Aspen Avionics Evolution EFD 1000 C3 Pro PFD Pilot's Manual

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Aspen Avionics Evolution EFD 1000 C3 Pro PFD Pilot's Manual | Manualzz
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page iii
Document Revisions
Revision
Description of Change
()
Initial Release
A
Grammatical, pictorial, and technical updates. Revised to update for software v2.0, including the following:
r
B
Page iv
Additions to text, tables, and figures that reference display of traffic information.
Grammatical, pictorial, and technical updates. Revised to update text, tables, and figures for software versions 2.1, 2.2, 2.3.1, and 2.3.2.
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Table of Contents
Document Revisions ....................................................................iv Chapter 2
Copyrights, Trademarks and Patents ......................................xxi Controls and Display .................................................................. 2-1
2.1. Controls & Display Orientation .......................................................................2-2
Approvals .....................................................................................xxii
Chapter 1
Welcome and Introduction ....................................................... 1-1
2.2. Controls......................................................................................................................2-4
2.2.1. Left and Right Knobs ...................................................................... 2-4
2.2.1.1. Left Knob Functions .......................................................... 2-5
2.2.1.2. Right Knob Functions ...................................................... 2-5
2.2.1.3. SYNC Function........................................................... 2-6
2.2.1.4. Using the Knobs (Example) .......................................... 2-8
2.2.2. Navigation Source Select Buttons ........................................... 2-8
2.2.2.1. CDI Nav Source Select Button..................................... 2-9
2.2.2.2. Bearing Pointer Source Select Buttons ................2-10
2.2.3. Hot Keys ................................................................................................2-11
2.2.4. MENU......................................................................................................2-14
2.2.4.1. Using the Menus ...............................................................2-14
2.2.4.2. Display Lighting.................................................................2-18
2.2.5. Range Buttons ...................................................................................2-19
2.2.6. REV Button ...........................................................................................2-19
1.1. System Overview ..................................................................................................1-4
1.1.1. Primary Flight Display Unit (PFD) ............................................. 1-5
1.1.2. Configuration Module (CM) ........................................................ 1-6
1.1.3. Analog Converter Unit (ACU) ..................................................... 1-6
1.1.4. Remote Sensor Module (RSM) ................................................... 1-7
2.3. Display .....................................................................................................................2-20
2.3.1. Cleaning the Display Screen .....................................................2-21
2.3.2. Attitude Display................................................................................2-22
2.3.2.1. Attitude Director Indicator (ADI) .............................2-24
2.3.2.2. Airspeed Tape and Bug .................................................2-25
Technical Standard Orders: ............................................................ xxii
European Technical Standard Orders: ...................................... xxii
LIMITED WARRANTY
Aspen Avionics, Inc. ..................................................................xxiii
Conventions...............................................................................xxvii
Terminology ................................................................................................................... xxvii
Color Philosophy ...........................................................................................................xxix
Warnings, Cautions, and Notes..............................................................................xxx
Example Graphics .........................................................................................................xxxi
Pilot Familiarity................................................................................................................xxxi
Information Covered in this Pilot’s Guide .................................................... xxxii
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page v
2.3.2.2.a. Mach Number Display for Mmo Aircraft............2-26
3.2. Example Flight Scenario ..................................................................................3-5
2.3.2.3. Altitude Tape, Altitude Alerter, and
3.2.1. Pre-Departure (Startup) ................................................................. 3-6
Vertical Speed .....................................................................2-27
3.2.2. Departure .............................................................................................3-16
2.3.2.4. Instrument Approach Indicators ............................2-28
3.2.3. Enroute ..................................................................................................3-18
2.3.3. Data Bar .................................................................................................2-29
3.2.4. Arrival and Approach to Landing ..........................................3-21
2.3.4. Navigation Display ..........................................................................2-30
Chapter 4
2.3.4.1. Direction Indicator (Magnetic Compass) ...........2-32
Reference Guide ......................................................................... 4-1
Compass Modes: 360º vs. ARC............................................ 2-32
4.1. Air Data, Attitude and Heading Reference System (ADAHRS) .4-2
Navigation Information........................................................ 2-33
4.1.1. Attitude.................................................................................................... 4-3
Ground Track Marker.............................................................. 2-33
4.1.2. Pitot Obstruction Monitor ............................................................ 4-4
2.3.4.2. Horizontal Situation Indicator (HSI) .......................2-34
4.1.3. Heading................................................................................................... 4-5
2.3.4.3. Course Pointer and
4.1.4. Free Gyro Mode .................................................................................. 4-6
Course Deviation Indicator (CDI) Bar.....................2-34
4.1.5. Degraded ADAHRS Performance............................................. 4-7
2.3.4.4. Deviation Off Scale Indication ..................................2-35
4.2. Attitude Display ....................................................................................................4-8
2.3.4.5. Auto Course Select ..........................................................2-35
4.2.1. Attitude Indicator .............................................................................. 4-8
2.3.4.6. Bearing Pointers ................................................................2-36
4.2.1.1. Roll Scale.................................................................................. 4-9
2.3.4.7. Rate of Turn Indicator .....................................................2-37
4.2.1.2. Pitch Scale ............................................................................... 4-9
2.3.4.8. Vertical Speed Indicator (VSI) ....................................2-37
4.2.1.3. Slip/Skid Indicator .............................................................. 4-9
2.3.4.9. Situational Awareness Map ........................................2-38
4.2.1.4. Flight Director ....................................................................... 4-9
Chapter 3
4.2.2. Airspeed Indicator ...........................................................................4-10
Flying the PFD ............................................................................. 3-1
4.2.2.1. Selected Airspeed ...........................................................4-12
3.1. Quick Controls Overview .................................................................................3-3
4.2.2.2. Airspeed Display ...............................................................4-13
4.2.2.3. MACH Number Display for Mmo Aircraft ...........4-14
Page vi
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
4.2.3. Altimeter ...............................................................................................4-15
4.2.3.1. Barometric Units of Measure .....................................4-16
4.2.3.2. Selected Altitude Field ..................................................4-17
4.2.3.3. Altitude Level-Off and Deviation Alert ................4-18
4.2.3.4. MINIMUMS Annunciation ............................................4-19
4.2.3.5. Radio Altitude Display ...................................................4-22
4.2.3.6. Altitude Display .................................................................4-23
4.3. Data Bar...................................................................................................................4-24
4.3.1. True Airspeed or Mach Number (when enabled).........4-24
4.3.2. Ground Speed ...................................................................................4-25
4.3.3. Outside Air Temperature (when enabled) ........................4-25
4.3.4. Wind Speed, Direction and Arrow (when enabled) ....4-26
4.3.5. Barometric Pressure Setting Display ....................................4-26
4.4. Navigation Display ...........................................................................................4-27
4.4.1. Compass ..............................................................................................4-28
4.4.1.1. 360° Compass Mode.......................................................4-28
4.4.1.2. ARC Compass Mode .......................................................4-28
4.4.2. Course Pointer ..................................................................................4-31
4.4.3. TO/FROM Indicator.........................................................................4-32
4.4.4. Course Deviation Indicator and Scale .................................4-33
4.4.4.a. Localizer Back Course (BC) Operation..................................4-34
4.4.5. CDI Navigation Source .................................................................4-34
4.4.6. Auto Course .......................................................................................4-38
4.4.7. CDI Selected Course .....................................................................4-39
4.4.8. Bearing Pointer Source Selection .........................................4-40
091-00019-001 REV B
4.4.9. Heading Bug .......................................................................................4-43
4.4.10. Aircraft Heading Display ...........................................................4-44
4.4.11. Rate of Turn Indicator .................................................................4-44
4.4.12. Basemap Overlays ........................................................................4-45
4.4.12.1. Basemap Declutter and Range ..............................4-46
4.4.12.2. Flight Plan...........................................................................4-48
4.4.12.3. Map Data Source and Reversion ..........................4-48
4.4.13. Ground Track Marker ...................................................................4-49
4.4.14. GPS OBS Operation with a PFD and a
Mechanical Standby Nav Indicator ....................................4-49
4.4.15. Course Pointer Operation with Integrated
VOR/Localizer/GPS Navigation Systems .........................4-49
4.5. Lateral and Vertical Deviation Indicator ..............................................4-50
4.5.1. Lateral Deviation Indicator .........................................................4-50
4.5.2. Vertical Deviation Indicator ......................................................4-51
4.6. Vertical Speed Indicator ................................................................................4-52
4.7. Autopilot Integration........................................................................................4-53
4.7.1. GPS Steering (GPSS) .......................................................................4-54
4.7.2. Flight Director ....................................................................................4-58
4.7.3. Typical Autopilot Operations ....................................................4-58
4.8. Hazard Awareness .............................................................................................4-65
4.8.1. Traffic Overlay ....................................................................................4-65
4.8.1.1. Traffic Symbols ...................................................................4-66
4.8.1.2. Traffic Altitude Filter ........................................................4-68
4.8.1.3. Traffic Unavailable ............................................................4-69
EFD1000 C3 Pro PFD Pilot’s Guide
Page vii
Chapter 5
Chapter 7
Customizing the PFD ................................................................. 5-1 Appendices .................................................................................. 7-1
5.1. Menu Overview .....................................................................................................5-1
7.1. Operating Limitations........................................................................................7-1
5.2. Customizing Basemap Symbol Declutter Settings .........................5-8
7.2. Software Versions and Serial Number .....................................................7-1
5.3. Configuring Vspeeds .......................................................................................5-11
7.3. Specifications ..........................................................................................................7-3
7.3.1. Primary Flight Display Unit (PFD) ............................................. 7-3
7.3.2. Remote Sensor Module (RSM) .................................................. 7-5
7.3.3. Analog Converter Unit (ACU) ..................................................... 7-5
7.3.4. Operational Specifications ........................................................... 7-6
5.4. LCD Brightness Control..................................................................................5-16
Chapter 6
Expanded Emergency and Abnormal Procedures ............... 6-1
6.1. Pitot/Static System Blockage ........................................................................6-2
6.1.1. Identifying and Handling Suspected Pitot and/or Static
System Failures..................................................................................... 6-4
7.4. Glossary ......................................................................................................................7-7
7.5. Index ..........................................................................................................................7-11
6.2. Frequent or Persistent
CROSS CHECK ATTITUDE Annunciation ................................................6-7
6.3. Difference Detected Between the PFD and
Mechanical Attitude Indicators ....................................................................6-7
6.4. Abnormal Shutdown Procedure .................................................................6-8
6.5. Loss of Aircraft Electrical Power ..................................................................6-9
6.6. GPS Failures and RSM Emergency GPS Use .....................................6-11
6.7. Power Override ...................................................................................................6-13
6.8. In-Flight AHRS Reset ........................................................................................6-14
6.9. GPSS Operation, Annunciations, and Autopilot Modes ............6-16
6.10. Warning, Caution, and Advisory Summary ....................................6-18
Page viii
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Table of Figures
Figure 1 C3 Pro PFD Display, Knobs, Buttons, and Keys .....................xxviii
Chapter 1
Figure 2-16 Menu Edit Mode ...............................................................................2-15
Figure 2-17 Menu........................................................................................................2-15
Figure 1-1 EFD1000 C3 Pro Display Unit ..........................................................1-1
Figure 2-18 Menu Text - Editable .....................................................................2-16
Figure 1-2 Single Display EFD1000 PFD System .........................................1-2
Figure 2-19 Menu Text - Enabled for Editing..............................................2-16
Figure 1-3 Dual Display System: PFD & MFD.................................................1-2
Figure 2-20 Menu Text - Status Only ..............................................................2-16
Figure 1-4 Trio Display System: PFD & Dual MFDs .....................................1-3
Figure 2-21 Menu Text - Disabled ....................................................................2-16
Figure 1-5 EFD 1000 C3 Pro PFD System Architecture............................1-4
Figure 2-22 Menu Display ......................................................................................2-16
Figure 1-6 EFD1000 Display Unit Rear Connections ................................1-5
Figure 2-23 EDIT VALUE Displays Above Right Knob ............................2-17
Figure 1-7 Configuration Module (CM) ............................................................1-6
Figure 2-24 Display Brightness in BRT AUTO Mode ...............................2-18
Figure 1-8 Analog Converter Unit (ACU) ........................................................1-6
Figure 2-25 Display Brightness in BRT ADJUST Mode ..........................2-18
Figure 1-9 Remote Sensor Module (RSM) .......................................................1-7
Figure 2-26 EFD1000 C3 Pro PFD Display Areas .....................................2-20
Chapter 2
Figure 2-27 Attitude Display Components .................................................2-23
Figure 2-1 EFD1000 C3 Pro PFD ............................................................................2-2
Figure 2-28 Slip/Skid .................................................................................................2-24
Figure 2-2 EFD1000 C3 Pro PFD Display Elements ....................................2-3
Figure 2-29 Flight Director ....................................................................................2-24
Figure 2-3 Left and Right Knobs and Corresponding Fields ...............2-6
Figure 2-30 Airspeed Tape .....................................................................................2-25
Figure 2-5 Editing the HDG field...........................................................................2-8
Figure 2-30a Mach Number Display................................................................2-26
Figure 2-6 HDG field updated and inactive ...................................................2-8
Figure 2-31 Altitude Tape .......................................................................................2-27
Figure 2-7 CDI and Bearing Pointer Source Select Buttons .................2-9
Figure 2-33 Decision Height Annunciation ................................................2-28
Figure 2-8 Hot Key Menu Legend.....................................................................2-12
Figure 2-32 Instrument Approach Indications .........................................2-28
Figure 2-9 Hot Key Menu 2 of 2 .........................................................................2-13
Figure 2-34 Data Bar Components...................................................................2-29
Figure 2-15 Menu Navigation Mode ...............................................................2-14
Figure 2-35 Navigation Display Components ...........................................2-31
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page ix
Figure 2-36 360° Compass Mode ......................................................................2-32 Chapter 3
Figure 2-37 ARC CDI Compass Mode with Basemap ...........................2-32
Figure 3-1 Basic EFD1000 Settings ......................................................................3-2
Figure 2-38 Magnetic Heading...........................................................................2-33
Figure 3-2 EFD1000 PFD Initializing....................................................................3-6
Figure 2-39 Navigation Source Information Block .................................2-33
Figure 3-3 CDI Navigation Source Slashed Invalid ....................................3-6
Figure 2-40 Ground Track Marker ......................................................................2-33
Figure 3-4 CDI Source Slashed Invalid ..............................................................3-7
Figure 2-42 Off Scale Deviation Diamond, ARC CDI Mode ...............2-35
Figure 3-5 GPS Caution Annunciations ............................................................3-7
Figure 2-43 Auto Course Indication on CRS Field ...................................2-35
Figure 3-6 BARO Setting Field Enabled ............................................................3-8
Figure 2-44 Auto Course Indication over Left Knob ..............................2-35
Figure 3-7 BARO Setting Field Disabled ...........................................................3-8
Figure 2-41 Off Scale CDI Bar ...............................................................................2-35
Figure 3-8 Selected Heading Field Enabled ..................................................3-9
Figure 2-45 BRG#1 Set to GPS1 TAKLE
Figure 3-9 Selected Heading Field Disabled .................................................3-9
(Single Line Bearing Pointer) .....................................................2-36
Figure 3-10 CDI Navigation Source Selection Button ..........................3-10
Figure 2-46 Rate of Turn Indicator, Rate Shown >6º/second...........2-37
Figure 3-11 Bearing Pointer Nav Source Select Buttons .....................3-10
Figure 2-47 VSI Tape Showing 370 FPM Descent...................................2-37
Figure 3-12 No Bearing Pointer Sources Selected ..................................3-10
Figure 2-48 VSI Tape Capped,
Figure 3-13 Changing the Map Declutter Level .....................................3-11
Digital Value Showing 2,100 FPM Climb ............................2-37
Figure 3-13a Map Declutter Icon Location ................................................3-11
Figure 2-49 20nm Range at Declutter Level 3 ..........................................2-38
Figure 3-13b Declutter Level 4 ..........................................................................3-11
Figure 2-50 Declutter Level 4...............................................................................2-38
Figure 3-13c Declutter Level 3 ............................................................................3-11
Figure 2-51 Declutter Level 3...............................................................................2-38
Figure 3-13d Declutter Level 2 ..........................................................................3-11
Figure 2-52 Declutter Level 2...............................................................................2-38
Figure 3-13e Declutter Level 1 ...........................................................................3-11
Figure 2-53 Declutter Level 1...............................................................................2-38
Figure 3-13f Declutter Level 0 ............................................................................3-11
Figure 2-54 Declutter Level 0 (OFF) .................................................................2-38
Figure 3-14 Range Button......................................................................................3-12
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EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Figure 3-15 Current Range 20nm from Ownship to
Figure 3-35 360º Mode Showing Procedure Turn,
Edge of Compass Rose ................................................................3-12
Figure 3-16 Current Range 10nm from Ownship to
GPSS Enabled.....................................................................................3-22
Figure 3-36 Vertical and Horizontal Deviation Indicator,
Edge of Compass Rose .................................................................3-12
Showing Glide Slope .....................................................................3-25
Figure 3-17 Traffic Overlay On .............................................................................3-13
Figure 3-37 MINIMUMS Alert ...............................................................................3-25
Figure 3-18 Altitude Bug Enabled.....................................................................3-14 Chapter 4
Figure 3-19 Altitude Field Enabled ...................................................................3-14
Figure 4-1 Cross Check Attitude Annunciation ..........................................4-3
Figure 3-20 Altitude Bug Disabled ...................................................................3-14
Figure 4-2 Attitude Indicator ..................................................................................4-8
Figure 3-21 Selected Airspeed Field Enabled ...........................................3-15
Figure 4-3 Pitch and/or Roll Data Invalid .........................................................4-8
Figure 3-22 Selected Airspeed Field Enabled ............................................3-15
Figure 4-4 Pitch Markings - Chevrons indicate Pitch Down ................4-9
Figure 3-24 Flight Director V-bars .....................................................................3-15
Figure 4-6 Flight Director ..........................................................................................4-9
Figure 3-23 Selected Airspeed Field Disabled...........................................3-15
Figure 4-5 Pitch Markings - Chevrons indicate Pitch Up .......................4-9
Figure 3-25 Altitude Alerter Flag Illuminated ............................................3-16
Figure 4-7 Airspeed Indicator ..............................................................................4-10
Figure 3-26 CDI Shown Hollow at Full-Scale Deflection.....................3-18
Figure 4-9 Pitot Obstruction Monitoring Airspeed <30kts,
Figure 3-27 CDI “Alive” and Shown Solid .......................................................3-18
Ground Speed >50kts Annunciation......................................4-11
Figure 3-28 GPSS Enabled legend in Green ...............................................3-19
Figure 4-8 Actual Airspeed Greater Than the Vne...................................4-11
Figure 3-29 GPSS Enabled ....................................................................................3-19
Figure 4-10 Airspeed Bug Selected to Edit .................................................4-12
Figure 3-30 360° Compass Mode ......................................................................3-20
Figure 4-11 New Airspeed Selected ................................................................4-12
Figure 3-31 ARC CDI Compass Mode .............................................................3-20
Figure 4-12 Editing Airspeed Tape Display ................................................4-13
Figure 3-32 Data Bar ..................................................................................................3-20
Figure 4-13 Airspeed Tape Disabled................................................................4-13
Figure 3-33 MIN Hot Key (shown disabled) ................................................3-21
Figure 4-13a Altitude Transition Setting .......................................................4-14
Figure 3-34 MIN Display Selected for Editing ............................................3-21
Figure 4-13b Speed Transition Setting ..........................................................4-14
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Page xi
Figure 4-14 Altimeter ................................................................................................4-15
Figure 4-33 DH Annunciation .............................................................................4-22
Figure 4-15 Altitude Failure...................................................................................4-16
Figure 4-34 Editing Altitude Tape Display....................................................4-23
Figure 4-16 BARO Shown in Inches of Mercury .......................................4-16
Figure 4-35 Altitude Tape Disabled..................................................................4-23
Figure 4-17 BARO Shown in Millibars .............................................................4-16
Figure 4-36 Data Bar ..................................................................................................4-24
Figure 4-18 Editing BARO Units of Measure
Figure 4-37 Select OAT Units of Measure .....................................................4-25
GENERAL SETTINGS B ...................................................................4-16
Figure 4-38 Wind Direction Arrow ....................................................................4-26
Figure 4-19 Editing BARO from in to mB ......................................................4-16
Figure 4-39 Horizontal Situation Indicator ..................................................4-27
Figure 4-20 BARO Set to mB (millibars) .........................................................4-16
Figure 4-40 360° Compass Mode ......................................................................4-28
Figure 4-21 BARO Field Enabled ........................................................................4-17
Figure 4-41 ARC HSI Compass Mode..............................................................4-28
Figure 4-22 Altitude Bug and Altitude Alerter Enabled ......................4-18
Figure 4-42 ARC CDI Compass Mode .............................................................4-29
Figure 4-23 Altitude Alert.......................................................................................4-18
Figure 4-43 GENERAL SETTINGS A....................................................................4-29
Figure 4-24 Altitude Alert Extinguishes at Selected Altitude ..........4-18
Figure 4-44 Changing the ARC Compass MODE.....................................4-29
Figure 4-25 Minimums Green Triangle ..........................................................4-19
Figure 4-45 CDI ARC Compass MODE Selected .......................................4-29
Figure 4-26 Minimums Yellow Triangle .........................................................4-19
Figure 4-46 360/ARC Hot Key ..............................................................................4-30
Figure 4-27 Minimums Red Striped Triangle .............................................4-19
Figure 4-47 ARC CDI Compass Mode .............................................................4-30
Figure 4-28 MIN Hot Key – Selected MINIMUMS Annunciation
Figure 4-48 360˚ Compass Mode ......................................................................4-30
and Markers Disabled ....................................................................4-20
Figure 4-49 Reduced Length Course Pointer,
Figure 4-29 Selected MINIMUMS Annunciation and
ARC HSI Compass Mode .............................................................4-31
Markers Enabled ..............................................................................4-20
Figure 4-50 Stub Course Arrowhead ,
Figure 4-30 Selected MINIMUMS Field - MIN Enabled .........................4-21
ARC CDI Compass Mode .............................................................4-31
Figure 4-31 New Selected MINIMUMS Annunciation Setting ........4-21
Figure 4-51 Stub Course Tail , ARC CDI Compass Mode .....................4-31
Figure 4-32 MINIMUMS Annunciation Active ...........................................4-21
Figure 4-54 HSI TO Indication ..............................................................................4-32
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Figure 4-55 HSI FROM Indication ......................................................................4-32
Figure 4-71 AUTOCRS Enabled ...........................................................................4-38
Figure 4-56 CDI TO Indication .............................................................................4-32
Figure 4-72 Menu, GENERAL SETTINGS.........................................................4-39
Figure 4-52 360° TO Indication ...........................................................................4-32
Figure 4-73 Editing AUTOCRS..............................................................................4-39
Figure 4-53 360° FROM Indication....................................................................4-32
Figure 4-74 AUTOCRS Disabled ..........................................................................4-39
Figure 4-57 CDI FROM Indication .....................................................................4-32
Figure 4-75 CRS Field Enabled for Editing ...................................................4-39
Figure 4-59 Course Deviation Indicator,
Figure 4-76 Bearing Pointer Description ......................................................4-40
ARC CDI Compass Mode ............................................................4-33
Figure 4-60 Course Deviation Indicator,
Figure 4-77 Bearing Pointers OFF......................................................................4-41
Figure 4-78 Invalid Bearing Pointer Source .................................................4-41
ARC CDI Compass Mode with Back Course ....................4-33
Figure 4-79 Icons when Bearing Pointers are OFF ................................4-41
Figure 4-62 Deviation Exceeded, ARC CDI ..................................................4-33
Figure 4-80 Single-Line Bearing Pointer and Button ............................4-42
Figure 4-58 Deviation Indicator, 360° and
Figure 4-81 Double-Line Bearing Pointer and Button .........................4-42
ARC HSI Compass Modes ............................................................4-33
Figure 4-61 Exceeded Deviation, 360° and
Figure 4-82 Heading Bug and Selected Heading Field ......................4-43
Figure 4-83 Selected Heading Bug Outside of the
ARC HSI Arc Compass Modes ...................................................4-33
ARC Compass Scale Range.........................................................4-43
Figure 4-63 CDI Source selection and Information................................4-35
Figure 4-84 Heading Selected to Edit ............................................................4-43
Figure 4-64 CDI Source Information Block ..................................................4-36
Figure 4-85 Direction of Flight Numerical Display .................................4-44
Figure 4-65 No Course Deviation Bar or TO/FROM Indicator ..........4-37
Figure 4-86 Direction Indicator Fail ..................................................................4-44
Figure 4-66 Invalid CDI Navigation Source Label ....................................4-37
Figure 4-87 Rate of Turn Indicator (360° Compass Mode) .................4-44
Figure 4-67 CDI Source Information Blank Block ...................................4-37
Figure 4-88 Rate of Turn Indicator (ARC Compass Mode) .................4-44
Figure 4-68 Menu, GENERAL SETTINGS.........................................................4-37
Figure 4-89 Basemap (ARC CDI Compass Mode Shown)...................4-45
Figure 4-69 Editing AUTOCRS..............................................................................4-38
Figure 4-90 Basemap Symbol Set .....................................................................4-45
Figure 4-70 AUTOCRS Enabled ...........................................................................4-38
Figure 4-91 MAP Hot Key .......................................................................................4-46
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Figure 4-92 New Basemap Display Level ....................................................4-46
Figure 4-111 GPSS Disabled and Autopilot in HDG Mode ................4-56
Figure 4-93 Basemap Range Buttons .............................................................4-46
Figure 4-112 GPSS Automatically Disabled —
Figure 4-94 New Basemap Range ....................................................................4-46
Wings Level Mode ........................................................................4-58
Figure 4-95 Auto Range Mode ...........................................................................4-47
Figure 4-113 Flight Director..................................................................................4-58
Figure 4-96 GENERAL SETTINGS B Page
Figure 4-114 Traffic Overlay Enabled ..............................................................4-65
Editing Auto Range Setting ......................................................4-47
Figure 4-114a Traffic Overlay Disabled ..........................................................4-65
Figure 4-97 GPS1 Failure, Reversionary Navigation ...............................4-48
Figure 4-115 Traffic Symbology..........................................................................4-66
Figure 4-98 RSM GPS Reversionary Navigation .......................................4-48
Figure 4-117 Traffic Altitude Filter ....................................................................4-68
Figure 4-99 Invalid or Failed GPS Annunciations.....................................4-49
Figure 4-118 Traffic Sensor Invalid ....................................................................4-69
Figure 4-100 ARC Compass Mode, Ground Track Marker ..................4-49 Chapter 5
Figure 4-101 360° Compass Mode, Ground Track Marker..................4-49
Figure 5-1 GENERAL SETTINGS A .........................................................................5-1
Figure 4-102 Lateral and Vertical Deviation Indicators and
Figure 5-2 GENERAL SETTINGS B ..........................................................................5-2
Source Information......................................................................4-50
Figure 5-3 360° MAP SETTINGS .............................................................................5-3
Figure 4-103 Lateral Deviation Diamond Off Scale Indication .......4-51
Figure 5-4 ARC MAP SETTINGS ..............................................................................5-4
Figure 4-104 LDI Source Invalid .........................................................................4-51
Figure 5-5 VSPEEDS A ..................................................................................................5-5
Figure 4-105 Vertical Deviation Diamond Off Scale Indication ......4-51
Figure 5-6 VSPEEDS B...................................................................................................5-5
Figure 4-106 VSI............................................................................................................4-52
Figure 5-7 POWER SETTINGS ..................................................................................5-6
Figure 4-107 VSI Tape Off-Scale ..........................................................................4-52
Figure 5-8 SYSTEM STATUS .......................................................................................5-7
Figure 4-108 VSI Fail – 360° Compass Mode ..............................................4-52
Figure 5-9 360° Compass Mode Display Options ......................................5-8
Figure 4-109 GPSS Hot Key ...................................................................................4-55
Figure 5-10 ARC Compass Mode Display Options ....................................5-8
Figure 4-110 GPSS Enabled with Autopilot in HDG Mode ................4-56
Figure 5-11 Editing 360° Airports Display Option ......................................5-9
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Figure 5-12 360° Airports Display Option Set To OFF ..............................5-9
Figure 6-8 AHRS Reset Confirmation Message .........................................6-15
Figure 5-13 Level 4 ....................................................................................................5-10
Figure 6-9 Operating in GPSS Mode ...............................................................6-16
Figure 5-14 Level 3 .....................................................................................................5-10
Figure 6-10 GPSS in Wings Level Mode.........................................................6-16
Figure 5-15 Level 2 .....................................................................................................5-10
Figure 6-11 GPSS Disabled ....................................................................................6-17
Figure 5-16 Level 1 .....................................................................................................5-10
Figure 6-13 Battery Operational.........................................................................6-18
Figure 5-17 Level 0 Off............................................................................................5-10
Figure 6-14 Attitude Fail..........................................................................................6-18
Figure 5-18 Speed Bands .......................................................................................5-13
Figure 6-15 Direction Indicator Fail ..................................................................6-18
Figure 5-19 Menu, VSPEEDS A .............................................................................5-14
Figure 6-16 Chevrons indicate Pitch Down ................................................6-19
Figure 5-20 Editing VSPEEDS................................................................................5-14
Figure 6-17 Chevrons indicate Pitch Up .......................................................6-19
Figure 5-21 VSPEEDS Enabled .............................................................................5-14
Figure 6-18 Cross Check Attitude .....................................................................6-20
Figure 5-22 Menu, VSPEEDS A .............................................................................5-15
Figure 6-19 Check Pitot Heat ...............................................................................6-20
Figure 5-23 Editing Va Vspeed.............................................................................5-15
Figure 6-20 GPS Invalid............................................................................................6-21
Figure 5-24 Va Vspeed Set With New Value ................................................5-15
Figure 6-21 RSM GPS.................................................................................................6-21
Figure 5-25 Display Brightness in BRT AUTO Mode ...............................5-16
Figure 6-22 GPS Reversion ....................................................................................6-21
Figure 5-26 Display Brightness in BRT ADJUST Mode ..........................5-16
Figure 6-23 GPS Reversion Emergency ........................................................6-21
Chapter 6
Figure 6-24 GPS Integrity Flag.............................................................................6-21
Figure 6-1 Powering Off the PFD ........................................................................6-8
Figure 6-25 Altitude Caution................................................................................6-21
Figure 6-2 Battery Operation ..................................................................................6-9
Figure 6-26 Decision Height Caution .............................................................6-21
Figure 6-3 External Power Voltage Status ....................................................6-13
Figure 6-27 GPSS Source Lost/Changed ......................................................6-22
Figure 6-4 Battery Status ........................................................................................6-13
Figure 6-28 Minimums Caution .........................................................................6-22
Figure 6-5 Attitude Degraded Performance ..............................................6-14
Figure 6-29 REV Button Off ...................................................................................6-23
Figure 6-6 Attitude Failure .....................................................................................6-14
Figure 6-30 GPSS On .................................................................................................6-23
Figure 6-7 AHRS Reset Menu Key .....................................................................6-15
Figure 6-31 GPS Annunciations .........................................................................6-24
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Table of Tables
Figure 6-32 Navigation Source Invalid or Unavailable .........................6-24
Table 1 C3 Pro PFD Display, Knobs , Buttons, and Keys ......................xxviii
Figure 6-33 Traffic Enabled ....................................................................................6-24
Table 2 Color Guide .....................................................................................................xxix
Figure 6-34 GPSS Disabled ....................................................................................6-24
Table 3 Warning, Caution, and Note...................................................................xxx
Chapter 2
Chapter 7
Figure 7-1 View Main Application Processor Software Version .........7-2
Table 2-1 EFD1000 C3 Pro PFD Components ...............................................2-3
Figure 7-2 View Input/Output Processor Software Version .................7-2
Table 2-2 Left and Right Knob SYNC Description ......................................2-7
Figure 7-3 View Unit Serial Number ...................................................................7-2
Table 2-3 Hot Key Descriptions ..........................................................................2-12
Table 2-4 Menu Text ..................................................................................................2-15
Table 2-5 Brightness Control ................................................................................2-17
Table 2-6 Attitude Display Components ......................................................2-22
Table 2-7 Data Bar Components........................................................................2-27
Table 2-8 Navigation Display Components ................................................2-29
Chapter 3
Table 3-1 Basic EFD1000 Settings ........................................................................3-2
Chapter 4
Table 4-1 Selected MINIMUMS Markers ........................................................4-18
Table 4-2 ARC Compass Mode Course Pointer Display .......................4-31
Table 4-3 TO/FROM Indicator Description...................................................4-32
Table 4-4 VHF NAV Radio Modes .......................................................................4-36
Table 4-5 Bearing Pointer Description ...........................................................4-40
Table 4-5 Traffic Filter Parameters......................................................................4-68
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Chapter 7
Chapter 5
Table 5-1 Menu – GENERAL SETTINGS A .........................................................5-1
Table 7-1 EFD1000 Display Unit Specifications ...........................................7-4
Table 5-2 Menu – GENERAL SETTINGS B .........................................................5-2
Table 7-2 Remote Sensor Module (RSM) Specifications ........................7-5
Table 5-3 Menu – 360° MAP SETTINGS ............................................................5-3
Table 7-3 Analog Converter Unit (ACU) Specifications ..........................7-5
Table 5-4 Menu – ARC MAP SETTINGS .............................................................5-4
Table 7-4 Operational Specifications .................................................................7-6
Table 5-5 Menu – VSPEEDS A ................................................................................5-5
Table 5-6 Menu – VSPEEDS B .................................................................................5-5
Table 5-7 Menu – POWER SETTINGS ................................................................5-6
Table 5-8 Menu – SYSTEM STATUS .....................................................................5-7
Table 5-9 Map Feature Group Layering, Range, and
Declutter Levels .....................................................................................5-10
Table 5-10 EFD1000 PFD Vspeed Definitions.............................................5-12
Table 5-11 Speed Band Ranges .........................................................................5-13
Table 5-12 Brightness Control .............................................................................5-16
Chapter 6
Table 6-1 Warning Annunciations ....................................................................6-18
Table 6-2 Caution Annunciations......................................................................6-21
Table 6-3 Advisory Annunciations ....................................................................6-23
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Table of Tasks
Chapter 2
Set Barometric Units of Measure .......................................................................4-16
Knob SYNC Function (Figure 2-3) ........................................................................2-6
Set the Barometric Pressure .................................................................................4-17
How to Set the Heading Bug (HDG) ..................................................................2-8
Set Altitude Bug and Altitude Alerter.............................................................4-17
Access To and Navigation Within the Menu ..............................................2-16
Display/Hide Minimums .........................................................................................4-20
Edit Menu Items...........................................................................................................2-17
Set Altitude Minimum .............................................................................................4-21
Chapter 3
Enable or Disable the Radio Altitude Display ............................................4-22
Set the Barometric Pressure ....................................................................................3-8
Hide/Display Altitude Tape ...................................................................................4-23
Set the Heading Bug ....................................................................................................3-9
Select the Transition Setting ................................................................................4-25
Select the CDI Navigation Source.....................................................................3-10
Set OAT Units of Measure ......................................................................................4-25
Select Bearing Pointer Nav Sources.................................................................3-10
Select ARC CDI/HSI Compass Mode ...............................................................4-29
To change the Map Declutter Level ................................................................3-11
Select Compass Type ................................................................................................4-30
Change the Map Range ..........................................................................................3-12
Select the CDI Navigation Source.....................................................................4-35
Display the Traffic Overlay .....................................................................................3-13
Enable Auto Course ...................................................................................................4-38
Set the Altitude Alerter............................................................................................3-14
Disable Auto Course..................................................................................................4-39
Set the Airspeed Bug ................................................................................................3-15
Select CDI Course ......................................................................................................4-39
Engage GPSS..................................................................................................................3-18
Select the Single-Line Bearing Pointer Source .........................................4-42
Select a Compass Mode .........................................................................................3-20
Select the Double-Line Bearing Pointer Source ......................................4-42
Chapter 4
Set Heading Bug..........................................................................................................4-43
Set Airspeed Bug .........................................................................................................4-12
Select Map Declutter Level ...................................................................................4-46
Hide/Display Airspeed Tape .................................................................................4-13
Change Map Range...................................................................................................4-46
Select the Altitude or Speed Transition setting .......................................4-14
Enable Auto Range ...................................................................................................4-47
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Activate Auto Range .................................................................................................4-47
Change Brightness Mode ......................................................................................5-16
Deactivate Auto Range ...........................................................................................4-47
Adjust Display Brightness Manually ................................................................5-16
Enable/Disable GPSS.................................................................................................4-55 Chapter 6
HDG Mode Operation – Heading Bug Steering ......................................4-59
Blocked Pitot or Static Line Suspected .............................................................6-3
HDG Mode Operation – GPS Steering (GPSS) ...........................................4-59
CROSS CHECK ATTITUDE ...........................................................................................6-7
NAV Mode Operation – VLOC Navigation ...................................................4-59
NAV Mode Operation – GPS Navigation ......................................................4-60
Compare Alternate Sources of Available Attitude, Airspeed, and
Attitude ................................................................................................................................6-7
APPR Mode Operation – ILS Approach with Vectors to Final .........4-61
Shutdown PFD (on ground)...................................................................................6-8
APPR Mode Operation – GPS or
Power On Manually ......................................................................................................6-8
GPS/RNAV APV WAAS Approach ......................................................................4-62
Loss of or Degraded Aircraft Power or ON BAT Annunciation ...........6-9
GPS APPR Mode Operation – WAAS GPS Underlay to ILS Approach
Using Pilot Navigation and GPSS ......................................................................4-63
Restore aircraft power to the PFD.....................................................................6-11
GPS APPR Mode Operation – WAAS GPS Underlay to ILS Approach
With ATC Vectors to Final........................................................................................4-64
View External Voltage Status................................................................................6-13
Display the Traffic Overlay .....................................................................................4-65
Perform an In-Flight AHRS Reset .......................................................................6-15
Change the Traffic Altitude Filter..................................................................4-68
Chapter 5
Power Override.............................................................................................................6-13
View Internal Battery Status .................................................................................6-13
When GPSS Automatically Changes to Wings Level Mode ..............6-17
Disable GPSS ..................................................................................................................6-17
Set Map Symbol Display ...........................................................................................5-9
Display or Hide the Vspeed Textual Markers
Chapter 7
View the Main Application Processor Software Version ........................7-2
on the Airspeed Tape................................................................................................5-14
View the Input/Output Processor Software Version ................................7-2
Set Textual Vspeed Labels ......................................................................................5-15
View the EFD1000 Display Unit’s Serial Number ........................................7-2
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Copyrights, Trademarks and Patents
Copyright 2007-2012.
