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Pilot’s Guide
EFS 50
5-inch Electronic Flight
Instrumentation System
B
AlliedSignal General Aviation Avionics
400 North Rogers Road
Olathe, Kansas 66062-1212
TELEX 669916 KINGRAD FAX 913-791-1302
TELEPHONE (913) 768-3000
©1995 AlliedSignal Inc.
4/95 006-08485-0000 1K PRINTED IN THE U.S.A.
SW 06/07/08/11
A
A
Registration
This pilot's guide has been tailored by the installation and or certification agency to cover the following EFS 50 installation:
AIRCRAFT TYPE
AIRCRAFT TAIL OR SERIAL NUMBER
AIRCRAFT OWNER
EFIS TYPE
EFIS SYSTEM CONFIGURATION
EFIS SYSTEM SOFTWARE LEVEL
EFIS DISPLAY UNIT TYPE
EFIS CONTROL PANELS
REVERSIONARY MODES
Throughout this pilot's guide various configuration options are described. A ✔❏ (check box) precedes each configuration option. A check mark may be placed in the appropriate boxes to define which configuration options are available in a given installation.
Registration
Table of Contents
TABLE OF CONTENTS
Section I
INTRODUCTION
Section 1
I.1
SYSTEM CONFIGURATION
GENERAL
CONTROL DISPLAY
CONTROL DISPLAY OPTIONS
SYMBOL GENERATOR
EQUIPMENT INTERFACE & OPERATING CONFIGURATION
SOFTWARE 06 CONFIGURATION PAGES
SOFTWARE 07 CONFIGURATION PAGES
(includes both 0701 and 0702)
SOFTWARE 08 CONFIGURATION PAGES
SOFTWARE 11 CONFIGURATION PAGES
1.10
1.14
1.18
1.1
1.1
1.1
1.3
1.3
1.5
1.6
Section 2
EHSI OPERATION
Detailed Operating Controls
EHSI Controls (CP 467)
HSI 360-DEGREE MODE SELECTION
ARC SECTORED MODE SELECTION
NAV NAVIGATION SENSOR SELECT
1-2 NAVIGATION SYSTEM SELECT
BEARING POINTER SELECT
RANGE SELECTION
TST/REF
TST -
2.1.6
2.1.7
2.1.8
2.1.8
REF GROUND SPEED or TIME-TO-STATION selection 2.1.8
REF MAP FORMAT 2.1.9
COURSE SELECT KNOB
HEADING SELECT KNOB
DISPLAY BRIGHTNESS CONTROL
2.1.10
2.1.10
2.1.10
2.1.1
2.1.1
2.1.3
2.1.3
2.1.3
2.1.4
2.1.6
EADI OPERATION
EADI Detailed Operating Controls
BRIGHTNESS
DH SET
RALT TST
2.2.1
2.2.1
2.2.1
2.2.1
2.2.2
Issued 4/95 SW 06/07/08/11 TOC.1
Table of Contents
RADAR OPERATION
Radar Controls, (CP 466A & CP 466B)
OFF-STBY-TST-ON
OFF
STBY
TST
ON
WX
WXA
GND MAP
LIGHTNING
VP
TRK
GAIN
PULL ARL
TILT
MFD OPERATION
Multi Function Display Control Panel
Control Panel Button Operations
TCAS ONLY BUTTON
HSI BUTTON
ARC BUTTON
ENT BUTTON
LNAV MAP
PLAN-VIEW MAP (available with software 07)
CHECKLIST (available with software 08)
NAV BUTTON
RANGE UP/DOWN BUTTONS
CHECKLIST BUTTON
COURSE SELECT KNOB/BUTTON
BEARING #1 & #2 BUTTON
JOYSTICK
LNAV MAP
PLAN-VIEW MAP
CHECKLIST MODE (available with software 08)
1-2 BUTTON
TST/REF BUTTON
Section 3
ABBREVIATED OPERATIONS
2.4.2
2.4.2
2.4.3
2.4.3
2.4.3
2.4.3
2.4.4
2.4.4
2.4.1
2.4.1
2.4.2
2.4.2
2.4.2
2.4.2
2.4.2
2.4.2
2.4.4
2.4.5
2.4.6
2.4.6
2.4.7
2.3.4
2.3.4
2.3.4
2.3.5
2.3.5
2.3.6
2.3.7
2.3.7
2.3.7
2.3.1
2.3.3
2.3.4
2.3.4
2.3.4
2.3.4
2.3.4
3.1
TOC.2
SW 06/07/08/11 Issued 4/95
Issued 4/95 SW 06/07/08/11
Table of Contents
Section 4
EHSI DISPLAYS
EFS 50 Color Standards
Standard EHSI Displays
NORMAL COMPASS CARD
NAVIGATION SOURCE ANNUNCIATION
SYMBOLIC AIRCRAFT
HEADING SELECT “BUG”
COURSE SELECT
LATERAL COURSE DEVIATION SCALE
LATERAL COURSE DEVIATION BAR
TO/FROM INDICATOR
DISTANCE, GROUNDSPEED and TIME-TO-STATION
DUAL MULTI CHANNEL DME INSTALLATION
DME HOLD
BEARING POINTER
MAGNETIC/TRUE HEADING ANNUNCIATIONS
GLIDE SLOPE/VERTICAL NAVIGATION
WIND VECTOR
DRIFT ANGLE POINTER (LNAV only)
LNAV MODE ANNUNCIATIONS
360 Map Displays
MAP 360 COMPASS CARD
SELECTED COURSE
MAP COURSE DEVIATION INDICATOR
TO/FROM
BEARING POINTER
REFERENCE WAYPOINT
RANGE RING
360-DEGREE MAP WX RADAR (IF EQUIPPED)
TRACK LINE
LIGHTNING DETECTION
FULL TIME LNAV MAP
ARC (Expanded Sectored Mode) Displays
HDG BUG (ALL ARC FORMAT MODES)
COURSE DEVIATION INDICATOR
(EHSI ARC NON-MAP FORMAT)
EADI DISPLAYS
Normal Attitude Display
PITCH ATTITUDE
ROLL ATTITUDE
ROLL INDICATOR
TOC.3
4.1.14
4.1.14
4.1.14
4.1.15
4.1.16
4.1.16
4.1.17
4.1.17
4.1.10
4.1.10
4.1.12
4.1.12
4.1.12
4.1.13
4.1.13
4.1.13
4.1.18
4.1.20
4.1.20
4.1.20
4.1.3
4.1.4
4.1.4
4.1.5
4.1.5
4.1.6
4.1.7
4.1.8
4.1.1
4.1.1
4.1.1
4.1.1
4.1.2
4.1.3
4.1.3
4.2.1
4.2.1
4.2.1
4.2.1
4.2.1
Table of Contents
PERSPECTIVE LINES
SYMBOLIC AIRCRAFT
HEADING TAPE
FLIGHT DIRECTOR COMMAND BARS
AUTOPILOT/FLIGHT DIRECTOR MODE ANNUNCIATION
STANDARD 429 AUTOPILOT/FLIGHT
DIRECTOR MODE ANNUNCIATION
RADIO ALTIMETER
DECISION HEIGHT SET
DECISION HEIGHT ALERT
PRECISION APPROACH MODE FORMAT
EXPANDED LATERAL DEVIATION SCALE
RISING RUNWAY
GLIDESLOPE/VERTICAL NAVIGATION
MARKER BEACON ANNUNCIATION
FAST/SLOW
RATE OF TURN DISPLAY
CATEGORY II ANNUNCIATOR
CATEGORY II OPERATION ANNUNCIATIONS
CATEGORY II THRESHOLDS
ATTITUDE MONITOR
CROSS COMPARATOR ANNUNCIATORS
RA
LOC
GS
ATT
HDG
COMPOSITE DISPLAYS
COMPOSITE MODE
HEADING TAPE
SELECTED COURSE
HEADING BUG SELECT
NAVIGATION SOURCE ANNUNCIATION
LATERAL COURSE DEVIATION SCALE
(Non Approach Mode)
LATERAL COURSE DEVIATION BAR
TO/FROM
DISTANCE INFORMATION
DME HOLD
MFD DISPLAYS
CRS , CRS NOT SELECT
WEATHER ONLY
TRACK LINE
4.2.2
4.2.2
4.2.2
4.2.3
4.2.3
4.2.3
4.2.8
4.2.8
4.2.9
4.2.9
4.2.9
4.2.11
4.2.12
4.2.12
4.2.5
4.2.6
4.2.6
4.2.6
4.2.6
4.2.7
4.2.8
4.2.12
4.2.12
4.2.12
4.2.12
4.2.13
4.3.1
4.3.1
4.3.1
4.3.1
4.3.1
4.3.2
4.3.2
4.3.2
4.3.3
4.3.3
4.3.3
4.4.1
4.4.1
4.4.1
4.4.1
TOC.4
SW 06/07/08/11 Issued 4/95
Table of Contents
VERTICAL PROFILE (VP)
SYMBOLIC AIRCRAFT
RANGE RINGS
ALTITUDE LINE
PROFILE ANGLE
PLAN-VIEW, NORTH-UP MAP
TCAS INTERFACE
TCAS ONLY SELECTION
TCAS DISPLAY FORMAT
TCAS TRAFFIC SYMBOLOGY
Intruder Symbols
Vertical Speed Arrow
Data Tag
Off-Scale Traffic
TCAS DISPLAY ANNUNCIATIONS
Traffic
TCAS
TCAS Status
TCAS Mode
Range
Range Rings
Above/Norm/Below
No-Bearing Traffic
FLXXX and FL
Weather/Lightning Annunciation
CHECKLIST INTERFACE
LOADING AND MODIFYING CHECKLIST DATA
NOTICE
CHECKLIST PAGE ORGANIZATION
ROOT INDEX PAGE
SUB INDEX PAGES
CHECKLIST ITEM PAGES
NOTE PAGES
CLEARING CHECKLIST ITEMS
EMERGENCY PAGE ACTIVATION
CHECKLIST CONTROLS
Checklist: CHKLIST
Joystick
Enter : ENT
HSI
ARC
NAV
Up Arrow
Down Arrow
1-2
4.4.8
4.4.8
4.4.8
4.4.8
4.4.9
4.4.9
4.4.10
4.4.10
4.4.5
4.4.6
4.4.6
4.4.7
4.4.7
4.4.7
4.4.7
4.4.7
4.4.4
4.4.4
4.4.4
4.4.4
4.4.4
4.4.5
4.4.5
4.4.5
4.4.1
4.4.1
4.4.1
4.4.2
4.4.2
4.4.2
4.4.3
4.4.3
4.4.11
4.4.11
4.4.11
4.4.12
4.4.12
4.4.13
4.4.13
4.4.14
4.4.14
4.4.14
4.4.14
4.4.14
4.4.15
Issued 4/95 SW 06/07/08/11 TOC.5
Table of Contents
RMI 1
RMI 2
CRS(NOT) SEL
TST REF
CRS Knob
Section 5
OPERATING INSTRUCTIONS
PREFLIGHT PROCEDURES
START UP
SELF TEST
PUSH BUTTON TEST
PRE-TAKEOFF PROCEDURES
IN-FLIGHT OPERATION
ADF
LNAV (RNAV)
VNAV
APPROACH PROCEDURES
ILS APPROACH
BACK COURSE APPROACH
ADF APPROACH
LNAV (RNAV) APPROACH
VOR APPROACH
DECISION HEIGHT SELECTION
LIMITATIONS
EMERGENCY PROCEDURES
Section 6
FAULT ANNUNCIATIONS
General
EXTERNAL SYSTEM FAILURES
HEADING
ATTITUDE
FLIGHT DIRECTOR
EFS 50 SYSTEM FAILURES
DU—DISPLAY UNIT LOSS OF COOLING
SG—SYMBOL GENERATOR LOSS OF COOLING
CP—CONTROL PANEL (CP 467 OR CP 469/A)
HEADING SELECT “BUG”
COURSE SELECT
RCP—RADAR CONTROL PANEL (if equipped)
SG—SYMBOL GENERATOR
RAW DATA DEVIATION ANNUNCIATIONS
4.4.15
4.4.15
4.4.15
4.4.15
4.4.15
5.2
5.3
5.3
5.3
5.3
5.4
5.4
5.4
5.1
5.1
5.1
5.1
5.1
5.1
5.2
5.2
5.4
5.5
5.5
6.1
6.2
6.2
6.2
6.2
6.3
6.3
6.1
6.1
6.1
6.1
6.1
6.1
6.1
6.1
TOC.6
SW 06/07/08/11 Issued 4/95
Table of Contents
BEARING POINTER ANNUNCIATIONS
ALPHANUMERIC READOUT ANNUNCIATIONS
CHECK CONFIG
WEATHER RADAR ANNUNCIATIONS
WX FLT
WX OFF
BUSY VP
STB LMT
429 FLT
ANT FLT
TX FLT
RANGE
STB OFF
WAIT
TCAS FAULT MESSAGES
FAULT MESSAGES
6.4
6.4
6.4
6.4
6.5
6.5
6.5
6.5
6.3
6.3
6.4
6.4
6.4
6.4
6.4
6.4
Section 7
REVERSIONARY MODES
CMPST - COMPOSITE
DISPLAY (EADI) DOWN
SG 3
Section 8
GLOSSARY
Section 9
INDEX
7.1
7.2
7.3
7.4
8.1
9.1
Issued 4/95 SW 06/07/08/11 TOC.7
Table of Contents
*This page intentionally left blank.
TOC.8
SW 06/07/08/11 Issued 4/95
Introduction
INTRODUCTION
This pilot’s guide describes the components, operation, and operational procedures of the
BENDIX/KING EFS 50 Electronic
Flight Instrumentation System
(EFS) containing system software 0601 and 0701, 0702,
0801, 0802, and 1101. These software versions will normally be referred to as 06, 07, 08, and 11 where version 07 includes both
0701 (version 07, mod 1) and
0702 (version 07, mod 2).
Likewise 08 includes both 0801 and 0802.
The EFS 50 system uses a remote mode controller, CP 467, and display unit, ED 551/A, for control and display of navigation data and sensor selection. The remote SYMBOL GENERATOR,
SG 465, interfaces with the navigation sensors to compute the display and EFIS output data required by other systems on board the aircraft.
The CP 469 or CP 469A will control and select navigation data for display on the MFD. A
CP 466A or CP 466B provides the radar control function when an RDS 81/82/84 or 86 weather radar is interfaced with the system, and the associated radar control/display unit is not installed.
Equipment covered in this pilot’s guide includes:
ED 551A Display unit, 5” X 5”
SG 465
CP 467
EFIS symbol generator
EFIS control panel with DH set and test
CP 466A RDS 81/82/84 radar control panel
CP 466B RDS 86 radar control panel
CP 469 MFD control panel
CP 469A MFD control panel with checklist and TCAS selection
An Abbreviated Operations section included in this manual covers the functions of the EFS
50 in minimal detail. The Abbreviated Operations section gives a brief visual overview of features and push button operations.
However, it is necessary to read the entire Pilot’s Guide for a full understanding of the EFS 50 system.
Please note: the EFS 50 display illustrations used in this pilot’s guide are artist’s reproductions.
Extreme care has been taken to ensure the accuracy of symbology placement and relative size.
However, it is impossible to exactly duplicate the display of a
CRT and compensate for all brightness levels, as line width displayed on the CRT varies with
Issued 4/95 SW 06/07/08/11 I.1
Introduction brightness. In many cases, unrealistic displays provide the most informative display possible on a single display. Therefore, we ask that you use and treat the graphic illustrations contained in this pilot’s guide as they were intended. These illustrations are to familiarize the pilot with the type and placement of data to be provided by the EFS 50.
Note: The data presented in this pilot’s guide is general in nature and not tailored toward a specific installation. Not all equipment interfaces nor display options presented are certifiable in all aircraft types or by all certification agencies.
Each installation may incorporate different equipment complements and use different display options. For the unique certified operating procedure of a particular aircraft, refer to the appropriate approved
Flight Manual Supplement for that aircraft.
I.2
SW 06/07/08/11 Issued 4/95
System Configuration
SYSTEM CONFIGURATION
GENERAL CONTROL DISPLAY
The 5 tube EFS 50 system Electronic Flight Instrumentation System) offered on the Lear 31A consists of:
• 2 ea EHSI Display Unit
(ED 551A)
• 2 ea EADI Display Unit
(ED 551A)
• 1 ea MFD (ED 551A)
• 2 ea EFIS Control Panels
(CP 467)
• 1 ea MFD Control Panel
(CP 469 or CP 469A)
• 1 ea RADAR Control Panel
(CP 466A/B)
• 3 ea Symbol Generators
(SG 465)
• 1 ea Switching Unit
(SU 463)
Refer to figure 1.1 for the Control
Display configurations.
The CP 467 Control Panel controls the presentation displayed on the ED 551A Display Unit when it is utilized as an EHSI or
EADI. The CP 469/A and CP
466A/B Control Panels control the ED 551A Display Unit presentation when it is utilized as an
MFD (Multi Function Display).
Figure 1.1 depicts the EFS 50
Control Display Configurations.
Issued 4/95 SW 06/07/08/11 1.1
System Configuration ı
1
DH
CRS
RALT TST
HSI ARC
SYS REF
NAV
1-2
RNG
RNG
BRT
HDG
EADI, EHSI CONTROL DISPLAY
2 EA ED 551A & CP 467 ı
1.2
TCAS
ONLY
CRS
HSI ARC
CRS SEL
ENT NAV
1-2
TST REF
CHK
LIST
BRT
TST
ON
STBY
OFF
GAIN
Wx
VP
PULL ARL
WxA
GND
MAP
TK
TK
UP
TILT O
PULL AUTO
DN
BRT
OFF
MFD CONTROL DISPLAY
ED 551/A, CP 469/A & CP 466B
Figure 1.1
CONTROL DISPLAY CONFIGURATIONS
SW 06/07/08/11 Issued 4/95
System Configuration
CONTROL DISPLAY
OPTIONS
The CP 467 and CP 469/A mode controllers offer a simple means for the pilot to select the desired display format, such as standard compass rose or sectored compass rose, 360-degree map or sectored map and weather radar overlay. Also incorporated on the mode controller is the course and heading (CP 467) select knobs with auto sync. The auto sync feature will slew the heading bug to the lubber line or the course pointer to the DIRECT TO course for the selected NAV sensor providing a centered D-Bar.
The CP 467 incorporates Decision Height Set and Radio
Altimeter Test.
SYMBOL GENERATOR
THE SG 465 EADI/EHSI/MFD symbol generator is a remotemounted processing unit packaged in an ARINC 3/8 ATR short form factor.
SG 465
Issued 4/95
Figure 1.2
SG 465 SYMBOL GENERATOR
SW 06/07/08/11 1.3
System Configuration
A
N
AP
YD
F
N
LOC
1
12555 K
T
GS
20 20
10
3
10
6 T
G
S
S
10
20
10
20
LOC
ED 551A
DH
CRS
RALT
HSI
TST SYS REF
ARC NAV
1-2
RNG
RNG
BRT
HDG
CP 467
SG 465
SG 465
1
CRS
23
340
33
V
O
R
1
WXA
A 2.2
ANT FLT
VOR 1
36.7 NM
N
40
ADF 2
36.7
3
90°
ED 551A ı
I
L
S
1
CRS
359
30
33
N
21
S
15
3
6
126
NM
3.5
ADF 2
360°
ED 551A
TST
ON
STBY
OFF
GAIN
Wx WxA
GND
MAP
UP
TILT 0
PULL STAB OFF
DN
CP 466
SG 465
TCAS
ONLY
CRS
HSI ARC ENT
CRS SEL
NAV
1-2
TST REF
CHK
LIST
BRT
CP 469A
SG 465
Figure 1.3
TYPICAL EFS 50 SYSTEM BLOCK DIAGRAM
{
REMOTE
EQUIPMENT
SW 06/07/08/11 Issued 4/95 1.4
EQUIPMENT INTERFACE &
OPERATING CONFIGURATION
The following pages are provided to document the EFS 50 equipment interface and operating configuration established at the time of installation and certification. Those pages referring to software configuration versions not applicable to this aircraft are to be removed from this pilot’s guide.
System Configuration
Issued 4/95 SW 06/07/08/11 1.5
7
8
5
6
1
2
3
4
9
10
11
12
13
System Configuration
SOFTWARE 06 CONFIGURATION PAGES
7
8
5
6
3
4
1
2
9
10
11
12
13
The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and
MFD,, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 (left side) as the pilot’s side and side 2 (right side) as the co-pilot’s side.
——————————|
VIEW/EDIT EQUIPMENT
ITEM
SG NUMBER
SINGLE/DUAL
DU TYPE
ATTITUDE/HDG #1
ATTITUDE/HDG #2
RATE OF TURN
ADF #1
ADF #2
VOR/ILS #1
VOR/ILS #2
..MORE..
PG 01
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT EQUIPMENT
ITEM
DME #1
DME #2
MLS #1
MLS #2
FMS #1
FMS #2
RNAV #1
RNAV #2
TACAN #1
TACAN #2
..MORE..
PG 02
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
1.6
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8
9
10
11
12
13
6
7
4
5
1
2
3
5
6
7
3
4
1
2
System Configuration
——————————|
VIEW/EDIT EQUIPMENT
ITEM
VNAV
PG 03
RADAR ALT
AFCS TYPE
_______________
_______________
_______________
AFCS COMMAND BAR _______________
AFCS MODE ANN _______________
F/S AIR DATA
RADAR TYPE
RADAR CTL PNL
RADAR INDICATOR
CHECKLIST
..MORE..
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT EQUIPMENT
ITEM
JOYSTICK
TCAS
HOMING #1
HOMING #2
LIGHTNING DET
PG 04
_______________
_______________
_______________
_______________
_______________
Issued 4/95 SW 06/07/08/11 1.7
8
9
10
11
12
13
6
7
4
5
1
2
3
8
9
10
11
12
13
6
7
4
5
1
2
3
System Configuration
——————————|
VIEW/EDIT OPERATING CHAR
ITEM
VERT SCALE SIDE
PG 06
_______________
DCLTR GS ON BC
FULLTIME FMS MAP
DISPLAY WIND VEC
DISPLAY DRIFT
_______________
_______________
_______________
_______________
DG ONLY MODE
DME DIST ONLY
RADAR ONLY MODE
HOVER MODE
MFD NAV CONTROL
..MORE..
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT OPERATING
ITEM
DISPLAY HDG TAPE
COMMAND BARS
ROLL INDICATOR
DCLTR UNUS ATT
CAT II AVAILABLE
PERSPECTIVE LINES
DH SELECT
CABLE MODE
SEL HDG SYNC
SEL CRS SYNC
..MORE..
PG 07
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
1.8
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6
7
4
5
1
2
3
8
9
10
11
System Configuration
——————————|
VIEW/EDIT OPERATING
ITEM
NORTH UP MAP
VERT PTR TYPE
DISPLAY FMS MSG
SEL HDG COLOR
CMD BAR COLOR
REV MODE ANN
RISING RUNWAY
ADI DEV SRC
CMD BAR FILTER
PG 08
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
Issued 4/95 SW 06/07/08/11 1.9
8
9
10
11
12
13
6
7
4
5
1
2
3
System Configuration
SOFTWARE 07 CONFIGURATION PAGES
(includes both 0701 and 0702)
The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and
MFD, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 (left side) as the pilot’s side and side 2 (right side) as the co-pilot’s side.
——————————|
VIEW/EDIT EQUIPMENT
ITEM
SG NUMBER
SINGLE/DUAL
DU TYPE
ATTITUDE/HDG #1
ATTITUDE/HDG #2
RATE OF TURN
ADF #1
ADF #2
VOR/ILS #1
VOR/ILS #2
..MORE..
PG 01
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
1.10
SW 06/07/08/11 Issued 4/95
8
9
10
11
12
13
6
7
4
5
1
2
3
8
9
10
11
12
13
6
7
4
5
1
2
3
System Configuration
——————————|
VIEW/EDIT EQUIPMENT
ITEM
DME #1
DME #2
MLS #1
MLS #2
FMS #1
FMS #2
RNAV #1
RNAV #2
TACAN #1
TACAN #2
..MORE..
PG 02
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT EQUIPMENT
ITEM
VNAV
RADAR ALT
AFCS TYPE
AFCS COMMAND BAR
AFCS MODE ANN
F/S AIR DATA
RADAR TYPE
RADAR CTL PNL
RADAR INDICATOR
CHECKLIST
..MORE..
PG 03
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Issued 4/95 SW 06/07/08/11 1.11
8
9
10
11
12
13
6
7
4
5
1
2
3
6
7
4
5
8
9
1
2
3
System Configuration
——————————|
VIEW/EDIT EQUIPMENT
ITEM
JOYSTICK
TCAS
HOMING #1
HOMING #2
LIGHTNING DET
HOVER MODE
CABLE MODE
PG 04
_______________
_______________
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT OPERATING CHAR
ITEM
VERT SCALE SIDE
PG 06
_______________
DCLTR GS ON BC
FULL TIME FMS MAP
DISPLAY WIND VEC
DISPLAY DRIFT
_______________
_______________
_______________
_______________
DG ONLY MODE
DME DIST ONLY
RADAR ONLY MODE
SPARE
MFD NAV CONTROL
..MORE..
_______________
_______________
_______________
_______________
_______________
1.12
SW 06/07/08/11 Issued 4/95
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1
2
9
10
11
8
9
10
11
12
13
6
7
4
5
1
2
3
System Configuration
——————————|
VIEW/EDIT OPERATING
ITEM
DISPLAY HDG TAPE
COMMAND BARS
ROLL INDICATOR
DCLTR UNUS ATT
CAT II AVAILABLE
PERSPECTIVE LINES
DH SELECT
CTL PNL SYNC
SEL HDG SYNC
SEL CRS SYNC
..MORE..
PG 07
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
VIEW/EDIT OPERATING
ITEM
NORTH UP MAP
VERT PTR TYPE
DISPLAY FMS MSG
SEL HDG COLOR
CMD BAR COLOR
REV MODE ANN
RISING RUNWAY
ADI DEV SRC
CMD BAR FILTER
PG 08
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
Issued 4/95 SW 06/07/08/11 1.13
7
8
5
6
3
4
1
2
9
10
11
12
13
System Configuration
SOFTWARE 08 CONFIGURATION PAGES
7
8
5
6
1
2
3
4
9
10
11
12
13
The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and
MFD, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 (left side) as the pilot’s side and side 2 (right side) as the co-pilot’s side.
——————————|
VIEW/EDIT EQUIPMENT
ITEM
SG NUMBER
SINGLE/DUAL
DU TYPE
ATTITUDE/HDG #1
ATTITUDE/HDG #2
RATE OF TURN
ADF #1
ADF #2
VOR/ILS #1
VOR/ILS #2
..MORE..
PG 01
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——————————|
VIEW/EDIT EQUIPMENT
ITEM
DME #1
DME #2
MLS #1
MLS #2
FMS #1
FMS #2
RNAV #1
RNAV #2
TACAN #1
TACAN #2
..MORE..
PG 02
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1.14
SW 06/07/08/11 Issued 4/95
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3
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1
2
8
9
10
11
12
13
6
7
4
5
1
2
3
System Configuration
——————————|
VIEW/EDIT EQUIPMENT
ITEM
VNAV
RADAR ALT
AFCS TYPE
AFCS COMMAND BAR
AFCS MODE ANN
F/S AIR DATA
RADAR TYPE
RADAR CTL PNL
RADAR INDICATOR
CHECKLIST
..MORE..
PG 03
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_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT EQUIPMENT
ITEM
JOYSTICK
TCAS
HOMING #1
HOMING #2
LIGHTNING DET
HOVER MODE
CABLE MODE
PG 04
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_______________
_______________
_______________
_______________
_______________
Issued 4/95 SW 06/07/08/11 1.15
8
9
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11
12
13
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4
5
1
2
3
8
9
10
11
12
13
6
7
4
5
1
2
3
System Configuration
——————————|
VIEW/EDIT OPERATING CHAR
ITEM
VERT SCALE SIDE
PG 06
_______________
DCLTR GS ON BC
FULL TIME FMS MAP
DISPLAY WIND VEC
DISPLAY DRIFT
_______________
_______________
_______________
_______________
DG ONLY MODE
DME DIST ONLY
RADAR ONLY MODE
SPARE
MFD NAV CONTROL
..MORE..
_______________
_______________
_______________
_______________
_______________
——————————|
VIEW/EDIT OPERATING
ITEM
DISPLAY HDG TAPE
COMMAND BARS
ROLL INDICATOR
DCLTR UNUS ATT
CAT II AVAILABLE
PERSPECTIVE LINES
DH SELECT
CTL PNL SYNC
SEL HDG SYNC
SEL CRS SYNC
..MORE..
