Pilot’s Guide EFS 40/50 - BendixKing

EFS 40/50Pilot’s Guide

Bendix/King® 4-inch/5-inchElectronic Flight

Instrumentation System

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Registration

This pilot's guide has been tailored by the installation and or certifica-tion agency to cover the following EFS 40/50 installation:

AIRCRAFT TYPE

AIRCRAFT TAIL OR SERIAL NUMBER

AIRCRAFT OWNER

EFIS TYPE (EFS 40 or EFS 50)

EFIS SYSTEM CONFIGURATION

EFIS SYSTEM SOFTWARE LEVEL

EFIS DISPLAY UNIT TYPE

EFIS CONTROL PANELS

REVERSIONARY MODES

Throughout this pilot's guide various configuration options aredescribed. A 4o (check box) precedes each configuration option. Acheck mark may be placed in the appropriate boxes to define whichconfiguration options are available in a given installation.

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Registration

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Table of Contents

TABLE OF CONTENTS

Section I

INTRODUCTION I.1

Section 1

SYSTEM CONFIGURATION 1.1GENERAL 1.1CONTROL PANEL 1.2SYMBOL GENERATOR 1.3EQUIPMENT INTERFACE & OPERATING CONFIGURATION 1.5SOFTWARE 04 CONFIGURATION PAGES 1.6SOFTWARE 05 CONFIGURATION PAGES 1.9SOFTWARE 06 CONFIGURATION PAGES 1.12SOFTWARE 07 CONFIGURATION PAGES 1.15(includes both 0701 and 0702) SOFTWARE 08 CONFIGURATION PAGES 1.18SOFTWARE 09 CONFIGURATION PAGES 1.21SOFTWARE 10 CONFIGURATION PAGES 1.25SOFTWARE 11 CONFIGURATION PAGES 1.29SOFTWARE 12 CONFIGURATION PAGES 1.33SOFTWARE 13 CONFIGURATION PAGES 1.37SOFTWARE 14 CONFIGURATION PAGES 1.41SOFTWARE 15 CONFIGURATION PAGES 1.45SOFTWARE 16 CONFIGURATION PAGES 1.48

Section 2

EHSI OPERATION 2.1.1DETAILED OPERATING CONTROLS 2.1.1EHSI CONTROLS (ED 461 & CP 467/468) 2.1.1

1-2 NAVIGATION SYSTEM SELECT 2.1.3NAV NAVIGATION SENSOR SELECT 2.1.3HSI 360° MODE SELECTION 2.1.5BEARING POINTER SELECT 2.1.6ARC SECTORED MODE SELECTION 2.1.7RANGE SELECTION 2.1.8TST/REF 2.1.8

TST— 2.1.8REF GROUND SPEED or TIME-TO-STATION selection 2.1.8REF MAP FORMAT 2.1.9

COURSE SELECT KNOB 2.1.10HEADING SELECT KNOB 2.1.10DISPLAY BRIGHTNESS CONTROL 2.1.10

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EADI OPERATION 2.2.1EADI DETAILED OPERATING CONTROLS 2.2.1

BRIGHTNESS 2.2.2DH SET 2.2.2RALT TST 2.2.2

RADAR OPERATION 2.3.1RADAR CONTROLS, (CP 466A & CP 466B) 2.3.1

OFF-STBY-TST-ON 2.3.2OFF 2.3.2STBY 2.3.2TST 2.3.2ON 2.3.2

WX 2.3.2WXA 2.3.2GND MAP 2.3.2LIGHTNING 2.3.3VP 2.3.3TRK 2.3.4GAIN 2.3.5PULL ARL 2.3.5TILT 2.3.5

MFD OPERATION 2.4.1MULTI FUNCTION DISPLAY CONTROL PANEL 2.4.1CONTROL PANEL BUTTON OPERATIONS 2.4.2

COURSE SELECT KNOB/BUTTON 2.4.2HSI BUTTON 2.4.2ARC BUTTON 2.4.2NAV BUTTON 2.4.21-2 BUTTON 2.4.3BEARING #1 & #2 BUTTON 2.4.3RANGE UP/DOWN BUTTON 2.4.3JOYSTICK 2.4.3

WAYPOINT ENTRY OPERATION 2.4.3PLAN VIEW OPERATION (available with 07 and higher) 2.4.4CHECKLIST OPERATION(available with 08 and higher) 2.4.5

ENT BUTTON 2.4.5WAYPOINT ENTRY OPERATION 2.4.5PLAN VIEW OPERATION(available with 07 and higher) 2.4.5CHECKLIST OPERATION(available with 08 and higher) 2.4.6

TEST/REFERENCE 2.4.6CHECKLIST SELECT (available with 08 and higher) 2.4.6TCAS ONLY SELECT (available with 08 and higher) 2.4.6

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Table of Contents

Section 3

ABBREVIATED OPERATIONS 3.1

Section 4

EHSI DISPLAYS 4.1.1EFS 40/50 COLOR STANDARDS 4.1.1STANDARD EHSI DISPLAYS 4.1.1

NORMAL COMPASS CARD 4.1.1NAVIGATION SOURCE ANNUNCIATION 4.1.2SYMBOLIC AIRCRAFT 4.1.3HEADING SELECT “BUG” 4.1.4COURSE SELECT 4.1.4LATERAL COURSE DEVIATION SCALE 4.1.5LATERAL COURSE DEVIATION BAR 4.1.6TO/FROM INDICATOR 4.1.6DISTANCE, GROUNDSPEED and TIME-TO-STATION 4.1.6DUAL MULTICHANNEL DME INSTALLATIONS 4.1.7DME HOLD 4.1.8BEARING POINTER 4.1.9MAGNETIC/TRUE HEADING ANNUNCIATIONS 4.1.11RADIO ALTITUDE 4.1.11GLIDE SLOPE/VERTICAL NAVIGATION 4.1.11WIND VECTOR 4.1.13DRIFT ANGLE POINTER ( LNAV only) 4.1.13LNAV MODE ANNUNCIATIONS 4.1.14

360 Map Displays 4.1.14MAP 360 COMPASS CARD 4.1.15SELECTED COURSE 4.1.15MAP COURSE DEVIATION INDICATOR 4.1.16TO/FROM 4.1.16BEARING POINTER 4.1.16REFERENCE WAYPOINT 4.1.16RANGE RING 4.1.17360-DEGREE MAP WX RADAR (IF EQUIPPED) 4.1.18RDR 1400 WEATHER RADAR 4.1.19LIGHTNING DETECTION 4.1.20FULL TIME LNAV MAP 4.1.21

ARC (Expanded Sectored Mode) Displays 4.1.22HDG BUG (ALL ARC FORMAT MODES) 4.1.22COURSE DEVIATION INDICATOR (EHSI ARC NON-MAP FORMAT) 4.1.22

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Table of Contents

Custom (Non-Standard EHSI) Displays 4.1.23DOPPLER 4.1.23

COMPASS CARD 4.1.23DOPPLER VELOCITY BARS 4.1.23VELOCITY AND TARGET SCALE 4.1.23LNAV GROUND SPEED AND READOUT 4.1.24WIND VECTOR INFORMATION 4.1.24TARGET WAYPOINT 4.1.24TENDENCY CIRCLE 4.1.24MEMORY 4.1.24HEADING BUG 4.1.24

CABLE 4.1.25COMPASS CARD 4.1.25ANGLE BARS 4.1.25FUNNEL SCALE 4.1.25WIND VECTOR INFORMATION 4.1.25OPTIMUM CABLE POSITION CIRCLE 4.1.26THRUST COMMAND 4.1.26HEADING BUG 4.1.26

HOMING 4.1.26LATERAL DEVIATION BAR 4.1.27

EADI DISPLAYS 4.2.1NORMAL ATTITUDE DISPLAY 4.2.1

PITCH ATTITUDE 4.2.1ROLL ATTITUDE 4.2.1ROLL INDICATOR 4.2.2

Sky Pointer Roll Scale 4.2.2Roll Indicator Scale 4.2.2

PERSPECTIVE LINES 4.2.2SYMBOLIC AIRCRAFT 4.2.2HEADING TAPE 4.2.3FLIGHT DIRECTOR COMMAND BARS 4.2.3AUTOPILOT/FLIGHT DIRECTOR MODE ANNUNCIATION 4.2.4

STANDARD 429 AUTOPILOT/FLIGHTDIRECTOR MODE ANNUNCIATION 4.2.4SFIM CDV AUTOPILOT/FLIGHT DIRECTOR MODE ANNUNCIATION 4.2.7

RADIO ALTIMETER 4.2.8DECISION HEIGHT SET 4.2.9DECISION HEIGHT ALERT 4.2.9PRECISION APPROACH MODE FORMAT 4.2.9EXPANDED LATERAL DEVIATION SCALE 4.2.9RISING RUNWAY 4.2.10GLIDESLOPE/VERTICAL NAVIGATION 4.2.11

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EADI OFF-SIDE ILS/MLS 4.2.11MARKER BEACON ANNUNCIATION 4.2.12FAST/SLOW OR COLLECTIVE DISPLAY 4.2.12MACH DISPLAY 4.2.13RATE OF TURN DISPLAY 4.2.13CATEGORY II ANNUNCIATOR 4.2.14

CATEGORY II OPERATION ANNUNCIATIONS 4.2.14DUAL EFS SYSTEM 4.2.14SINGLE EFS SYSTEM 4.2.15CATEGORY II THRESHOLDS 4.2.16

ATTITUDE MONITOR 4.2.17CROSS COMPARATOR ANNUNCIATORS 4.2.17

RA 4.2.17LOC 4.2.17GS 4.2.17ATT 4.2.17HDG 4.2.18

COMPOSITE DISPLAYS 4.3.1COMPOSITE MODE 4.3.1HEADING TAPE 4.3.1SELECTED COURSE 4.3.1HEADING BUG SELECT 4.3.1NAVIGATION SOURCE ANNUNCIATION 4.3.2LATERAL COURSE DEVIATION SCALE 4.3.2LATERAL COURSE DEVIATION BAR 4.3.2TO/FROM 4.3.3DISTANCE INFORMATION 4.3.3DME HOLD 4.3.3

MFD DISPLAYS 4.4.1CRS, NOT CRS SELECT 4.4.1WEATHER ONLY 4.4.1

TRACK LINE 4.4.1VERTICAL PROFILE (VP) 4.4.1

SYMBOLIC AIRCRAFT 4.4.1RANGE RINGS 4.4.2ALTITUDE LINE 4.4.2PROFILE ANGLE 4.4.2

PLAN VIEW NORTH-UP MAP 4.4.2CHECKLIST INTERFACE 4.4.3

LOADING AND MODIFYING CHECKLIST DATA 4.4.3CHECKLIST PAGE ORGANIZATION 4.4.4ROOT INDEX PAGE 4.4.4

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SUB INDEX PAGES 4.4.5CHECKLIST ITEM PAGES 4.4.5NOTE PAGES 4.4.6CLEARING CHECKLIST ITEMS 4.4.6EMERGENCY PAGE ACTIVATION 4.4.6CHECKLIST CONTROLS 4.4.7

Checklist: CHKLIST 4.4.7Joystick 4.4.7Enter : ENT 4.4.8HSI 4.4.9ARC 4.4.9NAV 4.4.9Up Arrow 4.4.9Down Arrow 4.4.91-2 4.4.9RMI 1 4.4.10RMI 2 4.4.10CRS (NOT) SEL 4.4.10TST REF 4.4.10CRS Knob 4.4.10

REMOTELY MOUNTED SWITCHES 4.4.10FAULT ANNUNCIATIONS 4.4.10TCAS INTERFACE 4.4.11

TCAS ONLY SELECTION 4.4.11TCAS DISPLAY FORMAT 4.4.12TCAS TRAFFIC SYMBOLOGY 4.4.12

Intruder Symbols 4.4.12Vertical Speed Arrow 4.4.12Data Tag 4.4.12Off-Scale Traffic 4.4.13

TCAS DISPLAY ANNUNCIATIONS 4.4.13Traffic 4.4.13TCAS 4.4.13TCAS Status 4.4.14TCAS Mode 4.4.14Range 4.4.15Above/Norm/Below 4.4.15No-Bearing Traffic 4.4.15FLXXX and FL 4.4.15

EGPWS INTERFACE 4.4.16EGPWS SELECTION 4.4.16EGPWS DISPLAY FORMAT 4.4.16EGPWS MODE/STATUS 4.4.16EGPWS RANGE 4.4.16

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Table of Contents

Section 5

OPERATING INSTRUCTIONS 5.1PREFLIGHT PROCEDURES 5.1

START UP 5.1SELF TEST 5.1PUSH BUTTON TEST 5.1

PRE-TAKEOFF PROCEDURES 5.2IN-FLIGHT OPERATION 5.2

ADF 5.2LNAV (RNAV) 5.3VNAV 5.3

APPROACH PROCEDURES 5.3ILS APPROACH 5.3BACK COURSE APPROACH 5.4ADF APPROACH 5.4LNAV (RNAV) APPROACH 5.4VNAV GPS PRECISION APPROACH 5.4VOR APPROACH 5.5DECISION HEIGHT SELECTION 5.5

LIMITATIONS 5.5EMERGENCY PROCEDURES 5.5

Section 6

FAULT ANNUNCIATIONS 6.1GENERAL 6.1

EXTERNAL SYSTEM FAILURES 6.1HEADING 6.1ATTITUDE 6.1FLIGHT DIRECTOR 6.1

EFS 40/50 SYSTEM FAILURES 6.1DU—DISPLAY UNIT LOSS OF COOLING 6.1SG—SYMBOL GENERATOR LOSS OF COOLING 6.1CP—CONTROL PANEL (CP 467, CP 468,ED 461 OR CP 470) 6.2HEADING SELECT “BUG” 6.2COURSE SELECT 6.2RCP—RADAR CONTROL PANEL (if equipped) 6.2SG—SYMBOL GENERATOR 6.2

RAW DATA DEVIATION ANNUNCIATIONS 6.3BEARING POINTER ANNUNCIATIONS 6.3ALPHANUMERIC READOUT ANNUNCIATIONS 6.3CHECK CONFIG 6.3

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WEATHER RADAR ANNUNCIATIONS 6.4WX FLT 6.4WX OFF 6.4BUSY VP 6.4RT FLT 6.4STB LMT 6.4TGTALRT 6.4TGT 6.4429 FLT 6.4ANT FLT 6.5TX FLT 6.5RANGE 6.5STB OFF 6.5WAIT 6.5

CUSTOM DISPLAY FAILURE ANNUNCIATIONS 6.5DOPPLER/CABLE 6.5

EXTERNAL SYSTEM FAILURES 6.5FMS Warning 6.5Autopilot Warning 6.5

TCAS FAULT MESSAGES 6.6Fault Messages for TCAS Fail 6.6Fault Messages for No TCAS 6.6

LIGHTNING DETECTION DISPLAY FAULT MESSAGES 6.6

Section 7

REVERSIONARY MODES 7.1CMPST - COMPOSITE 7.2COPY OFF-SIDE 7.3DISPLAY (EADI) DOWN 7.4STBY - STANDBY 7.5REVERSIONARY MODE SELECTION 7.6

THREE TUBE EFS 40/50 7.6FOUR TUBE EFS 40/50 7.7FIVE TUBE EFS 40 7.8FIVE TUBE EFS 50 7.9

Section 8

GLOSSARY 8.1ABBREVIATIONS 8.1

Section 9

INDEX 9.1

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Introduction

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INTRODUCTION

This pilot’s guide describes thecomponents, operation, andoperational procedures of theBENDIX/KING EFS 40/50 Elec-tronic Flight Instrumentation Sys-tem (EFIS) containing systemsoftware 04, 05, 06, 07, 08, 09,10, 11, 12, 13, 14, 15, and 16.The EFS 40 system uses either asingle control display unit, fourinch ED 461, or a separateC P 467 mode controller and fourinch ED 462 display unit for con-trol and display of navigation dataand sensor selection. When aMulti-Function Display is incorpo-rated in the system, theC P 469/A will control and selectnavigation data for display on theMFD. A CP 466A or CP 4 6 6 B

provides the radar control func-tion when an RDS 81/82/84 or 86weather radar is interfaced withthe system, and the associatedradar control/display unit is noti n s t a l l e d .The EFS 50 system uses aremote CP 467 mode controllerand an ED 551/A display unit forcontrol and display of navigationdata and sensor selection. Theremote SYMBOL GENERATOR,S G 464 or SG 465, interfaceswith the navigation sensors tocompute the display and EFISoutput data required by othersystems on board the aircraft.The SG 464 is no longer avail-able and has not been producedwith software versions 08 or later.

An Abbreviated Operationssection included in this manualcovers the functions of the EFS

40/50 in minimal detail. TheAbbreviated Operations sectiongives a brief visual overview of

Equipment covered in this pilot's guide includes:E D 4 6 1 Control display unit, 4" X 4"E D 462 Display unit, 4" X 4"S G 4 6 4 EHSI/MFD-only symbol generator

(not available with software 08 or later)S G 4 6 5 EFIS symbol generator C P 4 6 6 A R D S 81/82/84 radar control panelC P 4 6 6 B R D S 86 radar control panelC P 4 6 7 EFIS control panel with DH set and testC P 4 6 8 EFIS control panel, less DH set and testC P 4 6 9 MFD control panelC P 4 6 9 A MFD control panel with Checklist,

TCAS and Joystick featuresC P 4 7 0 EADI brightness and DH set and test panelE D 5 5 1 Display unit, 5" X 5" (not available in current production)E D 5 5 1 A Display unit, 5" X 5" (~16% larger symbols

compared with ED 461/2 presentation)

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Introduction

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features and push button opera-tions. However, it is necessary toread the entire Pilot’s Guide for aful l understanding of theE F S 40/50 system.

N o t e : The EFS 40/50 displayillustrations used in this pilot'sguide are artist's reproduc -tions. Extreme care has beentaken to ensure the accuracyof symbology placement andrelative size. However, it isimpossible to exactly duplicatethe display of a CRT and com -pensate for all brightness lev -els, as line width displayed onthe CRT varies with bright -ness. In many cases, unrealis -tic displays provide the mostinformative display possible ona single display. Therefore,we ask that you use and treatthe graphic illustrations con -tained in this pilot's guide asthey were intended. These

illustrations are to familiarizethe pilot with the type andplacement of data to be provid -ed by the EFS 40/50.

ED 551A is the only version incurrent production.

The data presented in thispilot ’s guide is general innature and not tailored towarda specific installation. Not allequipment interfaces nor dis -play options presented are cer -tifiable in all aircraft types or byall certification agencies. Eachinstallation may incorporatedifferent equipment comple -ments and use different dis -play options. For the uniquecertified operating procedureof a particular aircraft, refer tothe appropriate approvedFlight Manual Supplement forthat aircraft.

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System Configuration

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GENERAL

Various configurations of theE F S 40/50 system are currentlyavailable to fulfill the particularneeds of the user. These config-urations are differentiated by thenumber of display units, type ofmode controller, number of sym-bol generators and the interfac-ing equipment.

The basic EFS 40 ( 2 tube fourinch Electronic Flight Instrumen-tation System) consists of:

• 1ea EHSI Control/DisplayUnit (ED 4 6 1 )

• 1 ea EADI DisplayUnit (ED 4 6 2 )

• 1 ea EADI controlpanel (CP 4 7 0 )

• 1 ea Symbol Generator( S G 4 6 5 )

• Or 1 ea remote EFISControl Panel (CP 4 6 7 )

• 1 ea EHSI DisplayUnit (ED 4 6 2 )

• 1 ea EADI DisplayUnit (ED 4 6 2 )


The basic EFS 50 (2 tube fiveinch Electronic Flight Instrumen-tation System) consists of:• 1 ea remote EFIS Control

Panel (CP 467)

• 1 ea EHSI DisplayUnit (ED 5 5 1 A ) ,

• 1 ea EADI DisplayUnit (ED 5 5 1 A )


Beginning with software 09, aconfiguration option was addedallowing an MFD only installation.This option removes the headingbug from the display allowing theMFD SG to stand alone withoutany other symbol generator inthe installation. The display unitin this case can be either an ED462 or ED 551A. The controlpanel must be a CP 469A.

o MFD ONLY - no selectedheading bug.

Two new configuration optionsfor display unit (DU) type werealso added with software 09.These options allow the MFD SGto drive a 5” ED 551A MFD dur-ing normal operation and changeto either ED 461 or ED 462 EHSIand ED 462 EADI during standbyo p e r a t i o n .

o MFD - ED 551AEHSI - ED 461EADI - ED 462

o MFD - ED 551AEHSI - ED 462EADI - ED 462

SYSTEM CONFIGURATION

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CONTROL PANEL

The ED 461 Control/Display Unitincorporates the EHSI mode con-troller in the bezel of the display,reducing the required panelspace to 4” X 4”. For those instal-lations that are not sensitive topanel space, an independent dis-play unit, ED 462, ED 551A, andmode controller, CP 467, are

offered. Figure 1.1 depicts theE F S 40/50 Control DisplayO p t i o n s .

Regardless of which display unitand method of control is select-ed, the system’s performance willbe identical. Both mode con-trollers offer a simple means forthe pilot to select the desired dis-play format, such as standard

Figure 1.1CONTROL DISPLAY OPTIONS

ED 551/A MFD & CP 469A

2 EA ED 462 & CP 467

2 EA ED 551A & CP 467 ED 461, ED 462, & CP 470



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compass rose or sectored com-pass rose, 360-degree map orsectored map and weather radaroverlay. Also incorporated onthe mode controller is the courseand heading select knobs withauto sync. The auto sync feature

will slew the heading bug to thelubber line or the course pointerto the DIRECT TO course for theselected NAV sensor providing acentered D-Bar. The CP 4 6 7and CP 470 incorporate DecisionHeight Set and Radio AltimeterT e s t .

Figure 1.2SG 464 AND SG 465 SYMBOL GENERATORS

SYMBOL GENERATOR

The SG 464 EHSI/MFD-onlysymbol generator is a remote-mounted processing unit pack-aged in an ARINC 1/4 ATR shortform factor. The SG 4 6 5EADI/EHSI/MFD symbol genera-tor is a remote-mounted process-ing unit packaged in an ARINC3/8 ATR short form factor. A ver-sion of the SG 465 3/8 ATR shortsymbol generator is offered withEHSI/MFD-only provisions.

The SG 464 or SG 465 with soft-ware version 05 and above willdrive either the 4” X 4” (ED 4 6 1or 462) or 5” X 5” (ED 551A) dis-plays. Software version 06 incor-porates the capability to drive theE D 551 display. The SG 464 isno longer available and has notbeen produced with software ver-sions 08 or later.



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Figure 1.3TYPICAL EFS 40/50 SYSTEM BLOCK DIAGRAM



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EQUIPMENT INTERFACE &OPERATING CONFIGURATION

The EFS 40/50 equipment inter-face and operating configurationis establ ished at the time ofinstallation and certification. Thefollowing pages are provided todocument the certified configura-

tion of a specific aircraft. Thosepages referring to software con-figuration versions not applicableto this aircraft are to be removedfrom this pilot’s guide.



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SOFTWARE 04 CONFIGURATION PAGES

The EHSI, EADI, and Reversion software will display these pages. Allitems will be identical among all 3 displays, however, the ADI will notbe able to show the rack configurations, instead it will show the config-uration data coming from the HSI and the data in its own EEPROM.The descriptions given in this section refer to side 1 (left side) as thepilot’s side and side 2 (right side) as the co-pilot’s side.

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 012 I T E M3 SG NUMBER _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 S I N G L E / D U A L _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 DU TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 ATTITUDE/HDG #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 ATTITUDE/HDG #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 RATE OF TURN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 ADF #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 ADF #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 VOR/ILS #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 VOR/ILS #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 022 I T E M3 DME #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 DME #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 MLS #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 MLS #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 FMS #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 FMS #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RNAV #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RNAV #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 TACAN #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 TACAN #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .



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— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 032 I T E M3 V N A V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR ALT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 AFCS TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 AFCS COMMAND BAR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 AFCS MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 AIR DATA _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RADAR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR CTL PNL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 RADAR INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 C H E C K L I S T _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR GRAPHICS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

— — — — — — — — — — |1 VIEW/EDIT OPERATING CHAR PG 062 I T E M3 VERT SCALE SIDE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 DCLTR GS ON BC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 S P A R E _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DISPLAY WIND VEC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 DISPLAY DRIFT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 DG ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DME DIST ONLY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 . . M O R E . .



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— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 072 I T E M3 DISPLAY HDG TAPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 COMMAND BARS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ROLL INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DCLTR UNUS ATT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CAT II AVAILABLE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 PERSPECTIVE LINES _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DH SELECT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



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The EHSI, EADI, MFD and Reversion software will display the follow-ing pages. All display information will be identical on the EHSI andMFD, however, the EADI will not display the rack configurations, it willdisplay a comparison of the EHSI and EADI configuration data. Thedescriptions given in this section refer to side 1 (left side) as the pilot’sside and side 2 (right side) as the co-pilot’s side.





1.10 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 032 I T E M3 V N A V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR ALT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 AFCS TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 AFCS COMMAND BAR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 AFCS MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 AIR DATA _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RADAR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR CTL PNL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 RADAR INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 C H E C K L I S T _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR GRAPHICS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

— — — — — — — — — — |1 VIEW/EDIT OPERATING CHAR PG 062 I T E M3 VERT SCALE SIDE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 DCLTR GS ON BC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 FULL TIME FMS MAP _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DISPLAY WIND VEC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 DISPLAY DRIFT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 DG ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DME DIST ONLY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 MFD NAV CONTROL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .



1.11Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 072 I T E M3 DISPLAY HDG TAPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 COMMAND BARS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ROLL INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DCLTR UNUS ATT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CAT II AVAILABLE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 PERSPECTIVE LINES _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DH SELECT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 SEL HDG SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 SEL CRS SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.12 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.13Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 032 I T E M3 V N A V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR ALT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 AFCS TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 AFCS COMMAND BAR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 AFCS MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 F/S AIR DATA _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RADAR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR CTL PNL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 RADAR INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 C H E C K L I S T _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 T C A S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LIGHTNING DET _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

— — — — — — — — — — |1 VIEW/EDIT OPERATING CHAR PG 062 I T E M3 VERT SCALE SIDE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 DCLTR GS ON BC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 FULLTIME FMS MAP _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DISPLAY WIND VEC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 DISPLAY DRIFT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 DG ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DME DIST ONLY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 MFD NAV CONTROL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .



1.14 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 072 I T E M3 DISPLAY HDG TAPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 COMMAND BARS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ROLL INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DCLTR UNUS ATT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CAT II AVAILABLE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 PERSPECTIVE LINES _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DH SELECT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 SEL HDG SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 SEL CRS SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 082 I T E M3 NORTH UP MAP _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 VERT PTR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 DISPLAY FMS MSG _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 SEL HDG COLOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CMD BAR COLOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 REV MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RISING RUNWAY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 ADI DEV SRC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 CMD BAR FILTER _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.15Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

SOFTWARE 07 CONFIGURATION PAGES(includes both 0701 and 0702)


——————————| 1 VIEW/EDIT EQUIPMENT PG 012 I T E M3 SG NUMBER _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 S I N G L E / D U A L _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 DU TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 ATTITUDE/HDG #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 ATTITUDE/HDG #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 RATE OF TURN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 ADF #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 ADF #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 VOR/ILS #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 VOR/ILS #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .




1.16 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 032 I T E M3 V N A V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR ALT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 AFCS TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 AFCS COMMAND BAR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 AFCS MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 F/S AIR DATA _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RADAR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR CTL PNL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 RADAR INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 C H E C K L I S T _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 T C A S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LIGHTNING DET _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

— — — — — — — — — — |1 VIEW/EDIT OPERATING CHAR PG 062 I T E M3 VERT SCALE SIDE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 DCLTR GS ON BC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 FULL TIME FMS MAP _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DISPLAY WIND VEC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 DISPLAY DRIFT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 DG ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DME DIST ONLY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR ONLY MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 S P A R E _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 MFD NAV CONTROL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .



1.17Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 072 I T E M3 DISPLAY HDG TAPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 COMMAND BARS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ROLL INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DCLTR UNUS ATT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CAT II AVAILABLE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 PERSPECTIVE LINES _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DH SELECT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 CTL PNL SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 SEL HDG SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 SEL CRS SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

1 VIEW/EDIT OPERATING PG 082 I T E M3 NORTH UP MAP _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 VERT PTR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 DISPLAY FMS MSG _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 SEL HDG COLOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CMD BAR COLOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 REV MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RISING RUNWAY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 ADI DEV SRC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 CMD BAR FILTER _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.18 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


The EHSI, EADI, MFD and Reversion software will display the follow-ing pages. All display information will be identical on the EHSI andMFD, however, the EADI will not display the rack configurations, it willdisplay a comparison of the EHSI and EADI configuration data. Thedescriptions given in this section refer to side 1 as the pilot’s side andside 2 as the co-pilot’s side.





1.19Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 032 I T E M3 FMS VNAV _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 RADAR ALT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 AFCS TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 AFCS COMMAND BAR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 AFCS MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 F/S AIR DATA _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RADAR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RADAR CTL PNL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 RADAR INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 C H E C K L I S T _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .





1.20 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 072 I T E M3 DISPLAY HDG TAPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 COMMAND BARS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ROLL INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DCLTR UNUS ATT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CAT II AVAILABLE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 PERSPECTIVE LINES _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DH SELECT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 CTL PNL SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 SEL HDG SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 SEL CRS SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 082 I T E M3 NORTH UP MAP _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 VERT PTR TYPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 DISPLAY FMS MSG _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 SEL HDG COLOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CMD BAR COLOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 REV MODE ANN _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RISING RUNWAY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 ADI DEV SRC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 CMD BAR FILTER _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 MLS VRT ANNUNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 092 I T E M3 DATUM SCALING _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 HDG FAIL ANNUNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 VNAV APR SCALE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 LNAV CRS CTRL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 SG #1 SIDE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 AIRCRAFT SYMBOL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 TACAN ANNUNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 TCAS DISPLAYS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 CAT II SENSORS _______________



1.21Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.22 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.23Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 072 I T E M3 DISPLAY HDG TAPE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 ADI PLANE/CMD BAR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ROLL INDICATOR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 DCLTR UNUS ATT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 CAT II AVAILABLE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 PERSPECTIVE LINES _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 DH SELECT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 CTL PNL SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 SEL HDG SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 SEL CRS SYNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 3 . . M O R E . .


— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 092 I T E M3 DATUM SCALING _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 HDG FAIL ANNUNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 VNAV APR SCALE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 LNAV CRS CTRL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 SG #1 SIDE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 AIRCRAFT SYMBOL _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 TACAN ANNUNC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 TCAS DISPLAYS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 CAT II SENSORS _______________ 1 2 RADAR SCAN _______________



1.24 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 102 I T E M3 RADAR SDI _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.25Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.26 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.27Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.28 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 102 I T E M3 RADAR SDI _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 PITCH SYNC DISC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.29Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.30 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 T C A S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LIGHTNING DET _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 VARIABLE LNAV _ _ _ _ _ _ _ _ _ _ _ _ _ _ _




1.31Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.32 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16




1.33Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.34 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.35Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.36 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16




1.37Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.38 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.39Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.40 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 102 I T E M3 RADAR SDI _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 PITCH SYNC DISC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ADF PTR HOLD DST _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.41Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.42 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 T C A S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LIGHTNING DET _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 VARIABLE LNAV _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 E G P W S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _




1.43Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.44 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 102 I T E M3 RADAR SDI _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 PITCH SYNC DISC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ADF PTR HOLD DST _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 FMS OUTPUT BUS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.45Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16







1.46 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 T C A S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LIGHTNING DET _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 VARIABLE LNAV _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 E G P W S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 V A R I A B L E V N A V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _




1.47Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.48 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 102 I T E M3 RADAR SDI _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 PITCH SYNC DISC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ADF PTR HOLD DST _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 FMS OUTPUT BUS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LNAV VERT APR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 L/VNAV VERT A P R _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 LP VERT A P R _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 LPV VERT APR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 LNAV SELECT OUT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.49Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16




— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 022 I T E M3 DME #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 DME #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 MLS #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 MLS #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 FMS #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 FMS #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 RNAV #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 RNAV #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 TACAN #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 TACAN #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _



1.50 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


— — — — — — — — — — |1 VIEW/EDIT EQUIPMENT PG 042 I T E M3 J O Y S T I C K _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 T C A S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 HOMING #1 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 HOMING #2 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LIGHTNING DET _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 HOVER MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 CABLE MODE _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 VARIABLE LNAV _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 E G P W S _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 2 V A R I A B L E V N A V _ _ _ _ _ _ _ _ _ _ _ _ _ _ _




1.51Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16






1.52 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

— — — — — — — — — — |1 VIEW/EDIT OPERATING PG 102 I T E M3 RADAR SDI _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4 PITCH SYNC DISC _ _ _ _ _ _ _ _ _ _ _ _ _ _ _5 ADF PTR HOLD DST _ _ _ _ _ _ _ _ _ _ _ _ _ _ _6 FMS OUTPUT BUS _ _ _ _ _ _ _ _ _ _ _ _ _ _ _7 LNAV VERT APR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _8 L/VNAV VERT A P R _ _ _ _ _ _ _ _ _ _ _ _ _ _ _9 LP VERT A P R _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 0 LPV VERT APR _ _ _ _ _ _ _ _ _ _ _ _ _ _ _1 1 LNAV SELECT OUT _ _ _ _ _ _ _ _ _ _ _ _ _ _ _


EHSI Operation

2.1.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

EHSI OPERATION

DETAILED OPERATING CONTROLS

All possible EFS 40/50 Interfac-ing Equipment is described in theDetailed Operating Controls sec-tion of the EFS 40/50 Pilot’sGuide, however, all may not beactive in a specific installation.

This section, EHSI Operation, willdescribe the operation of both

the ED 461 control display unit,C P 468 EHSI control panel andthe EHSI section of the CP 4 6 7EHSI/EADI control panel. TheEADI operation of the CP 467 iscovered in section 2.2, EADIOperation. The CP 466A/B radarcontrol panels are covered insection 2.3, RADAR Operation.

Figure 2.1ED 461 EHSI

Section 2.1mp 9/8/10 7:46 PM Page 2.1.1

EHSI Operation

For clarification on a particulardisplay or operational feature,refer to section IV. EHSI DIS-PLAYS or section V. OPERAT-ING INSTRUCTIONS. Figure2.1 shows the ED 461 combined

control/display unit and figure 2.2shows the CP 468 dedicatedstand-alone EHSI mode con-troller and companion ED 4 6 2display unit.

2.1.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 2.2ED 462 Display Unit & Companion

CP 468 Control Panel


EHSI Operation

1-2 NAVIGATIONSYSTEM SELECT

The 1-2 button is used to cyclebetween primary navigation sen-sor system #1 and #2 for display.The primary NAV system select-ed is annunciated as sensor 1 orsensor 2 on the EHSI. Example,if VOR 1 is being displayed andthe 1-2 button is pressed, VOR 2will become the displayed sen-sor. If only one sensor isinstalled, the display will not cycleand the sensor annunciation willnot show a system number. Forexample ADF would be displayed(not ADF 1) in installations con-taining a single ADF.

Note: The cross-side sensor forVOR could be TCN, for LNAVsit could be a combination ofFMS, GPS, OMG or LOR.Beginning with software 08,the 1-2 button no longerselects between unlike LNAVsources.

Software release 0402 added“FUNCTION NOT IMPLE -MENTED” annunciation wheneither the 1-2, RMI or NAVsensor select button is pressedand it is not active in the sys -tem. A yel low FUNCTIONNOT IMPLEMENTED will bedisplayed in the center of thescreen.

NAV NAVIGATIONSENSOR SELECT

During installation, the EFS40/50 symbol generator was pro-grammed with the type andquantity of each piece of interfac-ing equipment. Not al l theequipment interfaced to the EFS40/50 is usable for primary navi-gation. The EFS 40/50 createsand maintains in permanentmemory a list of the interfacingnavigation sensors.

The NAV push button is used toselect which NAV sensor pro-vides primary navigation data. Apress of the NAV sensor selectbutton sequentially selects thenext available sensor from the listof those installed. Primary Navi-gation Data is defined as the dis-tance in the upper right corner,selected course, course pointerand deviation.

2.1.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

EHSI CONTROLS (ED 461 & CP 467/468)

1-212 NAV

NAV


EHSI Operation

The Primary Navigation Sensoris annunciated at the side of thedisplay unit opposite the verticalscale. Only those sensors inter-faced to the EFS 40/50 in a spe-cific installation will be selectablefor use and display.

For instal lations with dualVOR/ILS receivers and a KNS81, the KNS 81 will be pro-grammed as an RNAV. Theannunciation displayed on theEHSI for this configuration will beNAV and wil l not change asmodes on the KNS 81 arechanged. The sensor annuncia-tion and associated navigationdata colors will change to matchthe normal enroute or approach

color scheme, green for on-sideapproach navigation data, cyanfor on-side non approach naviga-tion data and yellow for off-sidenavigation data.

S o f t w a r e 04 added two new heli-copter navigation sensor options,Doppler (DOPP) and Cable(CAB). These sensors requireunique display formats, thereforewhen they are selected for dis-play their unique format will bepresented and are not change-able by the HSI or ARC button.

The following is an all-inclusivelist, in order, of primary naviga-tion sensors that may be inter-faced with the EFS 40/50:

2.1.4 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

DOPP

MLS

NAV (KNS 81 ONLY)

LNAV, (FMS, LOR or OMG)

TCN (Control head)

ADF

CAB

HOM

TCN (Control head)

VOR (VOR, LOC, TCN or RNV) VOR (VOR, LOC, TCN or RNV)

LNAV, (FMS, LOR or OMG)

NAV (KNS 81 ONLY)

MLS

ADF

HOM

ON-SIDE EFS CROSS-SIDE EFS

1-2

1-2

1-2

1-2

1-2

1-2

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

1-2

NAV

NAV

NAV

NAV

NAV

NAV

DOPP

MLS

NAV (KNS 81 ONLY)

ADF

CAB

HOM

NAV (KNS 81 ONLY)

MLS

ADF

HOM

1-2

1-2

1-2

1-2

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

NAV

LNAV, (FMS, LOR, OMG or GPS)

TCN (Control head) TCN (Control head)

VOR (VOR, LOC, TCN or RNV) VOR (VOR, LOC, TCN or RNV)

ON-SIDE EFS CROSS-SIDE EFS

1-2

1-2

NAV

NAV NAV

NAV

LNAV, (FMS, LOR, OMG or GPS)

NAV

SOFTWARE 04/05/06/07 SOFTWARE 08 OR LATER


EHSI Operation

See Section 4 for display detailson Doppler, Cable and Homing.

Note: If a number 2 NAV sen -sor has been selected for dis -play on the number 1 EHSI bypressing the 1-2 button andthe number 1 EHSI NAV pushbutton is pressed, the nextavailable number 1 NAV sen -sor will be selected.

ADF D-Bar presentation maynot be available if the ADFdoes not provide a suitableflag output.

Software 08 treats unlikeLNAV sources (i.e. FMS, LOR,OMG, or GPS) as single sen -sors. When two unlike LNAVsources are configured, theEFS will display both the on-side LNAV and the off-sideLANV without a system num -ber and the NAV button isused to select between them.

HSI 360° MODESELECTION

The EFS 40/50 EHSI has fourpossible 360-degree display for-mats: standard HSI compassrose, NAV map, NAV map withweather, and DG mode. Eachpress of the HSI button sequen-tially selects the next display for-mat. A press of the HSI buttonwhile in the ARC mode willchange the display to the stan-dard HSI compass rose.

The display selection list mayinclude the following:

2.1.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

DG and WEATHER are optionsselected at the time of installationand are included in the systemcertification. Software 06 addedlightning detection presentation.

If a compatible weather radar orlightning detection is notinstalled, the weather option willnot be in the sequence.

Software release 05 added aHeading Bug to the DG mode.Primary use of this display formatis for training or as an option toprovide an uncluttered display foran NDB approach (using theEHSI as an ADF RMI).

Software release 07 provides theadditional, optional display formatof "Plan View" which can be con-figured for display on the MFDo n l y .

HSIHSI


EHSI Operation

BEARING POINTERSELECT

The bearing pointer select but-tons work in a similar manner asthe NAV sensor select button. Apress of the bearing pointer but-ton sequentially selects the nextavailable sensor for display. Thebearing pointer sensor list con-tains only those sensors whichhave bearing information capabil-ities. If the selected sensor hasdistance information paired withit, that distance will also be dis-played below the sensor annun-

ciation. An optional push buttonsequence allows independentselection and display of therespective DME distance withoutthe presence of the bearingp o i n t e r .

E x a m p l e : For a single ADFinstallation, the ADF bearingpointer may be displayed oneither the single or double barpointer. The annunciationassociated with either bearingpointer will be ADF, not ADF 1or ADF 2.

The following is an all-inclusivelist, in order, of the bearing point-er sensors that may be interfacedwith the EFS 4 0 / 5 0 :

2.1.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Only those sensors interfaced tothe EFS 40/50 will be included inthe sequence.

N o t e : Software release 0 5allows single bearing sensorsto be displayed on either bear -ing pointer.Software release 07 and high -er, the DME only field can beconfigured to annunciate‘DME’ or ‘NAV’.

DECLUTTER, (NO #1 OR #2 BEARING POINTER INFORMATION IS DISPLAYED)

VOR, (VOR OR TCN)

TCN, (ONLY AVAILABLE WHEN THE TACAN HAS AN INDEPENDENT CONTROL HEAD)

LNAV, (FMS, LOR, OMG or *GPS)

NAV (KNS 81 ONLY)

MLS

ADF

DME ONE DISTANCE ONLY, (OPTIONAL)

OR

*SW 08 OR LATER


EHSI Operation

ARC SECTOREDMODE SELECTION

The ARC mode provides the pilota large scale view of the CDI bypresenting an approximate 85-degree sector display of the com-p a s s .

The EFS 40/50 EHSI has fivepossible ARC sectored displayformats: standard HSI compassrose, NAV CDI map, NAV CDImap with weather and standardHSI compass rose with weather.Software release 05 provides aconfiguration option, selectable at

the time of installation and certifi-cation, that allows a weather onlymode to be selected on the MFD.A press of the ARC button willsequentially select the possibledisplay formats.

A press of the ARC button whilein the 360-degree mode willresult in an ARC presentation ofthe same format. For example, ifthe 360 NAV MAP WITHWEATHER mode is being dis-played and the ARC button ispressed, the resulting display for-mat will be ARC NAV MAP WITHW E A T H E R .

The ARC display selection listmay include the following:

2.1.7Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

ARCARC

WEATHER is an option selectedat the time of installation and isincluded in the system certifica-tion. If a compatible weatherradar is not installed, the weatheroption will not be in thes e q u e n c e .

Software release 05 providesMFD, multi function display,capabilit ies. If an MFD isinstalled, an additional ARC for-mat option is offered, selectableat the time of installation and cer-tification, which provides an

A

R

C

ARC COMPASS ROSE

ARC NAV MAP

ARC NAV MAP WITH WEATHER (OPTIONAL)

ARC COMPASS ROSE WITH WEATHER (OPTIONAL)

ARC WEATHER ONLY (OPTIONAL ON MFD)


EHSI Operation

uncluttered weather radar pre-sentation. The MFD ARC weath-er only format provides a typicalweather radar presentation, nonavigation data is presentedwhen this mode is selected.

Refer to radar controls in thissection for details on weatherradar operation.

RANGE SELECTION

A press of the RANGE DOWNbutton selects the next lowerrange to be displayed while in theNAV MAP or WEATHER modesof operation. Once the lowestselectable range is reached, theRANGE UP button must be usedfor a range change.

The operation of the RANGE UPbutton is similar to the RANGEDOWN except it selects the nexthigher range to be displayedwhile in the NAV MAP orWEATHER modes of operation.

TST/REF

The TST/REF button will per-forms SELF TEST display,Ground speed, Time-to-Stationor LNAV formatting selectionswith software 04/05/06/07.The TST/REF button will per-forms SELF TEST or LNAV for-matting selections with softwarerelease 08 and higher.

w TST—

To display the EHSI systemSELF TEST, press and hold theTST/REF button for three sec-onds. Upon entering Self Test, atest pattern will be displayed. Inthe center of the test pattern,either a SELF TEST PASS orSELF TEST FAIL will be annun-ciated. With 04/05/06 software,the SELF TEST display willremain until the TST/REF buttonis pressed again. Beginning with07 software, the EFS will cancelthe test mode and return both theEADI and EHSI to normal opera-tion after 5 seconds.

N o t e : If the SELF TEST FAILmessage is annunciated, thesystem should be serviced.

w REF GROUND SPEEDor TIME-TO-STATIONs e l e c t i o n

With software 04/05/06/07, theTST/REF button allows alternateselection of Ground speed orTime-to-station as calculated bythe selected primary NAV sys-tem. When Ground speed orTime-to-station information isavailable it will be displayedbelow the distance information inthe upper right corner of the dis-play. If the information is not pro-vided, the associated annuncia-tor will be removed. Thealternate selection of Groundspeed and Time-To-Station willnot be allowed in the MAP modewith an LNAV selected as the pri-mary navigation source. Begin-ning with software 08, both

2.1.8 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

RNG

RNG

SYS REF

TST

REF


EHSI Operation

ground speed and time-to-stationare displayed simultaneously.Time-To-Station is displayedimmediately below the GroundSpeed using the format of hoursand minutes separated by acolon (H:MM).

Note: The Time-To-Station fieldused with software 08 can alsobe used for an abnormal DMEannunciation which has priori -ty.

The EFS 40/50 will calculateground speed and time-to-stationin instal lations which use anA R I N C 568 type DME. If a con-ventional DME indicator is alsoused, differences in groundspeed and time-to-station displaymay be noticed.

N o t e : Time-To-Station isreplaced with Time-To-Way -point when the selected prima -ry nav is an LNAV providingthis information.

w REF MAP FORMAT

When the selected EFS 4 0 / 5 0display is LNAV MAP, theTST/REF button allows selectionof the desired NAV MAP format.To determine the present MAPformat momentarily press theTST/REF button. The momen-tary button press will activate thepresent MAP format annuncia-tion. If the displayed format isdesired, no additional action isrequired; the format message willbe removed within 5 seconds. Ifa different format is desired,sequence through the list bymomentarily pressing theTST/REF button until the desiredformat is displayed. Approxi-mately 5 seconds after the lastbutton press, the map formatannunciation will be removed.

The following is an all-inclusivelist, in order, of the possible NAVMAP formats:

2.1.9Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Note: Depending upon the Flight Management System installed,the above format options may not be fully supported. Systemssuch as the BENDIX/KING KNS 660, KLN 88, and KLN 90, thatsupport the GAMA 429 LNAV data bus will provide the above for -mat options.

FPL ID

AIRPORT

NAVAIDS

TEST

REF

(FLIGHT PLAN WITH

FULL ICAO IDENTIFIERS)

(TO WAYPOINT AND NEAREST

AIRPORTS WITH ICAO IDENTIFIERS)

(TO WAYPOINT AND NEAREST NAVAIDS

WITH ICAO IDENTIFIERS)


EHSI Operation

COURSE SELECT KNOB

Rotation of the COURSESELECT knob allows the coursepointer and digital course to beset at the desired course.

The ED 461, CP 467 and CP468 provide a ”DIRECT TO” fea-ture. Pushing the center of theE D 461 Course Select knob orpulling the CP 467 or CP 4 6 8COURSE SELECT knob willcause the course pointer and dig-ital course readout on the EHSIto slew to the direct course to theselected NAVAID or active way-p o i n t .

If the selected NAV sensor is anLNAV system, it may havemodes of operation that controlthe selected course.

During these LNAV modes ofoperation the EFS 4 0 / 5 0COURSE SELECT knob will beinactive.

HEADING SELECT KNOB

Rotation of the HEADINGSELECT knob allows the head-ing bug on the EHSI to be rotatedto the desired heading.

The ED 461, CP 467 and CP468 provide a “HEADINGSYNC” feature. Pushing the cen-ter of the ED 461 heading selectknob or pulling the CP 467 orC P 468 HEADING SELECTknob will cause the heading bugon the EHSI to slew to the pre-sent aircraft heading (lubber line).

2.1.10 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

DISPLAY BRIGHTNESS CONTROL

The BRT knob controls the dis-play brightness.

Note: The display brightnesscontrol provides full range dim -ming to allow night operation inno- or low-light situations. The

lower limit of the display bright -ness may appear as an inoper -ative tube during normal day -light operation. It is thereforeadvisable to check the BRTknob setting during preflighttest.

To ensure maximum displaytube life, it is highly recom -mended that the display beoperated at the lowest accept -able brightness level.

BRT


EADI Operation

2.2.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

This section, EADI Operation, ofthe EHI 40/50 Pi lot ’s Guidedescribes the EADI operationalcontrols of the CP 467 and CP470 used with an ED 462 or ED551/A EADI.

EADI controls are limited to threebasic functions: EADI displaybrightness adjustment, DH (deci-sion height) set and Radio Alti-tude test.

For clarification on a particulardisplay or operational featurerefer to section IV, EADI DIS-PLAYS or section V, OPERAT-ING INSTRUCTIONS.

The CP 467 shown in Figure2.2.1 is used in EFIS installationsutilizing an ED 462 or ED 5 5 1 / Aas the EHSI. The CP 4 7 0shown in Figure 2.2.2 is used inEFIS installations utilizing the ED461 EHSI control display unitwith an ED 462 EADI.

EADI OPERATION

EADI DETAILED OPERATING CONTROLS

Figure 2.2.1CP 467 EFIS CONTROL PANEL

Figure 2.2.2CP 470 EADI CONTROL PANEL

DH

BRT

ADIRALT

TSTSET


EADI Operation

2.2.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

BRIGHTNESS

The BRT knob controls the dis-play brightness.

N o t e : The display brightnesscontrol provides full range dim -ming to allow night operation inno- or low-light situations. Thelower limit of the display bright -ness may appear as an inoper -ative tube during normal day -light operation. It is thereforeadvisable to check the BRTknob setting during preflighttest.

To ensure maximum displaytube life, it is highly recom -mended that the display beoperated at the lowest accept -able brightness level.

DH SET

To set the Decision Height, pullout and turn the DH knob. Turn-ing clockwise will increase theDecision Height selected, turningcounter clockwise will decreasethe Decision Height. The DH setknob is variable rate, the fasterthe knob is turned the greater thechange in a given amount ofrotation. The Decision Heightrange is from “OFF” to 2,500 feetand will be displayed in one foot

increments up to 500 feet andthen in 10 foot increments to2,500 feet.

Once the desired DH is selected,push in the DH set knob to lockthe selected DH altitude. If DH isset to OFF, the “DH” annuncia-tion will not be displayed.

RALT TST

Pressing the RALT TST (RadioAltimeter Test) push button pro-vides a discrete output to theRadio Altimeter initiating its selftest function.

The height displayed on theEADI will depend on the type ofRadio Altimeter installed. Fordetails on this information refer tothe Radio Altimeter Pilot’s Guideof approve Flight Manual Sup-p l e m e n t .

DH

BRT

ADIRALT

TSTBRT

DH

BRT

ADIRALT

TSTDH

RALT

TST

RALT TST


Radar Operation

2.3.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

The following section providesgeneral operating information onE F S 40/50 radar control panels,C P 466A & CP 466B. Figure2.3.1 shows the CP 466A usedwith an RDS 81, RDS 82 orR D S 82VP, RDS 84 or RDS

84VP, RDR 2000. Figure 2.3.2shows the CP 466B used withan RDS 86, RDS 86VP or RDR2100. For detailed informationon the specific weather radarfunctions, refer to the appropriateradar pilot’s guide.

RADAR OPERATION

RADAR CONTROLS, (CP 466A & CP 466B)

Figure 2.3.1CP 466A

Figure 2.3.2CP 466B

Note: The CP 466A and B shown include the push buttons requiredfor the Vertical Profile radars. For non-VP installations using theCP 466A or B the VP and two track buttons will not be present.

DNPULL STAB OFF

ONTST

STBY

OFF

GAIN

Wx WxA GNDMAP

UPTILT O

DNPULL STAB OFF

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK

ONTST

STBY

OFF

GAIN

Wx WxA GNDMAP

UPTILT O

DNPULL AUTOPULL ARL

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK


Radar Operation

OFF-STBY-TST-ON

The rotary OFF-STBY-TST-ONknob selects the desired operat-ing condition for the radar.

w OFF

Disables the ART (Antenna,Receiver and Transmitter) powersupply. “OFF” is displayed belowthe NAV source annunciator onthe radar mode line.

w STBY

After 30 seconds in this mode,the system is in a state of readi-ness. No radar transmissionoccurs, and the antenna isparked in the down position.“STBY” is displayed below theNAV source annunciator on theradar mode line, if a weathermode is selected.

w TST

Causes the test pattern to be dis-played on the indicator, i f aweather mode is selected.“TEST” is displayed below theNAV source annunciator on theradar mode line.

w ON

Selects the condition of normaloperation, allowing for weatherdetection or other modes of oper-

ation. Depending on the select-ed mode of operation, WX,WXAor MAP is displayed below theNAV source annunciator on theradar mode line.

Note: If “ON” is selected on theC P 466 radar control panel,the radar Antenna, Receiverand Transmitter (ART) is oper -ational. However, if a weatherradar mode is not selected fordisplay on one of the indicatorsthe ART is placed in standbyby the EFIS.

WX

Selects the weather mode (WX)when pressed. “WX” will be dis-played below the NAV sourceannunciator on the radar modeline, if a weather mode is select-e d .

WXA

Selects the weather-alert modewhen pressed. The magentaarea of a storm will flash betweenmagenta and black. “WXA” willbe displayed below the NAVsource annunciator on the radarmode line, if a weather mode iss e l e c t e d .

GND MAP

Places the radar in ground map-ping mode of operation; disablesweather-alert feature and acti-

2.3.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

BRT

OFF

UPTILT

DN

GAIN

Wx WxA GNDMAP

TRKVP TRK

PULL AUTO

ONTST

STBY

OFF

PULL ARL

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK


Radar Operation

vates gain control. “MAP” will bedisplayed below the NAV sourceannunciator on the radar modeline. (Magenta is not active in theGND MAP mode.)

LIGHTNING

o (Optional) Enables the Light-ning display when pressed if aweather mode is selected for dis-p l a y .

VP

o (Optional) Once the desiredazimuth is selected with the TRKbutton, press the VP button toenter the Vertical Profile mode ofoperation. The Vertical ProfileScreen will appear. The weathermode of operation (WX, WXA orGND MAP) displayed in thelower left corner of the displaywill be the same as existed justprior to selecting VP. To select adifferent weather mode once inVertical Profile, simply select thedesired mode (WX, WXA or GNDMAP) by pressing the appropri-ate button.

Note: A brief period of time willnormally elapse before the dis -play will “paint” the VerticalProfile “picture”. This timedelay is due to the fact that theradar continues i ts normalazimuth scan after the VP but -ton is pressed.

The operation of scanning theantenna vertically (+/- 20 or +/-

30 degrees depending on theRadar) is referred to as taking avertical “slice”.

Once Vertical Profile is selected,the desired profile-azimuth anglemay be changed in two degreeincrements by pressing and hold-ing the appropriate TRK button.One of two things will happenwhen a TRK button is pressed:(1) If the radar ’s antenna isalready profiling, the antenna willmove in the two-degree incre-ments, “slicing” in the directiondetermined by the TRK button; or(2) A “WAIT” annunciation will bedisplayed indicating that theradar’s antenna will perform thedesired “slicing” function as soonas the antenna returns to the lastselected profiling-azimuth angle.

Depending on the software ver-sion of the RDS VP radar andthe system installation, the anten-na may also scan horizontallywhile in the VP mode. If theantenna is not sweeping vertical-ly when the TRK button ispressed, a “WAIT” annunciationwill be displayed until the anten-na returns to the last vertical“slice” azimuth.

To terminate the Vertical Profilemode and return to the normalmode (horizontal scan), press theVP button. The radar system willretain its existing weather modeand return to horizontal scanning.A track line will be present on thescreen for 15 seconds to indicatethe location of the last profiling-azimuth angle.

2.3.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK


Radar Operation

Beginning with EFS software ver-sion 09, a Split Screen mode isadded to the VP button selectionsequence immediately followingthe Vertical Profile mode. Duringthis Split Screen mode the EFSwill toggle the antenna betweenvertical and horizontal scansevery 6 seconds, allowing both tobe displayed simultaneously onthe MFD. See Figure 4.4.4.

Note: This Split Screen mode isan operational enhancementadded to EFS 09 software thatdoes not require any modifica -tion to the existing RDS82VP/84VP/86VP/RDR 2000weather radar systems. Sincethis feature was not part of theoriginal design of these radars,the transition between horizon -tal and vertical scans is notsynchronized to the antennascan and will therefore occurat random scan positions.

Horizontal (azimuth) and vertical(tilt) track lines are displayed onthe MFD full time during the splitscreen mode to indicate theantenna scan position in eachp l a n e .

TRK

o (Optional) If the weather onlymode is selected on the MFD,pressing the TRK button acti-vates and slews a yellow dashedazimuth line. It also activates adigital display showing the num-ber of degrees the azimuth line islocated left or right from the nose

of the aircraft. In any other mapweather presentation, only theyellow dashed line will be dis-played.

For VP operations, the TRK but-ton performs two functions. 1.)Prior to engaging VP, the appro-priate button (left or right) is usedto place the track line at thedesired azimuth angle to be verti-cally scanned (sliced). When VPis engaged, the slice will be takenat the last position of the trackline, whether it is visible or not. Ifthe track line has not beenselected after power has beenapplied to system and VP isengaged, the slice will be takenat 0 degrees (directly in front ofthe aircraft). 2.) When in VPmode, pressing the TRK willchange the selected azimuthtwo-degrees left or right, depend-ing on which button is pressed.Continuously holding the TRKbutton will result in the system“slicing” in two-degree incre-ments, called continuous profile.Continuous profile is not used onthe RDR 2 0 0 0 .

Beginning with EFS software ver-sion 09, the Drift Angle Track fea-ture can be activated on the MFDby pressing both TRK buttonssimultaneously. While active, thisfeature places the track line atthe drift angle provided by anLNAV. The track line always indi-cates the azimuth angle at whicha vertical scan is performed forVP operation.

Note:Approximately 15 secondsafter drift angle track is select -

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BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK


Radar Operation

ed, the track line will disap -pear, however, the weatherradar will continue to use thedrift angle even though thetrack line is not displayed.

The EFS must be receiving validdrift angle information from anLNAV and have the drift anglebug displayed before the DrfitAngle Track feature can be acti-v a t e d .

o A configuration option wasadded with software 09 to allowthe drift angle bug to be dis-played full time, in addition to theoriginal option which displayedthis bug only when the LNAVproviding drift angle was selectedas the primary nav sensor onE F S .

Drift angle track is de-activatedand manual control returned bypressing either TRK left or TRKright buttons individually.

GAIN

Manual gain control becomesactive when GND MAP is select-ed. In all other modes, gain isinternally set.

PULL ARL

Only present when an RDS 8 6or RDS 86VP is installed. Auto-matic Range Limit displays ablue area behind weather sys-

tems where weather detection isno longer possible because ofattenuation.

TILT

Permits manual adjustment ofantenna tilt 15 degrees up ordown to enable the pilot to ana-lyze the weather presentation.The tilt angle is displayed belowthe NAV source annunciator onthe radar tilt annunciator line.

If a CP 466A is installed, pull theTilt selector knob, PULL STABOFF, for “STAB OFF” opera-tions. “STAB OFF” will appearon the Radar Fault/Warning linedisplayed below the NAV sourceannunciator just under the Anten-na Tilt annunciation line.

If a CP 466B is installed, pull theTilt selector knob, PULL AUTO,for Auto Tilt. If selected, an “A”will follow the tilt direction indica-tion arrow preceding the internal-ly calculated Auto tilt angle sup-plied by the ART.

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BRT

OFF

UPTILT

DNPULL AUTO

GAIN

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK

BRT

OFF

UPTILT

DNPULL AUTO

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK

BRT

OFF

UPTILT

DN

GAIN

PULL ARL

ONTST

STBY

OFF

Wx WxA GNDMAP

TRKVP TRK


Radar Operation

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*This page intentionally left blank.


MFD Operation

2.4.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

The EFS 40/50 Multi FunctionDisplay Control Panel providesfor display of a more meaningfulvariety of data than was previ-ously accessible on EFIS MFDdisplays. In fact, the EFS 4 0 / 5 0MFD may be used as a secondEHSI by the pilot or copilot, pro-viding them the ability to crosscheck their primary EHSI, pre-view or set up for a potential nav-igation scenario, and still functionas a primary weather radar orLNAV map display.

The CP 469, MFD control panel,provides control of the selectionof Nav source selection, displayformat and course selection.Starting with software release 08,the CP 469A MFD control panelreplaces the CP 469 and pro-vides additional control of Check-list, Joystick and TCAS functions.Weather radar control functionsand mode selection are per-formed by the CP 466A/B, anindependent weather radar con-trol panel.

MFD OPERATION

MULTI FUNCTION DISPLAY CONTROL PANEL

CP469

Note: Software levels 04, 05, 06 and 07 do not support Checklist orTCAS functions.

CP 469AWITH CHECKLIST & JOYSTICK


MFD Operation

Those push buttons which havecommon operation between theMFD and EHSI control panels,E D 461, CP 467 and CP 4 6 8 ,will function as defined in thesection 2.1, EHSI Operationunless otherwise noted in thissection. For detailed operationalinformation on those buttonsplease refer section 2.1.