Aspen Avionics® is a registered trademark of Aspen Avionics, Inc.
Evolution™, EFD1000 C3 Pro PFD™, EFD1000 Pro PFD™, EFD1000 MFD™,
EFD500 MFD™, EFD1000™, EFD500™, and the Aspen Avionics logo
are trademarks of Aspen Avionics, Inc. These trademarks may not be
used without the express permission of Aspen Avionics, Inc. All rights
reserved.
All other trademarks are the property of their respective companies. No
part of the Pilot’s Guide may be reproduced, copied, stored, transmitted,
or disseminated, for any reason, without the express written permission
of Aspen Avionics, Inc. Aspen Avionics hereby grants permission to
download a single copy, and any revision, of the Pilot’s Guide onto a
hard drive or other electronic storage medium for personal use, provided
that such electronic or printed copy of the Pilot’s Guide or revision must
contain the complete text of this copyright notice and provided further
that any unauthorized commercial distribution of the Pilot’s Guide or
revision hereto is strictly prohibited.
Avidyne® is a registered trademark of Avidyne Corporation; Bendix/King®
is a registered trademark of Honeywell; Garmin GTX™is a trademark of
Garmin International, Inc.
The EFD1000, EFD1000C3, EFD1000H, EFD500, and EFD500H, and
derivatives thereof, are protected under U.S. Patent Number 8,085,168
and additional patents pending.
091-00019-001 REV B
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Page xxi
Approvals
The FAA and the EASA (European Aviation Safety Agency) has approved
the EFD1000 PFD under the following TSOs and ETSOs:
Technical Standard Orders:
TSO-C2d, TSO-C3d, TSO-C4c, TSO-C6d, TSO-C8d, TSO-C10b,TSO-C106,
TSO-C113
Aspen Avionics, Inc.
5001 Indian School Road NE
Albuquerque, NM 87110
Phone: (505) 856-5034
Fax: (505) 314-5440
www.aspenavionics.com
European Technical Standard Orders:
ETSO-C2D, ETSO-C3D, ETSO-C4C, ETSO-C6D, ETSO-C8D, ETSO-C10B,
ETSO-C106, ETSO-C113
The following certification levels also apply to this product:
r
r
Environmental Certification Level: RTCA DO-160E
Software Certification Level: RTCA DO-178B Level B
This Pilot’s Guide provides information on the use and operation of the
Evolution Flight Display 1000 Primary Flight Display (EFD1000 PFD).
This guide is current as of the latest revision listed on the Document
Revisions page. Specifications and operational details are subject to
change without notice when using an earlier or later software version.
Please visit the Aspen Avionics web site for the most up-to-date Pilot’s
Guide.
Installation of the EFD1000 PFD in a type-certificated aircraft must be
performed in accordance with the latest revision of the EFD1000 and
EFD500 Installation Manual.
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091-00019-001 REV B
LIMITED WARRANTY
Aspen Avionics, Inc.
1. YOUR WARRANTY. Aspen Avionics, Inc. (“Aspen”) warrants to you,
the original purchaser, that its Products (if purchased from an authorized
dealer) will comply with applicable specifications (as set forth in the
owner’s manual) in all material respects and will be free from material
defects in workmanship or materials for a period of twenty-four (24)
months beginning with the date that the aircraft in which the Product
has been installed has been returned to service following installation
by an Aspen authorized dealer (“Return to Service Date”). “Product”
means new end equipment or hardware items, replaceable units and
components of those units.
B.
Furnish proof sufficient to establish that the item is a
Nonconforming Product, and
C.
Allow Aspen access to all relevant records in order to
substantiate your warranty claim.
4. EXCLUSIONS. The following are not covered by (and are
expressly excluded from) this warranty:
A.
Normal wear and tear and the need for regular overhaul
and maintenance,
2. YOUR REMEDY. During the term of this warranty, Aspen will repair
or replace, at its discretion, without charge (see Section 13 below for
information on covered transportation costs), any Product that does
not comply with the warranty of Section 1 above (a “Nonconforming
Product”), so long as the warranty claim is timely submitted and the
procedures in Section 14 (below) are followed. Aspen warrants repaired
and/or replacement items only for the unexpired portion of the original
warranty period, or, if the warranty has expired, for six months from
Aspen’s shipment of the repaired or replacement Product.
B.
Exposure of the Product to temperature, environmental,
operating, or other conditions other than those prescribed
in the owner’s manual,
C.
Failure to install or operate the Product as prescribed in the
owner’s manual or as Aspen otherwise directs,
D.
Alterations or repairs made by anyone other than Aspen or
its authorized service center,
3. CONDITIONS TO COVERAGE. Aspen’s obligation under this
warranty is conditioned on your fulfillment of the obligation to:
E.
Maintenance, repair, installation, handling, transportation,
storage, operation (including, without limitation, operation
of the product’s software or host medium), or use which
is improper or otherwise does not comply with Aspen’s
instructions as set forth in the owner’s manual,
A.
Maintain records accurately reflecting operating time of and
maintenance performed on the Product,
091-00019-001 REV B
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Page xxiii
F.
Accident, contamination, damage from a foreign object or
weather conditions, abuse, misuse, neglect, or negligence,
G.
Exposure of the product or the product’s host medium to any
computer virus or other intentionally disruptive, destructive, or
disabling computer code, and
H.
Any damage precipitated by failure of a product Aspen has
supplied that is not under warranty or by any product supplied
by someone else.
5. INVALIDATION OF WARRANTY. This warranty is void if the
product is altered or repair is attempted or made by anyone other than
Aspen or its authorized service center.
6. WARRANTY CARD. The Return to Service Date must be included
in an accurately completed Aspen warranty application form submitted
by the installing authorized dealer within 30 days of the Return to
Service Date. The warranty application must be signed by the authorized
repairman who certifies that the equipment has been safely and
properly installed in accordance with all Aspen supplied technical
information and in accordance with all applicable FAA procedures and
requirements. The warranty application form must note the repairman’s
FAA certificate number to be valid. FAILURE TO COMPLETE AND RETURN
THE WARRANTY CARD MAY RESULT IN DENIAL OF WARRANTY CLAIMS.
MAKING CERTAIN THAT THE WARRANTY CARD IS COMPLETED, SIGNED,
AND RETURNED IS YOUR RESPONSIBILITY.
7. SOLE REMEDY. Aspen’s sole obligation, and your exclusive remedy
under this warranty, is limited to either the repair or replacement, at
Aspen’s option, of any Nonconforming Product as provided herein.
Page xxiv
8. EXCLUSIVE WARRANTY. THIS WARRANTY IS EXCLUSIVE AND
IN LIEU OF ALL OTHER WARRANTIES. THE IMPLIED WARRANTY OF
MERCHANTABILITY AND IMPLIED WARRANTY OF FITNESS FOR A
PARTICULAR PURPOSE, AS WELL AS ALL OTHER IMPLIED WARRANTIES
(STATUTORY OR OTHERWISE) EXPIRE AT THE END OF THE WARRANTY
PERIOD PRESCRIBED IN SECTION 1.
Some States do not allow limitations on how long an implied warranty
lasts, so the above limitation may not apply to you.
9. INCIDENTAL DAMAGES. ASPEN SHALL NOT UNDER ANY
CIRCUMSTANCES BE LIABLE FOR ANY SPECIAL, DIRECT, INDIRECT,
INCIDENTAL OR CONSEQUENTIAL LOSS OR DAMAGES OF ANY KIND
(INCLUDING WITHOUT LIMITATION: DAMAGES FOR LOSS OF PROFITS,
LOSS OF REVENUES, OR LOSS OF USE OR BUSINESS INTERRUPTION),
EVEN IF ASPEN HAS BEEN ADVISED OF THE POSSIBILITY OR CERTAINTY
OF THOSE DAMAGES OR IF ASPEN COULD HAVE REASONABLY
FORESEEN THOSE DAMAGES.
Some states do not allow the exclusion of incidental or consequential
damages, so the preceding limitations may not apply to you.
10. LIMITATION OF LIABILITY. ASPEN’S AGGREGATE LIABILITY
HEREUNDER, WHETHER BASED UPON CONTRACT, TORT (INCLUDING
NEGLIGENCE AND STRICT LIABILITY), INDEMNITY, OR OTHERWISE, WILL
NOT EXCEED THE PRICE PAID BY YOU FOR THE WARRANTED PRODUCT.
THE EXCLUSIONS OF TYPES OF DAMAGES CONTAINED HEREIN WILL BE
DEEMED INDEPENDENT OF, AND WILL SURVIVE, ANY FAILURE OF THE
ESSENTIAL PURPOSE OF ANY LIMITED REMEDY UNDER THE TERMS OF
ANY AGREEMENT.
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
11. EXTENSION OF WARRANTY. No extension of this warranty will
be binding upon Aspen unless set forth in writing and signed by Aspen’s
authorized representative.
12. DEALER WARRANTIES. Any express or implied warranty or
remedy in addition to or different from those stated herein that is
offered by a dealer (“Dealer Warranty”) will be the sole responsibility
of the dealer, who will be solely responsible for all liability, loss, cost,
damage, or expense arising out of or in connection with any such Dealer
Warranty. Although Aspen provides training and assistance to dealers,
it cannot control the installation of its Products by its dealers, which are
independent businesses not owned or controlled by Aspen.
14. WARRANTY PROCEDURE. If you require warranty service, you
may contact your local Aspen Authorized Dealer or you may contact
Aspen directly as described below. An original or copy of the sales
receipt from the original Aspen Authorized dealer will be required
to obtain any warranty service. You may contact Aspen for warranty
service directly by calling Aspen Customer Service at (505) 856-5034;
by writing to Aspen Customer Service Department, Aspen Avionics,
Inc., 5001 Indian School Road NE, Albuquerque, New Mexico, 87110;
or by visiting the Aspen Website at http://www.aspenavionics.com.
This warranty gives you specific legal rights, and you may also have other
rights, which vary from State to State.
13. TRANSPORTATION COSTS. Aspen will assume round trip
transportation costs for a Product determined by Aspen to be a
Nonconforming Product in an amount not to exceed normal (non
express) shipping charges within the continental United States. You
are responsible for all import/export fees, taxes, duties, customs,
documentation fees, clearance fees, and similar fees and charges.
You may contact Aspen to obtain a freight courier account number
for prepaid shipping of the return. If Aspen subsequently determines
that the Product is not a Nonconforming Product, that this warranty
is inapplicable, that the Product is out of warranty, that the defect or
malfunction is excluded from coverage, or that the warranty is invalid,
Aspen will invoice you for repair or replacement costs and the shipping
costs. Risk of loss or damage for any Product in transit will be borne by
the party initiating the transportation.
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Conventions
The following conventions, functionality, terminology, color philosophy,
and definitions are used in this manual and on the EFD1000 PFD.
Covered Functionality
This guide covers all the functionality available in the EFD1000 PFD and the optional
Hazard Awareness Traffic Overlay functionality.
See Aspen Avionics’ document number 091-00006-001 EFD1000/500 MFD Pilot’s Guide
for complete instructions on the EFD1000 MFD and the EFD500 MFD.
Terminology
The term “PFD”, is used throughout this Pilot’s Guide and refers to the EFD1000 PFD.
Figure 1 shows a typical EFD1000 PFD display. This guide uses the terminology listed in
Table 1 when referring to specific parts of the PFD and Chapter 4 provides an in-depth
discussion and step-by-step instructions for all the available functionality.
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Term
Example
Buttons
REV Button, Range Buttons, MENU Button
Hot Keys / Menu Keys
Five keys on the lower right of the display
Buttons
Lower Left Button, CDI Navigation Source Select Button,
Lower Right Button
Knobs
Left (CRS) Knob, Right (HDG) Knob
Navigation Display
Data Bar
Attitude Display
Table 1
EFD1000 PFD Display, Knobs , Buttons, and Keys
NOTE
Figure 1
EFD1000 PFD Display, Knobs , Buttons, and Keys
Page xxviii
As the number of colors used on the display is limited, to ensure adequate color
differentiation under all lighting conditions, there are a few cases where a given color is
used in a slightly different context than described in Table 2.
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091-00019-001 REV B
Color Philosophy
Table 2 provides the operational philosophy of color usage on the PFD display.
COLOR
PURPOSE
COLOR
PURPOSE
Used to indicate flight envelope and system limits, and
for warning annunciations that require immediate pilot
recognition and which may require immediate pilot
correction or compensatory action.
GREEN
Used for navigation information or mode data related to
or provided by the navigation source currently selected for
display on the Course Deviation Indicator (CDI) (i.e., navigation
deviations, equipment operating state, waypoint information).
Green is also used to indicate status of user controls (i.e., ON,
enabled, or active).
AMBER
Used to indicate abnormal information sources, and for
caution information that requires immediate pilot awareness
and for which subsequent pilot action may be required.
WHITE
Used to show primary flight data (e.g., IAS, ALT, HDG), scales,
and Menu items that are selectable for editing.
MAGENTA
Used for pilot-selectable references (Bugs) enabled for editing,
for depicting the active GPS navigation leg on a moving map
display, and for depicting the flight director bar.
GRAY
Used to show supplemental flight data and for Hot Key and
Menu legends that are OFF, disabled, or inactive.
CYAN
Used to indicate editable values that are not currently selected
for editing. CYAN is also used to display GPS track marker,
bearing pointers, proximity and other traffic icons.
BLUE
Used to indicate the sky.
RED
BROWN
Used to indicate the ground.
Table 2
Color Guide
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Warnings, Cautions, and Notes
Where applicable warnings, cautions, and notes are given. Aspen Avionics uses the
following icons and definitions (Table 3).
Icon
Definition
Warning
Emphasizes a crucial operating or maintenance procedure, which, if not
strictly observed, could result in injury to, or death of, personnel or long
term health hazards.
Indicates a hazard that may require immediate corrective action.
Caution
Indicates an essential operating or maintenance procedure, which,
if not strictly observed, could result in damage to, or destruction of,
equipment.
Indicates the possible need for future corrective action.
Note
Highlights an important operating or maintenance procedure,
condition, or statement.
Safe operation.
Table 3
Warning, Caution, and Note
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Example Graphics
The example graphics and screen shots used throughout this Pilot’s Guide are provided
for reference only and are taken from a simulated flight. They should not be used for
actual flights.
Most of the example graphics and screen shots used throughout this Pilot’s Guide
& Reference are based on flying the ILS 16R instrument approach into Reno/Tahoe
International Airport (KRNO) in Reno, Nevada, USA. Those images with the airplane in
a right bank show the airplane completing the procedure turn in-bound to intercept
the Localizer, descending through 8,660 feet to the target altitude of 8,500 feet. The
other main group of images, showing the airplane straight and level, are earlier in the
approach, tracking outbound for the procedure turn.
Pilot Familiarity
While the PFD is reasonably intuitive and easy to use, some familiarity with Electronic
Flight Instrument Systems (EFIS) and Horizontal Situation Indicators (HSI) is required.
Aspen Avionics strongly recommends that new users of the PFD get some dual
instruction from an experienced instrument CFI, and spend some time becoming
familiar with the PFD in day VFR conditions with a safety pilot, before flying in actual
instrument meteorological conditions (IMC). To reduce pilot workload, the use of an
autopilot (when available) is strongly encouraged.
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Information Covered in this Pilot’s Guide
This Pilot’s Guide covers all the features and options available for the EFD1000 PFD.
Because of individual configuration and options purchased, some features may not be
available on your particular PFD.
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CHAPTER 1 WELCOME
Chapter 1
Welcome and Introduction
Welcome to Aspen Avionics’ Evolution Flight Display (EFD) System, the
most flexible, expandable, and upgradable Electronic Flight Instrument
System (EFIS) available for general aviation aircraft. Designed to replace
traditional mechanical primary flight instruments—in whole or in part,
all at once, or in phases. This modularity and upgradability allows the
system to grow with you and your airplane, over time and affordably.
The EFD system is built around the EFD1000 PFD, which replaces a vertical pair of your
six primary flight instruments. The PFD has a bright, high-resolution, six-inch diagonal
LCD display, and a number of knobs, buttons, and keys the pilot uses to control the
system. The three-inch diameter, four-inch deep can on the back of the display slides
into existing panel cutouts (where the top mechanical instrument used to be) (Figure
1-1).
Figure 1-1
EFD1000 C3 Pro Display Unit
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Page 1-1
CHAPTER 1 WELCOME
The center of the EFD System is the EFD1000 Primary Flight Display (PFD), which
replaces the traditional mechanical Attitude Indicator (AI) and Directional Gyro (DG)
or Horizontal Situation Indicator (HSI) (Figure 1-2).
Figure 1-2
Single Display EFD1000 PFD System
Add a second EFD1000 configured as a Multi-Function Display (MFD) (Figure 1-3),
replacing the altimeter and Vertical Speed Indicator (VSI), and you’ll double the
capabilities of your system, while also providing complete redundancy and backup to
your PFD. The EFD1000 MFD contains the same AHRS, ADC, and I/O capabilities as the
PFD for full redundancy and can assume the role of the PFD should it ever fail.
Figure 1-3
Dual Display System: PFD & MFD
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CHAPTER 1 WELCOME
Adding another MFD, replacing the Airspeed Indicator (ASI) and turn coordinator,
round out a complete six-pack replacement and gain even more capability and
flexibility (Figure 1-4). When ready to upgrade, simply contact an Aspen Avionics
Authorized Dealer for more information.
Figure 1-4
Trio Display System: PFD & Dual MFDs
This Pilot’s Guide covers the EFD1000 Pro PFD model. This system is powerfully flexible
and can be configured in a variety of ways, depending on the other aircraft systems
with which it is integrated.
NOTE
NOTE
Please spend some time with your avionics installer to understand exactly how your PFD
is installed and configured in your particular aircraft, to understand the features and
capabilities available to you, and to understand how various aircraft system failures and
abnormalities may affect your PFD.
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With multiple EFD installations, an independent,
standby attitude indicator must be within the pilot’s
primary maximum field of view.
Page 1-3
CHAPTER 1 WELCOME
Pitot
Existing Aircraft
Pitot Line
Aircraft Power
Configuration Module (CM)
Optional Tone Generator
(Primary Flight Display)
Discrete
Digital GPS/VLOC
Digital VLOC/GPS
Sources
The PFD system typically consists of four components:
Existing Aircraft
Static Line
EFD1000 Pro PFD
12C
1.1. System Overview
Static
ARINC 429
SPI
RS-232
Remote
Sensor
Module
(RSM)
1.
2.
3.
4.
EFD1000 Display Unit (PFD)
Configuration Module (CM)
Remote Sensor Module (RSM)
Analog Converter Unit (ACU)
The ACU converts older analog signals and interfaces to the
industry-standard digital ARINC 429 interface, which is the
native language of the PFD. In some installations, generally
when the aircraft is not equipped with an autopilot and has
only digital GPS/Nav/Comm, the ACU may be omitted.
The system architecture in Figure 1-5 shows the
relationships of the PFD, RSM, CM and ACU.
Analog GPS/VLOC via ACU
Analog NAV Sources
Radar Altimeter
Analog
Converter Unit
(ACU)
Autopilot
Legacy GPS
RS-232
Figure 1-5
EFD1000 Pro PFD System Architecture
Page 1-4
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The Primary Flight Display Unit (PFD) is a digital system that consists of a high
resolution, six-inch diagonal color LCD display, user controls, photocell, and microSD
data card slot. The three-inch diameter, four-inch deep can on the back of the display
contains a non-removable electronics module that includes:
Pitot & Static System Connections
r A Sensor Board with solid-state Attitude and Heading Reference System (AHRS) and
digital Air Data Computer (ADC)
44-pin D-Sub for Electrical Connections
r A Main Application Processor (MAP) board with Central Processing Unit (CPU),
graphics processor and system memory
r An Input-Output Processor (IOP) board for integrating communications with other
aircraft systems
Also on the rear of the unit (Figure 1-6) are:
Access Cover to Internal Battery
r An access cover for removing and replacing the built-in backup battery
r Pneumatic connections to the aircraft’s pitot and static systems
r 44-pin D-sub connector for electrical connections to the PFD
r A cooling fan, to cool the electronics and LCD backlights
The PFD mounts to the front surface of the instrument panel using the standard
installation kit; an optional flush-mount installation kit is also available.
Cooling Fan
Figure 1-6
EFD1000 Display Unit Rear Connections
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Page 1-5
CHAPTER 1 WELCOME
1.1.1. Primary Flight Display Unit (PFD)
CHAPTER 1 WELCOME
1.1.2. Configuration Module (CM)
The Configuration Module (Figure 1-7) contains an EEPROM device that retains system
configuration and calibration data and provides two primary functions:
Figure 1-7
Configuration Module (CM)
r Retains aircraft-specific configuration information, calibration data, and user
settings, allowing the PFD to be swapped for service purposes without re-entering
or re-calibrating the installation
r Contains a license key that configures the PFD software features
The CM is typically attached to the wire bundle coming out of the D-sub connector on
the display unit.
1.1.3. Analog Converter Unit (ACU)
The Analog Converter Unit (ACU) (Figure 1-8), included with the PFD system, enables
the all-digital, EFD1000 System to interface with analog avionics when required. The
ACU converts multiple analog interfaces to the digital ARINC 429 buses supported by
the PFD. Control parameters, such as desired heading, are also sent from the PFD to the
ACU for conversion to analog format for autopilot support. The ACU is required when
any of the following capabilities are required in a PFD installation:
r Interface to supported autopilots
r Interface to conventional VHF navigation radios
r Interface to legacy (non-ARINC 429) GPS navigators
Figure 1-8
Analog Converter Unit (ACU)
Page 1-6
r Interface to supported radar altimeter decision height annunciations
If ARINC 429-based digital radios, such as the Garmin 400/500-series GPS/nav/comm
radios, are installed in the aircraft, and no other aircraft interfaces are desired, the ACU is
not required.
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CHAPTER 1 WELCOME
1.1.4. Remote Sensor Module (RSM)
The Remote Sensor Module (RSM) (Figure 1-9) is an integral part of the PFD system
and works together with the display unit sensors as part of the AHRS and ADC. The RSM
looks and mounts like a GPS antenna and is mounted on the exterior of the fuselage,
typically aft of the cabin.
The RSM contains the following sub-systems:
r 3D magnetic flux (heading) sensors
r Outside Air Temperature (OAT) sensor
Figure 1-9
Remote Sensor Module (RSM)
r Emergency backup GPS engine and antenna
The RSM communicates with the PFD via a digital cable connection.
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CHAPTER 1 WELCOME
This Page Intentionally Left Blank
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CHAPTER 2 CONTROLS AND DISPLAY
Chapter 2
Controls and Display
The PFD is a flat-panel LCD primary flight instrument that presents
the pilot with all of the information from the traditional six-pack of
mechanical instruments: Airspeed, Attitude, Altitude, Turn Coordinator,
Heading Indicator (or HSI) and Vertical Speed Indicator (VSI). Modern
technology and standard EFIS symbology enable the consolidation of
all six instruments into a single display, tightening the pilot’s instrument
scan and reducing pilot workload.
The PFD is a single vertical instrument that replaces the existing Attitude Indicator
and Heading Indicator/HSI. The display is divided into three parts: an upper Attitude
Display, a lower Navigation Display, and a Data Bar between the upper and lower halves.
The Attitude and Navigation displays are highly customizable — from stripped-down,
minimalist presentations, to dense, information-rich displays — depending on pilot
preference and phase of flight.
This chapter gives an overview of all the instruments, information, and controls of
the PFD. Table 2-1 and Figure 2-2 identify the controls and display orientation (see
Chapter 4, Reference Guide for more details).
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Page 2-1
CHAPTER 2 CONTROLS AND DISPLAY
2.1. Controls & Display Orientation
CONTROLS
16
Attitude Display
17
Aircraft Reference Symbol
18
Single-Cue Flight Director 2
19
Roll Pointer
20
Slip/Skid Indicator
21
Altitude Tape
22
Selected Altitude Field (controls the Altitude Bug)
1
Reversion and Power Button
2
Range Buttons
3
Menu Button
4
1/2 Hot Key Menu 1 of 2 4
2/2 Hot Key Menu 2 of 2 1, 4
5
MIN - Minimums
On/Off 4
No function
6
360/ARC View
No function
23
Altitude Alerter
7
GPSS - GPS Steering On/Off 4
TRFC – Traffic Overlay On/Off
24
Numerical Altitude Indication, Altitude Drum/
Pointer
8
BARO
BARO
25
Altitude Trend Vector
9
Right Knob
26
Altitude Bug
10
Lower Right Button, Double-Line Bearing Pointer Source Select
27
Decision Height Annunciation 3, 4
11
CDI Navigation Source Select Button
28
Selected Minimums Field
12
Lower Left Button, Single-Line Bearing Pointer Source Select
29
Radio Altitude 3, 4
13
Left Knob
30
MINIMUMS Marker
14
Automatic Dimming Photocell
31
LDI Navigation Source Indication
15
microSD Card Slot
32
Airspeed Tape
33
Selected Airspeed Field (controls the Airspeed Bug)
34
Airspeed Bug
35
Numerical Airspeed Indicator, Airspeed Drum/
Pointer
36
Vertical Deviation Indicator (VDI)
37
Lateral Deviation Indicator (LDI)
Figure 2-1
EFD1000 C3 Pro PFD
Page 2-2
ATTITUDE DISPLAY
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091-00019-001 REV B
57
Vertical Speed Tape
38
True Airspeed (TAS) or Mach number
58
Single-Line Bearing Pointer
39
Barometric Pressure Setting Field
59
Single-Line Bearing Pointer Source
40
Wind Direction and Speed
60
Single-Line Bearing Pointer Source Info Block
41
Wind Direction Arrow
61
Double-Line Bearing Pointer
42
Outside Air Temperature (OAT)
62
Double-Line Bearing Pointer Source
43
Ground Speed
63
Double-Line Bearing Pointer Source Info Block
64
Selected CDI Navigation Source
65
Selected CDI Navigation Source Information Block
NAVIGATION DISPLAY
44
Navigation Display
45
Ownship Symbol
46
Course Pointer
47
TO/FROM Indicator
48
Rate of Turn Indicator
49
Ground Track Indicator
50
Numerical Direction Indicator
51
Selected Course (CRS) Field
52
Selected Heading Field
53
Heading Bug
54
Course Deviation Scale
55
Course Deviation Indicator
56
Vertical Speed Numerical Value
66
Left Knob State
67
Right Knob State
68
Hot Key Labels
69
Basemap Range
70
33
23
27
22
19
20
1
32
30
16
35
34
26
36
30
28
29
31
38
43
37
42
51
65
2
24
17
18
21
25
41
52
50
48
53
46
Declutter Level
4
56
49
58
3
39
40
68
6
55
Table 2-1
PFD Components
45
61
1. The Hot Key menu 2/2 is only available when the PFD is
configured with the Evolution Hazard Awarenes Traffic option
and the associated sensor(s)
69
70
66
2. With compatible autopilots
54
44
7
47
60
8
63
59
64
5
57
62
67
3. With compatible radar altimeters
4. When configured with the Evolution Synthetic Vision option,
refer to the Evolution Synthetic Vision Pilot Guide Supplement
091-00031-001 for additional Hot Key menu
14
13
12
11
15
10
9
Figure 2-2
EFD1000 C3 Pro PFD Display Elements
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Page 2-3
CHAPTER 2 CONTROLS AND DISPLAY
DATA BAR
CHAPTER 2 CONTROLS AND DISPLAY
2.2. Controls
The primary means for the pilot to control the PFD are the two knobs and three buttons
at the bottom of the display. The knobs control setting CRS and HDG, and additional
bugs and altitude settings. The lower three buttons control selection of navigation
sources for the CDI and Bearing Pointers. There are three additional buttons above
the Hot Keys to control entering and exiting the Menu, setting the Map Range, and
Reversion or Manual Power Control.
Five Hot Keys to the right of the Navigation Display toggle various features on and off.
The function of each is indicated by the label on the display to the left of each key.
2.2.1. Left and Right Knobs
The Left and Right Knobs are designed to provide immediate operation yet minimize
the possibility of an inadvertent operation. This is accomplished by requiring that the first
action of the knob “wakes up” the knob and changes the label from cyan to magenta.
The first click when the knob is turned or the first press on the knob, “wakes up” the knob
function.
Press the knob more than once to cycle through its Menu options in a round-robin
sequence or press and hold the knob to synchronize (SYNC) the function’s value (see
Section 2.2.1.3. SYNC Function). After 10 seconds of inactivity, the knob returns to its
default setting.
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The Left Knob is used to set the Course (CRS) and Airspeed Bug (IAS).
Course (CRS) is the default setting for the Left Knob.
Refer to Table 2-1 and Figure 2-2
r Rotate the Left Knob one click or Press the knob once to set the course
(CRS) (Refs. 46 and 51 and see NOTE about Auto Course)
r Press the Left Knob twice to set the Airspeed Bug (IAS) and Selected
Airspeed Field (Refs. 33 and 34)
2.2.1.2. Right Knob Functions
The Right Knob is used to set Heading (HDG), Selected Altitude Field (ALT),
Barometric Pressure (BARO), and Instrument Approach Minimums (MIN). Successive
presses of the Right Knob will cycle through HDG and ALT (and MIN, if selected) in
a round-robin sequence. Rotate the Right Knob to the left or right to decrease or
increase the value of selected field. Heading (HDG) is the default setting for the Right
Knob.
Refer to Table 2-1 and Figure 2-2
r Rotate the Right Knob one click or Press the knob once to set the Selected
Heading Field/Heading Bug (HDG) (Refs. 52 and 53)
r Press the Right Knob twice to set the Selected Altitude Field (ALT)/Altitude
Bug (Refs. 22 and 26)
r When the MIN Hot Key is selected, press the Right Knob three times to set
the Selected Minimums Field (MIN) (Ref. 28)
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NOTE
MIN will only be shown if the MIN function is already
active. When the MIN function is active, the MIN Hot
Key label (Ref. 5) is shown in green with dark blue
letters, and the MIN value is shown on the Attitude
Display (Ref.28).
When the MIN function is inactive (blue label with
green letters), pressing the MIN Hot Key will both
activate the function and immediately make it
available for editing.
NOTE
When the CDI navigation source is selected to a GPS
receiver and the Auto Course is enabled in the Menu,
the course is set automatically by the GPS and is not
pilot-adjustable (see Section 4.4.6.). This state is
indicated by the CRS field and Knob label shown in
green with an inverse “A”. In this case, pressing the Left
Knob will enable you to set only the Airspeed Bug (IAS).
Page 2-5
CHAPTER 2 CONTROLS AND DISPLAY
2.2.1.1. Left Knob Functions
CHAPTER 2 CONTROLS AND DISPLAY
2.2.1.3. SYNC Function
Knob SYNC Function
1.
2.
3.
Press the Knob until its state shows the value you want to set in magenta.
Press and hold the Knob for approximately one (1) second to SYNC the
setting according to the rules shown in Table 2-2.
After 10 seconds of inactivity, the knob defaults to CRS or HDG. The label and
field will appear in cyan.
RIGHT KNOB
Item
Figure 2-3
Left and Right Knobs and
Corresponding Fields
Page 2-6
SYNC Action
ALT
Altitude Bug and Altitude Alerter are set to the current altitude.
MIN
Set to the current altitude.
BARO
Set to 29.92 in. Hg or 1013 mB.
HDG
Set to the current heading.
Right Knob -Current State default setting: HDG
Cyan indicates field is inactive.
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Item
CHAPTER 2 CONTROLS AND DISPLAY
LEFT KNOB
SYNC Action
IAS
CRS
Set to the current Indicated Airspeed.
VOR navigation
Course Pointer points to the VOR. CRS value is the
reciprocal of the current VOR radial. The deviation
bar centers with a “TO” indication.
ILS navigation
Current aircraft heading.
GPS
Course Pointer points to the active GPS waypoint.
The deviation bar centers with a “TO” indication.
(AUTOCRS must be disabled)
GPS
AUTOCRS enabled
No effect.
Left Knob - Current State default setting: CRS
Cyan indicates field is inactive.
Table 2-2
Left and Right Knob SYNC Description
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Page 2-7
CHAPTER 2 CONTROLS AND DISPLAY
2.2.1.4. Using the Knobs (Example)
How to Set the Heading Bug (HDG)
1.
2.
Figure 2-5
Editing the HDG field
Rotate the Right Knob to the desired heading value, shown both by
the position of the Heading Bug and the numeric value in the Selected
Heading Field (Figure 2-5). The HDG label, Heading Bug and the Selected
Heading Field appears in magenta
After 10 seconds of inactivity, the knob defaults to HDG. The HDG label,
Heading Bug and Selected Heading Field value will appear in cyan
(Figure 2-6).
2.2.2. Navigation Source Select Buttons
The three buttons on the bottom of the PFD (Figure 2-7) allow the pilot to select
the navigation source for the CDI and Bearing Pointers (see Section 4.4.5. CDI
Navigation Source and Section 4.4.8. Bearing Pointer Source Selection for more
detailed information).
Figure 2-6
HDG field updated and inactive
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The CDI Nav Source Select Button is the center button (Figure 2-7). It selects which
of the available navigation sources will couple to the CDI, which in turn couples to
the autopilot (if available). Each press of the CDI Nav Source Button selects the next
available nav source, cycling through all available sources in a round-robin sequence.
The currently coupled CDI nav source is displayed directly above the CDI Nav Source
Select Button.
The available nav sources are configured when the PFD was installed (depending on
what is installed in the aircraft and connected to the PFD). The available nav source
choices are: GPS1, GPS2, VLOC1, and VLOC2.
If a nav source is configured to be available, but is not providing valid navigation data,
its nav source annunciation will be shown with a red slash through it, and the CDI will
not be shown with the Course Pointer. The pilot is able to select the invalid source, but
no navigation data is provided.
When one or more of the connected nav sources is a combined GPS/Nav device (e.g.,
some of the Garmin 400/500-series), the list of nav sources available for selection will be
determined by the current CDI mode of the GPS navigator.
Single-Line
Bearing Pointer
Source
CDI Nav
Source
Double-Line
Bearing Pointer
Source
Figure 2-7
CDI and Bearing Pointer Source Select Buttons
NOTE
When GPS is selected as the CDI’s nav source, but no
active waypoint is programmed in the GPS navigator,
that source will be shown as invalid until an active
flight plan or direct-to waypoint is programmed into
the GPS.
For example, with a Garmin GNS-430 installed as
the #1 navigation source, when “GPS” is shown
immediately above the CDI Button on the GNS-430,
the PFD will show GPS1 as an available , but invalid,
nav source. When the pilot presses the CDI Button on
the GNS-430 so that VLOC is now displayed on the
GNS-430, the PFD will show VLOC1 as the available nav
source, and GPS1 cannot be selected.
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Page 2-9
CHAPTER 2 CONTROLS AND DISPLAY
2.2.2.1. CDI Nav Source Select Button
CHAPTER 2 CONTROLS AND DISPLAY
2.2.2.2. Bearing Pointer Source Select Buttons
The Lower Left Button and the Lower Right Button are the Bearing Pointer Nav Source
Select Buttons (Figure 2-7). The Lower Left Button controls the Single-Line Bearing
Pointer and the Lower Right Button controls the Double-Line Bearing Pointer. Each
button controls which nav source is connected to the respective Bearing Pointer.
The Bearing Pointers act like a conventional RMI (Radio Magnetic Indicator); the needle
points to the station. Unlike a conventional RMI, the PFD Bearing Pointers can also
point to the active waypoint of a GPS navigator whether that is a VOR, NDB, airport,
intersection, or missed approach point.
Each Bearing Pointer can be connected to any of the available navigation sources; GPS1,
VOR1, GPS2, VOR2, ADF1 or ADF2 (depending on configuration), or to none. Each press
of the Bearing Pointer Nav Source Select Button selects the next available nav source,
cycling through all available nav sources and none, in a round-robin sequence. The
currently connected nav source is displayed directly above its respective button; blank
with only the Bearing Pointer icon indicates that no nav source is selected, and the
Bearing Pointer is removed from the display.
If the selected nav source is a valid choice, but no usable nav data is being received
(e.g., the VOR station is out of range, or the VLOC is tuned to a localizer frequency), the
Bearing Pointer will not be displayed.
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The five Buttons along the lower right side of the PFD function as either single-action
Hot Keys for frequently used commands or as Menu Keys when the Menu has been
activated. The Hot Key functions are accessible at any time, except when the Menu is
active.
Each Hot Key provides instant access to the assigned command. Each press of a Hot Key
toggles between the settings that each key controls (see Table 2-3).
NOTE
When the PFD is configured with the Evolution Hazard
Awareness option, there are two levels of Hot Keys,
controlled by the first Hot Key (1/2 or 2/2).
The second level (2/2) provides access to Hazard
Awareness overlays as described in Section 4.8.,
Hazard Awareness.
