analog /
Digital
GND =
GND =
Weight on Weight on
Wheels
WOW
Wheels
GND=
GND=
Single or
DUAL EFIS DUAL EFIS
dual
OPN=
OPN=
SINGLE configuration
SINGLE
GND =
Traffic
Select
FCS/TCAS See note W
VNAV ARM
GND =
ABV/BLW/
VNAV CAP ABS toggle FCS/TCAS See note W
GND =
expanded
pitch
ALT ARM
VOR
J170 DGND13
Note Ref.
EFIS 520
USE
GND=EFIS,
OPEN =
EHSI only
True/Mag True/Mag True/Mag
select (SAF select (SAF select (SAF
only)
only)
only)
GND =
expanded
pitch
GND =
Terrain
Pop-Up
See note B
FCS/
EGPWS
See note W
ILS/VOR
GND=EFIS,
OPEN =
EHSI only
EHSI only configuration
True/Mag
select (SAF
only)
FCS
ADI pitch
scale
Page 309
9976-0041
Rev F
EFIS 5XX
SIGNAL
NAME
PIN
J18
DGND15
J110 DGND16
J137 DGND17
J112 DGND18
J114 DGND19
J117 DGND20
J119 DGND21
J165
J167
J35
J37
J39
PILOT
ADI
PILOT
HSI
HDG
HDG
HDG
HDG
FCS
VS
VS
VS
VS
FCS
CO-PILOT CO-PILOT
ADI
HSI
Reserved
Reserved
Reserved
Reserved
GA
GND =
Slave,
Open
=Free
GA
GND =
Slave,
Open
=Free
GA
GND =
Slave,
Open
=Free
GA
GND =
Slave,
Open
=Free
GND =
HDG Valid
Open =
DME Hold
GND =
HDG Valid
Open =
DME Hold
OPEN=ATT
/ ATT 1,
GND=ATT2
OPN=HDG
or HDG1,
GND=HDG
2
GND =
HDG Valid
Open =
DME Hold
OPEN =
ATT 2,
GND = ATT
1
OPN =
HDG2,
GND =
HDG1
GND =
HDG Valid
Open =
DME Hold
OPEN=ATT
2,
GND=ATT
1
OPN =
HDG2,
GND =
HDG1
DGND23
OPEN=ATT
/ ATT 1,
GND=ATT2
OPN=HDG
or HDG1,
GND=HDG
2
DGND24
IAS
IAS
IAS
DGND25
ILS ARM
ILS ARM
DGND26
GS CAP
DGND27
PILOT
ADI
PILOT
HSI
CO-PILOT CO-PILOT
ADI
HSI
FCS
FCS
TURB
GND =
Doppler
mode
enable
TURB
GND =
Doppler
mode
enable
FCS
FCS
/
DOPPLER
See note X
FCS
Heading
Gyro
Note Ref.
EFIS 520
USE
HDG Gyro
GND =
GND =
GND =
GND =
HDG / HDG HDG / HDG HDG / HDG HDG / HDG
2 Valid
1 Valid
1 Valid
2 Valid
HDG Gyro
See note K
DME
DME
Switch
Att Select
See note D
Switch
Hdg Select
See note D
IAS
FCS
FCS
ILS ARM
ILS ARM
FCS
FCS
GS CAP
GS CAP
GS CAP
FCS
FCS
NAV ARM
NAV ARM
NAV ARM
NAV ARM
FCS
FCS
DGND28
NAV CAP
NAV CAP
NAV CAP
NAV CAP
FCS
FCS
DGND29
BC ARM
BC ARM
BC ARM
BC ARM
FCS
FCS
DGND30
BC CAP
BC CAP
BC CAP
BC CAP
FCS
FCS
FCS
FCS
FCS
Signal
GND
Signal
GND
Signal
GND
Signal
GND
FCS
J144 DGND22
J121
J164
J163
J162
J161
J159
J171
J156
J318
J327
J139
J141
J356
J358
EFIS 520 ONLY
EFIS
500
USE
DGND31
VAPP ARM VAPP ARM VAPP ARM VAPP ARM
DGND32
VAPP CAP
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
DGND_COM
DGND_COM
DGND_COM
DGND_COM
DGNDOUT1
VAPP CAP
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
VAPP CAP
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
VAPP CAP
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
DGND
Signal Com
DGNDOUT2
N/C
Reserved
N/C
Reserved
RAD ALT 1 RAD ALT 2 RAD ALT 2 RAD ALT 1
Test
Test
Test
Test
Rad Alt
DGNDOUT3
TTL TO FD TTL TO FD TTL TO FD TTL TO FD
FCS
DGNDOUT4
DH ALERT DH ALERT DH ALERT DH ALERT
DME XFR DME XFR DME XFR DME XFR
=GND
=GND
=GND
=GND
Rad Alt
DME
Rev
DGNDOUT5
J311 DGNDOUT6
Reserved
Reserved
Reserved
Reserved
TA/RA
Display
Status =