COURSE SELECTKNOB/BUTTON

The course select knob will func-tion identical to, but independentof the one on the EHSI controlpanel, ED 461, CP 467 or CP468, when the CRS SEL buttonis activated. This provides inde-pendent selection of course onthe MFD referenced to the sameor a different nav sensor.

If the CRS SEL button is not acti-vated, the course select knob onthe CP 469 will not be active. Inthis mode the MFD will obtainselected course data from thepilot EHSI control panel. In thismode the course on the EHSIand MFD will be synchronized,unless the selected sensor onthe MFD is a LNAV providingD T K .

When the MFD course selectknob is not active, a bar the colorof the CRS annunciator will beplaced above it. This will alert the

pilot that the MFD CRS knob isnot active and is referenced tothe pilot’s EHSI selected course.

Example: C R S 1 3 5

HSI BUTTON

Will function identical to, but inde-pendent of, the one on the ED461, CP 467 or CP 468. Begin-ning with software 07, an addi-tional "Plan View" display formatcan be configured for presenta-tion on the MFD. When config-ured, this display format is addedto the end of the HSI buttonselection list provided in section2 . 1 .

Refer to section 2.1 EHSI OPER-ATION for detailed information.

ARC BUTTON

Will function similar to, but inde-pendent of, the one on the ED461, CP 467 or CP 468. TheMFD ARC button will allow theselection of an optional radaronly MFD display. This displaywill not contain navigation or mapdata and is added to the end ofthe ARC button selection list pro-vided in section 2.1.

NAV BUTTON

The NAV button may be config-ured at the time of installationand certification to operate in oneof two methods.

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CONTROL PANEL BUTTON OPERATIONS

TST REFCRS SEL

CRS

BRT

ENT C-LTCS ARCHSI NAV

1-2

TST REFCRS SEL

CRS

BRT


1-2


MFD Operation

o Configuration option numberone will slave the MFD to the #1EHSI. The NAV push button willcause the MFD to display eitherthe same NAV sensor as dis-played on the EHSI or the LNAV.When this configuration is select-ed the 1-2 push button allowsselection between the on s i d eand off side sensors. Once aside is selected, that side willremain the selected side until the1-2 button is pressed again. Thisallows the pilot the ability toselect the off side sensor to pro-vide himself a constant visualcross comparison.

o Configuration option numbertwo enables the NAV button tofunction identical to, but indepen-dent of, the one on the ED 4 6 1 ,C P 467 or CP 468. When thisconfiguration option is selectedthe pilot can select any availablenav sensor for display on theMFD independent of what is dis-played on the EHSI.

1-2 BUTTON

If NAV push button configurationoption number one is selected,where the MFD is slaved to theEHSI, the 1-2 push button allowsthe pilot to select between onside and off side NAV sensors.Unlike the 1-2 push button on theEHSI control panel, it selectswhich side will be displayed untilpushed again. A press of theNAV push button will not cause aselected off side sensor to cycleback to an on side sensor as itdoes on the EHSI.

If NAV push button configurationoption number two is selected,the 1-2 button functions identicalto, but independent of, the one onthe ED 461, CP 467 or CP 4 6 8 .

BEARING #1 & #2 BUTTON

Will function identical to, but inde-pendent of, the one on the ED461, CP 467 or CP 468.

Refer to section 2.1 EHSI OPER-ATION for detail information.

RANGE UP/DOWN BUTTON

Will function identical to, but inde-pendent of, the one on the ED461, CP 467 or CP 4 6 8 .

Refer to section 2.1 EHSI OPER-ATION for detail information.

JOYSTICK

w W A Y P O I N TE N T R YO P E R A T I O N

When the joystick is interfaced toan EFS 40/50 system, it can beused to generate and move sin-gle waypoint on the display unit.These waypoints can then beentered into the KNS 81, KNS660, KLN 88, KLN 90, or anyother LNAV using an appropriateGAMA 429 interface. The KNS

2.4.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


MFD Operation

81 must have the graphic outputb u s .

With an LNAV, RNAV, (or KNS81 configured as a NAV) select-ed for the primary nav sensorand during display of a NAV MAPon the MFD, initial movement ofthe joystick will create a waypointcursor ahead of the aircraft onthe half range ring at the currentheading. This will be true for bothHSI and ARC display formats.The cursor will be a standardwhite waypoint symbol. Move-ment of the waypoint will be inany of the eight directions com-manded by the joystick. The rateof movement will start off slowand increase in speed in twosteps. Return of the joystick toits center, off position at any timewill reset the rate of movement tothe slowest speed. The cursorlocation on the display screenand its rate of movement relativeto the display screen will be inde-pendent of the display rangeselected. The cursor is notallowed to exit the compass.When an LNAV is selected asthe primary navigation source,Lat/Lon coordinates of the cursorwill be displayed in the lower cen-ter of the display. When a KNS81 is the active primary naviga-tion source, and it is not in theILS mode, radial and distance ofthe cursor from the navaid in useby the KNS 81 will be displayedinstead of Lat/Lon coordinates.The cursor position informationcan be transferred to the LNAVor KNS 81 that is selected as theprimary navigation sensor, bypressing the ENTER button while

the cursor and its coordinates aredisplayed. The coordinates of thecursor will remain displayed for atleast 10 seconds and disappearfrom the display within 15 sec-onds after activating the ENTERbutton. If the waypoint cursor isnot moved for 20 seconds, it willdisappear from view. The nexttime the joystick is moved, thecursor will re-appear in the samelocation on the display screen.However, a change of primaryNAV sensor or display modes willreset the invisible cursor locationto its initial starting position.

Note: Systems with an MFD canhave the joystick on the CP469A MFD control panel or astand alone joystick. Additionaljoysticks for the pilot or copilotnormally will not be installed.Systems without an MFD mayhave up to two joysticks thatare completely independent ofeach other; one for the pilotand one for the copilot. Thepilot’s joystick can create ormove a waypoint only on thepilot’s EHSI, and any waypointcreated by the pilot can onlybe loaded into the #1 RNAV or#1 LNAV. Likewise, the copi -lot ’s joystick can create ormove a waypoint only on thecopilot’s EHSI, and any way -point created by the copilotcan only be loaded into the #2RNAV or #2 LNAV.

w PLAN VIEW OPERATION(available with 07 and higher)

Plan View will be available in theHSI key selection sequence

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MFD Operation

immediately following “DGMODE”. In addition to selectingthe plan view display mode, theoperator must be using a navsource which will provide flightplan information like FMS, GPS,and LORAN sensors.

If joystick is not available, thecenter of the screen will repre-sent the aircraft present positionwhen plan view mode is entered,and the map may not be movedfrom this reference. Range couldbe changed using the range but-tons. When a joystick is avail-able, it will control the flight planview relative to the aircraft pre-sent position. Pressing the “ENT’button wiil reset the displaywhere the aircraft is displayed inthe center of the display.

w CHECKLIST OPERATION(available with 08 and higher)

In the Checklist mode, the Joy-stick commands will be limited tofour positions: UP, DOWN, LEFTand RIGHT. The 45° commandswill be ignored.

A down push on the joystick willadvance the cursor checklist line.A down push at the bottom of achecklist page will advance thecursor to the next page if avail-able. Continuous downwardpushes will wrap the cursor withina checklist level.

An up push on the joystick willmove the cursor up one checklistline. An up push at the top of achecklist page will move the cur-sor to the previous page if avail-

able. Continuous upward pusheswil l wrap the cursor within achecklist level.A right push on the joystick willmove the cursor to the top of thenext checklist page. Continuousright pushes will wrap the cursorto the top of the next page withinthe list.

A left push on the joystick willmove the cursor to the top of theprevious checklist page. Contin-uous left pushes will wrap thecursor to the top of the previouspage within the list.

ENT BUTTON

w W A Y P O I N TENTRY OPERATION

In the map mode the cursor posi-tion information can be trans-ferred to the LNAV or KNS 81that is selected as the primarynavigation sensor, by pressingthe ENTER button while the cur-sor and its coordinates are dis-played. The coordinates of thecursor will remain displayed for atleast 10 seconds and will disap-pear from the display within 15seconds after the ENTER buttonis pressed.

w PLAN VIEW OPERATION(available with 07 and higher)

In the Plan View mode the enterbutton will be used to reset theaircraft in the center of the dis-p l a y .

2.4.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

ENT


MFD Operation

w CHECKLIST OPERATION(available with 08 and higher)

In the Checklist mode the enterbutton will generally function tocheck items in the list. Thechecklist was designed such thatthe pilot can complete the entirechecklist by using only the enterb u t t o n .

Normally, pressing the ‘ENT’ but-ton will cause an uncheckedchecklist line to be checked andthe cursor to advance to the nextunchecked line. At the end of apage pressing the ‘ENT’ buttonwill cause the cursor to advanceto the next page (if available) andto check the first unchecked lineon that page. If no uncheckeditems exist between the cursorposition and the end of the list,the cursor is placed on the firstunchecked page which refer-enced the specific list.

TEST/REFERENCE

Will function identical to, but inde-pendent of, the one on the ED461, CP 467 or CP 468.

With checklist active, this buttonwill cause a checklist "help" pageto be displayed on the MFD.

Refer to section 2.1 EHSI OPER-ATION for detailed information.

CHECKLISTSELECT

(available with 08 and higher)

This button is not functional inSoftware 04, 05, 06 or 07.

Pressing the checklist button willdisplay the root page of thechecklist. If an emergency dis-crete is active, pressing thechecklist button will display theemergency page

TCAS ONLYSELECT


This button is not functional inSoftware 04, 05, 06 or 07.

The TCAS ONLY button will tog-gle the MFD display between theTCAS only presentation and thepreviously selected mode.

TERRAIN SELECT


This button is not functional inSoftware 04, 05, 06, 07, 08, 09,10, 11, 12 or 13.

The TERRAIN SELECT buttonwil l toggle the MFD displaybetween the Terrain presentationand the previously selectedweather mode.

2.4.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

TST REFCRS SEL

CRS

BRT


1-2

CHKLIST

TCASONLY


Abbreviated Operations

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 3.1

Figure 3.1ED 461 EHSI CONTROL PANEL OPERATION

Section 3mp 9/9/10 1:43 AM Page 3.1


SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 3.2

Figure 3.2CP 468 EFIS CONTROL PANEL OPERATION



SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 3.3

Figure 3.3CP 467 EFIS CONTROL PANEL OPERATION



SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 3.4

Figure 3.4CP 469 MFD CONTROL PANEL OPERATION



SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 3.5

Figure 3.5CP 469A MFD CONTROL PANEL OPERATION


EHSI Displays

4.1.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

The EFS 40/50 uses a defined color set which aids the pilot in inter-preting displayed information. A brief summary of the color set is asf o l l o w s :

For an example of the color usage, refer to figure 4.1.3 at the back ofthis section, Typical EFS 40/50 EHSI Color Displays.

EHSI DISPLAYS

EFS 40/50 COLOR STANDARDS

WarningsCautions/Abnormal SourceScales and associated figuresOn-side approach and navigation dataCross-side NAV dataOn-side non-approach navigation data (LNAV)On-side commanded dataCross-side commanded dataSelected heading, DME HOLD annunciationSelected source

Selected active route/flight planCross-side selected active route/flight planHeld DME distance display

RedYellowWhiteGreenYellowCyanGreenYellowOrange

GreenYellowWhite

Matches NAVdata color

Refer to Figures 4.1.5 and 4.1.6while reviewing STANDARDEHSI DISPLAYS.

NORMAL COMPASS CARD

360° rotating white compassscale indicates aircraft headingreferenced to white triangularheading index (lubber line). Thecompass scale is divided in 5-degree increments with the 10-degree divisions being approxi-mately twice as long. Fixed

45-degree index marks are adja-cent to the compass scale.

Free DG (directional gyro) opera-tion will be annunciated by a yel-low FDG (or FHDG) to the left ofthe lubber. The Free modeannunciation will only be support-ed in installations with an ARINC429 AHRS (Attitude HeadingReference System) that supportsthe Free DG (directional gyro)mode of operation via the digitaldata bus.

STANDARD EHSI DISPLAYS

Section 4.1mp 9/9/10 1:45 AM Page 4.1.1

EHSI Displays

N o t e : Software release 06changed the DG annunciationto HDG to better describe thevariety of heading sources thatmay be interfaced with theE F S 40/50, ie. INS, AHRSand conventional gyros.

Dual selectable compass inputsare provided for. If a secondcompass system is installed, thecross-side source is selected bymeans of a remote mountedswitch. Once the alternate com-pass source has been selected,a yellow DG1 (HDG1) or DG2(HDG2) will be displayed to theleft of the lubber line.

In a dual EFS 40/50 installationwith software release 04 or 05, ifboth systems use the sameheading source, annunciationswill appear on both EHSI’s alert-ing the pilots they have the samesource selected. The EHSI that isusing its normal heading sourcewill annunciate a yellow “DG”with a yellow box around it toindicate that its primary headingsource has been selected for useon the other EHSI. The EHSI thatis using its alternate headingsource will annunciate a yellow“DG1” or “DG2” as applicablewith a yellow box around it toindicate the heading sourcebeing used is the same onebeing used by the other EHSI.For example, if the co-pilot wereto select his alternate headingsource, heading #1, “DG1” wouldappear with a box around it onthe co-pilot’s EHSI and DG wouldappear with a box around it on

the pilot’s EHSI.

In a dual EFS 40/50 installationwith software release 06 andabove, if both systems select thesame heading source, a yellow“HDG1” or “HDG2” with a yellowbox around it will appear on bothEHSIs alerting the pilots that theyhave the same source selected.

Figure 4.1.1SAME HEADING SOURCE

SELECTION

When two compass sources areavailable, the two inputs arecompared for agreement. If thetwo inputs do not fall within 6-degrees of each other while inlevel flight, a yellow comparisonwarning, HDG under a double-ended arrow, will be annunciatedto the right of the lubber line.See figure 4.1.5, EHSI SYMBOLDEFINITION.

NAVIGATION SOURCEANNUNCIATION

A vertical three- or four-letteralphanumeric readout located onthe left or right side of the dis-play, depending on vertical scaleside selection, indicates the sys-tem selected as the primary navi-gation sensor.

For dual sensor installations thecross-side navigation systemmay be selected by pressing the1-2 push button. Example: pilot

4.1.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


EHSI Displays

selecting co-pilot’s navigationsystem or co-pilot selecting pilot’snavigation system. The 1-2 pushbutton will not be active if thesystem configuration does notsupport two of the same typeNAV sensors.

Green annunciations indicate anon-side approach NAV system oran enroute NAV system whichhas been approved for approachuse is being displayed. Yellowindicates the cross-side systemhas been selected. Cyan annun-ciations apply to on-side non-approach LNAV systems. Thesecolor codes apply to the NAVsource annunciator, CRS pointer,deviation bar, CRS line in MAPmode, CRS, distance, ground-speed, time-to-station, drift anglepointer and vertical deviationp o i n t e r .

Software release 06 incorporatedthe ability to interface with theTACAN version of the KNS 8 1and annunciate TCN when theK N S 81 is in the TACAN modeof operation.

If both sides select the samenavigation source, (i.e., pilot andco-pilot select VOR 2) a yellowbox is placed around the naviga-tion source annunciator on bothE H S I ‘ s .

If both sides select their respec-tive cross-side navigation source(i.e., pilot selects system 2, co-pilot selects system 1) then bothNAV source annunciators will beyellow with no yellow box.

N o t e : Same source annuncia -tion rules also apply to theheading source.

4.1.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

SYMBOLIC AIRCRAFT

The orange symbolic aircraft pro-vides a visual reference of theaircraft present position in rela-tionship to the deviation bar.

N o t e : Starting with software 08a configuration option is avail -able for the display of Fixedwing or Rotary Wing symbolicaircraft.

Figure 4.1.2SAME NAVIGATION SOURCE SELECTION ANNUNCIATION


EHSI Displays

HEADING SELECT “BUG”

A notched heading bug is manu-ally rotated around the compassscale by the heading select knobon the control panel. In the 360-degree compass mode a full timedigital readout of the selectedheading is displayed below thevertical deviation scale position.In the ARC mode, a digital head-ing readout is displayed when theheading bug is not completely inview. The digital readout will bepositioned just inside the com-pass scale on the side nearestthe heading bug. Once set, theheading bug rotates with thecompass card. The heading bugis used to indicate desired head-ing and provides selected head-ing reference for autopilot steer-i n g .

A RED X will be drawn throughthe heading bug if there is aheading select knob failure onthe EFS 40/50 control panel.

Software release 06 added theoptions, selectable at the time ofinstallation and certification, toselect one of three heading bugand digital readout color choices:

o O r a n g eo C y a no M a g e n t a

Prior to software 06, the headingbug and selected heading read-out are always orange. Theheading bug is not displayed inMFD only installations. Thisbecame an EFS system configu-ration option with software 09.

COURSE SELECT

The CRS control knob rotates thecourse pointer about the com-pass scale and sets digitalcourse readout. Once set, thecourse pointer rotates with thecompass card. The selectedcourse indicates desired naviga-tion course to be flown. Depend-ing on the LNAV (long range nav-igation) installed, the coursepointer may automatically bepositioned to the DTK (desiredtrack) when LNAV is selected asthe primary sensor. When LNAVis the selected sensor and DTKis displayed, the EFS 4 0 / 5 0course select knob is disabled.

In the upper left corner of the dis-play, an alphanumeric readoutannunciates the letters CRS andindicates the selected navigationcourse in degrees. When in aNAV map display mode, thecourse pointer will not be dis-played, the alphanumeric readoutwill be the only reference for theselected course.

N o t e : Desired track readout(DTK) generated by an LNAVsystem replaces (CRS) inLNAV mode. Some LNAVsystems may display CRS orDTK depending on the select -ed mode. MLS may displayAZ (azimuth) or BAZ (backazimuth) depending on theselected mode.

Systems with Software release05 retain (remember) the manu-ally selected course, as set bythe CRS knob, when the selected

4.1.4 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


EHSI Displays

primary NAV sensor issequenced through the LNAVposition. In previous softwarereleases, once the LNAV sensorwas displayed, its CRS or DTKwould become the selectedcourse, requiring the CRS to bereset when another primary Navsensor was selected.

This change will allow an ILSinbound course to be selectedprior to the completion of anLNAV flight leg that will be fol-lowed by an ILS approach.

In the event of a heading failure,the course pointer head and tailare removed and the coursedeviation scale is fixed in a hori-

zontal position, providing stan-dard course deviation information(CDI) referenced to the digitalCRS selected. A RED X will bedrawn through the CRS annunci-ation if there is a course selectknob failure. In the event theselected course or desired trackreceived from the LNAVbecomes invalid, a RED X willbe drawn through the digitalr e a d o u t .

Note: The above heading failuremode does not apply whenADF is the primary NAV sen -sor. (ADF D-Bar is headingdependent and is non-opera -tional without valid heading.)

4.1.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

LATERAL COURSE DEVIATION SCALEThe course deviation scale, twowhite dots evenly spaced on bothsides of the symbolic aircraft,provides a reference for thecourse deviation bar to indicatethe center line of the selected

navigation or localizer course inrelation to the symbolic airplane.

The following represents thedeviation scale for different navi-gation sources.

N o t e : D e p e n d i n gon the type ofLNAV instal led,the Lateral Devia -tion may be differ -ent. GPS lateraldeviation scale isfor TSO C129capable unitsonly. SW 15 andlater acceptsC145/C146 equip -ment var iabledeflection values.

LATERAL DEVIATION SCALE(Aircraft Displacement)


EHSI Displays

LATERAL COURSEDEVIATION BARThe course deviation bar repre-sents the center line of theselected navigation or localizerc o u r s e .

If invalid or failed primary NAVsensor data is received thecourse deviation bar and scaleare removed and a RED Xa n n u n c i a t e d .

Beginning with software 09, thedeviation bar and scale aredecluttered without displaying aRED X when the deviation infor-mation is provided in ARINC 429format with a status of NO COM-PUTED DATA (NCD). The REDX will still be displayed if the datais missing or invalid.

TO/FROM INDICATOR A white filled triangle near thecenter of the EHSI pointingtoward the head (“TO”) or tail(“FROM”) of the course pointerindicates whether the selectedcourse is TO or FROM the sta-tion or waypoint. The TO/FROMannunciator is not displayed dur-ing ILS/MLS operation or whenan invalid NAV signal is received.

D I S TANCE, GROUNDSPEEDand TIME-TO - S TAT I O NThe EFS 40/50 provides up tothree distance displays — onefor each selected navigationsource (if distance information isavailable from that source).

The readout for the primary NAV

source is shown in the upperright corner. This readout willalso show aircraft groundspeedand Time-to-Station/Waypoint.Both are displayed simultaneous-ly with software 08 and higher.

The distance readout for naviga-tion source 1 (the single-barbearing pointer) is in the lowerleft corner below the navigationsource annunciator. The readoutfor navigation source 2 (the dou-ble-bar bearing pointer) is in thelower right corner below the navi-gation source annunciator.

These readouts show distance(in nautical miles) to the selectedstation when in VOR, TACAN,ILS or MLS mode. When inLNAV, RNAV or GPS mode, dis-tance to the waypoint is shown.

Each of these three distancereadouts is displayed in the samecolor as the source annunciatorand pointer with which it is asso-c i a t e d .

With software 04/05/06/07 theE F S 40/50 will display groundspeed up to 999 KTS, Time-To-Station up to 511 minutes anddistance up to 4,095 nauticalmiles. In most cases, the DMEwill be the limiting factor in dis-playable data.

With software 08 and higher, theE F S 40/50 will display groundspeed up to 999 KTS, Time-To-Station up to 8:31 (H:MM univer-sal format) and distance up to4,095 nautical miles. Time-To-Station is displayed immediatelybelow and at the same time as

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ground speed. In most cases,the DME will be the limiting factorin displayable data.

When DME HOLD is selected,the distance displayed is white incolor. “H” follows GS/TTS field(GS field after software 08) in theupper right corner. During HOLDthe displayed distance probablywill not be associated with theselected bearing pointer. Formore information on DME HOLD,refer to the DME HOLD sectionwhich follows.

o The bearing sensor selectionfunction offers an optional DME-only display feature in the cycle.If the DME-only option wasselected at the time of installationand certification, DME #1 and #2information may be independent-ly selected for display in the bear-ing pointer information area with-out displaying a bearing pointer.

To annunciate operational Dis-tance Measuring Equipment(including those associated withan RNAV or LNAV) which hasnot acquired lock on to theselected station, dashes of thesame color as the sensor annun-ciator will be placed in the dis-tance data field. If the equipmenthas failed or information is notbeing received by the EFS40/50, the dashes will be Red. Inboth cases the NM annunciationwill remain and the KT/TTS willbe removed if normally dis-p l a y e d .

DUAL MULTI CHANNELDME INSTALLATIONS

o Software 07 incorporated thecapability to interface with a vari-ety of multi channel DME,VOR/ILS and MLS installations,and perform automatic reversionin the event of a failed DME sen-sor in certain installations.

For those installations supportingthe automatic reversionary mode,the system can experience aDME failure without the pilot orcopilot loosing the normal dis-tance presentation. For exam-ple, i f the number one DME,whose primary job is servicingthe number one VOR/ILS, failed,the symbol generator would lookto DME number two for VOR/ILSDME number one distance infor-mation. If the information waspresent, a yellow boxed DME 2would be displayed in the upperright hand corner of the numberone EHSI and MFD. This alertsthe pilot he is now getting dis-tance information from the copi-lot’s DME. A green boxed DME2 is placed in the same locationon the number 2 EHSI alertingthe copilot the pilot is getting dis-tance information from his DME.These boxed DME annunciationsuse the same display field as theTime-to-station (or Time-to-way-point) after software 08. Theabnormal DME annunciation haspriority over TTS/TTW.Note: The variety of the various

DME installations is numerous,and therefore may be neces -sary to refer to the aircraftflight manual supplement forspecific operation of a giveninstallation.

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DME HOLD

When DME HOLD is selected,the DME distance and annuncia-tor color will change to white andremain that color until HOLDfunction is released. The sensoridentifier (ADF, VOR ILS, etc)shall retain the original assignedcolor, this color difference indi-cates there may be no relation-ship between the two fields. TheHOLD function is additionallyindicated by an orange letter “H”which is displayed directly belowand to the right of the distanceinformation. DME groundspeedand time-to-station will not be dis-played when DME HOLD isactive. If the DME providesARINC 429 frequency informa-tion, the HELD FREQUENCY willbe displayed in white wheregroundspeed was previously dis-p l a y e d .

DME HOLD for BEARINGPOINTER/DME #1 and BEAR-ING POINTER/DME #2 will oper-ate as described above, butHELD FREQUENCY informationwill not be displayed.

Once the DME is placed inHOLD, its distance will continueto be displayed and will not beaffected when bearing pointersand primary NAV sensors arechanged unless the selectedsensor provides range informa-tion such as an LNAV, RNAV orMLS. In these cases, the heldinformation will be replaced withthe selected sensor’s range infor-m a t i o n .

The bearing pointer sensorannunciators located in the lowerright and left corners of the dis-play also provide range informa-tion when the selected bearingsensor has associated range. Ifthe associated range informationis provided by DME, then therange information and NMannunciation will change from thenormal light blue or magentacolor to white and be followed byan orange “H” when HOLD isactivated. If an ADF is theselected bearing pointer sensorand the DME assigned to thatside is placed in HOLD, the largeADF annunciation will reduce insize as the white held DMErange information and orange “H”is displayed below it.

Please note that the range infor-mation being displayed is not ref-erenced to the ADF, but to what-ever channel the DME was tunedto when the pilot placed it inH O L D .

DME HOLD will not functionwhen an LNAV or RNAV is theselected sensor, and is notallowed when MLS or TACAN isthe selected primary sensor. Theassociated distance field is usedto display waypoint distance ordistance to the MLS or TACANs t a t i o n .

N o t e : It is important to remem -ber that once a DME is placedin HOLD it probably is not ref -erenced to any VOR/ILS sen -sor being displayed. Holdremoves the dependency of

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EHSI Displays

the DME to the VOR/ILS con -trol head. It is, therefore, up tothe pi lot to recognize thatwhen the DME distance infor -mation color changes to whiteand the orange “H” is dis -played, the distance presentedis probably not paired to theVOR/ILS control head frequen -cy.

Hold is a pilot selected mode ofoperation for the DME. Once thepilot selects hold, it is the pilot’sresponsibility to remember wherethe DME is HELD.

DME and DME HOLD operationmay vary greatly from installationto installation. This variation inoperation is directly dependentupon the number and types ofDME installed. To best under-stand how these two functionswork in a particular installation,refer to the aircraft flight manualsupplement or contact theinstalling agency for a detailede x p l a n a t i o n .

BEARING POINTER

The rotating light blue single bar#1 Bearing Pointer points in thedirection of the selected bearingsensor ground station (or way-point when in the LNAV or RNAVm o d e ) .

The rotating magenta double bar#2 Bearing Pointer performs theidentical function for #2 bearingsensor systems.

If the selected bearing sensor is

not receiving valid data, the Bear-ing pointer assigned to that bear-ing source will not be displayedand a RED X wil l be drawnthrough the selected bearingsource annunciator at the bottomleft or right of the display. Theassociated distance data willremain displayed if valid.

If the compass card is MAG(magnetic) referenced, TRUEbearing sensor pointers, such asLNAV, may be displayed if validmag var (magnetic variation) isprovided to the EFS 40/50. Inthis case, the TRUE sourcedbearing pointer information willbe converted to MAGNETIC ref-erence.

If the compass card is TRUE ref-erenced, MAGNETIC bearingsensor pointers, such as VORand ADF, may be displayed ifvalid mag var (magnetic varia-tion) is provided to the EFS40/50. In this case, the MAG-NETIC sourced bearing pointerinformation will be converted toTRUE reference.

In most cases mag var is provid-ed by an LNAV. In a singleLNAV installation the EFS 4 0 / 5 0wil l use the single mag varsource to compute display cor-rection for both number 1 andnumber 2 sensors. In dual LNAVinstallations with an LNAV select-ed as the primary nav source,that LNAV is the only source ofmag var. In dual LNAV installa-tions with a primary nav sourceother than an LNAV, the mag var

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will be supplied only by the on-side LNAV with software prior to08, but beginning with SW 08,the off-side LNAV is used as asecondary source of mag varinformation.

If valid mag var is not available,those bearing pointers displayedwith mag var correction will beremoved and a RED X is drawnthrough the sensor annunciatorin the lower right or left corner.

In the event a heading failureoccurs, a heading flag will be dis-played to the pilot, the compasscard will remain active to followinput form the compass system.Bearing pointer information willcontinue to be displayed. TheE F S 40/50 will process the bear-ing information and present allbearing pointer informationexcept ADF referenced to thecompass card, the ADF bearingpointer will be relative to the noseof the aircraft and lubber line onthe EHSI.

E X A M P L E :

N o t e : Refer to f igure 4.1.4BEARING POINTER OPERA -TION WITH LOSS OF HEAD -ING when reviewing thisexample.

Aircraft actual mag heading is030 degrees, but EHSI com -pass is failed and displays anincorrect heading of 090degrees — 60 degrees greaterthan actual. Bearing pointernumber one is referenced to aVOR station and is pointing to

120 degrees on the compasscard. Bearing pointer numbertwo is referenced to an ADFstation and is pointing to 180degrees on the compass card.

When interpreting bear ingpointer number one in thisexample, remember that VOR,TCN, RNV, OMG, FMS, GPSor LOR indications are refer -enced to the compass card.Therefore, since bearing point -er number one is pointing to120 degrees on the compasscard, the correct course to theVOR is 120 degrees. Like -wise, since the tail of bearingpointer number one is on the300-degree mark on the com -pass card, the correct bearingfrom the VOR is 300 degrees.

Caution: Do not assume thatthe course to the VOR is 30degrees to the right of the air -craft nose. Although the bear -ing pointer is pointing 30degrees to the right of the lub -ber line, you must rememberthat the pointer in this instanceis referenced to the compasscard — not the lubber line orsymbolic aircraft.

When interpreting bear ingpointer number two in thisexample, remember that ADFindications are referenced tothe lubber line and the symbol -ic aircraft. They are not refer -enced to the compass card.The compass card can beused only to help you deter -mine ADF relative bearing.

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Likewise, the tail of the pointeris at 360. Indicated headingon the compass card is 090.So relative bearing is 90degrees left. Actual heading is30 degrees. So actual bearingfrom the NDB is 90 degrees tothe left of 30 degrees, which is300 degrees.One other thing to note aboutADF indications with failedheading is this: The ADFbearing pointer points to thestation relative to the symbolicairplane. Since the bearingpointer in the example is point -ing straight off the right wing ofthe symbolic airplane, you mayconclude the station is straightoff the right wing of the actualairplane.

MAGNETIC/TRUEHEADING ANNUNCIATIONSTo the left of the lubber line awhite “T” will be displayed whenthe compass card is in the truemode of operation or left blankwhen in magnetic mode.