PG 07
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1.16
SW 06/07/08/11 Issued 4/95
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9
10
11
8
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10
11
12
13
6
7
4
5
1
2
3
——————————|
VIEW/EDIT OPERATING
ITEM
NORTH UP MAP
VERT PTR TYPE
DISPLAY FMS MSG
SEL HDG COLOR
CMD BAR COLOR
REV MODE ANN
RISING RUNWAY
ADI DEV SRC
CMD BAR FILTER
MLS VRT ANNUNC
..MORE..
——————————|
VIEW/EDIT OPERATING
ITEM
DATUM SCALING
HDG FAIL ANNUNC
VNAV APR SCALE
LNAV CRS CTRL
SG #1 SIDE
AIRCRAFT SYMBOL
TACAN ANNUNC
TCAS DISPLAYS
CAT II SENSORS
System Configuration
PG 08
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_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
_______________
PG 09
_______________
_______________
_______________
_______________
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_______________
Issued 4/95 SW 06/07/08/11 1.17
7
8
5
6
3
4
1
2
9
10
11
12
13
System Configuration
SOFTWARE 11 CONFIGURATION PAGES
7
8
5
6
1
2
3
4
9
10
11
12
13
The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and
MFD, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 as the pilot’s side and side 2 as the co-pilot’s side.
——————————|
VIEW/EDIT EQUIPMENT
ITEM
SG NUMBER
SINGLE/DUAL
DU TYPE
ATTITUDE/HDG #1
ATTITUDE/HDG #2
RATE OF TURN
ADF #1
ADF #2
VOR/ILS #1
VOR/ILS #2
..MORE..
PG 01
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——————————|
VIEW/EDIT EQUIPMENT
ITEM
DME #1
DME #2
MLS #1
MLS #2
FMS #1
FMS #2
RNAV #1
RNAV #2
TACAN #1
TACAN #2
..MORE..
PG 02
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1.18
SW 06/07/08/11 Issued 4/95
8
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11
12
13
6
7
4
5
1
2
3
7
8
5
6
3
4
1
2
9
10
System Configuration
——————————|
VIEW/EDIT EQUIPMENT
ITEM
FMS VNAV
RADAR ALT
AFCS TYPE
AFCS COMMAND BAR
AFCS MODE ANN
F/S AIR DATA
RADAR TYPE
RADAR CTL PNL
RADAR INDICATOR
CHECKLIST
..MORE..
PG 03
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——————————|
VIEW/EDIT EQUIPMENT
ITEM
JOYSTICK
TCAS
HOMING #1
HOMING #2
LIGHTNING DET
HOVER MODE
CABLE MODE
VARIABLE LNAV
PG 04
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_______________
7
8
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6
1
2
3
4
9
10
11
12
13
Issued 4/95
——————————|
VIEW/EDIT OPERATING CHAR
ITEM
VERT SCALE SIDE
DCLTR GS ON BC
FULL TIME FMS MAP
DISPLAY WIND VEC
PG 06
_______________
_______________
_______________
_______________
DISPLAY DRIFT
DG ONLY MODE
DME DIST ONLY
RADAR ONLY MODE
SPARE
MFD NAV CONTROL
..MORE..
_______________
_______________
_______________
_______________
_______________
_______________
SW 06/07/08/11 1.19
System Configuration
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2
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12
13
——————————|
VIEW/EDIT OPERATING
ITEM
DISPLAY HDG TAPE
ADI PLANE/CMD BAR
ROLL INDICATOR
DCLTR UNUS ATT
CAT II AVAILABLE
PERSPECTIVE LINES
DH SELECT
CTL PNL SYNC
SEL HDG SYNC
SEL CRS SYNC
..MORE..
——————————|
VIEW/EDIT OPERATING
ITEM
NORTH UP MAP
VERT PTR TYPE
DISPLAY FMS MSG
SEL HDG COLOR
CMD BAR COLOR
REV MODE ANN
RISING RUNWAY
ADI DEV SRC
CMD BAR FILTER
MLS VRT ANNUNC
..MORE..
——————————|
VIEW/EDIT OPERATING
ITEM
DATUM SCALING
HDG FAIL ANNUNC
VNAV APR SCALE
LNAV CRS CTRL
SG #1 SIDE
AIRCRAFT SYMBOL
TACAN ANNUNC
TCAS DISPLAYS
CAT II SENSORS
RADAR SCAN
1.20
PG 07
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PG 08
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PG 09
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SW 06/07/08/11 Issued 4/95
System Configuration
3
4
1
2
——————————|
VIEW/EDIT OPERATING
ITEM
RADAR SDI
PITCH SYNC DISC
PG 10
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_______________
Issued 4/95 SW 06/07/08/11 1.21
System Configuration
* This page intentionally left blank.
1.22
SW 06/07/08/11 Issued 4/95
EHSI Operation
EHSI OPERATION
DETAILED OPERATING CONTROLS
All possible EFS 50 Interfacing
Equipment is described in the
Detailed Operating Controls section of the EFS 50 Pilot’s Guide, however, all may not be active in a specific installation.
This section, EHSI Operation, will describe the operation of both the CP468 EHSI control panel and the EHSI section of the
CP467 EHSI/EADI control panel.
The EADI operation of the
CP467 is covered in section 2.2,
EADI Operation. The CP466A/B radar control panels are covered in section 2.3, RADAR Operation. The CP 469/A MFD Control
Panel is covered in section 2.4,
MFD Operation.
1
CRS
23
340
33
V
O
R
1
ARL
WXA
A 2.2
ANT FLT
VOR 1
36.7 NM
N
36.7
NM
243 KT
0:09
3
90°
40
ADF 2
DH
CRS
RALT TST
HSI ARC
SYS REF
NAV
1-2
RNG
RNG
Issued 4/95
Figure 2.1
ED 551A Display Unit and
Companion/CP 467 Control Panel
SW 06/07/08/11
BRT
HDG
2.1.1
EHSI Operation
360 MODE SELECT
HSI COMPASS ROSE
NAV MAP
NAV MAP WITH WX
DG
SECTORED MODE SELECT
ARC COMPASS ROSE
ARC NAV MAP
ARC NAV MAP WITH WX
ARC COMPASS ROSE WITH WX
PULL SET
RADIO ALTIMETER
PUSH TEST
RADIO ALTIMETER
NAV SOURCE SELECT
VOR, LOC,TCN or RNV
TCN
FMS, LOR, OMG or GPS
NAV
MLS
ADF
HOM
TEST/REF
TEST
*GROUND SPEED
*TIME-TO-STATION
NAV MAP FORMAT
DH
CRS
RALT
HSI
TST SYS REF
ARC NAV
1-2
RNG
RNG
#1 BEARING
POINTER SELECT
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR, OMG, or GPS
NAV
MLS
ADF
DME DISTANCE ONLY
#2 BEARING
POINTER SELECT
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR, OMG, or GPS
NAV
MLS
ADF
DME DISTANCE ONLY
BRT
HDG
RANGE SELECT
NAV MAP
WX
SYSTEM 1-2 SELECT
*NO SELECTION
AFTER SW 08
Figure 2.2
CP 467 Control Panel
For clarification on a particular display or operational feature, refer to section IV. EHSI DIS-
PLAYS or section V. OPERAT-
ING INSTRUCTIONS. Figure
2.1 shows the CP467 standalone EHSI/EADI Mode Controller & companion ED 551/A
Display unit and figure 2.2 shows the CP 467 Mode Controller
Operation.
2.1.2
SW 06/07/08/11 Issued 4/95
EHSI Operation
EHSI CONTROLS (CP 467)
HSI 360-DEGREE MODE
SELECTION
HSI
The EFS 50 has four possible
360-degree display formats: standard HSI compass rose,
NAV map, NAV map with weather, and DG mode. Each press of the HSI button sequentially selects the next display format.
A press of the HSI button while in the ARC mode will change the display to the standard HSI compass rose.
The display selection list may include the following:
H
S
I
HSI COMPASS ROSE
HSI NAV MAP
HSI NAV MAP
WITH WEATHER
(OPTIONAL)
DG MODE
(OPTIONAL)
PLAN VIEW
(OPTIONAL ON MFD)
DG ONLY and WEATHER are options selected at the time of installation and are included in the system certification.
If a compatible weather radar is not installed, the weather option will not be in the sequence.
ARC SECTORED MODE
SELECTION
ARC
The ARC mode provides the pilot a large scale view of the CDI by presenting an approximate 85degree sector display of the compass.
The EFS 50 has five possible
ARC sectored display formats: standard HSI compass rose,
NAV CDI map, NAV CDI map with weather and standard HSI compass rose with weather. A software configuration option, selectable at the time of installation and certification, allows a weather only mode to be selected on the MFD. A press of the
ARC button will sequentially select the possible display formats.
A press of the ARC button while in the 360-degree mode will result in an ARC presentation of the same format. For example, if the 360 NAV MAP WITH
WEATHER mode is being dis-
Issued 4/95 SW 06/07/08/11 2.1.3
EHSI Operation played and the ARC button is pressed, the resulting display format will be ARC NAV MAP WITH
WEATHER.
The ARC display selection list may include the following:
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)
WEATHER is an option selected at the time of installation and is included in the system certification. If a compatible weather radar is not installed, the weather option will not be in the sequence.
An additional ARC format option is offered, selectable at the time of installation and certification, which provides an uncluttered weather radar presentation on the MFD. The MFD ARC weather only format provides a typical weather radar presentation, no navigation data is presented when this mode is selected.
Refer to radar controls in this section for details on weather radar operation.
NAV NAVIGATION SENSOR
SELECT
NAV
During installation, the EFS 50 symbol generator was programmed with the type and quantity of each piece of interfacing equipment. Not all the equipment interfaced to the
EFS 50 is usable for primary navigation. The EFS 50 creates and maintains in permanent memory a list of the interfacing navigation sensors.
The NAV push button is used to select which NAV sensor provides primary navigation data. A
2.1.4
SW 06/07/08/11 Issued 4/95
EHSI Operation press of the NAV sensor select button sequentially selects the next available sensor from the list of those installed. Primary Navigation Data is defined as the distance in the upper right corner, selected course, course pointer and deviation.
The Primary Navigation Sensor is annunciated at the side of the display unit opposite the vertical scale. Only those sensors interfaced to the EFS 50 in a specific installation will be selectable for use and display.
The following is an all-inclusive list, in order, of primary navigation sensors that may be interface with the EFS 50:
N
A
V
ON-SIDE EFS
VOR (VOR, LOC, TCN or RNV)
NAV
TCN (Control head)
NAV
LNAV, (FMS, LOR OMG or GPS)
NAV
MLS
NAV
ADF
NAV
HOM
NAV
CROSS-SIDE EFS
NAV
1-2
NAV
1-2
NAV
1-2
1-2
NAV
1-2
NAV
1-2
VOR (VOR, LOC, TCN or RNV)
TCN (Control head)
LNAV, (FMS, LOR, OMG, or GPS)
MLS
ADF
HOM
NOTES: If a number 2 NAV sensor has been selected for display on the number 1 EHSI by pressing the 1-2 button and the number
Issued 4/95 SW 06/07/08/11 2.1.5
EHSI Operation
1 EHSI NAV push button is pressed, the next available number 1 NAV sensor will be selected.
ADF D-Bar presentation may not be available if the ADF does not provide a suitable flag output.
Software 08 treats unlike LNAV sources (i.e. FMS, LOR, OMG, or
GPS) as single sensors. When two unlike LNAV sources are configured, the EFS will display both the on-side LNAV and the off-side LNAV without a system number and the NAV button is used to select between them.
Note: The cross-side sensor for
VOR could be TCN, for LNAVs it could be a combination of
FMS, OMG , LOR, or GPS.
After software 08, the 1-2 button no longer selects between unlike LNAV sources.
When a RMI or NAV sensor select button is pressed and it is not active in the system, a yellow “FUNCTION NOT
IMPLEMENTED” will be displayed in the center of the screen.
BEARING POINTER
SELECT
1-2 NAVIGATION SYSTEM
SELECT
1-2
The 1-2 button is used to cycle between primary navigation sensor system #1 and #2 for display.
The primary NAV system selected is annunciated as sensor 1 or sensor 2 on the EHSI. Example, if VOR 1 is being displayed and the 1-2 button is pressed, VOR 2 will become the displayed sensor. If only one sensor is installed, the display will not cycle and the sensor annunciation will not show a system number. For example ADF would be displayed
(not ADF 1) in installations containing a single ADF.
The bearing pointer select buttons work in a similar manner as the NAV sensor select button. A press of the bearing pointer button sequentially selects the next available sensor for display. The bearing pointer sensor list contains only those sensors which have bearing information capabilities. If the selected sensor has distance information paired with it, that distance will also be displayed below the sensor annunciation. An optional push button sequence allows independent selection and display of the respective DME distance without the presence of the bearing pointer.
2.1.6
SW 06/07/08/11 Issued 4/95
EHSI Operation
The following is an all-inclusive list, in order, of the bearing pointer sensors that may be interfaced with the EFS 50:
OR
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)
MLS
ADF
DME DISTANCE ONLY, (OPTIONAL)
Only those sensors interfaced to the EFS 50 will be included in the sequence.
Software 07 added an option selectable at the time of installation and certification that removes the ability to display a
MLS bearing pointer.
For a single ADF installation, the ADF bearing pointer may be displayed on either the single or double bar pointer. The annunciation associated with either bearing pointer will be
ADF, not ADF 1 or ADF 2.
Note: Any single bearing pointer sensor may be displayed on either pointer. This includes unlike LNAV sources after software 08.
RANGE SELECTION
RNG
RNG
A press of the RANGE DOWN button selects the next lower range to be displayed while in the
NAV MAP or WEATHER modes of operation. Once the lowest selectable range is reached, the
RANGE UP button must be used for a range change.
The operation of the RANGE UP button is similar to the RANGE
DOWN except it selects the next higher range to be displayed while in the NAV MAP or
WEATHER modes of operation.
Note: To display weather information on the copilot’s EHSI it selected range must match one of those ranges displayed on the MFD or pilot’s EHSI.
Issued 4/95 SW 06/07/08/11 2.1.7
EHSI Operation
When the map range on the
MFD or pilot’s EHSI no longer matches the range selected on the copilot’s EHSI the copilot will display stale weather information for 30 seconds. A “WX
FLT” warning will then display on the RADAR fault warning line alerting the pilot of range mismatch.
TST/REF
SYS REF
The TST/REF button performs three functions: SELF TEST display, Ground speed or Time-to-
Station selection and LNAV MAP formatting.
◗ TST -
To display the EHSI system
SELF TEST, press and hold the
TST/REF button for three seconds. Upon entering Self Test, a test pattern will be displayed. In the center of the test pattern, either a SELF TEST PASS or
SELF TEST FAIL will be annunciated. With 06 software, the
SELF TEST display will remain until the TST/REF button is pressed again. Beginning with
07 software, the EFIS will cancel the test mode and return both the
EADI and EHSI to normal operation after 5 seconds.
Note: If the SELF TEST FAIL message is annunciated, the system should be serviced.
◗ REF GROUND SPEED or
TIME-TO-STATION selection
With software 06 and 07, the
TST/REF button allows alternate selection of Ground speed or
Time-to-station (in minutes) as calculated by the selected primary NAV system. When Ground speed or Time-to-station information is available it will be displayed below the distance information in the upper right corner of the display. If the information is not provided, the associated annunciator will be removed.
The alternate selection of Ground speed and Time-to-station will not be allowed in the MAP mode with an LNAV selected as the primary navigation source.
After software 08, both ground speed and Time-to-station are displayed simultaneously. Timeto-station is displayed immediately below the Ground speed using the format of hours and minutes seperated by a colon (H:MM).
Note: The Time-to-station field used with software 08 can also be used for an abnormal DME annunciation which has priority.
The EFS 50 will calculate ground speed and Time-to-station in installations which use an ARINC
568 type DME. If a conventional
DME indicator is also used, differences in ground speed and
Time-to-station display may be notices.
2.1.8
SW 06/07/08/11 Issued 4/95
EHSI Operation
Note: Time-to-station is replaced with Time-to-waypoint when the selected primary nav is an LNAV providing this information.
◗ REF MAP FORMAT
When the selected EFS 50 display is LNAV MAP, the TST/REF button allows selection of the desired NAV MAP format. To determine the present MAP format momentarily press the
TST/REF button. The momentary button press will activate the present MAP format annunciation. If the displayed format is desired, no additional action is required; the format message will be removed within 5 seconds. If a different format is desired, sequence through the list by momentarily pressing the
TST/REF button until the desired format is displayed. Approximately 5 seconds after the last button press, the map format annunciation will be removed.
With software 06 and 07, the
NAV map format will remain as previously selected until changed using the TST/REF button, however beginning with 08 software the NAV map format is re-set to
FPL ID each time a MAP display is activated.
The following is an all-inclusive list, in order, of the possible NAV
MAP formats:
TEST
REF
FPL ID (FLIGHT PLAN WITH
FULL ICAO IDENTIFIERS)
AIRPORT (TO WAYPOINT AND NEAREST
AIRPORTS WITH ICAO IDENTIFIERS)
NAVAIDS (TO WAYPOINT AND NEAREST NAVAIDS
WITH ICAO IDENTIFIERS)
Note: Depending upon the Flight Management System installed, the above format options may not be fully supported. Systems such as the BENDIX/KING KNS 660 and KLN 88, that support the
GAMA 429 LNAV data bus will provide the above format options.
Issued 4/95 SW 06/07/08/11 2.1.9
EHSI Operation
COURSE SELECT KNOB
CRS
Rotation of the COURSE
SELECT knob allows the course pointer and digital course to be set at the desired course.
The CP467 and CP468 provide a ”DIRECT TO” feature. Pulling the CP467 or CP468 COURSE
SELECT knob will cause the course pointer and digital course read out on the EHSI to slew to the direct course to the selected
NAVAID.
If the selected NAV sensor is an
LNAV system, it may have modes of operation that control the selected course.
During these LNAV modes of operation the EFS 50 COURSE
SELECT knob will be inactive.
HEADING SELECT KNOB
HDG
The CP467 and CP468 provide a “HEADING SYNC” feature.
Pulling the CP467 or CP468
HEADING SELECT knob will cause the heading bug on the
EHSI to slew to the present aircraft heading (lubber line).
DISPLAY BRIGHTNESS
CONTROL
BRT
The BRT knob controls the display brightness.
Note: The display brightness control provides full range dimming to allow night operation in no- or low-light situations.
The lower limit of the display brightness may appear as an inoperative tube during normal daylight operation. It is therefore advisable to check the
BRT knob setting during preflight test.
To ensure maximum display tube life, it is highly recommended that the display be operated at the lowest acceptable brightness level.
Rotation of the HEADING
SELECT knob allows the heading bug on the EHSI to be rotated to the desired heading.
2.1.10
SW 06/07/08/11 Issued 4/95
EADI Operation
EADI OPERATION
EADI DETAILED OPERATING CONTROLS
This section, EADI Operation, of the EHI 50 Pilot’s Guide describes the EADI operational controls of the CP 467 used with an ED 551/A EADI.
EADI controls are limited to three basic functions: EADI display brightness adjustment, DH (decision height) set and Radio Altitude test.
For clarification on a particular display or operational feature refer to section IV, EADI DIS-
PLAYS or section V, OPERAT-
ING INSTRUCTIONS.
DH
CRS
RALT
HSI
TST SYS REF
ARC NAV
1-2
RNG
RNG
BRT
HDG
BRIGHTNESS
Figure 2.2.1
CP 467 EFIS CONTROL PANEL
BRT knob setting during preflight test.
BRT
To ensure maximum display tube life, it is highly recommended that the display be operated at the lowest acceptable brightness level.
DH SET
The BRT knob controls the display brightness.
Note: The display brightness control provides full range dimming to allow night operation in no- or low-light situations.
The lower limit of the display brightness may appear as an inoperative tube during normal daylight operation. It is therefore advisable to check the
DH
To set the Decision Height, pull out and turn the DH knob. Turning clockwise will increase the
Issued 4/95 SW 06/07/08/11 2.2.1
EADI Operation
Decision Height selected, turning counter clockwise will decrease the Decision Height. The DH set knob is variable rate, the faster the knob is turned, the greater the change in a given amount of rotation. The Decision Height range is from “OFF” to 2,500 feet and will be displayed in one foot increments up to 500 feet and then in 10 foot increments to
2,500 feet.
Once the desired DH is selected, push in the DH set knob to lock the selected DH altitude. If DH is set to OFF, the “DH” annunciation will not be displayed.
RALT TST
RALT TST
Pressing the RALT TST (Radio
Altimeter Test) push button provides a discrete output to the
Radio Altimeter initiating its self test function.
2.2.2
SW 06/07/08/11 Issued 4/95
Radar Operation
Radiation
WARNING!
This Instrument generates microwave radiation
DO NOT OPERATE UNTIL YOU HAVE READ
AND CAREFULLY FOLLOWED ALL SAFETY
PRECAUTIONS AND INSTRUCTIONS IN
THE OPERATING AND SERVICE MANUALS
IMPROPER USE OR EXPOSURE MAY CAUSE
SERIOUS BODILY INJURY
Caution:
1. Maintain prescribed safe distance when standing in front of a radiation antenna.*
*Reference FAA Advisory
Circular #20-68B
2. Never expose eyes or any part of the body to an unterminated waveguide.
Issued 4/95 SW 06/07/08/11 2.3.1
Radar Operation
Maximum Permissible Exposure Level (MPEL)
In order to avoid the envelope in which the radiation level exceeds the U.S. Government standard of
10 mW per square centimeter, all personnel should remain beyond the distance indicated in the illustration below. The distance to the MPEL boundary is calculated upon the basis of the largest antenna available with the RDS
81/82/82 VP/84/84 VP/86 and 86
VP system, rated output power of the transmitter and in the non rotating boresight position of the antenna.
With a scanning beam the power density at the MPEL boundary is significantly reduced.
MPEL BOUNDARY
3 FEET
OF AIRCRAFT
180˚
RADOME
2.3.2
SW 06/07/08/11 Issued 4/95
Radar Operation
RADAR OPERATION
RADAR CONTROLS, (CP 466A & CP 466B)
The following section provides general operating information on
EFS 50 radar control panels,
CP 466A & CP 466B. Figure
2.3.1 shows the CP 466A used with an RDS 81, RDS 82 or
RDS 82VP, RDS 84 or
RDS 84VP. Figure 2.3.2 shows the CP 466B used with an
RDS 86 or RDS 86VP. For detailed information on the specific weather radar functions, refer to the appropriate radar pilot’s guide.
TST
ON
STBY
OFF
GAIN
Wx
VP
WxA
GND
MAP
TK TRK TRK
UP
TILT O
PULL STAB OFF
DN
Figure 2.3.1
CP 466A
TST
ON
STBY
OFF
Wx WxA
GND
MAP
VP
GAIN
PULL ARL
UP
TILT O
DN
PULL AUTO
Figure 2.3.2
CP 466B
Note: The CP 466A and B shown include the push buttons required for the Vertical Profile radars. For non-VP installations using the
CP 466A or B the VP and two track buttons will not be present.
Issued 4/95 SW 06/07/08/11 2.3.3
Radar Operation
OFF-STBY-TST-ON
ON
TST
STBY
OFF
The rotary OFF-STBY-TST-ON knob selects the desired operating condition for the radar.
◗ OFF
Disables the ART (Antenna,
Receiver and Transmitter) power supply. “OFF” is displayed below the NAV source annunciator on the radar mode line.
◗ STBY
After 30 seconds in this mode, the system is in a state of readiness. No radar transmission occurs, and the antenna is parked in the down position.
“STBY” is displayed below the
NAV source annunciator on the radar mode line, if a weather mode is selected.
◗ TST
Causes the test pattern to be displayed on the indicator, if a weather mode is selected.
“TEST” is displayed below the
NAV source annunciator on the radar mode line.
◗ ON
Selects the condition of normal operation, allowing for weather detection or other modes of operation. Depending on the selected mode of operation, WX,WXA or MAP is displayed below the
NAV source annunciator on the radar mode line.
Note: If “ON” is selected on the
CP 466 radar control panel, the radar Antenna, Receiver and Transmitter (ART) is operational. However, if a weather radar mode is not selected for display on one of the indicators the ART is placed in standby by the EFIS.
WX
Wx
Selects the weather mode (WX) when pressed. “WX” will be displayed below the NAV source annunciator on the radar mode line, if a weather mode is selected.
WXA
WxA
Selects the weather-alert mode when pressed. The magenta area of a storm will flash between magenta and black. “WXA” will be displayed below the NAV source annunciator on the radar mode line, if a weather mode is selected.
GND MAP
GND
MAP
Places the radar in ground mapping mode of operation; disables weather-alert feature and activates gain control. “MAP” will be displayed below the NAV source
2.3.4
SW 06/07/08/11 Issued 4/95
Radar Operation annunciator on the radar mode line. (Magenta is not active in the
GND MAP mode.)
LIGHTNING
❏ (Optional) Enables the Lightning display when pressed if a weather mode is selected for display.
VP
VP
❏ (Optional) Once the desired azimuth is selected with the TRK button, press the VP button to enter the Vertical Profile mode of operation. The Vertical Profile
Screen will appear. The weather mode of operation (WX, WXA or
GND MAP) displayed in the lower left corner of the display will be the same as existed just prior to selecting VP. To select a different weather mode once in
Vertical Profile, simply select the desired mode (WX, WXA or GND
MAP) by pressing the appropriate button.
Note: A brief period of time will normally elapse before the display will “paint” the Vertical
Profile “picture”. This time delay is due to the fact that the radar continues its normal azimuth scan after the VP button is pressed.
The operation of scanning the antenna vertically (+/- 20 or +/-
30 degrees depending on the
Radar) is referred to as taking a vertical “slice”.
Once Vertical Profile is selected, the desired profile-azimuth angle may be changed in two degree increments by pressing and holding the appropriate TRK button.
One of two things will happen when a TRK button is pressed:
(1) If the radar’s antenna is already profiling, the antenna will move in the two-degree increments, “slicing” in the direction determined by the TRK button; or
(2) A “WAIT” annunciation will be displayed indicating that the radar’s antenna will perform the desired “slicing” function as soon as the antenna returns to the last selected profiling-azimuth angle.
Note: Depending on the software version of the RDS VP radar and the system installation, the antenna may also scan horizontally while in the
VP mode. If the antenna is not sweeping vertically when the TRK button is pressed, a
“WAIT” annunciation will be displayed until the antenna returns to the last vertical
“slice” azimuth.
To terminate the Vertical Profile mode and return to the normal mode (horizontal scan), press the
VP button. The radar system will retain its existing weather mode and return to horizontal scanning.
A track line will be present on the screen for 15 seconds to indicate the location of the last profilingazimuth angle.
Issued 4/95 SW 06/07/08/11 2.3.5
Radar Operation
Beginning with EFS software version 11, a Split Screen mode is added to the VP button selection sequence immediately following the Vertical Profile mode. Durng this Split Screen mode the EFS will toggle the antenna between vertical and horizontal scans every 6 seconds, allowing both to be displayed simultaneously on the MFD. See Figure 4.4.4.
Note: This Split Screen mode is an operational enhancement added to EFS 11 software that does not require any modification to the existing RDS
82VP/84VP/86VP weather systems. Since this feature was not part of the original design of these radars, the transition between horizontal and vertical scans is not synchronized to the antenna scan and will therefore occur at random scan positions.
Horizontal (azimuth) and vertical
(tilt) track lines are displayed on the MFD full time during the split screen mode to indicate the antenna scan position in each plane.
TRK
TRK TRK
❏ (Optional) If the weather only mode is selected on the MFD, pressing the TRK button activates and slews a yellow dashed azimuth line. It also activates a digital display showing the number of degrees the azimuth line is located left or right from the nose of the aircraft. In any other map weather presentation, only the yellow dashed line will be displayed.
For VP operations, the TRK button performs two functions. 1.)
Prior to engaging VP, the appropriate button (left or right) is used to place the track line at the desired azimuth angle to be vertically scanned (sliced). When VP is engaged, the slice will be taken at the last position of the track line, whether it is visible or not. If the track line has not been selected after power has been applied to system and VP is engaged, the slice will be taken at 0 degrees (directly in front of the aircraft). 2.) When in VP mode, pressing the TRK will change the selected azimuth two-degrees left or right, depending on which button is pressed.
Continuously holding the TRK button will result in the system
“slicing” in two-degree increments.
2.3.6
SW 06/07/08/11 Issued 4/95
Radar Operation
GAIN
GAIN
Manual gain control becomes active when GND MAP is selected. In all other modes, gain is internally set.
If a CP 466A is installed, pull the
Tilt selector knob, PULL STAB
OFF, for “STAB OFF” operations.