The Hot Key labels use the following color philosophy (see Figure 2-8 and Figure 2-9).
r
r
r
r
A green label and dark blue letters (also known as inverse green) indicates
that the Hot Key function is enabled
A dark blue label and green letters indicates that the Hot Key function is
diabled
A dark blue label and gray letters indicates that the Hot Key function is not
available
A dark blue label without letters indicates that the Hot Key has no function
NOTE
The TRFC Filter Hot Key is blank when Traffic Software
Option is not installed.
The 360/ARC Hot Key labels indicate which mode is currently active on the Navigation
Display.
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Page 2-11
CHAPTER 2 CONTROLS AND DISPLAY
2.2.3. Hot Keys
CHAPTER 2 CONTROLS AND DISPLAY
HOT KEY
Figure 2-8
Hot Key Menu 1 of 2
Page 2-12
DESCRIPTION
1/2
Hot Key Menu selection
MIN
Enables and displays or
disables and hides Minimums
Alerter 1 (see Section 4.2.3.4.)
OPTIONS
1/2
Hot Key Menu 1 of 2 4
2/2
Hot Key Menu 2 of 2 4
MIN
Minimums displayed and
alerter enabled 1
MIN
Minimums alerter Off
360
360° Compass Mode
ARC
ARC Compass Mode
360 / ARC
Toggles between 360 and ARC
modes of Navigation Display
(see Section 4.4.1.)
GPSS
GPSS On
GPSS 3
Toggles between GPS Steering
(GPSS) Mode and HDG mode
for Autopilot/Flight Director 3
(see Section 4.7.1.)
GPSS
GPSS Off, HDG mode active
BARO
BARO adjustment on
BARO
Toggles between BARO
adjustment on or off for
Barometric Pressure setting
BARO
BARO adjustment off
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
DESCRIPTION
2/2
Hot Key Menu selection
OPTIONS
2/2
Hot Key Menu 2 of 2 4
1/2
Hot Key Menu 1 of 2 4
CHAPTER 2 CONTROLS AND DISPLAY
Hot Key
No function
No function
TRFC
BARO
Displays Traffic Overlay
(see Section 4.8.1.2.)
Toggles between BARO
adjustment on or off for
Barometric Pressure setting
TFCN
Normal Filter
TFCU
Unrestricted (No Filtering)
TFCA
Above Filter
TFCB
Below Filter
TRFC
Traffic Overlay Off
BARO
BARO adjustment on
BARO
BARO adjustment off
Figure 2-9
Hot Key Menu 2 of 2
Table 2-3
Hot Key Descriptions
1. When the Minimums field is first enabled with the MIN Hot Key, the MIN value is immediately available for editing
2. Flight plan legs and waypoints display available in all installations including a GPS navigator. Basemap display of nearby
waypoints available with all ARINC 429 GPS navigators and some RS-232 GPS navigators.
3. GPSS available only with ARINC 429-based navigators
4. Traffic Overlay is available when the Evolution Hazard Awareness (EHA) option and compatible hazard awareness sensors are
installed. Hot Key is blank when function is not available
5. The Traffic Filter Hot Key is blank when the Traffic Overlay function is not available
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Page 2-13
CHAPTER 2 CONTROLS AND DISPLAY
2.2.4. MENU
The MENU Button is used to access the Menu to change options, and to change the
display brightness.
2.2.4.1. Using the Menus
Figure 2-15
Menu Navigation Mode
Press the MENU Button to activate the Menu (Ref. 3). The current Menu page name is
shown on the bottom center of the Navigation Display. Directly below the Menu Page
name is a segmented Menu Page Bar, giving a graphical representation of the current
page relative to the total number of Menu pages. The current Menu Page number is
shown in the lower right corner of the Navigation Display.
Menu Page 1, General Settings A, is the one most commonly used in flight. It allows
the pilot to enable or disable the AUTO COURSE SELECT mode, and to choose CDI type
for the ARC Compass mode. The other Menu Pages are used for barometric pressure
and OAT units of measure settings, Auto Range, Vspeeds and map customization, PFD
power management, product version information, and information and option settings,
relative to your specific equipment and installed options.
The Menu operates either in the Navigation or Edit mode, as indicated by the label
directly above the Right Knob. When the MENU Button is first pressed, the Menu is in
the Navigation mode, indicated by the magenta label SEL PAGE directly above the Right
Knob (Figure 2-15). When in the Navigation mode, rotating the Right Knob navigates
through the Menu Pages. Rotate the Right Knob clockwise to advance to the next Menu
Page, counterclockwise to return to the previous page.
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Figure 2-16
Menu Edit Mode
When you are finished changing Menu options, press the MENU Button to exit
Menu Options
Menu Page number and mode (Navigation mode shown)
Menu Page Name
Menu Page graphical bar
Brightness Control (see Section 2.2.4.2.)
Figure 2-17
Menu
Table 2-4 Menu
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CHAPTER 2 CONTROLS AND DISPLAY
Each Menu Page has up to five selectable options, each adjacent to one of the five
Hot Keys which double as Menu Keys when the Menu is active (Item 1 of Figure 2-17
and Table 2-4). After navigating to the Menu Page containing the option you want to
change, press the Menu Key adjacent to that option label, which initiates the Menu’s
Edit mode. When the Menu is in the Edit mode, the label, EDIT VALUE, is shown above
the Right Knob in magenta (Figure 2-16), and the label of the item selected for editing
is also shown in magenta. Rotate the Right Knob to change the value of the selected
item. When finished, either select another displayed Menu option to change , or press
the Right Knob to exit the Edit mode and return to Navigation mode to select another
Menu Page.
CHAPTER 2 CONTROLS AND DISPLAY
The MENU text will display in one of the four colors listed and described in Table 2-5.
Figure 2-18 Menu Text - Editable
Figure 2-19
Menu Text - Enabled for Editing
DISPLAY TEXT
DESCRIPTION
DISPLAY
WHITE
Editable option
Figure 2-18
Editable option enabled
Figure 2-19
Status Only
Figure 2-20
Disabled (Not available for selection or editing)
Figure 2-21
MAGENTA
GREEN
Figure 2-20
Menu Text - Status Only
GRAY
Table 2-5
Menu Text
Figure 2-21
Menu Text - Disabled
NOTE
These steps are provided as a basic overview. Each Menu command is covered in detail in
Chapter 5.
Access To and Navigation Within the Menu
1.
2.
3.
Press the MENU Button. The Menu displays on the Navigation Display
adjacent to the Hot Keys (Figure 2-22).
Rotate the Right Knob to navigate through the different pages of the
Menu. Rotating the Right Knob clockwise advances the Menu Pages,
counterclockwise returns to previous pages.
Press the MENU Button to exit.
Figure 2-22
Menu Display
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1.
2.
3.
4.
5.
6.
Press the MENU Button.
Navigate to the desired Menu Page.
Press the Menu Key of the desired option. The Menu label turns magenta, and
the EDIT VALUE label displays above the Right Knob (Figure 2-23).
Rotate the Right Knob to the desired value.
Press the Right Knob to return to Menu navigation mode.
Press the MENU Button to exit.
NOTE
Pressing the Right Knob returns to Navigation mode
and allows selection of other menu options on different
pages. Pressing another menu key on the current menu
page saves any changes made and activates the newly
selected option for editing.
Figure 2-23
EDIT VALUE Displays
Above Right Knob
NOTE
Upon reaching the end of a list of editable menu
options, continued rotation of the knob will not result in
the continuous wrapping through the available editable
menu options. Spinning the knob fully clockwise will
go to the last menu page, while spinning the knob fully
counterclockwise will go to the first menu page.
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CHAPTER 2 CONTROLS AND DISPLAY
Edit Menu Items
CHAPTER 2 CONTROLS AND DISPLAY
2.2.4.2. Display Lighting
When the MENU Button is pressed and the Menu is active, the Left Knob can be used to
adjust the display brightness.
By default, the LCD brightness operates in AUTO mode, and is adjusted based on
photocell sensing of ambient lighting conditions. When the MENU is active and the
LCD is in the BRT AUTO mode, the word AUTO and a brightness level of 1-100 will be
displayed in green above the Left Knob (Figure 2-24).
Figure 2-24
Display Brightness in BRT AUTO Mode
Figure 2-25
Display Brightness in BRT ADJUST Mode
NOTE
The BRT AUTO display brightness level is determined
by the amount of light detected by the photocell on
the front of the PFD. If a light is used to illuminate the
instrument panel, the photocell will respond, resulting
in a bright display. When this happens, use the manual
BRT ADJUST mode to reduce the brightness..
Page 2-18
To override the AUTO brightness setting, press the Left Knob once to switch to the BRT
ADJUST mode, and then rotate the Left Knob to set the brightness to the desired level.
To return to AUTO brightness control, press the Left Knob again (Figure 2-25).
LCD MODE
DESCRIPTION
DISPLAY
Automatic
BRT AUTO
LCD backlight intensity is automatically adjusted based
on the ambient lighting conditions sensed by the
Automatic Dimming Photocell. The maximum intensity
in Automatic mode is 70%.
Figure 2-24
Manual
BRT ADJUST
Allows the pilot to adjust the display brightness from
1-100%
Figure 2-25
Table 2-6
Brightness Control
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CHAPTER 2 CONTROLS AND DISPLAY
2.2.5. Range Buttons
When the MAP is enabled, the RNG (Range) Button is used to zoom the map in or out.
Press the RNG (+) Button to increase map range. Press the RNG (-) Button to decrease
map range. Additionally, an Auto Range control feature is available.
Pressing and holding either the RNG (+) or (-) Button will cause the map range to scale
continuously to its maximum or minimum range, respectively. When the map range is
at its maximum or minimum setting, release and then press and hold the RNG Button
again to activate the Auto Range control mode (see Section 4.4.12.1. for more details).
2.2.6. REV Button
The red REV Button on the PFD can be used to override automatic power control in
abnormal or emergency situations (see Chapter 6, Section 6.4. and Figure 6-29 for
more details).
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CHAPTER 2 CONTROLS AND DISPLAY
2.3. Display
The PFD replaces the existing Attitude Indicator and HSI or DG in the center of the
primary flight instrument cluster. Like the instruments it replaces, the top half presents
an Attitude Display and the bottom half contains a Navigation Display (Figure 2-26).
Between the two halves is the Data Bar. The Data Bar contains a dedicated display of
real-time winds, Outside Air Temperature (OAT), True Airspeed (TAS), and GPS Ground
Speed (GS).
Attitude Display
Data Bar
Navigation Display
Figure 2-26
EFD1000 C3 Pro PFD Display Areas
Page 2-20
Unlike the mechanical indicators it typically replaces, the PFD can also display all the
data provided by the remaining four instruments in the six pack (airspeed, altitude,
turn and slip, and vertical speed), and much more. Concentrating all primary flight
information onto a single instrument directly in front of the pilot improves instrument
scan and reduces pilot workload, thereby enhancing safety, especially in busy phases
of flight. Additionally, analog backup instruments can be retained in the pilot’s primary
field of view, and should be included in the instrument scan to cross-check indications
of both the primary (EFIS) and backup (analog) instruments.
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This section gives an overview of the main display elements and features. For more
details, see Chapter 4, Reference Guide.
CAUTION
2.3.1. Cleaning the Display Screen
The PFD Display Unit has an LCD screen that is prone to damage from scratches,
smudging, and clouding caused by the use of improper cleaning agents and abrasive
cloths. Exercise care when cleaning, using the following tips:
Use caution when using isopropyl alcohol as it is
flammable. Using any other chemicals or materials
voids the warranty.
r Only clean the display when the PFD is off.
r Use a clean, soft, lint-free cloth dampened with a 50/50 solution of isopropyl
alcohol and water, a pre-moistened lens cleaning tissue, such as Bausch &
Lomb Sight Savers®, or a cleaning solution made especially for LCD displays.
r Never spray any cleaning solutions directly onto the screen; spray it into the
cleaning cloth.
r Gently wipe the screen in a circular motion. Do not press hard on the screen.
r Remove all excess moisture to prevent damage to the display.
r The display should be dry before turning on the PFD.
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CHAPTER 2 CONTROLS AND DISPLAY
The PFD generally follows standard display conventions for Electronic Flight Instrument
Systems (EFIS), so a pilot with some experience and familiarity with other EFIS PFDs
will usually transition quickly to using the EFD1000. Pilots for whom the EFD1000 PFD
is their first real exposure to EFIS and glass cockpit flying should get some transition
training from a certified instrument flight instructor (CFII) with EFIS experience. Pilots are
also encouraged to study some of the excellent publications and training videos now
available to help with the transition.
CHAPTER 2 CONTROLS AND DISPLAY
2.3.2. Attitude Display
The Attitude Display includes an Attitude Director Indicator (ADI) with a singlecue Flight Director command V-bars (when connected to a compatible autopilot),
an Airspeed tape, an Altimeter tape, an Altitude Alerter, Radio Altitude, approach
minimums annunciations, and approach course and glide slope indicators (Table 2-7
and Figure 2-27), (see Chapter 4, Reference Guide for more details).
The Airspeed and Altitude tapes are the most obvious differences from a mechanical
ADI. These tapes are common on most EFIS PFDs and will be immediately familiar to
pilots with EFIS experience. Pilots without prior EFIS experience may need some training
and experience to become to get comfortable with the Airspeed and Altimeter tapes as
their primary references.
In single-display PFD installations, where the mechanical airspeed indicator and
altimeter remain in their original locations, transitioning pilots can use either their
familiar mechanical instruments or the PFD tapes for airspeed and altitude references.
Many pilots new to EFIS quickly find themselves relying on the tapes within a flight or
two. Should the tapes prove distracting, the pilot can remove them from the display
by disabling them in the Menu. (Page 1, GENERAL SETTINGS A — single display
installations only).
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27
16
Attitude Display
27
Decision Height Annunciation2
17
Aircraft Reference Symbol
28
Selected Minimums Field
18
Single-Cue Flight Director1
29
Radio Altitude
19
Roll Pointer
30
MINIMUMS Marker
20
Slip/Skid Indicator
31
LDI Navigation Source Indication
21
Altitude Tape
32
Airspeed Tape
22
Selected Altitude Field
33
Selected Airspeed Field
23
Altitude Alerter
34
Airspeed Bug
24
Numerical Altitude Value,
Altitude Drum/Pointer
35
Numerical Airspeed Value, Airspeed
Drum/Pointer
29
25
Altitude Trend Vector
36
Vertical Deviation Indicator (VDI)
31
26
Altitude Bug
37
Lateral Deviation Indicator (LDI)
23
19
20
21
32
30
16
Table 2-7
Attitude Display Components
22
35
18
24
17
25
36
34
28
26
30
37
Figure 2-27
Attitude Display Components
1. With compatible autopilots
2. With compatible radar altimeters
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CHAPTER 2 CONTROLS AND DISPLAY
33
ATTITUDE DISPLAY
CHAPTER 2 CONTROLS AND DISPLAY
2.3.2.1. Attitude Director Indicator (ADI)
The Attitude Director Indicator (ADI) features a conventional blue (sky) over brown
(ground) background, with a white horizon line dividing the two areas. A triangular
Aircraft Reference Symbol (Ref. 17) is in a fixed position and shows aircraft attitude
relative to the horizon.
The pitch scale (or ladder) indicates degrees of nose up (blue) or nose down (brown)
pitch relative to the apex of the aircraft symbol. Minor pitch marks are shown every
2.5º up to +/-20º of pitch, with major pitch marks every 10º up to +/-90º of pitch. The
distance between pitch marks is greater than on most mechanical attitude indicators,
making it easier for the pilot to fly more precise pitch attitudes.
At extreme pitch attitudes (above 30º nose up or below 25º nose down), red Unusual
Attitude Recovery chevrons come into view, pointing towards the horizon or ground
as applicable (see Chapter 4, Section 4.2.1.2. Pitch Scale). At extreme pitch attitudes,
some sky (blue) or ground (brown) will always be displayed to help maintain situational
awareness, even though the horizon line may be off-scale.
Figure 2-28
Slip/Skid
At the top of the ADI are the roll scale, roll pointer, and slip/skid indicator (Figure 2-28).
The roll scale is indicated by tick marks at 10º, 20º, 30º, 45º, and 60º on both sides of the
zero roll inverted solid white triangle. The 45º marks are represented as hollow triangles.
Slip/skid is indicated by the lateral position of the white rectangle under the roll pointer.
One rectangle width is equivalent to one ball width of a conventional inclinometer.
Figure 2-29
Flight Director
Page 2-24
When connected to a compatible autopilot system, the PFD will display a single-cue
Flight Director (Figure 2-29). The Flight Director command bars visually represent the
lateral and vertical steering cues transmitted to the PFD by the autopilot. When the FD
output from the autopilot is unavailable or invalid, the FD Command Bars are removed
from the display.
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CHAPTER 2 CONTROLS AND DISPLAY
2.3.2.2. Airspeed Tape and Bug
Airspeed is indicated by a moving airspeed tape against a fixed position airspeed
pointer, shown on the left-hand side of the Attitude Display (Figure 2-25). A numerical,
rolling drum readout indicating airspeed values to the closest one knot or mile per hour
is provided adjacent to the fixed pointer. Tick marks are provided on the airspeed tape
every 10 knots (or mph, if so configured). Airspeeds between 20 kts (23 mph) to 450 kts
(518 mph) are displayed. Outside of this range, the airspeed value is dashed.
Color speed bands are displayed on the indicated airspeed tape, corresponding to the
color arcs found on a mechanical airspeed indicator.
Color speed markers are also displayed on the indicated airspeed tape, corresponding
to the markers found on traditional airspeed indicators. All aircraft have a red line for
aircraft never-exceed speed (Vne). Multi-engine aircraft will usually also have another
red line for single-engine minimum control speed (Vmc), and a blue line for singleengine best rate of climb speed (Vyse). If the aircraft manufacturer has published an
initial flap extension speed, a white triangle will be presented on the airspeed tape at
this speed.
Figure 2-30
Airspeed Tape
Redline or Barber Pole airspeed limits that vary with pressure altitude can be displayed
when configured by the installer. The colors are configured to correspond with your
aircraft’s approved markings on the mechanical airspeed indicator.
Textual Vspeed markers can also be shown on the airspeed tape (e.g., Vx, Vy, Va, etc.).
These are typically programmed at installation, and (if left unlocked during installation)
may also be adjusted by the pilot. Vspeed display can be enabled or disabled by the
pilot from Page 1 of the Menu (see Chapter 5).
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CHAPTER 2 CONTROLS AND DISPLAY
The pilot can set a target airspeed using the Left Knob (see Section 4.2.2.1.). The target
airspeed is shown on the Airspeed Tape as an Airspeed Bug with its setting displayed
numerically above the Airspeed Tape (Figure 4-10 and Figure 4-11). The Airspeed
Bug and numerical value are for visual reference only, to help the pilot maintain a target
airspeed; there is no alerting for deviations from the target.
Figure 2-30a
Mach Number Display
2.3.2.2.a. Mach Number Display for Mmo Aircraft
The Mach number for Mmo aircraft is displayed in the Data Bar (Figure 2-30a). The
Mach number can be configured to be displayed whenever the aircraft is above the
selected transition altitude or above a selected Mach number.
When the configuration is set to ALTITUDE transition, the TAS indication will be
replaced by the Mach number whenever the aircraft is above the selected transition
altitude.
When the configuration is set to SPEED transition, the TAS indication will be replaced
by the Mach number whenever the aircraft is above the selected transition Mach
number (see Chapter 5, Table 5-2 for MACH Display setting options).
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CHAPTER 2 CONTROLS AND DISPLAY
2.3.2.3. Altitude Tape, Altitude Alerter, and Vertical Speed
Altitude is indicated by a moving altitude tape against a fixed position altitude pointer
(Figure 2-2, No. 21, 24), shown on the right-hand side of the Attitude Display
(Figure 2-31). A numerical rolling drum readout indicating altitude values to the closest
20 feet is provided adjacent to the fixed pointer. When climbing or descending, a
magenta Altitude Trend Vector displays above or below the altitude pointer, indicating
the altitude that will be reached in six seconds if the current rate of climb or descent is
maintained.
Minor tick marks are provided on the tape at 20-foot intervals, and major tick marks are
provided at 100-foot intervals. The thousand and ten-thousand digits are larger than
other digits on the tape. Negative altitudes are indicated by a “-“ sign preceding the
numerical altitude value in the drum.
The current altimeter barometric pressure setting is shown just below the Altitude tape
in the Data Bar (Figure 2-2, No. 39), and can be adjusted by pressing the BARO Hot Key
and rotating the Right Knob.
The Altitude Tape also includes a built-in Altitude Alerter, which consists of an
Altitude Bug on the Altitude Tape (Figure 2-2, No. 26), a Selected Altitude Field
(Figure 2-2, No. 22), a visual Altitude alert (Figure 2-2, No. 23), and an optional audio
alert. For more information on using the Altitude Alerter, see Chapter 3 and Chapter 4.
Figure 2-31
Altitude Tape
A Vertical Speed Indicator (VSI) is shown as a tape on the Navigation Display (Figure
2-48 and Figure 2-2, No. 57) to the right of the HSI in 360 Compass mode. A numerical
vertical rate is shown in the upper right-hand corner of the Navigation Display during
climbs and descents (Figure 2-2, No. 56). The VSI tape is not shown in ARC Compass
mode, but the numerical value display is shown in both 360 and ARC Compass modes.
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CHAPTER 2 CONTROLS AND DISPLAY
2.3.2.4. Instrument Approach Indicators
Additional indicators are shown on the Attitude Display when flying certain types of
instrument approaches. These enable the pilot to maintain a tighter instrument scan on
the ADI, reducing workload and improving safety (Figure 2-32).
A Lateral Deviation Indicator (LDI) (Figure 2-2, No. 37) is presented on the attitude
indicator whenever the pilot has selected an ILS, LOC, LOC Back Course (BC), or a GPS
approach and valid lateral course guidance is being received. The LDI’s navigation source
is annunciated to the left of the LDI (Figure 2-2, No. 31). A Vertical Deviation Indicator
(VDI) (Figure 2-2, No. 34)) is presented on the attitude indicator whenever the LDI is
shown and valid glide slope signal is being received, such as from an ILS or WAAS GPS LPV.
Figure 2-32
Instrument Approach
Indications
Whenever the lateral or vertical deviation exceeds the maximum displayable range of
LDI or VDI scale (2.5 dots), the deviation diamond turns into a hollow, ghosted image
pegged to the corresponding side. As soon as the deviation diamond comes into range,
the diamond turns solid green, making it easy to identify when the needle is “alive”.
Additionally, the pilot can pre-set the instrument approach minimums (MIN) with
the MIN Hot Key. Once the MIN data field value is set to a Decision Altitude, Decision
Height, or Minimum Descent Altitude, the PFD provides a MINIMUMS annunciation
when the aircraft reaches or descends below this altitude (Figure 2-2, No. 28).
Additionally there are three minimums markers shown on the altitude tape — a green
marker 500 feet above minimums; a hollow yellow triangle in the area from 100 feet to
200 feet above minimums; and a red and yellow marker at the programmed Selected
Minimums value (see Section 4.2.3.4. MINIMUMS Annunciation for more details).
Figure 2-33
Decision Height
Annunciation
Page 2-28
If a Radar Altimeter is installed in the aircraft and connected to the PFD, a Decision
Height annunciation (Figure 2-2, No. 27 and No. 29) will be displayed when the
aircraft descends to, or below, the selected radar altitude (Figure 2-33).
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The Data Bar visually separates the upper and lower halves of the PFD display. When
available, True Airspeed (TAS) or Mach Number, GPS Ground Speed (GS), Outside Air
Temperature (OAT), Wind Vector arrow, Wind Direction, Wind Speed, and Barometric
Pressure Setting are presented in the Data Bar (Table 2-8 and Figure 2-34).
38
43
42
41
39
40
Figure 2-34
Data Bar Components
When any of these values are not available or invalid, the corresponding data field is
dashed. If the Wind Direction and Speed are not available or invalid the Wind Direction
Arrow is removed. A GPS navigator must be connected and providing valid ground
speed and ground track to display GS and wind data (see Chapter 4, Section 4.3. for
more details).
DATA BAR
38
True Airspeed (TAS) or Mach Number
39
Barometric Pressure Setting Field
40
Wind Direction and Speed
41
Wind Direction Arrow
42
Outside Air Temperature (OAT)
43
Ground Speed (GS)
NOTE
When the winds aloft are less than 10 knots, the wind
data is not displayed.
Table 2-8
Data Bar Components
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CHAPTER 2 CONTROLS AND DISPLAY
2.3.3. Data Bar
CHAPTER 2 CONTROLS AND DISPLAY
2.3.4. Navigation Display
NOTE
The Vertical Deviation Indicator (VDI) and Lateral
Deviation Indicator (LDI) are part of the navigation
instruments and are displayed on the Attitude Display
during instrument approaches.
The lower half of the PFD is the Navigation Display (Table 2-9 and Figure 2-35), which
shows a wide range of navigation information and flight data, including:
r Horizontal Situation Indicator (HSI), with Course Pointer and Deviation
Indicator (CDI), and Heading Bug.
r 360° and ARC Compass rose display modes.
r Numeric displays of current magnetic heading, selected heading (HDG), and
selected course (CRS).
r Information about the selected CDI navigation source, or active GPS waypoint.
r Ground Track Marker.
r Vertical Speed Indicator (VSI) tape and numerical rate value.
r Rate of Turn Indicator.
r Dual bearing pointers (RMI) (360° Compass mode only).
r Situational Awareness Map display.
r Course Deviation Indicators (CDI) and Bearing Pointers, navigation source
information.
r GPS annunciations (TERM, APPR, WPT, and MSG).
r Caution annunciations for abnormal GPS status.
When connected to a GPS navigator, basic mapping can also be displayed under
the HSI, including GPS flight plan legs and waypoints, (and when connected to a
compatible GPS) Basemap data (airports, VORs, NDBs, and intersections).
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44
Navigation Display
58
Single-Line Bearing Pointer
45
Ownship Symbol
59
Single-Line Bearing Pointer Navigation
Source
46
Course Pointer
60
Single-Line Bearing Pointer Navigation
Source Info Block
47
TO/FROM Indicator
61
Double-Line Bearing Pointer
48
Rate of Turn Indicator
62
Double-Line Bearing Pointer Navigation
Source
49
Ground Track Marker
63
Double-Line Bearing Pointer Navigation
Source Info Block
50
Magnetic Heading
64
Selected CDI Navigation Source
51
Selected Course (CRS) Field
65
Selected CDI Navigation Source
Information Block
52
Selected Heading Field
66
Left Knob State
53
Heading Bug
67
Right Knob State
54
Course Deviation Scale
68
Hot Key Legend
55
Course Deviation Indicator
69
Navigation Display Range
56
Vertical Speed Numerical Value
70
Navigation Display Declutter Level
57
Vertical Speed Indicator Tape
51
65
52
50
48
46 49
53
56
68
57
47
54
45
61
58
55
44
69
70
66
60
63
59
64
62
67
Figure 2-35
Navigation Display Components
Table 2-9
Navigation Display Components
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CHAPTER 2 CONTROLS AND DISPLAY
NAVIGATION DISPLAY
CHAPTER 2 CONTROLS AND DISPLAY
2.3.4.1. Direction Indicator (Magnetic Compass)
The center of the Navigation Display is the Direction Indicator, or Magnetic Compass.
The compass always shows the current magnetic heading of the aircraft, both with a
numerical value of the current heading at the top of the display, and with a lubber line,
or pointer, to that heading on either a full or partial compass rose. This slaved compass
system compensates both for the turning and acceleration errors exhibited by wet
compasses and for precession errors found in common Directional Gyros. The pilot does
not need to make adjustments to the heading indicator during the flight.
Figure 2-36
360° Compass Mode
The Direction Indicator includes capabilities to make it an electronic Horizontal
Situation Indicator (HSI) with dual Bearing Pointers. The HSI features are explained in a
separate section below.
Compass Modes: 360º vs. ARC
The Direction Indicator can be presented in either a full 360º Compass rose mode
(shown in Figure 2-36), or in a 100º ARC mode (Figure 2-37).
The 360° Compass Mode resembles the mechanical instrument, with the ownship
position in the center of the display.
The ARC Compass Mode provides an extended forward view with the ownship position
at the bottom of the display. The ARC Compass is especially good for displaying flight
plan and basemap details.
The 360/ARC Hot Key is used to toggle the display between 360° and ARC Compass
Modes, with the current mode shown in green adjacent to the Hot Key.
Figure 2-37
ARC CDI Compass
Mode with Basemap
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Regardless of Compass Mode setting, the current magnetic heading is always shown
at the top center of the Navigation Display (Figure 2-2, No. 50 and Figure 2-38). The
HDG Bug setting is shown in the Selected Heading Field (Figure 2-2, No. 52). This field
is always visible even if the HDG Bug itself is only partially visible in ARC Compass Mode.
Similarly, on the HSI, the current Course setting (CRS) (Figure 2-2, No. 51) is always
shown, whether or not the Course Pointer itself is visible in ARC Compass Mode.
A Navigation Source Information Block (Figure 2-2, No. 65 and Figure 2-39) is
presented in the upper left corner of the Navigation Display. The Source Information
Block indicates the selected navigation source (coupled to the CDI on the PFD HSI),
and its associated mode (e.g., GPS, VOR, ILS, LOC) . Information is provided about
the selected source, including, when available, the waypoint or navaid identifier or
frequency, bearing and distance, and the estimated time to the active waypoint.
Ground Track Marker
Figure 2-38
Magnetic Heading
Figure 2-39
Navigation Source
Information Block
When the PFD is connected to a compatible GPS, a blue Ground Track Marker is
displayed on the compass rose at the value that corresponds to the aircraft’s ground
track (Figure 2-2, No. 49 and Figure 2-40).
When the Ground Track Marker is aligned with the Course Pointer on the PFD HSI, the
aircraft is tracking on, or parallel to its desired track.
To align the Ground Track Marker with the Course Pointer, turn away from the direction
in which the diamond is offset from the Course Pointer (think of it as a turn to pull the
Ground Track Marker toward the Course Pointer).
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Figure 2-40
Ground Track Marker
Page 2-33
CHAPTER 2 CONTROLS AND DISPLAY
Navigation Information
CHAPTER 2 CONTROLS AND DISPLAY
2.3.4.2. Horizontal Situation Indicator (HSI)
The traditional HSI is an instrument that combines a slaved magnetic Heading Indicator
overlaid with a rotating Course Pointer and Course Deviation Indicator (CDI). This combination
helps the pilot better visualize the aircraft position relative to the desired course. The HSI is a
vast improvement over the older, separate Directional Gyro (DG) and OBS course deviation
indicator, because the compass heading is always correct (slaved to a remote magnetic flux
detector), and the integration of the CDI onto the compass simplifies the instrument scan
and provides better situational awareness.
Pilots experienced with a mechanical HSI will find the PFD’s 360º Compass Mode immediately
familiar. In its basic form, it is just an electronic representation of a mechanical HSI. Pilots
transitioning from flying a DG and OBS should seek dual instruction from a CFII on the
differences in flying an HSI.
2.3.4.3. Course Pointer and Course Deviation Indicator (CDI) Bar
In the 360º Compass Mode, the Course Pointer and CDI resemble those of a mechanical
HSI, with an arrowhead pointing to the selected course, and a movable center bar
indicating course deviation against a scale of two dots to either side of the center. A
TO/FROM indication is shown as a triangle above (TO) or below (FROM) the ends of the
Course Deviation Indicator bar.
The ARC Compass Mode has two different CDI formats —ARC HSI Mode and ARC CDI Mode.
The ARC HSI Mode, presents a full rotating Course Pointer with CDI, which resembles that
used in the HSI in the 360° Compass Mode. The ARC CDI Mode presents a short Course
Pointer stub on the compass arc and a fixed CDI at the bottom of the display, similar to the
LDI and resembling that used in contemporary GPS navigation displays. The ARC CDI Mode
allows more open space for flight plan and basemap details. A TO indication is shown to the
left of the fixed CDI, and a FROM indication is shown to its right.
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Whenever the course deviation exceeds the maximum displayable range of 2.5 dots,
the CDI bar or deviation diamond is shown as a hollow, ghosted image pegged to the
corresponding side (Figure 2-41 and Figure 2-42). As soon as the deviation comes
into range, the CDI or diamond turns solid green, making it easy to identify when the
indicator is “alive”.
2.3.4.5. Auto Course Select
When a GPS is selected as the CDI’s navigation source, the default setting of the PFD is
Auto Course Select. When Auto Course Select is enabled, the GPS will automatically set
the Course Pointer to the current GPS course (CRS) value whenever the GPS sequences
between waypoints. This capability relieves the pilot from having to manually set the
course at each waypoint along a GPS route. When Auto Course Select is enabled, the
pilot cannot adjust the CRS value.
Auto Course Select is indicated by an inverse A on a green background, adjacent
to both the numerical CRS value and the CRS Left Knob State. (Figure 2-43 and
Figure 2-44).
If the GPS navigator enters the OBS or HOLD mode, Auto Course Select is automatically
disabled on the PFD until the GPS navigator resumes waypoint sequencing. The pilot
can disable Auto Course Select from Page 1 of the Menu.
Figure 2-41
Off Scale CDI Bar
Figure 2-42
Off Scale Deviation Diamond, ARC CDI Mode
Figure 2-43
Auto Course Indication on CRS Field
Figure 2-44
Auto Course Indication over Left Knob
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Page 2-35
CHAPTER 2 CONTROLS AND DISPLAY
2.3.4.4. Deviation Off Scale Indication
CHAPTER 2 CONTROLS AND DISPLAY
2.3.4.6. Bearing Pointers
The Single- (Figure 2-2, No. 58) or Double-line (Figure 2-2, No. 61) Bearing Pointers
can be overlaid on the HSI (Figure 2-45). Use the Lower Left and the Lower Right
Source Select Buttons (Figure 2-2, No. 12 and No. 10) to select the nav sources for the
Bearing Pointers, or select none (blank) to remove a Bearing Pointer from the display.
Bearing Pointers always point to a VOR or waypoint. When coupled to a VOR source,
the tail of the Bearing Pointer indicates the VOR radial on which the aircraft is currently
located. Bearing Pointers are excellent tools for identifying crossing radials, flying DME
arcs, and improving situational awareness.
Bearing Pointers are only available in the 360° Compass Mode. Any available navigation
source may be coupled to either Bearing Pointer. If coupled to a source that does not
provide angular bearing data, such as a localizer, the Bearing Pointer is not shown, and
the source is slashed as invalid.
Figure 2-45
BRG#1 Set to GPS1 TAKLE (Single Line Bearing Pointer)
Page 2-36
Each Bearing Pointer has an associated Source Information Block that displays
information about the source of the Bearing Pointer data. This may include distance
to station (if coupled to a GPS waypoint) and either the station identifier or the tuned
frequency for a VOR. This information is only presented when it is reported to the PFD
by the connected equipment.
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A Rate of Turn Indicator (Figure 2-2, No. 48) with a range of 0 to 6 degrees per second
is provided for both the 360 and ARC Compass Modes. The indicator consists of a
curved white tape that extends from the Magnetic Heading’s lubber line and in the
direction of the turn, along the outer curve of the compass card.
Figure 2-46
Rate of Turn Indicator, Rate Shown >6º/second
The Rate of Turn Indicator features an outer thick white tick mark for a Standard Rate
turn, and an inner thin white tick mark for Half-Standard Rate turns. A Standard Rate,
two-minute turn equals 3 degrees per second. When the rate of turn exceeds 6 degrees
per second, an arrowhead is added to the end of the tape to show that the rate of turn
has exceeded the limits of the indicator (Figure 2-46).
2.3.4.8. Vertical Speed Indicator (VSI)
Whenever the vertical speed exceeds +/- 100 feet per minute (FPM), the vertical
speed is indicated by a rising/sinking white vertical tape and associated scale markers
immediately to the right of the compass rose (Figure 2-2, No. 57 and Figure 2-47).
A numerical value of the aircraft’s vertical speed is shown directly above the tape, in the
upper right-hand corner of the Navigation Display (Figure 2-2, No. 56). Rates of up to
±2,000 FPM are indicated by the tape, while the numerical value will display rates of
up to ±9,990 FPM. A white triangle caps the tape whenever rates exceed ±2,000 FPM
(Figure 2-48). The vertical speed numerical value will be dashed whenever the vertical
speed exceeds +/- 10,000 FPM. In the ARC Compass Mode, only the numerical vertical
speed value is presented.
Figure 2-47
VSI Tape Showing 370 FPM Descent
Figure 2-48
VSI Tape Capped, Digital Value
Showing 2,100 FPM Climb
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CHAPTER 2 CONTROLS AND DISPLAY
2.3.4.7. Rate of Turn Indicator
CHAPTER 2 CONTROLS AND DISPLAY
2.3.4.9. Situational Awareness Map
When the PFD is connected to a compatible GPS navigator, basemap symbols can be
displayed underneath the Direction Indicator in either 360º or ARC Compass Modes.
Most GPS navigators output data for the PFD to display the GPS flight plan legs and
waypoints. The active GPS flight plan leg, waypoint, and its identifier are shown in
magenta. Other waypoints and legs are shown in white.
Figure 2-49
20nm Range at Declutter Level 3
Figure 2-50
Declutter Level 4
Figure 2-51
Declutter Level 3
Figure 2-52
Declutter Level 2
Figure 2-53
Declutter Level 1
Some GPS navigators (typically those using the ARINC 429 data protocol, such as
the Garmin 400/500 series) output basemap data (e.g., airports, VORs, NDBs, and
intersections). Often, these GPS navigators also display curved flight paths, such as arcs,
course reversals, and holding patterns.
The basemap is always oriented with magnetic North heading up and centered so that
the current aircraft position coincides with the aircraft ownship symbol. These basemap
symbols underlay all other instruments and annunciations in the Navigation Display.
The Map Declutter Settings can be found in the 360 or ARC MAP SETTINGS page of
the Menu. Pressing the desired 360 or ARC DCLTR LVL Menu Key and rotating the Right
Knob will select Declutter Levels 4, 3, 2, 1, or OFF (Figure 2-50, 2-51, 2-52, 2-53, 2-54).