Magnetic compass heading isautomatically displayed unlessTrue heading is selected by aremote switch or when theselected primary NAV sensor isan LNAV and it selects the Truemode of operation. Valid magvar must be present before Trueheading can be selected by theL N A V .

RADIO ALTITUDEBeginning with software version07, radio altitude provided by acompatible radio altimeter may

be displayed on the EHSI ininstallations that do not includeEADI displays. (The SG must beconfigured for EHSI only opera-tion). This radio altitude will bedisplayed in white with a “ft” suffixnear the bottom of the EHSI onthe side opposite the selectedNAV sensor annunciation. Deci-sion height (DH) select and DHalert annunciations are not pro-vided on the EHSI.

The displayed altitude range isfrom -20 ft to 990 ft in 5 ft incre-ments below 100 ft and 10 ftincrements above 100 ft for EFSsoftware 07 and 08. Beginningwith 09 software, 5 ft incrementsare provided up to 500 ft.

The radio altitude is declutteredat or above 1000 ft. Three reddashes will be displayed whenthe radio altitude is invalid andthree white dashes are displayedfor values below -20 ft or datawith a No Computed Data (NCD)s t a t u s .

N o t e : 20 ft is the minimum alti -tude displayed when a KRA10A is the configured radioaltimeter.

GLIDE SLOPE/VERTICALNAVIGATIONWhen the selected primary NAVsensor is ILS, MLS or LNAV withVNAV selected, a stationarywhite vertical deviation scale willappear on the right or left side ofthe EHSI display as configured atthe time of installation and certifi-cation. This scale provides a ref-

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erence for the vertical deviationpointer. The deviation pointermoves in relation to the scale toindicate glide path center withrespect to aircraft position.When the selected primary NAVsensor is an on-side ILS, MLS, orLNAV in the approach mode, thevertical deviation pointer is greenin color. If an off-side sensor isselected for display, the deviationpointer changes to yellow alertingthe pilot that he has selectedother than his on-side NAV sen-sor. A cyan ponter is displayedfor VNAV provided by an on-sideLNAV in the enroute mode. Fullscale VNAV deviation represents±1000 feet when provided by anLNAV in the enroute mode. Priorto 08 SW, full scale VNAV devia-tion represents ±500 feet whenprovided by an LNAV in theapproach mode, however after08 SW, this scaling can be con-figured to be ±1000, ±500, ±250,or ±200 feet.

If the selected sensor is ILS, a“GS” will be displayed in the verti-cal pointer. When MLS is theselected sensor, this annuncia-tion will be “GS” for SW 06 and07, but beginning with SW 08,either “GS” or “GP” (for GlidePath) may be annunciated.When MLS is the selected sen-sor, the selected glide path angleis displayed above the glideslopedeviation scale. If VNAV is dis-played “FT” (feet) or “ANG”(angle) wi ll be annunciatedabove the vertical deviationscale. “VN” will be annunciated ifthe selected sensor is an LNAVwith VNAV selected. Beginning

with SW 15, during a GPSapproach the vertical scale willdisplay the vertical annunciatoras “GP”.Additional configuration optionsselectable at the time of installa-tion and certification:

o Declutter GS on Back Course,allows the vertical deviation scale tobe in view at all times or only whenthe selected course is within 105degrees of the aircraft heading.

Vertical Scale Side, allows thevertical deviation scale to be dis-played on either the:o Right or o Left side of the EADI and

EHSI display.VNAV Approach ModeS c a l i n g, a configuration optionadded by software 08, allows thefollowing values for a full scaleVNAV approach deviation.o 1000 feeto 500 feeto 250 feeto 200 feet

Vertical Pointer Type, incorpo-rated in software 06, allows thevertical pointer to be displayed asone of three optionso

o

o

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GS

GS

GS


EHSI Displays

Vertical Pointer Annunciationfor MLS A configuration optionadded by software 08, allows thechoice of two pointer annuncia-tions when an MLS is the select-ed primary NAV sensor.

o G SoG P

For a particular installation, referto the Aircraft Flight Manual Sup-plement to determine the EFS40/50 VNAV scale factors.

If invalid or failed glide slope orVNAV data is received, the verti-cal deviation bar and scale areremoved and replaced with aRED X annunciation.

Beginning with software 09, thevertical deviation bar and scaleare decluttered without displayinga RED X when the deviationinformation is provided in ARINC429 format with a status of NOCOMPUTED DATA (NCD). TheRED X is still displayed for invalidor missing data.

WIND VECTORo When the aircraft is equippedwith the appropriate LNAV equip-ment, an optional full time windvector indicating approximatewind direction and speed may bedisplayed in white in the upperleft corner below the selectedcourse. Wind vector informationwill be available only when validdata is provided by the LNAV.The information provided by thisvector is advisory only. It is NOTintended for use during approachas critical flight data because it

will become inaccurate duringaltitude changes.

In single LNAV systems the windvector data may be displayed onall EHSI displays. In dual LNAVinstallations with an LNAV select-ed as the primary nav source,that LNAV is the only source ofwind vector data. In dual LNAVinstallations with a primary navsource other than an LNAV, thewind vector data will be suppliedonly by the on-side LNAV withsoftware prior to 08, but begin-ning with SW 08, the off-sideLNAV is used as a secondarysource of wind vector informa-t i o n .

N o t e : If the selected LNAV isconfigured as a CrouzetOmega, the wind vector will bedisplayed as the standardmeteorological wind symbol.

DRIFT ANGLE POINTER( LNAV only)The drift angle pointer is anoptional hollow cyan (green oryellow in approach mode) trian-gular pointer which is generatedby some LNAVs and rotatesabout the outside of the compassscale. Referenced to the lubberline, the drift angle pointer repre-sents drift angle left or right of theaircraft heading. With respect tothe compass scale, the driftangle pointer represents aircraftactual ground track.

o The optional drift angle pointermay be displayed only when theLNAV is selected as the primaryNAV source and valid information

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is present. If the pointer informa-tion becomes invalid it will beremoved from the display.

o An additional configurationoption was added with software09 allowing a full time display ofthe drift angle pointer. This allowsthe drift angle pointer to be dis-played when the selected prima-ry NAV source is not an LNAVand is intended to be used withthe “Drift Angle Track” featureadded to the weather radar inter-face by EFS software 09. Seethe section on Radar operationfor a detailed description.

LNAV MODEANNUNCIATIONS

o A configuration option selec-table at the time of installationand certification allows the LNAVmode annunciators to be dis-played above the three letter ver-tical source annunciator “FMS”,“LOR”, or "GPS". The followingannunciations will be displayed inthe priority listed:

• MSG white flashing for fiveseconds and then solid • D R white flashing for fiveseconds and then solid • W R N white flashing for fiveseconds and then solid (deletedin software 07 and higher)• W P T white flashing for fiveseconds and then solid • H D G white • X T K white • A P R w h i t e

Refer to Figures. 4.1.7 and 4.1.8while reviewing 360 MAP DIS-P L A Y S .

The EFS 40/50 provides twobasic map formats, a 360-degreemap display about the aircraftand an approximately 85-degreesectored map display in front ofthe aircraft. Information whichmay be displayed includes way-points, navaids, airports andweather radar information. Thetype and amount of data present-ed on the map will depend on theinterfacing equipment. Whencoupled with a compatible LNAV,such as the BENDIX/KING KNS660, GNS XL S or KLN 90B, theEHSI can show up to 15 mapsymbols. These will include allflight plan waypoints that arewithin the selected display range.

In addition, the pilot can chooseto display either navaids or air-ports that are located off theflight-planned route. Up to 10navaids or up to 4 airports can bedisplayed as long as the totalnumber of map symbols does notexceed 15.

In software version SW 06, up to10 airports may be displayed.

In addition to the above, the #1and #2 bearing pointers can beoverlayed to indicate the directionand distance to two additionalnavaids or waypoints.

Waypoints referenced to theselected VOR may be displayed

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360 MAP DISPLAYS


EHSI Displays

when coupled with a simpleRNAV, such as the BENDIX/KING KNS 81. The simplestmap data is provided by plottingmap symbols referenced to theaircraft using bearing and dis-tance from the select bearings e n s o r .

Beginning with software 10, spe-cial waypoints without symbolsare accepted by the EFS whichmay be used to display flight planlegs without the waypoint sym-bols at the connecting points.These waypoints are supplied bysome LNAV’s for search patternflight plans.

Note: The following will addressonly those areas of the EFS40/50 map mode which are dif -ferent from the standard com -pass presentations.All map presentations providea traditional CDI display.

MAP 360 COMPASS CARD

The operation of the compasscard remains the same in theMap mode as in the standardEHSI display. However, the out-side of the compass card nowperforms a secondary function bybecoming the outer range ring forthe Map display.

SELECTED COURSE

The alphanumeric course selectreadout in the upper left corner ofthe display functions the same inthe map mode as in the standardEHSI mode. The standard EHSIselected course pointer, to/from

pointer, deviation bar and devia-tion scale are removed from with-in the compass card display.When the primary NAV sensorprovides distance and bearinginformation the selected coursepointer is replaced with thecourse line. If the primary NAVsensor “TO” or “FROM” waypointor VOR is within the selectedmap range, a movable courseline is drawn through its center.As the selected course ischanged, the course line willrotate about the referenced point.If the selected primary NAV sen-sor is an approach on-side sen-sor, the inbound “TO” course lineis green and the outbound“FROM” course line is white. Ifthe selected primary NAV sensoris LNAV or enroute RNAV theinbound “TO” course line is cyan(green in approach mode). Anytime the cross-side sensor isselected as the primary NAVsensor the inbound “TO” courseline is yellow.

If the primary NAV sensor dis-tance or bearing informationbecomes invalid the NAV symboland course line will be removed.“NO MAP” will be displayed toalert the pilot that insufficient datais present to calculate and plotthe primary NAV sensor map.“NO MAP” will also be displayedif the selected primary NAV sen-sor, (e.g. ILS, ADF), does notprovide distance and bearinginformation. The lateral deviationscale will remain as long as validbearing or deviation informationis present.

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MAP COURSEDEVIATION INDICATOR

A stationary white scale alongthe bottom center of the displayprovides reference for the coursedeviation bar to indicate the posi-tion of the aircraft in relation tothe selected navigation course.This course scale provides aconventional CDI (course devia-tion indicator) presentation.When LOC is selected while in amap mode, Back Course annun-ciation and CDI needle reversalis provided when the selectedcourse is 105 degrees from theaircraft heading (results in a fly tosituation). “BC”, in green, (yellow“BC” i f cross-side sensor isselected) is annunciated left ofcenter on the lateral deviation .

TO/FROM

To the right of the alphanumericCourse Select a white “TO” or“FR” will replace the standardEHSI TO/FROM pointer when innon-ILS map modes.

BEARING POINTER

While in the map modes stan-dard EHSI bearing pointers aredisplayed when the selectedbearing source does not havedistance associated with it orwhen the distance is greater thanthe selected map distance. Oncethe bearing source falls withindisplay distance the bearingpointer is removed and the asso-ciated map symbol is displayed. The #1 system map symbol will

be displayed in light blue and the#2 will be displayed in magentaas are the standard bearingpointers. If bearing or distanceinformation becomes invalid, themap symbol will be removed. Ifonly the distance informationbecomes invalid, the map symbolwill be removed and replacedwith the standard bearing pointer.

Note: See BEARING POINTER,under STANDARD EHSI DIS -PLAYS in this section fordetails on the display of Mag -netic bearing pointers whenthe compass card is True ref -erenced and the display ofTrue bearing pointers whenthe compass card is magneticreferenced.

REFERENCE WAYPOINT

When the joystick is interfaced toan EFS 40/50 system, it can beused to generate and move asingle Reference Waypoint onthe display unit. This referencewaypoint can then be enteredinto the KNS 81, KNS 660, KLN88, or any other LNAV using anappropriate GAMA 429 inter-face. The KNS 81 must havethe graphic output bus.

With an LNAV, RNAV, (or KNS81 configured as a NAV) select-ed for the primary nav sensorand during display of a NAV MAPon the EHSI, initial movement ofthe joystick will create a refer-ence waypoint ahead of the air-craft on the half range ring at thecurrent heading. This will be truefor both HSI and ARC map dis-

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play formats. The referencewaypoint will be a standard whitewaypoint symbol. Movement ofthe waypoint will be in any of theeight directions commanded bythe joystick. The rate of move-ment will start off slow andincrease in speed in two steps.Return of the joystick to its cen-ter, off position at any time willreset the rate of movement to theslowest speed. The referencewaypoint location on the displayscreen and its rate of movementrelative to the display screen willbe independent of the displayrange selected. The referencewaypoint is not allowed to exit thecompass. When an LNAV isselected as the primary naviga-tion source, Lat/Lon coordinatesof the reference waypoint will bedisplayed in the lower center ofthe display. When a KNS 81 isthe active primary navigationsource, and it is not in the ILSmode, radial and distance of thereference waypoint from thenavaid in use by the KNS 81 willbe displayed instead of Lat/Loncoordinates. The reference way-point position information can betransferred to the LNAV or KNS81 that is selected as the primarynavigation sensor, by pressingthe ENTER button while the ref-erence waypoint and its coordi-nates are displayed. The coordi-nates of the reference waypointwill remain displayed for at least10 seconds and disappear fromthe display within 15 secondsafter activating the ENTER but-ton. If the reference waypoint isnot moved for 20 seconds, it willdisappear from view and will re-

appear in the same location rela-tive to the display screen (inde-pendent of range selection) thenext time the joystick is activated.However, a change of primaryNAV sensor or display modes willreset the invisible reference way-point location to its initial startingp o s i t i o n .

Note: Systems with an MFD canhave a joystick on the CP469A MFD control panel or astand alone joystick. Addition -al joysticks for the pilot or co-pilot normally wil l not beinstalled. Systems without anMFD may have up to two joy -sticks that are completely inde -pendent of each other; one forthe pilot and one for the co-pilot. The pilot’s joystick willnot be allowed to create ormove a waypoint on the co-pilot’s EHSI, and any waypointcreated by the pilot can beloaded only into the #1 RNAVor #1 LNAV. Conversely, theco-pilot’s joystick will not beallowed to create or move awaypoint on the pilot’s EHSI,and any waypoint created bythe co-pilot can be loaded onlyinto the #2 RNAV or #2 LNAV.

RANGE RING

A light blue range ring locatedhalf way between the center ofthe symbolic aircraft and the out-side of the map compass scaleaids in determining distance ofradar returns and/or position ofnavaids in relation to the aircraft.Off the right wing of the symbolicaircraft, adjacent to the range

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ring is the range ring distance.The range ring represents halfthe distance to the outer rangering of the compass scale. Theavailable ranges, selectable fromthe EFS 40/50 are 5, 10, 20, 40,80,160, 240, 320 and 1000 nm.

N o t e : Systems which have theR D R 1400 interfaced with theE F S 40/50 will display weath -er ranges of .5, 1 and 2 NM.However, the NAV MAP fea -ture is not supported on theseshorter ranges.

360-DEGREE MAPWX RADAR (IF EQUIPPED)Refer to Figure 4.1.7 whilereviewing this section.

If a compatible ARINC 708weather radar such as theBENDIX/KING RDR 2000 orRDS series is installed, weatherinformation may be selected fordisplay. When selected, weatherinformation wil l transparentlyoverlay the existing navigationdata. Light blue dotted lines rep-resent the weather radar scanl i m i t s .

Depending on the installation, theE F S 40/50 may act as a weatherradar range controller or as asimple remote display when theEHSI has weather selected andmatches the radar range. As adisplay only, if weather is select-ed for display and the EHSI maprange does not match the select-ed weather radar range “WXFLT” will be annunciated in theweather radar fault/warning posi-tion. As a range controller, if the

selected range does not matchone allowed by the radar, “WXFLT” will be annunciated in theweather radar fault/warning posi-tion. When the 1000 NM rangeis selected “RANGE” is displayedand the weather radar is placedin standby. If the EFS 40/50 isthe only display media for theweather radar, the radar will beplaced in standby when weatheris not selected for display.

Note: EHSI installations with theBENDIX/KING RDR 2000 orRDS series radar provide dualrange selection by allowing theradar indicator and EHSI ordual EHSIs to select indepen -dent ranges. Only one sourceof radar mode, tilt and gain issupported. When the rangesselected on the two controllingindicators do not match, theweather presentation will beupdated on alternating sweepsof the radar antenna. Exam -ple: if pilot’s EHSI is updatedon the right sweep then theradar indicator will be updatedon the left sweep or vice versa.In installations capable of pro -viding weather information onthree displays, the displaywithout radar range controlmust match one of the control -ling displays in order to pre -sent weather. If the rangedoes not match, “WX FLT” willbe annunciated in the weatherradar fault/warning position.

Four data lines are reservedbelow the primary NAV sensorsource annunciator to displayradar information. The first line

4.1.18 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


EHSI Displays

displays special performancefeature annunciations such asARL (automatic range limiting).The second line annunciates thestandard radar modes WX, WXAor MAP. The third line provides adigital readout of tilt angle dis-played in tenths of a degree pre-ceded by an arrow pointing up ordown to indicate tilt direction. IfAuto Tilt is activated, an “A” willfollow the tilt arrow. The fourthline will display radar faults andwarnings. The radar faults areprioritized. When more than onefault or warning occurs the onewith the highest priority will bed i s p l a y e d .

Target Alert is a feature providedby the RDR 2000 weather radarthat is fully supported by EFSwith software version 10. A white“TGT” annunciation in the weath-er radar failure/warning field indi-cates that the target alert featureof the RDR 2000 is enabled.When a target is actually detect-ed that satisfies the conditions fora target alert, the white “TGT”changes to a yellow “TGTALRT”and an arc shaped symbol is dis-played at the top center of theweather display. Consult theRDR 2000 pilot’s guide for mored e t a i l .Note: Wx gain must be max and

the ART must be scanninghorizontally before the TargetAlert feature is enabled. TargetAlert is n o t enabled in the VPmode.

EFS with 09 software interfacedto the RDR 2000 will display“TGTALRT” in white and the tar-

get alert symbol during an activetarget alert, however “TGT” willnot be displayed to indicate theenabled condition.

A yellow dashed line, originatingat the symbolic aircraft andextending to the edge of thecompass card, appears on theweather display when either thetrack left or track right button ispressed on the radar controlpanel. The track line will be auto-matically removed within 15 sec-onds after the button is released.

RDR 1400WEATHER RADARA complete interface to the RDR1400 Weather Radar becameavailable with the release of EFSsoftware version 09. This inter-face requires an indicator to beused as the source of all radarcontrol data except for rangewhich is selected on the EFScontrol panel. All RDR 1 4 0 0ranges are supported including2.0, 1.0, and 0.5 nm. All weatherand search primary modes, thebeacon secondary mode, andRDR 1400 faults are annunciatedin the radar information fieldsbelow the primary NAV sensorannunciation on the EHSI orMFD. The primary and sec-ondary modes are annunciatedas shown in the following table:

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EHSI Displays

All standard beacons (Type A)are displayed as two white arcsseparated by 3.6 to 13 nm (sepa-ration distance determined bybeacon ID code). All DO 172(Type B) beacons are displayedas two white framing arcs 1.2 nmapart with one to four additionalbeacon ID arcs between the twoframing arcs. When a beacon isidentified, its ID code preceededby an “A” or “B” to indicate bea-con type is displayed in blue atthe beacon location on the EFSweather display just beyond theclosest white arc.

RDR 1400 beacon and searchgains, and antenna tilt value arenot annunciated on the EFS.

N o t e : A limited interface to theRDR 1400 is provided withEFS software versions before09. TEST, STBY, and WX arethe only modes annunciated.Beacon and Search modes arenot annunciated. Beacon sym -bols are displayed as whitearcs at the proper location, butwithout an ID number.

LIGHTNING DETECTION

Up to 63 grey colored lightningcell symbols can be displayed onthe EHSI or MFD displays whenprovided by a compatable light-ning sensor. Unlike weatherradar information, lightning datamay be presented in all 360degrees of display area. Rangeselection for all lightning data dis-played on EFS is controlled bythe EFS control panel. The EFSwill display the following symbols

depicting three different levels oflightning intensity:

Lightning information will only bedisplayed while weather is select-ed for display on the EFS. Someversions of Radar Control Panels(RCP) have a lightning selectbutton (see section 2.3) whichwill alternately select and de-select lightning for display, how-ever when selected, the lightningdata will be in addition to theweather radar information if bothare provided. The weather radarmay be placed in standby if onlylightning information is desired.

A single lightning data field islocated immediately above theweather radar data fields. Threeannunciations are possible in thisfield as shown in figure 4.1.8 atthe end of this section. Theannunciation “ON” preceeded bythe lightning symbol indicatesthat lightning information hasbeen selected for display and thelightning sensor is operational.The annunciation “OFF” preceed-ed by the lightning symbol indi-cates that lightning has been de-selected using the lightningselect button on the RCP. Thisannunciation is only presentedwhile a weather mode is selectedon the EFS and will not be dis-played in installations without alightning select button on theRCP. A fault condition is indicat-

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EHSI Displays

ed by the annunciation “FLT” pre-ceeded by the lightning symbol.Possible faults are invalid ormissing 429 data from the light-ning sensor. Therefore, selectinglightning for display with powerremoved from the lightning sen-sor will cause a FLT annunciationon the EFS.

FULL TIME LNAV MAP

o Incorporated in software 05, isan option selectable at the timeof installation and certification. Itallows the LNAV map to be dis-played when the selected prima-ry NAV sensor is either an ILS orADF in the map mode.

Before software 05 or after soft-ware 05 without the full timeLNAV map configuration select-ed, when the selected primaryNAV sensor is either an ILS orADF with the map mode select-ed, the “NO MAP” message willbe annunciated since sufficientdata is not provided to create amap presentation. However, if abearing pointer sensor is select-ed which provides bearing anddistance information, an appro-priate map symbol will be dis-played if the selected map rangeis greater than the distance to thenavaid or waypoint. If the select-ed range is less, a normal bear-ing pointer will be displayed.

If the full time LNAV MAP optionis selected, the LNAV map will be

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presented when ever the select-ed primary NAV sensor is eitheran ILS or ADF with the mapmode selected. The LNAV mapwill be presented all in white toshow that the information beingdisplayed is not to be used as pri-mary navigation information. Thepurpose of the LNAV map infor-mation being presented is to pro-vide the pilot better orientationbetween his present position andintended flight plan, mainly foruse during the phase of theapproach while being vectoredfor the intercept. Primary naviga-tion must be accomplishedaccording to the raw data pre-sented by the selected primaryNAV sensor being displayed onthe lateral and vertical deviationpointers, not by the LNAV map

The LNAV map will be displayedonly if an LNAV is installed on thesame side as the selected ILS orADF primary NAV sensor and themap mode is being displayed.

N o t e : Extreme care must betaken when this mode is usednot to focus on the LNAV map.Depending on the LNAV beingused, the accuracy may be offseveral miles, providing oppo -site fly-to commands than theILS or ADF. It is a must thatthe primary NAV sensor databe the data flown.

Map not certified for primarynavigation.


EHSI Displays

Refer to Figure 4.1.9 whilereviewing ARC DISPLAYS.

The expanded sectored (ARC)format provides an enlarged dis-play of weather radar informationand increased resolution of navi-gation data due to the enlargedcompass scale presentations.

Note: The following will addressonly those areas of the EFS40/50 ARC mode which aredifferent from the standardEHSI compass or MAP pre -sentations.

HDG BUG(ALL ARC FORMAT MODES)

Heading bug operation is thesame in all modes. The only

noticeable difference in the ARCmode is that the digital orangereadout of selected heading isdisplayed only when the headingbug is not completely in view. Inthis event the heading readoutappears on the side of the com-pass scale closer to the headingbug’s hidden position.

COURSE DEVIATIONINDICATOR (EHSI ARCNON-MAP FORMAT)

The rotating white course devia-tion scale operates the same inall non-map modes. The differ-ences in the ARC modes arelocation and size: the scale ismoved to the bottom center ofthe display and is slightlyreduced in size.

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ARC (EXPANDED SECTORED MODE) DISPLAYS


EHSI Displays

The displays covered in this sec-tion are custom displays, createdat the request of specific cus-tomers to satisfy unique require-ments. Every attempt was madeto ensure these displays followedstandard EFS 40/50 colors, sym-bology and methodology. Insome cases this was not possi-ble, it is therefore, most importantto read the following informationand ensure you have a very goodunderstanding of the display andits intended use. If there are anyquestions concerning the follow-ing displays, contact the installingagency or a Honeywell factoryrepresentative for additional infor-m a t i o n .

DOPPLERRefer to Figure 4.1.10 whilereviewing the DOPPLER DIS-P L A Y .

o Incorporated in software 04,the Doppler mode, annunciatedas DOPP, provides navigationinformation from a Doppler NAVsensor. Primary use of thismode is helicopter related, withthe intended purpose of searchand rescue hover. The DOPPmode is displayed on the EHSIas dual concentric velocity andtarget range circles inside thecompass card. Cross bars repre-sent components of the aircraft’sleft/right and fore/aft velocity.

Note: The following will addressonly those areas of the EFS40/50 Doppler mode which are

different from the standardEHSI presentations.

w COMPASS CARD

The map compass card is usedin the DOPP mode, the symbolicaircraft however, is the larger oneused in the normal EHSI mode.

w DOPPLER VELOCITY BARS

Green bars, the length of thecompass card’s diameter, repre-sent the aircraft ’s velocityleft/right (Vx) and fore/aft (Vy) asreferenced to the symbolic air-craft. The intersection of the twobars provide the sum of the twovelocity components.

If the Doppler velocity informationbecomes invalid or failed thevelocity bars will be removed anda RED X will be displayed in thecenter of the compass.

w VELOCITY ANDTARGET SCALE

Two white concentric circlesinside the compass card providereference for the Doppler velocitybars and LNAV target waypoint.When used as a reference for theDoppler velocity these circlesrepresent 10 and 20 KTS withthe compass card representing30 KTS of velocity. When usedas a reference for the target way-point they represent .2 NM and .4NM with the compass card repre-senting .6 NM.

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CUSTOM (NON STANDARD EHSI) DISPLAY S


EHSI Displays

The symbolic aircraft is one sixththe size of the compass card;making it 5 KTS or .1 NM towing tips or tail and nose.

w LNAV GROUND SPEEDAND READOUT

A cyan display of ground speedinformation from the LNAV is pro-vided in the upper right corner.

If the ground speed informationbecomes invalid or failed, a cyanFMS with a RED X drawnthrough it will be displayed in thedistance location.

w WIND VECTORI N F O R M A T I O N

If an appropriate LNAV isinstalled and is providing validinformation, wind information willbe displayed in its normal loca-tion. See WIND VECTOR underSTANDARD EHSI DISPLAYS foradditional information.

w TARGET WAYPOINT

A cyan waypoint symbol will bedisplayed representing targetposition if an appropriate LNAV isinstalled and is providing validi n f o r m a t i o n .

w TENDENCY CIRCLE

A green circle, the diameter ofwhich corresponds to 5 kts, isdisplayed if an appropriateautopilot is installed and is pro-viding valid command data. Ifthe autopilot indicates winchmancontrol, the circle will be dashed.

If the autopilot fails, “COUPLER”in RED with a RED X through itwill be annunciated in the upperleft corner and the tendency cir-cle will be decluttered.

o An option selectable at thetime of installation and certifica-tion provides an interface for sys-tems that do not have an autopi-lot input. This configurationoption may also be selected if theRED “COUPLER” warning flag isnot desired when interfaced withan autopilot.

w M E M O R Y

If the Doppler NAV sensor goesinto the memory mode and advis-es the EHSI, “MEMORY” inorange will be displayed abovethe symbolic aircraft, and thevelocity bars and circles willchange to orange to alert thep i l o t .

w HEADING BUG

Software version 05 added theheading bug to the Doppler dis-play and activated the Headingdatum and analog deviation out-puts for autopilot coupling.

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EHSI Displays

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CABLE

Refer to Figure 4.1.11 whilereviewing the CABLE DISPLAY.

Incorporated in software 04, thecable mode, annunciated asCAB, provides navigation infor-mation from a cable position sen-sor. Primary use of this mode ishel icopter related, with theintended purpose of search andrescue hover, and heavy lift oper-ations. The CAB mode is dis-played on the EHSI as dual con-centric circles on the compasscard. Cross bars represent cableangular position left/right andfore/aft relative to the aircraft..

Only one cable sensor systemmay be interfaced to the EFS40/50 at a time. If more than onesystem is interfaced, it will haveto be externally switched into theE H S I .

Note: The following will addressonly those areas of the EFS40/50 Cable mode which aredifferent from the standardEHSI presentations.

w COMPASS CARD

The map compass card is usedin the CAB mode, the symbolicaircraft however, is the larger oneused in the normal EHSI mode.

w ANGLE BARS

Green bars, the length of thelarger circle’s diameter, representthe cable ’s position angle

left/right component (Px) andfore/aft component (Py) as refer-enced to the symbolic aircraft.The intersection of the two barsprovide the vector sum of the twoposition components, or actualangular position of the cable ref-erenced to the aircraft.

If the cable sensor informationbecomes invalid or failed theposition angle bars will beremoved and a RED X will bedisplayed in the center of thec o m p a s s .

w FUNNEL SCALE

Two concentric circles inside thecompass card and compass cardazimuth ring itself provide refer-ence for the cable position anglebars. A white inner circle repre-sents 6 degrees of cable deflec-tion. A yellow circle represents12 degrees. The compass cardazimuth ring represents 18degrees of cable displacement.

The symbolic aircraft is one sixththe size of the compass card;making it 3 degrees to wing tips,tail and nose.

w WIND VECTORI N F O R M A T I O N

If an appropriate LNAV isinstalled and is providing validinformation, wind information willbe displayed in its normal loca-tion. See WIND VECTOR underSTANDARD EHSI DISPLAYS foradditional information.


EHSI Displays

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w OPTIMUM CABLEPOSITION CIRCLE

A green circle, 1/12 the diameterof the compass card, is displayedif an appropriate autopilot isinstalled and is providing validcommand data. If the autopilotindicates winchman control, thecircle will be dashed.

If the autopilot fails, “COUPLER”in RED with a RED X through itwill be annunciated in the upperleft corner and the tendency cir-cle will be decluttered.

o An option (YES - NO COU-PLER), selectable at the time ofinstallation and certification, pro-vides an interface for systemsthat do not have an autopilotinput. This configuration optionalso may be selected if the RED“COUPLER” warning flag is notdesired when interfaced with ana u t o p i l o t .

w THRUST COMMAND

If the cable position sensor pro-vides the thrust command, theangle posit ion bars and 12-degree funnel circle change too r a n g e .

w HEADING BUG

Software version 05 added theheading bug to the Cable displayand activated the heading datumand analog deviation outputs forautopilot coupling. Course datumoutput is not active in this mode.

HOMING

Refer to Figure 4.1.12 while re-viewing the HOMING DISPLAY.