“STAB OFF” will appear on the
Radar Fault/Warning line displayed below the NAV source annunciator just under the Antenna Tilt annunciation line.
PULL ARL
PULL ARL
Only present when an RDS 86 or
RDS 86VP is installed. Automatic Range Limit displays a blue area behind weather systems where weather detection is no longer possible because of attenuation.
UP
TILT
TILT
DN
If a CP 466B is installed, pull the
Tilt selector knob, PULL AUTO, for Auto Tilt. If selected, an “A” will follow the tilt direction indication arrow preceding the internally calculated Auto tilt angle supplied by the ART.
Permits manual adjustment of antenna tilt 15 degrees up or down to enable the pilot to analyze the weather presentation.
The tilt angle is displayed below the NAV source annunciator on the radar tilt annunciator line.
Issued 4/95 SW 06/07/08/11 2.3.7
Radar Operation
* This page intentionally left blank.
2.3.8
SW 06/07/08/11 Issued 4/95
MFD Operation
MFD OPERATION
MULTI FUNCTION DISPLAY CONTROL PANEL
The EFS 50 Multi Function Display Control Panel provides for display of a more meaningful variety of data than was previously accessible on EFIS MFD displays. In fact, the EFS 50
MFD may be used as a second
EHSI by the pilot or copilot, providing them the ability to cross check their primary EHSI, preview or set up for a potential navigation scenario, and still function as a primary weather radar or
LRN map display.
The CP 469 or CP 469A, MFD control panel, provides control of the selection of Nav source selection, display format and course selection. The CP 469A provides the additional capability of checklist and TCAS traffic displays when used with EFS system software 08. Weather radar control functions and mode selection are performed by the
CP 466, an independent weather radar control panel.
CRS
CRS
HSI
SEL TST REF
ARC NAV
RNG
1-2
RNG
BRT
Figure 2.4.1
CP 469
TCAS
ONLY
CRS
HSI ARC
CRS SEL
ENT NAV
1-2
TST REF
CHK
LIST
BRT
Issued 4/95
Figure 2.4.2
CP 469A WITH CHECKLIST & JOYSTICK
SW 06/07/08/11 2.4.1
MFD Operation
CONTROL PANEL BUTTON OPERATIONS
Those push buttons which have common operation between the
MFD and EHSI control panels,
CP 467 and CP 468, will function as defined in the section 2.1,
EHSI Operation unless otherwise noted in this section. For detailed operational information on those buttons please refer section 2.1.
pendent of, the one on the CP
467. The MFD ARC button will allow the selection of an optional radar only MFD display. This display will not contain navigation or map data. The ARC button will not function while Plan-View is displayed. The ARC button will not function while Plan-View is displayed.
TCAS ONLY
BUTTON
TCAS
ONLY
This button is not functional in
Software 06 or 07. The message
“FUNCTION NOT IMPLEMENT-
ED” will be displayed on the MFD if this button is pressed with these software versions.
With software 08, this button will alternately select between “TCAS
ONLY” and the previously selected display on the MFD, if TCAS is installed.
HSI BUTTON
HSI
Will function identical to, but independent of, the one on the CP
467. The MFD HSI button will allow the additional selection of an optional plan view on the
MFD.
Refer to section 2.1 EHSI OPER-
ATION for detailed information.
ARC BUTTON
ARC
Will function similar to, but inde-
ENT BUTTON
◗ LNAV MAP
ENT
The cursor position information can be transferred to the LNAV that is selected as the primary navigation sensor, by pressing the ENTER button while the cursor and its coordinates are displayed. The coordinates of the cursor will remain displayed for at least 10 seconds and will disappear from the display within 15 seconds after the ENTER button is pressed.
◗ PLAN-VIEW MAP
(available with software 07)
When Plan-View is selected, pressing the enter button will place the symbolic aircraft, present position, at the center (+) of the display.
◗ CHECKLIST
(available with software 08)
In the Checklist mode the enter button will generally function to check items in the list. The checklist was designed such that
2.4.2
SW 06/07/08/11 Issued 4/95
MFD Operation the pilot can complete the entire checklist by using only the enter button.
Normally, pressing the ‘ENT’ button will cause an unchecked checklist line to be checked and the cursor to advance to the next unchecked line. At the end of a page pressing the ‘ENT’ button will cause the cursor to advance to the next page (if available) and to check the first unchecked line on that page. If no unchecked items exist between the cursor position and the end of the list, the cursor is placed on the first unchecked page which referenced the specific list.
two enables the NAV button to function identical to, but independent of, the one on the CP 467.
When this configuration option is selected the pilot can select any available nav sensor for display on the MFD independent of what is displayed on the EHSI.
RANGE UP/DOWN BUTTONS
NAV BUTTON
NAV
With checklist inactive, these buttons will function identical to, but independent of, the range buttons on the CP 467. With checklist active, these buttons will move up and down the “checklist tree” through the different levels of index pages.
The NAV button may be configured at the time of installation and certification to operate in one of two methods.
Refer to section 2.1 EHSI OPER-
ATION for detail information.
❏ Configuration option number one will slave the MFD to the #1
EHSI. The NAV push button will cause the MFD to display either the same NAV sensor as displayed on the EHSI or the LNAV.
When this configuration is selected the 1-2 push button allows selection between the on side and off side sensors. Once a side is selected, that side will remain the selected side until 1-2 button is pressed again. This allows the pilot the ability to select the off side sensor to provide himself a constant visual cross comparison.
CHECKLIST
BUTTON
CHK
LIST
This button is not functional for
Software 06 or 07. The message
“FUNCTION NOT IMPLEMENT-
ED” will be displayed on the MFD if this button is pressed with these software versions.
With software 08, this button will alternately activate and de-activate the checklist mode on the
MFD.
CRS
COURSE SELECT
KNOB/BUTTON
CRS
❏ Configuration option number
Issued 4/95 SW 06/07/08/11
SEL
2.4.3
MFD Operation
The course select knob will function identical to, but independent of the one on the EHSI control panel, CP 467, when the CRS
SEL button is activated. This provides independent selection of course on the MFD referenced to the same or a different nav sensor.
If the CRS SEL button is not activated, the course select knob on the CP 469 will not be active. In this mode the MFD will obtain selected course data from the pilot EHSI control panel. In this mode the course on the EHSI and MFD will be synchronized, unless the selected sensor on the MFD is a LNAV providing
DTK.
When the MFD course select knob is not active, a bar with the color of the CRS annunciator will be placed above it. This will alert the pilot that the MFD CRS knob is not active and is referenced to the pilot’s EHSI selected course.
Example:
CCRRSS
135
While checklist mode is active, the course select knob will not function and the CRS SEL button will cause a list of active checklist emergencies to be displayed on the MFD.
BEARING #1 & #2 BUTTON
Will function identical to, but independent of, the one on the CP
467.
Refer to section 2.1 EHSI OPER-
ATION for detail information.
JOYSTICK
◗ LNAV MAP
When the joystick is interfaced to an EFS 50 system, it can be used to generate and move single waypoints on the display unit.
These waypoints can then be entered into the KNS 660, or any other LNAV using an appropriate
GAMA 429 interface.
With an LNAV, RNAV, (or KNS
81 configured as a NAV) selected for the primary nav sensor and during display of a NAV MAP on the MFD, initial movement of the joystick will create a waypoint cursor ahead of the aircraft on the half range ring at the current heading. This will be true for both
HSI and ARC display formats.
The cursor will be a standard white waypoint symbol. Movement of the waypoint will be in any of the eight directions commanded by the joystick. The rate of movement will start off slow and increase in speed in two steps. Return of the joystick to its center, off position at any time will reset the rate of movement to the slowest speed. The cursor location on the display screen and its rate of movement relative to the display screen will be inde-
2.4.4
SW 06/07/08/11 Issued 4/95
MFD Operation pendent of the display range selected. The cursor is not allowed to exit the compass.
When an LNAV is selected as the primary navigation source,
Lat/Lon coordinates of the cursor will be displayed in the lower center of the display. The cursor position information can be transferred to the LNAV that is selected as the primary navigation sensor, by pressing the ENTER button while the cursor and its coordinates are displayed. The coordinates of the cursor will remain displayed for at least 10 seconds and disappear from the display within 15 seconds after activating the ENTER button. If the waypoint cursor is not moved for 20 seconds, it will disappear from view. The next time the joystick is moved, the cursor will reappear in the same location on the display screen. However, a change of primary NAV sensor or display modes will reset the invisible cursor location to its initial starting position.
Note: Systems with an MFD can have a joystick on the CP
469A MFD control panel or a stand alone joystick. Additional joysticks for the pilot or copilot normally will not be installed. Systems without an
MFD may have up to two joysticks that are completely independent of each other; one for the pilot and one for the copilot. The pilot’s joystick can create or move a waypoint only on the pilot’s EHSI, and any waypoint created by the pilot can only be loaded into the #1
RNAV or #1 LNAV. Likewise, the copilot’s joystick can create or move a waypoint only on the copilot’s EHSI, and any waypoint created by the copilot can only be loaded into the
#2 RNAV or #2 LNAV.
◗ PLAN-VIEW MAP
A small plus (+) marks the center of the Plan-View map. By moving the joystick the lat/long of the center of the screen will change, providing a “moving map” effect, however lat/long coordinates are not displayed. The flight plan moves about the display in the direction the joystick is moved.
The symbolic aircraft is shown, in its proper location with proper heading, when the present position from the LNAV is within the display area. There are no boundary limits and the symbolic aircraft may move out of the display area. Waypoints can not be created using the joystick while plan view is displayed.
Note: If a joystick or enter button is not installed in the aircraft, the symbolic aircraft may be repositioned to the center of the display by deselecting and reselecting the Plan-View
Mode. Selecting a greater range may bring the symbolic aircraft into view if the present position and the center of the display are not greater than a thousand nautical miles apart.
Issued 4/95 SW 06/07/08/11 2.4.5
MFD Operation
◗ CHECKLIST MODE
(available with software 08)
In the Checklist mode, the Joystick commands will be limited to four positions: UP, DOWN, LEFT and RIGHT. The 45° commands will be ignored.
A down push on the joystick will advance the cursor checklist line.
A down push at the bottom of a checklist page will advance the cursor to the next page if available. Continuous downward pushes will wrap the cursor within a checklist.
An up push on the joystick will move the cursor up one checklist line. An up push at the top of a checklist page will move the cursor to the previous page if available. Continuous upward pushes will wrap the cursor within a checklist.
A right push on the joystick will move the cursor to the top of the next checklist page. Continuous right pushes will wrap the cursor to the top of the next page within a checklist.
A left push on the joystick will move the cursor to the top of the previous checklist page. Continuous left pushes will wrap the cursor to the top of the previous page within a checklist.
1-2 BUTTON
1-2
If NAV push button configuration option number one is selected, where the MFD is slaved to the
EHSI, the 1-2 push button allows the pilot to select between on side and off side NAV sensors.
Unlike the 1-2 push button on the
EHSI control panel, it selects which side will be displayed until pushed again. A press of the
NAV push button will not cause a selected off side sensor to cycle back to an on side sensor as it does on the EHSI.
If NAV push button configuration option number two is selected, the 1-2 button functions identical to, but independent of, the one on the CP 467.
When checklist mode is active, the 1-2 key normally will not be active. However, if the active emergency summary page is currently displayed, the 1-2 key will cause the checklist unit to display an informational page listing all currently ‘bound’ emergency discretes. This page lists all eight emergency discretes, and the title of the checklist page that each was bound to using the
DEU utility software.
2.4.6
SW 06/07/08/11 Issued 4/95
TST/REF BUTTON
TST REF
With checklist inactive, this button will function identical to, but independent of, the TST/REF button on the CP 467.
With checklist active, thIs button will cause a checklist “help” page to be displayed on the MFD. The help page contains a list of all
CP 469A buttons that are active and thier function during the checklist mode.
Refer to section 2.1 EHSI OPER-
ATION for detailed information.
MFD Operation
Issued 4/95 SW 06/07/08/11 2.4.7
MFD Operation
*This page intentionally left blank.
2.4.8
SW 06/07/08/11 Issued 4/95
Issued 4/95
360 MODE SELECT
HSI COMPASS ROSE
NAV MAP
NAV MAP WITH WX
DG ONLY (OPTIONAL)
PLAN VIEW (OPTIONAL)
SECTORED MODE SELECT
ARC COMPASS ROSE
ARC NAV MAP
ARC NAV MAP WITH WX
ARC COMPASS ROSE WITH WX
WX ONLY (OPTIONAL)
COURSE SELECT
ACTIVATE
DEACTIVATE
NAV SOURCE SELECT
VOR, LOC,TCN or RNV
TCN
FMS, LOR or *GPS
NAV
MLS
ADF
HOM
TEST/REF
TEST
+GROUND SPEED
+TIME-TO-STATION
NAV MAP FORMAT
CRS
CRS
HSI
SEL
ARC
TST REF
NAV
RNG
RNG
1-2
BRT
Abbreviated Operations
#1 BEARING
POINTER SELECC
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR or *GPS
NAV
MLS
ADF
DME DISTANCE ONLY
#2 BEARING
POINTER SELECC
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR or *GPS
NAV
MLS
ADF
DME DISTANCE ONLY
RANGE SELECT
NAV MAP
WX
SYSTEM 1-2 SELECT
+NO SELECTION
BEGINNING WITH SW 08
*SW 08 OR LATER
Figure 3.1
CP 467 EFIS CONTROL PANEL OPERATION
SW 06/07/08/11 3.1
Issued 4/95
360 MODE SELECT
HSI COMPASS ROSE
NAV MAP
NAV MAP WITH WX
DG ONLY (OPTIONAL)
PLAN VIEW (OPTIONAL)
SECTORED MODE SELECT
ARC COMPASS ROSE
ARC NAV MAP
ARC NAV MAP WITH WX
ARC COMPASS ROSE WITH WX
WX ONLY (OPTIONAL)
COURSE SELECT
ACTIVATE
DEACTIVATE
Abbreviated Operations
NAV SOURCE SELECT
VOR, LOC,TCN or RNV
TCN
FMS, LOR or *GPS
NAV
MLS
ADF
HOM
TEST/REF
TEST
+GROUND SPEED
+TIME-TO-STATION
NAV MAP FORMAT
CRS
CRS
HSI
SEL
ARC
TST REF
NAV
RNG
1-2
RNG
BRT
#1 BEARING
POINTER SELECC
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR or *GPS
NAV
MLS
ADF
DME DISTANCE ONLY
#2 BEARING
POINTER SELECC
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR or *GPS
NAV
MLS
ADF
DME DISTANCE ONLY
RANGE SELECT
NAV MAP
WX
SYSTEM 1-2 SELECT
+NO SELECTION
BEGINNING WITH SW 08
*SW 08 OR LATER
Figure 3.2
CP 469 MFD CONTROL PANEL OPERATION
SW 06/07/08/11 3.2
Abbreviated Operations
360 MODE SELECT
HSI COMPASS ROSE
NAV MAP
NAV MAP WITH WX
DG ONLY (OPTIONAL)
PLAN VIEW (OPTIONAL)
TCAS ONLY SELECT
ACTIVATE
DEACTIVATE
SECTORED MODE SELECT
ARC COMPASS ROSE
ARC NAV MAP
ARC NAV MAP WITH WX
ARC COMPASS ROSE WITH WX
WX ONLY (OPTIONAL)
ENTER
SENDS JOYSTICK
WAYPOINT TO LNAV
CHECKS OFF
CHECKLIST ITEMS
NAV SOURCE SELECT
VOR, LOC,TCN or RNV
TCN
FMS, LOR or GPS
NAV
MLS
ADF
RANGE SELECT
CHECKLIST LEVEL
HOM NAV MAP
WX
TCAS
CHECKLIST SELECT
ACTIVATE
DEACTIVATE
TCAS
ONLY
CRS
HSI ARC ENT NAV
CHK
LIST
CRS SEL
1-2
TST REF
BRT
#1 BEARING
POINTER SELECC
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR or GPS
NAV
MLS
ADF
DME DISTANCE ONLY
COURSE SELECT
ACTIVATE
DEACTIVATE
CHECKLIST
ACTIVE EMER
#2 BEARING
POINTER SELECC
DECLUTTER
VOR, TCN OR RNV
TCN
FMS, LOR or GPS
NAV
MLS
ADF
DME DISTANCE ONLY
SYSTEM 1-2 SELECT
CHECKLIST EMER DISCRETES
TEST/REF
TEST
NAV MAP FORMAT
CHECKLIST HELP
JOYSTICK
MOVES WAYPOINT in LNAV MAP
MOVES MAP in PLAN VIEW
MOVES through CHECKLIST PAGES
Issued 4/95
Figure 3.3
CP 469A MFD CONTROL PANEL OPERATION
SW 06/07/08/11 3.3
EHSI Displays
EHSI DISPLAYS
EFS 50 COLOR STANDARDS
The EFS 50 uses a defined color set which aids the pilot in interpreting displayed information.
A brief summary of the color set is as follows:
Warnings
Cautions/Abnormal Source
Scales and associated figures
On-side approach and navigation data
Cross-side NAV data
On-side non-approach navigation data (LNAV)
On-side commanded data
Cross-side commanded data
Selected heading, DME HOLD annunciation
Selected source
Selected active route/flight plan
Cross-side selected active route/flight plan
Held DME distance display
Red
Yellow
White
Green
Yellow
Cyan
Green
Yellow
Orange
Matches NAV data color
Green
Yellow
White
STANDARD EHSI DISPLAYS
Refer to Figures 4.1.5 and 4.1.6
while reviewing STANDARD
EHSI DISPLAYS.
long. Fixed 45-degree index marks are adjacent to the compass scale.
NORMAL COMPASS CARD
360-degree rotating white compass scale indicates aircraft heading referenced to white triangular heading index (lubber line). The compass scale is divided in 5-degree increments with the 10-degree divisions being approximately twice as
Free AHRS operation will be annunciated by a yellow FHDG to the left of the lubber. The Free mode annunciation will only be supported in installations with an
ARINC 429 AHRS (Attitude
Heading Reference System) that supports the Free DG (directional gyro) mode of operation via the digital data bus.
Issued 4/95 SW 06/07/08/11 4.1.1
EHSI Displays
Dual selectable compass inputs are provided for. If a second compass system is installed, the cross-side source is selected by means of a remote mounted switch. Once the alternate compass source has been selected, a yellow HDG1 or HDG2 will be displayed to the left of the lubber line.
If both systems select the same heading source, a yellow “HDG1” or “HDG2” with a yellow box around it will appear on both
EHSIs alerting the pilots that they have the same source selected.
PILOT COPILOT
HDG1 HDG1
Figure 4.1.1
SAME HEADING SOURCE
SELECTION
When two compass sources are available, the two inputs are compared for agreement. If the two inputs do not fall within 6degrees of each other while in level flight, a yellow comparison warning, HDG under a doubleended arrow, will be annunciated to the right of the lubber line.
See figure 4.1.5, EHSI SYMBOL
DEFINITION.
NAVIGATION SOURCE
ANNUNCIATION
A vertical three- or four-letter alphanumeric readout located on the left or right side of the display, depending on vertical scale side selection, indicates the system selected as the primary navigation sensor.
4.1.2
For dual sensor installations the cross-side navigation system may be selected by pressing the
1-2 push button. Example: pilot selecting co-pilot’s navigation system or co-pilot selecting pilot’s navigation system. The 1-2 push button will not be active if the system configuration does not support two of the same type
NAV sensors.
Green annunciations indicate an on-side approach NAV system or an enroute NAV system which has been approved for approach use is being displayed. Yellow indicates the cross-side system has been selected. Cyan annunciations apply to on-side nonapproach LNAV systems. These color codes apply to the NAV source annunciator, CRS pointer, deviation bar, CRS line in MAP mode, CRS, distance, groundspeed readout, time-to-station readout, drift angle pointer, and vertical deviation pointer.
Note: For GPS installations, the color of annunciators may not change at mode arming unless the mode enable transition coincides with the mode arm.
If both sides select the same navigation source, (i.e., pilot and co-pilot select VOR 2) a yellow box is placed around the navigation source annunciator on both
EHSI‘s.
If both sides select their respective cross-side navigation source
(i.e., pilot selects system 2, copilot selects system 1) then both
SW 06/07/08/11 Issued 4/95
NORMAL
R
V
O
1
P
I
L
O
T
R
V
O
2
L
O
T
C
O
P
I
SAME SOURCE
R
V
O
2
P
I
L
O
T
R
V
O
2
L
O
T
C
O
P
I
EHSI Displays
BOTH SELECT
CROSS SIDE
R
V
O
2
P
I
L
O
T
R
V
O
1
L
O
T
C
O
P
I
GREEN GREEN YELLOW GREEN YELLOW YELLOW
YELLOW BOX AROUND SENSOR
Figure 4.1.2
SAME NAVIGATION SOURCE SELECTION ANNUNCIATION
NAV source annunciators will be yellow with no yellow box.
The heading bug is used to indicate desired heading and provides selected heading reference for autopilot steering.
Note: Same source annunciation rules also apply to the heading source.
SYMBOLIC AIRCRAFT
The orange symbolic aircraft provides a visual reference of the aircraft present position in relationship to the deviation bar.
HEADING SELECT “BUG”
A notched orange heading bug is manually rotated around the compass scale by the heading select knob on the control panel.
In the 360-degree compass mode a full time digital readout of the selected heading is displayed below the vertical deviation scale position. In the ARC mode, a digital heading readout is displayed when the heading bug is not completely in view. The digital readout will be positioned just inside the compass scale on the side nearest the heading bug.
Once set, the heading bug rotates with the compass card.
A RED X will be drawn through the heading bug if there is a heading select knob failure on the EFS 50 control panel.
COURSE SELECT
The CRS control knob rotates the course pointer about the compass scale and sets digital course readout. Once set, the course pointer rotates with the compass card. The selected course indicates desired navigation course to be flown. Depending on the LNAV (long range navigation) installed, the course pointer may automatically be positioned to the DTK (desired track) when LNAV is selected as the primary sensor. When LNAV is the selected sensor and DTK is displayed, the EFS 50 course select knob is disabled.
In the upper left corner of the display, an alphanumeric readout annunciates the letters CRS and
Issued 4/95 SW 06/07/08/11 4.1.3
EHSI Displays indicates the selected navigation course in degrees. When in a
NAV map display mode, the course pointer will not be displayed, the alphanumeric readout will be the only reference for the selected course.
Note: Desired track readout
(DTK) generated by an LNAV system replaces (CRS) in
LNAV mode. Some LNAV systems may display CRS or DTK depending on the selected mode. MLS may display AZ
(azimuth) or BAZ (back azimuth) depending on the selected mode.
The system retains (remembers) the manually selected course, as set by the CRS knob, when the selected primary NAV sensor is sequenced through the LNAV position.
This allows an ILS inbound course to be selected prior to the completion of an LNAV flight leg that will be followed by an ILS approach.
In the event of a heading failure, the course pointer head and tail are removed and the course deviation scale is fixed in a horizontal position, providing standard course deviation information (CDI) referenced to the digital CRS selected. A RED X will be drawn through the CRS annunciation if there is a course select knob failure. In the event the selected course or desired track received from the LNAV becomes invalid, a RED X will be drawn through the digital readout.
Note: The above heading failure mode does not apply when
ADF is the primary NAV sensor. (ADF D-Bar is heading dependent and is non-operational without valid heading.)
LATERAL COURSE
DEVIATION SCALE
The course deviation scale, two white dots evenly spaced on both sides of the symbolic aircraft, provides a reference for the course deviation bar to indicate the center line of the selected navigation or localizer course in relation to the symbolic airplane.
The following represents the deviation scale for different navigation sources.
Note: Depending on the type of
LNAV installed, the Lateral
Deviation may be different.
Beginning with EFS software version 11, variable scale factor
LNAV is added to the configuration options. This allows the full scale deviation to vary between
0.0567 and 128 NM. If variable scale factor LNAV is configured and unavailable to the EFS, the lateral deviation scale will be flagged.
LATERAL COURSE
DEVIATION BAR
The course deviation bar represents the center line of the
4.1.4
SW 06/07/08/11 Issued 4/95
EHSI Displays
MODE
VOR/TAC
ADF
ANGULAR DEV
(DEGREES)
1 dot 5.0 deg
2 dots 10.0 deg
1 dot 7.5 deg
2 dots 15.0 deg
LINEAR DEV
(MILES)
LNAV or RNAV
LNAV or RNAV APPR
1 dot 2.5 NM
2 dots 5.0 NM
1 dot 0.625 NM
2 dots 1.25 NM
LATERAL DEVIATION SCALE
Aircraft displacement selected navigation or localizer course.
Note: The Lateral Course Deviation Bar may not be used as the primary means of navigation during an ADF approach.
The D-bar may be used to supplement the bearing pointer which is used as the primary navigation source.
center of the EHSI pointing toward the head (“TO”) or tail
(“FROM”) of the course pointer indicates whether the selected course is TO or FROM the station or waypoint. The TO/FROM annunciator is not displayed during ILS/MLS operation or when an invalid NAV signal is received.
DISTANCE,
GROUNDSPEED and
TIME-TO-STATION
If invalid or failed primary NAV sensor data is received the course deviation bar and scale are removed and a RED X annunciated.
The EFS 50 provides up to three distance displays — one for each selected navigation source
(if distance information is available from that source).
Beginning with software 11, the deviation bar and scale are decluttered without displaying a
RED X when the deviation information is provided in ARINC 429 format with a status of NO COM-
PUTED DATA (NCD). The RED
X will still be displayed if the data is missing or invalid.
The readout for the primary NAV source is shown in the upper right corner. This readout will also show aircraft groundspeed or Time-to-Station/Waypoint.
Both are displayed simultaneously with software 08.
TO/FROM INDICATOR
A white filled triangle near the
The distance readout for NAV 1
(the single-bar bearing pointer) is
Issued 4/95 SW 06/07/08/11 4.1.5
EHSI Displays in the lower left corner below the
NAV 1 source annunciator. The readout for NAV 2 (the doublebar bearing pointer) is in the lower right corner below the NAV
2 source annunciator.
These readouts show distance
(in nautical miles) to the selected station when in VOR, TACAN,
ILS or MLS mode. When in
LNAV or RNAV mode, distance to the waypoint is shown.
Each of these three distance readouts is displayed in the same color as the source annunciator and pointer with which it is associated.
The EFS 50 will display ground speed up to 999 KTS, Time-To-
Station up to 511 minutes, or 8 hours, 31 minutes (8:31) with software 08, and distance up to
4,095 nautical miles. In most cases, the DME will be the limiting factor in displayable data.
When DME HOLD is selected, the distance displayed is white in color. “H” follows GS field in upper right corner. During HOLD the displayed distance probably will not be associated with the selected bearing pointer. For more information on DME HOLD, refer to the DME HOLD section which follows.
❏ The bearing sensor selection function offers an optional DMEonly display feature in the cycle.
If the DME-only option was selected at the time of installation and certification, DME #1 and #2 information may be independently selected for display in the bearing pointer information area without displaying a bearing pointer.
Software 07 added the option to configure the DME annunciation in the bearing pointer field as either:
❏ DME
❏ NAV
To annunciate operational Distance Measuring Equipment
(including those associated with
LNAV) which has not acquired lock on to the selected station, dashes of the same color as the sensor annunciator will be placed in the distance data field. If the equipment has failed or information is not being received by the
EFS 50, the dashes will be Red.
In both cases the NM annunciation will remain and the KT/TTS will be removed if normally displayed.
DUAL MULTI CHANNEL
DME INSTALLATIONS
❏ Software 07 incorporated the capability to interface with a variety of multi channel DME,
VOR/ILS and MLS installations, and perform automatic reversion in the event of a failed DME sensor in certain installations.
For those installations supporting the automatic reversionary mode, the system can experience a
DME failure without the pilot or copilot loosing the normal distance presentation. For example, if the number one DME,
4.1.6
SW 06/07/08/11 Issued 4/95
EHSI Displays whose primary job is servicing the number one VOR/ILS, failed, the symbol generator would look to DME number two for VOR/ILS
DME number one distance information. If the information was present, a yellow boxed DME 2 would be displayed in the upper right hand corner of the number one EHSI and MFD. This alerts the pilot he is now getting distance information from the copilot’s DME. A green boxed DME
2 is placed in the same location on the number 2 EHSI alerting the copilot the pilot is getting distance information from his DME.
These boxed DME annunciations use the same display field as the
Time-to-station (or Time-to-waypoint) after software 08. The abnormal DME annunciation has priority over TTS/TTW.
Note: The variety of the various
DME installations is numerous, and therefore may be necessary to refer to the aircraft flight manual supplement for specific operation of a given installation.