OK
TA/RA
Display
Status =
OK
Sig Com
See note A
Sig Com
See note A
Sig Com
See note A
Sig Com
See note A
TCAS
Rad Alt
To FCS
To Panel
light
See note Y
See note Z
DME Switch See note AA
Display in
Comp
Mode
Display in
Comp
Mode
Display in
Comp
Mode
Display in
Comp
Mode
ADI/HSI
See note AB
Page 310
9976-0041
Rev F
EFIS 5XX
SIGNAL
NAME
PIN
J313 DGNDOUT7
J316 DGNDOUT8
J146 A429I1J122 A429I1+
J148 A429I2J124 A429I2+
J166 A429I3J126 A429I3+
J150 A429I4J128
J130
J12
J132
A429I4+
EFIS 520 ONLY
PILOT
ADI
PILOT
HSI
Reserved
Reserved
Reserved
Reserved
Nav Pulse
Reserved
for
AHRS B
HS
Reserved
for
AHRS A
HS
Nav Pulse
Reserved
for
AHRS B
HS
Reserved
for
AHRS A
HS
Nav Pulse
Reserved
for
AHRS B
HS
Reserved
for
AHRS A
HS
Nav Pulse
Reserved
for
AHRS B
HS
Reserved
for
AHRS A
HS
LNAV 1
ARINC 429
in B LS
LNAV 1
ARINC 429
input A LS
LNAV 2
ARINC 429
input B LS
LNAV 2
ARINC 429
input A LS
LNAV 1
ARINC 429
in B LS
LNAV 1
ARINC 429
input A LS
LNAV 2
ARINC 429
input B LS
LNAV 2
ARINC 429
input A LS
CO-PILOT CO-PILOT
ADI
HSI
LNAV 1
ARINC 429
in B LS
LNAV 1
ARINC 429
input A LS
LNAV 2
ARINC 429
input B LS
LNAV 2
ARINC 429
input A LS
LNAV 1
ARINC 429
input B LS
LNAV 1
ARINC 429
input A LS
LNAV 2
ARINC 429
input B LS
LNAV 2
ARINC 429
input A LS
EFIS
500
USE
AHRS/IRS/ AHRS/IRS/ AHRS/IRS/
INS 1A HS INS 1A HS INS 2A HS
A429
A429
A429
TCAS B HS
A429
TCAS A HS
A429
LNAV
FMS 1 B
LS A429
FMS 1 B
LS A429
FMS 2 B
LS A429
LNAV
FMS 1 A
LS A429
FMS 2 A
LS A429
LNAV
RAD ALT 1
B LS A429
FMS 1 A
LS A429
FMS 2 B
LS
A429/RA
FMS 2 A
LS
A429/RA
ADF 1 B LS
A429
ADF 1 A LS
A429
Wx B LS
A429
Wx A LS
A429
(RCP)
VOR 1 B
LS A429
VOR 1 A
LS A429
ADC or
ADC 1 B
LS A429
ADC or
ADC 1 A
LS A429
Wx /
EGPWS B
LS A429
(Range)
Wx /
EGPWS A
LS A429
(Range)
LNAV
Wx 429 B
LS
Wx 429 B
LS
Wx
Wx 429 A
LS
Wx 429 A
LS
Wx
J136 A429O1-
Wx 429 B
LS out
Wx 429 B
LS out
Wx
J134 A429O1+
Wx 429 A
LS out
LNAV 1
ARINC 429
B
LNAV 1
ARINC 429
A
LNAV 2
ARINC 429
B
LNAV 2
ARINC 429
A
Wx 429 A
LS out
LNAV 1
ARINC 429
B
LNAV 1
ARINC 429
A
LNAV 2
ARINC 429
B
LNAV 2
ARINC 429
A
J363 A429I8J361 A429I8+
J312 A429O2J310 A429O2+
J338 A429O3J336 A429O3+
LNAV 1
ARINC 429
B
LNAV 1
ARINC 429
A
LNAV 2
ARINC 429
B
LNAV 2
ARINC 429
A
LNAV 1
ARINC 429
B
LNAV 1
ARINC 429
A
LNAV 2
ARINC 429
B
LNAV 2
ARINC 429
A
CO-PILOT CO-PILOT
ADI
HSI
AHRS/IRS/ AHRS/IRS/ AHRS/IRS/ AHRS/IRS/
INS 1B HS INS 1B HS INS 2B HS INS 2B HS
A429
A429
A429
A429
A429I5+
J14
A429I6+
J342 A429I7J317 A429I7+
PILOT
HSI
FDC
A429I5-
A429I6-
PILOT
ADI
RAD ALT 1
A LS A429
ADF 2 B LS
A429
ADF 2 A LS
A429
DFCC B LS
A429
DFCC A LS
A429
VOR 2 B
LS A429
VOR 2 A
LS A429
ADC or
ADC 1 B
LS A429
ADC or
ADC 1 A
LS A429
Wx
RAD ALT 2
B LS A429
RAD ALT 2
A LS A429
ADF 1 B LS
A429
ADF 1 A LS
A429
DFCC B LS
A429
DFCC A LS
A429
VOR 1 B
LS A429
VOR 1 A
LS A429
ADC or
ADC 2 B
LS A429
ADC or
ADC 2 A
LS A429
AHRS/IRS/
INS 2A HS
A429
TCAS B HS
A429
TCAS A HS
A429
FMS 1 B
LS A429
Note Ref.