Incorporated in software 05, theHoming mode, annunciated asHOM, provides navigation infor-mation from a homing sensor.Primary use of this mode is toprovide the pilot left-right naviga-tion information to a beacon.The HOM mode is displayed inmuch the same way as the stan-dard EHSI. Since the homingsensor provides only left-rightguidance information, thealphanumeric selected coursedisplay is removed from theupper left corner as is the coursepointer head and tail. The devia-tion scale and bar are displayedin a horizontal manner and donot rotate with the compass card.The display provided resemblesa standard EHSI with a headingfailure. However, the compasscard will function normally.

Two homing sensors may beinterfaced to the EFS 40/50 at at i m e .

Since the basic Homing displayclosely resembles the standardsystem, all normal displayoptions are provided in the Hom-ing mode. All 360 EHSI andARC formats are operational asis the addition of bearing point-ers.


EHSI Displays

Note: The following will addressonly those areas of the EFS40/50 Homing mode which aredifferent from the standardEHSI presentations.

w LATERAL DEVIATION BAR

A green bar, the length of a stan-dard EHSI D-Bar, represents flyleft, fly right commands as refer-enced to the symbolic aircraft.

If the Homing sensor informationbecomes invalid or failed thedeviation bar and scale will beremoved and a RED X will bedisplayed in the center of thec o m p a s s .

SENSITIVITY SCALEAND POINTER

If the installed Homing sensorprovides a sensitivity output, astationary white vertical sensitivi-ty scale will appear on the right orleft side of the EHSI display asconfigured at the time of installa-tion and certification. This scale

provides a reference for the sen-sitivity pointer, which moves inrelation to the scale to indicatesignal strength being received bythe Homing sensor.

The sensitivity pointer will have“SN” displayed inside it to advisethe pilot of the type of data he ism o n i t o r i n g .

When the on-side sensor isselected for display the sensitivitypointer is green in color. Whenthe off-side sensor is selected fordisplay the sensitivity pointerchanges to yellow alerting thepilot he has select other than hison-side NAV sensor.

If invalid or failed sensitivity datais received, the sensitivity devia-tion pointer and scale arer e m o v e d .

N o t e : The scale and pointerused to display sensit iv ityinformation is the same as thatused for Glideslope and Verti -cal Navigation.

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EHSI Displays

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EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.29

Figure 4.1.3TYPICAL EHI 40/50 DISPLAY

Section 4.1 POmp 9/9/10 1:57 AM Page 4.1.29

EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.30

Figure 4.1.4LOSS OF HEADING DISPLAY


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.31

Figure 4.1.5EHSI SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.32

Figure 4.1.6EHSI SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.33

Figure 4.1.7EHSI MAP SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.34

Figure 4.1.8EHSI MAP SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.35

Figure 4.1.9EHSI ARC MAP SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.36

Figure 4.1.10EHSI DOPPLER SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.37

Figure 4.1.11EHSI CABLE SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.38

Figure 4.1.12EHSI HOMING SYMBOL DEFINITION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.39

Figure 4.1.13EHSI FAULT ANNUNCIATION


EHSI Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.1.40

Figure 4.1.14EHSI CAT II SYMBOLOGY


EADI Displays

requested. While synchronized,two white plus(+) signs will indi-cate the location of the absolutehorizon. A momentary (push on -push off) action switch must beused to request pitch offset syncor return to absolute pitch with noo f f s e t .

Note: Pitch offset sync is a fea -ture intended for use on rotarywing ar icraft only, i t is notintended for use on fixed wingaircraft. If a power reset occurs(this includes ADI Down and/orComposite modes), the pitchoffset sync will be turned offand the attitude displayreturned to normal.

In the event of a pitch or roll atti-tude failure, the pitch scale, rollscale, roll index pointer, blue skyand brown ground are removedfrom the display. Centered justbelow the roll scale, a RED“ATTITUDE FAIL” enclosed in aRED box will be annunciated.

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PITCH ATTITUDE

A moving white simulated hori-zon line rotates angularly with theroll of the aircraft and moves upand down with the pitch of theaircraft. Blue sky above the hori-zon and brown ground below thehorizon align with the horizon lineas it follows the aircraft’s pitchand roll. Pitch scale referencemarks extend above and belowthe horizon line indicating 5,10,15, 20, 25, 30, 35, 40, 45, 50, 55,60, 65, 70, 75, 80 and 90degrees. Refer to Figure 4.2.3.

o Beginning with software ver-sion 13, Pitch Offset Sync can beconfigured to allow the displayedhorizon and pitch scale to be off-set by up to 10° above or belowthe absolute source. Intended foruse in rotary wing aricraft only,the offset (10° maximum) allowssynchronization of the displayedhorizon to the current aircraftpitch when synchronization is

EADI DISPLAYS

NORMAL ATTITUDE DISPLAY


EADI Displays

ROLL ATTITUDE

The EFS 40/50 provides twooptions for displaying roll attitude.The option selected for a particu-lar installation is first determinedby certification requirements of theaircraft, and secondly by pilot pref-erence. The most common rollattitude display for four and fiveinch instruments is a fixed rollscale and movable index (skypointer). The most common rollattitude display for three inchinstruments is a moveable rollscale and fixed index (roll) pointer.The roll scale provides referencemarks at 10, 20, 30, 45 and 60degrees. To allow easier recog-nit ion of the 30, 60 and 45degree marks, the 30 and 60degree marks are longer extend-ing further into the center of thedisplay and the 45 degree markis displayed in the form of a hol-low triangle. Refer to Figure4 . 2 . 4 .

o An optional configuration item,selected at the time of installationand certif ication, allows theE F S 40/50 to declutternonessential navigation data inthe event an unusual attitude isencountered. Removal of thedata will occur i f pitch angleexceeds +30 or -20 degrees, or ifbank angle exceeds 65 degrees.Red chevrons, used to indicatethe best unusual attitude recov-ery direction (not necessarilyright side up), will appear in the

brown ground raster between 40and 85 degrees, and in the bluesky raster between 50 and 85d e g r e e s .

In the event of a pitch or roll atti-tude failure, the pitch scale, bluesky, brown ground and roll indexpointer are removed from the dis-play. Centered just below the rollscale a RED “ATTITUDE FAIL”enclosed in a RED box will bea n n u n c i a t e d .

ROLL INDICATOR

A filled white or yellow triangularpointer positioned just below theroll scale. If the Sky pointeroption has been selected at thetime of installation and certifica-tion, the roll indicator will be whiteand rotate with the pitch scale asthe roll scale is fixed. If the Rollpointer option is selected at thetime of installation and certifica-tion, the roll indicator will be yel-low and fixed in the centeredposition as the roll scale rotates.

o Sky Pointer Roll Scale

Level Attitude

20˚ Right Roll

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EADI Displays

o Roll Indicator Scale

Level Attitude

20˚ Right RollIn the event of an attitude failure,the roll indicator is removed fromthe display.

PERSPECTIVE LINES

o A display option selected at thetime of installation and certifica-tion. Orange lines extending 30and 45 degrees downward fromthe center of the horizon line pro-vide additional pilot cues in steepturns. Refer to Figure 4.2.4.

N o t e : The display of perspec -tive lines with the delta (trian -gle) shaped aircraft symbol isconsidered unacceptable bysome certification agencies.

SYMBOLIC AIRCRAFT

Located in the center of the dis-play is the fixed orange aircraftsymbol. The pitch and roll atti-tudes of the aircraft are displayedby the relationship of the fixedsymbolic aircraft and the mov-able horizon. The symbolic air-craft is flown to satisfy the com-mand cues of the flight director.

Note: The display of perspec -tive lines with the delta (trian -gle) shaped aircraft symbol isconsidered unacceptable bysome certification agencies.

The EFS 40/50 offers two sym-bolic aircraft symbols, the Bull’sEye and Delta. Selection of thesingle cue command bars willpresent a delta aircraft symbol,while selection on the double cuecommand bars will provide a tra-ditional bull’s eye aircraft symbol.

Aircraft Reference Delta

Aircraft Reference Bulls's Eye

HEADING TAPE

o An optional configuration item,selected at the time of installationand certification, allows a whiteheading tape with or without theselected heading bug to be dis-played along the top of the hori-zon line. Index marks appearevery 5 degrees with headingannunciation displayed every 30d e g r e e s .

In the event heading databecomes unavailable or invalid, astationary RED “HDG” enclosedin a RED box will be displayedabove and to the right of thesymbolic aircraft.FLIGHT DIRECTOR

4.2.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


EADI Displays

COMMAND BARS

Flight director commands are dis-played as moving green ormagenta bars when the flightdirector is engaged. Located inthe center of the EADI displayabout the fixed aircraft symbol,indicating roll and pitch requiredto satisfy the computed flightdirector commands. Switchingthe flight director “OFF” or aninvalid “FD” will cause the com-mand bars to be removed.

Options selectable at the time ofconfiguration allow the display ofe i t h e r :

o Single cue command barso Dual cue command bars o Pilot selectable between

single or dual cue via anexternal switch.

The single cue command barswill present a delta aircraft sym-bol, while selection of the doublecue will provide a traditional bull’seye aircraft symbol. Commandbar color may also be configuredas either green or magenta.

Single Cue Command Bars

Dual Cue Command BarsIn the event of a flight director

failure, the command bars areremoved and a stationary REDFD enclosed in a RED box is dis-played just below the right 60degree roll mark.AUTOPILOT/FLIGHTDIRECTOR MODEANNUNCIATION

w STANDARD 429A U T O P I L O T / F L I G H TDIRECTOR MODEA N N U N C I A T I O N

o When interfaced with anappropriate 429 digital autopilot,such as the Bendix/King KFC500, KFC 400, KFC 325 or KFC225, an optional configurationitem, selected at the time ofinstallation and certification,allows the EFS 40/50 to annunci-ate a combination of autopilotand fl ight director modes.Engaged modes are annunciatedin green along the top of the dis-play and armed modes areannunciated in white just belowthe engaged modes. Only “GS”,“GP”, “VNAV” and “ALT” will beannunciated in white, in the Verti-cal Arm 2 field immediately belowthe engaged modes. Only “GS”,“GP”, and “ALT” will be displayedin the Vertical Arm 1 field imme-diately below the Vertical Arm 2field. The engaged modes willflash for a mimimum of 5 sec-onds when disengaged andbeginning with software 0702,the engaged mode annunciationcolor will change to yellow whilef l a s h i n g .

The following tables and figuredescribe the annunciations andlocation in which they may be

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EADI Displays

4.2.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

AP/FD MODE ANNUNCIATIONS

APAltitude

AirspeedMACHVerticalspeed

AP/FD MODE ANNUNCIATIONS

AP YD

COUPLEDSTATUS MISC

MODESBANKLIMIT

CWS CMDDATA

EFSSW

YD SR HB CWS

PTRMLTRMPTCHROLLYAW

RTRMYTRM

BL30----

BL01

SASorAP

04 andabove

05 andabove

06 andabove

09 andabove

13 andabove

(KFC 500)AP SAS DNT

d i s p l a y e d .


EADI Displays

4.2.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Software release 06 added thefollowing autopilot failure warningannunciations. They are listed inorder of priority and will be dis-played in the SR field:

• PTRM RED = pitchauto/manual trim fail

• LTRM RED = lateral autotrim fail

• PTCH RED = elevator servofailure

• ROLL RED = aileron servofailure

• YAW RED = rudder servofailure

• PITCH YELLOW = elevatormistrim

• ROLL YELLOW = aileronmistrim

• YAW YELLOW = rudderm i s t r i m

Two additional failure annuncia-tions were added by softwarerelease 09 to accomodate theKFC 500.

• RTRM RED = roll auto trim fail • YTRM RED = yaw autotrim fail

The KFC 500 will use these twoannunciations instead of “LTRM”.If the flight director data becomesinvalid, a RED “FD” enclosed in aRED box will be displayed at theright center of the display.

If the autopilot has been on andthen disengaged, a RED “AP” willbe annunciated in the upper lefthand corner. Depending on theautopilot type, the RED “AP” mayflash when disengaged.In dual autopilot installations, theactive side is annunciated by agreen “AP” and the inactive sidewill be annunciated by a yellow“AP” with a yellow arrow pointing

toward the active side.

Beginning with software release09, the KFC 500 autopilot cou-pled status “SAS” may be dis-played in place of “AP”. As withthe “AP” annunciation, “SAS” willbe either green or yellow to indi-cate active and inactive sidesrespectively and flashing redwhen disconnected. A steady redSAS annunciation indicates anautopilot power loss. See theKFC 500 pilots guide for morei n f o r m a t i o n .

Yaw damper, if engaged, mayflash RED when disconnecteddepending on the autopilot type.

Beginning with software version05, the following autopilot com-mand reference data will be dis-played in green when interfacedwith the KFC 4 0 0 / 5 0 0 :• AIRSPEED

0 to 512KTS in 1KTi n c r e m e n t s .

• MACH0 to 4.096M in0.005M increments.

• VERTICAL SPEED+/-20,480F/M in100F/M increments.

• ALTITUDE0 to 65536FT in 10FTi n c r e m e n t s .

• HIGH PROFILE“ H ”

• NORMAL PROFILE“ N ”

• LOW PROFILE“ L ”

N o t e : Lateral/vertical modesand other annunciators aredetermined by the auto-pilot/f l ight director systeminstalled.


EADI Displays

Two additional features wereadded with 09 EFS software toaccomodate the KFC 500 autopi-lot. Numerical bank limit annunci-ation and selected heading inputfrom the flight control computer(FCC). The numerical bank limitis annunciated in green as“BLXX” where XX is the banklimit in degrees (1 to 30) providedby the FCC. This annunciationhas priority over “HB” (half bank)which can be displayed in the

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SFIM CDV ENGAGED MODES

LATERAL VERTICAL COLLECTIVEBC

CPOSGSPDHDGHOVLOCNAVTST

VORAAZ

BAZ

ALTCPOS

GAGS

GSPDHOVIAS

TDWNTSTTUPVS

ALTCHT

CRHTGAGS

HHTTDWN

TSTTUPVS

SFIM CDV ARMED MODES

LATERAL VERTICAL COLLECTIVEBC

CPOSLOCNAVOSS

VORA

CPOSGS

TDWN

CHTGS

TDWN

same field. Acceptance of select-ed heading from the FCC allowsthe pilot to use the Cyclic BeepTrim (CBT) switch to move theheading bug displayed on theEHSI compass card while theheading select mode is active.

Beginning with software veresion14, the KFC 225 autopilot wasadded, and REV is annunciatedinstead of BC for the KFC 225o n l y .

w SFIM CDV AUTOPILOT/FLIGHT DIRECTOR MODEA N N U N C I A T I O N

o When the EFS 40/50 is config-ured to interface with the SFIMCDV 155 Autopilot/Flight Direc-tor, a unique set of armed andengaged lateral, vertical and col-lective mode annunciations willbe displayed. Engaged modesare displayed in green across the

top of the EADI and armedmodes are displayed in white onthe second line from the top onthe EADI.

The following annunciation modi-fiers are also provided by theSFIM CDV Autopilot/Flight Direc-t o r :• Green Autopilot Coupled Box

around the mode annunciator• Flashing Yellow Excessive

Deviation Chevron


EADI Displays

• Yellow Degraded sensor color RADIO ALTIMETER

o The radio altimeter display iscomposed of three elements;radio altimeter (RA) height, deci-sion height (DH) set and decisionheight (DH) alert. In the upperright corner of the display, a fieldof white alphanumeric data pro-vides radio altimeter height andannunciation. In the lower rightcorner of the display, a greenalphanumeric field displays theselected DH. This field is activeonly when the DH set knob isactive or when the radio altimeteris providing valid height data. Tothe right and above center of thedisplay, a yellow “DH” alert is dis-played in a black box outlined iny e l l o w .

Depending on the type of radioaltimeter installed, the elementsof data displayed may vary. Analtimeter which fully supports theinterface will provide display of allthree elements; RA, DH set and“DH” alert. Altimeters which donot fully support the interfacemay be limited to the “DH” alertannunciation. In such an installa-tion, selected DH will not be dis-played. DH set is accomplishedoutside the EFS 40/50 system onthe radio alt imeter. TheE F S 40/50 receives an externalcommand from the alt imeterwhich activates the “DH” alerta n n u n c i a t i o n .

Radio altimeter (RA) height dis-play range is -20 to 2,500 feet.Between -20 and 100 feet, heightwill be displayed in five foot incre-ments. Above 100 feet, heightwill be displayed in 10 foot incre-ments for EFS software before09. Beginning with 09 software,RA altitude is displayed in 5 footincrements between -20 and 500feet with 10 foot increments dis-played above 500 feet. Selectionof decision height and activationof “DH” alert will be in 1 footincrements. The maximum andminimum height displayed willdepend on the radio altimeterinstalled. Some radio altimetersprovide linear altitude informationonly to 1,000 feet. Refer to theoperators handbook for the par-ticular radio altimeter installed fordetails on the possible displayr a n g e .

N o t e : 20 ft is the minimum alti -tude displayed when a KRA10A is the configured radioaltimeter.

To annunciate an operationalradio altimeter which has notacquired a valid groundresponse, three white dashes areplaced in the height data field. Ifthe radio altimeter has failed,three RED dashes are placed inthe height data field. In eithercase, if the rising runway is dis-played, it will remain fixed at thebottom of its scale and moveslaterally to indicate the LOC orMLS deviation.

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EADI Displays

DECISION HEIGHT SET

o A part time green alphanumer-ic readout, located in the lowerright corner, displays the lettersDH and selected decision heightin feet as manually establishedby the DH set control knob. Withthe control pulled out, the DH setvalue is displayed and may beset regardless of aircraft altitude.With the control knob “in”, DH isdisplayed only for radio altimeteraltitude less than 2500 feet AGL.The DH set display range is from“OFF” (-1 ft.) to the RA decluttervalue (2,500’). Refer to Figure4 . 2 . 2 .

DECISION HEIGHT ALERT

When the radio altimeter heightis equal to or less than the select-ed decision height, the DHannunciator will be displayed.When first activated, the DHannunciator will flash for 10 sec-onds. The DH symbol is a largeyellow “DH” on a black back-ground enclosed by a yellow box,located to the right of the pitchscale and above the horizon linewhen in normal attitude. Refer toFigure 4.2.2.

PRECISION APPROACHMODE FORMAT

The precision approach modedisplay is obtained by selectingthe ILS MLS or GPS navigationsource. (i.e. using the NAV but-ton) If an ED 462 or 551A isused as the EADI, the full

sky/ground display is reduced insize to provide a high contrastblack background for variousscales and annunciations. A ris-ing runway symbol is provided forthe display of expanded left/rightdeviation and runway closureduring the final 200 feet of radioaltimeter height. The rising run-way center line, referenced to thelateral deviation scale, will pro-vide LOC, MLS or GPS devia-tion. A “LOC”, MLS, or “GPS”annunciation identifies the sensorin use. This annunciation is notprovided after 07 software if onlyone sensor type is used. A verti-cal scale is provided to display anapproach glidepath. Refer toFigure 4.2.2.

EXPANDED LATERALDEVIATION SCALE

Located at the bottom center ofthe EADI, displayed in white, with2 hollow circles on standard ADIdisplay and 4 circles on a com-posite ADI display and a centerdiamond is the expanded lateraldeviation scale. This scale pro-vides a reference for the risingrunway symbol with ILS, MLS orGPS selected. As an expandedscale, it represents 1/2 full scaledeviation as displayed on theEHSI. When the selected courseand aircraft heading differ bymore than 105 degrees, theleft/right sensitivity is reversedand a green (onside) or yellow(offside) BC is displayed left ofthe center diamond to alert thepilot that back course informationis being displayed. Refer to Fig-

4.2.9Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


EADI Displays

ure 4.2.3 and 4.2.4.

Software version 07 and higherwill display the expanded localiz-er/MLS/GPS scale as three dots.

Note: Warning, some conven -tional ADI expanded ILS andMLS displays represent 1/4 ofthe full scale displayed by theHSI. The EFS 40/50 provides1/2 the EHSI displayed devia -tion to provide better pilot inter -face.

RISING RUNWAY

Three configuration options areselectable at the time of installa-tion and certification for display ofthe rising runway symbol.

o The first option provides fulltime display of the rising runwayonly when in the precisionapproach mode. The symbolicrising runway will be displayed inthe lower center of the displayjust above the LOC/MLS/GPSapproach expanded lateral devia-tion scale. The center line of thesymbolic rising runway repre-sents ILS, MLS or GPS approachfly to command. If the radioaltimeter provides height abovethe ground information to theE F S 40/50, the rising runwaysymbol will start increasing insize at 200 feet and will continueto increase in size to 0 feet.When the on-side ILS, MLS orGPS approach is selected as theprimary NAV sensor, the risingrunway will be green in color. Ifthe off-side sensor is selected,the runway will change to yellow,

alerting the pilot that he hasselected off-side information.o A second configuration optionprovides for the display of a tradi-tional deviation bar in place of therising runway. The deviation barwill overlay the lateral deviationscale. It will not be positionedjust above the deviation scale asthe rising runway is.

o A third configuration optionallows the display of the risingrunway unless one of the follow-ing conditions exists, in whichcase the deviation bar will be dis-p l a y e d .

• No radio altimeter• Radio altimeter is not being

displayed, above 2,500 feet ornot providing computed data

• Radio altimeter is belowminimum altitude, white dashesd i s p l a y e d

• Radio altimeter is flagged,RED dashes displayed.

In the event the lateral deviationinformation becomes invalid orfailed, the rising runway or D b a rand lateral deviation scale areremoved, the lateral deviationscale is replaced with a RED “X.”

Beginning with software 09, thedeviation bar and scale aredecluttered when lateral devia-tion information is provided inARINC 429 format with a statusof No Computed Data (NCD).The red “X” is still displayed forinvalid or missing data.

4.2.10 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


EADI Displays

GLIDESLOPE/VERTICALNAVIGATIONWhen the selected primary NAVsensor is ILS, MLS or LNAV withVNAV selected, a stationarywhite vertical deviation scale willappear on the right or left side ofthe EADI display as configured atthe time of installation and certifi-cation. This scale provides a ref-erence for the vertical deviationpointer. The deviation pointermoves in relation to the scale toindicate glide path center withrespect to aircraft position.

When the on-side sensor isselected for display, the deviationpointer is green in color. Whenthe off-side sensor is selected fordisplay, the deviation pointerchanges to yellow alerting thepilot that he has selected his off-side nav sensor.

If the selected sensor is ILS orMLS, a “GS” (or “GP” for MLSwith software 08 and higher. Itcan be either GP or GS aftersoftware 08. The configuration isselectable.) will be displayed inthe pointer. “VN” will be annunci-ated if the selected sensor is anLNAV with VNAV selected. If theselected sensor is “GPS”, a GPwill be displayed in the verticalpointer during a GPSapproach,(with SW15 or higherand configured for varibleV N A V ) .

Additional configuration optionsselectable at the time of installa-tion and certification:

o Declutter GS on Back Course,allows the vertical deviation scaleto be in view at all times or onlywhen the selected course is within1 0 5 degrees of the aircraft heading. o Vertical Scale Side, allows thevertical deviation scale to be dis-played on either the right or leftside of the EADI and EHSI display.Vertical Pointer Type, allows thevertical pointer to be displayed asone of three options:o

o

o

o Vertical pointer annunciationfor MLS can be configured as"GP" beginning with software 08.

EADI OFF-SIDE ILS/MLS/GPS

o A configuration optionselectable at the time of installa-tion and certification allows dis-play of the off-side ILS/MLS/GPSdata on the EADI while the EHSIis displaying on-side data. Alldeviation data and symbologyare displayed as typically definedby the EFS 40/50 operationalcharacteristics. On-side informa-tion displayed on the EHSI will bedisplayed in green and the off-side information displayed on theEADI will be displayed in yellow.

4.2.11Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

GS

GS

GS


EADI Displays

Back course annunciation onboth the EADI and EHSI is a cal-culated reference to the courseselected by the on-side EHSI.

The EADI and EHSI deviation flag-ging will be independent when thisconfiguration option is selected. TheEADI may show a flag while theEHSI is displaying active data. Theflag is tied to the source of deviationd a t a .

N o t e : This mode is notselectable by the flight crew asan “as desired mode ofoperation”. EADI deviationinformation is always displayedin yellow.

To enable this feature, the followingconditions must be met:

• The configuration optionmust be selected

• EHSI must be on-side• Both sensors used (i.e. ILS, MLS,or GPS) must be in approach modeI.ILS/MLS tuned to an active frequen-cy or GPS with an active approach• EADI Down or Composite

mode may not be selected

MARKER BEACONANNUNCIATION

In the lower left corner, markerbeacon information is displayedinside a hexagon shaped box. Theouter marker, “OM” is displayed incyan. The middle marker, “MM” isdisplayed in orange. The innermarker, “IM” is displayed in white.All three markers may be displayedsimultaneously. Flashing of themarker display is also possible

providing the marker receiverflashes its output.FAST/SLOW OR COLLECTIVEDISPLAY

An optional display item, selectableat the time of installation and certifi-cation. If configured, will be dis-played on the opposite side of theEADI from the Glideslope scale. Thescale consists of two vertical whiteunfilled diamonds and one whiteunfilled circle.

Beginning with software 09, atwo dot fast/slow scale may beconfigured with the “F” and “S”representing full scale and thediamonds representing half-s c a l e .

If Fast/Slow is configured, thescale and pointer will be dis-played when the airspeed is with-in 13 knots of the airspeed bug.The scale and pointer may beremoved when the airspeed iseither 13 knots greater or lessthan the airspeed bug. The scaleprovides ±10 knots indication. Ifairspeed is the referenced data,AS will be annunciated in thepointer. If angle of attack is thereferenced data, AN will beannunciated in the pointer.

If the scale is configured for Collec-tive display, it will operate in thesame manner as the Fast/Slow.“CO” will be annunciated within thepointer when the scale providescollective information. As thescale factor may vary from air-craft to aircraft, it is necessary torefer to the aircraft flight manualsupplement for those details.

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EADI Displays

Configuration options selectableat the time of installation and cer-t i f i c a t i o n :o Display of no Fast/Slow or Col-lective scale.o Display of a single dotFast/Slow scale.o Display of a single dot Collec-tive scale.o Display of a two dot Fast/Slowscale, beginning with softwareversion 09.

4.2.13Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

or

+ Full Scale

- Full Scale

SINGLE DOTFAST/SLOW

FAST/SLOW AND COLLECTIVE DISPLAYS

or

TWO DOTFAST/SLOW

(SW 09 and above)

COLLECTIVE

MACH DISPLAYo MACH value may be displayedon the EADI beginning with soft-ware version 10. The MACHvalue is displayed in the lower leftcorner of the EADI as a whitethree digit number followed bythe letter M. For example: 1.23MConfiguring the EFS to displayMACH value will prevent the dis-play of a fast/slow or collectivescale. Invalid, missing, or NoComputed Data (NCD) for theMACH value will cause a flagcondition (red dashes).

RATE OF TURN DISPLAYo An optional display item,selectable at the time of installa-tion and certification, if config-ured, will be displayed at the bot-tom center of the EADI. The rateof turn scale is composed ofthree evenly spaced unfil ledwhite rectangles. The rate of turnpointer is an equally sized whitefilled rectangle balanced atop asmaller white filled rectangle.

The rate of turn indicator will notbe displayed when the compositereversionary mode is selected ford i s p l a y .

The pointer is green unless thecollective option is selected, thenit may be either green or magen-ta to match the color configuredfor the flight director commandbars. Three pointer styles arealso provided to match the con-figured GS pointer style.

If invalid or failed sensor data isreceived the deviation pointerand scale are removed and aRED X annunciated.


EADI Displays

If rate of turn data becomesinvalid, the pointer and scale willbe removed and replaced with aRED “X”.o Software release 0702 incor-porated configuration items forbank angle correction of the yawrate gyro. This correction takesinto account the aircraft roll atti-tude when displaying rate of turni n f o r m a t i o n .

CATEGORY IIANNUNCIATOR

Refer to Figure 4.2.7 whilereviewing this section.

o An optional annunciator pro-vides advisory only information,selectable at the time of installa-tion and certification. When con-figured, the symbol generator willmonitor the appropriate on-sideand cross-side information andalert the crew when Category IIrequirements or limits are not sat-i s f i e d .

The Category II Annunciator isfunctional in either single or dualEFIS installations and providesdifferent limits for FAR and JAR-AWO certifications. The function-ality and requirements are slightlydifferent between the two sys-tems, however, the intendedfunction is the same.

o Software release 0702expanded the configurationoptions for Category II display.The additional options allow theoperator to select at installationtime whether to display the CAT

II annunciation as well as theexcessive deviation limits or theCAT II annunciation only. Theseadditional options provide theflexibility of display where theoperator Category II l imitsdeviate from the set limit set inthe EFS 40/50 configurations e l e c t i o n s .

w CATEGORY II OPERATIONA N N U N C I A T I O N S

Activation of the remote momen-tary (Open/Ground after software07/02) Category II switch by thepilot will cause a yellow CAT II tobe displayed on the ADI and HSIto indicate that Category IIannunciations are active. Cate-gory II can be activated at anytime and in all normal modes ofthe EFS.

In the normal sequence ofevents, a white CAT II will be dis-played on the ADI and HSI inplace of the previous yellow CATII only when certain criteria arem e t :

w DUAL EFS SYSTEM

The following requirements mustbe met in a four or five tube EFSsystem before the Category IIannunciator will change to white:

1 . Valid ILS or MLS #1 isselected on Symbol Genera-tor #1.

2 . Valid ILS #2 is selected onSymbol Generator #2.

3 . Valid ATT #1 is selected onSymbol Generator #1.

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EADI Displays

4 . Valid ATT #2 is selected onSymbol Generator #2.

5 . Valid HDG #1 is selected onSymbol Generator #1.

6 . Valid HDG #2 is selected onSymbol Generator #2.

7 . Pilot and copilot symbolgen-erator are valid.

8 . Both crosstalk buses arev a l i d .

9 . Copy, composite or ADI-down modes are not active.

1 0 . Radio altitude is validand between 2,500 feet and50 feet.

1 1 . True heading is not active.1 2 . Valid pilot flight director.1 3 . Pilot’s command bars in view.1 4 . No attitude, heading, local-

izer, glideslope or radioaltitude miscompare flags.

1 5 . Front course ILS or MLSa p p r o a c h .

1 6 . Pilot’s flight director (if avail-able) engaged in localizerand glideslope.

Additional requirements to beadded to the above criteria ifa p p l i c a b l e :

• Both pilot and copilot ILS #1and #2 frequencies mustmatch if known and valid.

• Both pilot and copilot MLS #1and #2 channels must match ifknown and valid.

• Valid copilot flight director ifc o n f i g u r e d .

• Copilot’s flight directorengaged in localizer andglideslope if FD configured.

• Copilot’s command bars inview if FD configured.

w SINGLE EFS SYSTEM

The following requirements mustbe met in a single HSI and ADIEFS system before the CategoryII annunciator will change tow h i t e :

1 . Valid ILS or MLS #1 iss e l e c t e d.