DME HOLD
When DME HOLD is selected, the DME distance and annunciator color will change to white and remain that color until HOLD function is released. The sensor identifier (ADF, VOR ILS, etc) shall retain the original assigned color, this color difference indicates there may be no relationship between the two fields. The
HOLD function is additionally indicated by an orange letter “H” which is displayed directly below and to the right of the distance information. DME groundspeed and time-to-station will not be displayed when DME HOLD is active. If the DME provides frequency information, the HELD
FREQUENCY will be displayed in white where the groundspeed was previously displayed.
DME HOLD for BEARING
POINTER/DME #1 and BEAR-
ING POINTER/DME #2 will operate as described above, but
HELD FREQUENCY information will not be displayed.
Once the DME is placed in
HOLD, its distance will continue to be displayed and will not be affected when bearing pointers and primary NAV sensors are changed unless the selected sensor provides range information such as an LNAV, RNAV or
MLS. In these cases, the held information will be replaced with the selected sensor’s range information.
The bearing pointer sensor annunciators located in the lower right and left corners of the display also provide range information when the selected bearing sensor has associated range. If the associated range information is provided by DME, then the range information and NM annunciation will change from the normal light blue or magenta color to white and be followed by an orange “H” when HOLD is activated. If an ADF is the selected bearing pointer sensor
Issued 4/95 SW 06/07/08/11 4.1.7
EHSI Displays and the DME assigned to that side is placed in HOLD, the large
ADF annunciation will reduce in size as the white held DME range information and orange “H” is displayed below it.
Please note that the range information being displayed is not referenced to the ADF, but to whatever channel the DME was tuned to when the pilot placed it in
HOLD.
DME HOLD will not function when an LNAV or RNAV is the selected sensor, and is not allowed when MLS is the selected primary sensor. The associated distance field is used to display waypoint distance or distance to the MLS station.
Note: It is important to remember that once a DME is placed in HOLD it probably is not referenced to any VOR/ILS sensor being displayed. Hold removes the dependency of the DME to the VOR/ILS control head. It is, therefore, up to the pilot to recognize that when the DME distance information color changes to white and the orange “H” is displayed, the distance presented is probably not paired to the
VOR/ILS control head frequency.
Hold is a pilot selected mode of operation for the DME. Once the pilot selects hold, it is the pilot’s responsibility to remember where the DME is HELD.
DME and DME HOLD operation may vary greatly from installation to installation. This variation in operation is directly dependent upon the number and types of
DME installed. To best understand how these two functions work in a particular installation, refer to the aircraft flight manual supplement or contact the installing agency for a detailed explanation.
BEARING POINTER
The rotating light blue single bar
#1 Bearing Pointer points in the direction of the selected bearing sensor ground station (or waypoint when in the LNAV or RNAV mode).
The rotating magenta double bar
#2 Bearing Pointer performs the identical function for #2 bearing sensor systems.
If the selected bearing sensor is not receiving valid data, the Bearing pointer assigned to that bearing source will not be displayed and a RED X will be drawn through the selected bearing source annunciator at the bottom left or right of the display. The associated distance data will remain displayed if valid.
If the compass card is MAG
(magnetic) referenced, TRUE bearing sensor pointers, such as
LNAV, may be displayed if valid mag var (magnetic variation) is provided to the EFS 50. In this case, the TRUE sourced bearing pointer information will be con-
4.1.8
SW 06/07/08/11 Issued 4/95
EHSI Displays verted to MAGNETIC reference.
If the compass card is TRUE referenced, MAGNETIC bearing sensor pointers, such as VOR and ADF, may be displayed if valid mag var (magnetic variation) is provided to the EFS 50.
In this case, the MAGNETIC sourced bearing pointer information will be converted to TRUE reference.
In most cases mag var is provided by an LNAV. In a single
LNAV installation the EFS 50 will use the single mag var source to compute display correction for both number 1 and number 2 sensors. In dual LNAV installations, the on-side source of mag var will be used to compute correction unless the cross-side source is selected as the primary
NAV source; then its mag var will be used.
If mag var becomes invalid, those bearing pointers displayed with mag var correction will be removed and a RED X is drawn through the sensor annunciator in the lower right or left corner.
In the event a heading failure occurs, a heading flag will be displayed to the pilot, the compass card will remain active to follow input form the compass system.
Bearing pointer information will continue to be displayed. The
EFS 50 will process the bearing information and present all bearing pointer information except
ADF referenced to the compass card, the ADF bearing pointer will be relative to the nose of the aircraft and lubber line on the EHSI.
EXAMPLE:
NOTE: Refer to figure 4.1.4
BEARING POINTER OPERA-
TION WITH LOSS OF HEAD-
ING when reviewing this example.
Aircraft actual mag heading is
030 degrees, but EHSI compass is failed and displays an incorrect heading of 090 degrees — 60 degrees greater than actual. Bearing pointer number one is referenced to a
VOR station and is pointing to
120 degrees on the compass card. Bearing pointer number two is referenced to an ADF station and is pointing to 180 degrees on the compass card.
When interpreting bearing pointer number one in this example, remember that VOR,
TCN, RNV, FMS, LOR or GPS indications are referenced to the compass card. Therefore, since bearing pointer number one is pointing to 120 degrees on the compass card, the correct course to the VOR is 120 degrees. Likewise, since the tail of bearing pointer number one is on the 300-degree mark on the compass card, the correct bearing from the VOR is
300 degrees.
Caution: Do not assume that the course to the VOR is 30 degrees to the right of the aircraft nose. Although the bearing
Issued 4/95 SW 06/07/08/11 4.1.9
EHSI Displays pointer is pointing 30 degrees to the right of the lubber line, you must remember that the pointer in this instance is referenced to the compass card — not the lubber line or symbolic aircraft.
When interpreting bearing pointer number two in this example, remember that ADF indications are referenced to the lubber line and the symbolic aircraft. They are not referenced to the compass card. The compass card can be used only to help you determine ADF relative bearing.
Likewise, the tail of the pointer is at 360. Indicated heading on the compass card is 090. So relative bearing is 90 degrees left. Actual heading is 30 degrees. So actual bearing from the NDB is 90 degrees to the left of 30 degrees, which is 300 degrees.
One other thing to note about
ADF indications with failed heading is this: The ADF bearing pointer points to the station relative to the symbolic airplane.
Since the bearing pointer in the example is pointing straight off the right wing of the symbolic airplane, you may conclude the station is straight off the right wing of the actual airplane.
MAGNETIC/TRUE HEADING
ANNUNCIATIONS
To the left of the lubber line a white “T” will be displayed when the compass card is in the true mode of operation or left blank when in magnetic mode.
4.1.10
Magnetic compass heading is automatically displayed unless
True heading is selected by a remote switch or when the selected primary NAV sensor is an LNAV and it selects the True mode of operation. Valid mag var must be present before True heading can be selected by the
LNAV.
GLIDE SLOPE/VERTICAL
NAVIGATION
When the selected primary NAV sensor is ILS, MLS, or LNAV with
VNAV selected, a stationary white vertical deviation scale will appear on the right or left side of the EHSI display as configured at the time of installation and certification. This scale provides a reference for the vertical deviation pointer. The deviation pointer moves in relation to the scale to indicate glide path center with respect to aircraft position.
When the selected primary NAV sensor is an on-side ILS, MLS, or
LNAV in the approach mode, the vertical deviation pointer is green in color. If an off-side sensor is selected for display, the deviation pointer changes to yellow alerting the pilot that he has selected other than his on-side NAV sensor. A cyan ponter is displayed for VNAV provided by an on-side
LNAV in the enroute mode. Full scale VNAV deviation represents
±1000 feet when provided by an
LNAV in the enroute mode. Prior to 08 SW, full scale VNAV deviation represents ±500 feet when
SW 06/07/08/11 Issued 4/95
Issued 4/95 SW 06/07/08/11
EHSI Displays provided by an LNAV in the approach mode, however after
08 SW, this scaling can be configured to be ±1000, ±500, ±250, or ±200 feet.
If the selected sensor is ILS, a
“GS” will be displayed in the vertical pointer. When MLS is the selected sensor, this annunciation will be “GS” for SW 06 and
07, but beginning with SW 08, either “GS” or “GP” (for Glide
Path) may be annunciated. “VN” will be annunciated if the selected sensor is an LNAV with VNAV selected. When MLS is the selected sensor, the selected glide path angle is displayed above the glideslope deviation scale. If VNAV is displayed “FT”
(feet) or “AN” (angle) will be annunciated above the vertical deviation scale.
If the vertical deviation data becomes invalid, the course deviation bar and scale are removed and replaced with a RED X annunciation.
Additional configuration options selectable at the time of installation and certification:
❏ Declutter GS on Back
Course, allows the vertical deviation scale to be in view at all times or only when the selected course is within
105 degrees of the aircraft heading.
Vertical Scale Side, allows the vertical deviation scale to be displayed on either the:
❏ Right or
❏ Left side of the EADI and
EHSI display.
VNAV Approach Mode Scaling, a configuration option added by software 08, allows the following values for a full scale
VNAV approach deviation.
❏ 1000 feet
❏ 500 feet
❏ 250 feet
❏ 200 feet
Vertical Pointer Type, selected at the time of certification.
G
S
Vertical Pointer Annunciation
for MLS A configuration option added by software 08, allows the choice of two pointer annunciations when an MLS is the selected primary NAV sensor.
❏ GS
❏ GP
If invalid or failed glide slope or
VNAV data is received, the vertical deviation bar and scale are removed and replaced with a
RED X annunciation.
Beginning with software 11, the vertical deviation bar and scale are decluttered without displaying a RED X when the deviation information is provided in ARINC
429 format with a status of NO
COMPUTED DATA (NCD). The
RED X is still displayed for invalid or missing data.
4.1.11
EHSI Displays
WIND VECTOR
❏ When the aircraft is equipped with the appropriate LNAV equipment, an optional full time wind vector indicating approximate wind direction and speed may be displayed in white in the upper left corner below the selected course. Wind vector information will be available only when valid data is provided by the LNAV. The information provided by this vector is advisory only. It is NOT intended for use during approach as critical flight data because it will become inaccurate during altitude changes.
In single LNAV systems the wind vector data may be displayed on all EHSI displays. In dual LNAV installations with an LNAV selected as the primary nav source, that LNAV is the only source of wind vector data. In dual LNAV installations with a primary nav source other than an LNAV, the wind vector data will be supplied only by the on-side with software prior to 08, but after SW 08, the off-side LNAV is used as a secondary source of wind vector information.
Note: If the selected LNAV is configured as a Crouzet
Omega, the wind vector will be displayed as the standard meteorological wind symbol.
DRIFT ANGLE POINTER
(LNAV only)
❏ The drift angle pointer is an optional hollow cyan (green or yellow in approach mode) triangular pointer which is generated by some LNAVs and rotates about the outside of the compass scale. Referenced to the lubber line, the drift angle pointer represents drift angle left or right of the aircraft heading. With respect to the compass scale, the drift angle pointer represents aircraft actual ground track.
Drift angle pointer information is provided by the LNAV and will be displayed only when the LNAV is selected as the primary NAV source and valid information is present. If the pointer information becomes invalid it will be removed from the display.
LNAV MODE
ANNUNCIATIONS
❏ A configuration option selectable at the time of installation and certification allows the LNAV mode annunciators to be displayed above the three letter vertical source annunciator “FMS”, “LOR” or
“GPS”. The following annunciations will be displayed in the priority listed:
• MSG white flashing for five seconds and then solid
• DR white flashing for five seconds and then solid
• WRN white flashing for five seconds and then solid
(not displayed in SW 07 and later)
• WPT white flashing for five seconds and then solid
• HDG white
• XTK white
• APR white
4.1.12
SW 06/07/08/11 Issued 4/95
EHSI Displays
360 MAP DISPLAYS
Refer to Figures. 4.1.7 and 4.1.8
while reviewing 360 MAP DIS-
PLAYS.
The EFS 50 provides two basic map formats, a 360-degree map display about the aircraft and an approximately 85-degree sectored map display in front of the aircraft. Information which may be displayed includes waypoints, navaids, airports and weather radar information. The type and amount of data presented on the map will depend on the interfacing equipment. When coupled with a compatible LNAV, such as the BENDIX/KING KNS 660, the
EHSI can show up to 15 map symbols. These will include all flight plan waypoints that are within the selected display range.
In addition, the pilot can choose to display either navaids or airports that are located off the flight-planned route. Up to 10 navaids or up to 10 airports can be displayed as long as the total number of map symbols does not exceed 15.
In addition to the above, the #1 and #2 bearing pointers can be overlayed to indicate the direction and distance to two additional navaids or waypoints.
Note: The following will address only those areas of the EFS 50 map mode which are different from the standard compass presentations.
All map presentations provide a traditional CDI display.
MAP 360 COMPASS CARD
The operation of the compass card remains the same in the
Map mode as in the standard
EHSI display. However, the outside of the compass card now performs a secondary function by becoming the outer range ring for the Map display.
SELECTED COURSE
The alphanumeric course select readout in the upper left corner of the display functions the same in the map mode as in the standard
EHSI mode. The standard EHSI selected course pointer, to/from pointer, deviation bar and deviation scale are removed from within the compass card display.
When the primary NAV sensor provides distance and bearing information the selected course pointer is replaced with the course line. If the primary NAV sensor “TO” or “FROM” waypoint or VOR is within the selected map range, a movable course line is drawn through its center.
As the selected course is changed, the course line will rotate about the referenced point.
If the selected primary NAV sensor is an approach on-side sensor, the inbound “TO” course line is green and the outbound
“FROM” course line is white. If
Issued 4/95 SW 06/07/08/11 4.1.13
EHSI Displays the selected primary NAV sensor is LNAV or en route RNAV the inbound “TO” course line is cyan
(green in approach mode). Any time the cross-side sensor is selected as the primary NAV sensor the inbound “TO” course line is yellow.
If the primary NAV sensor distance or bearing information becomes invalid the NAV symbol and course line will be removed.
“NO MAP” will be displayed to alert the pilot that insufficient data is present to calculate and plot the primary NAV sensor map.
“NO MAP” will also be displayed if the selected primary NAV sensor, (e.g. ILS, ADF), does not provide distance and bearing information. The lateral deviation scale will remain as long as valid bearing or deviation information is present.
MAP COURSE DEVIATION
INDICATOR
A stationary white scale along the bottom center of the display provides reference for the course deviation bar to indicate the position of the aircraft in relation to the selected navigation course.
This course scale provides a conventional CDI (course deviation indicator) presentation.
When LOC is selected while in a map mode, Back Course annunciation and CDI needle reversal is provided when the selected course is 105 degrees from the aircraft heading (results in a fly to situation). “BC”, in green, (yellow
“BC” if cross-side sensor is selected) is annunciated left of center on the lateral deviation.
TO/FROM
To the right of the alphanumeric
Course Select a white “TO” or
“FR” will replace the standard
EHSI TO/FROM pointer when in non-ILS map modes.
BEARING POINTER
While in the map modes standard EHSI bearing pointers are displayed when the selected bearing source does not have distance associated with it or when the distance is greater than the selected map distance. Once the bearing source falls within display distance the bearing pointer is removed and the associated map symbol is displayed.
The #1 system map symbol will be displayed in light blue and the
#2 will be displayed in magenta as are the standard bearing pointers.
If bearing or distance information becomes invalid, the map symbol will be removed. If only the distance information becomes invalid, the map symbol will be removed and replaced with the standard bearing pointer.
Note: See BEARING POINT-
ER, under STANDARD EHSI
DISPLAYS in this section for details on the display of Mag-
4.1.14
SW 06/07/08/11 Issued 4/95
EHSI Displays netic bearing pointers when the compass card is True referenced and the display of
True bearing pointers when the compass card is magnetic referenced.
REFERENCE WAYPOINT
When the joystick is interfaced to an EFS 50 system, it can be used to generate and move a single Reference Waypoint on the display unit. This reference waypoint can then be entered into the KNS 660 or any other
LNAV using an appropriate
GAMA 429 interface.
With an LNAV or RNAV selected for the primary nav sensor and during display of a NAV MAP on the EHSI, initial movement of the joystick will create a reference waypoint ahead of the aircraft on the half range ring at the current heading. This will be true for both HSI and ARC map display formats. The reference waypoint will be a standard white waypoint symbol. Movement of the waypoint will be in any of the eight directions commanded by the joystick. The rate of movement will start off slow and increase in speed in two steps. Return of the joystick to its center, off position at any time will reset the rate of movement to the slowest speed. The reference waypoint location on the display screen and its rate of movement relative to the display screen will be independent of the display range selected. The reference waypoint is not allowed to exit the compass. When an LNAV is selected as the primary navigation source, Lat/Lon coordinates of the reference waypoint will be displayed in the lower center of the display. The reference waypoint position information can be transferred to the LNAV that is selected as the primary navigation sensor, by pressing the
ENTER button while the reference waypoint and its coordinates are displayed. The coordinates of the reference waypoint will remain displayed for at least
10 seconds and disappear from the display within 15 seconds after activating the ENTER button. If the reference waypoint is not moved for 20 seconds, it will disappear from view and will reappear in the same location relative to the display screen (independent of range selection) the next time the joystick is activated.
However, a change of primary
NAV sensor or display modes will reset the invisible reference waypoint location to its initial starting position.
Note: Systems with an MFD can have a joystick on the CP
469 MFD control panel or a stand alone joystick. Additional joysticks for the pilot or copilot normally will not be installed. Systems without an
MFD may have up to two joysticks that are completely independent of each other; one for the pilot and one for the copilot. The pilot’s joystick will not be allowed to create or
Issued 4/95 SW 06/07/08/11 4.1.15
EHSI Displays move a waypoint on the copilot’s EHSI, and any waypoint created by the pilot can be loaded only into the #1 RNAV or #1 LNAV. Conversely, the co-pilot’s joystick will not be allowed to create or move a waypoint on the pilot’s EHSI, and any waypoint created by the co-pilot can be loaded only into the #2 RNAV or #2 LNAV.
RANGE RING
A light blue range ring located half way between the center of the symbolic aircraft and the outside of the map compass scale aids in determining distance of radar returns and/or position of navaids in relation to the aircraft.
Off the right wing of the symbolic aircraft, adjacent to the range ring is the range ring distance.
The range ring represents half the distance to the outer range ring of the compass scale. The available ranges, selectable from the EFS 50 are 5, 10, 20, 40,
80,160, 240, 320 and 1000 nm.
Note: Systems which have the
RDR 1400 interfaced with the
EFS 50 will display weather ranges of .5, 1 and 2 NM.
However, the NAV MAP feature is not supported on these shorter ranges.
TEST, STBY and WX are the only RDR 1400 mode annunciation’s displayed on the
EHSI. Tilt and beacon information is displayed only on the
RDR 1400 Control/Display unit.
360-DEGREE MAP WX
RADAR (IF EQUIPPED)
Refer to Figure 4.1.7 while reviewing this section.
If a compatible ARINC 708 weather radar such as the
BENDIX/KING RDS series is installed, weather information may be selected for display.
When selected, weather information will transparently overlay the existing navigation data. Light blue dotted lines represent the weather radar scan limits.
Depending on the installation, the
EFS 50 may act as a weather radar range controller or as a simple remote display when the
EHSI has weather selected and matches the radar range. As a display only, if weather is selected for display and the EHSI map range does not match the selected weather radar range “WX
FLT” will be annunciated in the weather radar fault/warning position. As a range controller, if the selected range does not match one allowed by the radar, “WX
FLT” will be annunciated in the weather radar fault/warning position. When the 1000 NM range is selected “RANGE” is displayed and the weather radar is placed in standby. If the EFS 50 is the only display media for the weather radar, the radar will be placed in standby when weather is not selected for display.
Note: EHSI installations with the BENDIX/KING RDS series
4.1.16
SW 06/07/08/11 Issued 4/95
EHSI Displays radar provide dual range selection by allowing the radar indicator and EHSI or dual
EHSIs to select independent ranges. Only one source of radar mode, tilt and gain is supported. When the ranges selected on the two controlling indicators do not match, the weather presentation will be updated on alternating sweeps of the radar antenna. Example: if pilot’s EHSI is updated on the right sweep then the radar indicator will be updated on the left sweep or vice versa.
In installations capable of providing weather information on three displays, the display without radar range control must match one of the controlling displays in order to present weather. If the range does not match, “WX FLT” will be annunciated in the weather radar fault/warning position.
Four data lines are reserved below the primary NAV sensor source annunciator to display radar information. The first line displays special performance feature annunciations such as
ARL (automatic range limiting).
The second line annunciates the standard radar modes WX, WXA or MAP. The third line provides a digital readout of tilt angle displayed in tenths of a degree preceded by an arrow pointing up or down to indicate tilt direction. If
Auto Tilt is activated, an “A” will follow the tilt arrow. The fourth line will display radar faults and warnings. The radar faults are prioritized. When more than one fault occurs the one with the highest priority will be displayed.
◗ TRACK LINE
A yellow dashed line, originating at the symbolic aircraft and extending to the edge of the compass card, appears on the weather display when either the track left or track right button is pressed on the radar control panel. The track line will be automatically removed within 15 seconds after the button is released.
LIGHTNING DETECTION
Up to 63 grey colored lightning cell symbols can be displayed on the EHSI or MFD displays when provided by a compatable lightning sensor. Unlike weather radar information, lightning data may be presented in all 360 degrees of display area. Range selection for all lightning data displayed on EFS is controlled by the EFS control panel. The EFS will display the following symbols depicting three different levels of lightning intensity:
LEVEL 1 LEVEL 2 LEVEL 3
Lightning information will only be displayed while weather is selected for display on the EFS. Some versions of Radar Control Panels
(RCP) have a lightning select
Issued 4/95 SW 06/07/08/11 4.1.17
EHSI Displays button (see section 2.3) which will alternately select and deselect lightning for display, however when selected, the lightning data will be in addition to the weather radar information if both are provided. The weather radar may be placed in standby if only lightning information is desired.
A single lightning data field is located immediately above the weather radar data fields. Three annunciations are possible in this field as shown in figure 4.1.8 at the end of this section. The annunciation “ON” preceeded by the lightning symbol indicates that lightning information has been selected for display and the lightning sensor is operational.
The annunciation “OFF” preceeded by the lightning symbol indicates that lightning has been deselected using the lightning select button on the RCP. This annunciation is only presented while a weather mode is selected on the EFS and will not be displayed in installations without a lightning select button on the
RCP. A fault condition is indicated by the annunciation “FLT” preceeded by the lightning symbol.
Possible faults are invalid or missing 429 data from the lightning sensor. Therefore, selecting lightning for display with power removed from the lightning sensor will cause a FLT annunciation on the EFS.
FULL TIME LNAV MAP
❏ A configuration option selectable at the time of installation and certification. It allows the LNAV map to be displayed when the selected primary NAV sensor is either an ILS or ADF in the map mode.
For configurations without the full time LNAV map configuration selected, when the selected primary NAV sensor is either an ILS or ADF with the map mode selected, the “NO MAP” message will be annunciated since sufficient data is not provided to create a map presentation. However, if a bearing pointer sensor is selected which provides bearing and distance information, an appropriate map symbol will be displayed if the selected map range is greater than the distance to the anvaid or waypoint.
If the selected range is less, a normal bearing pointer will be displayed.
If the full time LNAV MAP option is selected, the LNAV map will be presented when ever the selected primary NAV sensor is either an ILS or ADF with the map mode selected. The LNAV map will be presented all in white to show that the information being displayed is not to be used as primary navigation information. The purpose of the LNAV map information being presented is to provide the pilot better orientation between his present position and intended flight plan, mainly for use during the phase of the approach while being vectored for the intercept. Primary naviga-
4.1.18
SW 06/07/08/11 Issued 4/95
tion must be accomplished according to the raw data presented by the selected primary
NAV sensor being displayed on the lateral and vertical deviation pointers, not by the LNAV map.
The LNAV map will be displayed only if an LNAV is installed on the same side as the selected ILS or
ADF primary NAV sensor and the map mode is being displayed.
Note: Extreme care must be taken when this mode is used not to focus on the LNAV map.
Depending on the LNAV being used, the accuracy may be off several miles, providing opposite fly-to commands than the
ILS or ADF. It is a must that the primary NAV sensor data be the data flown.
Not flight certified at time of publication.
Refer to Figure 4.1.9 while reviewing ARC DISPLAYS.
EHSI Displays
Issued 4/95 SW 06/07/08/11 4.1.19
EHSI Displays
ARC (EXPANDED SECTORED MODE) DISPLAYS
The expanded sectored (ARC) format provides an enlarged display of weather radar information and increased resolution of navigation data due to the enlarged compass scale presentations.
Note: The following will address only those areas of the
EFS 50 ARC mode which are different from the standard
EHSI compass or MAP presentations.
COURSE DEVIATION
INDICATOR (EHSI ARC
NON-MAP FORMAT)
The rotating white course deviation scale operates the same in all non-map modes. The differences in the ARC modes are location and size: the scale is moved to the bottom center of the display and is slightly reduced in size.
HDG BUG (ALL ARC
FORMAT MODES)
Heading bug operation is the same in all modes. The only noticeable difference in the ARC mode is that the digital orange readout of selected heading is displayed only when the heading bug is not completely in view. In this event the heading readout appears on the side of the compass scale closer to the heading bug’s hidden position.
The displays covered in this section are custom displays, created at the request of specific customers to satisfy unique requirements. Every attempt was made to ensure these displays followed standard EFS 50 colors, symbology and methodology. In some cases this was not possible, it is therefore, most important to read the following information and ensure you have a very good understanding of the display and its intended use. If there are any questions concerning the following displays, contact the installing agency or a Bendix/King factory representative for additional information.
4.1.20
SW 06/07/08/11 Issued 4/95
Issued 4/95
EHSI Displays
1
V
O
R
1
CRS 345
030
33
N
30
24
21
S
FMS 1
200 NM
15
3
6
175
NM
150 KT
1:10
12
ADF
020°
SW 06/07/08/11
Figure 4.1.3
TYPICAL EHI 50 DISPLAY
4.1.21
Issued 4/95
EHSI Displays
V
O
R
1
CRS 120
3
6
1
HDG
E
2
1
5
1
33
30
W
24
21
VOR
4.2 NM
4.2
NM
120 KT
0:02
ADF
SW 06/07/08/11
Figure 4.1.4
LOSS OF HEADING DISPLAY
4.1.22
Issued 4/95
EHSI Displays
Wind Speed
Course/Desired
Track
Drift Angle
Bug
DG Mode
OR Source
Lubber
Line
Heading Select
Bug
Heading
Miscompare
1
Wind Vector
Course Pointer
Symbolic Aircraft
Primary
Navigation
Source
System
Annunciator
Deviation Bar
#1 System Bearing
Pointer
L
O
C
1
CRS
359
23
24
30
21
33
FDG
ADF 1
12.6 NM H
S
N
HDG
15
3
12
6
12.6
VOR 2
50.8 NM
NM
3.5
360°
G
S
Primary Navigation
Source Range
(or Held DME)
Distance
Ground Speed
(or Held DME
Frequency)
Selected MLS
Glidepath Angle
Vertical Deviation
Scale
Pointer/Source
Annunciator
Heading Select
Display
Compass Card
SW 06/07/08/11
#1 Distance
#1 System Bearing
Pointer Source
Annunciator
#2 Distance
#2 System Bearing
Pointer Source
Annunciator
Figure 4.1.5
EHSI SYMBOL DEFINITION
#2 System
Bearing Pointer
4.1.23
Issued 4/95
Primary
Navigation
Source
VOR
LOC
RNV
TCN
FMS
LOR
GPS
NAV
MLS
ADF
HOM
TST
System
Annunciator
Blank
1
2
EHSI Displays
Course Selection
CRS
DTK
AZ
BAZ
FDG
HDG1
HDG2
Range
Annunciation
N
M
1
L
O
C
1
CRS
359
23
FDG
33
N
30
24
ADF 1
12.6 NM H
21
S
3
15
6
12
VOR 2
50.8 NM
12.