EFIS 520
USE
FCS
See note AC
AHRS
See note K &
P
AHRS
See note K &
P
TCAS
TCAS
FMS
See note K
FMS 1 A
LS A429
FMS
See note K
FMS 2 B
LS
A429/RA
FMS / RA
See note N
FMS 2 A
LS
A429/RA
FMS / RA
See note N
ADF 2 B LS
See note K &
A429
ADF/RCP
L
ADF 2 A LS
See note K &
A429
ADF/RCP
L
Wx B LS
A429
DFCC/ Wx See note M
Wx A LS
A429
(RCP)
DFCC/ Wx See note M
VOR 2 B
LS A429
VOR
See note K
VOR 2 A
LS A429
VOR
See note K
ADC or
ADC 2 B
LS A429
ADC
See note O
ADC or
ADC 2 A
LS A429
ADC
See note O
Wx /
EGPWS B
LS A429
(Range)
Wx/EGPWS See note M
Wx /
EGPWS A
LS A429
(Range)
Wx/EGPWS See note M
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
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
LNAV
FMS 2 B
LS A429
FMS 2 B
LS A429
FMS
See note K &
Q
LNAV
FMS 2 A
LS A429
FMS 2 A
LS A429
FMS
See note K &
Q
Page 311
9976-0041
Rev F
EFIS 5XX
PIN
J359
J357
J138
J111
J140
J158
J142
J160
J218
J219
J220
SIGNAL
NAME
PILOT
ADI
PILOT
HSI
EFIS 520 ONLY
CO-PILOT CO-PILOT
ADI
HSI
EFIS
500
USE
A429O4A429O4+
DME568_CLKDME568_CLK+
DME568_DATDME568_DAT+
DME568_SYNDME568_SYN+
DME568
CLKDME568
CLK+
DME568
BCDDME568
BCD+
DME568
SYNCDME568
SYNC+
DME568
CLKDME568
CLK+
DME568
BCDDME568
BCD+
DME568
SYNCDME568
SYNC+
DME568
CLKDME568
CLK+
DME568
BCDDME568
BCD+
DME568
SYNCDME568
SYNC+
DME568
CLKDME568
CLK+
DME568
BCDDME568
BCD+
DME568
SYNCDME568
SYNC+
PILOT
PILOT
CO-PILOT CO-PILOT
ADI
HSI
ADI
HSI
DFCC B LS DFCC B LS DFCC B LS DFCC B LS
A429
A429
A429
A429
DFCC A LS DFCC A LS DFCC A LS DFCC A LS
A429
A429
A429
A429
Note Ref.
EFIS 520
USE
DFCC
DFCC
DME
DME
DME
DME
DME
DME
See note AA
DME
DME
See note AA
DME
DME
DME
DME
Gyro (Pitch)
S1A
PITCH 1 X PITCH 2 X PITCH 2 X PITCH 1 X
Gyro
S1BD
PITCH 1 Z
PITCH 2 Z
PITCH 2 Z
PITCH 1 Z
Gyro
S1C
PITCH 1 Y
Pitch 1 Ref
- (+26 VAC
Com)
Pitch 1 Ref
+ (+26 VAC
Hi)
PITCH 2 Y
Pitch 2 Ref
- (+26 VAC
Com)
Pitch 2 Ref
+ (+26 VAC
Hi)
PITCH 2 Y
Pitch 2 Ref
- (+26 VAC
Com)
Pitch 2 Ref
+ (+26 VAC
Hi)
PITCH 1 Y
Pitch 1 Ref
- (+26 VAC
Com)
Pitch 1 Ref
+ (+26 VAC
Hi)
Gyro
See note K &
P
See note K &
Gyro (Pitch)
P
See note K &
Gyro (Pitch)
P
Gyro
Gyro (Pitch)
Gyro
Gyro (Pitch)
S2A
ROLL 1 X
ROLL 2 X
ROLL 2 X
ROLL 1 X
Gyro
Gyro (Roll)
S2BD
ROLL 1 Z
ROLL 2 Z
ROLL 2 Z
ROLL 1 Z
Gyro
Gyro (Roll)
ROLL 1 Y
Roll 1 Ref (+26 VAC
Com)
Roll 1 Ref +
(+26 VAC
Hi)
ROLL 2 Y
Roll 2 Ref (+26 VAC
Com)
Roll 2 Ref +
(+26 VAC
Hi)
ROLL 2 Y
Roll 2 Ref (+26 VAC
Com)
Roll 2 Ref +
(+26 VAC
Hi)
ROLL 1 Y
Roll 1 Ref (+26 VAC
Com)
Roll 1 Ref +
(+26 VAC
Hi)
Gyro
Gyro (Roll)
See note K &
V
See note K &
P
See note K &
P
See note K &
P
Gyro
Gyro (Roll)
See note K &
V
Gyro
S3A
HDG 2 X
HDG 1 X
HDG 1 X
HDG 2 X
Gyro
S3BD
HDG 2 Z
HDG 1 Z
HDG 1 Z
HDG 2 Z
Gyro
HDG 1 Y
HDG 1 Ref
- (+26 VAC
Com)
HDG 1 Ref
+ (+26 VAC
Hi)
HDG 1 Y
HDG 1 Ref
- (+26 VAC
Com)
HDG 1 Ref
+ (+26 VAC
Hi)
HDG 2 Y
HDG 2 Ref
- (+26 VAC
Com)
HDG 2 Ref
+ (+26 VAC
Hi)
Gyro
Gyro
Gyro (HDG)
See note K &
V
DEMOD3+
HDG 2 Y
HDG 2 Ref
- (+26 VAC
Com)
HDG 2 Ref
+ (+26 VAC
Hi)
See note K &
V
See note K &
Gyro (HDG)
P
See note K &
Gyro (HDG)
P
See note K &
Gyro (HDG)
P
Gyro
Gyro (HDG)
See note K &
V
S4A
VOR 2 SIN VOR 1 SIN VOR 1 SIN VOR 2 SIN