2 . Valid ATT #1 is selected.3 . Valid HDG #1 is selected4 . The symbol generator is

v a l i d .5 . Neither composite nor ADI

down mode is active.6 . Radio altitude is valid and

between 2,500 feet and 50f e e t .

7 . True heading is not active.8 Valid flight director.9 . Flight director engaged in

localizer and glideslope.1 0 . Command bars in view.1 1 . Front course ILS or MLS

a p p r o a c h .

A green CAT II will be displayedin place of the white CAT II onthe ADI and HSI when the abovecriteria are met and the radioaltimeter is between 500 and 100feet. Beginning with 0702 soft-ware, excessive deviation moni-toring became a configurationoption and if configured, mustalso be within limits before the“CAT II” annunciation colorchanges to green. Green exces-sive deviation arrows (>> <<) willappear on the ADI and HSI local-izer and glideslope scales. If therising runway is configured fordisplay, green chevrons will bedisplayed within it. Location ofthe excessive deviation arrows

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EADI Displays

on the localizer and glideslopescales will be displayed accord-ing to the Category II limits.

Yellow flashing arrows on thelocalizer scales and yellow flash-ing chevrons on the rising run-way will be displayed if the local-izer pointer exceeds the limits setby the arrows (>> < < ) .

Yellow flashing arrows on theglideslope scales and yellowflashing GS in the glideslopepointer will be displayed if the

glideslope pointer exceeds thelimits set by the arrows (>> <<).

All yellow excessive deviationsymbols will flash.

White CAT II will be displayedbelow 100 ft., and no excessivedeviation symbology will be dis-p l a y e d .

Yellow CAT II will be displayedbelow 50 ft., and no excessivedeviation symbology will be dis-p l a y e d .

4.2.16 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

CATEGORY II DEVIATION LIMITS

w CATEGORY II THRESHOLDS

The following Category II deviation limits can be configured for thecomparison of excessive deviation and for the placement of the devia-

tion scale arrows.Note: The FAR deviation limits are intended for guidance only since

the FAR does not specify operational deviation limits for a CAT IIdisplay. FAR localizer limits will change on initial 300 feet crossingand will remain at new limits. JAR-AWO old limits, as well as noexcessive deviation limits were added as configuration options bysoftware 0702.

When activated, Category II limit (>> <<) indicators are displayed onthe glideslope and localizer scale, chevrons will also be displayed on


EADI Displays

the rising runway if it is config-ured for display.ATTITUDE MONITOR

Dual channel processing of Atti-tude inputs provides validation ofthe processed displayed attitudeinformation within the symbolgenerator. If a failure is detectedin the processed information,“ATTITUDE FAIL” is annunciatedat the top center of the displayand blue sky and brown groundinformation and associated atti-tude scales are removed.

Note: There is no monitor func -tion in any reversionary mode.

CROSS COMPARATORANNUNCIATORS

Refer to Figure 4.2.5 whilereviewing this section.

Provides system comparisonbetween like on-side and off-sidesensors. The following listdescribes the associated symbol-ogy and sensors:

w R A

Radio altitude miscompare, a yel-low RA above a double-endedarrow displayed just below theradio alt itude readout in theupper right corner. This is dis-played when SG 1 and SG 2radio altitude differ by more than8 feet at between 0 and 99 feetAGL. The Allowable differenceincreases by 8 ft per 100 ft of alti-tude . If the off-side RA flag is dif-ferent the miscompare will also

be displayed.

w L O C

Localizer miscompare, a double-ended arrow will be displayedover the localizer deviation point-er on the EADI and EHSI whenboth SG 1 and SG 2 are tuned toan ILS/MLS frequency and differby more than halfscale deviation.

w G S

Glideslope miscompare, a dou-ble-ended arrow will be displayedabove the glideslope deviationpointer on the EADI and EHSIwhen both SG 1 and SG 2 aretuned to an ILS/MLS frequencyand differ by more than halfscale.

w A T T

Attitude miscompare, a yellowdouble-ended arrow over “ATT”will be displayed in the top leftcorner of the EADI if ADI pitch 1,2, and cross-side (if available)differ by more than 5 degrees orroll 1, 2, and cross-side (if avail-able) differ by more than 6degrees. The miscompare willalso be displayed if the failurewarning flags differ.

Note: In reversionary modes theEHSI Attitude may be used for

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EADI Displays

comparison if required.

w H D G

Heading miscompare, a yellowdouble-ended arrow over “HDG”will be displayed to the left of thelubber on the EHSI and right sidecenter of the EADI if heading 1,2, and cross-side (if available)differ by more than 6 degrees upto 6 degrees of bank and bymore than 20 degrees above 6degrees of bank. If bank infor-mation is not available, the mis-compare will be displayed ifheading differs by more than 20degrees. The miscompare willalso be displayed if the failurewarning flags differ. Headingmiscompare will be processed inthe EHSI section of the symbolgenerator and displayed on theEADI if the heading tape isselected for display. Headingmiscompare will not be per-formed if sources are not typematched (all magnetic or all true).

Note: In reversionary modes theEHSI Attitude may be used for

comparison if required.

N o t e : Beginning with software10, SG1 to SG2 comparisonsof attitude, heading, and radioaltitude are not performed ifvalid data is not available onthe cross-talk bus betweensymbol generators. Therefore,failure of an SG in installationswith both SG1 and SG2 config -ured can cause miscompareannunciations only with soft -ware versions before 10.

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EADI Displays

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Figure 4.2.1TYPICAL EADI 40/50 DISPLAY


EADI Displays

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Figure 4.2.2EADI SYMBOLOGY DEFINITION


EADI Displays

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EADI Displays

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EADI Displays

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EADI Displays

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Figure 4.2.6EADI FAULTS SYMBOLOGY


EADI Displays

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Figure 4.2.7CAT II SYMBOLOGY


EADI Displays

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Figure 4.2.8EXAMPLE EADI ENROUTE DISPLAY

WITH 08 SOFTWARE


EADI Displays

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Figure 4.2.9EXAMPLE EADI APPROACH DISPLAY

WITH 08 SOFTWARE


COMPOSITE Displays

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COMPOSITE MODE

Refer to Figures 4.3.1 and 4.3.2while reviewing this section.

In the event of a display unit orEADI symbol generator sectionfailure, the composite mode maybe selected for display on theremaining good display unit bymeans of an external switch.The base composite display uti-lizes the standard EADI displayfor its foundation. To it is addeda standard lateral deviation scale,selected CRS, selected HDG,distance information, DME HOLDannunciation, selected NAV sen-sor and TO/FR information. Cre-ating a composite display in thismanner provides the pilot a famil-iar display, which requires mini-mal transition time when it isselected for use.

Note: The following will addressonly those areas of the com -posite display which differ fromthe standard EADI display.

If the EADI section of the symbolgenerator fails, a full compositedisplay may be displayed on theEHSI. If the EHSI section fails,only pitch and roll information willbe displayed on the EADI.

HEADING TAPE

If not already configured for dis-play, a white heading tape will befixed along the top of the horizonline. Index marks appear every 5

degrees with heading annuncia-tion displayed every 30 degrees.

In the event heading databecomes unavailable or invalid, astationary red “HDG” will be dis-played above and to the right ofthe symbolic aircraft.

SELECTED COURSE

Toward the bottom of the display,left of center is a green alphanu-meric readout which provides adigital display of the selectedcourse. In addition to the digitaldisplay, on the heading tape adownward pointing arrow pro-vides a visual cue of the selectedcourse with reference to the air-craft heading.

If the selected Primary NAV sen-sor is an on-side sensor the digi-tal readout and pointer is dis-played in green. If an on-sideLNAV is the selected PrimaryNAV sensor and it is in theapproach mode, the readout andpointer wil l be green. If theenroute mode is selected, thereadout and pointer are cyan. Ifan off-side sensor is selected, thedigital readout and pointer will bedisplayed in yellow.

HEADING BUG SELECT

Toward the bottom of the display,right of center is an orange (con-figuration options for cyan ormagenta) alphanumeric readoutwhich provides a digital display of

COMPOSITE DISPLAYS


COMPOSITE Displays

the selected heading. In additionto the digital display, on theheading tape is a hollow orangeheading bug which provides avisual cue of the selected head-ing with reference to the aircrafth e a d i n g .

N o t e : As the aircraft headingchanges, the selected coursepointer and heading bug willfollow the heading tape andmay disappear from view. Theheading bug and course point -er function the same as theydo in the normal mode of oper -ation, once set they are fixedto the heading tape or com -pass card.

NAVIGATION SOURCEANNUNCIATION

A vertical three- or four-letteralphanumeric readout located onthe left or right side of the dis-play, depending on vertical scaleside selection, indicates the navi-gation selected as the primarynavigation sensor.

Green annunciations indicate anon-side approach NAV system isbeing displayed. Yellow indi-cates the cross-side system hasbeen selected. Cyan annuncia-tions apply to on-side non-approach NAV systems. Thesecolor codes apply to the NAVsource annunciator, CRS pointer,deviation bar, CRS, and dis-t a n c e .

If both sides select the samenavigation source (i.e., pilot and

copilot select VOR 2) a yellowbox is placed around the naviga-tion source annunciator on bothsides of the cockpit.

If both sides select their respec-tive cross-side navigation source(i.e., pilot selects system 2, copi-lot selects system 1) then bothNAV source annunciators will beyellow with no yellow box.

LATERAL COURSEDEVIATION SCALE

Located at the bottom center ofthe EADI, displayed in white, withfour hollow circles and a centerdiamond is the lateral deviationscale. The course deviationscale provides a reference for thecourse deviation bar to indicatethe centerline of the selectednavigation or localizer or MLScourse in relation to the centerdiamond.

The course width displayed in thecomposite mode is identical tothat typically shown on the EHSI.Refer to the table on page 4.1.5.

LATERAL COURSEDEVIATION BAR

The course deviation bar repre-sents the centerline of the select-ed navigation or localizer course.

If invalid or failed primary NAVsensor data is received thecourse deviation bar and scaleare removed and a RED Xa n n u n c i a t e d .

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COMPOSITE Displays

Beginning with software 09, thedeviation bar and scale aredecluttered when lateral devia-tion information is provided inARINC 429 format with a statusof No Computed Data (NCD).The red “X” is still displayed forinvalid or missing data.

TO/FROM

Displayed left of the center dia-mond on the lateral deviationscale, a white “TO” or “FR” willprovide TO/FROM informationwhen in non-ILS or non-MLSm o d e s .

DISTANCE INFORMATION

An alphanumeric readout, locat-ed in the lower left corner, annun-ciates distance in nautical milesfrom the aircraft to the selectedprimary NAV station when in theVOR, TACAN, ILS or MLS mode,or to the waypoint in the LNAV orRNAV mode.

DME HOLD

When DME HOLD is selected,the DME distance and annuncia-tor color will change to white andwill remain white until the HOLDfunction is released. The sensoridentifier (ADF, VOR, ILS, etc )shall retain the original assignedcolor. The HOLD function isadditionally annunciated by anorange letter “H” displayed imme-diately to the right of the distanceinformation. Ground speed andtime-to-station are not displayedwhile DME HOLD is active.

Once the DME is placed inHOLD, its distance will continueto be displayed and will not beaffected when the primary NAVsensor is changed.

DME HOLD will not functionwhen MLS, LNAV or RNAV is theselected sensor. In this situationthe associated distance field isalways used to display waypointor MLS distance.

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COMPOSITE Displays


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COMPOSITE Displays

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Figure 4.3.1COMPOSITE ENROUTE MODE DISPLAY


COMPOSITE Displays

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Figure 4.3.2COMPOSITE APPROACH MODE DISPLAY


MFD Displays

Software versions 05 and abovesupport the Multi Function Dis-play (MFD) used in three andfive-tube EFS 40/50 configura-tions. In traditional EFIS systemsthe MFD’s primary purpose wasto provide weather radar and/orLNAV or RNAV moving mapinformation. In addition to provid-ing the traditional display func-tionality, the MFD in EFS 4 0 / 5 0systems also has the ability tofunction as an independent EHSIif the system is configured to pro-vide such functionality.

In such cases, the informationdisplayed on the MFD follows thesame basic display format as theEHSI. Therefore this section willonly address those areas of theMFD that differ from the EHSI.

Refer to Figure 4.4.1, 4.4.2 and4.4.3 while reviewing this section. CRS, NOT CRS SELECT

When the MFD course selectknob is not active, a bar the colorof the CRS annunciator will beplaced above it. This will alert thepilot that the MFD CRS knob isnot active and the MFD’s courseannunciator is referenced to thepilot’s EHSI selected course.

E x a m p l e : C R S 1 3 5

WEATHER ONLYo A configuration option avail-able at the time of installation andcertification, provides a traditional

weather radar indicator display.Unlike most conventional EFISweather radar displays this dis-play will not present any nonweather related information. Allnavigation information isremoved, leaving a clean weath-er presentation consisting of fourcyan range rings and white radarannunciations located in thelower left corner.

Weather radar mode, warningsand failure annunciations are dis-played as they are on the normalEHSI ARC Weather mode.

w TRACK LINE

A yellow dashed line drawn fromthe center of the symbolic aircraftto the compass card or outerrange ring. Activated and slewedby pressing one of the TRK but-tons. Pressing the VP button willactivate VP at the location of theTrack Line. In the upper left cor-ner a yellow digital readout dis-plays the present position of thetrack line. Once the track linehas remained stationary for 15seconds it will be decluttered.

VERTICAL PROFILE (VP)

w SYMBOLIC AIRCRAFT

When the VP mode is selectedfor display, the symbolic aircraftis centered on the left edge of thed i s p l a y .

Beginning with software version09, the Split Screen display is

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MFD DISPLAYS


MFD Displays

activated by pressing the VP but-ton while VP is active. Therefore,the VP button will provide the fol-lowing selection sequence:

Vertical ProfileSplit ScreenHorizontal Scan Only

w RANGE RINGS

Four evenly spaced vertical cyanrange rings are displayed duringVP. At the bottom of each rangering, a cyan distance number isdisplayed annunciating it’s range.

w ALTITUDE LINE

Three horizontal altitude lines arepresent on the VP display. Thecenter line is off the nose (boreline) of the symbolic aircraft, rep-resenting the actual aircraft’s pre-sent altitude. Equally spacedabove and below the 0 foot cen-ter line are two altitude lines acertain number feet above andbelow the aircraft. The numberassociated with these lines varieswith the selected range to com-pensate for the radar beam widthat the various ranges.

w PROFILE ANGLE

In the upper left corner “PRO-FILE” is displayed annunciatingthat the VP mode is selected.Just below it, the present azimuthangle being sliced is displayed asL (left) or R (right) followed by anumber. “R6” would represent aVP slice being performed at 6degrees right of the aircraft nose.

w P L A N - V I E W ,NORTH-UP MAP

o Beginning with software 07,Plan-View is an option selectableat the time of installation. ThePlan-View North-Up map modeprovides a display in which asymbolic aircraft shows the actu-al aircraft’s position relative to theLNAV flight plan route. As theactual aircraft progresses alongthe flight plan route or deviatesfrom it, the symbolic aircraft like-wise progresses along or devi-ates from the flight plan depictionon the indicator. Range is depict-ed by the dashed white full scalerange ring and dashed light bluehalf scale range ring. When thePlan-View is first entered, thesymbolic aircraft is positioned inthe center of the display. As theactual aircraft moves, the sym-bolic aircraft will move about thedisplay and may move offscreen. If this occurs, the sym-bolic aircraft can be brought backonto the screen in any of threeways. One is by pressing theenter button. This will repositionthe symbolic aircraft at the centerof the display. Another method isto use the joystick to change thelat/ long of the center of thescreen (see Joystick operation inSection 2.4, MFD Operation). Athird method is to select a greaterrange scale.

The Plan-View, always displayedas a true north map, aids in flightplanning and aircraft positionawareness. Weather radar, light-ning and other navigation infor-mation are not available in Plan-

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MFD Displays

View mode.

To display the Plan-View, anLNAV with an active valid flightplan must be selected as the pri-mary navigation source and beproviding valid magnetic varia-tion. The current FROM way-point and the next 14 waypointson the flight plan may be dis-played. As defined for the nor-mal NAV Map, the pilot may electto display either the closestnavaids or airports along with thefirst five flight plan waypoints.

CHECKLIST INTERFACE

In software 08 and higher a con-figuration option available at thetime of installation and certifica-tion, provides Checklist displaycapability on the MFD. Checklistfunctions are controlled via theCP 469A, MFD Control Panel,buttons and joystick.

The user entered checklist datais organized in a simple page-ori-ented format with a pro-grammable index function whichallows quick access to the check-list entries. The index operatesfrom user entered title descrip-tions and relative page numberswhich provides maximum flexibili-ty in organizing and titling theindex items. It is also possible tocreate hierarchies of indiceswhen desired. An additionalcapability is provided to allowinvocation of emergency check-lists through discrete signalsapplied on the rear connector.Any index or checklist page listcan be mapped to any of the

eight emergency page inputsallowing a high degree of free-dom in defining and organizingthe operation of programmedfield units. In addition to beingable to program the index andemergency page operation, it isalso possible to program the col-ors used for the text fields, titlelines, and cursor lines for anyindexed list.All pages are organized astwelve lines of 32 characterseach for a total of 384 charactersper page. The CP 469A willstore a minimum of 800 checklistpages and 400 note pages.Since the actual storage require-ments vary according to the com-plexity of the pages themselves,the actual storage capacity willvary upward from this minimum.The upper limit for both checklistpages and note pages is fixed at1024 each.

w LOADING AND MODIFYING CHECKLIST DATA

The user may load the CP 469Awith predefined checklist datagenerated on an IBM™ c o m p a t i-ble laptop PC using DEU (DataEntry Utility) software on a 3.5inch disk, KPN 222-00337-xxxx,provided with the CP 469A. Thisdisk contains a “read me” file withmore detailed information ongenerating and modifying check-

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N O T I C ETHE USER IS SOLELYRESPONSIBLE FOR

CHECKLIST CONTENT


MFD Displays

list and note pages. The PCmust have DOS version 3.0 orgreater and should have at least512 Kbytes of free RAM. Acable, KPN 155-02794-0002 isrequired to load the checklistdata from the PC to the CP 469Avia RS 232. Checklist data in theCP 469A can also be download-ed from the CP 469A to the PCwhere it may be modified andthen re-loaded back into the CP469A. User programmable notepages can also be modified withthe use of the PC.

w CHECKLIST PAGEO R G A N I Z A T I O N

Available colors are red, green,blue, cyan, magenta, yellow, andwhite. Black is reserved. On allindex and checklist pages, thefirst two columns of charactersare reserved for the cursor andcheckoff status. A graphical cur-sor will move from item to item tolet the user know which line thecursor is on. In addition, thecolor of the line with the cursormay change. A special characterwill be displayed in the firstreserved column to indicate thechecked status of a line. A blankwill indicate that nothing withinthe sub-tree has been checkedoff, or that there is no element tobe checked off. A star symbolwill indicate that a list or sub-treeis partially checked off. A checkmark will be displayed when allchecklist items within a sub-treehave been checked off. Theseconditions may also involve acolor change on the line.

The following sections describethe checklist pages. For adescription of how the usermoves from page to page, referto the CONTROLS section.

w ROOT INDEX PAGE

Refer to f igure 4.4.6. Uponselecting checklist for display, theCP 469A will transmit a ‘root’index page to the EFS symbolgenerator for display. This ‘root’page will include disclaimer textthat states the user is responsiblefor the content and maintenanceof data within the checklist. It willalso contain user-supplied text todescribe the checklist, to be usedas a means to identify thesource/creator/version of thechecklist stored in CP 469Amemory. In addition to the titleand disclaimer lines, the rootpage will have index entries oftwo types: user-defined, andf i x e d .

The fixed entries will include aNOTES entry which allowsaccess to the note page sub-tree,and another entry, CLEAR ALLCHECKLIST ITEMS, whichallows the user to clear allchecked items in the entire tree.These entries will always be pre-sent on the root tree, and will fol-low any user-defined indexentries. The user is not requiredto have any NOTE pages, but theindex entry will always be pre-s e n t .

The user-defined index entriesmay point to sub-index pages, ordirectly to a checklist. The user

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MFD Displays

is free to name these entries, andto determine their organization.Typically, the first entry on theroot page would be ‘EMERGEN-CY PROCEDURES’, but theuser is free to provide anotherorganization. At least 4 suchuser-defined index entries will beprovided on the root index page.The initial cursor position willalways be at the first index entryin the root page. The cursor willbe restricted to the six indexentry lines.

The user will be able to specifythe color of the top title lines, thecolor of each of the four user-assigned index items, the color ofthe cursor line, and the colorsthat each of the user-assignedindex lines change to when allitems in the sub-tree have beenchecked off or when a portion ofthem have been checked off.The color of the other lines aref i x e d .

w SUB INDEX PAGES

Starting with the pointers associ-ated with the root index page,sub-index pages can be created.These sub-index pages, or sim-ply index pages, can have entrieswhich point to either a list ofchecklist pages, or to anotherindex page. Within a given level,the user can chain index pagestogether. For example, starting atone of the index entries on theroot page, the user can create acollection of N index pages trail-ing off the entry on the root.Each index entry on the N indexpages can in turn point to anoth-

er list of sub-index pages (or alist of checklist pages). The indexpages form a hierarchy whichcan be nested arbitrarily deeply(subject to memory constraints).Each index page consists of atitle line with relative page num-ber indication, and up to elevenindex entry lines. These indexentries may span more than asingle line, but may not crosspage boundaries. As with theroot index page, the first twocharacter columns are reserved.

The user can select the color ofthe title line, and the color ofeach of the index entry lines. Inaddition, the color of the cursorline, the color of partially-com-pleted items, and the color offully-checked items can be speci-f i e d .

w CHECKLIST ITEM PAGES

Refer to figure 4.4.7. At the bot-tom of the checklist ‘tree’ are thechecklist page lists. These pagescontain individual checklistcheckoff items. The items onthese pages are either checkedor unchecked.

The contents of checklist pagesis similar in format to the indexpages, but with some importantdifferences. The title line consistsof title text and a relative pagenumber indication, as with theindex pages. The checklist itemportion consists of eleven lines oftext, with the first two charactercolumns reserved like the indexpages. A checklist entry canspan more than one line, but

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MFD Displays

cannot span across checklistp a g e s .

The user may specify the color ofthe title line, the color of the cur-sor line, the color of the checkeditems, and the color of theunchecked items. Note that thisimplies that the unchecked colorof each item cannot be selectedseparately. This helps to avoidcolor confusion within a checklistpage. Also, each item is eitherchecked or unchecked, so nopartially-completed checklistitems apply.

w NOTE PAGES

A separate portion of CP469Amemory is reserved for the entryof data for reference by the flightcrew, and can be modified sepa-rately from the checklist pagedata. The note page portion ofmemory will normally be small,allowing a quick update from thePC to that portion of checklistm e m o r y .

The DEU utility running on a PCis used to create note pages sim-ilar to the way the checklist iscreated. The NOTES entry onthe root index page points to anindex page listing entries for notepage lists, or other note pageindex pages. Index pages in thenote-page sub-tree are formattedjust like regular index pages,except that the indicators forcompleted/partially completedlists will never appear. Only thecursor will appear in the first twocharacter columns. The notepages themselves are similar inappearance to the checklist

pages. They have a title line withrelative page numbering, and 11lines of text.

The user may select the color ofthe note page title line, the colorof the text on the page, and thecolor of the cursor line.

w CLEARING CHECKLISTI T E M S

There are two ways to quicklyreturn all checklist items to theunchecked state. The first is toremove power from the CP 469Afor more than 15 seconds. Thesecond is to move the cursorover the CLEAR ALL CHECKEDITEMS on the root index page,and press the ENTER key. Thiswill cause a warning page to bedisplayed, with instructions onwhat to do to clear all thechecked items.

The ENTER key can be used touncheck individual checklistitems by placing the cursor on achecked item and then pressingE N T .

w EMERGENCY PAGEA C T I V A T I O N

The CP 469A provides eight pri-oritized discrete lines for emer-gency page use. Using the PC,the user can bind these activelow inputs to specific checklistpages, which can be tailored tothe nature of the emergency dis-crete. Any discretes which arenot bound using the PC will beignored by the CP 469A.

Whenever one of these inputs

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MFD Displays

goes low while checklist mode isactive, the checklist unit will auto-matically display an emergencysummary page listing all currentlyactive emergencies, and the titleof the list that the emergency isbound to. The user may selectthe emergency of choice, andpress the ENTER button. Controlis then transferred directly to theemergency list desired. As soonas the user checks off all itemsassociated with a given activeemergency, the checklist unit willagain display the emergencysummary page, showing thatemergency condition aschecked-off. This allows the userto know when all the checklistitems associated with an emer-gency have been checked off,and allows an easy way to pro-ceed to the next active emergen-cy, if one exists.

If an emergency discrete activa-tion is detected by the CP 469Awhile the checklist mode is notactive, a yellow “C-L EMER”message will be displayed on theMFD. When the user pressesthe CHK LIST button to activatethe checklist mode, the checklistunit will display the emergencysummary page as describedabove. This provides thepilot/copilot with an easy meansto determine the source of theemergency discrete (the name ofthe checkl ist it is t ied to willappear on the emergency sum-mary page) and to proceed tocheck off the items associatedwith that emergency. Once allthe items associated with a givenemergency are checked off, the

checklist unit will consider thatemergency ‘handled’, and willremove the request for the “C-LEMER” message. However, if agiven emergency discrete is re-applied after all items associatedwith that emergency have beenchecked off, the checklist unit willagain notify the user that a givenemergency has re-occurred viathe emergency summary page.

The CRS/SEL button can bepressed to display the emergen-cy summary page any time thechecklist mode is active. A sec-ond press of the CRS/SEL buttonat this time, returns the previous-ly displayed checklist page.While the emergency summarypage is displayed, the 1-2 keycan be used to display a list of allthe emergencies that weremapped to an emergency dis-c r e t e .w CHECKLIST CONTROLSChecklist: CHKLISTSelecting the CHKLIST buttonactivates and deactivates thechecklist function and causes theinformation to be displayed onthe MFD. The checklist will pro-vide approximately 800 pages ofnormal, abnormal, and emergen-cy data.

J o y s t i c kThe joystick can be moved sideto side, up and down, and to the45 degree points. The 45 degreepoints will be ignored in checklistm o d e .

Joystick position data will betransmitted continually to the

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MFD Displays

EFS MFD for use in MAP pro-cessing, and will be used by theCP 469A processor to enablemovement through checklistpages (when the CP 469A is inchecklist mode).A downward push on the joystickwill cause the cursor to movedown one line or item in thechecklist. The line down opera-tion advances from oneindex/item page to the next, andwraps within one level. Holdingthe joystick down continuouslywill cause the cursor to slewd o w n .

An upward push on the joystickwill cause the cursor to move upone line or item in the checklist.The line up operation advancesfrom one index/item page to theprevious page, and wraps withinone level of pages. Holding thejoystick up continuously willcause the cursor to slew up.

A rightward push on the joystickwill cause the cursor to go to thetop of the next page. The nextpage operation applies only with-in a single level, and wraps to thefirst page within a level. Forexample, a rightward push whileon the last page of a list of check-list pages will move the cursor tothe top of the first page in the list.Holding the joystick right continu-ously will cause the cursor toslew forward through the pages.

An leftward push on the joystickwill cause the cursor to proceedt o the top of the currently selectedpage, and subsequent leftwardpushes will move the cursor to

the top of the preceding pages.Paging is within a single level,and wrapping from the first to thelast page within a level will besupported. Holding the joystickleft continuously will cause thecursor to slew through the pagesin reverse.

Enter : ENT

The state of the ENT key is con-tinually transmitted to the EFS forMAP processing use, and is alsoused by the CP 469A for check-list purposes.

When in the checklist mode, theenter button will behave different-ly depending on where in thechecklist the cursor is located.The general behavior of theENTER key is to enable the pilotto check off everything in thechecklist by using the ENTERkey alone. In the checklist pages,pressing enter on an uncheckeditem will cause the cursor tocheck off that item and proceedto the next unchecked item in thelist. If no unchecked items existbetween the cursor position andthe end of the list of item pages,the cursor is placed on the firstunchecked index entry of the par-ent index list. If no uncheckedindex entries exist at that level,the search continues up thechecklist tree until an uncomplet-ed index entry is found, or untilthe cursor reaches the root indexpage. If the item is checked offand the enter button isdepressed, the line will beunchecked and the cursor willremain at the line justunchecked.

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When on an index page, press-ing the enter button will cause thecursor to move to the nextunchecked item or index entry itfinds. If the entry is not fully com-pleted, the cursor is moved to thenext lower level, and parked onthe first uncompleted item/entryon that level. If the index entrythat the cursor is on is alreadyfully checked-off, the cursor firstsearches the current list of indexpages for an unchecked indexentry, and then searches all thelayers of index pages upward,toward the root index page,always looking for an incompletechecklist. If all items are checkedoff, the cursor moves to the top ofthe root index page.On the root index page when thecursor is on the “CLEAR ALLCHECKED ITEMS”, pressing theenter button will cause a warningpage to come up asking for verifi-cation that the pilot truly wants toclear all checked items. An addi-tional push on this screen willcause all checked items to bec l e a r e d .

H S I

The HSI button will not functionwhile the checklist is active.

A R C

The ARC button will not functionwhile the checklist is active.

N A V

The NAV button will not functionwhile the checklist is active.

Up Arrow

When in checklist mode, an up-arrow (range-up) push will serveto move the cursor up the ‘check-list tree’. That is, if the cursor ison a checklist page, a range upwill move the cursor to the indexpage entry used to access thatlist. When the cursor is posi-tioned over an index page entry,the cursor will move to the indexpage and entry from which thecurrent index entry is accessed.A range up push on the rootindex page has no effect, sinceno higher level exists to go to.

Down Arrow

When in checklist mode, thedown arrow (range down) willmove the cursor down the‘checklist tree’ by moving the cur-sor into the branch accessedthrough any index page entry. Arange down push while the cur-sor is on a item page has noeffect, since there are no ‘lower’levels to go to.

1 - 2

When checklist mode is active,the 1-2 key normally will not beactive. However, if the activeemergency summary page is cur-rently displayed, the 1-2 key willcause the checklist unit to displayan informational page listing allcurrently ‘bound’ emergency dis-cretes. This page lists all eightemergency discretes, and thetitle of the checklist page thateach was bound to using theDEU utility software.

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MFD Displays

RMI 1

The RMI 1 button will not functionwhile the checklist is active.

RMI 2The RMI 2 button will not functionwhile the checklist is active.