6
N
M
0:06
FT
360°
G
S
Ground Speed or
DME Hold Frequency
KT
H
Time-To-Station
H:MM
VNAV
FT
AN
Selected
Glidepath
Angle
X.XX
Vertical Scale
Sources
GS
GP
VN
RMI
Annunciators
VOR
RNV
TCN
FMS
LOR
GPS
NAV
MLS
ADF
DME
Figure 4.1.6
EHSI SYMBOL DEFINITION
SW 06/07/08/11 4.1.24
Issued 4/95
WX Radar
Scan Limits
WX Radar Automatic
Range Limiting
WX Radar Mode
WX Radar Tilt Angle
WX Radar
Fault/Warning
EHSI Displays
Map To/From
Indicator
True Heading
Annunciator Courseline
1
CRS 327 TO
23
V
O
R
30
1
24
ARL
WXA
A 2.2
ANT FLT
ADF 1
33
21
T
N
S
15
3
6
36.7
NM
243 KT
0:09
40
12
360°
VORTAC Map
Symbol
Range Ring
Half Range
Distance
360 Degree
Map Compass
Course Deviation
Indicator
Course
Deviation Bar
Figure 4.1.7
EHSI MAP SYMBOL DEFINITION
SW 06/07/08/11 4.1.25
Issued 4/95
EHSI Displays
N
N
N
ON
OFF
FLT
ARL
Blank
WX
WXA
MAP
STBY
TEST
Blank
TO
FR
1
CRS 327 TO
23
R
1
V
O
30
N ON
ARL
WXA
A 2.2
ANT FLT
24
ADF 1
33
21
T
N
S
15
3
6
36.7
NM
243 KT
0:09
40
12
SW 06/07/08/11
WX FLT
WX OFF
WAIT
RANGE
STB LMT
429 FLT
ANT FLT
TX FLT
RANGE
STB OFF
Blank
BUSY VP
Figure 4.1.8
EHSI MAP SYMBOL DEFINITION
360°
LEVEL 1
Lightning cell
LEVEL 2
Lightning cell
LEVEL 3
Lightning cell
4.1.26
Issued 4/95
EHSI Displays
Arc Compass Card
Auto Tilt
Annunciator
1
CRS
23
340
33
R
1
V
O
N ON
ARL
WXA
A 2.2
ANT FLT
VOR 1
36.7 NM
N
36.7
NM
243 KT
0:09
3
90°
40
ADF 2
Off Scale
Heading Bug
Read Out
SW 06/07/08/11
To/From
Pointer
Course
Deviation
Bar
Course
Deviation
Scale
Figure 4.1.9
EHSI ARC MAP SYMBOL DEFINITION
4.1.27
Issued 4/95
EHSI Displays
SW 06/07/08/11
1
L
O
C
1
CRS
359
23
30
33
N
24
21
S
ADF 1
15
3
6
6.2
NM
117.95 H
G
S
12
360°
CAT II
VOR 2
30.8 NM
VERTICAL EXCESSIVE
DEVIATION ARROWS
CAT II ANNUNCIATION
HORIZONTAL EXCESSIVE
DEVIATION ARROWS
Figure 4.1.10
EHSI CAT II SYMBOLOGY
4.1.28
EADI Displays
EADI DISPLAYS
NORMAL ATTITUDE DISPLAY
PITCH ATTITUDE
played in the form of a hollow triangle. Refer to Figure 4.2.4.
A moving white simulated horizon line rotates angularly with the roll of the aircraft and moves up and down with the pitch of the aircraft. Blue sky above the horizon and brown ground below the horizon align with the horizon line as it follows the aircraft’s pitch and roll. Pitch scale reference marks extend above and below the horizon line indicating 5,10,
15, 20, 25, 30, 35, 40, 45, 50, 55,
60, 65, 70, 75, 80 and 90 degrees. Refer to Figure 4.2.3.
In the event of a pitch or roll attitude failure, the pitch scale, roll scale, roll index pointer, blue sky and brown ground are removed from the display. Centered just below the roll scale, a RED
“ATTITUDE FAIL” enclosed in a
RED box will be annunciated.
ROLL ATTITUDE
The roll attitude display for the
Lear 31A is a movable index (sky pointer).
❏ An optional configuration item, selected at the time of installation and certification, allows the EFS
50 to declutter nonessential navigation data in the event an unusual attitude is encountered.
Removal of the data will occur if pitch angle exceeds +30 or -20 degrees, or if bank angle exceeds 65 degrees. Red chevrons, used to indicate the best unusual attitude recovery direction (not necessarily right side up), will appear in the brown ground raster between 40 and 85 degrees, and in the blue sky raster between 50 and 85 degrees.
In the event of a pitch or roll attitude failure, the pitch scale, blue sky, brown ground and sky pointer are removed from the display.
Centered just below the roll scale a RED “ATTITUDE FAIL” enclosed in a RED box will be annunciated.
ROLL INDICATOR
The roll scale provides reference marks at 10, 20, 30, 45 and 60 degrees. To allow easier recognition of the 30, 60 and 45 degree marks, the 30 and 60 degree marks are longer extending further into the center of the display and the 45 degree mark is dis-
The sky pointer roll indicator is a white triangular pointer positioned just below the roll scale.
The pointer rotates with the pitch scale while the roll scale remains fixed.
Issued 4/95 SW 06/07/08/11 4.2.1
EADI Displays
Level Attitude able horizon. The symbolic aircraft is flown to satisfy the command cues of the flight director.
The EFS 50 offers two symbolic aircraft symbols, the Bull’s Eye and Delta. Selection of the single cue command bars will present a delta aircraft symbol, while selection on the double cue command bars will provide a traditional bull’s eye aircraft symbol.
20° Right Roll
SKY POINTER ROLL SCALE
In the event of an attitude failure, the roll indicator is removed from the display.
PERSPECTIVE LINES
❏ A display option selected at the time of installation and certification. Orange lines extending
30 and 45 degrees downward from the center of the horizon line provide additional pilot cues in steep turns. Refer to Figure
4.2.4.
Note: The display of perspective lines with the delta shaped aircraft symbol is not acceptable to some certification agencies.
SYMBOLIC AIRCRAFT
Located in the center of the display is the fixed orange aircraft symbol. The pitch and roll attitudes of the aircraft are displayed by the relationship of the fixed symbolic aircraft and the mov-
Aircraft Reference Delta
Aircraft Reference Bull’s Eye
HEADING TAPE
❏ An optional configuration item, selected at the time of installation and certification, allows a white heading tape to be fixed along the top of the horizon line. Index marks appear every 5 degrees with heading annunciation displayed every 30 degrees. The heading tape can be configured with or without a heading bug.
In the event heading data becomes unavailable or invalid, a stationary RED “HDG” enclosed in a RED box will be displayed above and to the right of the symbolic aircraft.
4.2.2
SW 06/07/08/11 Issued 4/95
EADI Displays
FLIGHT DIRECTOR
COMMAND BARS
❏ Flight director commands are displayed as moving green or magenta bars when the flight director is engaged. Located in the center of the EADI display about the fixed aircraft symbol, indicating roll and pitch required to satisfy the computed flight director commands. Deselecting the flight director or an invalid
“FD” will cause the command bars to be removed.
The flight director command bards are pilot selectable between single or dual cue via an external switch.
The single cue command bars will present a delta aircraft symbol, while selection of the double cue will provide a traditional bull’s eye aircraft symbol. Command bar color may also be configured as either green or magenta.
Single Cue Command Bars
In the event of a flight director failure, the command bars are removed and a stationary RED
FD enclosed in a RED box is displayed just below the right 60 degree roll mark.
AUTOPILOT/FLIGHT
DIRECTOR MODE
ANNUNCIATION
◗ STANDARD 429
AUTOPILOT/FLIGHT
DIRECTOR MODE
ANNUNCIATION
❏ When interfaced with the
Bendix/King KFC 3100, the EFS
50 annunciates a combination of autopilot and flight director modes. Engaged modes are annunciated in green along the top of the display and armed modes are annunciated in white just below the engaged modes.
Only “GS”, “VNAV” and “ALT” will be annunciated in white, in the
“Vertical Arm 2” field immediately below the vertical engaged mode. Only “GS” and “ALT” will be annunciated in white in the
Vertical Arm 1 field immediately below the Vertical Arm 2 field.
The engaged mode annunciations will flash for a minimum of 5 seconds when disengaged. The color of a flashing mode annunciation is green with software 06 or
0701 and yellow with software
0702 or 08.
Dual Cue Command Bars
Issued 4/95 SW 06/07/08/11 4.2.3
EADI Displays
The following table and figure describes those modes supported and location in which they may be displayed.
AP
AUTOPILOT
SR
HB
CWS
YD
LATERAL
HDG
NAV
LOC
APR
BC
ROL
AZ
BAZ
FLIGHT DIRECTOR
VERTICAL
ALT
VS
ALTC
MACH
IAS
GS
GA
PIT
VNAV
(H,L,N)CLB
(H,L,N,)DES
1
AP
YD
SR
HB
CWS
NAV
LOC
20
12555 K
T
VNAV
ALT
GS
20
F
1257
RA
Software release 06 added the following autopilot failure warning annunciations. They are listed in order of priority and will be displayed in the SR field:
• PTRM RED = pitch auto/manual trim fail
• LTRM RED = lateral autotrim fail
• PTCH RED = elevator servo failure
• ROLL RED = aileron servo failure
• YAW RED = rudder servo failure
• PITCH YELLOW = elevator mistrim
• ROLL YELLOW = aileron mistrim
4.2.4
SW 06/07/08/11 Issued 4/95
EADI Displays
If the flight director data becomes invalid, a RED “FD” enclosed in a
RED box will be displayed at the right center of the display.
If the autopilot has been on and then disengaged, a RED “AP” will be annunciated in the upper left hand corner of the display. The
RED “AP” will flash when disengaged.
Dual autopilot installations, the active side is annunciated by a green “AP” and the inactive side will be annunciated by a yellow
“AP” with a yellow arrow pointing toward the active side.
Yaw damper “YD”, if engaged, may flash RED when disconnected.
The following autopilot command reference data will be displayed in green when interfaced with the
KFC 3100:
• AIRSPEED
60 to Vmo in 1KT
• MACH increments.
.5 to Mmo in 0.005M
increments.
• VERTICAL SPEED
+/-7,000F/M in 100F/M increments.
• ALTITUDE
0 to 65536FT in 10FT increments.
• HIGH PROFILE
“H”
• NORMAL PROFILE
“N”
RADIO ALTIMETER
❏ The radio altimeter display is composed of three elements; radio altimeter (RA) height, decision height (DH) set and decision height (DH) alert. In the upper right corner of the display, a field of white alphanumeric data provides radio altimeter height and annunciation. In the lower right corner of the display, a green alphanumeric field displays the selected DH. This field is active only when the DH set knob is active or when the radio altimeter is providing valid height data. To the right and above center of the display, a yellow “DH” alert is displayed in a black box outlined in yellow.
Radio altimeter (RA) height display range is -20 to 2,500 feet.
Between -20 and 100 feet, height will be displayed in five foot increments. Above 100 feet, height will be displayed in 10 foot increments. Selection of decision height and activation of “DH” alert will be in 1 foot increments. The maximum and minimum height displayed will depend on the radio altimeter installed.
To annunciate an operational radio altimeter which has not acquired a valid ground response, three white dashes are placed in the height data field. If the radio altimeter has failed, three RED dashes are placed in the height data field. In either case, if the rising runway is displayed, it will remain fixed at the
Issued 4/95 SW 06/07/08/11 4.2.5
EADI Displays bottom of its scale and moves laterally to indicate the LOC or
MLS deviation.
DECISION HEIGHT SET
A part time green alphanumeric readout, located in the lower right corner, displays the letters DH and selected decision height in feet as manually established by the DH set control knob. With the control pulled out, the DH set value is displayed and may be set regardless of aircraft altitude.
With the control knob “in”, DH is displayed only for radio altimeter altitude less than 2500 feet AGL.
The DH set display range is from
“OFF” (-1 ft.) to the RA declutter value (2,500’). Refer to Figure
4.2.2.
DECISION HEIGHT ALERT
When the radio altimeter height is equal to or less than the selected decision height, the DH annunciator will be displayed.
When first activated, the DH annunciator will flash for 10 seconds. The DH symbol is a large yellow “DH” on a black background enclosed by a yellow box, located to the right of the pitch scale and above the horizon line when in normal attitude. Refer to
Figure 4.2.2.
PRECISION APPROACH
MODE FORMAT
The precision approach mode display is obtained by selecting an ILS or MLS navigation source.
On the ED 551A used as the
EADI, the full sky/ground display is reduced in size to provide a high contrast black background for various scales and annunciations. A rising runway symbol is provided for the display of expanded left/right deviation and runway closure during the final
200 feet of radio altimeter height.
The rising runway center line, referenced to the lateral deviation scale, will provide LOC or MLS deviation. A “LOC” or “MLS” annunciation identifies the navigation mode. A vertical scale is provided to display ILS or MLS glide path. Refer to Figure 4.2.2.
After software release 07 “LOC” or “MLS” are only annunciated when both approach sensors are installed. If only one type is installed, the lateral deviation scale will not annunciate the navigation mode.
EXPANDED LATERAL
DEVIATION SCALE
Located at the bottom center of the EADI, displayed in white, with
4 hollow circles and a center diamond is the expanded lateral deviation scale. This scale provides a reference for ILS or MLS lateral deviation. As an expanded scale, it represents 1/2 full scale deviation as displayed on the EHSI. When the selected course and aircraft heading differ by more than 105 degrees, the left/right sensitivity is reversed and a green (onside) or yellow
(offside) BC is displayed left of the center diamond to alert the
4.2.6
SW 06/07/08/11 Issued 4/95
EADI Displays pilot that back course information is being displayed. Refer to Figure 4.2.3 and 4.2.4.
Software version 07 and higher will display the expanded
LOC/MLS scale as three dots.
Note: Warning, some conventional ADI expanded ILS and
MLS displays represent 1/4 of the full scale displayed by the
HSI. The EFS 50 provides 1/2 the EHSI displayed deviation to provide better pilot interface.
RISING RUNWAY
Three configuration options are selectable at the time of installation and certification for display of the rising runway symbol.
❏ The first option provides full time display of the rising runway only when in the precision approach mode. The symbolic rising runway will be displayed in the lower center of the display just above the LOC/MLS lateral deviation scale. The center line of the symbolic rising runway represents ILS or MLS fly to command. If the radio altimeter provides height above the ground information to the EFS 50, the rising runway symbol will start increasing in size at 200 feet and will continue to increase in size to
0 feet. When the on-side ILS or
MLS is selected as the primary
NAV sensor, the rising runway will be green in color. If the offside sensor is selected, the runway will change to yellow, alerting the pilot that he has selected off-side information.
❏ A second configuration option provides for the display of a traditional deviation bar in place of the rising runway. The deviation bar will overlay the lateral deviation scale. It will not be positioned just above the deviation scale as the rising runway is.
❏ A third configuration option allows the display of the rising runway unless one of the following conditions exists, in which case the deviation bar will be displayed.
• No radio altimeter
• Radio altimeter is not being displayed, above 2,500 feet or not providing computed data
• Radio altimeter is below minimum altitude, white dashes displayed
• Radio altimeter is flagged, RED dashes displayed.
In the event the lateral deviation information becomes invalid or failed, the rising runway or D bar and lateral deviation scale are removed, the lateral deviation scale is replaced with a RED “X.”
Software version 07 replaces the
5 dot expanded localizer scale with a 3 dot expanded localizer scale whenever the rising runway is displayed.
Issued 4/95 SW 06/07/08/11 4.2.7
EADI Displays
GLIDESLOPE/VERTICAL
NAVIGATION
When the selected primary NAV sensor is ILS, MLS or LNAV with
VNAV selected, a stationary white vertical deviation scale will appear on the right or left side of the EADI display as configured at the time of installation and certification. This scale provides a reference for the vertical deviation pointer. The deviation pointer moves in relation to the scale to indicate glide path center with respect to aircraft position.
played on either the right or left side of the EADI and EHSI display.
❏ Vertical pointer annunciation for MLS can be “GS” or “GP” with software 08.
Vertical Pointer Type selected at the time of certification.
G
S
MARKER BEACON
ANNUNCIATION
When the on-side sensor is selected for display, the deviation pointer is green in color. When the off-side sensor is selected for display, the deviation pointer changes to yellow alerting the pilot that he has selected his offside nav sensor.
If the selected sensor is ILS or
MLS, a “GS” (or “GP” for MLS with SW 08) will be displayed in the pointer. “VN” will be annunciated if the selected sensor is an
LNAV with VNAV selected.
In the lower left corner, marker beacon information is displayed inside a hexagon shaped box.
The outer marker, “OM” is displayed in cyan. The middle marker, “MM” is displayed in orange.
The inner marker, “IM” is displayed in white. All three markers may be displayed simultaneously. Flashing of the marker display is also possible providing the marker receiver flashes its output.
FAST/SLOW
Additional configuration options selectable at the time of certification:
❏ Declutter GS on Back Course, allows the vertical deviation scale to be in view at all times or only when the selected course is within 105degrees of the aircraft heading.
An optional display item, selectable at the time of installation and certification. If configured, will be displayed on the opposite side of the EADI from the Glideslope scale. The scale consists of two vertical white unfilled diamonds and one white unfilled circle.
❏ Vertical Scale Side, allows the vertical deviation scale to be dis-
4.2.8
When Fast/Slow is configured, the scale and pointer will be dis-
SW 06/07/08/11 Issued 4/95
EADI Displays played when the airspeed is less than 50 knots or less than 0.45
mach from the airspeed bug selected setting. The scale and pointer will be removed when the airspeed is greater than 50 knots or 0.45 mach from the airspeed bug. The scale provides ±10 knots indication and ±13 knots full scale deflection. AS will be annunciated in the pointer.
Configuration options selectable at the time of installation and certification:
❏ Display of Fast/Slow on the display.
Three pointer styles are provided. Color will be green and the style will match the GS pointer.
If invalid or failed sensor data is received the deviation pointer and scale are removed and a
RED X annunciated.
RATE OF TURN DISPLAY
❏ An optional display item, selectable at the time of installation and certification, if configured, will be displayed at the bottom center of the EADI. The rate of turn scale is composed of three evenly spaced unfilled white rectangles. The rate of turn pointer is an equally sized white filled rectangle balanced atop a smaller white filled rectangle. A standard rate turn of 3˚ per second is indicated when the pointer is directly below the left or right rectangle.
The rate of turn indicator will not be displayed when the composite reversionary mode is selected for display.
If rate of turn data becomes invalid, the pointer and scale will be removed and replaced with a
RED “X”.
❏ Beginning with software release 0702, configuration items are provided for bank angle correction of the yaw rate gyro. This correction takes into account the aircraft roll attitude when displaying rate of turn information.
CATEGORY II
ANNUNCIATOR
Refer to Figure 4.2.7 while reviewing this section.
❏ An optional annunciator provides advisory only information, selectable at the time of installation and certification. When configured, the symbol generator will monitor the appropriate on-side and cross-side information and alert the crew when Category II requirements or limits are not satisfied.
The Category II Annunciator provides different limits for FAR and
JAR-AWO certifications.
◗ CATEGORY II OPERATION
ANNUNCIATIONS
Special requirements and equipment are required for CAT II operation.
Issued 4/95 SW 06/07/08/11 4.2.9
EADI Displays
Activation of the remote Category
II switch by the pilot will cause a yellow CAT II to be displayed on the ADI and HSI to indicate that
Category II annunciations are active. The remote Category II selection switch will be a momentary contact type for software 06 and 0701, but must be alternate action for software 0702 and 08
(or later). Category II can be activated at any time and in all normal modes of the EFS.
In the normal sequence of events, a white CAT II will be displayed on the ADI and HSI in place of the previous yellow CAT
II only when certain criteria are met:
The following requirements must be met in a four or five tube EFS system before the Category II annunciator will change to white:
1. Valid ILS or MLS #1 is selected on Symbol Generator #1.
2. Valid ILS #2 is selected on
Symbol Generator #2.
3. Valid ATT #1 is selected on
Symbol Generator #1.
4. Valid ATT #2 is selected on
Symbol Generator #2.
5. Valid HDG #1 is selected on
Symbol Generator #1.
6. Valid HDG #2 is selected on
Symbol Generator #2.
7. Pilot and copilot symbol generator are valid.
8. Both crosstalk buses are valid.
9. SG3, composite or ADI-down modes are not active.
10. Radio altitude is valid and between 2,500 feet and 50 feet.
11. True heading is not active.
12. Valid pilot flight director.
13. Pilot’s command bars in view.
14. No attitude, heading, localizer, glideslope or radio altitude miscompare flags.
15. Front course ILS or MLS approach.
16. Pilot’s flight director (if avaiable) engaged in localizer and glideslope.
Additional requirements to be added to the above criteria if applicable:
• Both pilot and copilot ILS #1 and #2 frequencies must match if known and valid.
• Both pilot and copilot MLS #1 and #2 channels must match if known and valid.
• Valid copilot flight director if configured.
• Copilot’s flight director engaged in localizer and glideslope if FD configured.
• Copilot’s command bars in view if FD configured.
With software 06 and 0701, a green CAT II will be displayed in place of the white CAT II on the
ADI and HSI when the above criteria are met and the radio altimeter is between 500 and 100 feet. An additional requirement with software 0702 and 08 is for the excessive deviation monitor to be within the configured limits before the “CAT II” annunciation color changes to green. Green
4.2.10
SW 06/07/08/11 Issued 4/95
EADI Displays excessive deviation arrows
(>> <<) will appear on the ADI and HSI localizer and glideslope scales. If the rising runway is configured for display, green chevrons will be displayed within it. Location of the excessive deviation arrows on the localizer and glideslope scales will be displayed according to the Category
II limits.
Yellow flashing arrows on the localizer scales and yellow flashing chevrons on the rising runway will be displayed if the localizer pointer exceeds the limits set by the arrows(>> <<).
Yellow flashing arrows on the glideslope scales and yellow flashing GS in the glideslope pointer will be displayed if the glideslope pointer exceeds the limits set by the arrows(>> <<).
All yellow excessive deviation symbols will flash.
White CAT II will be displayed below 100 ft., and no excessive deviation symbology will be displayed.
Yellow CAT II will be displayed below 50 ft., and no excessive deviation symbology will be displayed.
◗ CATEGORY II THRESHOLDS
The following Category II limits are for the comparison of excessive deviation and for the placement of the deviation scale arrows.
EFS
SOFTWARE
CONDITIONS
DEVIATION RADIO
ALTITUDE
APPROACH
TYPE
DEVIATION
LIMITS (
µ a)
FAR JAR old
JAR new
0601
0701
0702
0801
Localizer
Localizer
Glideslope
Glideslope
Localizer
Localizer
Glideslope
500 to 300 ft
300 to 100 ft
500 to 100 ft
500 to 100 ft
500 to 300 ft
300 to 100 ft
500 to 100 ft
AP/FD
AP/FD
AP
FD
AP/FD
AP/FD
AP/FD
35
25
35
75
35
25
75
20
20
65
25
25
75
25
25
75
75
CATEGORY II DEVIATION LIMITS
Issued 4/95 SW 06/07/08/11 4.2.11
EADI Displays
Note: FAR localizer limits will change on initial 300 feet crossing and will remain at new limits.
An additional configuration option provided with 0702 and 08 software allows CAT II operation without any deviation monitoring.
When activated, Category II deviation limit (>> <<) indicators are displayed on the glideslope and localizer scale, chevrons will also be displayed on the rising runway if it is configured for display.
ATTITUDE MONITOR
Dual channel processing of Attitude inputs provides validation of the processed displayed attitude information within the symbol generator. If a failure is detected in the processed information,
“ATTITUDE FAIL” is annunciated at the top center of the display and blue sky and brown ground information and associated attitude scales are removed.
NOTE: There is no monitor function in any reversionary mode.
CROSS COMPARATOR
ANNUNCIATORS
Refer to Figure 4.2.5 while reviewing this section.
Provides system comparison between like on-side and off-side sensors. The following list describes the associated symbology and sensors:
◗ RA
Radio altitude miscompare, a yellow RA above a double-ended arrow displayed just below the radio altitude readout in the upper right corner. This is displayed when SG 1 and SG 2 radio altitude differ by more than
8 feet at between 0 and 99 feet
AGL. The Allowable difference increases by 8 ft per 100 ft of altitude . If the off-side RA flag is different the miscompare will also be displayed.
◗ LOC
Localizer miscompare, a doubleended arrow will be displayed over the localizer deviation pointer on the EADI and EHSI when both SG 1 and SG 2 are tuned to an ILS/MLS frequency and differ by more than halfscale deviation.
◗ GS
Glideslope miscompare, a double-ended arrow will be displayed above the glideslope deviation pointer on the EADI and EHSI when both SG 1 and SG 2 are tuned to an ILS/MLS frequency and differ by more than halfscale.
◗ ATT
Attitude miscompare, a yellow double-ended arrow over “ATT” will be displayed in the top left corner of the EADI if ADI pitch 1,
2, and cross-side (if available) differ by more than 5 degrees or roll 1, 2, and cross-side (if
4.2.12
SW 06/07/08/11 Issued 4/95
EADI Displays available) differ by more than 6 degrees. The miscompare will also be displayed if the failure warning flags differ.
Note: In reversionary modes the EHSI Attitude may be used for comparison if required.
◗ HDG
Heading miscompare, a yellow double-ended arrow over “HDG” will be displayed to the left of the lubber on the EHSI and right side center of the EADI if heading 1, 2 and cross-side (if available) differ by more than 6 degrees up to 6 degrees of bank and by more than 20 degrees above 6 degrees of bank. If bank information is not available, the miscompare will be displayed if heading differs by more than 20 degrees. The miscompare will also be displayed if the failure warning flags differ. Heading miscompare will be processed in the EHSI section of the symbol generator and displayed on the
EADI if the heading tape is selected for display. Heading miscompare will not be performed if sources are not type matched (all magnetic or all true).
Note: Beginning with software
11, SG1 to SG2 comparisons of attitude, heading, and radio altitude are not performed if valid data is not available on the crosstalk bus between symbol generators. Therefore, failure of an SG in installations with both SG1 and
SG2 configured can cause miscompare annunciations only with software versions before 11.
Issued 4/95 SW 06/07/08/11 4.2.13
EADI Displays
*This page intentionally left blank.
4.2.14
SW 06/07/08/11 Issued 4/95
Issued 4/95
EADI Displays
1
N
20
10
3
10
20
10
20
20
10
6 T
SW 06/07/08/11
Figure 4.2.1
TYPICAL EADI 50 DISPLAY
4.2.15
Issued 4/95
EADI Displays
HEADING
TAPE
AP/FD MODE
ANNUNCIATORS SKY POINTER
FAST SLOW
POINTER
FAST SLOW
SCALE
DIGITAL RADAR
ALTIMETER DISPLAY
A
S
AP
YD
SR
HB
CWS
NAV
20 ı
275 K
T
VNAV
ALT
20
F
10 10
N 3 6
1257
RA
T
G
S
S
10
20
10
20
OM
LOC
DH
200
RADIO
ALTIMETER
ANN
HEADING
BUG
SELECTED
DECISION
HEIGHT
SW 06/07/08/11
LATERAL
DEVIATION BAR
LOC SCALE
Figure 4.2.2
EADI SYMBOLOGY DEFINITION
STANDARD LATERAL
DEVIATION SCALE
4.2.16
Issued 4/95
EADI Displays
SINGLE CUE
FD COMMAND
BARS
AP MODES
LATERAL
FD/AP MODE
AP COMMAND
DATA
VERTICAL FD/AP
MODES
A
S
AP
YD
SR
HB
CWS
NAV
LOC
20 ı
12555 K
T
VNAV
ALT
GS
20
F
10 10
N 3 6
10 10
S
20 20
T
1257
RA
LOC
DH
200
G
S
VERTICAL
DEVIATION
POINTER
VERTICAL
DEVIATION
SCALE
PITCH SCALE
RISING RUNWAY
LATERAL DEVIATION
EXPANDED LATERAL
DEVIATION SCALE
Figure 4.2.3
EADI SYMBOLOGY DEFINITION
SW 06/07/08/11 4.2.17
Issued 4/95
EADI Displays
SINGLE CUE
FLIGHT DIRECTOR
COMMAND BARS
A
S
AP
YD
SR
HB
CWS
NAV
LOC
20 ı
12555 K
T
VNAV
ALT
GS
20
F
10 10
N 3 6 T
1257
RA
G
S
S
IM
10
20
10
20
LOC
DH
200
HORIZON LINES
WITH HEADING
TAPE
PERSPECTIVE
LINES
SCALE
ANNUNCIATOR
SW 06/07/08/11
SINGLE CUE
DELTA AIRCRAFT
SYMBOL
EXPANDED LATERAL
DEVIATION SCALE
Figure 4.2.4
EADI SYMBOLOGY DEFINITION
4.2.18
Issued 4/95
ATTITUDE
MISCOMPARE
ATTITUDE
SELECT
FLAG
HEADING
SELECT
FLAG
MARKERS
RATE OF TURN
SCALE
LOCALIZER
MISCOMPARE
RATE OF TURN
POINTER
Figure 4.2.5
EADI SYMBOLOGY DEFINITION
SW 06/07/08/11
EADI Displays
CHECK
CONFIGURATION
MESSAGE RADIO ALTIMETER
MISCOMPARE
A
S
AP
YD
SR
HB
CWS
NAV
20 ı
275 VNAV
ALT
20
1257
RA
CHECK CONFIG
F
ATT
ATT1
N
10
3
10
6
DH
T G
S
HDG1
S
IM
OM
SG
10
20
10
20
HDG
SG 3
COPY
LOC
DH
1300
DECISION
HEIGHT ALERT
GLIDE SLOPE
MISCOMPARE
HEADING
MISCOMPARE
4.2.19
Issued 4/95
DISPLAY UNIT
FAN FLAG
CONTROL PANEL
FLAG
SG FLAG
EADI Displays
ATTITUDE FAIL
ANNUNCIATOR
AP
YD
F
SR
HB
CWS
N
A
S
S
10
CP DU
SG SG
20 ı
12555 K
T
VNAV
ALT
20 20
ATTITUDE FAIL TEST
10
3
10
6
HDG
FD
T
---
RA
G
S
10
20
LOC
DH
200
FLIGHT TEST MODE
ANNUNCIATOR
FLIGHT DIRECTOR
FAILURE
ANNUNCIATOR
HEADING FAILURE
ANNUNCIATOR
SW 06/07/08/11
SG FAN
FLAG
Figure 4.2.6
EADI FAULTS SYMBOLOGY
4.2.20
Issued 4/95
EADI Displays
CAT II RISING
RUNWAY CHEVRONS
AP LOC
33
10
20
10
20 ı
GS 100
RA
20
10
DH
N
10
20
CAT II
LOC
DH
200
G
S
VERTICAL EXCESSIVE
DEVIATION ARROWS
CAT II
ANNUNCIATOR
LATERAL EXCESSIVE
DEVIATION ARROWS
Figure 4.2.7
CAT II SYMBOLOGY
SW 06/07/08/11 4.2.21
Issued 4/95
EADI Displays
A
S
AP
YD
SR
HB
CWS
NAV
20 ı
275 K
T
VNAV
ALT
20
F
N
10
3
10
6
S
10
20
10
20
2490
RA
DH
200
SW 06/07/08/11
Figure 4.2.8
EXAMPLE EADI ENROUTE DISPLAY
WITH 08 SOFTWARE
4.2.22
Issued 4/95
EADI Displays
A
S
AP
YD
SR
HB
CWS
NAV
20 ı
275 K
T
VNAV
ALT
20
F
N
10
3
10
6
S
10
20
10
20
OM
1257
RA
LOC
DH
200
G
S
SW 06/07/08/11
Figure 4.2.9
EXAMPLE EADI APPROACH DISPLAY
WITH 08 SOFTWARE
4.2.23
COMPOSITE Displays
COMPOSITE DISPLAYS
COMPOSITE MODE
Refer to Figures 4.3.1 and 4.3.2
while reviewing this section.