VOR
VOR / TCN
See note K
S4BD
VOR
VOR / TCN
See note K
S4C
VOR 2 RTN VOR 1 RTN VOR 1 RTN VOR 2 RTN
VOR 2
VOR 1
VOR 1
VOR 2
COS
COS
COS
COS
VOR / TCN
See note K
J276 DEMOD4-
VOR 2 Ref VOR 1 Ref VOR 1 Ref VOR 2 Ref
- (+26 VAC - (+26 VAC - (+26 VAC - (+26 VAC
Com)
Com)
Com)
Com)
VOR/TCN
See note K &
V
J267 DEMOD4+
J246 S5A
VOR 2 Ref VOR 1 Ref VOR 1 Ref VOR 2 Ref
+ (+26 VAC + (+26 VAC + (+26 VAC + (+26 VAC
Hi)
Hi)
Hi)
Hi)
ADF 2 /DF
ADF 2
X
ADF 1 X
ADF 1 X
/DFX
VOR/TCN
See note K &
V
ADF
See note K
J263 DEMOD1J262
J221
J222
J223
DEMOD1+
S2C
J265 DEMOD2J264
J224
J225
J226
DEMOD2+
S3C
J251 DEMOD3J266
J249
J248
J247
VOR
VOR
VOR
See note K &
V
Gyro (Roll)
VOR 2 /
VOR 2 /
VOR 2 /
VOR 2 /
TCN SIN
TCN SIN
TCN SIN
TCN SIN
VOR 2 /
VOR 2 /
VOR 2 /
VOR 2 /
TCN RTN TCN RTN TCN RTN TCN RTN
VOR 2 /
VOR 2 /
VOR 2 /
VOR 2 /
TCN COS TCN COS TCN COS TCN COS
VOR2/TCN VOR1/TCN VOR1/TCN VOR2/TCN
Ref
Ref
Ref
Ref
(26VAC
(26VAC
(26VAC
(26VAC
Com)
Com)
Com)
Com)
VOR2/TCN VOR1/TCN VOR1/TCN VOR2/TCN
Ref +
Ref +
Ref +
Ref +
(+26 VAC (+26 VAC (+26 VAC (+26 VAC
Hi)
Hi)
Hi)
Hi)
ADF
Page 312
9976-0041
Rev F
EFIS 5XX
PIN
J245 S5BD
J244 S5C
SIGNAL
NAME
J274 DEMOD5J275
J260
J243
J261
J279
J277
J217
J228
J253
J250
J242
J229
J278
J230
J241
J22
J273
J232
J259
J231
J268
J254
J36
J334
J38
DEMOD5+
PILOT
PILOT
ADI
HSI
ADF 2 /DF
Z
ADF 1 Z
ADF 2 /DF
Y
ADF 1 Y
ADF 2 Ref - ADF 1 Ref (+26 VAC (+26 VAC
Com)
Com)
ADF 2 Ref ADF 1 Ref
+ (+26
+ (+26
VAC Hi)
VAC Hi)
EFIS 520 ONLY
CO-PILOT CO-PILOT
ADI
HSI
ADF 2 /DF
ADF 1 Z
Z
ADF 2 /DF
ADF 1 Y
Y
ADF 1 Ref - ADF 2 Ref (+26 VAC (+26 VAC
Com)
Com)
ADF 1 Ref ADF 2 Ref
+ (+26
+ (+26
VAC Hi)
VAC Hi)
S6A
N/C
N/C
N/C
N/C
S6BD
N/C
N/C
N/C
N/C
S6C
N/C
N/C
N/C
N/C
DEMOD6-
Reserved
Reserved
Reserved
Reserved
DEMOD6+
Reserved
Reserved
Reserved
Reserved
RESOUT1_H
Reserved
Reserved
Reserved
Reserved
RESOUT1_JP
Reserved
Reserved
Reserved
Reserved
RESOUT1_JS
N/C
N/C
N/C
N/C
RESOUT1_L
Reserved
Reserved
Reserved
Reserved
RESOUT2_H
Reserved
Reserved
Reserved
Reserved
RESOUT2_JP
Reserved
Reserved
Reserved
Reserved
RESOUT2_JS
Reserved
Reserved
Reserved
Reserved
Reserved
HDG
ERROR Hi
JUMP TO
J2-73
JUMP TO
J2-2
HDG
ERROR Lo
CRS
DATUM Hi
JUMP TO
J2-68
JUMP TO
J2-31
CRS
DATUM Lo
Reserved
HDG
ERROR Hi
JUMP TO
J2-73
JUMP TO
J2-2
HDG
ERROR Lo
CRS
DATUM Hi
JUMP TO
J2-68
JUMP TO
J2-31
CRS
DATUM Lo
Reserved
HDG
ERROR Hi
JUMP TO
J2-73
JUMP TO
J2-2
HDG
ERROR Lo
CRS
DATUM Hi
JUMP TO
J2-68
JUMP TO
J2-31
CRS
DATUM Lo
Reserved
HDG
ERROR Hi
JUMP TO
J2-73
JUMP TO
J2-2
HDG
ERROR Lo
CRS
DATUM Hi
JUMP TO
J2-68
JUMP TO
J2-31
CRS
DATUM Lo
30HZ_INPUT_H
Reserved
Reserved
Reserved
Reserved
30HZ_RTN_C
Reserved
Reserved
Reserved
Reserved
RESOUT2_L
RESOUT3_H
RESOUT3_JP
RESOUT3_JS
RESOUT3_L
RESOUT4_H
RESOUT4_JP
RESOUT4_JS
RESOUT4_L
30HZ_STRAP1
J227 DC_OUT 1 +
J21
DC_OUT 2 +
J23
DC_OUT 3 +
Reserved
Reserved
Reserved
Reserved
Lateral
Lateral
Lateral
Lateral
Deviation 1 Deviation 1 Deviation 2 Deviation 2
Hi
Hi
Hi
Hi
Vertical
Vertical
Vertical
Vertical
Deviation 1 Deviation 1 Deviation 2 Deviation 2
Hi
Hi
Hi
Hi
Reserved
Reserved
Reserved
EFIS
500
USE
PILOT
ADI
PILOT
HSI
CO-PILOT CO-PILOT
ADI
HSI
Note Ref.