CRS (NOT) SEL

When in checklist mode, theCRS(NOT) button will cause thechecklist unit to display the list ofactive emergencies. A secondpress returns the previous dis-p l a y .TST REF

When in checklist mode, the TSTREF button will cause the check-list unit to display a ‘canned’ helppage. This help page can beused by the pilot/copilot to remindthem what button combinationsare used in checklist mode. This

help page will appear as follows:CRS KnobThe CRS knob will not functionwhile the checklist is active.

REMOTELY MOUNTEDSWITCHESThe following functions of the CP

469A can be implemented withremotely mounted switcheswired to the rear connector.• Up Arrow : EXT UP• Down Arrow : EXT DWN• Enter : EXT ENTER• Joystick

FAULT ANNUNCIATIONSThere will be two possible controlpanel faults that will get dis-played on the MFD display if thecontrol panel fails. One fault isthe normal red CP fault causedby a mode line failure. The sec-ond fault is a red CCP faultcaused by a failure in the check-list control panel processing.The faults to be detected by theCP 469A to cause this annuncia-tor include the following:1. CPU test failure2. ROM test failure3. RAM test failure4. Stuck joystick or control

panel key5. Invalid data in checklist/notes

EPROM (checksum failure).This fault condition appliesonly if the EPROM chip isNOT completely erased. Thatis, if the checksum test onEPROM chip data failsbecause the chip is erased, aCCP fault should NOT beraised. This is because theCP469A will come from thefactory with the EPROM chipserased, and it is undesirablefor the product to show a faultstraight out of the box. Only ifat least one of the bits in theEPROM are programmed,and the EPROM checksumtest fails will a CCP fault be

4.4.10 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

CHECKLIST KEYSTROKE OPERATIONS

JOYSTICK UP:

JOYSTICK DOWN:JOYSTICK LEFT:

JOYSTICK RIGHT:

UP ONE ITEM

DOWN ONE ITEMPREVIOUS PAGE

NEXT PAGE

RANGE UP:

RANGE DOWN:ENTER:

CRS/SEL:

UP ONE LEVEL

DOWN ONE LEVELCHECK-OFF ITEM

ACTIVE EMERGENCY

PRESS TST/REF TO EXIT HELP


MFD Displays

g e n e r a t e d .TCAS INTERFACE

With software 08 and higher aconfiguration option available atthe time of installation and certifi-cation, provides a TCAS ONLYtraffic display on the MFD. A“TRAFFIC” message is providedif TCAS is configured for the pilotand co-pilot EHSI displays duringan active TA or RA, but intrudertraffic will not be shown on thesedisplays, only the MFD.

Range control will be retained bythe CP 469A MFD control panel.Above/norm/below and actual/relative altitude selections will bemade on the TCAS control panel.

Resolution advisory (RA) infor-mation such as a climb arrow willnot be shown on the MFD. RAtraffic will be displayed withTCAS II, but not TCAS I.

Whenever a normal operatingmode that does not displayTCAS traffic information is select-ed on an MFD display , “TRAF-FIC” will be annunciated to indi-cate that a TA or RA is inprogress. This annunciation willremain on non-TCAS displays aslong as at least one TA or RA isa c t i v e .

All RA, TA, and PROXIMATETRAFFIC will be displayed on theMFD when TCAS is configuredand TCAS ONLY is selected,regardless of display format andaltitude limits. OTHER TRAFFIC

within the selected altitude limitswill also be displayed when pos-sible. The EFS 40/50 will displayup to 20 TCAS intruders on theM F D .

w TCAS ONLY SELECTION

With EFS software 08 and later,a dedicated TCAS select pushbutton on the CP 469A MFDControl Panel labeled “TCASONLY” will provide 360° TCASONLY (range = 5 nm) on theMFD with a single selection. Thismomentary switch will altermate-ly select TCAS ONLY and lastdisplay mode. The last displaymode will be restored exactly,including previous range andmap format.

TCAS and checklist are mutuallyexclusive modes that will canceleach other such that only themost recently selected will bea c t i v e .

Default conditions at selection:360° format5 NM rangeAll intruders displayed

(20 max.)Operation while selected:

Ranges available: 2, 5, 10, 20,40 NM

360° format onlyTST/REF, NAV, RMI 1, RMI 2,

ENT, JOYSTICK and 1/2buttons are inactive

D e - s e l e c t i o n :The dedicated TCAS ONLY select always returns to the last

4.4.11Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


MFD Displays

display mode.w TCAS DISPLAY FORMAT

TCAS ONLY display will be 360°format and normally contain thefollowing elements:

* Small cyan symbolic aircraftsymbol located in the center ofthe 360° TCAS ONLY display.

* Two NM range ring consistingof cyan dots positioned every30 degrees to represent the 12clock positions. Presented on 2NM (after software 10), 5 NM and 10 NM ranges only.

* Full range ring consisting ofcyan radial tick marks pos-itioned every 30 degrees torepresent the 12 clock pos-itions plus intervening cyandots every 10 degrees.

* Map type half range ring (whitedashes) without range annunc-iation on 20 NM and 40 NMr a n g e s .

* “TCAS” annunciation in verticalfield in place of nav source.

* TCAS mode annunciation.* TCAS range annunciation.* Up to two no-bearing intruder

m e s s a g e s .* Above/norm/below annuncia-

t i o n .* Actual intruder altitude and

(FLXXX) annunciation whena p p r o p r i a t e .

* TCAS traffic symbols (intruder,data tag, and vertical speeda r r o w ) .

w TCAS TRAFFIC SYMBOLO -G Y

Each intruder symbol wil l beaccompanied by a data tag and,

when appropriate, a verticalspeed arrow. The data tag andarrow will be the same color asthe intruder symbol that they areassociated with. The intrudersymbol, data tag, and verticalspeed arrow will appear thesame size regardless of ranges e l e c t i o n .

Intruder Symbols

Note: RA traffic is not providedwith TCAS I.

Traffic generating a ResolutionAdvisory (RA) will be displayedas solid red squares. Traffic gen-erating a Traffic Advisory (TA)will be displayed as solid yellowcircles. Proximate traffic will bedisplayed as solid white dia-monds. All other, no threat trafficwill be displayed as hollow (out-line only) white diamonds.Intruder symbols are centered onthe actual intruder location.

Vertical Speed Arrow

The vertical speed arrow will bepositioned immediately to theright of the intruder symbol whenthe intruder vertical trend is climbor descend as reported by theTCAS processor. The arrow willpoint up for climbing traffic anddown for descending traffic.

Data Tag

The data tag will normally consist

4.4.12 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


MFD Displays

of a + or - followed by two digitsof altitude difference (relative alti-tude) in hundreds of feetbetween the intruder and ownaircraft. (+ = intruder above ownaircraft) During selection of actu-al alt itude, and with a validsource of own altitude providedby the TCAS processor, the datatag will consist of three digits rep-resenting hundreds of feet aboveMSL. Actual altitudes below sealevel will be displayed as two dig-its preceded by a minus sign.The data tag will be centered onthe intruder symbol and posi-tioned above it when the intruderis above own aircraft. The datatag will be positioned below theintruder symbol when the intruderis below own aircraft. The rela-tive altitude data tag for intrudersat the same altitude as own air-craft will consist of “00” without a+ or - sign and be positioned toindicate the intruder ’s mostrecent altitude deviation fromown aircraft. When no altitudetrend information is available, the“00” is positioned below the traffics y m b o l .

Off-Scale Traffic

RA and TA traffic that is locatedbeyond the selected range of aTCAS display will be shown asone half of the appropriate intrud-er symbol located on the outeredge of the displayed area at theproper bearing. A data tagand/or vertical speed arrow asso-ciated with this intruder will retainits normal position relative to theintruder symbol and only thatportion (if any) within the normal

display area will be visible.

w TCAS DISPLAYA N N U N C I A T I O N S

T r a f f i c

During an active RA or TA, a“TRAFFIC” message will beannunciated in large text on allEFS displays configured for dis-playing TCAS traffic but withTCAS de-selected. This annun-ciation will be provided for all nor-mal operating modes, but notwhile maintenance or configura-tion pages are displayed.“TRAFFIC” will be red during anactive RA and yellow during anactive TA (an RA has priorityover a TA). This annunciationwill not be made while TCAS isselected for display. Beginningwith software 0802, the "TRAF-FIC" message will be replaced bya "NO TCAS " message for 15seconds following a TCAS failureor a change of TCAS mode toS t a n d b y .

N o t e : A remote annunciatormay be included in someinstallations to provide full timeTCAS operational status.

T C A S

TCAS ONLY format will include acyan “TCAS” displayed in thevertical field where the selected

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MFD Displays

navigation source is normally displayed in other modes.TCAS Status

TCAS mode, range, above/norm/below selection, and actual altitude(FL) selection will be presented in the bottom right corner of the dis-play normally used for the RMI 2 pointer annunciations. FLxxx and

ABV/BLW are both provided inthe same five character fieldwhen specific conditions are sat-isfied as shown in the followingt a b l e .TCAS Mode

TEST - Indicates that the TCASprocessor is performing sys -tem test.

4.4.14 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

TCAS STATUS ANNUNCIATION

TD FAIL - Indicates that thecapability of the EFS to prop -erly display TCAS traffic issuspect.

TCAS FAIL - Indicates that theTCAS processor (or a TCASantenna) has failed.


MFD Displays

NO TCAS - Indicates that aTCAS system component(other than TCAS processorand TCAS antenna) has failed.

TCAS STBY - Indicates thatTCAS has been intentionallyplaced in standby mode.

TA - Indicates that TA ONLYmode has been entered by theTCAS processor.

When displayed, the annuncia -tion color will be yellow if anyintruder is a Traffic Advisory(TA). The color will be cyanwhen there are no intrudersclassified as a TA.

TA/RA - Indicates normal opera -tion for TCAS II. This annunci -ation wil l not appear whenTCAS I is installed.

R a n g e

Range is annunciated in cyanwithout an alpha prefix immedi-ately to the left of the TCAS sta-tus information. The rangesavailable are 2, 5, 10, 20, 40.

A b o v e / N o r m / B e l o w

All TCAS displays will annunciatea cyan “ABV” or “BLW” whenabove or below respectively areselected on the TCAS controller.Neither annunciation is providedwhen normal is selected. Thissame three character field is alsoused to present own aircraft alti-tude when actual altitude (FL) isselected. The FL annunciationhas priority over ABV and BLW.

No-Bearing Traffic

During any TCAS display, up totwo no-bearing traffic messagesmay be required. The format forthese messages is “TA 5.7NM/-0 6↑” or “RA 0.8NM/+01↓” where-06 and +01 are the relative alti-tudes of the intruder aircraft. Rel-ative altitudes (including the + or- sign) will be replaced by a 3digit actual altitude in hundreds offeet whenever the conditions fordisplay of actual altitude havebeen satisfied. RA messageswill be red and TA messages willbe yellow. The vertical speedarrow, when climb or descend isindicated, will be displayed imme-diately to the right of the altituded i g i t s .

FLXXX and FL

A white FLXXX is annunciatedonly when actual intruder altitude(FL) is being displayed. Thisannunciation will be absent whenrelative intruder altitudes are dis-played. XXX will be own aircraftactual altitude in hundreds of feetas provided. This annunciationwill be “FL---” (dashes added bysoftware version 10) in yellowwhen actual altitude has beenselected but a valid source ofown aircraft actual altitude is notprovided by the TCAS processor.Negative actual altitudes will bedisplayed as two digits precededby a negative sign. (FL-XX)

4.4.15Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


MFD Displays

Note: At the time of this publica -tion, TCAS displays in con -junction with other display for -mats has not been certified.

EGPWS INTERFACEo Beginning with software 14, aconfiguration option available atthe time of installation and certifi-cation provides an EGPWS ter-rain display on the MFD.

w EGPWS SELECTION

Beginning with EFS software 14,a dedicated Terrain Select pushbutton determines whetherWeather or Terrain data is shownon the MFD.

When EGPWS is manuallyselected via the Terrain Selectpushbutton, the terrain data willbe displayed in the currentlyselected HSI/ARC format.

When EGPWS is automatically(pop-up) selected, the display willchange to:

ARC format, 10 NM range

Automatic selection (pop-up) isinitiated by the EGPWS detectinga terrain Warning or Caution con-dition and setting a pop-up dis-crete. Pop-up is monitored onlywhen the terrain is selected.

Upon deselection of Terrainmode, weather data will be redis-played in the current HSI/ARCformat. The previous scan anglefor weather will be restored. If VPor SS was selected prior to ter-rain selection, VP or SS display

mode will be restored.

w EGPWS DISPLAY FORMAT

Terrain display will show 180° ofscan angle and normally containthe following elements:* Mode/status annunciation.* Range annunciation.

w EGPWS MODE/STATUSEGPWS mode will be presentedon three lines in the bottom right(or left, as configured) corner ofthe display.

The first line will be a whiteTERR annunciation. Lines twoand three each may be a sixcharacter text message annuciat-ing the current EGPWSm o d e / s t a t u s .

TEST - EGPWS processor isperforming system test.

TERR FAIL - EGPWS processoris no longer communicatingwith the EFIS system.

TERR RANGE EXCEED - Arange greater than 320 nm isselected.

TERR RANGE FAULT - Indi -cates a mismatch of the speci -fied range between the EFISCP and the 453 data.

EGPWS PEAKS ELEVATION -Maximum peaks elevation dis -played over minimum peakselevation.

w EGPWS RANGE

Range control will be retained by

4.4.16 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.17

Figure 4.4.1MFD ARC COMPASS + WX SYMBOL DEFINITION


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.18

Figure 4.4.2MFD WEATHER ONLY DISPLAY


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.19

Figure 4.4.3MFD VP DISPLAY


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.20

Figure 4.4.4MFD SPLIT SCREEN DISPLAY

(NOTE: SW 09 and later)


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.21

Figure 4.4.5MFD PLAN VIEW DISPLAY


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.22

Figure 4.4.6TCAS ONLY DISPLAY


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.22a

Figure 4.4.6aEGPWS DISPLAY


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.23

Figure 4.4.7MFD CHECKLIST ROOT INDEX PAGE DEFINITION


MFD Displays

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 4.4.24

Figure 4.4.8MFD CHECKLIST SAMPLE PAGE


Operating Instructions

Consult Aircraft Flight ManualSupplement for specific proce-dures and limitations in opera-t i o n .

PREFLIGHT PROCEDURES

w START UP

At engine start, power should notbe applied to the EHI 40/50 sys-tem, low voltage may turn theE F S 40/50 system off momentar-ily, and transient voltages mayinduce premature failures. Withengines operating, turn on gyrosand flight control systems, turnon avionics master switches toinclude the EFS 40/50 master,and turn on NAV systems toremove the EHSI flags.

When power is initially applied tothe EFS 40/50 system, variousflags maybe annunciated on thedisplay, representing systems notyet operational.

w SELF TEST

Adjust BRT control on theE F S 40/50 CP 467, CP 468 orE D 461 and CP 470 for thedesired brightness.

After a short warm-up time, pressand hold the TST/REF button forthree seconds to display theSELF TEST. A SELF TESTPASS or SELF TEST FAIL mes-sage will be annunciated. If the

system is operating properly theSELF TEST PASS message willbe annunciated. If a malfunctionexists, SELF TEST FAIL will beannunciated and the systemshould be serviced. Refer to fig-ure 5.1 and 5.2, Self Test annun-ciation. Additionally, the pilotshould ensure that the compassscale is white, which indicatesthat all three colors are opera-tional in the display unit.

Note: Performing the EFS 40/50Self Test is not required atanytime. If a failure was tooccur or exist, the small REDSG in a red box would be dis -played. This test is intended tofamiliarize the pilot with thevarious flagging methodologyused and a quick check forproper color presentation.

The EADI self test page will auto-matically revert to a normal EADIdisplay. After software 07, theEHSI will also automaticallyrevert to normal operation fromthe self-test page after five sec-o n d s .

w PUSH BUTTON TEST

Check each push button functionon the EFS 40/50 control panel.Push button operation should beas described in 2.1 EHSI Opera-tion, 2.2 EADI Operation, 2.3RADAR Operation.and 2.4 MFDO p e r a t i o n .

5.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

OPERATING INSTRUCTIONS



PRE-TAKEOFFPROCEDURES

After the system test has beencompleted, select the desired Pri-mary NAV sensor with the NAVsource select push button. Setthe desired course and heading,and check that the appropriatedisplay is present on the indica-tor. Set the desired NAV frequen-cies for the departure phase ofthe flight. Then press the appro-priate push buttons (HSI, ARC,BEARING #1, BEARING #2,etc.) on the EFS 40/50 controlpanel for the desired display pre-sentation.

IN-FLIGHT OPERATION

Select the desired type of NAVsensor for the primary NAV dis-play by pressing the NAV pushbutton until the desired source isannunciated.

Select NAV system #1 (left) or #2(right) by pressing the 1-2 pushb u t t o n .

Select HSI or ARC display bypressing either the HSI or theARC push button.

Select the display mode (mapand/or weather radar) by sequen-tial presses of the HSI or ARCpush button.

Use HEADING SELECT (SYNCor HDG) or COURSE SELECT(DIR or CRS) knobs to select thedesired heading or course.

On the ED 461 with built in con-trols, the center push buttons onthe knobs may be used to 1)rapidly acquire the DIRECT TOcourse to the station (DIR pushbutton), or 2) center the headingbug under the lubber line (SYNCpush button). On the CP 468 separate controlpanel, the heading and courseknobs may be used to 1) rapidlyacquire the DIRECT TO courseto the station (pull DIR knob), or2) center the heading bug underthe lubber line (pull SYNC knob).

Use the #1 and #2 BEARINGPOINTER SELECT push buttonsto select the sensor desired bypressing the push button until thedesired source is annunciated.These push buttons are alsoused to display independentDME information without a bear-ing pointer.

w ADF

After selecting ADF mode andtuning ADF #1 receiver to thedesired NDB, set Bearing pointer#1 to ADF. Using CRS control,select desired course TO orFROM the NDB. The coursedeviation bar on the EHSI nowprovides left-right guidance in fly-ing the selected course just as itwould in flying a VOR course.This eliminates the mental calcu-lations required while tracking anNDB course in the conventionalmanner. NDB station passage isindicated by the TO-FROM indi-cator and Bearing pointer rever-s a l .

5.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16



Note: ADF D-Bar presentationmay not be avai lable if theADF does not provide a suit -able flag output.

w LNAV (RNAV)

After selecting LNAV, NAV( K N S 81 programmed as anRNAV), GPS or RNAV mode andthe desired waypoint, set BearingPointer #1 to the desired #1bearing source. Using CRSknob, select desired course TOor FROM the waypoint (for theon-side LNAV only). The coursedeviation bar on the EHSI nowprovides guidance in flying theselected course. Waypoint pas-sage is indicated by the TO-FROM indicator and waypointBEARING pointer reversal.

N o t e : Wind vector and speedinformation is presented if sup -plied by ancillary equipmentand only if the system wasconfigured to display the infor -mation during installation.

Once the external LNAV systemtransmits to the EFS 40/50 that itis in an enroute mode, the EHSIand system sensitivity is set at5NM left or right of course for full-scale CDI deflection.

Note: Depending on the type ofLNAV installed, the LateralDeviation Scale may be differ -ent and may support only DTK.

w V N A V

VNAV operation greatly dependson the type of VNAV installed. Itis therefore very important torefer to the Aircraft Flight ManualSupplement and VNAV operationmanual for additional information.

APPROACH PROCEDURES

w ILS APPROACH

On the CP 467, CP 468 orE D 461, select VOR as the Pri-mary NAV sensor with the NAVpush button. Then tune theappropriate ILS frequency. Noteon the EHSI that when an ILSfrequency is selected LOCreplaces the VOR annunciation,the glideslope scale is displayed,and as the glide slope and local-izer scales appear on the EADIthe sky/ ground raster is reducedin size to provide a high-contrastbackground for them. Once anILS frequency is selected, theBearing pointer and TO-FROMindicator associated with thatNAV disappears.

When DME Hold is selected onthe DME control panel, DME dis-tance is displayed in white.Groundspeed or Time-To-Stationis replaced with the held VORfrequency followed by an orangeH for HOLD. (DME groundspeedand VOR frequency may not bedisplayed in all installations.)

5.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16



w BACK COURSE APPROACH

An option may be selected at thetime of installation and certifica-tion to automatically declutter GSinformation when the aircraftheading is greater than + or - 105degrees from selected ILScourse. EHSI NAV MAP CDIsensing is reversed and “BC” isannunciated below the deviationscale. EADI CDI sensing isreversed and “BC” is displayed tothe left of the center diamond.

Not all installations will declutterthe glideslope scale. This is adisplay configuration optionselected at the time of installa-t i o n .

w ADF APPROACH

After selecting ADF mode andtuning ADF #1 receiver to thedesired NDB, set Bearing pointer#1 to ADF. Using CRS control,select desired course TO orFROM the NDB. The coursedeviation bar on the EHSI nowprovides left-right guidance in fly-ing the selected course as itwould in flying a VOR course.This eliminates the mental calcu-lations required while tracking anNDB course in the conventionalmanner. NDB station passage isindicated by the TO-FROM indi-cator and Bearing pointer rever-s a l .

N o t e : DF D-Bar presentationmay not be avai lable if theADF does not provide a suit -able flag output.

w LNAV (RNAV) APPROACH

After selecting LNAV mode andthe desired waypoint, set BearingPointer #1 to the desired #1bearing sensor. If the installedLNAV supports selected coursefrom the EFS 40/50, use theCRS knob to select desiredcourse TO or FROM the way-point. The course deviation baron the EHSI now provides guid-ance in flying the selectedcourse. Waypoint passage isindicated by the TO-FROM indi-cator and waypoint Bearingpointer reversal.

Once the external LNAV systemtransmits to the EFS 40/50 that itis in an approach mode, the cyancolors turn green on the EHSIand system sensitivity increasesto 1.25 NM or ± 0.3 NM for GPSleft or right for full-scale CDIdeflection. The sensitivi tybecomes variable when doing aG P S approach with variableVNAV enabled for SW 15 andlater. Cross-side annunciationremains yellow, but the increasedsensitivity is implemented if thecross-side LNAV is in ApproachApproved mode.

Note: Depending on the type ofLNAV instal led, the LateralDeviation Scale may be differ -ent and may only support DTK.

w VNAV GPS PRECISIONAPPROACH

When the LNAV is capable ofdisplaying precision approaches

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(such as WAAS), the verticaldeviation scale will appear pro-vided valid data is being receivedfrom the LNAV and a properapproach procedure is active.Refer to the navigator pilot'sguide for full scale vertical deflec-tion operation.

w VOR APPROACH

After selecting NAV mode andtuning the VOR receiver to thedesired frequency, set BearingPointer #1 to VOR #1. UsingCRS control, select desiredcourse TO or FROM the VORstation. The course deviation baron the EHSI now provides guid-ance in f lying the selectedcourse. VOR passage is indicat-ed by the TO-FROM indicatorand Bearing pointer reversal.

Note that EHSI NAV informationis similar to ADF except thatVOR is displayed rather thanA D F .

w DECISION HEIGHTS E L E C T I O N

Pull the DH set knob on theC P 467 or CP 470 to activate theDH set display on the EADI.Adjust the DH set knob to selectthe desired decision height forthe particular approach. Pushthe DH set knob in, the select DHwill be decluttered until the radaraltimeter becomes valid at orbelow 2500 feet.

LIMITATIONS

For information on EFS 4 0 / 5 0system operating limitationsplease refer to the approvedFlight Manual Supplement for theparticular aircraft in question, ifone is provided.

EMERGENCYPROCEDURES

For information on EFS 4 0 / 5 0system emergency proceduresplease refer to the approvedFlight Manual Supplement for theparticular aircraft in question, ifone is provided.

5.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16




5.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16



SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 5.7

Figure 5.1EHSI SELF TEST

Section 5 POmp 9/9/10 3:54 AM Page 5.7


SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 5.8

Figure 5.2EADI SELF TEST


Fault Annunciations

GENERAL

EXTERNAL SYSTEM FAILURESw H E A D I N GOnce a heading failure is detect-ed, the EHSI lubber line andcourse pointer head and tail areremoved. The lubber line isreplaced by a RED box with aRED HDG inside it. The coursedeviation scale is frozen horizon-tally to perform the function of aconventional CDI. Selectedcourse reference is provided bythe alphanumeric CRS readout inthe upper left corner. If headingwas configured for display onEADI horizon line, a RED boxwith a RED HDG inside it will bedisplayed upper left of center.During a heading failure the auto-matic Back Course function nor-mally performed by the

6.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

FAULT ANNUNCIATIONS

E F S 40/50 system is inhibited.Refer to Figure 6.2 and 6.4.w A T T I T U D EOnce an Attitude failure is detect-ed, the pitch scale, roll scale, rollindex pointer, horizon line, head-ing tape, blue sky and brownground are removed from the dis-play. A RED box with a red“ATTITUDE FAIL” inside it is dis-played on a black background inthe upper center of the display.w FLIGHT DIRECTOROnce a Flight Director failure isdetected a RED box with a red“FD” inside it will be displayed onthe upper right side of the EADI.Refer to Figure 6.4, EADI Faults.

w DU—DISPLAY UNIT LOSSOF COOLING

A yellow DU enclosed in a yellowbox is annunciated at the bottomleft center of the EHSI or bottomleft of the EADI when insufficientairflow is detected in the DisplayUnit. Once annunciated, thefaulty Display Unit will continue tooperate for at least 30 minutes ifthe rated ambient temperature isnot exceeded. To extend theoperating time, reduce displayinformation and brightness to aminimum. Refer to Figure 6.1and 6.4.

w SG—SYMBOL GENERATORLOSS OF COOLING

A yellow SG enclosed by a yel-low box is annunciated at thebottom right center of the EHSIand bottom left of the EADI ifinsufficient airflow is detected inthe Symbol Generator. Onceannunciated, the Symbol Gener-ator will continue to operate for atleast 30 minutes if the ratedambient temperature is notexceeded. To extend the operat-ing time, reduce display informa-tion and brightness to a mini-mum. Refer to Figure 6.1 and6 . 4 .

EFS 40/50 SYSTEM FAILURES


Fault Annunciations

w CP—CONTROL PANEL(CP 467, CP 468, ED 461 ORC P 4 7 0 )

A RED CP enclosed by a REDbox is annunciated left center ofthe EHSI and lower left of theEADI if a control panel switchbecomes stuck for greater than10 seconds. If a switch fails thedisplay should maintain all cur-rently selected conditions. If theswitch should become functionalthe fault annunciation will beremoved and normal operationwill be restored. Refer to Figure6.1 and 6.4.

There are two possible MFD con-trol panel faults that can be dis-played on the MFD. One fault isthe normal red CP fault causedby a mode line failure. The sec-ond fault is a red CCP faultcaused by a failure in the check-list control panel processing. Thefaults to be detected by the CP469A to cause this annunciatorinclude the following:

1.CPU test failure2.ROM test failure3.RAM test failure4.Stuck joystick or control panel

k e y5. Invalid data in checklist/notesEPROM (checksum failure). Thisfault condition applies only if theEPROM chip is NOT completelyerased. That is, if the checksumtest on EPROM chip data failsbecause the chip is erased, aCCP fault should NOT be raised.This is because the CP469A willcome from the factory with theEPROM chips erased, and it is

undesirable for the product toshow a fault straight out of thebox. Only if at least one of thebits in the EPROM are pro-grammed, and the EPROMchecksum test fails will a CCPfault be generated.

w HEADING SELECT “BUG”

A RED X will be drawn throughthe heading bug if there is aheading select knob failure onthe EFS 40/50 control panel.Refer to Figure 6.2.

w COURSE SELECT

A RED X will be drawn throughthe course pointer head and tail ifthere is a course select knob fail-ure on the EFS 40/50 controlp a n e l .

w RCP—RADAR CONTROLPANEL (if equipped)

A RED RCP enclosed by a REDbox is annunciated at the lowerleft center of the EHSI display if aradar control panel failure isdetected. Refer to Figure 6.1.

w SG—SYMBOL GENERATOR

A RED SG enclosed by a REDbox is annunciated at the upperleft center of the EHSI or lowerleft of the EADI if certain moni-tored functions are detectedinvalid. If the RED SG annuncia-tion is encountered extreme cau-tion should be used to validateany data used on the display fornavigation. Even after validationand revalidation the data should

6.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Fault Annunciations

only be used as supplementaryi n f o r m a t i o n .

A large RED “SG” appearing ona black display annunciates aSymbol Generator failure whichwould result in processed datathat is unusable for navigation.

RAW DATA DEVIATIONANNUNCIATIONS

Pointer/Scale malfunctions areannunciated by removal of theassociated pointer/scale andplacing a RED X drawn in theirplace. A flag presented on thevertical deviation scale will resultin the deviation pointer beingremoved. On the EHSI, thepointer/scale annunciationsinclude lateral deviation, GS orVN and fore/aft in Doppler andhoming mode. On the EADI, thescale annunciations include later-al deviation and GS or VN. Referto figure 6.1 for display presenta-tions showing these annuncia-t i o n s .

Beginning with software 09, bothlateral and vertical deviation barsand scales are decluttered with-out displaying a RED X when thedeviation information is providedin ARINC 429 format with a sta-tus of No Computed Data (NCD).The RED X is still displayed forinvalid or missing data.

w BEARING POINTERA N N U N C I A T I O N S

Bearing pointer source failure orinvalid data or No ComputedData (NCD) causes a RED X to

be drawn through the sourceannunciator. The bearing pointeror NAVAID symbol is alsoremoved.

w ALPHANUMERIC READOUTA N N U N C I A T I O N S

Failures affecting alphanumericreadouts are annunciated by aRED X drawn through the read-out. On the EHSI (figure 6.1), thealphanumeric readouts includeNAV bearing pointer source andcourse (CRS) or desired track( D T K ) .

Failures affecting distance infor-mation are annunciated by REDdashes in the data field. Whenthe Distance Source is opera-tional but not providing valid dis-tance data (no lock on or NCD)dashes the color of the sensorwill be placed in the data field.Speed (KT) and time (MN)annunciation will be removed ifvalid distance, speed and time-to-station information is not pro-vided by the primary NAV sensors y s t e m .Failures affecting radio altimeterinformation are annunciated byRED dashes in the data field onthe EADI. When the radioaltimeter source is operationalbut not providing valid data (nolock on or NCD) white dasheswill be placed in the data field.Refer to Figure 6.4.

w CHECK CONFIG

A yellow “CHECK CONFIG”message will display in the upperright corner of the EHSI and

6.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Fault Annunciations

EADI whenever the system con-figuration memory in the symbolgenerator and aircraft installationrack do not match.

Test routines resident in the sym-bol generator select the best pos-sible system configuration to use,however, the selected configura-tion may not be the intended one.Once the CHECK CONFIG mes-sage is noted, extreme cautionshould be exercised when usingany information. It is also mostimportant that the aircraft betaken to an authorized dealer forrepair as soon possible.

WEATHER RADARANNUNCIATIONSWhile displaying weather, a whiteweather radar failure or warningannunciation can appear belowthe Weather Mode annunciation.