In the event of a display unit or
EADI symbol generator section failure, the composite mode may be selected for display on the remaining good display unit by means of an external switch.
The base composite display utilizes the standard EADI display for its foundation. To it is added a standard lateral deviation scale, selected CRS, selected HDG, distance information, DME HOLD annunciation, selected NAV sensor and TO/FR information. Creating a composite display in this manner provides the pilot a familiar display, which requires minimal transition time when it is selected for use.
Note: The following will address only those areas of the composite display which differ from the standard EADI display.
If the EADI section of the symbol generator fails, a full composite display may be displayed on the
EHSI. If the EHSI section fails, only pitch and roll information will be displayed on the EADI.
line. Index marks appear every 5 degrees with heading annunciation displayed every 30 degrees.
In the event heading data becomes unavailable or invalid, a stationary red “HDG” will be displayed above and to the right of the symbolic aircraft.
SELECTED COURSE
Toward the bottom of the display, left of center is a green alphanumeric readout which provides a digital display of the selected course. In addition to the digital display, on the heading tape a downward pointing arrow provides a visual cue of the selected course with reference to the aircraft heading.
If the selected Primary NAV sensor is an on-side sensor the digital readout and pointer is displayed in green. If an on-side
LNAV is the selected Primary
NAV sensor and it is in the approach mode, the readout and pointer will be green. If the enroute mode is selected, the readout and pointer are cyan. If an off-side sensor is selected, the digital readout and pointer will be displayed in yellow.
HEADING TAPE
If not already configured for display, a white heading tape will be fixed along the top of the horizon
HEADING BUG SELECT
Toward the bottom of the display, right of center is an orange alphanumeric readout which provides a digital display of the
Issued 4/95 SW 06/07/08/11 4.3.1
COMPOSITE Displays selected heading. In addition to the digital display, on the heading tape is a hollow orange heading bug which provides a visual cue of the selected heading with reference to the aircraft heading.
Note: As the aircraft heading changes, the selected course pointer and heading bug will follow the heading tape and may disappear from view. The heading bug and course pointer function the same as they do in the normal mode of operation, once set they are fixed to the heading tape or compass card.
NAVIGATION SOURCE
ANNUNCIATION
A vertical three- or four-letter alphanumeric readout located on the left or right side of the display, depending on vertical scale side selection, indicates the navigation selected as the primary navigation sensor.
Green annunciations indicate an on-side approach NAV system is being displayed. Yellow indicates the cross-side system has been selected. Cyan annunciations apply to on-side nonapproach NAV systems. These color codes apply to the NAV source annunciator, CRS pointer, deviation bar, CRS, and distance.
If both sides select the same navigation source (i.e., pilot and copilot select VOR 2) a yellow box is placed around the navigation source annunciator on both sides of the cockpit.
If both sides select their respective cross-side navigation source
(i.e., pilot selects system 2, copilot selects system 1) then both
NAV source annunciators will be yellow with no yellow box.
LATERAL COURSE
DEVIATION SCALE
(Non Approach Mode)
Located at the bottom center of the EADI, displayed in white, with four hollow circles and a center diamond is the lateral deviation scale. The course deviation scale provides a reference for the course deviation bar to indicate the centerline of the selected navigation or localizer or MLS course in relation to the center diamond.
The course width displayed in the composite mode is identical to that typically shown on the EHSI.
LATERAL COURSE
DEVIATION BAR
The course deviation bar represents the centerline of the selected navigation or localizer course.
If invalid or failed primary NAV sensor data is received the course deviation bar and scale are removed and a RED X annunciated.
4.3.2
SW 06/07/08/11 Issued 4/95
COMPOSITE Displays
Beginning with software 11, the deviation bar and scale are decluttered when lateral deviation information is provided in
ARINC 429 format with a status of No Computed Data (NCD).
The red “X” is still displayed for invalid or missing data.
TO/FROM
Displayed left of the center diamond on the lateral deviation scale, a white “TO” or “FR” will provide TO/FROM information when in non-ILS or non-MLS modes.
DISTANCE INFORMATION
An alphanumeric readout, located in the lower left corner, annunciates distance in nautical miles from the aircraft to the selected primary NAV station when in the
VOR, TACAN, ILS or MLS mode, or to the waypoint in the LNAV or
RNAV mode.
DME HOLD
When DME HOLD is selected, the DME distance and annunciator color will change to white and will remain white until the HOLD function is released. The sensor identifier (ADF, VOR, ILS, etc ) shall retain the original assigned color. The HOLD function is additionally annunciated by an orange letter “H” displayed immediately to the right of the distance information. Ground speed and time-to-station are not displayed while DME HOLD is active
Once the DME is placed in
HOLD, its distance will continue to be displayed and will not be affected when the primary NAV sensor is changed.
DME HOLD will not function when MLS, LNAV or RNAV is the selected sensor. In this situation the associated distance field is always used to display waypoint or MLS distance.
Issued 4/95 SW 06/07/08/11 4.3.3
COMPOSITE Displays
*This page intentionally left blank.
4.3.4
SW 06/07/08/11 Issued 4/95
Issued 4/95
COMPOSITE Displays ı
20
10
20
10
R
1
V
O
33
175 NM
N
10 10
20
CRS
355
TO
20
HDG
020
3
SW 06/07/08/11
Figure 4.3.1
COMPOSITE ENROUTE MODE DISPLAY
4.3.5
Issued 4/95
COMPOSITE Displays
COURSE
POINTER
PRIMARY
NAVIGATION
SENSOR
DME/LNAV
DISTANCE ı
20
10
C
1
L
O
175 NM
IM
33
10
20
CRS
355
N
20
10
10
20
HDG
020
3
100
RA
G
S
HEADING
BUG
SW 06/07/08/11
SELECTED
COURSE
SELECTED
HEADING
Figure 4.3.2
COMPOSITE APPROACH MODE DISPLAY
4.3.6
MFD Displays
MFD DISPLAYS
The MFD’s primary purpose is to provide weather radar and/or
LNAV moving map information.
In addition to providing the traditional display functionality, the
EFS 50 MFD also has the ability to function as an independent
EHSI if the system is configured to provide such functionality.
In such cases, the information displayed on the MFD follows the same basic display format as the
EHSI. Therefore this section will only address those areas of the
MFD that differ from the EHSI.
Refer to the figures at the end of this section.
CCRRSS
, CRS NOT SELECT
When the MFD course select knob is not active, a bar the color of the CRS annunciator will be placed above it. This will alert the pilot that the MFD CRS knob is not active and the MFD’s course annunciator is referenced to the pilot’s EHSI selected course.
Example: CCRRSS 135
WEATHER ONLY
❏ A configuration option available at the time of installation and certification, provides a traditional weather radar indicator display.
Unlike most conventional EFIS weather radar displays this display will not present any non weather related information. All navigation information is
Issued 4/95 removed, leaving a clean weather presentation consisting of four cyan range rings and white radar annunciations located in the lower left corner.
Weather radar mode, warnings and failure annunciations are displayed as they are on the normal
EHSI ARC Weather mode.
◗ TRACK LINE
A yellow dashed line drawn from the center of the symbolic aircraft to the compass card or outer range ring. Activated and slewed by pressing one of the TRK buttons. Pressing the VP button will activate VP at the location of the
Track Line. In the upper left corner a yellow digital readout displays the present position of the track line. Once the track line has remained stationary for 15 seconds it will be decluttered.
VERTICAL PROFILE (VP)
◗ SYMBOLIC AIRCRAFT
When the VP mode is selected for display, the symbolic aircraft is centered on the left edge of the display.
◗ RANGE RINGS
Four evenly spaced vertical cyan range rings are displayed during
VP. At the bottom of each range ring, a cyan distance number is displayed annunciating it’s range.
SW 06/07/08/11 4.4.1
MFD Displays
◗ ALTITUDE LINE
Three horizontal altitude lines are present on the VP display. The center line is off the nose (bore line) of the symbolic aircraft, representing the actual aircraft’s present altitude. Equally spaced above and below the 0 foot center line are two altitude lines a certain number feet above and below the aircraft. The number associated with these lines varies with the selected range to compensate for the radar beam width at the various ranges.
◗ PROFILE ANGLE
In the upper left corner “PRO-
FILE” is displayed annunciating that the VP mode is selected.
Just below it, the present azimuth angle being sliced is displayed as
L (left) or R (right) followed by a number. “R6” would represent a
VP slice being performed at 6 degrees right of the aircraft nose.
◗ PLAN-VIEW,
NORTH-UP MAP
❏ Beginning with software 07
Plan-View is an option selectable at the time of installation. The
Plan-View North-Up map mode provides a display in which a symbolic aircraft shows the actual aircraft’s position relative to the
LNAV flight plan route. As the actual aircraft progresses along the flight plan route or deviates from it, the symbolic aircraft likewise progresses along or deviates from the flight plan depiction on the indicator. Range is depicted by the dashed white full scale range ring and dashed light blue half scale range ring. When the
Plan-View is first entered, the symbolic aircraft is positioned in the center of the display. As the actual aircraft moves, the symbolic aircraft will move about the display and may move off screen. If this occurs, the symbolic aircraft can be brought back onto the screen in any of three ways. One is by pressing the enter button. This will reposition the symbolic aircraft at the center of the display. Another method is to use the joystick to change the lat/long of the center of the screen (see Joystick operation in
Section 2.4, MFD Operation). A third method is to select a greater range scale.
NOTE: Enter and joystick functions are only available on the
CP 469A.
The Plan-View, always displayed as a true north map, aids in flight planning and aircraft position awareness. Weather radar, lightning and other navigation information are not available in Plan-
View mode.
To display the Plan-View, an
LNAV with an active valid flight plan must be selected as the primary navigation source and be providing valid magnetic variation. The current FROM waypoint and the next 14 waypoints on the flight plan may be displayed. As defined for the normal NAV Map, the pilot may elect to display either the closest navaids or airports along with the first five flight plan waypoints.
4.4.2
SW 06/07/08/11 Issued 4/95
MFD Displays
TCAS INTERFACE
❏ With software 08 and higher a configuration option available at the time of installation and certification, provides a TCAS ONLY traffic display on the MFD. A
“TRAFFIC” message is provided for the pilot and co-pilot EHSI displays during an active TA or RA, but intruder traffic will not be shown on these displays, only the MFD.
NOTE: In some installations
TCAS “TRAFFIC” and status advisories may not be displayed on the EHSI’s.
Range control will be retained by the CP 469A MFD control panel.
Above/norm/below and actual/ relative altitude selections will be made on the TCAS control panel.
Resolution advisory (RA) information such as a climb arrow will not be shown on the MFD. RA traffic will be displayed with
TCAS II, but not TCAS I.
Whenever a normal operating mode that does not display
TCAS traffic information is selected on an MFD display , “TRAF-
FIC” will be annunciated to indicate that a TA or RA is in progress. This annunciation will remain on non-TCAS displays as long as at least one TA or RA is active.
All RA, TA, and PROXIMATE
TRAFFIC will be displayed on the
MFD when TCAS is configured and TCAS ONLY is selected, regardless of display format and altitude limits. OTHER TRAFFIC within the selected altitude limits will also be displayed when possible. The EFS 40/50 will display up to 20 TCAS intruders on the
MFD.
◗ TCAS ONLY SELECTION
With EFS software 08 and later, a dedicated TCAS select push button on the CP 469A MFD
Control Panel labeled “TCAS
ONLY” will provide 360° TCAS
ONLY (range = 5 nm) on the
MFD with a single selection. This momentary switch will alternately select TCAS ONLY and last display mode. The last display mode will be restored exactly, including previous range and map format.
TCAS and checklist are mutually exclusive modes that will cancel each other such that only the most recently selected will be active.
Default conditions at selection:
360° format
5 NM range
All intruders displayed
(20 max.)
Operation while selected:
Ranges available: 2, 5, 10, 20,
40 NM
360° format only
TST/REF, NAV, RMI 1, RMI 2,
ENT, JOYSTICK and 1/2 buttons are inactive
De-selection:
The dedicated TCAS ONLY select always returns to the last display mode.
Issued 4/95 SW 06/07/08/11 4.4.3
MFD Displays
◗ TCAS DISPLAY FORMAT
TCAS ONLY display will be 360° format and normally contain the following elements:
* Small cyan symbolic aircraft symbol located in the center of the 360° TCAS ONLY display.
* Two NM range ring consisting of cyan dots positioned every
30 degrees to represent the 12 clock positions is presented on
5 NM and 10 NM ranges only.
* Full range ring consisting of cyan radial tick marks positioned every 30 degrees to represent the 12 clock positions plus intervening cyan dots every 10 degrees.
* Map type half range ring (white dashes) without range annunciation on 20 NM and 40 NM ranges.
* “TCAS” annunciation in vertical field in place of nav source.
* TCAS mode annunciation.
* TCAS range annunciation.
* Up to two no-bearing intruder messages.
* Above/norm/below annunciation.
* Actual intruder altitude and
(FLXXX) annunciation when appropriate.
* TCAS traffic symbols (intruder, data tag, and vertical speed arrow).
◗ TCAS TRAFFIC SYMBOLOGY
Each intruder symbol will be accompanied by a data tag and, when appropriate, a vertical speed arrow. The data tag and arrow will be the same color as the intruder symbol that they are associated with. The intruder symbol, data tag, and vertical speed arrow will appear the same size regardless of range selection.
Intruder Symbols
+02
-01 -03 - 0 5
RA TA PROXIMATE OTHER
TCAS INTRUDER SYMBOLS
NOTE: RA traffic is not provided with TCAS I.
Traffic generating a Resolution
Advisory (RA) will be displayed as solid red squares. Traffic generating a Traffic Advisory (TA) will be displayed as solid yellow circles. Proximate traffic will be displayed as solid white diamonds. All other, no threat traffic will be displayed as hollow (outline only) white diamonds.
Intruder symbols are centered on the actual intruder location.
Vertical Speed Arrow
The vertical speed arrow will be positioned immediately to the right of the intruder symbol when the intruder vertical trend is climb or descend as reported by the
TCAS processor. The arrow will point up for climbing traffic and down for descending traffic.
Data Tag
The data tag will normally consist of a + or - followed by two digits of altitude difference (relative alti-
4.4.4
SW 06/07/08/11 Issued 4/95
MFD Displays tude) in hundreds of feet between the intruder and own aircraft. (+ = intruder above own aircraft) During selection of actual altitude, and with a valid source of own altitude provided by the TCAS processor, the data tag will consist of three digits representing hundreds of feet above
MSL. Actual altitudes below sea level will be displayed as two digits preceded by a minus sign.
The data tag will be centered on the intruder symbol and positioned above it when the intruder is above own aircraft. The data tag will be positioned below the intruder symbol when the intruder is below own aircraft. The relative altitude data tag for intruders at the same altitude as own aircraft will consist of “00” without a
+ or - sign and be positioned to indicate the intruder’s most recent altitude deviation from own aircraft. When no altitude trend information is available, the
“00” is positioned below the traffic symbol.
◗ TCAS DISPLAY
ANNUNCIATIONS
Traffic
During an active RA or TA, a
“TRAFFIC” message will be annunciated in large text on the
MFD and EHSI. The “TRAFFIC” message will not be displayed on the MFD if the MFD is in TCAS
ONLY format. This annunciation will be provided for all normal operating modes, but not while maintenance or configuration pages are displayed. “TRAFFIC” will be red during an active RA and yellow during an active TA
(an RA has priority over a TA).
This annunciation will not be made while TCAS is selected for display. Beginning with software
0802,the “TRAFFIC” mesage will be replaced by a "NO TCAS" message for 15 seconds following a TCAS failure or a change of
TCAS mode to Standby.
NOTE: In some installations a remote annunciator may be installed to provide full time
TCAS operational status.
Off-Scale Traffic
RA and TA traffic that is located beyond the selected range of a
TCAS display will be shown as one half of the appropriate intruder symbol located on the outer edge of the displayed area at the proper bearing. A data tag and/or vertical speed arrow associated with this intruder will retain its normal position relative to the intruder symbol and only that portion (if any) within the normal display area will be visible.
TCAS
TCAS ONLY format will include a cyan “TCAS” displayed in the vertical field where the selected navigation source is normally displayed in other modes.
Issued 4/95 SW 06/07/08/11 4.4.5
MFD Displays
TCAS Status
TCAS mode, range, above/norm/below selection, and actual altitude
(FL) selection will be presented in the bottom right corner of the display normally used for the RMI 2 pointer annunciations. FLxxx and
ABV/BLW are both provided in the same five character field when specific conditions are satisfied as shown in the following table.
CONDITIONS TCAS ANNUNCIATION
ABOVE
BELOW
SELECT
REL/FL
ALT
SELECT
Valid
Altitude provided
Normal
Above
Below
X
Normal
Above
Below
Relative
Relative
Relative
FL
FL
FL
FL
X
X
X
YES
NO
NO
NO
TA/RA
(7)
TA/RA
TA
ONLY
(6)
TA
TA/RA
ABV
TA/RA
BLW
TA/RA
FL123
TA/RA
FL
TA/RA
FLABV
TA/RA
FLBLW
TA
ABV
TA
BLW
TA
FL123
TA
FL
TA
FLABV
TA
FLBLW
TCAS
STBY
(5)
TCAS MODES
(Display priority)
NO
TCAS
(4)
TCAS
FAIL
(3)
TCAS
STBY
TCAS
STBY
TCAS
STBY
TCAS
STBY
TCAS
STBY
TCAS
STBY
TCAS
STBY
NO
TCAS
NO
TCAS
NO
TCAS
NO
TCAS
NO
TCAS
NO
TCAS
NO
TCAS
TCAS
FAIL
TCAS
FAIL
TCAS
FAIL
TCAS
FAIL
TCAS
FAIL
TCAS
FAIL
TCAS
FAIL
TD FAIL
(2)
TD
FAIL
TD
FAIL
TD
FAIL
TD
FAIL
TD
FAIL
TD
FAIL
TD
FAIL
TCAS
TEST
(1)
TCAS
TEST
TCAS
TEST
TCAS
TEST
TCAS
TEST
TCAS
TEST
TCAS
TEST
TCAS
TEST
ANNUNCIATION COLOR
X = Doesn't matter.
* ** CYAN CYAN YEL YEL CYAN
*TA/RA will be cyan. FL 123 will be white when a valid altitude is available, otherwise FL will be yellow.
ABV and BLW will be cyan.
**TA (for TA ONLY mode) will be yellow during an active TA and cyan otherwise. FL123 will be white
when a valid altitude is available, otherwise FL will be yellow. ABV and BLW will be cyan.
TCAS STATUS ANNUNCIATIONS
TCAS Mode
TEST - Indicates that the TCAS processor is performing system test.
TD FAIL - Indicates that the capability of the EFS to properly display TCAS traffic is suspect.
TCAS FAIL - Indicates that the
TCAS processor (or a TCAS antenna) has failed.
NO TCAS - Indicates that a
TCAS system component
(other than TCAS processor and TCAS antenna) has failed.
TCAS STBY - Indicates that
TCAS has been intentionally placed in standby mode.
TA - Indicates that TA ONLY mode has been entered by the
TCAS processor. When displayed, the annunciation color will be yellow if any intruder is
4.4.6
SW 06/07/08/11 Issued 4/95
MFD Displays a Traffic Advisory (TA). The color will be cyan when there are no intruders classified as a
TA. TCAS I installations will indicate TA during normal operation.
TA/RA - Indicates normal operation for TCAS II. This annunciation will not appear when
TCAS I is installed.
Above/Norm/Below
All TCAS displays will annunciate a cyan “ABV” or “BLW” when above or below respectively are selected on the TCAS controller.
Neither annunciation is provided when normal is selected. This same three character field is also used to present own aircraft altitude when actual altitude (FL) is selected. The FL annunciation has priority over ABV and BLW.
No-Bearing Traffic
Range
Range is annunciated in cyan without an alpha prefix immediately to the left of the TCAS status information. The ranges available are 2, 5, 10, 20 and 40 NM.
Range Rings
• Full range ring consisting of cyan radial tick marks positioned every 30 degrees to represent the 12 clock positions plus intervening cyan dots every 10 degrees.
• If range is less than 20 NM, a two NM range ring consisting of cyan dots positioned every 30 degrees to represent the 12 clock positions.
• If range is greater than 10 NM, a standard map half range ring with no range annunciation.
• If range is 2 NM, the outer range ring is replaced with the 2
NM range ring consisting of 12 dots (and no tic marks) around the circle.
During any TCAS display, up to two no-bearing traffic messages may be required. The format for these messages is “TA 5.7NM/-
06
≠
” or “RA 0.8NM/+01
≠
” where -
06 and +01 are the relative altitudes of the intruder aircraft.
Relative altitudes (including the + or - sign) will be replaced by a 3 digit actual altitude in hundreds of feet whenever the conditions for display of actual altitude have been satisfied. RA messages will be red and TA messages will be yellow. The vertical speed arrow, when climb or descend is indicated, will be displayed immediately to the right of the altitude digits.
FLXXX and FL
A white FLXXX is annunciated only when actual intruder altitude
(FL) is being displayed. This annunciation will be absent when relative intruder altitudes are displayed. XXX will be own aircraft actual altitude in hundreds of feet as provided. This annunciation
Issued 4/95 SW 06/07/08/11 4.4.7
MFD Displays will be “FL” (without the three digit number) in yellow when actual altitude has been selected but a valid source of own aircraft actual altitude is not provided by the TCAS processor. Negative actual altitudes will be displayed as two digits preceded by a negative sign. (FL-XX)
NOTE: At the time of this publication TCAS display in conjunction with other display formats was not certified.
Weather/Lightning
Annunciations
All weather and/or lightning annunciations will be located in the lower left or lower right
(depending on configuration) corner of the display in the same location as non-TCAS displays.
CHECKLIST INTERFACE
In software 08 and higher a configuration option available at the time of installation and certification, provides Checklist display capability on the MFD. Checklist functions are controlled via the
CP 469A, MFD Control Panel, buttons and joystick.
The user entered checklist data is organized in a simple page-oriented format with a programmable index function which allows quick access to the checklist entries. The index operates from user entered title descriptions and relative page numbers which provides maximum flexibility in organizing and titling the index items. It is also possible to create hierarchies of indices when desired. An additional capability is provided to allow invocation of emergency checklists through discrete signals applied on the rear connector.
Any index or checklist page list can be mapped to any of the eight emergency page inputs allowing a high degree of freedom in defining and organizing the operation of programmed field units. In addition to being able to program the index and emergency page operation, it is also possible to program the colors used for the text fields, title lines, and cursor lines for any indexed list.
All pages are organized as twelve lines of 32 characters each for a total of 384 characters per page. The CP 469A will store a minimum of 800 checklist pages and 400 note pages.
Since the actual storage requirements vary according to the complexity of the pages themselves, the actual storage capacity will vary upward from this minimum.
The upper limit for both checklist pages and note pages is fixed at
1024 each.
◗ LOADING AND MODIFYING
CHECKLIST DATA
The user may load the CP 469A with predefined checklist data generated on an IBM™ compatible laptop PC using DEU (Data
Entry Utility) software on a 3.5
inch disk, KPN 222-00337-xxxx, provided with the CP 469A. This disk contains a “read me” file with
4.4.8
SW 06/07/08/11 Issued 4/95
MFD Displays
NOTICE
THE USER IS SOLELY
RESPONSIBLE FOR
CHECKLIST CONTENT more detailed information on generating and modifying checklist and note pages. The PC must have DOS version 3.0 or greater and should have at least
512 Kbytes of free RAM. A cable, KPN 155-02794-0002 is required to load the checklist data from the PC to the CP 469A via RS 232. Checklist data in the
CP 469A can also be downloaded from the CP 469A to the PC where it may be modified and then re-loaded back into the CP
469A. User programmable note pages can also be modified with the use of the PC.
◗ CHECKLIST PAGE
ORGANIZATION
Available colors are red, green, blue, cyan, magenta, yellow, and white. Black is reserved. On all index and checklist pages, the first two columns of characters are reserved for the cursor and checkoff status. A graphical cursor will move from item to item to let the user know which line the cursor is on. In addition, the color of the line with the cursor may change. A special character will be displayed in the first reserved column to indicate the checked status of a line. A blank will indicate that nothing within the sub-tree has been checked off, or that there is no element to be checked off. A star symbol will indicate that a list or sub-tree is partially checked off. A check mark will be displayed when all checklist items within a sub-tree have been checked off. These conditions may also involve a color change on the line.
The following sections describe the checklist pages. For a description of how the user moves from page to page, refer to the CONTROLS section.
◗ ROOT INDEX PAGE
Refer to figure 4.4.6. Upon selecting checklist for display, the
CP 469A will transmit a ‘root’ index page to the EFS symbol generator for display. This ‘root’ page will include disclaimer text that states the user is responsible for the content and maintenance of data within the checklist. It will also contain user-supplied text to describe the checklist, to be used as a means to identify the source/creator/version of the checklist stored in CP 469A memory. In addition to the title and disclaimer lines, the root page will have index entries of two types: user-defined, and fixed.
The fixed entries will include a
NOTES entry which allows access to the note page sub-tree, and another entry, CLEAR ALL
CHECKLIST ITEMS, which allows the user to clear all checked items in the entire tree.
These entries will always be present on the root tree, and will fol-
Issued 4/95 SW 06/07/08/11 4.4.9
MFD Displays low any user-defined index entries. The user is not required to have any NOTE pages, but the index entry will always be present.
The user-defined index entries may point to sub-index pages, or directly to a checklist. The user is free to name these entries, and to determine their organization.
Typically, the first entry on the root page would be ‘EMERGEN-
CY PROCEDURES’, but the user is free to provide another organization. At least 4 such user-defined index entries will be provided on the root index page.
The initial cursor position will always be at the first index entry in the root page. The cursor will be restricted to the six index entry lines.
The user will be able to specify the color of the top title lines, the color of each of the four userassigned index items, the color of the cursor line, and the colors that each of the user-assigned index lines change to when all items in the sub-tree have been checked off or when a portion of them have been checked off.
The color of the other lines are fixed.