The map display range is controlled by the RNG Button (Figure 2-2, Ref. 2), enabling
the pilot to zoom in or out on the map. Automatic declutter logic changes the map
features displayed depending on the selected map range.
The current range and declutter level map settings are shown in the lower left-hand
corner of the navigation display (Figure 2-49). The map range is displayed in nautical
miles, measuring the distance from the ownship symbol to the outside edge of the
compass rose. The map declutter level is indicated by one to four green parallelograms
below the range value. More parallelograms indicate that more basemap features are
displayed.
Figure 2-54
Declutter Level 0 (Off)
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Chapter 3
Flying the PFD
This chapter provides an overview of flying the PFD on an IFR
cross-country flight, explaining how to access and change the
necessary settings of the PFD. Refer to Chapter 4 for detailed stepby-step instructions for all PFD functionality.
While you can jump right in to using the PFD with this chapter, it may be
helpful to first read Chapter 2 to become more familiar with the controls,
operating logic, and display elements of the PFD.
The PFD is a powerful Electronic Flight Instrument System (EFIS), offering the same
capabilities and features found in larger glass cockpit systems in airliners, business
jets, and newer general aviation aircraft. It is capable of far more than the analog
instruments it typically replaces. It will take some time and experience to master all of its
advanced capabilities, especially if this is your first exposure to flying an EFIS and a glass
cockpit. Nonetheless, in its most basic configuration, the PFD will look immediately
familiar to anyone accustomed to flying mechanical instruments, and its basic operation
is very similar and intuitive.
Before flying your new PFD on an actual IFR flight, first be sure to spend some time
with your installer to understand exactly how your aircraft is configured. It’s also
recommended to get some dual instruction and practice in VFR conditions until you are
comfortable with how the PFD performs and integrates with the other avionics in your
airplane.
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
FEATURE
SETTING
SETTING
Set as desired
Barometric
Pressure
(BARO) Hot
Key
Allows for BARO
adjustment
Map RNG
(Range)
Buttons
Set as desired
Lower Left
and Right
Buttons,
Bearing
Pointers Nav
Source
Select as desired
Barometric
Pressure
Setting Field
on/off
CDI
Navigation
Source Select
Select as desired
Heading Bug
Value
Set as desired
Selected
Course (CRS)
Field
Set as desired
Compass
Mode (360°
or ARC) Hot
Key
Set as desired
MINIMUMS
Setting
Set approach
minimums
GPS Steering
(GPSS) Hot
Key
on/off
Selected
Airspeed
Set as desired
Selected
Altitude
Figure 3-1
Basic PFD Settings
FEATURE
Table 3-1
Basic EFD1000 Settings
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3.1. Quick Controls Overview
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Chapter 2 explains the PFD controls in detail. The following is a quick summary:
Knobs
(see Chapter 2, Section 2.2.1 for details)
The Left or Right Knob each has a Home State, to which it returns after 10 seconds of
inaction. The Left Knob is the CRS knob, and the Right Knob is the HDG knob.
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The current function of each knob is shown by its State, displayed
immediately above the knob. If the Knob State is shown in magenta, turning
the knob will change the value of the function shown. If the legend is shown
in cyan or green, turning the knob will have no effect.
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From the Home State, rotating the knob one click or pressing the knob once
will “wake up” and enable the current function to be set (Knob State color
changes from cyan to magenta). Successive presses of the knob will cycle
through the functions that the knob can control. When the function you want
to change is shown in magenta, turning the knob will change its value.
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The Left Knob sets the Course Pointer (CRS, except when Auto Course Select
is enabled) and Indicated Airspeed Bug (IAS).
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The Right Knob sets Heading (HDG), Selected Altitude (ALT), Barometric
Pressure Setting (BARO Hot Key selected), and Approach Minimums (MIN Hot
Key selected).
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Pressing and holding a knob syncs the selected function.
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Page 3-3
Navigation Source Buttons
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
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Three Buttons at the bottom of the display couple the available navigation
sources to the CDI and the Bearing Pointers.
The Center Button - CDI Navigation Source Select Button (Figure 2-2, Ref.
11) selects the nav source to couple to the CDI and to drive the autopilot (if
installed).
The Lower Left Button and Lower Right Button (Figure 2-2, Refs. 12 and
10) select which nav source couples to each of the two Bearing Pointers or
none to hide the bearing pointers (see Chapter 2, Section 2.2.2 for details)
Hot Keys
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Page 3-4
The five keys on the lower right-hand side of the display are Hot Keys,
the function of which is shown by the legend on the screen immediately
adjacent to each key.
The current status of each Hot Key is shown by the legend in a green label
and dark blue letters if active or in a blue label and green letters if inactive.
Each press of a Hot Key will either toggle its function on or off, or will cycle
among available settings (see Chapter 2, Section 2.2.3 for details).
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3.2. Example Flight Scenario
Our aircraft for this example flight scenario is a Beechcraft Baron P58TC, equipped with
dual Garmin GNS-430W WAAS GPS/Nav/Comm and the Bendix/King KFC-200 Autopilot.
The C3 PFD is configured with Auto Course Select enabled, BARO setting in inches Hg,
Vspeed text markers displayed, ARC compass mode in CDI, and Basemap configured
with its default settings.
NOTE
The tasks and procedures you will use in your airplane
will vary depending on your aircraft and equipment,
and on how they are configured and integrated with
the PFD in your specific installation
The Garmin 430Ws are configured with ILS CDI Capture set to AUTO, meaning that when
an ILS approach is loaded and active in the GPS, and the aircraft is established inbound
to the FAF, the GNS-430W will automatically switch its CDI output from GPS to the VHF
localizer frequency. The PFD will follow this switch on its CDI Navigation Source Select,
automatically changing from GPS1 to VLOC1.
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
This section will walk you through using the PFD on an IFR flight from Albuquerque
International Sunport (KABQ) to Reno/Tahoe International Airport (KRNO), flying Victor
airways to the ILS16R approach into KRNO. This scenario uses one pilot’s technique for
setting up the navigation instruments, but there are many other valid possibilities. Use
whatever techniques work best for you.
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
3.2.1. Pre-Departure (Startup)
Once the pre-flight inspections and checklists are complete, start the engines and turn
on the PFD Master switch.
When power is applied to the PFD, the bezel backlighting illuminates and within a few
seconds the PFD splash screen displays while it initializes and the AHRS data is validated
(Figure 3-2).
As the software initializes and the PFD warms up, the Attitude and Navigation Displays
will appear first (typically within 20-30 seconds), with red X’s showing for the airspeed
and altitude tapes and the CDI Navigation Source is slashed as invalid (Figure 3-3).
Depending on how cold the aircraft is, the air data sensors will quickly warm to
operating temperature, and the airspeed and altitude tapes will appear. At this point,
the red X’s will disappear and the PFD is ready.
NOTE
Figure 3-2
EFD1000 PFD Initializing
Start-up times for the PFD are highly dependent on aircraft temperature. In extremely cold
weather, when the aircraft has been cold soaked, it may take several minutes (usually no
more than five) for the PFD to be fully operational. On the second or third flight of the day,
and/or on very hot days, the PFD may initialize within 30 seconds or less.
Figure 3-3
CDI Navigation Source
Slashed Invalid
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Figure 3-4
CDI Source Slashed Invalid
NOTE
GPS navigators will not output valid navigation information until programmed with
an active flight plan or direct-to waypoint, and thus will be treated as invalid by the
PFD and cannot be selected as a CDI or Bearing Pointer navigation source until they are
programmed with an active waypoint.
Figure 3-5
GPS Caution Annunciations
When the PFD is interfaced to a Garmin 4xx /5xx or 4xx(W)/5xx(W) navigator, and the
navigator’s Instrument Panel Self-Test page is displayed, the indicated lateral deviation
can be verified on the PFD’s CDI. This confirms that a valid digital signal has been
received from the Garmin system.
The interface between the Garmin 4xx/5xx and PFD system should be considered fully
operational once the presence of the digital signal is confirmed. If there is no GPS failure
annunciation on the PFD, the lateral deviation indication on the PFD HSI correlates to
the indication on the Garmin 4xx/5xx Instrument Panel Self-Test Page, then the digital
signal is confirmed and the interface is operational.
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NOTE
The graphics used in this chapter illustrate the
descriptions of the features and tasks, but do not
necessarily correspond to the values associated with
this example flight scenario.
Page 3-7
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Turn the Avionics Master ON. Until the navigation radios are operational, the CDI
Navigation Source annunciations on the PFD is slashed as invalid (Figure 3-4), and
the GPS1, GPS2 caution annunciations on the left (Figure 3-5), and INTEG caution
annunciated on the right edge of the display. The CDI Navigation Source Select will
default to VLOC1 the first time the PFD is turned on. After that the CDI Navigation
Source Select will display the last used CDI Source. Once the nav radios have warmed
up, the red line will be removed from the CDI Navigation Source annunciation.
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
WARNING
Whenever there is a new altimeter setting, set both the
PFD and the standby altimeter.
The navigator’s indicated lateral and vertical deviations cannot be compared to the
PFD Lateral Deviation Indicator (LDI) and Vertical Deviation Indicator (VDI) because the
4xx/5xx Instrument Panel Self-Test Page does not send an Approach Mode signal to the
PFD.
Once the radios are available, we listen to the ATIS and learn that the local altimeter
setting is 30.15 and that Runway 8 is in use for departures.
First set the standby altimeter to 30.15, then set the PFD barometric pressure setting.
Set the Barometric Pressure
Figure 3-6
BARO Setting Field
Enabled
Page 3-8
1.
Press the BARO Hot Key. The BARO label above the Right Knob and Barometric
Pressure Setting Field appear in magenta - enabled for editing (Figure 3-6).
2.
Rotate the Right Knob clockwise to increase or counterclockwise to decrease
the value of the Barometric Pressure Setting Field.
3.
Once the correct value is selected, press the BARO Hot Key or any knob,
button/key to exit the BARO function. After 10 seconds of inaction or if any
other button/key is pressed, the BARO function is disabled and the Right
Knob returns to normal operation (Figure 3-7).
Figure 3-7
BARO Setting Field
Disabled
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Next, since we’ll be departing from Runway 8, we set our Heading Bug to runway
heading, 080°.
1.
Press or simply rotate the Right Knob to edit the HDG field. The HDG label
above the Right Knob and the HDG field are both rendered in magenta for
editing (Figure 3-8). The Heading Bug is also be rendered in magenta, and a
dashed magenta line will extend from the ownship symbol to the Heading
Bug to make it easier to see the bug position.
2.
Rotate clockwise to increase, or counterclockwise to decrease, the HDG value.
Once the correct heading is selected and after 10 seconds of inaction, the
field is disabled, and the label and field are rendered in cyan (Figure 3-9).
We call Clearance Delivery to pick up our IFR clearance. It is:
Figure 3-8
Selected Heading Field Enabled
Baron N1234 is cleared to the Reno/Tahoe Airport via the LARGO2 departure,
Zuni (ZUN) transition, then as filed; Maintain 7,000; Expect 10,000 in five minutes;
Departure frequency is 127.4; Squawk 0123.
We copy and read back our clearance, and then set up our avionics for an instrument
departure. We set our transponder code and comm radio frequencies. Then we enter
our flight plan into GPS1, load the LARGO2 departure, crossfill into GPS2, and activate
the flight plan. We make sure the CDI Button on the GNS-430W is set to GPS.
The LARGO2 departure calls for vectors to our route. From past experience, we expect
to be vectored past ABQ VOR, and then given a vector to join the departure on the
ABQ-to-ZUN leg (a 255º course). While we navigate with GPS, for situational awareness,
we tune those first two VOR fixes into our nav radios. We tune the ABQ VOR (113.2) into
VLOC1 and the ZUN VOR (113.4) into VLOC2.
Figure 3-9
Selected Heading Field Disabled
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Page 3-9
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Set the Heading Bug
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Select GPS1 as the CDI Navigation Source. Because we have enabled Auto Course
Select, the Course Pointer automatically slews to 261º (the initial course from the airport
to the first fix on the LARGO2 departure, ABQ VOR).
Select the CDI Navigation Source
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Figure 3-10
CDI Navigation Source Selection Button
Figure 3-11
Bearing Pointer Nav Source Select Buttons
NOTE
When no source is selected, only the Bearing
Pointer icon is shown above the applicable Button
(Figure3-12).
Press the CDI Navigation Source Select Button (Figure 3-10) until the desired
navigation source is shown above the Button (in this case, GPS1).
For a traditional RMI view, we could use our two Bearing Pointers to monitor our
passing the ABQ VOR and then intercepting the course to ZUN. We’d use the left,
Single-Line Bearing Pointer Source Select Button to select VOR1 (ABQ), and use the right
Double-Line Bearing Pointer Source Select Button to select VOR2 (ZUN). Since the ZUN
VOR is too far away to receive on the ground at Albuquerque, VLOC2 will be shown with
a red line through it above the Double Bearing Pointer Source Select Button, and the
Double-Line Bearing Pointer will not be displayed. But we know that the station will
be received, and the pointer will be shown, by the time we climb to our initial cruise
altitude.
Select Bearing Pointer Nav Sources
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Press the Lower Left Button (Single-Line Bearing Pointer) or the Lower Right
Button (Double-Line Bearing Pointer) until the desired navigation source is
shown above the Button (Figure 3-11).
For even better situational awareness, we choose to display the map of our flight plan
legs and waypoints. We press the MAP Hot Key to bring up the Basemap. We use the
Range Control Buttons to select the 20nm range, which will give a good perspective for
intercepting the course to ZUN. Our initial flight plan leg, from the airport to the ABQ
VOR, is shown in magenta, with subsequent legs and waypoints shown in white.
Figure 3-12
No Bearing Pointer Sources Selected
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Select Map Declutter Level
To change the Map Declutter Level
1.
Press the MENU Button and rotate the Right Knob to the 360 MAP SETTINGS
or the ARC MAP SETTINGS page.
2.
Press the DCLTR LVL Menu Key and rotate the Right Knob to select the
desired declutter level, then press MENU Button to exit.
NOTE
The Basemap symbols and flight plan legs rendered
for each of the map’s declutter levels (4, 3, 2, 1, or 0) are
based on the selected map range. These are manually
configured to display or not from the MENU. Detailed
information is provided in Chapter 5, Section 5.2.
Figure 3-13b
Declutter Level 4
Figure 3-13c
Declutter Level 3
Figure 3-13d
Declutter Level 2
Figure 3-13a
Map Declutter Icon Location
Figure 3-13
Changing the Map Declutter Level
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Figure 3-13e
Declutter Level 1
Figure 3-13f
Declutter Level 0
Page 3-11
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
The Map Declutter function can be found in the 360 MAP SETTINGS page or in the ARC
MAP SETTINGS page of the MENU (Figure 3-13). The Map Declutter Icon is located
on the bottom left of the Nav Display (Figure 3-13a) The Declutter settings can be
configured to Levels 4, 3, 2, 1, or 0 (Figures 3-13b thru 3-13f) (see Chapter 5, Table 5-9
for more details).
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Change the Map Range
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Press the RNG (Range) Buttons (Figure 3-14) UP (+) to increase the range
or DOWN (-) to decrease the range until the desired range is shown
(Figures 3-15 and 3-16).
Figure 3-14
Range Button
Ownship
Symbol
Current Range
Figure 3-15
Current Range 20nm from Ownship to Edge of Compass Rose
Page 3-12
Figure 3-16
Current Range 10nm from Ownship to Edge of Compass Rose
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Evolution Hazard Awareness and Traffic Overlay
Display the Traffic Overlay
1.
2.
3.
Display the 2/2 Hot Key menu.
Press the TRFC Hot Key to select the desired Altitude Filter. The label turns
inverse green for TFCN (Normal), TFCU (Unrestricted), TFCA (Above), and
TFCB (Below). The TFRC annunciation displays in the lower left of the display
(Figure 3-17).
Press the 1/2 Hot Key menu for access to GPSS for departure.
Figure 3-17
Traffic Overlay On
Altitude Alerter
Next, we set our assigned initial altitude of 7,000 feet in the Selected Altitude Field
which enables the Altitude Alerter. We press the Right Knob twice, changing the legend
above the knob to ALT in magenta. Then we turn the Right Knob to set 7,000. This will
help us capture and maintain our assigned altitude.
NOTE
Setting the Altitude Alerter provides visual and aural cues to help the pilot capture and
maintain target altitudes. When set to a new altitude, the Alerter will illuminate a yellow flag
adjacent to the target altitude display and sound a one-second tone; 15 seconds (or 200 feet)
before the aircraft will reach the target altitude (based on current rate of climb or descent).
The yellow flag will extinguish once the target is reached. Subsequently, if the aircraft deviates
more than 200 feet above or below the target altitude, the flag will again illuminate, and
another one-second tone will sound to alert the pilot to the deviation.
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Aspen’s Evolution Hazard Awareness (EHA) option allows a traffic system to be
connected to the PFD. This option enables traffic hazard display capability on the PFD
Navigation Display.
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Set the Altitude Alerter
1.
Press the Right Knob until ALT displays above the Right Knob and the
Selected Altitude numerical field and Bug are enabled for editing, all three
rendered in magenta (Figures 3-18 and 3-19).
2.
Rotate the Right Knob to change the value of the Selected Altitude field.
Rotate clockwise to increase, or counterclockwise to decrease, the value.
3.
Once the correct value is selected, and after 10 seconds of inaction, the field
is disabled and the label, Selected Altitude field, and Bug are rendered in cyan
(Figure 3-20).
Figure 3-18
Altitude Bug Enabled
Figure 3-19 Altitude Field Enabled
Figure 3-20
Altitude Bug Disabled
NOTE
Synchronizing the altitude sets the selected altitude to
the current altitude, see Section 2.2.1.3.
Page 3-14
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Set the Airspeed Bug
1.
2.
3.
Figure 3-22
Selected Airspeed Field Enabled
Press the Right Knob until ALT displays above the Right Knob and the
Selected Altitude Field and Bug are enabled for editing, all three rendered in
magenta (Figures 3-21 and 3-22).
Rotate the Left Knob clockwise to increase, or counterclockwise to decrease
the value of the Selected Airspeed Field.
Once the correct value is selected, and after 10 seconds of inaction, the field
is disabled, and the label, Selected Airspeed Field, and Bug are rendered in
cyan (Figure 3-23).
We plan to hand-fly the plane until reaching our final enroute altitude of 10,000 feet,
but would like to use the Flight Director (FD) (Figure 3-24). So, as part of our Before
Takeoff set-up, we press the FD Button on the autopilot mode selector, and the
magenta V-bars display on the PFD. As an easy way to give us guidance on the takeoff,
we press the Go Around Button. This commands wings level and about a 10° pitch-up
attitude, which works well for our initial climb.
Figure 3-21
Selected Airspeed Field Enabled
Now our avionics are all set, so we taxi out to the runway, do our run-up, and call tower,
ready for departure. As we taxi into position and hold on Runway 8, we verify that our
PFD compass shows 080°, lined-up with our pre-set Heading Bug. As tower clears us for
takeoff, it tells us to wait until reaching the end of the runway, and then to turn left to
heading 250°. Rotate the Right Knob to set the Heading Bug to 250°.
Figure 3-23
Selected Airspeed
Field Disabled
Figure 3-24 Flight Director V-bars
NOTE
Synchronizing the airspeed sets the selected airspeed to
the current airspeed, see Section 2.2.1.3.
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Our normal climb speed is 120 KIAS, so we set the Airspeed Bug as a reminder. To do so,
we press the Left Knob twice, until it shows IAS in magenta above the knob. Then turn
the knob until 120 shows in the Selected Airspeed Field.
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
3.2.2. Departure
As we start the takeoff roll, we note the airspeed on the PFD comes “alive” at 20 KIAS. All
indications are normal, so we continue the takeoff, rotate at 90 KIAS and fly the Flight
Director command bars at 10º pitch up with wings level. As we run out of usable runway to
land, we bring the gear up, and soon we’re over the end of the 13,800 ft. runway.
We engage HDG mode on the autopilot mode selector, and the FD commands a left turn to
our assigned 250° heading, which we have already set with the Heading Bug. Through 1,000
feet AGL, we power back and adjust the pitch attitude to maintain our target 120 KIAS climb
speed, as shown by the Bug on the airspeed tape, and set the FD pitch to that attitude.
Figure 3-25 Altitude Alerter Flag
Illuminated
Soon we hear a one-second tone and see the yellow flag appear next to our Selected
Altitude field at the top of the PFD airspeed tape (Figure 3-25). This means we are 15
seconds away from reaching our assigned altitude. We begin to shallow our climb, and level
off at 7,000 feet, engaging ALT hold on the AP/FD mode selector. The yellow Altitude Alert
on the PFD goes out as we capture and hold our altitude.
While on the 250° vector, we pass abeam the ABQ VOR. The Single-Line Bearing Pointer
points abeam, toward the VOR, and then swings behind the aircraft. We also notice that
the GPS then sequences to the next flight plan waypoint, the ZUN VOR. The PFD Course
Pointer automatically swings left to the new course, 255°, and the leg on our Basemap turns
magenta.
Albuquerque Departure now tells us to fly heading 220° to join the LARGO2 departure, and
climb and maintain 10,000. Departure also calls out slower traffic at our 10 o’clock, seven
miles, west-bound at 8,000, and asks us to expedite our climb through 8,000.
1.
2.
Page 3-16
Rotate the Right Knob to set the Heading Bug to 220°.
Press the Right Knob to activate ALT, and rotate to set 10,000 in the Selected
Altitude field at the top of the Altitude Tape.
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
Auto Course Select has already set our Course Pointer to the 255° course from ABQ to ZUN
on the LARGO2 departure, and a 220° heading sets us up for a nice intercept. We disengage
ALT hold on the autopilot, set our cruise climb attitude and power, set the V-bars to that
pitch, and initiate the climb from 7,000 to 10,000 feet. We pitch a little higher to climb at 115
KIAS through 8,000 for traffic, then lower the nose to maintain our target airspeed of 120
KIAS by reference to the Airspeed Bug.
Even though our traffic should be right ahead of us and about five miles by now, we don’t
see it out the window. But we see the traffic target on our PFD Navigation Display and
continue to monitor it even though it appears not to be a factor.
At about 9,700 feet, the Altitude Alerter tone sounds, and the yellow alert flag by the
Selected Altitude field illuminates, telling us we are 15 seconds from reaching our assigned
10,000 feet. We begin our level-off, and upon reaching 10,000 feet, engage ALT hold on the
autopilot’s mode selector.
Departure calls again to hand us off to Albuquerque Center on 133.0. As we’re tuning the
radio, we hear an alert tone. A glance at the PFD shows the Altitude Alerter flag flashing, our
altitude indicates 10,200 and climbing, and our Flight Director V-bars are commanding pitch
down. We quickly stop the climb, correct back down to our assigned altitude of 10,000, and
engage the autopilot before calling to check in with Center.
As we level out, accelerate to cruise speed, and then power back, we finally see our traffic
out the left window, same direction, now about two miles and 2,000 feet below us — just
where the traffic symbol on our PFD says it should be.
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
3.2.3. Enroute
Albuquerque Center gives us a new altimeter setting of 30.11. We set 30.11 on the
standby altimeter and then on the PFD.
r
r
Press the BARO Hot Key and rotate the Right Knob to set 30.11.
Press the BARO Hot Key, or any knob, button/key to exit.
Soon, the CDI comes “alive” and attracts our attention as it changes from hollow (Figure
3-26) to solid green (Figure 3-27) and begins to move in towards the Course Pointer as
we intercept our course. We enable GPSS to complete the intercept and steer us along
the airways all the way to Reno, and engage the autopilot.
Figure 3-26
CDI Shown Hollow at Full-Scale Deflection
Figure 3-27
CDI “Alive” and Shown Solid
Page 3-18
Engage GPSS
1.
Press the GPSS Hot Key to Enable GPS Steering (Figure 3-28).
2.
Verify indications that GPSS is now enabled on the PFD.
r
The GPSS legend adjacent to the GPSS Hot Key should be shown in
inverse green.
r
The annunciation GPSS1 (or GPSS2, depending on the selected CDI
Navigation Source), along with an inverse A, should be shown next to
the HDG reference at the top of the navigation display (Figure 3-29).
3.
Select HDG mode on the autopilot’s mode selector.
r
The Flight Director V-bars should be showing appropriate steering cues
to intercept and track the course.
4.
Engage the autopilot (if desired).
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Now that we’re established at our final cruise altitude and in the enroute phase of our
flight, we’ll switch to the ARC Compass mode of the HSI to maximize a forward view.
1.
2.
Figure 3-28
GPSS Enabled legend in Green
Press the 360 Hot Key and observe that HSI changes to its ARC Compass
mode and the Hot Key label changes from 360 to ARC.
Press the RNG Buttons to adjust the map range to suit your preference.
Figure 3-29
GPSS Enabled
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Page 3-19
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
With GPS Steering (GPSS), a compatible GPS navigator (in this case, a Garmin 430W)
drives the autopilot directly via the autopilot’s HDG mode, telling it how to bank to
stay centered on course. GPSS can drive the autopilot far more accurately than the NAV
mode (which is based on course deviation indications) because the GPS always knows
the ground track and how to adjust to maintain that track, implicitly accounting for
changing wind conditions. The GPS also includes turn anticipation based on current
ground speed and track, enabling it to turn early and roll out centered on the new
course without overshooting. As we’ll soon see when flying an instrument approach, an
autopilot with a WAAS GPS and GPSS enabled can even fly procedure turns and holding
patterns (see Chapter 4, Section 4.7.1. GPS Steering for more details).
Select a Compass Mode
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
r
Press the 360/ARC Hot Key to alternately select either the 360° (Figure 3-30)
or the ARC (Figure 3-31) Compass Mode.
We set cruise power and lean the mixture. As the airplane stabilizes in cruise, we check
the Data Bar to monitor performance. True Airspeed (TAS) is close to book performance
for this altitude and power setting. OAT is close to ISA. Winds aloft are close to forecast,
about a 30º left quartering headwind at 15 knots, so we’ll expect to gain some ground
speed due to a stronger tailwind component when we turn northwest toward Reno.
Figure 3-30
360° Compass Mode
Check TAS, GS, and winds and temperature aloft on the Data Bar (Figure 3-32).
Continuing enroute, we monitor progress along our flight plan on the extended
forward view of ARC mode, watching as GPSS keeps us exactly centered on course
through several turns on the airways.
NOTE
Each HSI Compass Mode (360 and ARC) retains its own Range and Map declutter settings
when switching between the two.
Figure 3-31
ARC CDI Compass Mode
Figure 3-32 Data Bar
Page 3-20
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3.2.4. Arrival and Approach to Landing
Reno-Tahoe International Airport, Information Romeo, 2253 Zulu. Winds 180 at
17. Ceiling 1,400 broken. Temperature 23, Dewpoint 18, Altimeter 30.08. ILS16R
approach in use. Advise on initial contact you have Information Romeo.
Our route along V105 brings us to the Mustang VOR (FMG), which has a published
transition to TAKLE, an Initial Approach Fix (IAF) for the ILS RWY 16R instrument
approach procedure. Because we’d like some practice with our new PFD and GPSS, we’ll
ask to fly the full procedure with pilot nav.
We load the KRNO ILS16R approach into the GPS, selecting TAKLE as our IAF and the
ILS frequency (110.9) is placed in the standby window of the 430W. With Auto Course
Select enabled on the PFD, the HSI Course Pointer will be slewed automatically once
we turn inbound to the Final Approach Course of 164º. Briefing the approach, we load
the Ground and Tower frequencies into our #2 comm and note our Decision Height is
6,446 feet. We set our approach MINIMUMS on the PFD to 6,450 feet (MINIMUMS are
set in increments of 10 feet, so we round up), and we set our Selected Airspeed for the
approach at 120 KIAS.
1.
2.
3.
4.
Figure 3-33
MIN Hot Key (shown disabled)
Press the MIN Hot Key (Figure 3-37).
The Selected Minimums Field appears on the lower right-hand corner of
the Attitude Display and the Right Knob State changes from HDG to MIN in
magenta, ready for setting (Figure 3-38).
Turn the Right Knob to set 6,450 on the Selected Minimums Field.
Press the Left Knob twice to select IAS for editing.
Turn the Left Knob to set 120 kt as our target airspeed.
Figure 3-34
MIN Display Selected for Editing
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
As we near Reno, we prepare for our arrival. Within range, we pick up the ATIS:
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
We’re all set up for the approach. Nearing Mustang VOR (FMG), Oakland Center hands
us off to Reno Approach, and we request nav for the ILS16R. Approach gives us the new
altimeter setting of 30.08, clears us down to 9,000 feet, and after FMG direct TAKLE. We
initiate the descent, set 30.08 in the standby altimeter and on the PFD:
1.
2.
3.
4.
Press the Right Knob twice to select ALT for editing.
Turn the Right Knob left to set 9,000 as our Selected Altitude.
Press the BARO Hot Key for editing.
Turn the Right Knob left to set 30.08 as our barometric pressure setting.
Fifteen seconds before reaching 9,000 feet, the Altitude Alerter flag illuminates, and
the alert tone sounds. We begin our level-off and re-engage ALT hold on the autopilot
upon reaching 9,000 feet. We leave the autopilot in HDG mode and continue with GPSS
enabled on the PFD.
Figure 3-35
360º Mode Showing Procedure Turn,
GPSS Enabled
Approaching FMG, the GPS turn anticipation sequences to TAKLE, our Course Pointer
swings automatically from 302° to 316°, and GPSS steers us through the turn, rolling
out precisely on course. We power back and select the first notch of flaps to slow
down. Reno Approach calls, reports us six miles from TAKLE, and clears us for the ILS16R
approach, pilot nav.
We activate the approach on the GPS and move the ILS frequency into the
active window.
GPSS continues to steer the plane to the initial approach fix, TAKLE, and, at TAKLE,
turns us outbound on a 344° course for the procedure turn (Figure 3-35). We see the
procedure turn drawn on the Basemap ahead of us and watch it turn magenta as GPSS
turns and flies the procedure turn for us, with no further pilot action required.
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1.
2.
3.
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
As GPSS completes the procedure turn and rolls out centered on our final approach
course of 164°, we begin a descent down to 8,500 feet, which we will maintain until
glideslope intercept.
Press the Right Knob twice to select ALT for editing.
Turn the Right Knob to set 8,500 as our Selected Altitude.
On reaching 8,500, re-engage ALT hold on the autopilot.
We are still navigating along the ILS16R approach using GPS, with GPSS driving the
autopilot in HDG mode. We know we’ll have to switch the autopilot to APPR mode
before glideslope intercept in order for the autopilot to capture the glideslope and fly
us down the ILS. But we’ll continue in GPSS and HDG mode a while longer because it
tracks the course more accurately with our aging autopilot.
Along this intermediate segment of the approach, watch for the 430W to switch
automatically from GPS to VLOC output on its CDI.
r
Watch for the PFD CDI Source Select field to change from GPS1 to VLOC1.
This automatic switch from GPS to VLOC should occur 2–10nm outside the Final
Approach Fix (FAF). If it has not occurred automatically by 2nm outside the FAF,
manually press the CDI Button on the 430W to make the switch to the ILS frequency,
and the PFD will follow by switching its Navigation Source Select to VLOC1.
As the PFD navigation source switches to the ILS on VLOC1, the LDI and VDI (Figure
2-2, Refs. 36 and 37) will appear on the Attitude Display.
1.
2.
The LDI Navigation Source Indication (Figure 2-2, Ref. 31) will show ILS, if
it is receiving a valid glide slope signal, or LOC, if it is not receiving the glide
slope (GS).
The CDI Source Information Block (Figure 2-2, Ref. 65) will also show ILS
or LOC.
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Page 3-23
The Garmin 400/500 series navigators continue to
output GPS Steering commands to follow the GPS flight
plan even when the CDI source is set to VLOC.
Even though the PFD Navigation Source for the CDI has switched to VLOC1 and the ILS,
and the CDI, LDI and VDI are showing deviations relative to the localizer and glideslope,
we still have GPSS Enabled with the autopilot in HDG mode. We are not yet flying the
ILS, required for this approach. GPSS is still shown in the inverse green label next to the
GPSS Hot Key, and GPSS1 and an inverse A are still shown at the top of the Navigation
Display where the numerical HDG value is usually shown.
The PFD permits GPSS to be enabled even when VLOC is
selected as the CDI navigation source.
The PFD, permits GPSS to be enabled even when VLOC is selected as the CDI Navigation
Source.
Whenever the GPSS is on and the autopilot is in the
HDG mode, the autopilot will fly the GPS flight plan. The
autopilot must be switched to APPR mode in order to fly
the VLOC source selected on for the CDI and to capture
and track the glideslope of an ILS or even an RNAV
approach with vertical guidance.
Whenever GPSS is enabled on the PFD, and the autopilot is in HDG mode, the autopilot
will fly the GPS flight plan. The autopilot must be switched to APPR mode in order to fly
the VLOC source selected for the CDI and to capture and track the glideslope of an ILS,
or even an RNAV approach with vertical guidance.
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
CAUTION
A couple of miles outside the FAF (TAKLE), we switch to APPR mode on the autopilot,
which begins to track the localizer and is armed for glideslope capture. At this point, we
could Disable GPSS on the PFD by pressing the Hot Key to remove potentially confusing
annunciations on the PFD, but we know our equipment well. We understand fully that
GPSS is just another form of HDG as far as the autopilot is concerned, and the autopilot
will not fly GPSS unless it is in HDG mode. So we leave GPSS enabled on the PFD,
planning to use it to fly the Missed Approach if necessary.
With that setup, if we have to fly the Missed Approach, we’ll do so by hitting Go Around
mode on the autopilot and climbing straight ahead to 6,700 feet. Then we’ll press the
OBS button on the GPS to allow the missed approach flight plan to sequence. Engage
the autopilot in the HDG mode and begin the climb out. With GPSS still enabled, the
autopilot will navigate the aircraft directly to the FMG VOR. If the GPS supports curved
flight plans, such as a WAAS GPS, the autopilot will automatically enter and fly the hold
for us. All we have to do is level off when reaching 11,000 feet - and if we had Altitude
Pre-Select on the autopilot, it would even do that for us, too!
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CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
When the glideslope is full-scale deflection above us, the Deviation Indicator on the
VDI will show as a hollow diamond at the top of the scale (Figure 3-36). When the
glideslope comes “alive”, the Indicator will change to a solid green diamond and begin
to move down the VDI. Just before intercepting the glideslope, we drop the gear
and check for three green lights. At glideslope intercept, we verify that the autopilot
switches to glideslope-capture and begins to fly the aircraft down the glide slope.
We continue to monitor the approach and verify that the autopilot is tracking both
localizer and glide slope. The weather is well above minimums, and we intend to land
out of the approach but will let the autopilot fly it down to minimums. As we get
close to minimums, a green triangle appears on the Altimeter Tape at 500 feet above
minimums; a hollow yellow triangle appears with its tip at 200 feet above minimums
and its base at 100 feet above. A red and yellow-striped triangle appears at the
MINIMUMS setting. These three color markers on the Altimeter Tape give us visual cues
that we are approaching or at minimums.
On reaching the pre-set minimums (6,450 feet):
r
The MIN legend in the Selected Minimums Field turns inverse amber (Figure
3-37).
r
The MINIMUMS alert tone sounds three times.
Figure 3-36
Vertical and Horizontal Deviation
Indicator, Showing Glide Slope
We disconnect the autopilot and hand-fly the plane, continuing to fly the Flight Director
and track the glide slope down to a smooth landing.
Figure 3-37
MINIMUMS Alert
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Page 3-25
3.3. Conclusion
CHAPTER 3 FLYING THE EFD1000 C3 PRO PFD
The PFD is a powerful addition to any cockpit, providing far more capability,
information, and automation than the mechanical instruments it typically replaces.
While it is simple and intuitive enough to start using with only a short orientation, fully
understanding and exploiting all of its features require some study and experience.
Chapter 4 covers all of the PFD features in detail.
Chapter 5 explains how to customize the PFD to suit your preferences.
Chapter 6 addresses Emergency and Abnormal procedures.
Please read through these chapters to fully understand how to use your PFD.
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Chapter 4
Reference Guide
CHAPTER 4 REFERENCE GUIDE
The PFD is a panel-mounted Electronic Flight Instrument System (EFIS)
that presents the pilot with displays of attitude, altitude, indicated
airspeed, heading, rate of turn, slip/skid, and navigation course deviation
information. The system also displays supplemental flight data, such as
winds, TAS, OAT, groundspeed, moving maps, pilot-selectable indices
(bugs), and various annunciations to increase situational awareness and
enhance flight safety. Moving map situational awareness information is
displayed when the unit is connected to compatible GPS equipment.
The PFD system components include the PFD display head, a Remote Sensor Module
(RSM), a Configuration Module (CM), and the optional Analog Converter Unit (ACU).
Chapter 1, Welcome and Introduction, provides a detailed discussion on the PFD
system components.
When interfaced with a compatible autopilot, the PFD system provides heading and
course information to the autopilot, which enables the autopilot to follow the Course
and Heading values set by the pilot on the PFD in much the same way as with a
mechanical HSI. When interfaced with a compatible GPS, the PFD can provide GPS
Steering (GPSS) to an autopilot.
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NOTE
The optional ACU enables the interface of the PFD
system with legacy panel-mounted GPS navigators,
VOR/Localizer radios, and autopilots.
Page 4-1
4.1. Air Data, Attitude and Heading Reference
System (ADAHRS)
CHAPTER 4 REFERENCE GUIDE
One of the many benefits of glass cockpit systems like the Aspen Evolution system is
that they replace old, less-reliable mechanical instruments and sensors with electronic
equivalents. For aircraft primary flight instruments, spinning metal gyros are replaced
with electronic gyros and accelerometers, and mechanical air data instruments
(airspeed indicator, altimeter, and VSI) are replaced by electronic sensors to measure
static and ram air pressures. As we’ve all seen with computers and consumer goods,
these modern electronic systems tend to be smaller, faster, cheaper, and more reliable
than the older technologies they replace, while also enabling many new, advanced
features and capabilities.