The annunciations capable ofbeing displayed when interfacedwith an RDS 81, 82/VP, 84/VP,86/VP and RDR 2000/2100 arelisted below in order of priority.

w WX FLT

Advises a mismatch of mode, tilt,gain or range informationbetween the EFIS and radar RThas existed for more than 30 sec-o n d s .

w W X O F F

This annunciation (“OFF” beforeS W 08) is displayed when theradar is off.

w BUSY VP

Displayed when the radar is inthe continuous VP mode.

w RT FLT

Displayed with an RDR2000/2100 radar only to indicatean ART fault that can not beidentified as a radar transmitterfault (TX FLT).

w STB LMT

Displayed when the combinationof tilt, roll, roll trim and pitchexceeds +/- 30 degrees.

w T G T A L R T

Beginning with EFS software ver-sion 10, “TGTALRT” is annunci-ated in yellow to indicate anactive Target Alert. EFS with soft-ware version 09 displays thismessage in white. This messageis only provided by the RDR2 0 0 0 / 2 1 0 0 .

w T G T

Beginning with EFS software ver-sion 10, “TGT” is displayed inwhite to indicate that the TargetAlert feature is armed. This mes-sage is only provided by the RDR2 0 0 0 / 2 1 0 0 .

w 429 FLT

Displayed when 429 control datais missing or incorrect at theradar RT. Can also indicateimproper data from a 429 sensorto the RDR 2000/2100 radar.

6.4 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Fault Annunciations

w ANT FLT

Displayed when the measuredantenna tilt does not match therequested tilt angle.

w TX FLT

Displayed when a fault is detect-ed in the radar transmitter.

w R A N G E

Displayed when the pilot hasselected the 1000 mile range onthe EFIS. The radar is unable tooperate at this range and isplaced in standby.

o Installation with an RDS 81,RDS 82, RDS 82VP or RDR 2000with EFS software 07 or later,“RANGE” will annunciate whenthe 5 NM, 320 NM or 1000 NMrange is selected.

o Installation with software 06“WX FLT” (weather fault) willannunciate when the 5 NM or320 NM range is selected.These annunciations alert thepilot of a range mismatchbecause the RDS 81, RDS 82and RDS 82VP do not supportthese radar ranges.

w STB OFFDisplayed when stab off hasbeen selected or when the stabi-lization reference is not presentat the radar.

w W A I TDisplayed when in VP mode andone of the TRACK buttons ispressed, indicating the radar willperform the desired slicing func-tion as soon as the antennareturns to the last selected profil-ing azimuth angle.

CUSTOM DISPLAYFAILURE ANNUNCIATIONS

DOPPLER/CABLEw EXTERNAL SYSTEMF A I L U R E S

FMS WarningIn the upper right hand corner ofthe display, a RED X will bedrawn through a cyan FMS if theFMS has failed or is not supply-ing the EFS 40/50 with validcomputed data.Autopilot WarningIn the upper left hand corner ofthe display, a RED X will bedrawn through a red COUPLER ifthe autopilot or coupler has failedor is not supplying the EFS 4 0 / 5 0with valid computed data.N o t e : A configuration option

selectable at the time of instal -lation and certification allowsfor installations of the Dopplerand Cable mode without inter -face to an autopilot or coupler.If this option is selected theCOUPLER warning will not beannunciated.

6.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Fault Annunciations

w TCAS FAULT MESSAGESThe TCAS ONLY display on anMFD will be replaced with up tosix yellow fault messages. Dur-ing this time the annunciatedTCAS status will be either “TCASFAIL” or “NO TCAS” as appro-priate. Except for the statusannunciation and fault mes-sages, the display will be com-pletely black.The fault messages are listed inorder of priority with the highestfirst. TCAS FAIL messages havepriority over NO TCAS mes-sages, however both can be dis-played simultaneously (up to sixt o t a l ) .

Also refer to the TCAS Statusmessages listed in Section 4.4.

N o t e : The following is a com -plete list of all TCAS II faultsthat the EFIS will display, how -ever some of these are notapplicable to TCAS I and willnot be generated by a TCAS Iprocessor. Refer to the TCASPilot's Guide for more informa -tion.

Fault Messages for TCAS Fail:P R O C E S S O RUPPER ANTENNALOWER ANTENNA

Fault Messages for No TCAS:RADIO ALT 1/2RADIO ALT 1RADIO ALT 2XPDR 1/2XPDR 1XPDR 2A T T I T U D E

6.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

H E A D I N GRA DISPLAY 1/2RA DISPLAY 1RA DISPLAY 2XPDR UPPER ANTXPDR LOWER ANTTCAS TO XPDRCP TO XPDRALT 1/2 TO XPDRALT 1 TO XPDRALT 2 TO XPDR

w LIGHTNING DETECTIONDISPLAY FAULT MESSAGESWhen 429 data from the lightningsensor is missing for two sec-onds or remains invalid for tenseconds, the EFIS will removethe lightning cells from the dis-play and present a fault annunci-ation consisting of a lightningsymbol followed by the letters“ F L T ” .


Fault Annunciations

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 6.7

Figure 6.1EHSI FAULT ANNUNCIATION


Fault Annunciations

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 6.8



Fault Annunciations

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 6.9



Fault Annunciations

SW 04/05/06/07/08/09/10/11/12/13/14/15/16Issued 8/10 6.10

Figure 6.4EADI FAULTS


REVERSIONARY Modes

The EFS 40/50 provides four dif-ferent reversionary modes ofoperation in the event of a sys-tem component failure; compos-ite, copy, display down andstandby. The reversionarymodes offered in a particular air-craft will vary depending on EFISsystem configuration, installationwiring and certification. The fol-lowing section describes the vari-ous reversionary modes offeredwhen using the SU 4 6 3 .

All external switches and plac-ards are part of the installationsupplied by the installer. Forinformation pertaining to a partic-ular aircraft installation refer tothe approved Aircraft Flight Man-ual Supplement.

N o t e : This Pilot’s Guide refersto the left of the aircraft as thePilot’s position. The right sideis considered the copi lot ’sposition.

7.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

REVERSIONARY MODES


REVERSIONARY Modes

CMPST - COMPOSITE

Refer to Figure 7.1 ,COMPOSITE MODES E L E C T I O N .

CMPST (composite) is generallyused to compensate for a failureof a display unit or the EADI sec-

tion of the symbol generator.Available for use in two, three,four and five-tube installations. Asingle switch input to the SG 465instructs the symbol generator tooutput the CMPST display on theEADI and EHSI. See section 4.3for details on the composite dis-p l a y .

7.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 7.1COMPOSITE MODE SELECTION


REVERSIONARY Modes

COPY OFF-SIDE

Refer to Figure 7.2PILOT COPY OFF-SIDEMODE SELECTION.

COPY OFF-SIDE is generallyused to compensate for a failureof the EADI or EHSI section ofthe symbol generator or both.Available for use in dual EHSIand four-tube installations. TheCOPY mode will allow either thepilot or copilot to copy the EADIand EHSI display presentationsfrom the off-side system. When“COPY” is requested, the OFF-

SIDE SG will provide identicalcopied presentation on both thepilot and copilot displays. Topositively annunciate the selec-tion of the “COPY OFF-SIDE”mode, yellow boxes will be dis-played around all sensors alert-ing pilot and copilot they are bothusing the same NAV, HDG andATT source, also “COPY” will beannunciated in the lower rightcorner of the EADI and EHSI dis-play. Operational control will beretained by the side with theoperating SG (the side that didnot request COPY).

7.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 7.2PILOT COPY SELECTION


REVERSIONARY Modes

DISPLAY (EADI) DOWN

Refer to Figure 7.3,EADI DOWN MODES E L E C T I O N .

DISPLAY (ADI) DOWN modeselection is generally used tocompensate for a failure of theEADI display unit or section ofthe symbol generator. Availablefor use in two, three, four andfive-tube installations. The DIS-PLAY DOWN mode will allow the

pilot or copilot to transfer the nor-mal EADI display to the EHSIbelow the failed EADI and trans-fer the EHSI display to the MFD ifone is installed. A singlemomentary switch input to theS U 463 removes power from thefailed EADI, transfers the EFIScontrol panel control to the MFDsymbol generator, instructs theEHSI symbol section to calculateEADI function and the MFD sym-bol generator to calculate match-ing EHSI functions.

7.4 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 7.3DISPLAY (EADI) DOWN MODE SELECTION


REVERSIONARY Modes

STBY - STANDBY

Refer to Figure 7.4,PILOT STBY MODES E L E C T I O N .

STBY (STANDBY) mode selec-tion is generally used to compen-sate for a failed pilot’s or copilot’ssymbol generator. Available inthree or five-tube installations.The STBY mode selection willallow the pilot or copilot to substi-tute the MFD symbol generatorfor his on-side symbol generator.A single momentary switch inputto the SU 463 removes the failedon-side symbol generator drive

from the EADI and EHSI andtransfers the MFD display driveto the on-side EADI and EHSI.Also, the MFD control panel inputis removed from the MFD symbolgenerator as the EFIS controlpanel output is switched in. TheMFD symbol generator is nowperforming normal on-side EADIand EHSI functions (inputs andoutputs). To alert the pilot orcopilot that the STBY mode ofoperation has been selected, ayellow “STBY” (SG2 or SG3 areoptional in SW 06) will be annun-ciated in the lower right corner ofthe EADI and EHSI.

7.5Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 7.4PILOT STANDBY SELECTION


REVERSIONARY Modes

The following matrices provideinformation on the ability to selectdifferent reversionary modeswhen the SU 463 switching unitis part of the aircraft installation.

Depending on the installation andcertification requirements, allreversionary modes possiblemay not be installed in a particu-lar aircraft.

7.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

REVERSIONARY MODE SELECTION

Figure 7.5THREE TUBE EFS 40/50

REVERSIONARY MODE SELECTION

THREE TUBE EFS 40/50


REVERSIONARY Modes

7.7Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 7.6FOUR TUBE EFS 40/50

REVERSIONARY MODE SELECTIONS

FOUR TUBE EFS 40/50


REVERSIONARY Modes

FIVE TUBE EFS 40

Figure 7.7FIVE TUBE EFS 40


7.8 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


REVERSIONARY Modes

FIVE TUBE EFS 50

7.9Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

Figure 7.8FIVE TUBE EFS 50


Note: EFS 50 installations will support dual STBY, allowing the pilotand copilot to select STBY at the same time. EFS 40 will not sup -port dual standby.


REVERSIONARY Modes

* This page intentionally left blank.

7.10 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Glossary

GLOSSARYABBREVIATIONSA B V A b o v eA D F Automatic Direction FinderA D S Air Data SystemA D I Attitude Director IndicatorAHRS Attitude Heading Reference SystemA H S Attitude Heading SystemA N G A n g l eA N T A n t e n n aARINC Aeronautical Radio INCorporatedA T R Air Transport RadioA T T Attitude AZ Azimuth BAZ Back AzimuthB C Back CourseB L W B e l o wB R G B e a r i n gBRT B r i g h tC C P ̀ Checklist Control PanelCDI Course Deviation Indicator or Course

Deviation InformationC D U Control Display UnitCONFIG C o n f i g u r a t i o nC P Control PanelCRS C o u r s eC R T Cathode Ray TubeD - B A R Deviation BarD E G D e g r e e ( s )D E V D e v i a t i o nD G Directional GyroDIR D i r e c tD M E Distance Measuring Equipment DTK Desired TrackDU Display UnitE A D I Electronic Attitude Direction IndicatorE D Electronic DisplayEFS or EFIS Electronic Flight Instrument SystemE G P W S Enhanced Ground Proximity Warning SystemE H S I Electronic Horizontal Situation IndicatorF H D G Free Directional Gyro (heading)F L Flight Level (Pressure altitude)FLT F a u l tF M S Flight Management System

8.1Issued 6/08 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Glossary

F P L Flight PlanF R F r o mFT Feet G P Glidepath (used with MLS and GPS a p p r o a c h )G P S Global Positioning SystemG S Ground Speed or GlideslopeH D G H e a d i n gH S I Horizontal Situation Indicator I C A O International Civil Aviation Organization I D I d e n t i f i c a t i o nILS Instrument Landing SystemK T S Knots (nautical miles per hour)LMT L i m i tL N A V Long-range NAVigationL O R L o r a nM L S Microwave Landing SystemN A V N a v i g a t i o nNM Nautical MileR A Resolution AdvisoryRCP Radar Control PanelR E F Reference R M I Radio Magnetic IndicatorRNAV Area NAVigationSG Symbol GeneratorS N Sensitivity STB Stabilization S T B Y S t a n d b yS W S o f t w a r eSYNC Synchronization T A Traffic AdvisoryTACAN Tactical Air Navigation T C A S Traffic alert and Collision Avoidance SystemT C N TACAN, Tactical Air Navigation T D Traffic DisplayT S T T e s tT T S T i m e - T o - S t a t i o nT T W T i m e - t o - W a y p o i n tTX T r a n s m i t t e rVNAV Vertical NavigationV N Vertical Navigation ScaleV O R VHF Omni RangeV O R T A C VOR and TACAN co-locatedVP Vertical ProfileW X W e a t h e rW X A Weather Alert

8.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Index

INDEXA

ADF ...........................................................................................................ADF 1...........................1.6, 1.9, 1.12, 1.15, 1.18, 2.1, 2.3, 2.6, 5.2, 5.4ADF 2....................................................1.6, 1.9, 1.12, 1.15, 1.18, 2.1.6

ALPHANUMERIC READOUT ANNUNCIATIONS................................6.3

AN ...................i.1, 1.1, 1.3, 2.1.4-10, 2.2.1-2, 2.3.1, 2.3.4, 2.4.1-6, 4.1.1, ..............................4.1.3-21, 4.1.23-25, 4.2.1-5, 4.2.7-12, 4.2.15, 4.3.1-3,....................4.4.1-3, 4.4.6-9, 4.4.11, 4.4.13, 4.4.15, 5.2-4, 6.1, 6.4-5, 8.1

ANT FLT ...............................................................................................6.4

APPROACH PROCEDURES ...............................................................5.3

ARC ...........................................................................................................ARC NAV MAP ..............................................................................2.1.7ARC SECTORED MODE SELECTION: ........................................2.1.7

ATT........................1.8, 1.11, 1.14, 1.17, 1.20, 4.2.12-13, 4.2.15, 7.3, 8.1

ATTITUDE..................................1.6, 1.9, 1.12, 1.15, 1.18, 4.1.1, 4.2.1-2,............................................4.2.7, 4.2.11, 4.2.13, 4.2.15-16, 6.1, 6.5, 8.1

AUTO TILT ............................................................................2.3.4, 4.1.18

AUTOPILOT WARNING.......................................................................6.5

BBACK COURSE ........................................................................................

BACK COURSE APPROACH...........................................................5.3BC..........................1.7, 1.10, 1.13, 1.16, 1.19, 4.1.15, 4.2.8, 5.3-4, 8.1

BEARING ..................................................................................................#1 BEARING POINTER.................................................................4.1.9#2 BEARING POINTER..........................................................4.1.9, 5.21-2 PUSH BUTTON...................................................2.4.3, 4.1.2-3, 5.2BEARING POINTER ........2.1.6, 4.1.6-11, 4.1.15-16, 4.1.20, 5.2-4, 6.3BEARING POINTER ANNUNCIATIONS ..........................................6.3BEARING POINTER SELECT................................................2.1.6, 5.2

BRT KNOB ............................................................................2.1.10, 2.2.2

BUSY VP ..............................................................................................6.4

9.1Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16

IndexMP 9/8/10 7:38 PM Page 9.1

Index

CCATEGORY I .............................................................................4.2.12-14

CHECK CONFIG...............................................................................6.3-4

CHECKLIST ..............................................................................................CHECKLIST INTERFACE .............................................................4.4.3

COMMAND BARS.......1.8, 1.11, 1.14, 1.17, 1.20, 4.2.2-3, 4.2.11, 4.2.13

COMPASS CARD ...........................4.1.1, 4.1.4, 4.1.9-11, 4.1.14, 4.1.16, ...................................................................4.1.18, 4.1.22-25, 4.3.2, 4.4.1

COMPOSITE ..........................................4.2.10-11, 4.2.13, 4.3.1-4, 7.1-2

COPY ................................................................................4.2.13, 7.1, 7.3

COOLING .............................................................................................6.1

COURSE DEVIATION INDICATOR .............................4.1.15, 4.1.21, 8.1

COURSE SELECT ....................................................................................COURSE SELECT KNOB ...................2.1.10, 2.4.2, 4.1.4-5, 4.4.1, 6.2CRS ................................1.11, 1.14, 1.17, 1.20, 2.4.2, 4.1.3-5, 4.3.1-2, ..................................................4.4.1, 4.4.7, 4.4.10, 5.2-4, 6.1, 6.3, 8.1CRS KNOB..........................................2.4.2, 4.1.5, 4.4.1, 4.4.10, 5.3-4

CONTROL PANELS..........................................2.1.1, 2.3.1, 2.4.2, 4.1.19

CP 466A ..............................................................i.1, 2.1.1, 2.3.1, 4, 2.4.1

CP 466B ............................................................................i.1, 2.3.1, 2.3.4

CP 468 ..........................i.1, 2.1.1-2, 2.1.10, 2.4.2-3, 2.4.6, 3.2, 5.1-3, 6.2

CP 469A............i.1, 1.2, 2.4.1, 2.4.4, 3.5, 4.4.3-4, 4.4.6-8, 4.4.10-11, 6.2

DDETAILED OPERATING CONTROLS....................................2.1.1, 2.2.1

DG ............................1.7, 1.10, 1.13, 1.16, 1.19, 2.1.5, 2.4.5, 4.1.1-2, 8.1

DIRECT TO .......................................................................1.2, 2.1.10, 5.2

DISPLAY BRIGHTNESS CONTROL ....................................2.1.10, 2.2.2

DISTANCE, GROUNDSPEED AND TIME-TO-STATION .................4.1.6

DME...........................................................................................................DME HOLD......................................................4.1.6-9, 4.3.1, 4.3.3, 5.3

DOPPLER .................................................................................................DOPP.................................................................................2.1.4, 4.1.22DOPPLER VELOCITY BARS ......................................................4.1.22

9.2 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Index

DRIFT ANGLE POINTER......................................................4.1.3, 4.1.13

DTK ..............................................................2.4.2, 4.1.4-5, 5.3-4, 6.3, 8.1

DU-DISPLAY UNIT LOSS OF COOLING ............................................6.1

EEGPWS ...........................................................................................4.4.16

EMERGENCY PROCEDURES ..................................................4.4.4, 5.5

EXTERNAL SYSTEM FAILURES .................................................6.1, 6.5

FFAULT ANNUNCIATIONS ....................................................4.4.10, 6.1-6

FR.........................................................................4.1.15, 4.3.1, 4.3.3, 8.2

FREE DG...........................................................................................4.1.1

FROM .........1.5-6, 2.1.3, 2.2.2, 2.3.4, 2.4.2, 2.4.4-5, 4.1.5-11, 4.1.13-17, ..............................4.1.19, 4.1.21-26, 4.2.1-2, 4.2.6-7, 4.2.11-12, 4.3.1-3, .............................4.4.1-4, 4.4.6, 4.4.8-10, 4.4.13, 5.2-4, 6.1-2, 7.3-5, 8.2

FT ..................................................................4.1.12, 4.2.7, 4.2.14-15, 8.2

FULL TIME LNAV MAP..............................................................4.1.19-20

GGAIN............................................................................2.3.3-4, 4.1.18, 6.4

GLIDESLOPE............................................................................................GS.....................................1.7, 1.10, 1.13, 1.16, 1.19, 4.1.7, 4.1.11-12, ...........................................4.2.4, 4.2.9, 4.2.11, 4.2.14-15, 5.3, 6.3, 8.2

GND MAP.......................................................................................2.3.2-4

HHEADING SELECT ...................................................................................

HEADING BUG......................................................................................HDG BUG.................................................................................4.1.21

HEADING SELECT “BUG” .....................................................4.1.4, 6.2HEADING SELECT KNOB .........................................2.1.10, 4.1.4, 6.2

HEADING SYNC .............................................................................2.1.10

HOMING....................................................................................................HOM.............................................................................................4.1.25

9.3Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Index

HSI ...............................................1.6, 2.1.4-5, 2.1.7, 2.4.2, 2.4.4, 4.1.16, .................................................................4.2.8, 4.2.12-13, 4.4.9, 5.2, 8.2

IILS .............................................................................................................

ILS APPROACH .....................................................................4.1.5, 5.3IN-FLIGHT OPERATION......................................................................5.2

KKNS 81 ........................................2.1.4, 2.4.3-5, 4.1.3, 4.1.14, 4.1.16, 5.3

LLATERAL COURSE ..................................................................................

LATERAL COURSE DEVIATION BAR................................4.1.6, 4.3.2LATERAL COURSE DEVIATION SCALE ...........................4.1.5, 4.3.2

LIGHTNING ...............................................................................................LIGHTNING DETECTION..................................................2.1.5, 4.1.19

LIMITATIONS ................................................................................5.1, 5.5

LNAV .........................................................................................................LNAV MAP..........................................................2.1.9, 2.4.1, 4.1.19-20

LOC .................................................................4.1.15, 4.2.7-8, 4.2.15, 5.3

LOR ..........................................................2.1.3, 2.1.5, 4.1.10, 4.1.13, 8.2

MMAGNETIC................................................................................................

MAG..........................................................................................4.1.9-11MAG VAR .................................................................................4.1.9-11

MAP...........................................................................................................360 MAP DISPLAYS....................................................................4.1.14360 NAV MAP................................................................................2.1.7360 DEGREE MAP WX RADAR..................................................4.1.17MAP 360 COMPASS CARD ........................................................4.1.14MAP COURSE DEVIATION INDICATOR....................................4.1.15NO MAP...........................................................................4.1.15, 4.1.19

MEMORY ..........................................................2.1.3, 4.1.23, 4.4.4-6, 6.3

MFD....i.1, 1.2-3, 1.9-10, 1.12-13, 1.15-16, 1.18-19, 2.1.5, 2.1.7-8, 2.3.4, .............2.4.1-6, 3.4-5, 4.1.7, 4.1.17, 4.1.19, 4.4.1-16, 5.1, 6.2, 6.5, 7.4-5

9.4 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Index

MULTI FUNCTION DISPLAY ........................................2.1.7, 2.4.1, 4.4.1

MLS...1.6, 1.9, 1.12, 1.15, 1.18, 1.20, 4.1.4, 4.1.6-8, 4.1.11-12, 4.2.7-10, ...................................................................4.2.12-13, 4.2.15, 4.3.2-3, 8.2

MODE........................................................................................................1-2......................................2.1.3, 2.1.5, 2.4.3, 4.1.2-3, 4.4.7, 4.4.9, 5.2360-DEGREE MODE.....................................................................2.1.7

NNAV ...........................................................................................................

1-2 NAVIGATION SYSTEM SELECT............................................2.1.3NAV CDI MAP................................................................................2.1.7NAV MAP ...................2.1.5, 2.1.7-9, 2.4.4, 4.1.4, 4.1.16-17, 4.4.3, 5.3NAV NAVIGATION SENSOR SELECT .........................................2.1.3NAVIGATION SOURCE ANNUNCIATION ..........................4.1.2, 4.3.2

NDB .........................................................................2.1.5, 4.1.11, 5.2, 5.4

OOFF.......2.2.2, 2.3.2, 2.3.4, 2.4.3-4, 4.1.11, 4.1.14, 4.1.16-17, 4.1.19-20, ....................................4.2.3, 4.2.7, 4.4.2, 4.4.4-5, 4.4.7-9, 5.1, 6.4-5, 7.3

OFF-STBY-TST-ON ..........................................................................2.3.2

OMG .........................................................2.1.3, 2.1.5, 4.1.10, 4.1.13, 8.2

ON ............i.1-2, 1.2, 1.2, 1.7, 1.9-10, 1.12-13, 1.15-16, 1.18-19, 2.1.2-8, ........................2.1.10, 2.2.1-2, 2.3.1-4, 2.4.1-6, 4.1.2-5, 4.1.7, 4.1.10-22, .....................4.1.24, 4.1.26, 4.2.2, 4.2.5-16, 4.3.1-3, 4.4.1-13, 4.4.15-16, ...............................................................................5.1-5, 6.1-5, 7.1-3, 7.6

OPERATING INSTRUCTIONS .....................................2.1.2, 2.2.1, 5.1-6

PPITCH.....................................4.2.1-3, 4.2.5, 4.2.7, 4.2.15, 4.3.1, 6.1, 6.4

PLAN VIEW................................................................2.1.5, 2.4.2, 2.4.4-5

PRE-TAKEOFF PROCEDURES ..........................................................5.1

PRE-FLIGHT PROCEDURES..............................................................5.1

PULL ARL..........................................................................................2.3.4

PULL AUTO.......................................................................................2.3.4

PULL STAB OFF ...............................................................................2.3.4

PUSH BUTTON TEST..........................................................................5.1

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Index

9.6 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16

RRADAR ......................................................................................................

RADAR CONTROLS ...........................................................2.1.8, 2.3.1RCP-RADAR CONTROL PANEL .....................................................6.2RDR 1400 ........................................................................4.1.17, 4.4.15TARGET ALERT...................................................................4.1.19, 6.4

RADIO ALTIMETER...................................1.2, 2.2.2, 4.2.6-9, 4.2.13, 6.3

RANGE......................................................................................................RANGE DOWN....................................................................2.1.8, 4.4.9RANGE RING..........................2.4.4, 4.1.14, 4.1.16-17, 4.4.1-2, 4.4.12RANGE SELECTION........................................2.1.8, 4.1.17-19, 4.4.12RANGE UP ................................................................2.1.8, 2.4.3, 4.4.9

RAW DATA DEVIATION ANNUNCIATIONS .......................................6.3

REF ...........................................................................................................REF MAP FORMAT.......................................................................2.1.9

REVERSIONARY MODE ................................4.1.7, 4.2.11, 4.2.15, 7.6-9

RISING RUNWAY..............................1.14, 1.17, 1.20, 4.2.7-9, 4.2.13-14

RNAV.........................................................................................................RNV .............................................................................................4.1.10

ROLL ..................................................1.8, 1.11, 1.14, 1.17, 1.20, 4.2.1-3, ...........................................................4.2.5, 4.2.11, 4.2.15, 4.3.1, 6.1, 6.4

SSELECTED COURSE..................2.1.3, 2.1.10, 2.4.2, 4.1.4-6, 4.1.12-15, ...................................................4.1.25, 4.2.8-9, 4.3.1-2, 4.4.1, 5.2-4, 6.1

SELF TEST ......................................................................2.1.8, 2.2.2, 5.1

SN.............................................................................................4.1.26, 8.2

SOFTWARE ..............................................................................................SOFTWARE 04...........i.1, 1.6, 2.1.4, 2.1.8, 2.4.6, 4.1.6, 4.1.22, 4.1.24SOFTWARE 05.........................................................1.9, 4.1.19, 4.1.25SOFTWARE 06........................................1.12, 2.1.5, 4.1.4, 4.1.12, 6.4SOFTWARE 07..................1.15, 2.4.2, 4.1.7, 4.1.13, 4.2.12, 4.4.2, 6.4SOFTWARE 08 ......................i.1, 1.18, 2.1.3-5, 2.1.8-9, 4.1.3, 4.1.6-7, ................................................................4.1.12, 4.2.9-10, 4.4.3, 4.4.11

STAB OFF ..................................................................................2.3.4, 6.5

STANDARD EHSI DISPLAYS..............................4.1.1, 4.1.16, 4.1.22-24


Index

START UP............................................................................................5.1

STB LMT ..............................................................................................6.4

STB OFF ..............................................................................................6.5STBY........................................................2.3.2, 4.1.17, 4.4.14, 7.5, 7.9, 8.2

SYMBOL....................................................................................................SG-SYMBOL GENERATOR.............................................................6.2SG-SYMBOL GENERATOR LOSS OF COOLING...........................6.1SYMBOLIC AIRCRAFT ........4.1.3, 4.1.5, 4.1.10, 4.1.17-18, 4.1.22-24, .....................................................4.1.26, 4.2.2-3, 4.3.1, 4.4.1-2, 4.4.12

SYSTEM CONFIGURATION ...............................1.1-20, 4.1.3, 6.3-4, 7.1

TTCAS .........................................................................................................

TCAS INTERFACE ................................................................................TCAS SELECTION ....................................................................2.4.6TCAS DISPLAY FORMAT .......................................................4.4.12TCAS TRAFFIC SYMBOLOGY................................................4.4.12TCAS DISPLAY ANNUNCIATIONS.........................................4.4.13

TCN ......................................................................2.1.3, 4.1.3, 4.1.10, 8.2

TENDENCY CIRCLE...........................................................4.1.23, 4.1.25

THRUST COMMAND ......................................................................4.1.25

TILT ...........................................................................2.3.4, 4.1.17-18, 6.4

TO ................................i.1-2, 1.1-3, 1.5-6, 1.9, 1.12, 1.15, 1.18, 2.1.2-10, ..............................................2.2.1-2, 2.3.1-4, 2.4.1-6, 4.1.1-26, 4.2.1-13, ................................4.2.15-16, 4.3.1-3, 4.4.1-15, 5.1-5, 6.1-5, 7.1-6, 7.9

TO-FROM..........................................................................................5.2-4

TRUE.............................2.4.4, 4.1.9, 4.1.11, 4.1.16, 4.2.13, 4.2.16, 4.4.2

TST .............................................2.1.8-9, 2.2.2, 2.3.2, 4.4.10-11, 5.1, 8.2

TST/REF....................................................................................................SELF TEST...................................................................2.1.8, 2.2.2, 5.1

TX FLT..................................................................................................6.4

VVELOCITY AND TARGET SCALE..................................................4.1.22

VN...................................................................................4.1.12, 4.2.9, 6.3

9.7Issued 8/10 SW 04/05/06/07/08/09/10/11/12/13/14/15/16


Index

VNAV .......1.7, 1.10, 1.13, 1.16, 1.19-20, 4.1.11-12, 4.2.4, 4.2.9, 5.3, 8.2VNAV GPS PRECISION APPROACH..............................................5.4

VOR...........................................................................................................VOR APPROACH .............................................................................5.5

VERTICAL PROFILE.................................................................................VP.......................................................2.3.1, 2.3.3-4, 4.4.1-2, 6.4-5, 8.2

WWAIT...........................................................................................2.3.3, 6.5

WEATHER.................................................................................................WEATHER RADAR ANNUNCIATIONS............................................6.4WX...............................................................2.3.2-3, 4.1.17-18, 6.4, 8.2WX FLT.................................................................................4.1.18, 6.4WXA.........................................................................2.3.2-3, 4.1.18, 8.2

WIND VECTOR .........................................................................................WIND VECTOR INFORMATION ................................4.1.13, 4.1.23-24

9.8 Issued 8/10SW 04/05/06/07/08/09/10/11/12/13/14/15/16


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Pilot’s Guide EFS 40/50 - BendixKing

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