◗ SUB INDEX PAGES
Starting with the pointers associated with the root index page, sub-index pages can be created.
These sub-index pages, or simply index pages, can have entries which point to either a list of checklist pages, or to another index page. Within a given level, the user can chain index pages together. For example, starting at one of the index entries on the root page, the user can create a collection of N index pages trailing off the entry on the root.
Each index entry on the N index pages can in turn point to another list of sub-index pages (or a list of checklist pages). The index pages form a hierarchy which can be nested arbitrarily deeply (subject to memory constraints).
Each index page consists of a title line with relative page number indication, and up to eleven index entry lines. These index entries may span more than a single line, but may not cross page boundaries. As with the root index page, the first two character columns are reserved.
The user can select the color of the title line, and the color of each of the index entry lines. In addition, the color of the cursor line, the color of partially-completed items, and the color of fully-checked items can be specified.
◗ CHECKLIST ITEM PAGES
Refer to figure 4.4.7. At the bottom of the checklist ‘tree’ are the checklist page lists. These pages contain individual checklist checkoff items. The items on these pages are either checked or unchecked.
The contents of checklist pages
4.4.10
SW 06/07/08/11 Issued 4/95
MFD Displays is similar in format to the index pages, but with some important differences. The title line consists of title text and a relative page number indication, as with the index pages. The checklist item portion consists of eleven lines of text, with the first two character columns reserved like the index pages. A checklist entry can span more than one line, but cannot span across checklist pages.
The user may specify the color of the title line, the color of the cursor line, the color of the checked items, and the color of the unchecked items. Note that this implies that the unchecked color of each item cannot be selected separately. This helps to avoid color confusion within a checklist page. Also, each item is either checked or unchecked, so no partially-completed checklist items apply.
◗ NOTE PAGES
A separate portion of CP469A memory is reserved for the entry of data for reference by the flight crew, and can be modified separately from the checklist page data. The note page portion of memory will normally be small, allowing a quick update from the
PC to that portion of checklist memory.
The DEU utility running on a PC is used to create note pages similar to the way the checklist is created. The NOTES entry on the root index page points to an index page listing entries for note page lists, or other note page index pages. Index pages in the note-page sub-tree are formatted just like regular index pages, except that the indicators for completed/partially completed lists will never appear. Only the cursor will appear in the first two character columns. The note pages themselves are similar in appearance to the checklist pages. They have a title line with relative page numbering, and 11 lines of text.
The user may select the color of the note page title line, the color of the text on the page, and the color of the cursor line.
◗ CLEARING CHECKLIST ITEMS
There are two ways to quickly return all checklist items to the unchecked state. The first is to remove power from the CP 469A for more than 15 seconds. The second is to move the cursor over the CLEAR ALL CHECKED
ITEMS on the root index page, and press the ENTER key. This will cause a warning page to be displayed, with instructions on what to do to clear all the checked items.
The ENTER key can be used to uncheck individual checklist items by placing the cursor on a checked item and then pressing
ENT.
◗ EMERGENCY PAGE
ACTIVATION
The CP 469A provides eight pri-
Issued 4/95 SW 06/07/08/11 4.4.11
MFD Displays oritized discrete lines for emergency page use. Using the PC, the user can bind these active low inputs to specific checklist pages, which can be tailored to the nature of the emergency discrete. Any discretes which are not bound using the PC will be ignored by the CP 469A.
Whenever one of these inputs goes low while checklist mode is active, the checklist unit will automatically display an emergency summary page listing all currently active emergencies, and the title of the list that the emergency is bound to. The user may select the emergency of choice, and press the ENTER button. Control is then transferred directly to the emergency list desired. As soon as the user checks off all items associated with a given active emergency, the checklist unit will again display the emergency summary page, showing that emergency condition as checked-off. This allows the user to know when all the checklist items associated with an emergency have been checked off, and allows an easy way to proceed to the next active emergency, if one exists.
If an emergency discrete activation is detected by the CP 469A while the checklist mode is not active, a yellow “C-L EMER” message will be displayed on the
MFD. When the user presses the CHK LIST button to activate the checklist mode, the checklist unit will display the emergency summary page as described above. This provides the pilot/copilot with an easy means to determine the source of the emergency discrete (the name of the checklist it is tied to will appear on the emergency summary page) and to proceed to check off the items associated with that emergency. Once all the items associated with a given emergency are checked off, the checklist unit will consider that emergency ‘handled’, and will remove the request for the “C-L
EMER” message. However, if a given emergency discrete is reapplied after all items associated with that emergency have been checked off, the checklist unit will again notify the user that a given emergency has re-occurred via the emergency summary page.
The CRS/SEL button can be pressed to display the emergency summary page any time the checklist mode is active. A second press of the CRS/SEL button at this time, returns the previously displayed checklist page.
While the emergency summary page is displayed, the 1-2 key can be used to display a list of all the emergencies that were mapped to an emergency discrete.
◗ CHECKLIST CONTROLS
Checklist: CHKLIST
Selecting the CHKLIST button activates and deactivates the checklist function and causes the information to be displayed on the MFD. The checklist will
4.4.12
SW 06/07/08/11 Issued 4/95
MFD Displays provide approximately 800 pages of normal, abnormal, and emergency data.
Joystick
The joystick can be moved side to side, up and down, and to the
45 degree points. The 45 degree points will be ignored in checklist mode.Joystick position data will be transmitted continually to the
EFS MFD for use in MAP processing, and will be used by the
CP 469A processor to enable movement through checklist pages (when the CP 469A is in checklist mode).
A downward push on the joystick will cause the cursor to move down one line or item in the checklist. The line down operation advances from one index/item page to the next, and wraps within one level. Holding the joystick down continuously will cause the cursor to slew down.
An upward push on the joystick will cause the cursor to move up one line or item in the checklist.
The line up operation advances from one index/item page to the previous page, and wraps within one level of pages. Holding the joystick up continuously will cause the cursor to slew up.
A rightward push on the joystick will cause the cursor to go to the top of the next page. The next page operation applies only within a single level, and wraps to the first page within a level. For example, a rightward push while on the last page of a list of checklist pages will move the cursor to the top of the first page in the list.
Holding the joystick right continuously will cause the cursor to slew forward through the pages.
An leftward push on the joystick will cause the cursor to proceed to the top of the currently selected page, and subsequent leftward pushes will move the cursor to the top of the preceding pages.
Paging is within a single level, and wrapping from the first to the last page within a level will be supported. Holding the joystick left continuously will cause the cursor to slew through the pages in reverse.
Enter : ENT
The state of the ENT key is continually transmitted to the EFS for
MAP processing use, and is also used by the CP 469A for checklist purposes.
When in the checklist mode, the enter button will behave differently depending on where in the checklist the cursor is located.
The general behavior of the
ENTER key is to enable the pilot to check off everything in the checklist by using the ENTER key alone. In the checklist pages, pressing enter on an unchecked item will cause the cursor to check off that item and proceed to the next unchecked item in the list. If no unchecked items exist between the cursor position and the end of the list of item pages,
Issued 4/95 SW 06/07/08/11 4.4.13
MFD Displays the cursor is placed on the first unchecked index entry of the parent index list. If no unchecked index entries exist at that level, the search continues up the checklist tree until an uncompleted index entry is found, or until the cursor reaches the root index page. If the item is checked off and the enter button is depressed, the line will be unchecked and the cursor will remain at the line just unchecked.
When on an index page, pressing the enter button will cause the cursor to move to the next unchecked item or index entry it finds. If the entry is not fully completed, the cursor is moved to the next lower level, and parked on the first uncompleted item/entry on that level. If the index entry that the cursor is on is already fully checked-off, the cursor first searches the current list of index pages for an unchecked index entry, and then searches all the layers of index pages upward, toward the root index page, always looking for an incomplete checklist. If all items are checked off, the cursor moves to the top of the root index page.
On the root index page when the cursor is on the “CLEAR ALL
CHECKED ITEMS”, pressing the enter button will cause a warning page to come up asking for verification that the pilot truly wants to clear all checked items. An additional push on this screen will cause all checked items to be cleared.
HSI
The HSI button will not function while the checklist is active.
ARC
The ARC button will not function while the checklist is active.
NAV
The NAV button will not function while the checklist is active.
Up Arrow
When in checklist mode, an uparrow (range-up) push will serve to move the cursor up the ‘checklist tree’. That is, if the cursor is on a checklist page, a range up will move the cursor to the index page entry used to access that list. When the cursor is positioned over an index page entry, the cursor will move to the index page and entry from which the current index entry is accessed.
A range up push on the root index page has no effect, since no higher level exists to go to.
Down Arrow
When in checklist mode, the down arrow (range down) will move the cursor down the
‘checklist tree’ by moving the cursor into the branch accessed through any index page entry. A range down push while the cursor is on a item page has no effect, since there are no ‘lower’ levels to go to.
4.4.14
SW 06/07/08/11 Issued 4/95
MFD Displays
1-2
When checklist mode is active, the 1-2 key normally will not be active. However, if the active emergency summary page is currently displayed, the 1-2 key will cause the checklist unit to display an informational page listing all currently ‘bound’ emergency discretes. This page lists all eight emergency discretes, and the title of the checklist page that each was bound to using the
DEU utility software.
RMI 1
The RMI 1 button will not function while the checklist is active.
CRS (NOT) SEL
When in checklist mode, the
CRS(NOT) button will cause the checklist unit to display the list of active emergencies. A second press returns the previous display.
TST REF
When in checklist mode, the TST
REF button will cause the checklist unit to display a ‘canned’ help page. This help page can be used by the pilot/copilot to remind them what button combinations are used in checklist mode. This help page will appear as follows:
RMI 2
The RMI 2 button will not function while the checklist is active.
CRS Knob
The CRS knob will not function while the checklist is active.
CHECKLIST KEYSTROKE OPERATIONS
JOYSTICK UP:
JOYSTICK DOWN:
JOYSTICK LEFT:
JOYSTICK RIGHT:
UP ONE ITEM
DOWN ONE ITEM
PREVIOUS PAGE
NEXT PAGE
RANGE UP:
RANGE DOWN:
ENTER:
CRS/SEL:
UP ONE LEVEL
DOWN ONE LEVEL
CHECK-OFF ITEM
ACTIVE EMERGENCY
PRESS TST/REF TO EXIT HELP
Issued 4/95 SW 06/07/08/11 4.4.15
MFD Displays
*This page intentionally left blank.
4.4.16
SW 06/07/08/11 Issued 4/95
Issued 4/95
MFD Displays
NOT CRS SELECT
ANNUNCIATION
ARC COMPASS
CARD
AUTO TILT
ANNUNCIATOR ı
CRS
23
340
33
V
O
R
1
ARL
WXA
A 2.2
ANT FLT
VOR 1
36.7 NM
N
36.7
NM
243 KT
0:09
3
90°
40
ADF 2
OFF SCALE
HEADING BUG
READOUT
SW 06/07/08/11
TO/FROM
POINTER
COURSE
DEVIATION
BAR
COURSE
DEVIATION
SCALE
Figure 4.4.1
MFD ARC COMPASS + WX SYMBOL DEFINITION
4.4.17
Issued 4/95
TRACK LINE
RADAR MODE
STBY
2
.2
MFD Displays
L 25
TRACK LINE
LOCATION
ANNUNCIATION ı
40
SELECTED RANGE
RANGE RINGS
20
SW 06/07/08/11
TILT ANGLE
SYMBOLIC AIRCRAFT
Figure 4.4.2
MFD WEATHER ONLY DISPLAY
4.4.18
Issued 4/95
MFD Displays
PROFILE
ANGLE
SYMBOLIC
AIRCRAFT
WEATHER
MODE ı
PROFILE
R
WX
5
10
15 20
+30
0
-30
ALTITUDE
LINES
RANGE
RINGS
Figure 4.4.3
MFD VP DISPLAY
SW 06/07/08/11 4.4.19
Issued 4/95
MFD Displays
TRACK LINE
LOCATION
SYMBOLIC
AIRCRAFT
TRACK LINE (INDICATES
AZIMUTH OF VERTICAL SLICE) ı
L12
40
30
20
10
-20
WXA
↑ 10
+60
10
20 30
0
40
-60
TILT LINE
(INDICATES TILT
OF HORIZONTAL
SLICE)
ALTITUDE
LINES
SW 06/07/08/11
Figure 4.4.4
MFD SPLIT SCREEN DISPLAY
(NOTE: SW 11 and later)
4.4.20
Issued 4/95
MFD Displays
LNAV MESSAGE
ANNUNCIATION
PLAN VIEW
MODE ANNUNCIATION
PLAN
T ı
TRUE NORTH
ANNUNCIATION
N
PRIMARY
NAVIGATION
SOURCE
MSG
F
M
S
5
IXDA
WAYPOINT
SYMBOL
OJC
“NORTH-UP”
ANNUNCIATION
FLIGHT PLAN
DESIRED TRACK
LINE
SW 06/07/08/11
AIRPORT
SYMBOL
SYMBOLIC AIRCRAFT
(PRESENT POSITION)
VORTAC SYMBOL
Figure 4.4.5
MFD PLAN VIEW DISPLAY
CENTER OF MAP
DISPLAY
FULL SCALE
RANGE RING
HALF SCALE
RANGE RING
4.4.21
Issued 4/95
MFD Displays
2 NM
RANGE
RING
DISPLAY
MODE
A
S
T
C
NO BEARING
INTRUDERS
RA0.8NM/+01 ı
TA5.7NM/-06
-03 +02
-05
-01
10
TA/RA
FL ABV
TCAS
RANGE
ACTUAL/RELATIVE
ALTITUDE SELECTION
ABOVE/NORM/BELOW
ALTITUDE SELECTION
Figure 4.4.6
TCAS ONLY DISPLAY
SW 06/07/08/11
OTHER
TRAFFIC
PROXIMATE
INTRUDER
TA
INTRUDER
RA
INTRUDER
(TCAS II ONLY)
TCAS MODE
SELECTION
(TA/RA - TCAS II ONLY)
4.4.22
Issued 4/95
MFD Displays
USER CREATED
GENERAL USE LINES
FIXED TEXT LINES (YELLOW)
USER CAN NOT CHANGE
TST/REF BUTTON BRINGS
UP HELP PAGE
CHECKED OFF
INDEX ENTRY
PARTIALLY
CHECKED OFF
INDEX ENTRY
CURSOR LOCATION ı
TITLE
CREATOR/VERSION DATA LINE
USER/INSTALLER IS RESPONSIBLE
FOR THE CHECKLIST CONTENTS
TST/REF-HELP
✓ EMERGENCY PROCEDURES
* NORMAL PROCEDURES
➩ ABNORMAL PROCEDURES
OTHER PROCEDURES
NOTE PAGES
CLEAR ALL CHECKED ITEMS
SW 06/07/08/11
Figure 4.4.7
MFD CHECKLIST ROOT INDEX PAGE DEFINITION
4.4.23
Issued 4/95
MFD Displays ı
TAXI
✓ 1.
✓ 2.
✓ 3.
➩ 4.
5.
6.
BRAKES
FLIGHT INSTRUMENTS
NAV EQUIPMENT
ELECTRICAL POWER
MONITOR
ENGINE INSTRUMENTS
THRUST REVERSERS
7.
CHECK
CHECK
SET
CHECK
CHECK
CHECK AND STOWED
ANTI ICE SYSTEMS
CHECK AS REQD
SW 06/07/08/11
Figure 4.4.8
MFD CHECKLIST SAMPLE PAGE
4.4.24
Operating Instructions
OPERATING INSTRUCTIONS
Consult Aircraft Flight Manual
Supplement for specific procedures and limitations in operation.
PREFLIGHT PROCEDURES
◗ START UP should be serviced. Refer to figure 5.1 and 5.2, Self Test annunciation. Additionally, the pilot should ensure that the compass scale is white, which indicates that all three colors are operational in the display unit.
At engine start, power should not be applied to the EHI 50 system, low voltage may turn the EFS 50 system off momentarily, and transient voltages may induce premature failures. With engines operating, turn on avionics master switches, and turn on NAV systems to remove the EHSI flags.
Note: Performing the EFS 50
Self Test is not required at anytime. If a failure was to occur or exist, the small RED
SG in a red box would be displayed. This test is intended to familiarize the pilot with the various flagging methodology used and a quick check for proper color presentation.
When power is initially applied to the EFS 50 system, various flags maybe annunciated on the display, representing systems not yet operational.
◗ SELF TEST
Adjust BRT control on the
EFS 50 CP 467, and CP 469 for the desired brightness.
The EADI self test page will automatically revert to a normal EADI display.
❏ Software 07 and later will also cause the EHSI to automatically revert from the selftest page to normal operation.
◗ PUSH BUTTON TEST
After a short warm-up time, press and hold the TST/REF button for three seconds to display the
SELF TEST. A SELF TEST
PASS or SELF TEST FAIL message will be annunciated. If the system is operating properly the
SELF TEST PASS message will be annunciated. If a malfunction exists, SELF TEST FAIL will be annunciated and the system
Check each push button function on the EFS 50 control panel.
Push button operation should be as described in 2.1 EHSI Operation, 2.2 EADI Operation, 2.3
RADAR Operation, and 2.4 MFD
Operation.
PRE-TAKEOFF
PROCEDURES
After the system test has been completed, select the desired Pri-
Issued 4/95 SW 06/07/08/11 5.1
Operating Instructions mary NAV sensor with the NAV source select push button. Set the desired course and heading, and check that the appropriate display is present on the indicator. Set the desired NAV frequencies for the departure phase of the flight. Then press the appropriate push buttons (HSI, ARC,
BEARING #1, BEARING #2, etc.) on the EFS 50 control panel for the desired display presentation.
IN-FLIGHT OPERATION
Select the desired type of NAV sensor for the primary NAV display by pressing the NAV push button until the desired source is annunciated.
Select NAV system #1 (left) or #2
(right) by pressing the 1-2 push button.
Select HSI or ARC display by pressing either the HSI or the
ARC push button.
Select the display mode (map and/or weather radar) by sequential presses of the HSI or ARC push button.
Use HEADING SELECT (SYNC or HDG) or COURSE SELECT
(DIR or CRS) knobs to select the desired heading or course.
On the CP 467 control panel, the heading and course knobs may be used to 1) rapidly acquire the
DIRECT TO course to the station
(pull DIR knob), or 2) center the heading bug under the lubber line (pull SYNC knob).
Use the #1 and #2 BEARING
POINTER SELECT push buttons to select the sensor desired by pressing the push button until the desired source is annunciated.
These push buttons are also used to display independent
DME information without a bearing pointer.
◗ ADF
After selecting ADF mode and tuning ADF #1 receiver to the desired NDB, set Bearing pointer
#1 to ADF which will be used for primary navigation. Using CRS control, select desired course TO or FROM the NDB. The course deviation bar on the EHSI now provides left-right guidance in flying the selected course just as it would in flying a VOR course.
This eliminates the mental calculations required while tracking an
NDB course in the conventional manner. NDB station passage is indicated by the TO-FROM indicator and Bearing pointer reversal. The ADF may become invalid during station passage, a
RED X will be displayed in place of the deviation scale and D-Bar.
Note: ADF D-Bar presentation may not be available if the
ADF does not provide a suitable flag output.
◗ LNAV (RNAV)
After selecting LNAV mode and the desired waypoint, set Bearing
5.2
SW 06/07/08/11 Issued 4/95
Operating Instructions
Pointer #1 to the desired #1 bearing source. Using CRS knob, select desired course TO or FROM the waypoint (for the on-side LNAV only). The course deviation bar on the EHSI now provides guidance in flying the selected course. Waypoint passage is indicated by the TO-
FROM indicator and waypoint
BEARING pointer reversal.
Note: Wind vector and speed information is presented if supplied by ancillary equipment and only if the system was configured to display the information during installation.
Once the external LNAV system transmits to the EFS 50 that it is in an enroute mode, the EHSI and system sensitivity is set at
5NM left or right of course for fullscale CDI deflection.
Note: Depending on the type of
LNAV installed, the Lateral
Deviation Scale may be different and may support only DTK.
◗ VNAV
VNAV operation greatly depends on the type of VNAV installed. It is therefore very important to refer to the Aircraft Flight Manual
Supplement and VNAV operation manual for additional information.
APPROACH PROCEDURES
◗ ILS APPROACH
On the CP 467 or CP 469 , select
VOR as the Primary NAV sensor with the NAV push button. Then tune the appropriate ILS frequency. Note on the EHSI that when an ILS frequency is selected
LOC replaces the VOR annunciation, the glideslope scale is displayed, and as the glide slope and localizer scales appear on the EADI the sky/ ground raster is reduced in size to provide a high-contrast background for them. Once an ILS frequency is selected, the Bearing pointer and
TO-FROM indicator associated with that NAV disappears.
When DME Hold is selected on the DME control panel, DME distance is displayed in white.
Groundspeed or Time-To-Station is replaced with the held VOR frequency followed by an orange
H for HOLD. (DME groundspeed and VOR frequency may not be displayed in all installations.)
◗ BACK COURSE APPROACH
An option may be selected at the time of installation and certification to automatically declutter GS information when the aircraft heading is greater than + or - 105 degrees from selected ILS course. EHSI NAV MAP CDI sensing is reversed and “BC” is annunciated below the deviation scale. EADI CDI sensing is reversed and “BC” is displayed to the left of the center diamond.
Not all installations will declutter the glideslope scale. This is a display configuration option selected at the time of installation.
Issued 4/95 SW 06/07/08/11 5.3
Operating Instructions
◗ ADF APPROACH
After selecting ADF mode and tuning ADF #1 receiver to the desired NDB, set Bearing pointer
#1 to ADF which will be used for primary navigation. Using CRS control, select desired course TO or FROM the NDB. The course deviation bar on the EHSI now provides left-right guidance in flying the selected course as it would in flying a VOR course.
This eliminates the mental calculations required while tracking an
NDB course in the conventional manner. NDB station passage is indicated by the TO-FROM indicator and Bearing pointer reversal. The ADF may become invalid during station passage, a
RED X will be displayed in place of the deviation scale and D-Bar.
Note: ADF D-Bar presentation may not be available if the
ADF does not provide a suitable flag output.
◗ LNAV (RNAV) APPROACH
After selecting LNAV mode and the desired waypoint, set Bearing
Pointer #1 to the desired #1 bearing sensor. If the installed
LNAV supports selected course from the EFS 50, use the CRS knob to select desired course TO or FROM the waypoint. The course deviation bar on the EHSI now provides guidance in flying the selected course. Waypoint passage is indicated by the TO-
FROM indicator and waypoint
Bearing pointer reversal.
Once the external LNAV system transmits to the EFS 50 that it is in an approach mode, the cyan colors turn green on the EHSI and system sensitivity increases to 1.25 NM left or right for fullscale CDI deflection. Cross-side annunciation remains yellow, but the increased sensitivity is implemented if the cross-side LNAV is in Approach Approved mode.
Note: Depending on the type of
LNAV installed, the Lateral
Deviation Scale may be different and may only support DTK.
◗ VOR APPROACH
After selecting NAV mode and tuning the VOR receiver to the desired frequency, set Bearing
Pointer #1 to VOR #1. Using
CRS control, select desired course TO or FROM the VOR station. The course deviation bar on the EHSI now provides guidance in flying the selected course. VOR passage is indicated by the TO-FROM indicator and Bearing pointer reversal.
◗ DECISION HEIGHT
SELECTION
Pull the DH set knob on the
CP 467 to activate the DH set display on the EADI. Adjust the
DH set knob to select the desired decision height for the particular approach. Push the DH set knob in, the select DH will be decluttered until the radar altimeter becomes valid at or below 2500 feet.
5.4
SW 06/07/08/11 Issued 4/95
LIMITATIONS
For information on EFS 50 system operating limitations please refer to the approved Flight Manual Supplement for the particular aircraft in question, if one is provided.
EMERGENCY
PROCEDURES
For information on EFS 50 system emergency procedures please refer to the approved
Flight Manual Supplement for the particular aircraft in question, if one is provided.
Operating Instructions
Issued 4/95 SW 06/07/08/11 5.5
Operating Instructions
*This page intentionally left blank.
5.6
SW 06/07/08/11 Issued 4/95
Issued 4/95
Operating Instructions
1
T
S
T
1
CRS 360 HDG
30
33
SG
N
3
CHECK CONFIG
6
24
RCP
SELF TEST PASS
12
21
S
15
ADF 1
DUSG
VOR 2
--NM
SW 06/07/08/11
Figure 5.1
EHSI SELF TEST
5.7
Issued 4/95
Operating Instructions
1
CHECK CONFIG
T
S
T
1
CP DU
SG SG
ATTITUDE FAIL
ATT
HDG
FD
CRS
360
HDG
360
DH
OFF
SW 06/07/08/11
Figure 5.2
EADI SELF TEST
5.8
Fault Annunciations
FAULT ANNUNCIATIONS
GENERAL
EXTERNAL SYSTEM FAILURES
◗ HEADING system is inhibited. Refer to Figure 6.2 and 6.3.
Once a heading failure is detected, the EHSI lubber line and course pointer head and tail are removed. The lubber line is replaced by a RED box with a
RED HDG inside it. The course deviation scale is frozen horizontally to perform the function of a conventional CDI. Selected course reference is provided by the alphanumeric CRS readout in the upper left corner. If heading was configured for display on
EADI horizon line, a RED box with a RED HDG inside it will be displayed upper left of center.
During a heading failure the automatic Back Course function normally performed by the EFS 50
◗ ATTITUDE
Once an Attitude failure is detected, the pitch scale, roll scale, sky pointer, horizon line, heading tape, blue sky and brown ground are removed from the display. A
RED box with a red “ATTITUDE
FAIL” inside it is displayed on a black background in the upper center of the display.
◗ FLIGHT DIRECTOR
Once a Flight Director failure is detected a RED box with a red
“FD” inside it will be displayed on the upper right side of the EADI.
Refer to Figure 6.3, EADI Faults.
EFS 50 SYSTEM FAILURES
◗ DU—DISPLAY UNIT LOSS
OF COOLING
A yellow DU enclosed in a yellow box is annunciated at the bottom left center of the EHSI or bottom left of the EADI when insufficient airflow is detected in the Display
Unit. Once annunciated, the faulty Display Unit will continue to operate for at least 30 minutes if the rated ambient temperature is not exceeded. To extend the operating time, reduce display information and brightness to a minimum. Refer to Figure 6.1
and 6.3.
◗ SG—SYMBOL GENERATOR
LOSS OF COOLING
A yellow SG enclosed by a yellow box is annunciated at the bottom right center of the EHSI and bottom left of the EADI if insufficient airflow is detected in
Issued 4/95 SW 06/07/08/11 6.1
Fault Annunciations the Symbol Generator. Once annunciated, the Symbol Generator will continue to operate for at least 30 minutes if the rated ambient temperature is not exceeded. To extend the operating time, reduce display information and brightness to a minimum. Refer to Figure 6.1 and
6.3.
◗ CP—CONTROL PANEL
(CP 467 OR CP 469/A)
A RED CP enclosed by a RED box is annunciated left center of the EHSI and lower left of the
EADI if a control panel switch becomes stuck for greater than
10 seconds. If a switch fails the display should maintain all currently selected conditions. If the switch should become functional the fault annunciation will be removed and normal operation will be restored. Refer to Figure
6.1 and 6.3.
There are two possible MFD control panel faults that can be displayed on the MFD. One fault is the normal red CP fault caused by a mode line failure. The second fault is a red CCP fault caused by a failure in the checklist control panel processing. The faults to be detected by the CP
469A to cause this annunciator include the following:
1.CPU test failure
2.ROM test failure
3.RAM test failure
4.Stuck joystick or control panel key
5. Invalid data in checklist/notes
EPROM (checksum failure). This fault condition applies only if the
EPROM chip is NOT completely erased. That is, if the checksum test on EPROM chip data fails because the chip is erased, a
CCP fault should NOT be raised.
This is because the CP469A will come from the factory with the
EPROM chips erased, and it is undesirable for the product to show a fault straight out of the box. Only if at least one of the bits in the EPROM are programmed, and the EPROM checksum test fails will a CCP fault be generated.
◗ HEADING SELECT “BUG”
A RED X will be drawn through the heading bug if there is a heading select knob failure on the EFS 50 control panel. Refer to Figure 6.2.
◗ COURSE SELECT
A RED X will be drawn through the course pointer head and tail if there is a course select knob failure on the EFS 50 control panel.
Refer to Figure 6.2.
◗ RCP—RADAR CONTROL
PANEL (if equipped)
A RED RCP enclosed by a RED box is annunciated at the lower left center of the EHSI display if a radar control panel failure is detected. Refer to Figure 6.1.