EFIS 520
USE
ADF
ADF
See note K
ADF
ADF
See note K
ADF
ADF
See note K &
V
ADF
ADF
See note K &
V
FCS
FCS
See note AE
Jumper
Jumper
Jumper
Jumper
FCS
FCS
See note AE
FCS
FCS
See note AE
Jumper
Jumper
Jumper
Jumper
FCS
FCS
See note AE
FCS
FCS
See note K &
AH
FCS
FCS
See note K &
AH
Reserved
Page 313
9976-0041
Rev F
EFIS 5XX
SIGNAL
NAME
PIN
J252 DC_OUT 4 +
J369 DC34_STRAP3
J234 VDCC1J233 VDCC1+
J236 VDCC2J235
J238
J237
J212
J239
J25
J24
VDCC2+
VDCC3VDCC3+
VDCC4VDCC4+
VDCV1VDCV1+
EFIS 520 ONLY
CO-PILOT CO-PILOT
ADI
HSI
EFIS
500
USE
PILOT
ADI
PILOT
HSI
Reserved
Reserved
Reserved
Reserved
Reserved
FD Pitch
Command FD Pitch
Command
+
FD Roll
Command FD Roll
Command
+
VOR/LOC
DEV 2VOR/LOC
DEV 2+
Reserved
FD Pitch
Command FD Pitch
Command
+
FD Roll
Command FD Roll
Command
+
VOR/LOC
DEV 1VOR/LOC
DEV 1+
Reserved
FD Pitch
Command FD Pitch
Command
+
FD Roll
Command FD Roll
Command
+
VOR/LOC
DEV 1VOR/LOC
DEV 1+
Reserved
FD Pitch
Command FD Pitch
Command
+
FD Roll
Command FD Roll
Command
+
VOR/LOC
DEV 2VOR/LOC
DEV 2+
GS DEV 2 GS DEV 2
+
RAD ALT 1
Signal RAD ALT 1
Signal +
GS DEV 1 GS DEV 1
+
RAD ALT 2
Signal RAD ALT 2
Signal +
GS DEV 1 GS DEV 1
+
RAD ALT 2
Signal RAD ALT 2
Signal +
GS DEV 2 - VOR
GS DEV 2
+
VOR
RAD ALT 1
Signal Rad Alt
RAD ALT 1
Signal +
Rad Alt
FCS
VOR
VOR/ILS
See note K
VOR
VOR/ILS
See note K
VOR/ILS
See note K
VOR/ILS
See note K
Rad Alt
See note K
Rad Alt
Gyro
/
DOPPLER
Gyro
/
DOPPLER
FS
/
DOPPLER
FS
/
DOPPLER
See note K
DOPPLER
Turn Rate
XTurn Rate
Signal VELOCITY
Signal DOPPLER
X+
Turn Rate
Turn Rate
Signal + VELOCITY Signal +
DOPPLER
YFast / Slow
Fast / Slow
VELOCITY
Signal Signal DOPPLER
Fast / Slow
Y+
Fast / Slow
Signal + VELOCITY Signal +
J28
VDCV3+
J258 VDC5+
J256 VDC6J255 VDC6+
J270 VDC7J269 VDC7+
J272 VDC8J271 VDC8+
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
+5 VDC
INPUT (IM)
+5 VDC
INPUT (IM)
+
+5 VDC
INPUT
(MM) +5 VDC
INPUT
(MM) +
+5 VDC
INPUT
(OM) +5 VDC
INPUT
(OM) +
FD
COLLECTIVE FD
COLLECTIVE +
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
+5 VDC
INPUT (IM)
+5 VDC
INPUT (IM)
+
+5 VDC
INPUT
(MM) +5 VDC
INPUT
(MM) +
+5 VDC
INPUT
(OM) +5 VDC
INPUT
(OM) +
FD
COLLECTIVE FD
COLLECTIVE +
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
+5 VDC
INPUT (IM)
+5 VDC
INPUT (IM)
+
+5 VDC
INPUT
(MM) +5 VDC
INPUT
(MM) +
+5 VDC
INPUT
(OM) +5 VDC
INPUT
(OM) +
FD
COLLECTIVE FD
COLLECTIVE +
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
>1.4 V =
FD Valid,
<1.4 V =
FD Invalid
+5 VDC
INPUT (IM)
+5 VDC
INPUT (IM)
+
+5 VDC
INPUT
(MM) +5 VDC
INPUT
(MM) +
+5 VDC
INPUT
(OM) +5 VDC
INPUT
(OM) +
FD
COLLECTIVE FD
COLLECTIVE +
Note Ref.