An electronic system that replaces the functions of the six primary flight instruments is
often called an ADAHRS (Air Data, Attitude, and Heading Reference System). Sometimes,
two separate systems work together to deliver those functions: an AHRS for attitude
and heading, and an ADC (Air Data Computer) for airspeed, altitude, and vertical speed.
Aspen uses an integrated ADAHRS mounted to the back of the PDF display. While
such systems deliver the same basic information to the pilot as the old mechanical
instruments, they work in very different ways. It is important that the pilot have at least a
basic understanding of how an ADAHRS works to better understand the sorts of failure
modes or degraded performance than can occur, how to recognize the symptoms, and
what corrective actions the pilot can take.
The PFD uses Micro Electro-Mechanical Systems (MEMS) technology and solid-state
accelerometers and magnetometers on all three axes to provide the attitude reference.
Generally, MEMS attitude solutions use multiple sensors and inputs, processed through
Kalman filter software, to derive and validate the attitude solution.
The Aspen system uses more than a dozen different inputs to determine and monitor
the aircraft attitude. In this way, the system can validate the derived attitude indication
by cross-checking the various inputs to the solution for consistency.
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4.1.1. Attitude
CHAPTER 4 REFERENCE GUIDE
The Aspen ADAHRS attitude solution uses inputs from its internal three-axis
accelerometers, rate gyros, and magnetometers, supplemented by ram and static air
pressure inputs from the aircraft pitot-static system. Failures or incorrect input from any
of these sensors (such as might occur if the pitot tube or static system become blocked)
will affect the attitude solution. The PFD is designed to be robust to such failures, either
by being tolerant to incorrect inputs, or by detecting and annunciating a degraded
attitude solution. The Aspen ADAHRS includes a Cross-Check Monitor, which predicts the quality of the
attitude solution by performing a continuous, real-time statistical analysis of the various
parameters computed within the AHRS Kalman filter. When the predicted quality of
the attitude calculation drops below a certain threshold, CROSS CHECK ATTITUDE is
annunciated on the attitude indicator (Figure 4-1). The annunciation thresholds for
the CROSS CHECK ATTITUDE message were determined during company flight tests,
and strike a balance between minimizing nuisance annunciations (when the attitude
solution is fine) and failing to annunciate (when the attitude solution is significantly
degraded). This balance can occasionally result in momentary CROSS CHECK ATTITUDE
annunciations, especially during aggressive maneuvering, steep or high-G turns, abrupt
pitch changes, etc.
In such situations, these annunciations indicate that the statistical quality of the attitude
solution is less than nominal and that the pilot should cross-check the AHRS against
alternate attitude indications. Should the annunciation persist, then degraded AHRS
performance is statistically more likely to be experienced. In other words, momentary
CROSS CHECK ATTITUDE annunciations indicate that the AHRS solution is working
hard enough that the AHRS quality measure has degraded to something less than that
associated with normal, unaccelerated flight. This situation demands increased pilot
vigilance and cross-monitoring of other cockpit instrumentation.
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Figure 4-1
Cross Check Attitude
Annunciation
Page 4-3
4.1.2. Pitot Obstruction Monitor
CHAPTER 4 REFERENCE GUIDE
Most light aircraft have only a single pitot and static system available for flight
instrument use. As such, a common pitot and static input is shared between the PFD
and analog standby instruments. Should one or both of these pitot and static lines
become blocked, both the PFD and any standby airspeed and altitude indicators
could display erroneous airspeed and altitude information. Furthermore, because
the PFD uses pitot and static pressures as part of the AHRS attitude calculations, loss
or corruption of the pitot or static pressures can also influence the accuracy of the
displayed attitude information.
The PFD has been tested to be robust to these failures, either by being tolerant to
incorrect pitot or static inputs or by detecting and annunciating a degraded attitude
solution. When connected to an IFR-certified GPS, the system is further able to detect
and annunciate blockages in the pitot system and will fail the attitude solution before
it becomes degraded. In that case, the system will red X the attitude and heading
information and display a CHECK PITOT HEAT message as a reminder to the pilot to
check for ice accumulating on the pitot probe.
Once the system detects that the pitot obstruction has been cleared, the CHECK PITOT
HEAT annunciation is removed and the system automatically performs an AHRS in-flight
reset.
Should a GPS failure be experienced in flight, the Pitot Obstruction Monitor continues
to operate in a fail-safe mode and will continue to detect obstructions in the pitot
system that may occur while airborne. However, after landing, the monitor remains
active and as the airplane slows to taxi speeds, the system will indicate a failure of the
AHRS and annunciate CHECK PITOT HEAT. In this circumstance, restoring the GPS will
restore normal monitor operation.
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CHAPTER 4 REFERENCE GUIDE
In summary, loss or degradation of the PFD attitude solution is unlikely if the pilot
assures the proper operation of the pitot-static system. If the pitot or static system
become blocked, an ADAHRS internal sensor fails, or a CROSS CHECK ATTITUDE
indication is frequent or persists, the attitude indication on the PFD should be
considered compromised. In this case, the pilot must use the backup attitude indicator
for attitude reference until the cause of the problem has been identified and resolved
and normal system operation has been restored.
4.1.3. Heading
The PFD ADAHRS also includes a slaved compass system that provides accurate
magnetic heading indications throughout most operating conditions and phases
of flight. Its electronic gyros compensate for turning and acceleration errors and its
remote fluxgate compensates for gyroscopic precession errors, so there is no need for
the pilot to adjust heading throughout the flight. Nonetheless, all compass systems are
subject to some error and the pilot should be aware of when and how the PFD heading
indication can be affected.
The earth’s magnetic field is measured directly by a 3-axis fluxgate magnetometer
built into the Remote Sensor Module (RSM) and magnetic heading is derived from the
flux on a plane perpendicular to gravity, providing immunity from pitching and rolling
effects. Electronic gyros and accelerometers in the PFD system are then used to stabilize
that raw heading data to eliminate the short-term turning and acceleration errors seen
on a traditional magnetic compass.
Together, these systems provide accurate heading indications even during aggressive
maneuvering. The gyros stabilize magnetic errors while maneuvering and are slaved
to the fluxgate, which continuously updates heading to compensate for gyroscopic
precession. The end result is a compass system that requires no pilot action to show
accurate magnetic heading throughout the flight.
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CHAPTER 4 REFERENCE GUIDE
Just like other compass systems, the accuracy of the fluxgate is affected by its location
on the airframe. Ferrous metal structures, electrical fields produced by motors, pumps,
wiring, magnets in cabin speakers and other airframe-related sources of interference
either constant or momentary (i.e. operating an electric trim motor, windshield heat,
pumps, etc) can all affect the accuracy of the compass. The installer can compensate
for much of this interference when calibrating the RSM, but some effects cannot be
eliminated. Proper location of the RSM during installation of the PFD is critical to the
AHRS performance and accuracy.
Furthermore, all magnetic compass systems are susceptible to local disturbances in the
earth’s magnetic field (some of which are shown on aviation charts or by NOTAM) and
will exhibit degraded performance when operating in extreme northern and southern
latitudes close to the earth’s magnetic poles.
4.1.4. Free Gyro Mode
When the PFD system detects that the horizontal component of the earth’s magnetic
field is no longer strong enough to provide reliable heading data, the PFD will detect
the condition and annunciate that the heading system is no longer slaved to magnetic
north. If the condition persists, attitude and heading indications are removed.
While the condition can occur at greater distances, it is most likely to be observed
within 750 nautical miles from the magnetic poles. In the Northern Hemisphere, this
equates to operations in the Arctic Islands found north of continental North America.
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CHAPTER 4 REFERENCE GUIDE
Two minutes after detection, a FREE GYRO MODE annunciation will be presented across
the HSI, indicating the heading system no longer can be aligned with magnetic north. Some precession of the heading is possible, especially during abrupt maneuvers. If the
condition persists for four more minutes (six minutes total), the attitude and heading
indicators will be removed and replaced with red X indications. When the conditions
causing Free Gyro Mode are no longer present, attitude and heading indications will be
restored after an automatic AHRS reset.
4.1.5. Degraded ADAHRS Performance
For Degraded ADAHRS Performance, reference the following:
t
t
t
Sections 6.1. Pitot/Static System Blockage
Sections 6.8. In-Flight AHRS Reset
Geographic Limitations in the Aircraft Flight Manual Supplement that was
installed in the aircraft with your PFD.
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Page 4-7
4.2. Attitude Display
CHAPTER 4 REFERENCE GUIDE
4.2.1. Attitude Indicator
The Attitude Indicator consists of an aircraft reference symbol on a blue (sky) and brown
(ground) background. The white horizon line separates the sky from the ground and
extends to the edge of the display. The Roll Scale curves over the top of the Attitude
Indicator while the Pitch Scale extends vertically in the middle. The slip/skid rectangle is
directly underneath the roll pointer (Figure 4-2).
Figure 4-2
Attitude Indicator
Sky
Flight Director
Aircraft Reference Symbol
Roll Scale
Horizon Line
Roll Pointer
Ground
Slip/Skid Indicator
Pitch Scale
Figure 4-3
Pitch and/or Roll Data Invalid
NOTE
A red X and the annunciation ATTITUDE FAIL displays
on the Attitude Indicator as long as pitch or roll
attitude data is invalid (Figure 4-3).
Page 4-8
The Attitude Indicator cannot be disabled by the pilot. The Aircraft Reference Symbol is
fixed relative to the Attitude Indicator and overlays all other Attitude Indicator symbols.
Pitch and roll panel tilt adjustments are provided to installers to compensate for
variations in installations and tilted panels.
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
4.2.1.1. Roll Scale
4.2.1.2. Pitch Scale
The pitch scale consists of minor pitch marks in 2.5º increments up to ±20º and major
pitch marks in 10º increments up to ±90º. Red chevrons come into view for nose-up
pitch angles of 15º or more (Figure 4-4), or nose-down pitch angles of 10º or less
(Figure 4-5). The red chevrons aid the pilot in unusual attitude recovery.
Figure 4-4
Pitch Markings - Chevrons
indicate Pitch Down
Figure 4-5
Pitch Markings - Chevrons
indicate Pitch Up
The range of movement of the background sky and ground boundaries are limited so
that some sky or ground is always visible.
4.2.1.3. Slip/Skid Indicator
The Slip/Skid Indicator is the small white rectangle under the roll pointer. The Slip/
Skid Indicator moves left and right relative to the roll pointer in proportion to lateral
acceleration. The width of the rectangle is equivalent to the width of the ball in a
mechanical inclinometer.
NOTE
4.2.1.4. Flight Director
When connected to a compatible autopilot and configured through an ACU during
installation, the PFD displays a single-cue (two-axis) Flight Director on the Attitude
Indicator (Figure 4-6). The pilot may follow the Flight Director’s pitch and roll cues,
even when the autopilot is not engaged, to remain on heading or altitude, climb or
descend, turn, or navigate along a programmed flight path.
091-00019-001 REV B
Figure 4-6
Flight Director
EFD1000 C3 Pro PFD Pilot’s Guide
Refer to the autopilot’s AFMS for information on the
operation of the Flight Director. The Flight Director
is a visual representation of the pitch and roll
commands from the autopilot. The Flight Director’s
pitch and bank limits are based on the emulation
mode set at installation and are limited to +/- 45°
roll and +/- 25° pitch.
Page 4-9
CHAPTER 4 REFERENCE GUIDE
The Roll Scale is displayed at the top of the Attitude Indicator and comprises a moving
scale set against a fixed, white, triangle roll pointer. Tick marks are displayed at 0º, 10º,
20º, 30º, 45º, and 60º of roll. The 45º marks are triangles.
4.2.2. Airspeed Indicator
CHAPTER 4 REFERENCE GUIDE
The Airspeed Indicator comprises a moving tape, airspeed bug, and numerical airspeed
value (drum). Textual Vspeeds, color Speed Bands, and Speed Markers are also rendered
on the moving tape (Figure 4-7).
Selected Airspeed Field
Color Speed Bands
Textual Vspeeds
Initial Flap Extension Speed Marker
Airspeed Tape
Speed Marker
Numerical Airspeed Value (drum)
Figure 4-7
Airspeed Indicator
Page 4-10
Selected Airspeed Bug
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CHAPTER 4 REFERENCE GUIDE
Indicated airspeed is displayed in knots, miles per hour or mach number, set at
installation, with tick marks rendered on the Airspeed tape every ten (10) units. Speed
Bands and Speed Markers are configured during installation and cannot be changed
or removed by the pilot. The textual Vspeeds are pilot-configurable and are discussed
in Chapter 5, Customizing the PFD. Although the pilot can set the selected airspeed
(bug), there is no visual or aural annunciation provided when the actual airspeed
deviates from the selected airspeed value.
The numerical airspeed value is displayed in a rolling drum format in the center of the
airspeed tape with numbers moving downward as speed increases, and upward as
speed decreases. The display range of the indicated airspeed is 20–450 (knots or miles
per hour). The numerical airspeed value is displayed in red when Vne is exceeded or
when the airspeed drops below Vs0 during stalls or landing roll-outs (Figure 4-8).
Figure 4-8
Actual Airspeed Greater Than the Vne
NOTE
When airspeed is less than 30 knots but ground GPS speed is greater than 50 knots, a
red X and annunciation of CHECK PITOT HEAT is displayed on the Attitude Indicator
(Figure 4-9).
Figure 4-9
Pitot Obstruction Monitoring Airspeed
<30kts, Ground Speed >50kts
Annunciation
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Page 4-11
CHAPTER 4 REFERENCE GUIDE
4.2.2.1. Selected Airspeed
The Selected Airspeed Field value and associated Airspeed Bug are shown on the
Airspeed Tape. The Selected Airspeed Field value is shown at the top of the Airspeed
Tape. The Airspeed Bug is displayed next to the Airspeed Tape when the Selected
Airspeed value is within the visible range of the tape. The Selected Airspeed Field’s
default value is 20 knots Indicated Airspeed (IAS), or the value previously set. SYNCing
the IAS field sets the Selected Airspeed Field value to the current indicated airspeed
(Section 2.2.1.3). Setting the Selected Airspeed Field to a value less than 20 disables
the Airspeed Bug and dashes the Selected Airspeed Field value.
Set Airspeed Bug
1.
Figure 4-10
Airspeed Bug Selected to Edit
Figure 4-11
New Airspeed Selected
Press the Left Knob until IAS is shown above the Left Knob.
The Airspeed Field and Airspeed Bug appear in magenta - enabled for editing (Figure
4-10).
2.
Rotate the Left Knob clockwise to increase, or counterclockwise to decrease
the airspeed value in the Selected Airspeed Field.
After 10 seconds of inactivity, label, field and bug appear in cyan (Figure 4-11).
NOTE
A typical installation sets the Tapes (TPS) display
to UNLOCKED, allowing the pilot to display or
hide the Airspeed and Altitude Tapes as desired. If
the Airspeed and Altitude Tapes were LOCKED ON
during installation, the Tapes will remain on. If the
Airspeed and Altitude Tapes were LOCKED OFF during
installation, the Tapes will not display.
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4.2.2.2. Airspeed Display
Hide/Display Airspeed Tape
1.
2.
3.
Press MENU Button.
Rotate Right Knob until first Menu Key displays TPS (Figure 4-12).
Press TPS Menu Key.
TPS label and EDIT VALUE label (above Right Knob) appear in magenta.
4.
5.
Rotate Right Knob to the desired value: ENABLE or DISABLE (Figure 4-13).
Press MENU Button to exit.
Figure 4-12
Editing Airspeed Tape Display
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EFD1000 C3 Pro PFD Pilot’s Guide
NOTE
The Altitude Tape can also be turned off for screen
declutter. Setting will be retained when PFD is
turned off.
NOTE
When the Airspeed Tape is disabled, the numerical
display of the selected airspeed remains. An installer
can disable and remove the Selected Airspeed Field
from the display.
Figure 4-13
Airspeed Tape Disabled
Page 4-13
CHAPTER 4 REFERENCE GUIDE
In some configurations, such as a stand-alone PFD, the airspeed tape can be turned off
at the pilot’s discretion to facilitate screen declutter. This setting will be retained when
the PFD system is turned off then powered on again.
4.2.2.3. MACH Number Display for Mmo Aircraft
CHAPTER 4 REFERENCE GUIDE
For Mmo aircraft, the PFD can show aircraft Mach number in the Data Bar with a
display resolution of 0.01 Mach.
The Mach number (configured during initial installation) can be displayed for either
altitude or speed transition.
When configured to ALTITUDE transition, the TAS indication will be replaced by the
Mach number whenever the aircraft is above the selected transition altitude.
Figure 4-13a
Altitude Transition Setting
When configured to SPEED transition, the TAS indication will be replaced by the Mach
number whenever the aircraft is above the selected transition Mach number.
Select the Altitude or Speed Transition setting
1.
2.
3.
Figure 4-13b
Speed Transition Setting
NOTE
Refer to Chapter 5, Table 5-2, Menu - General Settings
B for the available Altitude and Speed settings
Page 4-14
Press the MENU Button and rotate the Right Knob to the GENERAL
SETTINGS B page.
Press the MACH DSPL Menu Key and rotate the Right Knob to the desired
Altitude setting (Figure 4-13a) or Speed setting (Figure 4-13b).
Press the MENU Button to exit.
NOTE
The installer will configure the EFD1000 to display redline or barber pole airspeed limits
that vary with pressure altitude. The colors are configured to correspond with the aircraft’s
approved markings on the mechanical airspeed indicator.
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
4.2.3. Altimeter
Altitude Alerter
Altitude Tape
Selected Altitude Field
MINIMUMS Annunciation/
Selected MINIMUMS Field
Minimums Marker
Radio Altitude / Decision
Height Window
Numerical Altitude Value
Decision Height
Annunciation
Altitude Trend Vector
CHAPTER 4 REFERENCE GUIDE
The altimeter comprises an Altitude Bug, Numerical Altitude Value (drum), Altitude Tape,
Altitude Trend Vector, MINIMUMS annunciation, Selected Altitude Field value, Decision
Height Annunciation, Altitude Alerter and an aural tone (when configured) DH (Figure
4-14).
Figure 4-14
Altimeter
The Altitude Tape range is from -1,600 to 51,000 feet. Major tick marks are provided
every 100 feet and minor tick marks every 20 feet. A barometric pressure adjustment
(BARO) is provided to the pilot to accurately display the aircraft’s altitude above mean
sea level.
The Numerical Altitude Value is shown in a rolling drum format in the center of the
Altimeter Tape, with numbers moving downward as the altitude increases and upward
as altitude decreases. The Numerical Altitude Value shows the altitude to the nearest
20 feet.
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CHAPTER 4 REFERENCE GUIDE
An adjacent, magenta Altitude Trend Vector predicts the anticipated
altitude, in the next six seconds, if the current rate of climb or decent is
maintained. Like the VSI, there is a slight lag in the indication. If the ribbon
meets or exceeds the display limit, the vertical trend is large. The Altitude
Trend Vector does not display when the altitude remains constant.
If the altitude exceeds 51,000 feet, the Numerical Altitude Value is dashed,
and the tape is frozen at this limit. All altitude information is removed and
replaced with a red X with the textual annunciation of ALT FAIL when
altitude data is invalid (Figure 4-15).
Figure 4-18
Editing BARO
Units of Measure
GENERAL SETTINGS B
Figure 4-15
Altitude Failure
4.2.3.1. Barometric Units of Measure
Figure 4-16
BARO Shown in Inches of Mercury
Figure 4-19
Editing BARO
from in to mB
Barometric units of measure adjustment may be made in either inches of
mercury (in) (Figure 4-16) or millibars (mB) (Figure 4-17), as configured
by the pilot in the Menu. The adjustment range is 28.10 – 30.99 inches
Hg or 946 – 1049 mB. The barometric pressure default value is 29.92
inches, or as previously set.
Set Barometric Units of Measure
Figure 4-17
BARO Shown in Millibars
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob to select the GENERAL SETTINGS B page
(Figure 4-18).
Press the BARO Menu Key.
The Menu label turns magenta, and the EDIT VALUE label displays above
the Right Knob (Figure 4-19).
4.
5.
Rotate the Right Knob to select either in or mB (Figure 4-20).
Press the MENU Button to exit.
Figure 4-20
BARO Set to mB (millibars)
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091-00019-001 REV B
Set the Barometric Pressure
1.
Press the BARO Hot Key.
2.
3.
Rotate the Right Knob to change the value of the Barometric Pressure
Setting Field.
Press the BARO Hot Key or any knob, button/key to exit.
If no action is taken, after 10 seconds of inactivity, the label and field are rendered in
cyan.
4.2.3.2. Selected Altitude Field
The Selected Altitude Field value is displayed at the top of the Altitude Tape. The
Selected Altitude Field range is 100 to 51,000 feet, in 100 foot increments. The
default value for the Selected Altitude value is 100 feet, or the previously set value.
Additionally, the Altitude Bug is displayed adjacent to the Altitude Tape and at the
Selected Altitude Field value when within the visible range of the current altitude.
Set Altitude Bug and Altitude Alerter
1.
Press the Right Knob until ALT displays above the Right Knob.
The Selected Altitude Field and bug are enabled for editing, all rendered in magenta
(Figure 4-22).
2.
Rotate the Right Knob (clockwise to increase, or counterclockwise to
decrease) to change the value of the Selected Altitude Field.
Once the correct value is selected, and after 10 seconds of inaction, the field is
disabled, and the label, field, and bug are rendered in cyan.
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EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-21
BARO Field Enabled
WARNING
Always check and set the PFD BARO whenever the
mechanical altimeter is adjusted
NOTE
Since the altitude tape display is limited to
approximately 400 feet, the altitude bug symbol is
shown on the altitude tape when the Selected Altitude
Field value is within the visible range of the current
altitude.
Page 4-17
CHAPTER 4 REFERENCE GUIDE
The BARO label above the Right Knob and Barometric Pressure Setting Field appear
in magenta (Figure 4-21).
4.2.3.3. Altitude Level-Off and Deviation Alert
CHAPTER 4 REFERENCE GUIDE
NOTE
Rotating the knob quickly will change the altitude
value in larger increments.
The Altitude (level-off ) Alert is ARMED and rendered on-screen as a yellow alert flag
next to the Selected Altitude value when the aircraft altitude transitions to within 200
feet or 15 seconds of reaching the selected altitude (Figure 4-23).
When an optional Sonalert tone generator device is installed, a one-second tone
also sounds. Once the current altitude is within ± 25 feet of the Selected Altitude, the
Altitude Alert extinguishes (Figure 4-24).
After reaching the Selected Altitude, if the aircraft’s current altitude differs from
the selected altitude by more than 200 feet, the yellow alert flag flashes. When an
optional Sonalert tone generator device is installed, a one-second tone also sounds.
Figure 4-22
Altitude Bug and Altitude Alerter Enabled
Figure 4-23
Altitude Alert
NOTE
Setting the Altitude Alerter provides visual and aural cues to help the pilot capture and
maintain target altitudes. When set to a new altitude, the Alerter will illuminate a yellow flag
adjacent to the target altitude display and sound a one-second tone; 15 seconds (or 200 feet)
before the aircraft will reach the target altitude (based on current rate of climb or descent).
The yellow flag will extinguish once the target is reached. Subsequently, if the aircraft deviates
more than 200 feet above or below the target altitude, the flag will again illuminate, and
another one-second tone will sound to alert the pilot to the deviation.
Figure 4-24
Altitude Alert Extinguishes at Selected Altitude
Page 4-18
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4.2.3.4. MINIMUMS Annunciation
Marker Color
Description
Green
The aircraft is 500 feet above selected
MINIMUM.
The aircraft is 100 feet to 200 feet
above the selected MINIMUM.
Hollow Yellow
The marker base is at 100 feet above
MINIMUM, and the tip is at 200 feet
above MINIMUM.
Red and
Yellow stripes
The aircraft is at the selected
MINIMUM.
CHAPTER 4 REFERENCE GUIDE
The PFD provides an adjustable MINIMUMS field to enhance situational awareness
during instrument approaches. The PFD provides a MINIMUMS annunciation with a
series of markers on the Altitude Tape that provide the pilot with improved awareness
when approaching and operating at minimums. There are three different color
markers that are shown on the Altitude Tape that are associated with the MINIMUMS
Annunciation, as described in Table 4-1.
Figure 4-25
Minimums Green Triangle
Figure 4-26
Minimums Hollow Yellow
Triangle
Figure 4-27
Minimums Red/Yellow Striped
Triangle
Table 4-1
Selected MINIMUMS Markers
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Page 4-19
CHAPTER 4 REFERENCE GUIDE
Once the Selected Minimums field value is set to a Decision Altitude, Decision Height,
or Minimum Descent Altitude, the PFD provides an alert when the aircraft descends
below this altitude. To activate this feature, enable the Selected Minimums (MIN) field
and set the value with the Right Knob.
Display/Hide Minimums
1.
Press the MIN Hot Key to alternately hide or display the Selected Minimums
Field, MINIMUMS Annunciation, and Markers (Figures 4-28 and 4-29).
The range for the MIN data field is 0 – 15,000 feet, in increments of 10 feet. SYNCing sets
the Selected Minimums field value to the current altitude (Section 2.2.1.3). The default
value is 100 feet, or the previously set value.
Figure 4-28
MIN Hot Key – Selected MINIMUMS
Annunciation and Markers Disabled
NOTE
Pressing the MIN Hot Key presents the MINIMUMS Markers on the Altitude Tape and the
Selected Minimums Field on the Attitude Display. The MIN label above the Right Knob and
the MIN field value are rendered in magenta for editing.
Figure 4-29
Selected MINIMUMS
Annunciation and Markers
Enabled
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091-00019-001 REV B
Set Altitude Minimum
1.
Press the MIN Hot Key to set the altitude minimum.
2.
CHAPTER 4 REFERENCE GUIDE
The Selected MINIMUMS Field and the MIN label above the Right Knob are rendered in
magenta (Figure 4-30).
Rotate the Right Knob to change the value of the Selected MINIMUMS Field.
Once the correct value is selected, and after 10 seconds of inaction, the field is disabled
(Figure 4-31).
Whenever the aircraft is at or below the Selected MINIMUMS setting, the MIN legend in
the Selected Minimums Field turns inverse amber (Figure 4-32) and when configured
with an optional Sonalert, a one-second stuttered tone is generated.
Figure 4-30
Selected MINIMUMS Field MIN Enabled
The amber MIN Annunciation is cancelled when the aircraft is 100 feet above the
selected minimums setting or when the selected minimums is set to a new altitude.
Additionally, the MINIMUMS Markers on the Altitude Tape provide the pilot with
additional awareness of aircraft altitude with respect to the set MINIMUMS.
Figure 4-31
New Selected MINIMUMS
Annunciation Setting
Figure 4-32
MINIMUMS
Annunciation Active
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Page 4-21
CHAPTER 4 REFERENCE GUIDE
4.2.3.5. Radio Altitude Display
Figure 4-32b
Radio Altitude with
red slash
Figure 4-32a
Radio Altitude
When a compatible radio altimeter is connected to the Evolution Display, radio altitude
height in feet above ground level (AGL) can be displayed at the bottom left of the
Attitude Display Figure 4-32a. When the aircraft is above the maximum range of
the radio altimeter, the Radio Altimeter display window is removed. The maximum
displayed altitude value will depend on the range of the radar altimeter equipment
installed in the aircraft.
Radio Altitudes that are greater than or equal to 500 feet AGL are displayed in 100 foot
increments (RA 500, RA 600, RA 700...) and altitudes less than 500 feet AGL are displayed
in 10 foot increments (RA 490, RA 480, RA 470...)
The digital readout in the Radio Altitude (RA) window is normally displayed in green,
however, when the aircraft is at or below the Decision Height (DH) set on the onboard
radio altimeter’s indicator (if applicable), the RA window on the PFD will show the DH
legend as inverse amber and the current RA readout in amber. An amber DH (Decision
Height annunciation is also displayed near the upper left corner of the Attitude Display
(Figure 4-33).
If the PFD detects a malfunction on the onboard radio altimeter, the RA window is
displayed with a red slash through the digital readout Figure 4-32b.
Figure 4-33
DH Annunciation
NOTE
“RAD ALT: DISABLE” Menu Key label is shown in gray if
a compatible radio altimeter is not installed.
Page 4-22
Enable or Disable the Radio Altitude Display
1.
2.
3.
Press the MENU Button and rotate the Right Knob to the GENERAL SETTINGS
A page.
Press the RAD ALT Menu Key and rotate the Right Knob to toggle between
ENABLE or DISABLE.
Press the MENU Button to exit.
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091-00019-001 REV B
4.2.3.6. Altitude Display
Hide/Display Airspeed and Altitude Tape
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob counterclockwise until GENERAL SETTINGS A page
displays (Figure 4-34).
Press the TPS Menu Key.
The Menu label turns magenta, and the EDIT VALUE label displays above the Right
Knob.
4.
5.
NOTE
A typical PFD only installation sets the tapes display
to UNLOCKED, allowing the pilot to display or hide
the Airspeed and Altitude tapes as desired. If the
Airspeed and Altitude Tapes were LOCKED ON during
installation, such as the case with a PFD and MFD
configuration, then the tapes must remain on. If the
Airspeed and Altitude Tapes were LOCKED OFF during
installation, the tapes will not display.
Rotate the Right Knob to the desired value, ENABLE (On) or DISABLE (Off )
(Figure 4-35).
Press the MENU Button to exit.
NOTE
Figure 4-34
Editing Airspeed and Altitude Tape Display
091-00019-001 REV B
Figure 4-35
Airspeed and Altitude Tape Disabled
EFD1000 C3 Pro PFD Pilot’s Guide
When the Altitude tape is disabled, the numerical
display of the selected altitude and altitude minimums
remain on. However, an installer can disable and
remove the Selected Altitude and Minimums Fields,
and the MINIMUMS Annunciation and Markers from
the display.
Page 4-23
CHAPTER 4 REFERENCE GUIDE
In some configurations, such as a stand-alone PFD, the altitude tape can be turned off,
at the pilot’s discretion, to facilitate screen declutter. Both Airspeed and Altitude tapes
are affected by this action.
CHAPTER 4 REFERENCE GUIDE
4.3. Data Bar
The Data Bar presents True Airspeed (TAS) or the Mach number, GPS Ground Speed (GS),
Outside Air Temperature (OAT), Wind Direction, Wind Speed, and Barometric Pressure
Setting, as shown in Figure 4-36. The Data Bar is always present on the display. Invalid
or out-of-range Data Bar values are dashed.
Figure 4-36
Data Bar
True Airspeed (TAS) or MACH
Wind Direction Arrow
Barometric Pressure Setting
Field
Outside Air Temperature (OAT)
Wind Speed
Ground Speed (GS)
Wind Direction
NOTE
If the OAT was set to disabled during installation, as
would be the case if the RSM is mounted internally to
the aircraft structure, then the TAS, OAT, Wind Direction
and Wind Speed are not displayed.
4.3.1. True Airspeed or Mach Number (when enabled)
The True Airspeed (TAS) or the Mach number is displayed in the upper left of the Data
Bar. The TAS has a range of 20–999 knots or mph, using the same unit of measurement
as the aircraft’s Airspeed Indicator. The TAS is a correction of the IAS for nonstandard
pressure and temperature.
The Mach number can be configured to be displayed whenever the aircraft is above
a selected altitude or above a selected Mach number and is shown with a display
resolution of 0.01 Mach.
Page 4-24
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Select the Transition Setting
1.
3.
4.3.2. Ground Speed
The Ground Speed (GS) comes from a configured GPS navigator and is digitally
displayed in the lower left corner of the Data Bar with a value range of 5–999 knots or
mph, using the same unit of measurement as the Airspeed Indicator.
4.3.3. Outside Air Temperature (when enabled)
Figure 4-37
Select OAT Units of Measure
The Outside Air Temperature (OAT) is displayed in the center of the Data Bar (Figure
4-36). The temperature is obtained from the temperature sensor located in the RSM.
Temperature sensor ranges from -55°C to +80°C (-67°F to +176°F).
Set OAT Units of Measure
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob counterclockwise until GENERAL SETTINGS B page
displays.
Press the OAT Menu Key.
The Menu label turns magenta and the EDIT VALUE label displays above the Right Knob
(Figure 4-37).
4.
5.
Rotate the Right Knob to select either °C or °F (Figure 4-37).
Press the MENU Button to exit.
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Page 4-25
CHAPTER 4 REFERENCE GUIDE
2
Press the MENU Button and rotate the Right Knob to the GENERAL SETTINGS
C page.
Press the MACH DSPL Hot Key and rotate the Right Knob to the desired
Altitude or Speed setting.
Press the MENU Button to exit.
4.3.4. Wind Speed, Direction and Arrow (when enabled)
CHAPTER 4 REFERENCE GUIDE
Figure 4-38
Wind Direction Arrow
The Wind Direction Arrow, Wind Direction and Wind Speed are displayed in the lower
right portion of the Data Bar (Figure 4-36).
The Wind Speed has a range of 10 to 999 knots or mph, using the same unit of measure
as the Airspeed Indicator.
NOTE
The wind computations require a GPS-provided
ground track and ground speed to compute the wind
direction and speed. If a GPS is not connected to the
PFD or the data is invalid, the Wind Direction/Wind
Speed is dashed and the Wind Direction Arrow is
removed.
The Wind Direction Arrow (Figure 4-38) and Wind Direction have a range of 001° to
360°, using the same direction reference used by the Direction Indicator. The arrow
points in the direction of the wind and is displayed relative to the current direction of
flight. For example, if the current direction of flight is 360° and the wind is from 360°, the
arrow will point straight down on the display (a headwind blowing toward aircraft).
When the computed wind speed is below 10 knots or mph, (depending on aircraft
configuration) or if the wind data is out of range or invalid, the Wind Direction/Wind
Speed values are blank and the Wind Direction Arrow is removed.
4.3.5. Barometric Pressure Setting Display
The Barometric Pressure Setting Field is displayed on the upper right corner of the Data
Bar (Figure 4-36) and is pilot-adjustable, as discussed in Section 4.2.3.1. When the
Altitude Tape is disabled, the Barometric Pressure Setting field remains visible. However,
an installer can disable the field and remove it from the display. Section 4.2.3.1
provides complete information and step-by-step instructions for setting the barometric
pressure.
Page 4-26
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4.4. Navigation Display
The Horizontal Situation Indicator (HSI) on the Navigation Display of the PFD, combines
a Direction Indicator with a Course Deviation Indicator (CDI) (Figure 4-39).
CHAPTER 4 REFERENCE GUIDE
The Direction Indicator comprises a compass, numerical direction indication, heading
bug, Ground Track Marker (when GPS ground track information is available), rate of turn
indicator, and aircraft ownship symbol. The CDI is comprises a selected course pointer,
Deviation Scale and indicator, TO/FROM indicators, and selected navigation source label
and information block.
CDI Source Info Block
Aircraft Ownship Symbol
Magnetic Heading
Heading Bug
Rate of Turn Indicator
Selected CDI Navigation Source
Selected Heading Field
Course Deviation Scale
Ground Track Indicator
Compass Scale
Course Pointer
Course Deviation Indicator
NOTE
The size, shape and location of the Course Pointer,
Deviation Scale, and Deviation Indicator depend on
the Compass Mode selected..
TO/FROM Indicator
091-00019-001 REV B
Figure 4-39
Horizontal Situation Indicator
EFD1000 C3 Pro PFD Pilot’s Guide
Page 4-27
CHAPTER 4 REFERENCE GUIDE
All Magnetic Headings are displayed in degrees. The value range is from 001° - 360°,
always displayed in three digits, and use leading zeros when applicable. The Magnetic
North is expressed as 360°.
4.4.1. Compass
Figure 4-40
360° Compass Mode
The PFD offers three Compass Modes: 360°, ARC HSI, and ARC CDI. The default Compass
Mode is 360. The aircraft’s heading is always expressed degrees magnetic. The magnetic
headings inside of the compass scale omit the last zero for brevity (i.e., 30°, 60°, 120°,
150°, 210°, 240°, 300°, and 330° are labeled 3, 6, 12, 15, 21, 24, 30, and 33, respectively).
The four cardinal compass headings are shown as letters (i.e. N for 360°; E for 090°; S for
180°; and W for 270°).
4.4.1.1. 360° Compass Mode
The 360° Compass Mode displays a full 360° compass rose with all other components
of the Direction Indicator. The 360° compass rose rotation centers on the aircraft
ownship symbol so that the numerical direction indication corresponds to the current
aircraft heading (Figure 4-40).
4.4.1.2. ARC Compass Mode
The two ARC Compass Modes have an abbreviated 100° ARC compass scale. All
other elements of the Direction Indicator are retained. The ARC Compass Mode’s
scale rotation centers on the aircraft ownship symbol so that the numerical direction
indication corresponds to the current aircraft heading. The default ARC Compass Mode
is ARC HSI.
Figure 4-41
ARC HSI Compass Mode
Page 4-28
The ARC HSI Compass Mode presents a rotating CDI, similar to that used in the 360°
Compass Mode (Figure 4-41).
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
The ARC CDI Compass Mode uses a fixed CDI, resembling a contemporary GPS
navigation deviation display. The ARC CDI Compass Mode is intended to maximize the
lower display area for map and flight plan data (Figure 4-42).
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob to the GENERAL SETTINGS A page
(Figure 4-43).
Press the ARC MODE Menu Key.
The Menu label turns magenta, and the EDIT VALUE label displays above the Right Knob
(Figure 4-44).
4.
5.
Rotate the Right Knob to select either HSI or CDI (Figure 4-45).