6.2
SW 06/07/08/11 Issued 4/95
Fault Annunciations
◗ SG—SYMBOL GENERATOR
A RED SG enclosed by a RED box is annunciated at the upper left center of the EHSI or lower left of the EADI if certain monitored functions are detected invalid. If the RED SG annunciation is encountered extreme caution should be used to validate any data used on the display for navigation. Even after validation and revalidation the data should only be used as supplementary information.
A large RED “SG” appearing on a black back display annunciates a Symbol Generator failure which would result in processed data that is unusable for navigation.
Refer to Figure 6.1 and 6.3.
RAW DATA DEVIATION
ANNUNCIATIONS
Pointer/Scale malfunctions are annunciated by removal of the associated pointer/scale and placing a RED X drawn in their place. A flag presented on the vertical deviation scale will result in the deviation pointer being removed. On the EHSI, the pointer/scale annunciations include L/R deviation, GS or VN and fore/aft in Doppler and homing mode. On the EADI, the scale annunciations include L/R deviation and GS or VN. Refer to figure 6.1 for display presentations showing these annunciations.
◗ BEARING POINTER
ANNUNCIATIONS
Bearing pointer source failure or invalid data reception (No Computed Data, NCD) causes a RED
X to be drawn through the source annunciator. The bearing pointer or NAVAID symbol is also removed.
◗ ALPHANUMERIC READOUT
ANNUNCIATIONS
Failures affecting alphanumeric readouts are annunciated by a
RED X drawn through the readout. On the EHSI (figure 6.1), the alphanumeric readouts include
NAV bearing pointer source and course (CRS) or desired track
(DTK).
Failures affecting distance information are annunciated by RED dashes in the data field. When the Distance Source is operational but not providing valid distance data (no lock on or NCD) dashes the color of the sensor will be placed in the data field.
Speed (KT) and time (MN) annunciation will be removed if valid distance, speed and timeto-station information is not provided by the primary NAV sensor system.
Failures affecting radio altimeter information are annunciated by
RED dashes in the data field on the EADI. When the radio altimeter source is operational but not providing valid data (no lock on or NCD) white dashes
Issued 4/95 SW 06/07/08/11 6.3
Fault Annunciations will be placed in the data field.
Refer to Figure 6.3.
◗ CHECK CONFIG
A yellow “CHECK CONFIG” message will display in the upper right corner of the EHSI and
EADI whenever the system configuration memory in the symbol generator and aircraft installation rack do not match.
Test routines resident in the symbol generator select the best possible system configuration to use, however, the selected configuration may not be the intended one.
Once the CHECK CONFIG message is noted, extreme caution should be exercised when using any information. It is also most important that the aircraft be taken to an authorized dealer for repair as soon possible.
WEATHER RADAR
ANNUNCIATIONS
When a weather radar failure occurs while operating in the WX mode, a white alphanumeric annunciation appears below the
Weather Mode annunciation.
The annunciations capable of being displayed when interfaced with an RDS 81, 82/VP, 84/VP and 86/VP are listed below in order of priority.
◗ WX FLT
Advises a mismatch of mode, tilt, gain or range information between the EFIS and radar RT has existed for more than 30 seconds.
◗ WX OFF
This annunciation (“OFF” before
SW 08) is displayed when the radar is off.
◗ BUSY VP
Displayed when the radar is in the continuous VP mode.
◗ STB LMT
Displayed when the combination of tilt, roll, roll trim and pitch exceeds +/- 30 degrees.
◗ 429 FLT
Displayed when 429 control data is missing or incorrect at the radar RT.
◗ ANT FLT
Displayed when the measured antenna tilt does not match the requested tilt angle.
◗ TX FLT
Displayed when a fault is detected in the radar transmitter.
◗ RANGE
Displayed when the pilot has selected the 1000 mile range on the EFIS. The radar is unable to operate at this range and is placed in standby.
6.4
SW 06/07/08/11 Issued 4/95
Issued 4/95 SW 06/07/08/11
Fault Annunciations
❏ Installation with an RDS 81,
RDS 82 or RDS 82VP with software 07 or later, “RANGE” will annunciate when the 5 NM, 320
NM or 1000 NM range is selected.
❏ Installation with software 06
“WX FLT” (weather fault) will annunciate when the 5 NM or
320 NM range is selected.
These annunciations alert the pilot of a range mismatch because the RDS 81, RDS 82 and RDS 82VP do not support these radar ranges.
◗ STB OFF
Displayed when stab off has been selected or when the stabilization reference is not present at the radar.
◗ WAIT
Displayed when in VP mode and one of the TRACK buttons is pressed, indicating the radar will perform the desired slicing function as soon as the antenna returns to the last selected profiling azimuth angle.
◗ TCAS FAULT MESSAGES
The TCAS ONLY display on an
MFD will be replaced with up to six yellow fault messages. During this tie the annunciated TCAS status will be either “TCAS FAIL” or “NO TCAS” as appropriate.
Except for the status annunciation and fault messages, the display will be completely black.
The fault messages are listed in order of priority with the highest first. TCAS FAIL messages have priority over NO TCAS messages, however both can be displayed simultaneously (up to six total).
Note: The following is a complete list of all TCAS II faults that the EFIS will display, however some of these are not applicable to TCAS I and will not be generated by a TCAS I processor. Refer to the TCAS
Pilot's Guide for more information.
Note: In some installations a remote annunciator may be installed to provide full time
TCAS operational status.
Fault Messages for
TCAS FAIL:
PROCESSOR
UPPER ANTENNA
LOWER ANTENNA
Fault Messages for
NO TCAS:
RADIO ALT 1/2
RADIO ALT 1
RADIO ALT 2
XPDR 1/2
XPDR 1
XPDR 2
ATTITUDE
HEADING
RA DISPLAY 1/2
RA DISPLAY 1
RA DISPLAY 2
XPDR UPPER ANT
XPDR LOWER ANT
TCAS TO XPDR
CP TO XPDR
ALT 1/2 TO XPDR
ALT 1 TO XPDR
ALT 2 TO XPDR
6.5
Fault Annunciations
*This page intentionally left blank.
6.6
SW 06/07/08/11 Issued 4/95
Issued 4/95
Fault Annunciations ı
L
O
C
1
CRS 360
30
33
SG
N
24
21
RCP
CP
S
3
15
6
12
ADF1 DU SG
---NM
045°
VOR 2
16.3
NM
SW 06/07/08/11
Figure 6.1
EHSI FAULT ANNUNCIATION
6.7
Issued 4/95
Fault Annunciations ı
L
O
C
1
CRS 360
33
HDG
N
30
24
21
S
3
15
ADF 1
6
12
---NM
DME1
11.
5
VOR 2
16.3
NM
045°
SW 06/07/08/11
Figure 6.2
EHSI FAULT ANNUNCIATION
6.8
Issued 4/95
Fault Annunciations
A
N
AP
YD
F ı
SR
HB
CWS
N
NAV
APR
12555 K
T
20
ATTITUDE FAIL
VNAV
ALT
GS
20
TEST
---
RA
CHECK CONFIG
10
3
10
6
HDG
FD
T
G
S
10
S
DME1
10
CP DU
SG SG
20 20
LOC
DH
200
SW 06/07/08/11
Figure 6.3
EADI FAULTS
6.9
REVERSIONARY Modes
REVERSIONARY MODES
The EFS 50 provides four different reversionary modes of operation in the event of a system component failure; composite, display down and SG 3. The reversionary modes offered in a particular aircraft will vary depending on EFIS system configuration, installation wiring and certification. The following section describes the various reversionary modes offered.
All external switches and placards are part of the installation supplied by the installer. For information pertaining to a particular aircraft installation refer to the approved Aircraft Flight Manual Supplement.
Note: This Pilot’s Guide refers to the left of the aircraft as the
Pilot’s position. The right side is considered the copilot’s position.
Issued 4/95 SW 06/07/08/11 7.1
REVERSIONARY Modes
CMPST - COMPOSITE
Refer to Figure 7.1 ,
COMPOSITE MODE
SELECTION.
CMPST (composite) is generally used to compensate for a failure of a display unit or the EADI section of the symbol generator. A single switch input to the SG 465 instructs the symbol generator to output the CMPST display on the
EADI and EHSI. See section 4.3
for details on the composite display.
EADI
CMPST
DISP
EHSI
CMPST
DISP
EFS CONTROL PANEL
CMPST
DISP
7.2
E
A
D
I
/
M
F
D
/
E
H
S
I
E
A
D
I
SYMBOL
GENERATOR
Figure 7.1
COMPOSITE MODE SELECTION
SW 06/07/08/11 Issued 4/95
REVERSIONARY Modes
DISPLAY (EADI) DOWN
Refer to Figure 7.2,
EADI DOWN MODE
SELECTION.
DISPLAY (ADI) DOWN mode selection is generally used to compensate for a failure of the
EADI display unit or section of the symbol generator. Available for use in two, three, four and five-tube installations. The DIS-
PLAY DOWN mode will allow the pilot or copilot to transfer the normal EADI display to the EHSI below the failed EADI and transfer the EHSI display to the MFD if one is installed. A single momentary switch input removes power from the failed EADI, transfers the EFIS control panel control to the MFD symbol generator, instructs the EHSI symbol section to calculate EADI function and the MFD symbol generator to calculate matching EHSI functions.
BLANK
EHSI
EADI
EADI
EFS CONTROL PANEL
SYMBOL
GENERATOR
#1
E
A
D
I
28 VDC
AIRCRAFT
POWER
OPEN
/
M
F
D
E
H
S
I
/
E
A
D
I
RDR CONTROL PANEL
EFS CONTROL PANEL
E
A
D
I
/
M
F
D
E
H
S
I
/
E
A
D
I
SYMBOL
GENERATOR
#2 (3)
Issued 4/95
Figure 7.2
DISPLAY (EADI) DOWN MODE SELECTION
SW 06/07/08/11 7.3
REVERSIONARY Modes
SG 3
Refer to Figure 7.3
PILOT STBY MODE
SELECTION.
SG 3 mode selection is generally used to compensate for a failed pilot’s or copilot’s symbol generator. The SG 3 mode selection will allow the pilot or copilot to substitute the MFD symbol generator for his onside symbol generator. A single momentary switch input removes the failed onside symbol generator drive from the EADI and EHSI and transfers the MFD display drive to the onside EADI and EHSI.
Also, the MFD control panel input is removed from the MFD symbol generator as the EFIS control panel output is switched in. The
MFD symbol generator is now performing normal onside EADI and EHSI functions (inputs and outputs). To alert the pilot or copilot that the SG 3 mode of operation has been selected, a yellow “SG 3” will be annunciated in the lower right corner of the
EADI and EHSI.
EADI
STBY
EHSI
EHSI
STBY
EFS CONTROL PANEL STBY
EFS CONTROL PANEL
RDR CONTROL PANEL
SYMBOL
GENERATOR
#1
E
A
D
I
/
M
F
D
E
H
S
I
/
E
A
D
I
VIDE0
7.4
VIDE0
Figure 7.3
PILOT SG 3 SELECTION
SW 06/07/08/11
VIDE0
E
A
D
I
/
M
F
D
E
H
S
I
/
E
A
D
I
SYMBOL
GENERATOR
#3
Issued 4/95
GLOSSARY
ABBREVIATIONS
ABV
ADF
ADS
ADI
AHRS
AHS
AN
ANT
ARINC
ATR
ATT
AZ
BAZ
BC
BLW
BRG
Above
Automatic Direction Finder
Air Data System
Attitude Director Indicator
Attitude Heading Reference System
Attitude Heading System
Angle
Antenna
Aeronautical Radio INCorporated
Air Transport Radio
Attitude
Azimuth
Back Azimuth
Back Course
Below
Bearing
BRT
CCP`
CDI
CDU
Bright
Checklist Control Panel
Course Deviation Indicator or Course
Deviation Information
Control Display Unit
CONFIG Configuration
CP Control Panel
CRS
CRT
D-BAR
Course
Cathode Ray Tube
Deviation Bar
DEG
DEV
DG
DIR
DME
Degree(s)
Deviation
Directional Gyro
Direct
Distance Measuring Equipment
DTK
DU
EADI
ED
Desired Track
Display Unit
Electronic Attitude Direction Indicator
Electronic Display
EFS or EFIS Electronic Flight Instrument System
EHI
EHSI
FHDG
FL
FLT
FMS
Electronic Horizontal Situation Indicator
Electronic Horizontal Situation Indicator
Free Directional Gyro (heading)
Flight Level (Pressure altitude)
Fault
Flight Management System
Issued 4/95 SW 06/07/08/11
Glossary
8.1
Glossary
OMG
RA
RCP
REF
RMI
RNAV
SG
SN
STB
STBY
SW
SYNC
TA
TACAN
TCAS
TCN
TD
TST
TTS
TTW
ILS
IRU
KTS
LMT
LNAV
LOR
MLS
NAV
NM
OBI
FPL
FR
FT
GP
GPS
GS
HDG
HSI
ICAO
ID
Flight Plan
From
Feet
Glidepath (used with MLS)
Global Positioning System
Ground Speed or Glideslope
Heading
Horizontal Situation Indicator
International Civil Aviation Organization
Identification
Instrument Landing System
Inertial Reference Unit
Knots (nautical miles per hour)
Limit
Long-range NAVigation
Loran
Microwave Landing System
Navigation
Nautical Mile
Omni-Bearing Indicator
Omega
Resolution Advisory/Radio Altimeter
Radar Control Panel
Reference
Radio Magnetic Indicator
Area NAVigation
Symbol Generator
Sensitivity
Stabilization
Standby
Software
Synchronization
Traffic Advisory
Tactical Air Navigation
Traffic alert and Collision Avoidance System
TACAN, Tactical Air Navigation
Traffic Display
Test
Time-To-Station
Time-to-Waypoint
TX
VNAV
Transmitter
Vertical Navigation
VOR VHF Omni Range
VORTAC VOR and TACAN co-located
VP Vertical Profile
WX
WXA
Weather
Weather Alert
8.2
SW 06/07/08/11 Issued 4/95
Index
INDEX
A
ADF
ADF 1 1.6, 1.10, 1.14, 2.1.6-7, 5.2, 5.4
ADF 2 1.6, 1.10, 1.14, 2.1.7
ALPHANUMERIC READOUT ANNUNCIATIONS 6.3
AN I.1, 1.1, 1.3, 2.1.3-10, 2.2.1, 2.3.1, 2.3.3, 2.3.6, 2.4.1-6, 4.1.1-2, 4-20,
4.2.1-3, 4.2.5-6, 4.2.8-12, 4.3.1-3, 4.4.1-3, 5, 7-8, 11-14, 5.2-4, 6.1,
6.4-5, 8.1
ANT FLT 6.4
APPROACH PROCEDURES 5.3
ARC
ARC NAV MAP 2.1.4
ARC SECTORED MODE SELECTION 2.1.3
ATT 1.8, 1.13, 1.16, 4.2.10, 4.2.12, 8.1
ATTITUDE 1.6, 1.10, 1.14, 4.1.1, 4.2.1-2, 4.2.6, 4.2.10, 4.2.12, 6.1, 6.5, 8.1
AUTO TILT 2.3.6, 4.1.17
B
BACK COURSE
BC 1.8, 1.12, 1.16, 4.1.14, 4.2.6, 5.3, 8.1
BEARING
#1 BEARING POINTER 4.1.8
#2 BEARING POINTER 4.1.8, 5.2
1-2 PUSH BUTTON 2.4.3, 2.4.6, 4.1.2, 5.2
BEARING POINTER 2.1.6-7, 4.1.5-10, 4.1.14-15, 4.1.18-19, 5.2-4, 6.3
BEARING POINTER ANNUNCIATIONS 6.3
BEARING POINTER SELECT 2.1.6, 5.2
BRT KNOB 2.1.10, 2.2.1
BUSY VP 6.4
C
CATEGORY II 4.2.9-11
CHECK CONFIG 6.4
CHECKLIST
CHECKLIST INTERFACE 4.4.8
COMMAND BARS 1.8, 1.13, 1.16, 4.2.2-3, 4.2.10
COMPASS CARD 4.1.1, 4.1.3, 4.1.9-10, 4.1.13-15,, 4.1.17, 4.3.2, 4.4.1
COMPOSITE 4.2.9-10, 4.3.1-4, 7.1-2
COURSE DEVIATION INDICATOR 4.1.14, 4.1.20, 8.1
COURSE SELECT
COURSE SELECT KNOB 2.1.10, 2.4.3-4, 4.1.3-4, 4.4.1, 6.2
CRS 1.8, 1.13, 1.16-17, 2.4.4, 4.1.2-4, 4.3.1-2, 4.4.1, 4.4.12, 4.4.15, 5.2-4,
6.1, 6.3, 8.1
Issued 4/95 SW 06/07/08/11 9.1
Index
CRS KNOB 2.4.4, 4.1.4, 4.4.1, 4.4.15, 5.3-4
CP 466A I.1, 1.1, 2.1.1, 2.3.3, 2.3.6
CP 466B I.1, 1.2, 2.3.3, 2.3.6
CP 468 2.1.1, 2.1.10, 2.4.2
CP 469A I.1, 1.1, 2.4.1, 2.4.5-6, 4.4.3, 4.4.8-9, 4.4.11-13, 6.2
D
DETAILED OPERATING CONTROLS 2.1.1, 2.2.1
DG 1.8, 1.12, 1.16, 2.1.3, 4.1.1, 8.1
DIRECT TO 1.3, 2.1.10, 5.2
DISPLAY BRIGHTNESS CONTROL 2.1.10, 2.2.1
DISTANCE, GROUNDSPEED AND TIME-TO-STATION 4.1.5
DME
DME HOLD 4.1.6-8, 4.3.1, 4.3.3, 5.3
DRIFT ANGLE POINTER 4.1.2, 4.1.12
DTK 2.4.4, 4.1.3-4, 5.3-4, 6.3, 8.1
E
EMERGENCY PROCEDURES 4.4.9, 5.5
EXTERNAL SYSTEM FAILURES 6.1
F
FAULT ANNUNCIATIONS 6.1-6
FR 4.1.14, 4.3.1, 4.3.3, 8.2
FREE DG 4.1.1
FROM 1.5, 2.1.5, 2.2.2, 2.3.6, 2.4.2, 2.4.4-5, 4.1.4-5, 4.1.7-8, 4.1.10,
4.1.12-16, 4.1.18, 4.1.20, 4.2.1-2, 4.2.6, 4.2.8-9, 4.3.1-3, 4.4.1-2,
4.4.5, 4.4.8-9, 4.4.11, 4.4.13-14, 5.1-4, 6.1-2, 7.3-4, 8.2
FT 4.1.11, 4.2.6, 4.2.11-12, 8.2
FULL TIME LNAV MAP 4.1.18-19
G
GAIN 2.3.4, 2.3.6, 4.1.17, 6.4
GLIDESLOPE
GS 1.8, 1.12, 1.16, 4.1.6, 4.1.11-12, 4.2.3, 4.2.8-9, 4.2.11-12, 5.3, 6.3, 8.2
GND MAP 2.3.4-6
H
HEADING SELECT
HEADING BUG
HDG BUG 4.1.20
HEADING SELECT “BUG” 4.1.3, 6.2
HEADING SELECT KNOB 2.1.10, 4.1.3, 6.2
9.2
SW 06/07/08/11 Issued 4/95
Index
HEADING SYNC 2.1.10
HSI 2.1.3, 2.4.2, 2.4.4, 4.1.15, 4.2.7, 4.2.9-10, 4.4.14, 5.2, 8.2
I
ILS
ILS APPROACH 4.1.4, 5.3
IN-FLIGHT OPERATION 5.2
K
KNS 81 2.4.4
L
LATERAL COURSE
LATERAL COURSE DEVIATION BAR 4.1.5, 4.3.2
LATERAL COURSE DEVIATION SCALE 4.1.4, 4.3.2
LIGHTNING
LIGHTNING DETECTION 4.1.17
LIMITATIONS 5.1, 5
LNAV
LNAV MAP 2.1.8-9, 2.4.2, 2.4.4, 4.1.18-19
LOC 4.1.14, 4.2.6-7, 4.2.12, 5.3
LOR 2.1.6, 4.1.9, 4.1.12, 8.2
M
MAGNETIC
MAG 4.1.9-10
MAG VAR 4.1.9-10
MAP
360 MAP DISPLAYS 4.1.13
360 NAV MAP 2.1.3
MAP 360 COMPASS CARD 4.1.13
MAP COURSE DEVIATION INDICATOR 4.1.14
NO MAP 4.1.14, 4.1.18
MEMORY 2.1.4, 4.4.9-11, 6.4
MFD I.1, 1.1-3, 1.6, 1.8, 1.10, 1.12, 1.14, 1.16, 2.1.1, 2.1.3-4, 2.1.7-8, 2.3.6,
2.4.1-6, 4.1.7, 4.1.16-17, 4.4.1-16, 5.1, 6.2, 6.5, 7.3-4
MULTI FUNCTION DISPLAY 1.1, 2.4.1
MLS 1.6, 1.11, 1.14, 1.17, 2.1.7, 4.1.4-8, 4.1.10-11, 4.2.6-8, 4.2.10, 4.2.12,
MODE
4.3.2-3, 8.2
1-2 2.1.5-6, 2.4.3, 2.4.6, 4.1.2, 4.4.12, 4.4.14, 5.2
360-DEGREE MODE 2.1.3
Issued 4/95 SW 06/07/08/11 9.3
Index
N
NAV
1-2 NAVIGATION SYSTEM SELECT 2.1.6
NAV CDI MAP 2.1.3
NAV MAP 2.1.3-4, 2.1.7, 2.1.9, 2.4.4, 4.1.4, 4.1.15-16, 4.4.2, 5.3
NAV NAVIGATION SENSOR SELECT 2.1.4
NAVIGATION SOURCE ANNUNCIATION 4.1.2, 4.3.2
NDB 4.1.10, 5.2, 4
O
OFF 2.2.2, 2.3.4, 2.3.6, 2.4.3-4, 2.4.6, 4.1.10, 4.1.13, 4.1.15-16, 4.1.18-19,
4.2.3, 4.2.6, 4.4.2, 4.4.9-10, 4.4.12-14, 5.1, 6.4
OFF-STBY-TST-ON 2.3.4
OMG 2.1.6, 4.1.9, 4.1.12, 8.2
ON I.1-2, 1.1, 1.3, 1.6, 1.8, 1.10, 1.12, 1.14, 1.16, 2.1.2-8, 2.1.10, 2.2.1,
2.3.3-6, 2.4.1-6, 4.1.2-4, 4.1.6-7, 4.1.9-20, 4.2.2, 4.2.5-13, 4.3.1-3,
4.4.1-5, 4.4.7-14, 5.1-5, 6.1-5, 7.1-2
OPERATING INSTRUCTIONS 2.1.2, 2.2.1, 5.1-6,
P
PITCH 4.2.1-4, 4.2.6, 4.2.12, 4.3.1, 6.1, 4
PRE-TAKEOFF PROCEDURES 5.1
PULL ARL 2.3.6
PULL AUTO 2.3.6
PULL STAB OFF 2.3.6
PUSH BUTTON TEST 5.1
R
RADAR
RADAR CONTROLS 2.1.4, 2.3.3
RDR 1400 4.1.16, 4.4.7
RADIO ALTIMETER 1.3, 2.2.2, 4.2.5-7, 4.2.10, 6.3
RANGE
RANGE DOWN 2.1.7, 4.4.14
RANGE RING 2.4.4, 4.1.13, 4.1.15-16, 4.4.1-2, 4.4.4
RANGE SELECTION 2.1.7, 4.1.15, 4.1.17-18, 4.4.4
RANGE UP 2.1.7, 2.4.3, 4.4.14
RAW DATA DEVIATION ANNUNCIATIONS 6.3
REF
REF MAP FORMAT 2.1.9
REVERSIONARY MODE 4.1.6, 4.2.9, 4.2.12
RISING RUNWAY 1.9, 1.13, 1.17, 4.2.5-7, 4.2.10-12
RNAV
RNV 4.1.9
9.4
SW 06/07/08/11 Issued 4/95
Index
ROLL 1.8, 1.13, 1.16, 4.2.1-4, 4.2.12, 4.3.1, 6.1, 6.4
S
SELECTED COURSE 2.1.5, 2.1.10, 2.4.4, 4.1.3-5, 4.1.11-14, 4.2.6, 4.2.8,
4.3.1-2, 4.4.1, 5.2-4, 6.1
SELF TEST 2.1.8, 2.2.2, 5.1
SN 8.2
SOFTWARE
SOFTWARE 06 1.6, 2.1.8-9, 2.4.2-3, 4.2.3, 4.2.9-10, 6.5
SOFTWARE 07 1.10, 2.1.7, 2.4.2, 4.1.6, 5.1, 6.4
SOFTWARE 08 1.14, 2.1.6-8, 2.4.1-3, 2.4.5, 4.1.5-7, 4.1.11, 4.2.8, 4.4.3,
4.4.8
SOFTWARE 11 1.18, 2.3.6, 4.1.4-5,4.1.11, 4.2.13, 4.3.3, 4.4.20
STAB OFF 2.3.6, 6.4
STANDARD EHSI DISPLAYS 4.1.1, 4.1.15
START UP 5.1
STB LMT 6.4
STB OFF 6.4
STBY 2.3.4, 4.1.16, 4.4.6, 7.4, 8.2
SYMBOL
SG I. 1, 1. 1, 1.3, 1.6, 1.10, 1.14, 1.17 4.2. 12, 5. 1, 6. 1, 6.3, 7. 1-2,
7.4, 8. 2
SYMBOL GENERATOR I. 1, 1. 3, 2.1. 4, 4.1. 7, 4.2. 9-10, 4.2.12-13,
4.3. 1, 4.4. 9, 6. 1-4, 7. 2-4, 8. 2
SYMBOL GENERATOR LOSS OF COOLING 6. 1
SYMBOLIC AIRCRAFT 2.4.2, 2.4.5, 4.1.3-4, 4.1.10, 4.1.16-17, 4.2.2,
4.3.1, 4.4.1-2, 4.4.4
SYSTEM CONFIGURATION 1.1-18, 4.1.2, 6.4, 7.1
T
TCAS
TCAS INTERFACE
TCAS ONLY BUTTON 2.4.2
TCAS ONLY SELECTION 4.4.3
TCAS DISPLAY FORMAT 4.4.4
TCAS TRAFFIC SYMBOLOGY 4.4.4
TCAS DISPLAY ANNUNCIATIONS 4.4.5
TCAS ONLY DISPLAY 4.4.22
TCAS FAULT MESSAGES 6.5
TCN 2.1.6, 4.1.9, 8.2
TILT 2.3.6, 4.1.16-17, 6.4
TO I.1-2, 1.1, 1.3, 1.5-6, 1.10, 1.14, 2.1.2-10, 2.2.1-2, 2.3.1-6, 2.4.1-6,
4.1.1-20, 4.2.1-3, 4.2.5-10, 4.2.12-13, 4.3.1-3, 4.4.1-15, 5.1-5, 6.1-5,
7.1-4
TO-FROM 5.2-4
TRUE 2.4.4, 4.1.9-10, 4.1.15, 4.2.10, 4.2.13, 4.4.2
Issued 4/95 SW 06/07/08/11 9.5
Index
TST 2.1.8-9, 2.2.2, 2.3.4, 2.4.6, 4.4.3, 4.4.15, 5.1, 8.2
TST/REF
SELF TEST 2.1.8, 2.2.2, 5.1
TX FLT 6.4
V
VN 4.1.11, 4.2.8, 6.3
VNAV 1.7, 1.11, 1.15, 1.17, 4.1.10-11, 4.2.3, 4.2.7-8, 5.3, 8.2
VOR
VOR APPROACH 5.4
VERTICAL PROFILE
VP 2.3.2-3, 2.3.5-6, 4.4.1-2, 6.4-5, 8.2
W
WAIT 2.3.5, 6.5
WEATHER
WEATHER RADAR ANNUNCIATIONS 6.4
WX 2.1.8, 2.3.4-5, 4.1.16-17, 6.4-5, 8.2
WX FLT 2.1.8, 4.1.17, 6.4-5
WXA 2.3.4-5, 4.1.17, 8.2
WIND VECTOR
WIND VECTOR INFORMATION 4.1.12
9.6
SW 06/07/08/11 Issued 4/95
Pilot’s Guide
EFS 50
5-inch Electronic Flight
Instrumentation System
B
AlliedSignal General Aviation Avionics
400 North Rogers Road
Olathe, Kansas 66062-1212
TELEX 669916 KINGRAD FAX 913-791-1302
TELEPHONE (913) 768-3000
©1995 AlliedSignal Inc.
4/95 006-08485-0000 1K PRINTED IN THE U.S.A.
SW 06/07/08/11
A
A
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