EFIS 520
USE
FCS
J29
VDCV3-
J257 VDC5-
CO-PILOT CO-PILOT
ADI
HSI
FCS
J26
VDCV2+
J210 VDCV4+
PILOT
HSI
FCS
J27
VDCV2-
J211 VDCV4-
PILOT
ADI
DOPPLER
XVELOCITY
DOPPLER
X+
VELOCITY
DOPPLER
YVELOCITY
DOPPLER
Y+
VELOCITY
FDC
FDC
FDC
FDC
MB
MB
MB
MB
MB
MB
MB
MB
MB
MB
MB
MB
FDC
FDC
FDC
FDC
See note AG
See note AG
See note AG
See note AG
Page 314
9976-0041
Rev F
EFIS 5XX
PIN
J240
J145
J120
J375
J373
J379
J377
J32
J33
J331
J31
J371
J34
J332
J353
J354
J349
J350
J351
J367
J352
J214
J328
J330
J365
J340
SIGNAL
NAME
SIGNALGND
PILOT
ADI
PILOT
HSI
Signal Gnd Signal Gnd
EFIS 520 ONLY
CO-PILOT CO-PILOT
ADI
HSI
Signal Gnd Signal Gnd
EFIS
500
USE
Signal
GND
PILOT
ADI
PILOT
HSI
CO-PILOT CO-PILOT
ADI
HSI
EFIS 520
USE
Tie to AC
GND
Note Ref.
WX453-
N/C
WX453-
N/C
WX453-
Wx
WX/EGPWS See note AF
WX453+
N/C
WX453+
N/C
WX453+
Wx
WX/EGPWS See note AF
AIORS232_RX
Reserved
Reserved
Reserved
Reserved
AIORS232_TX
Reserved
Reserved
Reserved
Reserved
DIORS232_RX
Reserved
Reserved
Reserved
Reserved
DIORS232_TX
Reserved
Reserved
Reserved
Reserved
RS232/422_GND
Reserved
Reserved
Reserved
Reserved
RS232/422_RX_HI
Reserved
Reserved
Reserved
Reserved
RS232/422_RX_LO
Reserved
Reserved
Reserved
Reserved
RS232/422_TX_HI
Reserved
Reserved
Reserved
Reserved
AC12_STRAP2
Reserved
Reserved
Reserved
Reserved
AIO_SPARE01
Reserved
Reserved
Reserved
Reserved
AIO_SPARE02
Reserved
Reserved
Reserved
Reserved
AIO_SPARE03
Reserved
Reserved
Reserved
Reserved
AIO_SPARE04
Reserved
Reserved
Reserved
Reserved
AIO_SPARE05
Reserved
Reserved
Reserved
Reserved
AIO_SPARE06
Reserved
Reserved
Reserved
Reserved
AIO_SPARE07
Reserved
Reserved
Reserved
Reserved
AIO_SPARE08
Reserved
Reserved
Reserved
Reserved
AIO_SPARE09
Reserved
Reserved
Reserved
Reserved
AIO_SPARE10
Reserved
Reserved
Reserved
Reserved
UIC_SPARE1
Reserved
Reserved
Reserved
Reserved
UIC_SPARE2
Reserved
Reserved
Reserved
Reserved
UIC_SPARE3
Reserved
Reserved
Reserved
Reserved
UIC_SPARE4
Reserved
Reserved
Reserved
Reserved
Data
Load
Data
Load
Data
Load
Data Load
See note T
Data Load
See note T
Data Load
See note T
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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Copilot
Pilot
Heading 1
Heading 2
RADALT 2
RADALT 1
LNV 2
LNV 1
Attitude 2
Attitude 1
M-net
DME
DME
D. ADF 2
D. ADF 1
VOR 2
VOR 1
D. VOR 1
ADF
EADI
2
EADI
1
HDG ERR
CRS
DATUM
Lat Dev
Vert Dev
Flags, TTL
D. RADALT 1
D. RADALT 2
AHRS 1
HDG ERR
CRS
DATUM
Lat Dev
Vert Dev
Flags, TTL
D. VOR 2
DF
D. RADALT 1
D. RADALT 2
AHRS 1
AHRS 2
AHRS 2
Airdata 1
Airdata 1
Airdata 2
Airdata 2
FDC
AHRS 1
AHRS 1
AHRS 2
AHRS 2
Airdata 1
Airdata 1
HDG ERR
CRS
DATUM
Lat Dev
Vert Dev
Flags, TTL
Airdata 2
WX CP
D. RADALT 2
Heading 2
RADALT 1
LNV 1
HDG ERR
CRS
DATUM
Lat Dev
Vert Dev
Flags, TTL
EHSI
2
Airdata 2
WX CP
D. RADALT 1
Heading 1
EHSI
1
RADALT 2
LNV 1
LNV 2
LNV 2
DME
DME
D. ADF 2
M-net
D. ADF 1
VOR 2
VOR 1
D. VOR 2
D. VOR 1
DF
ADF
TCAS
TCAS
ARINC 453
TAWS
ARINC 429
ARINC 453
ARINC 429
D. = digital (ARINC 429)
ARINC 453
ARINC 429
WX R/T
ARINC 453
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 1
ADI
J1-21
J1-50
J1-2
J1-30
LNV1 A
LNV1 B
LNV2 A
LNV2 B
J3-10
J3-12
J3-36
J3-38
LNAV1 CNTL A
LNAV1 CNTL B
LNAV2 CNTL A
LNAV2 CNTL B
EFIS IN
COMMAND
RELAY
+28 VDC
EFIS IN COMMAND
TO COPILOT LNAV REVERSIONARY RELAY
REV. RELAY
+28 VDC
HSI VALID
HSI
J3-10
J3-12
J3-36
J3-38
LNV1 CNTL A
LNV1 CNTL B
LNV2 CNTL A
LNV2 CNTL B
EFIS IN
COMMAND
RELAY
LNAV 2
+28 VDC
EFIS IN COMMAND
J1-21
J1-50
J1-2
J1-30
LNAV1
LNAV1
LNAV2
LNAV2
A
B
A
B