Press the MENU Button to exit.
Figure 4-42
ARC CDI Compass Mode
091-00019-001 REV B
Figure 4-44
Changing the ARC Compass MODE
Figure 4-43
GENERAL SETTINGS A
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-45
CDI ARC Compass MODE Selected
Page 4-29
CHAPTER 4 REFERENCE GUIDE
Select ARC CDI/HSI Compass Mode
Select Compass Type
1.
Press the 360/ARC Hot Key (Figure 4-46) to alternately select either the 360°
or ARC Compass Mode.
CHAPTER 4 REFERENCE GUIDE
The Navigation Display changes and the Hot Key label reflects the currently selected
Compass Mode (Figures 4-47 and 4-48).
Figure 4-46
360/ARC Hot Key
Page 4-30
Figure 4-47
ARC CDI Compass Mode
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-48
360˚ Compass Mode
091-00019-001 REV B
4.4.2. Course Pointer
COMPASS
DESCRIPTION
ARC HSI
The Course Pointer length shortens as necessary when rotated to remain
within the display area (Figure 4-49).
ARC CDI
The Course Pointer is shown as a stub arrow or tail whenever the CRS value
or its reciprocal falls within the displayable range of the compass scale arc
(Figure 4-50 and 4-51).
CHAPTER 4 REFERENCE GUIDE
For all Compass Modes, the arrowhead of the Course Pointer aligns with the
corresponding value on the compass scale regardless of the aircraft heading. The ARC
Compass HSI and CDI Course Pointers are different and are described in Table 4-2.
Figure 4-49
Reduced Length Course Pointer,
ARC HSI Compass Mode
Table 4-2
ARC Compass Mode Course Pointer Display
Figure 4-50
Stub Course Arrowhead ,
ARC CDI Compass Mode
Figure 4-51
Stub Course Tail , ARC
CDI Compass Mode
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EFD1000 C3 Pro PFD Pilot’s Guide
Page 4-31
4.4.3. TO/FROM Indicator
CHAPTER 4 REFERENCE GUIDE
Each of the Compass Modes has a TO/FROM indicator. The TO/FROM indicator shows
whether the aircraft is heading toward a waypoint or radio navaid, or from a waypoint
or radio navaid. For each Compass Mode, the TO/FROM indication is slightly different, as
described in Table 4-3.
COMPASS
DESCRIPTION
360°
The TO indicator is an arrowhead on the top half of the Course Pointer,
oriented in the same direction as the course arrowhead
(Figure 4-52). The FROM indicator is an arrowhead on the bottom half
of the Course Pointer, oriented in the direction opposite to the course
arrowhead (Figure 4-53).
ARC HSI
The TO indicator is shown as two arrowheads, one on each half of the
Course Pointer, oriented in the same direction as the course arrowhead
(Figure 4-54). The FROM indicator is shown as two arrowheads, one on
each half of the Course Pointer, oriented opposite to the direction of the
course arrowhead (Figure 4-55).
ARC CDI
The TO indication is shown as TO on the left side of the Deviation Scale
(Figure 4-56). The FROM indication is shown as FROM on the right of the
Deviation Scale (Figure 4-57).
Figure 4-52
360° TO Indication
Figure 4-53
360° FROM Indication
Figure 4-54
HSI TO Indication
Table 4-3
TO/FROM Indicator Description
Figure 4-56
CDI TO Indication
Figure 4-55
HSI FROM Indication
Figure 4-57
CDI FROM Indication
Page 4-32
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091-00019-001 REV B
4.4.4. Course Deviation Indicator and Scale
The 360° and ARC HSI Compass Modes show the CDI as a green line centered on the
display and parallel with the Course Pointer. The scale is a set of four hollow, green dots
that are perpendicular to the Course Pointer (Figure 4-58).
Course Deviation Indicator
Figure 4-58
Deviation Indicator, 360° and
ARC HSI Compass Modes
Course Deviation Scale
The ARC CDI Compass Mode’s CDI and Scale are located at the bottom of the lower
display. The indicator is a green diamond, and the Scale is a set of four hollow, white
dots with a white index mark at the center (Figure 4-59). When in the ARC CDI
Compass Mode, on a Localizer Back Course approach, a BC label is presented to the left
of the scale, and the Indicator corrects for reverse sensing (Figure 4-60).
When the lateral deviation exceeds the maximum displayable range of 2.5 dots,
the Deviation Indicator bar or diamond, as applicable, becomes hollow and darker
(Figure 4-61 and 4-62).
Figure 4-59
Course Deviation Indicator, ARC CDI
Compass Mode
091-00019-001 REV B
Figure 4-60
Course Deviation Indicator, ARC CDI
Compass Mode with Back Course
Figure 4-62
Deviation Exceeded, ARC CDI
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-61
Exceeded Deviation, 360° and
ARC HSI Arc Compass Modes
Page 4-33
CHAPTER 4 REFERENCE GUIDE
Selected course deviation is depicted by a Course Deviation Indicator and Scale.
Deviation is indicated by positioning the Course Deviation Indicator on the Scale
corresponding to the lateral deviation value.
4.4.4.a. Localizer Back Course (BC) Operation
CHAPTER 4 REFERENCE GUIDE
When flying a Back Course final approach (the aircraft heading is opposite to the localizer
front course), set the CRS value to the front course localizer or ILS approach value. The tail
of the CDI will match the back course runway’s magnetic orientation.
When the LOC(BC) mode is active, two “BC” annunciations are shown; on the Attitude
Display left of the Lateral Deviation Indicator (LDI) and on the ARC Compass left of the
Course Deviation Scale (Figure 4-62a). The left/right deviation indications are corrected
for reverse sensing and will behave intuitively, the same as with a front course localizer.
4.4.5. CDI Navigation Source
When the PFD powers up, the default Selected CDI Navigation Source is the last source
selected. The pilot can select from any of the installed navigation sources using the
Lower Center Button. The PFD supports navigation information display from VHF Omnidirectional Radio Range (VOR) navaids, Localizers (LOC), Glide Slope receivers (GS), and
Global Positioning Systems (GPS). There can be up to four dedicated, two integrated, or
a combination of one integrated and two dedicated navigation systems installed.
Figure 4-62a
Back Course (BC) Annunciation Locations
When individual GPS and VLOC devices are installed, the GPSS signal source, Basemap
GPS position, flight plan, and Basemap information for VLOC1, VLOC2, and GPS1
are provided by the GPS1 navigation source whenever GPS1 is selected as the CDI
navigation source and by GPS2 whenever GPS2 is selected as the Selected CDI
navigation source.
When integrated GPS/VLOC equipment are installed, the GPSS signal source, Basemap
GPS position, flight plan and Basemap information for the integrated GPS-VLOC is
provided by the associated GPS whenever the CDI navigation source is selected to
either the GPS side or the VLOC side of the integrated GPS/VLOC receiver.
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091-00019-001 REV B
Select the CDI Navigation Source
1.
CDI Navigation Source Select Button
NOTE
For integrated systems, the CDI navigation source label
indicates the current operating mode (GPS or VLOC) of
the GPS/VHF NAV system.
Selected CDI Source Label
When an integrated system is selected but not
reporting its operating mode, VLOC1 or VLOC2 is
shown as the Selected CDI Navigation Source.
CDI Source Information Block
Refer to the GPS or VHF NAV AFMS for information on
the operation of the connected navigation equipment.
NOTE
When the PFD is connected to some GPS and the active
flight plan is changed (e.g. “Direct To” is selected), the
display of the active (magenta) leg on the Nav Map
may be delayed for up to 20 seconds. The Course Pointer
and autopilot will react immediately to the flight plan
change.
NOTE
Figure 4-63
CDI Source selection and Information
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
There are many radio configurations available. Your
authorized Aspen Avionics Dealer can explain the
configuration used on your aircraft.
Page 4-35
CHAPTER 4 REFERENCE GUIDE
Press the CDI Navigation Source Select Button until the desired navigation
source is displayed above the Button (e.g., GPS1, GPS2, VLOC1, VLOC2)
(Figure 4-63).
Whenever the CDI Navigation Source’s data is valid, a CDI Source Information Block
for the selected source is shown in the upper left corner of the Navigation Display, as
shown in Figure 4-64 and described in Table 4-4.
CHAPTER 4 REFERENCE GUIDE
Radio Mode
Information Block Label
GPS
GPS1 or GPS2
VHF
Figure 4-64
CDI Source Information Block
VOR
VOR1 or VOR2
Localizer
LOC1 or LOC2
Localizer Back
LOC1(BC) or LOC2 (BC)
ILS
ILS1 or ILS2
Table 4-4
VHF NAV Radio Modes
Selected CDI Navigation Source
Waypoint identifier or tuned frequency (when available)
Bearing (in degrees)/Distance (in Nautical Miles) to waypoint or navaid
(when available)
Estimated Time Enroute (Hours:Minutes)
If both the station identifier and the tuned frequency of the associated VHF NAV
radio are available, only the station identifier is displayed on the second line of the
information block. In most cases, however, only the tuned frequency is available for
display from integrated GPS/VLOC devices.
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091-00019-001 REV B
When available, the bearing and distance to station is displayed on the third line of the
information block in the format dddº/nnnn or dddº/nn.n, where ddd is the bearing in
degrees and nnnn or nn.n is the distance in nautical miles (e.g., 360º/1103 or 322º/3.2,
shown in Figure 4-64). The distance to waypoint is displayed as follows:
r Distance to waypoint is 100–9999nm, display in whole miles, i.e., ####.
r Distance to waypoint is > 9999nm, display is dashed, i.e., ----.
When available, the estimated time enroute information is displayed on the fourth line
of the information block in the format h:mm (where h is hours and mm is minutes).
Figure 4-65
No Course Deviation Bar or
TO/FROM Indicator
When CDI Navigation Source data is invalid or unavailable from a configured navigation
source, the HSI course deviation bar and the TO/FROM indicator are removed from the
display (Figure 4-65). Additionally, the selected CDI Navigation Source label in the CDI
Source Information Block is slashed with a red line (Figure 4-66).
Figure 4-66
Invalid CDI Navigation Source Label
When information for a configured and selected navigation source is unavailable or is
invalid, the CDI Source Information Block is blank (Figure 4-67).
Figure 4-67
CDI Source Information Blank Block
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-68
Menu, GENERAL SETTINGS
Page 4-37
CHAPTER 4 REFERENCE GUIDE
r Distance to waypoint < 100nm, display is in tenths of a mile, i.e., ##.#.
CHAPTER 4 REFERENCE GUIDE
4.4.6. Auto Course
The pilot can either use the Auto Course (AUTOCRS) or manually set a CRS value. By
default, AUTOCRS is enabled. When the selected CDI Navigation Source is a connected
GPS receiver and AUTOCRS is enabled, CRS is not adjustable (current course value
is automatically slewed and controlled by the desired track from the GPS). When
AUTOCRS is enabled, the CDI navigation source is a GPS, and that system is configured
for automatic waypoint sequencing (i.e., not OBS or HOLD modes) then Auto Course
Select is active.
Figure 4-69
Editing AUTOCRS
Figure 4-70
AUTOCRS Enabled
Enable Auto Course
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob to the GENERAL SETTINGS A page (Figure 4-68).
Press the AUTOCRS Menu Key.
The Menu label turns magenta, and the EDIT VALUE label displays above the Right Knob
(Figure 4-69).
4.
5.
Rotate the Right Knob to select ENABLE (Figure 4-70).
Press the MENU Button to exit.
When AUTOCRS is enabled, the CRS value is set to the desired track output from the CDI
Navigation Source. The CRS value is shown in the upper left of the lower display area
in green under the CRS label. Additionally, an inverse green A is shown beside the CRS
label in the upper left of the lower display area and in the legend above the Left Knob.
This indicates that the course is being automatically adjusted (Figure 4-71).
Figure 4-71
AUTOCRS Enabled
Page 4-38
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091-00019-001 REV B
Disable Auto Course
Press the MENU Button.
Rotate the Right Knob to the GENERAL SETTINGS A page (Figure 4-72).
Press the AUTOCRS Menu Key.
The Menu label turns magenta, and the EDIT VALUE label displays above the Right Knob
(Figure 4-73).
4.
5.
Rotate the Right Knob to select DISABLE (Figure 4-74).
Press the MENU Button to exit.
Figure 4-72
Menu, GENERAL SETTINGS
4.4.7. CDI Selected Course
Figure 4-73
Editing AUTOCRS
When the CDI source changes from a GPS source with AUTOCRS to another CDI source,
the CRS value reverts to the last set value. When the CDI source is set to a VHF receiver
operating in the VOR or Localizer modes, editing the CRS value adjusts the current
selected CRS value. When the CDI source is set to a GPS receiver, and AUTOCRS is
disabled, the CRS value may be adjusted.
Select CDI Course
1.
Press the Left Knob.
The CRS label above the Left Knob and the Course field are enabled for editing, both
rendered in magenta (Figure 4-75).
2.
Rotate the Left Knob to change the value of the Course field.
Once the CRS value is set, and after 10 seconds of inaction, the CRS field is disabled, and
both the label and field are rendered in cyan.
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-74
AUTOCRS Disabled
Figure 4-75
CRS Field Enabled for Editing
Page 4-39
CHAPTER 4 REFERENCE GUIDE
1.
2.
3.
CHAPTER 4 REFERENCE GUIDE
4.4.8. Bearing Pointer Source Selection
When the 360° Compass mode is selected, single- and double-line bearing pointers are
available (Figure 4-76). The bearing pointers are independent of the CDI and provide
supplemental navigation information by pointing to active GPS waypoints or navaids.
By default, the bearing pointers are off and not displayed.
Single-Line Bearing Pointer
Single-Line Bearing Pointer Source Information
Figure 4-76
Bearing Pointer Description
Top Line
Distance (nm) to active GPS waypoint
Bottom Line
Waypoint identifier, station identifier (when available, or the tuned
frequency of the associated VHF NAV radio (when available)
Single-Line Bearing Pointer Icon
Double-Line Bearing Pointer
NOTE
Distance to waypoint < 100nm, display is in tenths of a
mile, i.e., ##.#.
Distance to waypoint is 100 – 9999nm, display in
whole miles, i.e., ####.
Distance to waypoint is > 9999nm, display is dashed,
i.e., ----.
Page 4-40
Double-Line Bearing Pointer Source Information
Top Line
Distance (nm) to active GPS waypoint
Bottom Line
Waypoint identifier, station identifier (when available), or the tuned
frequency of the associated VHF NAV radio (when available)
Double-Line Bearing Pointer Source
Table 4-5
Bearing Pointer Description
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Each Bearing Pointer is associated with a Lower Left Button or a Lower Right Button,
its source, and Information Block. The Lower Left Button, immediately adjacent to the
CDI Navigation Source Selection Button is associated with and controls the SingleLine Bearing Pointer. Likewise, the Lower Right Button controls the Double-Line
Bearing Pointer. The Bearing Pointers’ Source Information is shown directly above their
respective Buttons.
Unlike the CDI’s Course Pointer, which can be adjusted by the pilot, no adjustments can
be made to the Bearing Pointers. When a VOR is selected as the source, the arrow of
the needle points to the VOR navaid to which the receiver is tuned. The position of the
Bearing Pointer tail, with respect to the compass, indicates the aircraft’s current position
on the VOR radial. When a GPS source is selected, the Bearing Pointer indicates the
bearing to the active waypoint.
When the Bearing Pointer Source Information is unavailable or invalid, the Bearing
Pointer and its Source Information are removed (Figure 4-77). The Bearing Pointer’s
Source is also source legend slashed with a red line (Figure 4-78).
Figure 4-77
Bearing Pointers OFF
Figure 4-78
Invalid Bearing Pointer Source
When a Bearing Pointer is turned OFF, only the Bearing Pointer’s icon is shown.
The Selected Source, the Source Information, and the Bearing Pointer are removed
(Figure 4-79).
Figure 4-79
Icons when Bearing Pointers
are OFF
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EFD1000 C3 Pro PFD Pilot’s Guide
Page 4-41
CHAPTER 4 REFERENCE GUIDE
The Bearing Pointers indicate only the bearing information provided by their selected
navigation sources. They resemble and perform like traditional Radio Magnetic Indicator
(RMI) needles. Each Bearing Pointer’s head and tail is aligned with the corresponding
bearing/radial value on the compass. The pilot can select a navigation source for each
of the Bearing Pointers from the same VOR and GPS sources available to the CDI or
simply turn off the Bearing Pointer and Source Information.
CHAPTER 4 REFERENCE GUIDE
NOTE
A VOR that is tuned to a localizer frequency is
considered an invalid Bearing Pointer source since
Localizer signals provide no bearing information.
Select the Single-Line Bearing Pointer Source
1.
Press the Single-Line Bearing Pointer Button (Lower Left Button, Figure 4-80)
until the desired navigation source is shown above the Button.
Select the Double-Line Bearing Pointer Source
1.
Press the Double-Line Bearing Pointer Button (Lower Right Button,
Figure 4-81) until the desired navigation source is shown above the Button.
Figure 4-80
Single-Line Bearing Pointer and Button
Page 4-42
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-81
Double-Line Bearing Pointer and Button
091-00019-001 REV B
4.4.9. Heading Bug
When the Selected HDG Field value is outside the visible compass scale range in the
ARC Compass mode, only a portion of the Heading Bug is shown at the edge of the
compass arc, closest to the HDG value (Figure 4-83).
CHAPTER 4 REFERENCE GUIDE
The PFD offers a pilot-selectable Heading Bug. The Heading Bug symbol is positioned
on the compass scale according to the Selected Heading Field value (HDG) set by the
pilot (Figure 4-82).
Figure 4-82
Heading Bug and Selected
Heading Field
When selected for editing, the Heading Bug and the Selected HDG Field value are
shown in magenta. Additionally, a dashed magenta line extends from the Ownship
Symbol to the Heading Bug, corresponding to the HDG value. When the Heading Bug is
SYNCed, the HDG value is set to the current heading.
Set Heading Bug
1.
Press the Right Knob.
The HDG label above the Right Knob and the Selected Heading Field are enabled for
editing, both rendered in magenta (Figure 4-84).
2.
Rotate the Right Knob to change the value of the Selected Heading Field.
Figure 4-83
Selected Heading Bug Outside of
the ARC Compass Scale Range
Once the HDG value is set, and after 10 seconds of inaction, the Selected HDG Field is
disabled, and both the Right Knob State and the Selected Heading Field are displayed
in cyan.
Figure 4-84
Heading Selected to Edit
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page 4-43
4.4.10. Aircraft Heading Display
CHAPTER 4 REFERENCE GUIDE
The aircraft heading is displayed in degrees magnetic (Figure 4-85).
If the aircraft’s heading is unavailable or invalid, all heading and navigation information,
including the CDI and bearing pointers (if previously displayed), is removed and
replaced with a single red X covering the entire lower display area, along with the
annunciation DIRECTION INDICATOR FAIL (Figure 4-86).
Figure 4-85
Direction of Flight
Numerical Display
4.4.11. Rate of Turn Indicator
Figure 4-86
Direction Indicator Fail
The Rate of Turn Indicator consists of a curved white line originating from the
corresponding side of the aircraft heading (i.e., a left turn indication starts on the left
side of the index mark) and extends in the direction of the turn along the outer radius
of the compass scale. The turn rate indication is provided for every compass mode, 360°
(Figure 4-87) and ARC (Figure 4-88).
The Rate of Turn Indicator features tick marks for full and half-standard rate turns (a
standard rate turn = 3° per second).
Figure 4-87
Rate of Turn Indicator
(360° Compass Mode)
The Rate of Turn Indicator has a range of 0° – 6° per second. When the turn rate exceeds
6° per second, an arrowhead is added to the end of the tape to show that the rate of
turn has exceeded the limits of the instrument.
Figure 4-88
Rate of Turn Indicator
(ARC Compass Mode)
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091-00019-001 REV B
4.4.12. Basemap Overlays
Basemap Symbols
Figure 4-89
Basemap (ARC CDI Compass Mode Shown)
Aircraft Ownship Symbol
Basemap Declutter Level
Basemap Range
When enabled, the Basemap features on the Navigation Display are displayed and
layered as detailed in Table 5-12. The GPS flight plan is rendered in either straight or
curved lines, as supported by the configured GPS navigator. The displayed symbol set
includes active waypoints, active flight plan leg, flight plan waypoints, flight plan legs,
airports, VORs, VORTACs, TACANs, DMEs, intersections, and NDBs (Figure 4-90).
NOTE
All map and flight plan elements are received
from the GPS and are only available from
compatible GPS navigators (e.g. GNS 430/530).
091-00019-001 REV B
NOTE
A VORTAC is shown as a combined
VOR and DME symbol. A TACAN is
rendered as a DME symbol.
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-90
Basemap Symbol Set
Page 4-45
CHAPTER 4 REFERENCE GUIDE
The Basemap comprises symbols depicting the location of flight plan waypoints and
legs, airports, VORs, DMEs, NDBs, and intersections. The Basemap is always oriented
with magnetic heading up and centered so that the current aircraft position coincides
with the aircraft’s Ownship Symbol. The current Basemap declutter level and range are
shown on the lower left side of the display (Figure 4-89).
4.4.12.1. Basemap Declutter and Range
To turn the Basemap on or off, the pilot selects one of the declutter levels as described
in Section 5.2. The default map declutter level is Level 4.
CHAPTER 4 REFERENCE GUIDE
The map range corresponds to the outside radius of the compass scale, 2, 3, 5, 10, 15,
20, 30, 40, 60, 80, 100, or 200 nautical miles from the aircraft Ownship Symbol. The
default range is 15nm. Both the map declutter level and range are pilot-adjustable.
Figure 4-91
MAP Hot Key
Select Map Declutter Level
1.
2.
3.
Press the MENU Button and rotate the Right Knob to MAP SETTINGS page.
Press the DCLTR LVL Menu Key (Figure 4-91) and rotate the Right Knob to
select the desired map declutter level.
Press the MENU Button to exit.
The new Basemap display level appears above the Left Knob (Figure 4-92).
Change Map Range
1.
Press the Range Up (RNG +) or the Range Down (RNG -) Button (Figure 4-93).
until the desired range is displayed (Figure 4-94).
Figure 4-93
Basemap Range Buttons
NOTE
When connected to a GPS that does not provide
compatible Basemap data, then only OFF and FP ONLY
declutter levels are available.
Page 4-46
Figure 4-92
New Basemap Display Level
EFD1000 C3 Pro PFD Pilot’s Guide
Figure 4-94
New Basemap Range
091-00019-001 REV B
Enable Auto Range
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob to the GENERAL SETTINGS B page.
Press the AUTO RNG Menu Key.
The AUTO RNG label turns magenta (Figure 4-96).
4.
5.
Figure 4-95
Auto Range Mode
Figure 4-96
GENERAL SETTINGS B Page Editing
Auto Range Setting
Rotate the Right Knob to the desired value, either ENABLE or DISABLE.
Press the MENU Button to exit.
Activate Auto Range
1.
2.
Press the RNG +/- Button to select the highest or lowest map range.
Press and hold the RNG +/- Button for two seconds.
The map range changes and the new map range is indicated on the map. An inverse
white A displays next to the numeric range value.
NOTE
The map range increases or decreases one increment
each time the RNG + or - Button is pressed. Press and
hold to continuously increase or decrease the range.
Deactivate Auto Range
1.
Press the RNG +/- Button once to deactivate Auto Range mode.
The inverse white A next to the numeric range value is removed.
Pressing RNG + moves to the next higher range; pressing RNG - moves to the next
lower range.
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NOTE
The Basemap declutter setting can determine what is
displayed for a particular range. Refer to Chapter 5,
Table 5-9 for more information.
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CHAPTER 4 REFERENCE GUIDE
The PFD has an Auto Range feature that automatically scales the range (to the closest
range setting) to fit the Aircraft Ownship and the active waypoint within the Navigation
Display, e.g., if the active waypoint is 84 miles away, Auto Range will select a 100nm
range (the closest range setting is 100nm). When Auto Range is active, an inverse white
A is shown next to the range value (Figure 4-95).
CHAPTER 4 REFERENCE GUIDE
Auto Range is only available when a flight plan is active. Since Auto Range uses the
distance between the present position and the next active waypoint to compute the
appropriate map range, if the currently Selected CDI Navigation Source does not have
a valid flight plan, then Auto Range is not selectable. If the Auto Range cannot be
selected, check:
r To ensure a flight plan is active
r The GPS source with the flight plan is the Selected CDI Navigation Source
r That Auto Range is enabled from the General Settings B Menu page
4.4.12.2. Flight Plan
When a flight plan is provided by a configured GPS, the map shows flight plan
waypoints and legs. The active leg and waypoint and associated identifier are displayed
in magenta. Other waypoints and legs are white. Straight and curved flight plan details
are rotated within the map display to maintain their correct relative orientations at
all times.
4.4.12.3. Map Data Source and Reversion
Figure 4-97
GPS1 Failure, Reversionary Navigation
Figure 4-98
RSM GPS Reversionary Navigation
Page 4-48
If the selected GPS data is unavailable or invalid:
r The associated flight plan and map data are retained and displayed, as long as an
alternate source of position information remains available.
r The flight plan and waypoints become inactive and are displayed in white.
r Position is provided from:
1. Another configured GPS source if providing valid position data. In this case, a
GPS# REVERSION annunciation is shown above the Selected CDI Navigation
Source (Figure 4-97) (# indicates the configured GPS source that is now
providing the aircraft’s position, either 1 or 2).
2. The RSM GPS, if enabled, and position data are available. In this case, a RSM
GPS REVERSION EMER USE ONLY annunciation is shown above the Selected
CDI Navigation Source (Figure 4-98).
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When a GPS source’s position data are invalid or no longer available, an amber
annunciation, GPS1, GPS2, or RSM GPS, is shown in the lower left corner of the
Navigation Display to indicate which has failed (Figure 4-99).
When configured with a GPS that provides ground track data, a Ground Track Marker is
displayed on the compass scale to indicate the aircraft’s ground track. This marker may be
used to compensate for wind drift during flight (Figures 4-100 and 4-101). The Ground
Track Marker is removed from the display when ground track data is not available or invalid.
Figure 4-99
Invalid or Failed GPS Annunciations
4.4.14. GPS OBS Operation with a PFD and a Mechanical
Standby Nav Indicator
When the PFD and a mechanical standby Nav indicator are both connected to an integrated
VOR/Localizer/GPS Navigation system, the standby indicator and the PFD operate normally in
all VOR, GPS and localizer modes.
When the GPS OBS mode is selected, the PFD Selected Course (CRS) control commands the
GPS OBS course and the mechanical standby nav indicator’s OBS course selector is ignored
by the integrated navigation system. Deviation indications are shown on both displays.
When the PFD is turned off, the course selector on the mechanical standby Nav indicator
commands the GPS OBS value.
Figure 4-100
ARC Compass Mode, Ground Track Marker
Figure 4-101
360° Compass Mode, Ground Track Marker
4.4.15. Course Pointer Operation with Integrated VOR/
Localizer/GPS Navigation Systems
During manual or automatic operation of the integrated system, when transitioning from
GPS guidance to VOR or localizer guidance, the course pointer on the should manually be set
to the appropriate course.
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4.4.13. Ground Track Marker
CHAPTER 4 REFERENCE GUIDE
4.5. Lateral and Vertical Deviation Indicator
In addition to the CDI in the Navigation Display, separate displays of lateral and vertical
deviation information are shown in the Attitude Display during instrument approaches.
A Lateral Deviation Indicator (LDI) and a Vertical Deviation Indicator (VDI) (Figure
4-102) will automatically appear, depending on the operating mode of the selected
navigation sensor and the validity of the associated signal, as described below.
Vertical Deviation Indicator (VDI)
Lateral Deviation Indicator (LDI)
Figure 4-102
Lateral and Vertical Deviation Indicators
and Source Information
LDI Navigation Source Indicator
4.5.1. Lateral Deviation Indicator
The LDI and corresponding LDI Navigation Source Indication automatically display
when:
r The active navigation source is a GPS radio, GPS is in the Approach mode, and the
signal is valid.
Or
r The active navigation source is a VHF navigation radio and a valid LOC, LOC(BC), or
ILS signal is received.
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Figure 4-103
Lateral Deviation Diamond
Off Scale Indication
When the LDI navigation source is invalid or is no longer available, the Lateral Deviation
Diamond is removed from view, and the Navigation Source Indication is slashed by a
red horizontal line (Figure 4-104).
4.5.2. Vertical Deviation Indicator
The Vertical Deviation Indicator (VDI) is enabled and is shown on the Attitude Display
when the active navigation source is a VHF navigation radio, the ILS mode is active, and
a valid localizer signal is being received. The VDI is also displayed for a GPS, supplying
valid vertical deviation data, when in the Approach mode.
Figure 4-104
LDI Source Invalid
The VDI will only display with a valid vertical guidance signal. When the vertical
deviation exceeds the displayable range, the Glide Slope Deviation Diamond becomes
dim and hollow, and is parked at the extreme edge of the VDI scale (Figure 4-105).
Figure 4-105
Vertical Deviation Diamond Off Scale Indication
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When the LOC(BC) mode is active, deviation indications (corrected for reverse sensing)
are displayed. The deviation shown on the LDI directly corresponds to the deviation
indicated on the CDI in the Navigation Display. When the lateral deviation exceeds the
displayable range of 2.5 dots, the Course Deviation Diamond becomes dim and hollow,
and is parked at the extreme edge of the LDI scale (Figure 4-103).
CHAPTER 4 REFERENCE GUIDE
4.6. Vertical Speed Indicator
When the 360° Compass Mode is selected, the Vertical Speed Indicator (VSI) is rendered
on the right side of the Navigation Display, showing a numerical and graphical
representations of vertical speed. The VSI shows the change in pressure altitude over
time. The graphical display is a white VSI Tape, with the numerical value at the top
(Figure 4-106). In either ARC Compass mode, only the numerical value is shown.
The VSI Tape displays rates of ±2,000 FPM while the numerical value displays rates up to
±9,990 FPM. When the vertical speed exceeds ±2,000 FPM, a triangle caps the VSI Tape
(Figure 4-107).
Figure 4-106
VSI
Figure 4-107
VSI Tape Off-Scale
The VSI Tape is nonlinear, giving more display area to the 0 to ±1,000 FPM range than
to the ±1,000 to ±2,000 FPM range. Tick marks are presented only in the direction of
the climb or descent to provide visual cues for trends. The VSI’s numerical value, tape,
and scale are only shown if the aircraft is climbing or descending more than ±100 FPM.
During level flight in calm air conditions, the Tape, scale, and zero reference line are
removed from the display. The numerical value is always enabled and shows dashes
when vertical rates are out of range. If vertical speed is invalid, the Tape and numerical
display are replaced with a red X and the annunciation, VSI FAIL (Figure 4-108).
Figure 4-108
VSI Fail – 360° Compass Mode
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4.7. Autopilot Integration
When connected to an autopilot system that includes Nav or Approach couplers, the
PFD also acts as the navigation source selector switch to the autopilot. This assures that
the navigation information selected for the PFD is the same as that being provided
to the autopilot. This arrangement also eliminates the need for external autopilot
navigation source selector switches and relays that were previously used to select
which navigation radio would be connected to the autopilot. Selection of autopilot
modes and mode control is unaffected by the installation of the PFD.
NOTE
Refer to the autopilot AFMS for information on the
operation of the autopilot or Flight Director.
The PFD does not currently provide vertical coupling to barometric references, such as
altitude hold, vertical speed, or altitude capture.
See Section 4.7.3. Typical Autopilot Operation for more details on PFD operation
with the autopilot systems during typical aircraft operations, such as VOR/ILS/GPS
approaches.
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The PFD can connect with many different legacy autopilot systems that are typically
found in general aviation aircraft. The PFD emulates the HSI and/or Flight Director (FD)
with which the autopilot was originally certified. Autopilot integration is limited to
heading and navigation modes, including vertical approach modes.
CHAPTER 4 REFERENCE GUIDE
WARNING
GPS Steering is a powerful automation tool that
can substantially reduce pilot workload. However,
using GPSS safely and effectively requires a thorough
understanding of your specific aircraft installation and
the interaction between the PFD, your GPS navigator,
and your autopilot. Pilot actions required to use
GPSS safely can vary significantly depending on the
autopilot and GPS navigator installed, especially when
used on instrument approaches, especially those with
vertical guidance.
It is imperative that pilots new to GPSS gain experience
with it in VFR conditions and, ideally, get dual
instruction from a CFII who thoroughly understands
GPSS and the autopilot and GPS navigator in your
airplane before using GPSS on instrument procedures
in IMC.
4.7.1. GPS Steering (GPSS)
GPS Steering represents a modern approach to flying between flight plan waypoints,
and offers many advantages of over traditional methods of flying direct course lines
between waypoints.
With traditional point-to-point navigation, the autopilot is provided with desired course
and cross-track deviation information associated with the current flight leg. From there,
it will maneuver the aircraft to center the needle and track the desired course. The
autopilot does not anticipate upcoming course changes, nor can it fly curved flight
paths without pilot assistance, and it has to recompute wind corrections following each
course change. Upon reaching a waypoint, the pilot must set the course for the next
leg (unless AUTOCRS is enabled, see Section 4.4.6. Auto Course), and the autopilot will
then intercept and track that leg. In this type of operation, the CDI must always be set to
the desired course.
With GPSS, the PFD can unlock the GPS Steering capability already available in many
models of general aviation GPS navigators. With GPSS, the navigator continuously
computes the desired bank angle to track the GPS flight plan, and outputs that
information over a digital data bus. The GPS Steering command anticipates upcoming
turns; this includes the turn rate and turn initiation point required to roll out centered
on the next leg.
Some GPS navigators, such as the Garmin 4xx/5xxW series of WAAS navigators, even
provide GPS Steering commands for complex procedures, such as DME arcs, holding
patterns, and procedure turns allowing the autopilot to fly these maneuvers without
pilot intervention. Check with your GPS manufacturer to see if your GPS supports these
capabilities.
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The PFD translates GPS Steering commands received over a digital data bus into a
signal that is compatible with the autopilot Heading channel. Thus, by selecting GPSS
on the PFD and the Heading mode of the autopilot, the autopilot is able to fly GPSS
commands.
Enable/Disable GPSS
1.
Press the GPSS Hot Key to alternately enable or disable GPS Steering
(Figure 4-109).
Refer to the Aircraft Flight Manual Supplement for your
GPS for information about GPSS commands that may
be output by that system.
NOTE
When GPSS is selected on the PFD, the autopilot must
be in Heading mode to follow the GPSS commands.
NOTE
When GPSS is disabled, the autopilot will follow the
Heading Bug.
Figure 4-109
GPSS Hot Key
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If the connected GPS does not provide the required steering commands, the GPSS
legend adjacent to the GPSS Hot Key will be rendered in gray, and it will not be possible
to enable GPSS with the Hot Key.
NOTE
CHAPTER 4 REFERENCE GUIDE
When GPSS is enabled, and the autopilot is in HDG mode, the autopilot will follow the
steering commands from the GPS. A GPSS enabled state will be indicated on the PFD
in two locations: 1) the GPSS legend adjacent to the GPSS Hot Key will be shown in
inverse green; and 2) the annunciation GPSS1 (or GPSS2, depending on the selected
source), along with an inverse A, will be shown next to the HDG reference at the top of
the Navigation Display, to the right of the Magnetic heading indication (Figure 4-110).
Figure 4-110
GPSS Enabled with Autopilot in
HDG Mode
When GPSS is disabled, and the autopilot is in HDG mode, the autopilot will follow the
PFD Heading Bug. A GPSS disabled state will be indicated on the PFD in two locations:
1) the GPSS legend adjacent to the GPSS Hot Key will be shown in gray; and 2) the
Selected Heading Field will return. (Figure 4-111).
When the PFD Basemap navigation source is GPS1, enabling GPSS with the autopilot
in HDG mode will cause the autopilot to track the flight plan in GPS1, and GPSS1 will
be annunciated by the HDG reference at the top of the Navigation Display. Similarly,
when GPS2 is the Basemap navigation source on the PFD, and GPSS is enabled, the
autopilot in HDG mode will track the GPS2 flight plan, and GPSS2 will be annunciated
at the top of the navigation display. See Section 4.4.5. for additional information on the
relationship among the CDI Navigation Source, Basemap Navigation Sources, and GPSS
Navigation Source.
Figure 4-111
GPSS Disabled and Autopilot in
HDG Mode
Page 4-56
When using GPSS with a stand-alone VLOC receiver, or with a combined GPS/VLOC
navigator (e.g. the GNS-430/530), GPSS will continue to follow the GPS output of that
combined navigator, even when VLOC is selected as the PFD Selected CDI Navigation
Source. With combined GPS/VLOC receivers, the transition from GPS to VLOC may occur
automatically, depending on how that system has been configured by the pilot.
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When flying an ILS on a WAAS GNS-430W, the autopilot in HDG mode can use the GPSS
to fly the full course reversal automatically, and the GNS-430W will automatically switch
to VLOC once established inbound to the Final Approach Fix. But the pilot must then
engage the Approach mode on the autopilot to track the localizer and couple to the
glideslope.
NOTE
Refer to the autopilot systems Aircraft Flight Manual
Supplement and/or POH for details regarding use and
operation of the autopilot system.
Examples here are provided for reference only, based on
operation of the Bendix/King KFC-200 autopilot, and
actual operation may vary depending on the autopilot
system installed in your aircraft.
WARNING
It is your responsibility as Pilot in Command to ensure
that you are familiar with the operation of all installed
equipment. Operation of the PFD in IMC conditions
should not be attempted unless you are proficient in its
use and operation, as described herein.