TO COPILOT LNAV REVERSIONARY 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 / HEADING
INTERFACE
ADI 2
Pitch 2X
J2-18
Pitch 2Z
J2-19
Pitch 2Y
J2-20
Roll 2X
J2-21
Roll 2Z
J2-22
Roll 2Y
J2-23
HDG 1X
J2-24
HDG 1Z
J2-25
HDG 1Y
J2-26
J1-51 ATT 2 Valid
J1-17 HDG1 Valid
Pitch 1X
Pitch 1Z
Pitch 1Y
Roll 1X
Roll 1Z
Roll 1Y
HDG 2X
HDG 2Z
HDG 2Y
ATT1
GYRO
Att 1 Valid
J2-18
J2-19
J2-20
J2-21
J2-22
J2-23
J2-24
J2-25
J2-26
J1-51
J1-17
ADI 1
ATT REV
ATT REV
DIR
GYRO
1
HDG2 Valid
DIR
GYRO
2
HSI 2
J1-51
J2-18
J2-19
J2-20
J2-21
J2-22
J2-23
J2-24
J2-25
J2-26
J1-17
Pitch 1X
Pitch 1Z
Pitch 1Y
Roll 1X
Roll 1Z
Roll 1Y
HDG 2X
HDG 2Z
HDG 2Y
HDG 2 Valid
ATT 2
GYRO
Pitch 2X
Pitch 2Z
Pitch 2Y
Roll 2X
Roll 2Z
Roll 2Y
HDG 1X
HDG 1Z
HDG 1Y
ATT 2 Valid
HDG 1 Valid
J2-18
J2-19
J2-20
J2-21
J2-22
J2-23
J2-24
J2-25
J2-26
J1-51
J1-17
HSI 1
On all units
J2-62, J2-64, J2-66
+26 VAC
J2-63, J2-65, J2-51
+26 VAC Com
Figure 28—Attitude/Heading Interface Block Diagram
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ADF / RADIO ALT INTERFACE
ADI
HSI
J2-46
J2-45
J2-44
J1-76
ADF2 X
ADF2 Z
ADF2 Y
ADF Valid
J1-67
J3-07
J2-04
J2-05
J1-74
J3-23
RAD ALT TEST
DH OUT
RAD ALT+
RAD ALTRAD ALT Valid
DH IN
J2-75
J2-74
J2-67
J2-76
ADF2 REF+
ADF2 REFVOR2 REF+
VOR2 REF-
J2-75
J2-74
J2-67
J2-76
ADF1 REF+
ADF1 REFVOR1 REF+
VOR1 REF-
J1-67
J3-07
J2-04
J2-05
J1-74
J3-23
RAD ALT TEST
DH OUT
RAD ALT+
RAD ALTRAD ALT Valid
DH IN
J2-46
J2-45
J2-44
J1-76
ADF1 X
ADF1 Z
ADF1 Y
ADF Valid
ADF2/DF
RAD ALT 1
26VAC 400HZ
26VAC COM
26VAC 400HZ
26VAC COM
RAD ALT 2
ADF1
Figure 29—ADF/Radio ALT Interface Block Diagram
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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
DGND03
PILOT
PILOT
COPILOT
COPILOT
ADI
HSI
ADI
HSI
GND = ATT1 & ATT2 GND = ATT1 & ATT2 GND = ATT1 & ATT2 GND = ATT1 & ATT2
J3-78
OPEN = ATT
OPEN = ATT
OPEN = ATT
OPEN = ATT
GND = HDG1&HDG2 GND = HDG1&HDG2 GND = HDG1&HDG2 GND = HDG1&HDG2
J3-76
OPEN = HDG
OPEN = HDG
OPEN = HDG
OPEN = HDG
GND = VOR1&VOR2 GND = VOR1&VOR2 GND = VOR1&VOR2 GND = VOR1&VOR2
J3-74
OPEN = VOR
OPEN = VOR
OPEN = VOR
OPEN = VOR
DGND04
J3-72
DGND05
J3-70
DGND06
J3-68
DGND07
J3-66
DGND08
J3-64
DGND09
J3-62
DGND10
J3-60
DGND11
J1-05
DGND01
DGND02
PIN
NO.
GND = ADF & DF
OPEN = ADF
GND =
LNAV1&LNAV2
OPEN = LNV
GND = LNAV
OPEN = NO LNV
GND = ADF & DF
OPEN = ADF
GND =
LNAV1&LNAV2
OPEN = LNV
GND = LNAV
OPEN = NO LNV
GND = ADF & DF
OPEN = ADF
GND =
LNAV1&LNAV2
OPEN = LNV
GND = LNAV
OPEN = NO LNV
GND = ADF & DF
OPEN = ADF
GND =
LNAV1&LNAV2
OPEN = LNV
GND = LNAV
OPEN = NO LNV
GND = DUAL EFIS
OPEN = SINGLE
GND = RA1 & RA2
OPEN = RA
GND = RA
OPEN = NO RA
GND = DUAL EFIS
OPEN = SINGLE
GND = RA1 & RA2
OPEN = RA
GND = RA
OPEN = NO RA
GND = DUAL EFIS
OPEN = SINGLE
GND = RA1 & RA2
OPEN = RA
GND = RA
OPEN = NO RA
GND = DUAL EFIS
OPEN = SINGLE
GND = RA1 & RA2
OPEN = RA
GND = RA
OPEN = NO RA
GND = FD Aval
OPEN = NO FD
GND = WX
OPEN = NO WX
GND = FD Aval
OPEN = NO FD
GND = WX
OPEN = NO WX
GND = FD Aval
OPEN = NO FD
GND = WX
OPEN = NO WX
GND = FD Aval
OPEN = NO FD
GND = WX
OPEN = NO WX
COMMENTS
Configure for one or
two attitude sources
two heading sources
two VOR sources
two ADF or DF
sources
two LNAV sources
Configure for some or
no LNAV sources
Configure for single
EFIS (2-panel) or
dual EFIS (4-panel)
two RA sources
Configure for some or
no RA sources
Configure for flight
director available or
no flight director
Configure for weather
or no weather radar
Table 17—EFIS 500 Configurable Settings
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SIGNAL
NAME
PIN
NO.
DGND22
J1-44
OPEN=ATT2 OPEN=ATT 2 OPEN=ATT2 OPEN=ATT2 Cockpit switch to select EFIS attitude
or ATT1
or ATT1
GND = ATT1 GND = ATT1 source. Switch must switch both on-side
GND = ATT2 GND = ATT2
ADI and HSI.
DGND23
J1-21
OPEN=HDG1 OPEN=HDG1 OPEN=HDG2 OPEN=HDG2 Cockpit switch to select EFIS heading
GND=HDG2 GND=HDG2 GND=HDG1 GND=HDG1 source. Switch must switch both on-side
ADI and HSI.
28VIN10
J3-44
+28VDC=RA +28VDC=RA +28VDC=RA +28VDC=RA Cockpit switch to select EFIS RA source.
1
1
1
1
Switch must switch both on-side ADI and
OPEN = RA 2 OPEN = RA 2 OPEN = RA 2 OPEN = RA 2 HSI.
DGND03
J3-74
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
DGND17
J1-37
28VIN08
J1-68
28VIN14
J3-24
PILOT ADI
OPN =
onside ADC
GND =
offside ADC
Mag/True
Heading
PILOT HSI
OPN =
onside ADC
GND =
offside ADC
Mag/True
Heading
COPILOT
ADI
OPN =
onside ADC
GND =
offside ADC
Mag/True
Heading
Activate
Doppler
EFIS in
command
EFIS in
command
Terrain select
EFIS in
command
COPILOT
HSI
COMMENTS
OPN =
Cockpit switch to select airdata source.
onside ADC Switch must switch both onside ADI and
GND =
HSI (520 only).
offside ADC
Mag/True
Heading
Applies to digital heading (SAF only).
Activate
Doppler
Enable Doppler symbols when the full
map page is active (SAR only).
EFIS in
command
28V = this side in command, 0V this side
not in command.
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
DGND01
DGND02
PIN
No.
PILOT
ADI
PILOT
HSI
CO-PILOT
ADI
CO-PILOT
HSI
J3-78
GND = ATT1 &
ATT2
OPEN = ATT
GND = ATT1 &
ATT2
OPEN = ATT
GND = ATT1 &
ATT2
OPEN = ATT
GND = ATT1 &
ATT2
OPEN = ATT
J3-76
GND =
HDG1&HDG2
OPEN = HDG
GND =
HDG1&HDG2
OPEN = HDG
GND =
HDG1&HDG2
OPEN = HDG
GND =
HDG1&HDG2
OPEN = HDG
GND = ROTOR
OPEN = FIXED
WING
GND = A429 AHRS
OPEN =
SYNCHRO
GND = ROTOR
OPEN = FIXED
WING
GND = A429 AHRS
OPEN =
SYNCHRO
GND = ROTOR
OPEN = FIXED
WING
GND = A429 AHRS
OPEN =
SYNCHRO
GND = ROTOR
OPEN = FIXED
WING
GND = A429 AHRS
OPEN =
SYNCHRO
GND = DUAL EFIS
OPEN = SINGLE
GND =
EXPANDED
OPEN = NORMAL
GND= EFIS
OPEN = EHSI
ONLY
GND = DUAL EFIS
OPEN = SINGLE
GND =
EXPANDED
OPEN = NORMAL
GND = DUAL EFIS
OPEN = SINGLE
GND =
EXPANDED
OPEN = NORMAL
GND= EFIS
OPEN = EHSI
ONLY
DGND04
J3-72
DGND05
J3-70
DGND07
J3-66
DGND10
J3-60
GND = DUAL EFIS
OPEN = SINGLE
GND =
EXPANDED
OPEN = NORMAL
DGND13
J1-70
RESERVED
RESERVED
COMMENTS
Configure for
one or two
attitude sources
Configure for
one or two
heading
sources
Configure for
rotor or fixed
wing
AHRS or
VG/DG inputs
Configure for
single EFIS
(2-panel) or
dual EFIS
(4-panel)
EXPANDED
ADI PITCH
SCALE
---
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.
B.
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.
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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(2)
(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.
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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•
•
•
•
•
•
•
•
(3)
EFIS 520 TCAS I or TCAS II Configuration
•
•
•
•
(4)
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 (nonbeacon 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)
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.
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:
A.
Installation checkout is performed using the EFIS 520 maintenance mode
diagnostic pages the while the aircraft is on the ground only.
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)
B.
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.
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
Secondary
Action
Command
Command
AIO
Display AIO status.
DIO
Display DIO status.
SHO
ARINC429
Display ARINC status.
FAIL
Display unit failure history.
CLEARFAIL
Clears unit failure history.
CONFIG
Display current unit configuration
n/a
DNLD
Download new EFIS operating software.
?
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:
B.
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.
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
3.
(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,
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
Page 702

NEOAV 500 ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS

Transcription

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