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For example, suppose you use a GNS-430 to fly a GPS flight plan and have an ILS
instrument approach loaded and active, and the GNS-430 is set for Auto ILS CDI
changeover once you are established inbound on the final approach course. With GPSS
enabled on the PFD and the autopilot in HDG mode, the GPSS will steer the autopilot
laterally through the flight plan using GPS, even after the GNS-430 CDI automatically
switches to VLOC, and the PFD navigation source similarly switches to VLOC. However,
until you switch the autopilot into the Approach mode, it will not arm or capture the
glideslope to fly the ILS approach. This feature is particularly useful for autopilots that
do not automatically transition from Heading mode to Nav mode when the selected
course is intercepted.
CHAPTER 4 REFERENCE GUIDE
Figure 4-112
GPSS Automatically
Disabled — Wings Level Mode
NOTE
With the autopilot in HDG mode, if GPSS is
automatically disabled, the autopilot will roll wings
level; it will not follow the Heading Bug.
Several conditions can cause GPSS to be disabled automatically (switching to a different
GPS steering source on the PFD, losing the GPS navigator source, canceling the flight
plan, etc.). If this happens, the PFD will send a Wings Level command to the autopilot
when in HDG mode, the GPSS Hot Key will annunciate the condition by showing
GPSS in inverse amber, and the GPSS# and inverse A annunciation at the top of the
Navigation Display will be shown with a red slash. (Figure 4-112). To re-engage GPSS,
select a valid GPS navigation source (with valid flight plan or direct-to selection on
the GPS navigator), and then press the GPSS Hot Key. If a valid GPSS signal cannot be
restored, pressing the GPSS Hot Key will cancel GPSS mode and restore the Heading
Bug’s output to the autopilot. More detail on these abnormal conditions, and corrective
pilot actions, can be found in Chapter 6, Expanded Emergency and Abnormal
Procedures. See also Chapter 4, Section 4.7.3. Typical Autopilot Operations.
4.7.2. Flight Director
When connected to a compatible autopilot system, the PFD will display a single-cue
Flight Director (FD). The FD’s command bars visually represent the lateral and vertical
steering cues transmitted to the PFD by the autopilot (Figure 4-113). When the FD
output from the autopilot is unavailable or invalid, the FD command bars are removed
from the display. To hand fly using the FD, maneuver the airplane to tuck the Aircraft
Reference Symbol into the FD’s command bars.
4.7.3. Typical Autopilot Operations
Whenever the PFD installed configuration includes connections to GPS, VLOC, and
autopilot systems, it acts as a data conduit between the navigators and the autopilot.
This enables any compatible navigator to be coupled to the autopilot.
Figure 4-113
Flight Director
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HDG Mode Operation – Heading Bug Steering
Set the PFD Heading Bug to the desired heading (Section 4.4.9).
Verify that GPSS is not selected.
Select the autopilot’s Heading (HDG) mode.
Engage the autopilot and verify that the autopilot turns the aircraft to the
selected heading.
NOTE
When GPSS is enabled, the HSI Heading Bug is not
coupled to the autopilot. To connect the Heading Bug
to the autopilot, disable GPSS with the GPSS Hot Key.
HDG Mode Operation – GPS Steering (GPSS)
1.
2.
3.
4.
Couple the PFD CDI to a GPS navigation source with an active flight plan.
Enable GPSS by pressing the GPSS Hot Key.
Select the autopilot’s Heading (HDG) mode.
Engage the autopilot and verify that the autopilot turns the aircraft to follow
the GPS flight plan.
NAV Mode Operation – VLOC Navigation
1.
2.
3.
4.
5.
Using the CDI Source Select Button, couple a tuned/valid VLOC radio to the
PFD CDI and adjust the Course Pointer (CRS) to a value that will intercept the
course.
Set the PFD Heading Bug.
Engage the autopilot in Heading (HDG) mode and verify that the aircraft turns
to the desired heading.
If your autopilot supports automatic Heading to Navigation mode transitions,
arm Navigation capture on the autopilot by selecting its Navigation (NAV)
mode. Otherwise, select the autopilot’s Navigation (NAV) mode when the
autopilot’s navigation signal capture criteria are satisfied (see your autopilot
AFMS for more information).
Monitor the PFD CDI deflection and verify that, upon intercepting the desired
course, the autopilot modes transition appropriately and the autopilot tracks
the desired course.
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NOTE
The autopilot must be in Heading (HDG) Mode to
receive GPSS signals from the PFD.
NOTE
When using an integrated GPS/VLOC navigator, select
VLOC or GPS with the CDI source Button on the GPS
select until the desired CDI Navigation Source is shown
on the PFD (See Section 4.4.5.)
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1.
2.
3.
4.
NAV Mode Operation – GPS Navigation
CHAPTER 4 REFERENCE GUIDE
NOTE
Not all autopilots operate in the manner described
here for intercepting courses. See the AFMS for your
autopilot installation to understand how to adapt
these example procedures to your particular autopilot.
1.
2.
3.
4.
NOTE
In order for the autopilot to couple to vertical guidance
on GPS WAAS approaches, most autopilots must first
be established on the final approach course and in the
Altitude (ALT) Hold mode at least two miles outside the
Final Approach Fix (FAF). The Approach (APPR) mode
must be annunciated on both the PFD and the GPS.
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5.
6.
With a valid flight plan programmed and active in the GPS, use the CDI
Source Select Button to couple the GPS to the PFD (see Section 4.4.5.).
If AUTOCRS is disabled, set the Course Pointer to the desired course (CRS) (see
Section 4.4.7.), or enable AUTOCRS (see Section 4.4.6.).
With GPSS disabled, set the PFD Heading Bug (see Section 4.4.9.) to a value
that will intercept the active leg of the flight plan, or enable GPSS via the
GPSS Hot Key.
Engage the autopilot in Heading (HDG) mode and verify that the aircraft turns
to a heading to intercept the active leg of the flight plan.
If your autopilot supports automatic heading to nav mode transitions, arm
the navigation capture on the autopilot by selecting its Navigation (NAV)
mode. Otherwise, select the autopilot’s Navigation (NAV) mode when the
autopilot navigation signal capture criteria are satisfied (see your autopilot
AFMS for more information).
Monitor the PFD CDI deflection and verify that, upon intercepting the flight
plan leg, the autopilot modes transition appropriately and the autopilot tracks
the desired course.
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APPR Mode Operation – ILS Approach with Vectors to Final
1.
3.
4.
5.
6.
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2.
Using the CDI Source Select Button, couple a tuned/valid ILS radio frequency
to the PFD CDI, and adjust the course (CRS) (Section 4.4.7).
Set the PFD Heading Bug to a value that will intercept the desired course, or
as instructed by ATC (Section 4.4.9).
Engage the autopilot in Heading (HDG) and Altitude (ALT) Hold modes and
verify that the aircraft turns to the desired heading.
Once cleared for the ILS approach, arm the autopilot’s Approach (APPR)
mode, or continue to fly Heading (HDG) mode until the CDI centers.
Monitor the CDI’s deflection and verify (if supported by your autopilot) that,
upon intercepting the localizer, the autopilot switches to Approach (APPR)
capture, and tracks the localizer course. Otherwise, engage the autopilot
Navigation or Approach mode per the procedures in your autopilot’s AFMS.
Monitor the autopilot localizer tracking performance. Upon intercepting the
glide slope, verify that the autopilot captures the Glide Slope (GS) and initiates
a descent to track the glide slope.
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APPR Mode Operation – GPS or GPS/RNAV APV WAAS Approach
CHAPTER 4 REFERENCE GUIDE
NOTE
WAAS GPS navigators can provide vertical guidance
on several types of GPS/RNAV instrument approaches.
RNAV (GPS) APV (Approaches with Vertical Guidance),
such as LPV and LNAV/VNAV approaches, often have
lower approach minima shown on the approach
plate. Aircraft equipped with appropriate WAAS GPS
equipment may use these lower minima.
Even with more traditional lateral guidance- only
GPS/RNAV approaches (e.g. (LNAV) with step-down
altitudes) WAAS GPS may still provide a pseudo-glide
slope that enables a continuous descent to the MDA
(Minimum Descent Altitude). The autopilot may
consider this a glide slope and attempt to fly it. For this
type of instrument approach, the vertical guidance
is advisory only and the MDA is the appropriate
approach minimum.
These types of approaches are set up and flown the
same way, much like an ILS approach. The pilot must
be aware of the differences and which minima to use.
Page 4-62
1. With a valid GPS approach programmed in the GPS, use the CDI Source Select
Button to couple the GPS to the PFD (see Section 4.4.5.).
2. If AUTOCRS is disabled, set the Course Pointer to the desired course (see Section
4.4.7.), or enable AUTOCRS (see Section 4.4.7.).
3. With GPSS disabled, set the PFD Heading Bug to a value that will intercept the
active leg of the flight plan (see Section 4.4.9.) or enable GPSS via GPSS Hot Key.
4. Engage the autopilot in Heading (HDG) mode and verify that the aircraft turns to a
heading to intercept the active leg of the approach.
5. For autopilots that do not support automatic heading mode to Navigation (NAV)
or Approach (APPR) mode transitions, use the Heading Bug to establish the aircraft
inbound to the Final Approach Fix (FAF) and then engage the autopilot’s Approach
(APPR) mode.
6. For autopilots that support automatic Heading (HDG) to Approach (APPR) mode
transitions, monitor the PFD CDI and verify that, upon intercepting the active leg of
the approach, the autopilot turns to track the GPS approach course guidance.
THE FOLLOWING APPLY FOR WAAS GPS/RNAV APV APPROACHES ONLY
7. Once cleared for the GPS/RNAV approach, select the autopilot’s Approach (APPR) mode.
8. Monitor the PFD CDI and verify that the autopilot intercepts and tracks the final
approach course and the GPS switches to its Approach mode.
9. Most WAAS GPS navigators will not arm or activate vertical guidance until the
aircraft is within two miles of the FAF (unlike an ILS where the VDI will display as
soon as the aircraft is established on the final approach course and a valid localizer
signal with glide slope signal is received). As you approach the FAF, watch for the
VDI to appear on the PFD Attitude Display. This indicates that the autopilot is
ready to capture the glide slope.
10. Monitor the autopilot lateral approach course tracking with the PFD CDI and LDI.
Upon intercepting the WAAS GPS glide slope, verify that the autopilot switches
captures the glide slope and starts a descent.
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GPS APPR Mode Operation – WAAS GPS Underlay to ILS Approach
Using Pilot Navigation and GPSS
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NOTE
The PFD supports GPS LPV approaches (Approaches
with Vertical Guidance) by providing the autopilot
with GPS lateral and vertical deviation signals that are
identical to those typically provided by an ILS radio.
To fly GPS LPV approaches, configure and operate the
autopilot as you would for an ILS approach.
NOTE
Some IFR GPS navigators include ILS approaches
in their procedures database. GPS may be used to
navigate the initial segments of the ILS approach, but
the pilot must switch to VLOC navigation outside the
FAF and before glide slope intercept.
Some integrated GPS/NAV receivers (like the
Garmin 4xx/5xx series) can be configured to switch
automatically, and the PFD Selected CDI Navigation
Source will follow automatically. It is the pilot’s
responsibility to verify that the PFD CDI source is
correctly set to VLOC# before reaching either glide slope
intercept or the FAF.
Page 4-63
CHAPTER 4 REFERENCE GUIDE
1. With a valid ILS approach loaded and activated in the GPS, use the CDI Source
Select Button to couple the GPS to the PFD CDI (see Section 4.4.5.).
2. Verify that the correct ILS frequency is tuned.
3. When the active flight plan leg is the course to the Initial Approach Fix (IAF),
enable GPSS via the GPSS Hot Key.
4. Engage the autopilot in Heading (HDG) and Altitude (ALT) Hold modes and
verify that the aircraft continues to fly the course to the IAF.
5. Monitor the PFD CDI and aircraft track to ensure the aircraft flies to the IAF
and then turns outbound for the course reversal.
6. A WAAS GPS navigator provides guidance along curved flight paths, and will
guide the aircraft through the course reversal and establish it inbound to the
FAF without pilot intervention.
7. Once established on the final approach course to the FAF, engage the
autopilot’s Approach (APPR) mode.
8. Use the PFD CDI Source Select Button to change to the VLOC for the
approach (if not done automatically by the GPS/nav receiver).
9. Monitor the PFD CDI localizer deflection and verify that, upon intercepting
the localizer, the autopilot captures the final approach course and switches to
the Approach (APPR) mode.
10. Monitor the autopilot localizer tracking performance. Upon intercepting
the glide slope, verify that the autopilot captures glide slope and initiates a
descent.
GPS APPR Mode Operation – WAAS GPS Underlay to ILS Approach With ATC
Vectors to Final
CHAPTER 4 REFERENCE GUIDE
1. With a valid ILS approach loaded and activated in the GPS, use the CDI Source
Select Button to couple the PFD GPS to the CDI (see Section 4.4.5.).
2. Verify that the correct ILS frequency is tuned.
3. Set the Heading Bug to the heading assigned by ATC (see Section 4.4.9.).
4. Disable GPSS via the GPSS Hot Key.
5. Engage the autopilot in Heading (HDG) mode and verify that the aircraft turns to
the Selected Heading.
6. When cleared for the approach and given the final heading to intercept the final
approach course by ATC, arm the autopilot’s Approach (APPR) and Altitude (ALT)
Hold modes.
7. Monitor the CDI and aircraft track to verify that the autopilot intercepts the final
approach course and begins to track inbound to the FAF.
8. Use the PFD CDI Navigation Source Select Button to change to the VLOC
source for the approach (if not done automatically by the GPS/nav receiver).
9. Monitor the PFD CDI localizer deflection and verify that, upon intercepting the
localizer, the autopilot captures the final approach course and switches to the
Approach (APPR) mode.
10. Monitor the autopilot localizer tracking performance. Upon intercepting the glide
slope, verify that the autopilot captures the glide slope and initiates a descent to.
4.8. Hazard Awareness
The PFD supports the optional display of Traffic information from a compatible external
sensor (e.g. TCAS, TIS, TAS, ADS-B, etc.).
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4.8.1. Traffic Overlay
The Traffic Overlay will display the traffic symbols on the Navigation Display when the
PFD is configured with one of the following traffic sensors:
CHAPTER 4 REFERENCE GUIDE
r Avidyne TAS 600/610/620 series (TAS)
r Bendix/King KMH 880 (TAS)
r Bendix/King KTA 870 (TAS)
r Garmin GTX 330 (TIS)
Figure 4-114
Traffic Overlay Enabled
r RYAN 9900BX (TAS)
r SKYWATCH SKY 497 (TAS)
r SKYWATCH SKY 899 (TAS)
The TRFC Hot Key enables the Traffic Overlay and the selection of a Traffic Altitude Filter.
The Hot Key Label is inverse green (green label with dark blue letters) when enabled
(Figure 4-114) or a blue label with green letters when disabled (Figure 4-114a).
When the Traffic Overlay is enabled, a TFRC annunciation is presented on the lower left
of the Navigation Display. The traffic setting that was previously reset over a power cycle
is retained as last configured by the pilot.
Figure 4-114a
Traffic Overlay Disabled
Display the Traffic Overlay
1.
2.
Select the 2/2 Hot Key Menu.
Press the TRFC Hot Key to select the desired Altitude Filter.
NOTE
Because of their importance, the PFD will show Traffic
Advisories on the Navigation Display even when the
Traffic Overlay is disabled.
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Page 4-65
CHAPTER 4 REFERENCE GUIDE
4.8.1.1. Traffic Symbols
Traffic Advisory
Other Traffic
Proximity
Advisory
Figure 4-115
Traffic Symbology
NOTE
Refer to your traffic sensor’s Pilot Guide for detailed
information about the sensor limitations and
operational ranges.
Additionally, see the Aeronautical Information
Manual section entitled Traffic Information Service
(TIS) for detailed information about TIS requirements,
capabilities and limitations.
Page 4-66
The PFD will display traffic symbols prioritized in the order received from the
configured traffic sensor. The PFD includes three threat levels using TCAS symbology;
Traffic Advisory (amber circle), Proximity Advisory (cyan diamond), and Other Traffic
(hollow cyan diamond). All traffic symbols within the current display range and the
selected altitude filter are shown relative to the Ownship Symbol (Figure 4-115).
The Traffic Advisory System (TAS) use an airborne interrogator with a half-second
update rate; coverage follows the aircraft. The Traffic Information Service (TIS) system
use a GTX 330 transponder with a five-second update rate; coverage is limited to
specific areas listed in the Aeronautical Information Manual (AIM).
WARNING
Do not rely on the PFD as the sole source of data for collision avoidance. It is the pilot’s
responsibility to visually acquire other aircraft for safe flight. Maneuver your aircraft based
only on ATC guidance or positive acquisition of conflicting traffic. Traffic information is:
r Provided as a proximity warning only
r Intended to assist the pilot in the visual acquisition of other aircraft
r Not intended to provide recommended avoidance maneuvers
r Not provided for aircraft that are not transponder equipped, experiencing a
transponder failure, or out of radar coverage
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The PFD displays traffic information from the sensor with the threat level assigned by
the sensor. The sensor and type of traffic system defines the threat data, range, bearing,
altitude, and altitude trend. Each traffic symbol is positioned at a location representing
the relative range and bearing to the Ownship Symbol.
CHAPTER 4 REFERENCE GUIDE
A data block is provided for each traffic symbol with the relative altitude and vertical
direction (as acquired from the sensor). The data block text color is the same as the
traffic symbol, amber for Traffic Advisories and cyan for Proximity Advisories and Other
Traffic (Figure 4-115).
The relative altitude is shown as two digits indicating the relative altitude difference, in
hundreds of feet, from your aircraft. The altitude value for traffic above the ownship is
preceded by a plus symbol (+) and is displayed under the symbol. The altitude value for
traffic below the ownship is preceded by a minus symbol (-) and is displayed under the
symbol.
An arrow next to the traffic symbol gives the direction of vertical movement in relation
to the your aircraft. Traffic climbing or descending at a rate greater than 500 fpm are
given an up-arrow (climbing), or down-arrow (descending) to the right of the traffic
symbol. Traffic that is at the same altitude, with no vertical trend, is given an altitude
value of 00 below the traffic symbol.
For example, the Traffic Advisory shown in Figure 4-115 is 400 feet above your aircraft
and descending. No altitude information is shown in the data block when the altitude is
unavailable.
Traffic Advisories that are outside the current range are indicated by a half-symbol at
the edge of the Navigation Display with the appropriate data block. Proximity Advisories
and Other Traffic that are outside of the current range are not displayed.
When multiple traffic symbols partially or completely overlap, the symbols are visually
stacked, with the highest priority alert data on top, obscuring the lower priority alert.
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EFD1000 C3 Pro PFD Pilot’s Guide
NOTE
Traffic that is within 100 feet of the ownship shown an
altitude value of 00, above or below the traffic symbol
as appropriate.
NOTE
When the traffic is flying level, no arrow is shown.
When the traffic is not reporting an altitude, neither the
arrow nor the altitude indication is shown.
Page 4-67
When a traffic symbol and the Ownship Symbol partially or completely overlap, the
traffic symbol and data block will overlay the ownship symbol.
CHAPTER 4 REFERENCE GUIDE
NOTE
Depending on the position of the Traffic Advisory at the
edge of the screen, the traffic symbol data block may or
may not display.
NOTE
The altitude filters listed in Table 4-6 are referenced to
your aircraft and the PFD altitudes. The traffic sensor
configured with the PFD may have different (i.e., lower)
altitude thresholds. Check your traffic sensor’s pilot’s
manual for specifics.
4.8.1.2. Traffic Altitude Filter
There are five Traffic Altitude Filter settings: Off, Normal, Unrestricted, Above, and Below
(Table 4-6). Only traffic within the selected altitude filter value will display.
Hot Key Label
Altitude Filter Level
Traffic Display Volume
TRFC
Off
None
TFCN
Normal
±2,700 ft
TFCU
Unrestricted
±9,900 ft
TFCA
Above
+9,900 ft to -2,700 ft
TFCB
Below
+2,700 ft to -9,000 ft
Table 4-6
Traffic Filter Parameters
The pilot selects the Traffic Altitude Filter value by continuously pressing the TRFC Hot
Key, which cycles through each of the filter levels.
Change the Traffic Altitude Filter
1.
2.
Select the 2/2 Hot Key Menu
Press the TRFC Hot Key to select the desired filter level.
The TRFC annunciation displays in the lower left of the display (Figure 4-117).
Figure 4-117
Traffic Altitude Filter
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4.8.1.3. Traffic Unavailable
When the TAS (Traffic Advisory System) sensor’s status is STANDBY, TEST or FAIL:
When the Traffic interface is a TIS (Traffic Information Service) and the Traffic data is:
r Unavailable – TRFC UNVL is annunciated
Figure 4-118
Traffic Sensor Invalid
r Not refreshed within 6 seconds – TRFC COAST is annunciated
r Not refreshed within 12 seconds – TRFC RMVD is annunciated and the Traffic
symbols are removed from view
r Not refreshed for 60 seconds – TRFC RMVD annunciation is removed from view
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Page 4-69
CHAPTER 4 REFERENCE GUIDE
r An Invalid Traffic Sensor annunciation (Figure 4-131) is displayed and the Traffic
symbols are removed from view
CHAPTER 4 REFERENCE GUIDE
This Page Intentionally Left Blank
Page 4-70
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Chapter 5
Customizing the PFD
The following tables and figures provide a brief overview of each menu page and its
menu options.
KEY DESCRIPTION
OPTIONS
Displays Airspeed and
Altitude Tapes1
DISABLE or ENABLE
Radio Altitude
DISABLE or ENABLE
Auto Course Select
DISABLE or ENABLE
ARC Compass Mode
HSI or CDI
AHRS Reset
Action
Figure 5-1
GENERAL SETTINGS A
Table 5-1
Menu – GENERAL SETTINGS A
1. Available only in those installations where an additional airspeed indicator and
altimeter are added or retained within the pilot’s maximum field of view
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Page 5-1
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
5.1. Menu Overview
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
KEY DESCRIPTION
OPTIONS
Barometer Pressure Setting Units of Measure
in Hg or mB
Outside Air Temperature Units of Measure
°C or °F
Auto Range
DISABLE or ENABLE
ALTITUDE:
Figure 5-2
GENERAL SETTINGS B
MACH Display
OFF, ON>5K, ON>6K, ON>7K,
ON>8K, ON>9K, ON>10K, ON>11K,
ON>12K, ON>13K, ON>14K,
ON>15K, ON>16K, ON>17K,
ON>18K
SPEED:
OFF, ON>0.1, ON>0.2, ON>0.3,
ON>0.4, ON>0.5, ON>0.6, ON>0.7
Overspeed Warning Test
Action
Table 5-2 Menu – GENERAL SETTINGS B
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KEY DESCRIPTION
OPTIONS
0, 1, 2, 3, 4
360° Flight Plan
OFF, AUTO
360° Airports
OFF, AUTO
360° VORs (High, Low and Terminal)
OFF, AUTO
360° Intersections / NDB
OFF, AUTO
Figure 5-3
360° MAP SETTINGS
Table 5-3
Menu – 360° MAP SETTINGS
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Page 5-3
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
360° Declutter Level
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
KEY DESCRIPTION
Figure 5-4
ARC MAP SETTINGS
Page 5-4
OPTIONS
ARC Declutter Level
0, 1, 2, 3, 4
ARC Flight Plan
OFF, AUTO
ARC Airports
OFF, AUTO
ARC VORs (High, Low and Terminal)
OFF, AUTO
ARC Intersections / NDB
OFF, AUTO
Table 5-4
Menu – ARC MAP SETTINGS
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091-00019-001 REV B
KEY DESCRIPTION OPTIONS
KEY DESCRIPTION OPTIONS
DISABLE or ENABLE
Vx
0 to 450 or LOCKED
Va
0 to 450 or LOCKED
Vy
0 to 450 or LOCKED
Vbg
0 to 450 or LOCKED
Vlo
0 to 450 or LOCKED
Vref
0 to 450 or LOCKED
Vle
0 to 450 or LOCKED
Vr
0 to 450 or LOCKED
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
V SPEEDS
Figure 5-5
VSPEEDS A
Table 5-6
Menu – VSPEEDS B
Table 5-5
Menu – VSPEEDS A
NOTE
When V Speeds are LOCKED at installation, the legend and set value are shown in gray.
Setting any of the above values to zero removes the affected V Speed.
Figure 5-6
VSPEEDS B
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Page 5-5
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
KEY DESCRIPTION
Figure 5-7
POWER SETTINGS
NOTE
For external/battery power control, the legend of
the current power source is shown in green; pressing
the associated menu key will perform no action. The
legend of an available power source is shown in white,
and pressing the associated menu key changes input
power to that power source.
Page 5-6
OPTIONS
Operating from or Switch to Battery Power. Green when current
state (Pressing key performs no action). White if selection is
possible.
Status or Action
Operating from or Switch to External Power. Green when current
state (Pressing key performs no action). White if selection is
possible.
Status or Action
Restart (Depending on Air/Ground Logic State).
Action
External Power Source Voltage. Displays voltage level of
input power.
Status Only
BATTERY STATUS
DESCRIPTION
##%
Displays battery % charge.
CHARGING
The battery has sufficient voltage and can
accept charging, aircraft power is available,
and the temperature sensor is within limits
(0°C to +55°C).
FAILED
The battery voltage is less than 6 volts; i.e.
insufficient for charging.
READY
The connected battery and battery voltage
are satisfactory, but the temperature limits
(0°C to +55°C) that will permit charging
have been exceeded.
Status Only
Table 5-7
Menu – POWER SETTINGS
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
KEY DESCRIPTION
OPTIONS
Status Only
Input Output Processor Software Version
Status Only
Unit Serial Number
Status Only
Table 5-8
Menu – SYSTEM STATUS
Figure 5-8
SYSTEM STATUS
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Page 5-7
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
Main Application Processor Software Versions
5.2. Customizing Basemap Symbol Declutter Settings
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
The pilot can customize the Basemap symbol declutter settings to Level 4, Level 3,
Level 2, Level 1, or Level 0 (OFF) by pressing the MENU Button and selecting the 360
MAP SETTINGS Menu page or the ARC MAP SETTINGS Menu page.
Each Compass Mode has its own Menu page for Map Setting basemap symbol
display.
Figure 5-9
360° Compass Mode Display Options
r
The 360 MAP SETTINGS Menu page offers Map Setting options for the 360°
Compass Mode (Figure 5-12).
r
The ARC MAP SETTINGS Menu page offers Map Setting options for the ARC
Compass Mode (Figure 5-13).
As described in Table 5-9, the selected declutter level and range determine which
Basemap symbols are displayed. Basemap symbol identifiers may also be shown next to
their symbol.
See Chapter 4, Section 4.4.1. for more details about Compass Mode options
Figure 5-10
ARC Compass Mode Display Options
Page 5-8
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Set Map Symbol Display
1.
2.
3.
Figure 5-11
Editing 360° Airports Display Option
Figure 5-12
360° Airports Display Option Set To OFF
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Page 5-9
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
4.
5.
Press the MENU Button.
Rotate the Right Knob to navigate to the appropriate Map Settings Menu
page.
Press the desired Map Symbol Menu Key.
The menu label turns magenta, and the EDIT VALUE label displays above the
Right Knob (Figure 5-11 and 5-12).
Rotate the Right Knob to the desired value.
Select another Map Symbol Menu Key and edit the display option or press
the MENU Button to exit.
Feature Group & Layer Order
(top to bottom)
Max Range
Declutter Setting
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
Figure 5-13 Level 4
Overlay — enabled
via Hot Key
Figure 5-14 Level 3
Figure 5-15 Level 2
Traffic Overlay Symbol
1
Ownship Symbol
2
Always ON regardless of declutter level
Instruments1 and Annunciations2
3
Always ON regardless of declutter level
Flight Plan Legs and Waypoints3
4
200
Airports3
5
100
NDBs3
6
15
VORs, (HIGH, LOW, Terminal)3
7
200
Intersections
8
15
Figure 5-16 Level 1
Figure 5-17 Level 0 (Off)
Always ON regardless of declutter level
Table 5-9
Map Feature Group Layering, Range, and Declutter Levels
No symbols, legs,
or waypoints—
regardless
of selected
range— are
displayed.
When selected,
the Basemap
declutter and
range display
for two seconds
and then are
removed from
view. The MAP
Hot Key legend
is shown in gray.
1. e.g. VSI, Direction Indicator, CDI, TO/FROM
2. e.g. NAV INFO Block, Range
3. Shown only when data is provided by a compatible and connected GPS system
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5.3. Configuring Vspeeds
Vspeeds are used to designate different operating speeds of the aircraft and are defined
in Table 5-10.
DEFINITION
Vne
Never exceed
Vno
Maximum structural
cruising speed
Vfe
Maximum full flap
extension speed
Vs
No flap stall
Vso
Stall speed in landing
configuration
Va
Design maneuvering
speed
Vbg
Best glide
Vr
Rotation speed
Vref
Landing reference speed
Vx
Best angle of climb
Vy
Best rate of climb
Vle
Maximum landing gear
extended speed
091-00019-001 REV B
PRE-SET
BANDS
ADJUSTABLE
TEXT LABELS
PRE-SET
MARKERS
(Red Line)
NOTE
Setting the value of the white triangle, Vyse, and Vmc
markers to zero (0) during installation disables the
markers. Setting any of the adjustable Vspeed values to
zero (0) disables the associated label.
EFD1000 C3 Pro PFD Pilot’s Guide
Page 5-11
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
Vspeed
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
Vspeed
DEFINITION
PRE-SET
BANDS
ADJUSTABLE
TEXT LABELS
PRE-SET
MARKERS
Vlo
Maximum landing gear operating
speed
Vmc
(Multi-engine) Single-engine
minimum control airspeed
(Red Line)
Vyse
(Multi-engine) Best single-engine rate
of climb
(Blue Line)
Maximum initial flap extension speed
Table 5-10
Vspeed Definitions
Page 5-12
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The PFD uses color speed bands, color speed markers, and textual labels to help the
pilot recall Vspeed settings and limits. The speed band markings are determined by the
Federal Regulations and correspond to the aircraft operating speeds that are identified
in the Aircraft Flight Manual. They have a range between two speeds that are pre-set at
installation as outlined in Table 5-11 and shown in Figure 5-18.
BAND COLOR
SPEED RANGE
Red Band (High
Speed)
Vne–top tape
Never Exceed
Yellow Band
Vno – Vne
Caution Range
Green Band
Vs – Vno
Normal Operating Range
White Band
Vs0 – Vfe
Flap Operating Range
Red Band (Low
Speed)
Bottom of tape – Vs0
Disabled on the ground and during
takeoff
Figure 5-18
Speed Bands
Table 5-11 Speed Band Ranges
NOTE
NOTE
The color speed bands and color speed markers on the PFD Airspeed Tape are configured
to match the certified mechanical airspeed indicator.
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On aircraft without flaps, the white band is disabled,
and the green band is shown full width, as there isn’t
an applicable Flap Extend (Vfe) or Full Flap Stall (Vs0)
speed. These two speeds are set to the same speed as
the No Flap Stall (Vs) speed. This gives the white band a
value of zero, effectively disabling it.
Page 5-13
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
Speed markers are also pre-set during installation, indicating important aircraft-specific
speeds, where applicable. The textual Vspeed labels are made pilot adjustable or locked
during the PFD installation.
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
On aircraft with flaps, setting the upper and lower thresholds of the white and/or yellow
bands to the same value disables the applicable band. When disabled, the band does
not display.
Figure 5-19
VSPEEDS A
When using the Vspeed textual markers, the pilot must first ENABLE the display of
the markers and then set values for each Vspeed. The value range for Vspeed textual
markers is 0 – 450 or LOCKED. The default setting is 0 unless previously set to another
value. When the value is 0, the Vspeed is individually disabled, and the marker is not
shown on the Airspeed Tape. Once the values are set, the pilot can choose to disable all
the Vspeed textual markers to declutter the Airspeed Tape.
Display or Hide the Vspeed Textual Markers on the Airspeed Tape
1.
2.
3.
Figure 5-20
Editing VSPEEDS
4.
5.
Press the MENU Button.
Rotate the Right Knob to the VSPEEDS A menu page (Figure 5-19).
Press the VSPEEDS Menu Key.
The Menu label turns magenta, and the EDIT VALUE label displays above the
Right Knob (Figure 5-20).
Rotate the Right Knob to select ENABLE or DISABLE (Figure 5-21).
ENABLE will display the Vspeeds on the Airspeed Tape and DISABLE will hide
the Vspeeds to declutter the Airspeed Tape.
Press the MENU Button to exit.
Figure 5-21
VSPEEDS Disabled
Page 5-14
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091-00019-001 REV B
Set Textual Vspeed Labels
1.
2.
3.
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
4.
5.
Press the MENU Button.
Rotate the Right Knob to the appropriate Vspeed Menu page (Figure 5-22).
Press the appropriate Vspeed Menu Key.
The menu label turns magenta, and the EDIT VALUE label displays above the
Right Knob (Figure 5-23).
Rotate the Right Knob to the desired value (Figure 5-24).
Select another Menu Key and edit another Vspeed or press the MENU Button
to exit.
Figure 5-22
VSPEEDS A
NOTE
A typical installation sets the Airspeed Textual Markers to UNLOCKED, allowing the pilot
to edit the indicated Vspeed labels. If the Vspeed setting was LOCKED during installation,
no pilot adjustment is allowed.
Figure 5-23
Editing Va Vspeed
Figure 5-24
Va Vspeed Set With New Value
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Page 5-15
5.4. LCD Brightness Control
CHAPTER 5 CUSTOMIZING THE EFD1000 PFD
The LCD brightness of the PFD operates in either of two modes, Automatic or Manual
(Figures 5-25 and 5-26). The LCD brightness range is displayed as a value from 1–100,
displayed above the Left Knob.
Figure 5-25
Display Brightness in BRT AUTO Mode
Figure 5-26
Display Brightness in BRT ADJUST Mode
NOTE
When the PFD is operating on the internal battery,
the maximum brightness level is capped at 40% in
automatic mode and 70% in manual mode to preserve
battery operating time.
NOTE
To facilitate cooling of the PFD display unit, when
the backlight temperature is greater than or equal to
70°C, the display brightness level is limited to 30% in
automatic mode and 70% in manual mode. The limits
are removed when the PFD display temperature drops
below 60°C.
Page 5-16
LCD MODE
DESCRIPTION
AUTOMATIC
BRT AUTO
LCD backlight intensity is automatically adjusted based on the ambient
lighting conditions sensed by the Automatic Dimming Photocell (Figure
5-25). When using the auto-brightness, the maximum brightness level is
70%.
MANUAL
BRT ADJUST
Allows the pilot to adjust the LCD backlight intensity. (Figure 5-26) from
1–100%.
Table 5-12 Brightness Control
Change Brightness Mode
1.
2.
3.
Press the MENU Button.
Press the Left Knob to select the desired LCD Brightness Control mode, either
Automatic (BRT AUTO) (Figure 5-25), or Manual (BRT ADJUST) (Figure 5-26).
Press the MENU Button to exit the Menu.
Adjust Display Brightness Manually
1.
2.
3.
Switch to manual LCD Brightness Control mode (BRT ADJUST) (Figure 5-26).
Rotate the Left Knob clockwise to increase the display brightness or
counterclockwise to decrease the display brightness. The BRT: value changes
accordingly.
Press the MENU Button to exit the Menu and retain the selected brightness
level.
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Chapter 6
Expanded Emergency and Abnormal
Procedures
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
This section supplements and provides an expanded description of the
emergency and abnormal procedures included in the FAA-approved
Aircraft Flight Manual Supplement. The information provided here is
intended to provide additional background information to enhance
the pilot’s understanding of the emergency and abnormal conditions
and the associated procedures provided in the AFMS. This pilot guide
is provided for supplementary purposes only. The approved cockpit
reference for in-flight use is the AFMS. Both the Pilot Guide and the
AFMS must be immediately available to the pilot at all times in flight. In
the event of any conflict between this document and the FAA-approved
AFMS, the AFMS instructions must be followed.
Page 6-1
6.1. Pitot/Static System Blockage
A pitot line blockage will result in the airspeed indicator behaving like an altimeter
when the aircraft’s altitude changes, and it will not respond to airspeed changes. A pitot
line blockage can also affect the PFD’s attitude indication.
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
A static line blockage will result in altitude remaining fixed and a zero vertical speed
despite aircraft pitch and/or power setting changes. In addition, IAS indications will
be incorrect if the static line is blocked. Errors will typically be noticed during climbs
or descents. When descending, ambient pressure increases which will result in the
indicated airspeed reading more than the actual airspeed. The opposite effect will be
observed in a climb. A static line blockage can also affect the PFD’s attitude indication.
Indication of an obstructed pitot system is provided for PFD when the PFD’s indicated
airspeed is less than 30 KIAS (35 mph) and GPS ground speed is greater than 50
kts (58 mph), then attitude and heading instruments are replaced with red Xs and
textual annunciations to indicate their failure. In this case, an amber CHECK PITOT
HEAT annunciation accompanies the ATTITUDE FAIL annunciation. When the pitot
obstruction is subsequently removed and indicated airspeed ≥ 30 KIAS (35 mph), the
CHECK PITOT HEAT annunciation will be removed in 15 seconds. This indicates that
the PFD is performing an automatic AHRS reset in the background. No pilot action is
required to reset the system.
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Blocked Pitot or Static Line Suspected
1.
2.
3.
4.
5.
Turn Pitot Heat ON
Open the Alternate Static Source
Refer to alternate attitude, airspeed, altitude, and heading sources for primary
flight information
Consider exiting IMC
Land as soon as practicable
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
CAUTION
Most light aircraft have only a single pitot and static port available for flight instrument
use. As such, the pitot and static lines used by the PFD are shared with those lines used by
the standby airspeed indicator and altimeter. Should these lines become blocked, such
as might occur due to an inadvertent icing encounter, the PFD, the standby airspeed
indicators and the altimeters will display erroneous information.
Because the PFD uses pitot and static pressures as part of the ADAHRS solution, loss or
corruption of this data, such as from a line blockage, will affect the attitude and heading
information.
Whenever an erroneous pitot input is detected by the PFD inflight, it will replace
the affected instruments with red Function Fail Xs and display a CHECK PITOT HEAT
annunciation. In this case, the pilot should check pitot heat, select the aircraft’s
alternate static source and refer to secondary sources of attitude, airspeed, and heading
information.
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6.1.1. Identifying and Handling Suspected Pitot and/or
Static System Failures
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Blocked pitot and/or static system ports will compromise the PFD’s attitude solution
and soon cause it to Red-X (fail). Immediately begin flying by reference to backup
attitude sources. Therefore, the pilot must be especially vigilant about verifying proper
operation of the pitot and static systems both before and during flight.
It is important to check the pitot tube and static system ports, and to verify pitot heater
performance, as part of a thorough pre-flight inspection, especially when anticipating
flight in low IMC.
On takeoff roll, it is good practice to note and call out “airspeeds alive” when the
airspeed indicators (both primary and backup) begin moving and to compare and call
out readings at a pre-determined airspeed close to, but before rotation speed (e.g.
“60 knots cross check”), consciously noting the performance on each takeoff. If the
airspeed indicators do not come “alive” when they usually do or whenever there is a
significant difference between the primary and backup indicators and sufficient runway
is remaining, aborting the takeoff may be a prudent decision. Follow the Flight Manual
procedures for your aircraft.
When the static port is blocked on takeoff, it is imperative to quickly recognize the
condition. Sometimes the airspeed indicator will show substantially less than normal and
the airspeed will reduce in the climb. The natural—but incorrect—response is to lower
the nose. In this situation, maintaining proper pitch attitude to climb is vital. The airspeed
will continue to reduce as you climb, and at about 1,000 feet AGL the PFD attitude and
heading indications will be Red-X due to the reduced airspeed indication. As soon as
you suspect a blocked static port, try switching to an alternate static source. Know the
location of the alternate static air control in your airplane and learn how it works.
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
On the initial climb-out after takeoff, it is also good practice to note and call out passing
through a pre-determined altitude above ground level (AGL) a couple of minutes after
takeoff and ideally before entering the clouds (e.g. “2,000 feet”). If your primary and
backup instruments are not showing the altitude and airspeed you normally expect to
see at that point, you might have partially blocked static system ports. This AGL check
and call-out is also a good time to verify that no fuel is siphoning out from the fuel caps,
etc. If indications suggest a static system blockage, try switching to an alternate static
air source and consider landing to correct the problem.
In flight, if airspeed or altitude anomalies consistent with an obstructed pitot or static
line are observed, the pilot should recognize that the PFD attitude indication will soon
be compromised. If in IMC, immediately use the backup attitude indicator to fly the
airplane and turn pitot heat ON if icing is suspected. If at any time there is suspicion of
an obstructed pitot or static line, use the backup attitude indicator until the situation
is resolved.
If the pitot tube becomes blocked in flight, the most common cause is icing. In-flight
indications of a blocked pitot tube are typically:
1) All airspeed indicators incorrectly show zero (or close to zero);
or
2) Airspeed in level flight does not change in response to changes in power or
drag and airspeed indications act like an altimeter (decreasing in a descent
and increasing in a climb, exactly the opposite of normal behavior).
Airspeed going to zero is by far the most common symptom of a blocked pitot tube.
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If you see either of these indications of a blocked pitot tube, the first thing to do is turn
on the pitot heat to remove any ice blockage. This will quickly restore the attitude and
airspeed indications on the PFD systems (it takes about 40 seconds to recover after the
pitot pressure is restored).
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
To maintain proper aircraft attitude during the event (and if the heated pitot does
not work), use the outside horizon if possible, or use the backup attitude indicator to
continue safe flight. The autopilot attitude source is also independent of the PFD’s
attitude indicator and may be another means to maintain level flight. Use the autopilot
carefully and constantly monitor its performance against other flight instruments.
If in flight you suspect blocked static ports (probably due to icing), try switching to the
alternate static air source. If the static air sources are blocked, recognize that the readout
from the transponder and reports from ATC will be in error because of the blocked
static system.
If GPS altitude is available on your GPS navigator, become familiar with how the GPS
altitude is displayed. Although it can be in error, it might be your only source of altitude
information (WAAS GPS altitude is reasonably accurate).
If an instrument approach is necessary, consider a precision approach that will permit
vertical guidance with less reliance on the barometric pressure altitude indications.
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6.2. Frequent or Persistent
CROSS CHECK ATTITUDE Annunciation
Refer to alternate attitude, airspeed, altitude, and heading sources for primary flight
information. Consider the following:
CROSS CHECK ATTITUDE
Reference standby mechanical attitude indicator
Turn Pitot heat ON
Consider exiting IMC
Land as soon as practicable
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
1.
2.
3.
4.
For a detailed explanation of when and why the PFD may display a CROSS CHECK
ATTITUDE annunciation, either momentarily or persistently, see Chapter 4, Section 4.1.
Air Data, Attitude and Heading Reference System (ADAHRS).
6.3. Difference Detected Between the PFD
and Mechanical Attitude Indicators
Once diagnosed, ensure the correct attitude source is the only one referenced during
the remainder of the flight.
Compare Alternate Sources of Available Attitude, Airspeed, and Attitude
1.
2.
3.
Compare all available sources of attitude, airspeed, and attitude information
to diagnose a faulty indicator.
Consider exiting IMC.
Land as soon as practicable .
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6.4. Abnormal Shutdown Procedure
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Figure 6-1
Powering Off the
PFD
The PFD is typically powered through an PFD master switch that is connected to the
aircraft’s Battery bus. Normally, the PFD will power down when the PFD Master switch
is turned OFF or when aircraft power is removed when on the ground. To force the PFD
to power down, the following procedures are provided.
Shutdown PFD (on ground)
1.
2.
PFD Master switch OFF
Press and hold the REV Button until the display turns off (Figure 6-1)
1.
2.
3.
Press the MENU Button.
Rotate the Right Knob to the POWER SETTINGS Menu page
Press the SHUT DOWN Menu Key. The power down sequence initiates, and a
power down message displays
Or
A powering off annunciation displays indicating that the unit will shut down in 5
seconds. The pilot can press any control to abort the power-down sequence.
Power On Manually
r
Page 6-8
Press and hold the REV Button until the PFD powers on
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6.5. Loss of Aircraft Electrical Power
In the event that aircraft generated power is degraded or fails, the PFD will
automatically switch to its own dedicated battery (Figure 6-2). When continued safe
operation depends on the PFD, UNRESTORABLE LOSS OF EXTERNAL POWER IS AN
EMERGENCY SITUATION. The aircraft should divert to the nearest suitable airport.
1.
2.
Electrical System .....................................................Follow AFM procedures to restore
power
If unable to restore power ................................Land as soon as possible
The internal battery will normally provide between 30-60 minutes of operation at
approximately 20°C and warmer. At extreme cold temperatures, operation of the
internal battery is not assured.
When on battery, the auto backlight intensity level defaults to 40% and manual
backlight intensity is limited to 70%. Changing the backlight intensity will affect the
battery duration which is reflected in the % remaining indication.
Figure 6-2
Battery Charge Remaining
A fully charged battery will indicate a charge level of 99% for some time before
beginning to discharge. The charge level will steadily decrease when below 95%, with a
slight acceleration as the battery nears 0%.
The “ON BAT” annunciation, along with the estimated battery charge remaining is
displayed whenever the system is operating on battery.
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Loss of or Degraded Aircraft Power or ON BAT Annunciation
NOTE
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
When operating on the internal battery, the display
backlight intensity is limited to a value of 70.
NOTE
Setting the brightness to a value of greater than 40%
will reduce the battery operation time to less than 30
minutes.
WARNING
When fully charged, the internal battery will power the PFD to provide ADAHRS and
emergency RSM GPS position (if enabled) for approximately 30 minutes. When continued
safe operation depends on the PFD’s primary flight data, UNRESTORABLE LOSS OF
EXTERNAL POWER IS AN EMERGENCY SITUATION. The pilot should follow the
electrical failure checklist in the Aircraft Flight Manual land as soon as possible.
CAUTION
During situations where a high electrical demand is placed on the aircraft electrical
system, electrical transients that cause aircraft voltage to drop below 9.0V momentarily
or 12.3V for 2 minutes (14V electrical system) or 18.0V momentarily or 24.6V for 2 minutes
(28V electrical system) will cause the PFD display to automatically switch to its internal
battery.
This will be accompanied by an ON BAT annunciation.
The ON BAT annunciation should extinguish shortly after the electric transient demand
goes away. If the ON BAT annunciation does not extinguish, then an aircraft power source
failure has most likely occurred.
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6.5.1. Overvoltage Protection
In the event of an overvoltage condition in the aircraft’s electrical system, (greater
than 33 volts) the PFD will automatically switch to its battery power and continue to
operate without any pilot action. Operation from the aircraft electrical system will not
be possible while the overvoltage condition is present. When aircraft power decreases
below 33 volts, pilot action is required to manually switch from the PFD battery power.
1.
2.
3.
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Restore Aircraft Power to the PFD
Press the MENU Button and rotate the Right Knob to the POWER Settings
page
Press the EXT PWR Menu Key
Press the MENU Button to exit
6.6. GPS Failures and RSM Emergency GPS Use
Position and flight plan data for the PFD is provided from aircraft panel-mounted GPS
equipment. The PFD may be configured to receive data from one or two external GPS
receivers. In addition, if all aircraft GPS receivers fail, the RSM’s emergency GPS receiver
will provide position data if enabled by the installer.
The basemap will follow an automatic position reversion scheme to determine which
GPS is used to provide position data to the map. The primary GPS is always the one
selected by the pilot using CDI Navigation Source Select Button. If the selected GPS
fails, the PFD automatically switches to the other aircraft’s GPS (if installed) and will
annunciate GPS# REVERSION, where # represents the GPS source providing the position
data (Figure 6-22).
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
If all aircraft panel-mounted GPS receivers experience a failure, the RSM Emergency
GPS receiver will provide position data that is shared among all EFDs. In addition, a text
alert is presented at the bottom center of the Navigation Display annunciating RSM
GPS REVERSION EMER USE ONLY (Figure 6-23). This “sharing” feature permits any EFD
(as configured by the installer), to receive and display the RSM GPS position data, thus
assuring continuous navigational awareness to the pilot. In this case, the basemap data
is approved for emergency use only.
Whenever the map has reverted to an alternate position source, all map features and
capabilities are retained, including the display of the flight plan from the selected panelmount GPS. However, when the selected GPS is no longer providing position data, the
flight plan is displayed without an active (magenta) leg. The flight plan and basemap
data from each of the aircraft’s GPS receivers is retained independently. If two external
GPSs were connected prior to failure of both, and if each had a different flight plan at
the time of failure, both retained flight plans remain available to the pilot and may be
selected using the PFD’s Navigation Source Select Button.
In the unlikely event that there is a complete loss of all GPS data to the EFD, including
failure of the RSM GPS receiver, all mapping information would be removed from the
EFD display.
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6.7. Power Override
In the event that the pilot wishes to override the PFD’s automatic power configuration,
proceed as follows:
Power Override
1.
MENU .............................................................................“POWER SETTINGS” Page
2.
“BATTERY” LINE SELECT KEY..............................PRESS
When airborne, if the PFD’s input voltage is below the
12.8V (14V Electrical System) or 25.6V (28V Electrical
System) automatic battery transition threshold, and
EXT PWR is selected through the POWER SETTINGS
Menu, the PFD will automatically remain connected to
its internal battery.
To switch FROM internal Battery TO aircraft power:
3.
“EXT PWR” LINE SELECT KEY .............................PRESS
View External Voltage Status
1.
2.
3.
4.
Press the MENU Button.
Rotate the Right Knob to the POWER SETTINGS Menu displays.
The EXT PWR Menu Key (Figure 6-3) displays the external power voltage.
Press the MENU Button to exit.
View Internal Battery Status
1.
2.
3.
4.
Press the MENU Button.
Rotate the Right Knob to the POWER SETTINGS Menu displays.
The BAT Menu Key (Figure 6-4) displays the current Battery Status as either
Charging or a Percentage of Charge.
Press the MENU Button to exit.
Figure 6-3
External Power Voltage Status
Figure 6-4
Battery Status
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
To switch FROM aircraft power to Internal Battery:
NOTE
6.8. In-Flight AHRS Reset
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Figure 6-5
Attitude Degraded Performance
In the unlikely event the PFD determines a potential degradation of attitude
information, a warning annunciation, CROSS CHECK ATTITUDE, is shown (Figure 6-5).
If the attitude pitch or roll data become invalid, a red X and the textual annunciation
of ATTITUDE FAIL replaces the Attitude Indicator, and all aircraft roll, pitch, and
slip information is removed from the Attitude Display (Figure 6-6). Use alternate,
mechanical flight instruments for primary flight information and reset the PFD’s AHRS as
soon as possible.
During the In-Flight AHRS Reset, the aircraft should not be subjected to excessive turn
rates. Typical in-flight Resets will take approximately 30 seconds, but can take longer if
the reset is initiated while banked or maneuvering.
Figure 6-6
Attitude Failure
NOTE
When the PFD’s AHRS is reset in flight, it performs an
abbreviated initialization.
The AHRS Reset is considered complete when the PFD’s
attitude and heading is once again displayed, stable,
and correct with respect to the horizon or standby
attitude indicator.
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Perform an In-Flight AHRS Reset
8.
9.
Maintain straight and level flight.
Consider exiting IMC.
Fly by visual reference or by standby instruments.
Disconnect the autopilot.
Press the MENU Button.
Rotate the Right Knob to display the GENERAL SETTINGS A Menu page.
Press the AHRS RESET? Menu Key (Figure 6-7).
A confirmation message displays, prompting the user to confirm the reset
request (Figure 6-8).
Press the AHRS Menu Key again to confirm the AHRS reset. The AHRS reset is
performed, and the confirmation messages clears.
Press the MENU Button to exit.
Figure 6-7
AHRS Reset Menu Key
Figure 6-8
AHRS Reset Confirmation Message
NOTE
Pressing any other key, button, or knob cancels the
AHRS reset and clears the confirmation message.
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
1.
2.
3.
4.
5.
6
7.
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
6.9. GPSS Operation, Annunciations,
and Autopilot Modes
The Pro PFD offers GPSS. Three modes, Enabled, Wings Level, and Disabled, are possible
and annunciated in the PFD’s Navigation Display. When enabled, the configured GPS
source not only provides the basemap and flight plan data, but also passes GPSS as
the heading input to a configured autopilot. When engaged, a configured autopilot
will interpret GPSS commands as heading inputs and follow the active GPS flight plan,
including anticipated turns, if provided. The GPSS Enabled mode is indicated by a green
GPSS Hot Key label and a GPSS1 with an inverse A placed next to the Selected Heading
Field to describe the source (Figure 6-9) .
Figure 6-9
Operating in GPSS Mode
If GPSS is enabled and the GPS source is lost or changed, the GPSS mode automatically
changes to the Wings Level mode and annunciates as shown in Figure 6-10.
The Wings Level mode removes roll steering inputs to the autopilot, causing the
aircraft to roll wings level, and displays a red slash through the annunciated A HDG and
GPSS# source. The amber GPSS Hot Key label requires pilot action. If this occurs, do the
following:
NOTE
Figure 6-10
GPSS in Wings Level Mode
Page 6-16
When using GPSS with combined GPS / VLOC navigators (e.g. GNS 430/530), VLOC may
be selected as the navigation source while GPSS is engaged. To avoid confusion, note
the PFD Selected CDI Navigation Source controls the CDI and the autopilot’s navigation
and approach modes when engaged. GPSS reflects the heading commands required
to navigate the active flight plan leg and controls the autopilot’s heading mode when
engaged. Complete understanding of autopilot mode functions and their proper selection
is recommended.
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When GPSS Automatically Changes to Wings Level Mode
1.
2.
3.
Check the configured GPS source.
Check the PFD Selected CDI Navigation Source.
If the selected GPSS source is restored or changed, and GPSS is still desired,
press the GPSS Hot Key to activate GPSS. (The GPSS Hot Key label turns inverse
green).
Disable GPSS
Adjust the PFD HDG bug as desired.
Check or set the Autopilot Control Panel modes as desired.
Press the GPSS Hot Key until the Hot Key label turns gray (Figure 6-11).
Figure 6-11
GPSS Disabled
NOTE
The configured GPS source must provide an active flight plan (or Direct-To waypoint) for
GPSS to remain engaged or to be restored.
When the PFD’s navigation source is changed to another configured GPS or VLOC source
for longer than 2 seconds, the GPSS Enabled mode will change to Wings Level. The pilot
must then press the GPSS Hot Key to restore or disable GPSS, as desired.
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NOTE
When the GPSS is enabled and the autopilot is
engaged in the Heading (HDG) mode, disabling the
GPSS will cause the autopilot to follow the HDG Bug.
Page 6-17
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
1.
2.
3.
6.10. Warning, Caution, and Advisory Summary
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
WARNINGS
Presented when the PFD is operating on the internal battery. The countdown timer begins at 15
seconds and is then replaced by the ON BAT annunciation with the battery’s % charge remaining.
NOTE
Figure 6-12
Battery Countdown
Figure 6-13
Battery Charge Remaining
If the battery temperature is less than 0° C, the countdown timer will begin at 10 minutes.
Presented when the PFD has determined that the associated function is invalid or failed and should
not be used. The data is removed from the display and replaced by a red X over the affected display
feature.
Figure 6-14
Attitude Fail
Page 6-18
Figure 6-15
Direction Indicator Fail
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WARNINGS
Figure 6-16
Chevrons indicate Pitch Down
Figure 6-17
Chevrons indicate Pitch Up
Table 6-1
Warning Annunciations
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
When the Attitude Indicator display extreme pitch up or extreme pitch down attitudes, the red
chevrons indicate the direction to restore level flight.
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
CAUTION
Presented when the PFD AHRS internal integrity monitor determines that attitude is potentially
degraded. If a CROSS CHECK ATTITUDE annunciation is presented, the pilot should cross check
attitude, airspeed, and altitude indications with other sources of primary flight information.
Figure 6-18
Cross Check Attitude
The CHECK PITOT HEAT annunciation accompanies the ATTITUDE FAIL annunciation, and is
presented when the software detects an obstruction in the pitot system that could potentially
degrade the attitude solution. This annunciation is removed when the detected condition is
resolved, which would be followed by an automatic AHRS reset. A GPS is required for this monitor
to be enabled.
Figure 6-19
Check Pitot Heat
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CAUTION
Figure 6-20
GPS Invalid
Figure 6-21
RSM GPS
Figure 6-22
GPS Reversion
Figure 6-24
GPS Integrity Flag
Figure 6-25
Altitude Caution
Figure 6-26
Decision Height Caution
091-00019-001 REV B
Figure 6-23
GPS Reversion Emergency
Presented when the PFD Selected CDI Navigation Source is a GPS and that GPS is sending an
Integrity alert (see GPS AFMS for more information)..
Presented to indicate the aircraft is reaching (steady) or deviating (flashing) from the preset altitude.
May be accompanied by an optional one-second steady tone.
Presented when a connected radio altimeter indicates it has reached the altitude set by the pilot
(see Radio Altimeter AFMS for more information).
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Page 6-21
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Presented when a configured GPS source’s data is invalid or unavailable. GPS# or RSM REVERSION
annunciations indicate the current GPS basemap source.
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
CAUTION
Presented when the previously enabled and valid GPSS source is lost or has changed. Indicates the
GPSS Wings Level mode.
Figure 6-27
GPSS Source Lost/Changed
The Minimums Markers are presented on the altitude tape and the Selected Minimums Field is
presented on the Attitude Display when the MIN Hot Key is selected. The markers include three
components – a green triangle at 500 ft. above minimums, a hollow yellow triangle at 100 ft. to 200
ft. above minimums, and a red and yellow striped triangle at the selected minimums.
Figure 6-28
Minimums Caution
The MIN legend in the Selected Minimums Field turns inverse amber to alert the pilot whenever
the aircraft is at or below the selected minimums setting. When configured, an optional Sonaltert
generates a one-second stuttered tone .
Table 6-2
Caution Annunciations
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ADVISORY
Presented when the REV Button is pressed.
Presented when GPSS is enabled and the GPS source is valid. Either GPSS1 or GPSS2 may be
annunciated, depending on selection and the number of configured GPS navigators. This also indicates
the autopilot heading source.
NOTE
Figure 6-30
GPSS On
091-00019-001 REV B
GPSS will always reflect the GPS Basemap source in the Navigation Display and follow its source.
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CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Figure 6-29
REV Button Off
ADVISORY
CHAPTER 6 EXPANDED EMERGENCY AND ABNORMAL PROCEDURES
Associated with the GPS and the Selected CDI Navigation Source (see the GPS AFMS for
more information).
Figure 6-31
GPS Annunciations
NOTE
These annunciations do not display for RS232-based GPS.
Figure 6-32
Navigation Source Invalid or
Unavailable
A horizontal red line through the Selected CDI Navigation Source indicates that the data from the
source is invalid or unavailable.
Figure 6-33
Traffic Enabled
Indicates the traffic sensor is enabled.
Figure 6-34
GPSS Disabled
GPSS Hot Key label with a blue background and gray letters indicate that the GPSS is disabled.
Table 6-3
Advisory Annunciations
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Chapter 7
Appendices
7.1. Operating Limitations
CHAPTER 7 APPENDICES
Refer to the latest version of the Airplane Flight Manual Supplement
(AFMS) , Aspen Avionics document 900-00008-001 for the limitations that
apply to your specific aircraft installation.
The AFMS and this Pilot’s Guide must be carried in the aircraft and be
immediately available to the pilot while in flight.
For installations that include the optional EFD1000 MFD and/or the
EFD500 MFD, the EFD1000/500 MFD Pilot’s Guide, Aspen Avionics
document 091-00006-001, must be carried in the aircraft and be
immediately available to the pilot while in flight.
7.2. Software Versions and Serial Number
The system software versions for the Main Application Processor (MAP) and for the
Input-Output Processor (IOP) are displayed via the Menu SYSTEM STATUS page. The
ACU software version number is recorded on a software version label affixed to the ACU
hardware.
The Primary Flight Display Unit’s serial number is also found in the SYSTEMS STATUS page.
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View the Main Application Processor Software Version
1.
2.
3.
4.
Press the MENU Button. The Menu displays on the Navigation Display.
Rotate the Right Knob to the SYSTEM STATUS menu page.
The MAP VER Menu Key displays the current Main Application Processor
Software Version (Figure 7-1).
Press the MENU Button to exit the Menu.
CHAPTER 7 APPENDICES
Figure 7-1
View Main Application Processor
Software Version
View the Input/Output Processor Software Version
1.
2.
3.
4.
Press the MENU Button. The Menu displays on the Navigation Display.
Rotate the Right Knob to the SYSTEM STATUS menu page.
The IOP VER Menu Key displays the current Input/Output Processor Software
Version (Figure 7-2).
Press the MENU Button to exit the Menu.
Figure 7-2
View Input/Output Processor
Software Version
View the Primary Flight Display Unit’s Serial Number
1.
2.
3.
4.
Press the MENU Button. The Menu displays on the Navigation Display.
Rotate the Right Knob to the SYSTEM STATUS menu page.
The S/N Menu Key displays the unit’s serial number (Figure 7-3).
Press the MENU Button to exit the Menu.
Figure 7-3
View Unit Serial Number
Page 7-2
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
7.3. Specifications
7.3.1. Primary Flight Display Unit (PFD)
GENERAL SPECIFICATIONS
3.50 in. (Measured at Bezel)
Height
7.00 in. (Measured at Bezel)
Can Depth
4.15 in. (Rear of Bezel to Rear of Can)
Overall Depth
6.35 in. (Knob to Rear Pressure Fitting)
Weight
2.9 lbs. (with Mounting Bracket)
Display Type
6.0 in. Diagonal TFT Active Matrix LCD (400x760)
Display Colors
32,768
Face
Anti-Reflective Coated Glass
Backlight
High Intensity White LED
Rotary Knobs
Optical Encoder with Momentary Press
Dimming
Manual & Automatic (Front Bezel Mounted Sensor)
CHAPTER 7 APPENDICES
Width
OPERATIONAL SPECIFICATIONS
Operating Temp
-20°C to +55°C
Storage Temp
-55°C to +85°C
Max Un-Pressurized Operating Altitude
35,000 ft.
Max Pressurized Operating Altitude
55,000 ft.
Cooling
Integral Fan
Max Humidity
95% at 50°C
Input Voltage
+8 to +32 VDC
Max Current
2.4 Amps @ 28 VDC
4.8 Amps @ 14 VDC
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-3
I/O SPECIFICATIONS
ARINC 429 Inputs
5
ARINC 429 Outputs
1
RS-232 Inputs
5
RS-232 Outputs
3
Pitot / Static
Quick Connect
CERTIFICATION SPECIFICATIONS
CHAPTER 7 APPENDICES
Technical Standard Order
FAA and EASA (European Aviation
Safety Agency)
TSO-C2d / ETSO-C2D.......................................................................Airspeed Instruments
TSO-C3d / ETSO-C3D................................................................Turn and Slip Instrument
TSO-C4c / ETSO-C4C...........................................................Bank and Pitch Instruments
TSO-C6d / ETSO-C6D....................................................Direction Instrument Magnetic
(Gyroscopically Stabilized)
TSO-C8d / ETSO-C8D.......................Vertical Velocity Instrument (Rate of Climb)
TSO-C10b / ETSO-C10B......................Altitude Pressure ActivatedSensitive Type
TSO-C106 / ETSO-C106.........................................................................Air Data Computer
TSO-C113 / ETSO-C113....................Airborne Multipurpose Electronic Displays
Software
RTCA DO-178B Level B
Environmental
RTCA DO-160E
Categories
See Environmental Qualification Sheet found in the Installation Manual.
Table 7-1
Primary Flight Display Unit (PFD) Specifications
Page 7-4
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
7.3.2. Remote Sensor Module (RSM)
2.65 in.
Length
4.40 in.
Height
1.00 in.
Weight
0.2 lbs.
Input Voltage
Provided by EFD1000
Max Current
Included in EFD1000 Current
CHAPTER 7 APPENDICES
Width
Table 7-2
Remote Sensor Module (RSM) Specifications
7.3.3. Analog Converter Unit (ACU)
Width
5.75 in. (including mounting flange)
Length
4.30 in. (including connector)
Height
1.60 in. (including mounting flange)
Weight
0.8 lbs.
Input Voltage
+10 to +32 VDC
Max Current
0.5 Amps @ 28 VDC
1.0 Amps @ 14 VDC
Interfaces
ARINC-429 and RS-232
Table 7-3
Analog Converter Unit (ACU) Specifications
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-5
7.3.4. Operational Specifications
Airspeed Range
Minimum displayed airspeed
20 KIAS
Maximum displayed airspeed
500 KIAS
Minimum displayed altitude
-1,600 ft. MSL
Maximum displayed altitude
51,000 ft. MSL
Vertical Speed
Range
Maximum displayed vertical speed rates (tape)
+/-2,000 fpm
Maximum displayed vertical speed rates (numerical
value)
+/- 9,990 fpm
Turn Rate
Maximum displayed turn rate
6.0 °/second
Barometric
Pressure
Correction Range
28.10 to 30.99 In Hg (946 to 1049 mB)
Internal Battery
Minimum operating time while on internal battery
CHAPTER 7 APPENDICES
Altitude Range
30 minutes 1
Table 7-4 Operational Specifications
1. At extreme cold temperatures, the internal current limiting protections of the internal battery may cause the battery to shut
off and not power the display.
Page 7-6
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
7.4. Glossary
Automated Weather Observation System
Back Course
Localizer back course approach where the
signal on the back side of the localizer is used
for alignment to the runway opposite of
normal localizer alignment.
Battery Time
The time remaining on the battery before it is
fully discharged.
BC
Back Course
Bearing
The compass direction from the current
position to the destination.
BP
Bearing Pointer
Calibrated Airspeed
Indicated airspeed corrected for installation
and instrument errors.
°C
Degrees Celsius
°F
Degrees Fahrenheit
Accuracy
Estimated position accuracy in feet or meters
A/D
Analog to Digital
AC
Alternating Current
ACU
Analog Converter Unit
ADC
Air Data Computer
ADI
Attitude Director Indicator
AFMS
Airplane Flight Manual Supplement
AGL
Above Ground Level
AHRS
Attitude Heading Reference System
CDI
Course Deviation Indicator
AI
Attitude Indicator
CFR
Code of Federal Regulations
AIM
Aeronautical Information Manual
CM
Configuration Module
AIRMET
Airman’s Meteorological Information
Comm
Communication radio
Altitude
Elevation above sea level
Course
APPR
Approach
The route taken from the starting position to
destination.
APT
Airport
Course to Steer
ARC
Partial Compass Rose, arc format (100°)
ARINC
Aeronautical Radio, Inc.
The recommended direction to steer in order
to reduce cross-track error and return to the
course line.
ATC
Air Traffic Control
Cross Track
The perpendicular distance, left or right, away
from the selected course.
ATIS
Automatic Terminal Information Service
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-7
CHAPTER 7 APPENDICES
AWOS
CHAPTER 7 APPENDICES
Crosstrack Error
The distance the aircraft is off the desired course.
EFD
Evolution Flight Display
CRS
Course
EFIS
Electronic Flight Instrument System
CTS
Course to Steer
Elevation
The height above mean sea level.
dBZ
decibels ‘Z’ (radar return)
ETA (Destination)
DC
Direct Current
Decision Height
A specified height or altitude in the precision
approach at which a missed approach must
be initiated if the required visual reference to
continue the approach has not been acquired.
This allows the pilot sufficient time to safely
reconfigure the aircraft to climb and execute
the missed approach procedures while avoiding
terrain and obstacles.
Estimated Time of Arrival. The estimated time
you will reach a Go To destination or the final
waypoint in a route.
ETA (Next)
Estimated Time of Arrival. The estimated time
you will reach a Go To destination or the next
waypoint in a route.
ETE (Destination)
Estimated Time Enroute. The estimated time
required to reach a Go To destination or the final
waypoint in a route
ETE (Next)
Estimated Time Enroute. The estimated time
required to reach a Go To destination or the next
waypoint in a route.
Declutter
Reduce the number of basemap symbols
displayed on screen.
Deg
Degree
ETSO
European Technical Standard Order
Desired Track
The desired course between the active “from”
and “to” waypoints.
FAA
Federal Aviation Administration
FAF
Final Approach Fix
DH
Decision Height
FD
Flight Director
Distance (Next)
The great circle distance from current location
to a Go To destination or the final waypoint in a
route.
fpm
Feet Per Minute
ft
Feet
DME
Distance Measuring Equipment
GPS
Global Positioning System
DTK
Desired Track
GPSS
GPS Steering
EASA
European Aviation Safety Agency
Ground Track
See Track
Page 7-8
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Ground Speed
LAT
Latitude
LCD
Liquid Crystal Display
GS
Glide Slope or Ground Speed
LDI
Lateral Deviation Indicator
Heading
The direction an aircraft is pointed, based upon
indications from a magnetic compass or a
properly set directional gyro.
Leg
The portion of a flight plan between two
waypoints.
Hg
Mercury
LOC
Localizer
HSI
Horizontal Situation Indicator
MAP
Main Application Processor
Hz
Hertz (frequency)
mB
Millibars
MFD
Multi-Function Display
IAF
Initial Approach Fix
MHz
Megahertz
IAS
Indicated Air Speed
Mmo
Maximum Mach Operating Speed
IFR
Instrument Fight Rules
MSG
Message
ILS
Instrument Landing System
MSL
Mean Sea Level
IMC
Instrument Meteorological Conditions
NAVAID
Navigation Aid
in Hg
Inches of Mercury
NDB
Non-Directional Beacon
Indicated
Information provided by properly calibrated and
set instruments on the aircraft panel.
nm
Nautical Miles
NRST
Nearest
IOP
Input/Output Processor
OAT
Outside Air Temperature
kHz
Kilohertz
OBS
Omni-Bearing Selector
KIAS
Knots Indicated Air Speed
PFD
Primary Flight Display
km
Kilometer
RA
Radio Altitude
kts
Knots
RMI
Radio Magnetic Indicator
RSM
Remote Sensor Module
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
CHAPTER 7 APPENDICES
The velocity that the aircraft is travelling relative
to a ground position.
Page 7-9
CHAPTER 7 APPENDICES
SD
Secure Digital
TAS
Traffic Advisory System
TACAN
Tactical Air Navigation System
TAS
True Air Speed
TCAS
Traffic Collision Avoidance System
TERM
Terminal Mode
TIS
Traffic Information System
Track
Direction of aircraft movement relative to a
ground position; also ‘Ground Track’
TSO
Technical Standard Order
VAC
Volts, Alternating Current
VDC
Volts, Direct Current
VDI
Vertical Deviation Indicator
VFR
Visual Flight Rules
VHF
Very High Frequency
VLOC
VOR/Localizer
VOR
VHF Omni-Directional Radio Range
VORTAC
VHF Omni-Directional Radio Range and Tactical
Air Navigation
VSI
Vertical Speed Indicator
WAAS
Wide Area Augmentation System
WPT
Waypoint
Page 7-10
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
7.5. Index
A
091-00019-001 REV B
Altimeter ........................................................................................................................4-15 - 4-23
Decision Height ..................................................................................................................4-22
MINIMUMS ...............................................................................................................4-19 - 4-21
Altitude ...........................................................................................................................4-15 - 4-18
Alerter........................................................................................................................................4-15
Alerter, Set ..................................................................................................................3-14, 4-17
Bug ..........................................................................................................................................4-17
Bug, Set.....................................................................................................................................4-17
Caution .....................................................................................................................................6-20
Display.......................................................................................................................................4-22
Level-Off and Deviation Alert.....................................................................................4-18
Tape ..........................................................................................................................................4-15
Hide/Display .....................................................................................................................4-23
Trend Vector ..........................................................................................................................4-15
Altitude Display
Attitude Indicator............................................................................................2-23, 4-8, 4-9
Analog Converter Unit ...........................................................................................................1-7
Approvals........................................................................................................................................xxii
APV (Approaches with Vertical Guidance) ..............................................................4-62
ARC/360, Hot Key ...................................................................................................................2-12
Attitude Display ............................................................................................... 2-21 - 2-26, 4-8
Airspeed Indicator ...............................................................................................4-10 - 4-13
Altimeter ....................................................................................................................4-15 - 4-23
Attitude Indicator..................................................................................................................4-8
Components .........................................................................................................................2-22
Attitude Fail ................................................................................................................................6-17
Attitude Indicators, Difference ..........................................................................................6-7
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-11
CHAPTER 7 APPENDICES
ADAHRS ............................................................................................................................... 4-2 - 4-7
Attitude .......................................................................................................................................4-3
Free Gyro Mode......................................................................................................................4-6
Heading.......................................................................................................................................4-5
Pitot Obstruction Monitor ...............................................................................................4-4
Advisory............................................................................................................................6-23, 6-24
GPS Annunciations ...........................................................................................................6-23
GPSS On ...................................................................................................................................6-22
Navigation Source Invalid or Unavailable ...........................................................6-23
REV Button Off .....................................................................................................................6-22
AHRS Reset, In-Flight ............................................................................................................6-13
Perform .....................................................................................................................................6-14
Aircraft Ownship Symbol...................................................................................................4-27
Air Data, Attitude and Heading Reference System................................... 4-2 - 4-7
See also ADAHRS
Airspeed Indicator (Airspeed) ...........................................................................4-10 - 4-13
Airspeed ...................................................................................................................................4-10
Bug..............................................................................................................................4-10, 4-12
Bug, Set ....................................................................................................................3-15, 4-12
Range ....................................................................................................................................4-11
Airspeed Display .................................................................................................................4-13
Tape ..........................................................................................................................................4-10
Hide/Display .....................................................................................................................4-13
Tape and Bug ........................................................................................................................2-24
Speed Bands .....................................................................................................................2-24
Speed Markers .................................................................................................................2-24
ALT
................................................................................................................................. 2-5 - 2-8
CHAPTER 7 APPENDICES
Auto Course ...................................................................................................................2-34, 4-38
Disable ......................................................................................................................................4-39
Enable........................................................................................................................................4-38
Autopilot Integration ...........................................................................................................4-53
Autopilot Operations, Typical..........................................................................................4-58
APPR Mode Operation - GPS or GPS/RNAV APV WAAS Approach ......4-62
APPR Mode Operation - ILS Approach with Vectors to Final ..................4-61
GPS APPR Mode Operation - WAAS GPS Underlay to ILS Approach
Using Pilot Nav and GPSS ................................................................................4-63
GPS APPR Mode Operation - WAAS GPS Underlay to ILS Approach
With ATC Vectors to Final .................................................................................4-64
HDG Mode Operation - GPS Steering (GPSS) ...................................................4-59
HDG Mode Operation - Heading Bug Steering ..............................................4-59
NAV Mode Operation - GPS Navigation...............................................................4-60
NAV Mode Operation - VLOC Navigation............................................................4-59
Auto Range
Activate ....................................................................................................................................4-47
Deactivate...............................................................................................................................4-47
Enable........................................................................................................................................4-47
B
Barometer............................................................................................................... 2-5 - 2-8, 4-23
Barometric Pressure, Set .......................................................................................3-8, 4-17
Barometric Pressure Setting Display ......................................................................4-26
Barometric Units of Measure, Set .............................................................................4-16
Battery
Countdown............................................................................................................................6-17
Operational ............................................................................................................................6-17
Status, View ............................................................................................................................6-12
Bearing Pointers ......................................................................................................................2-34
Double-Line Bearing Pointer Source, Select .....................................................4-42
Page 7-12
Nav Sources, Select ...........................................................................................................3-10
Single-Line Bearing Pointer Source, Select ........................................................4-42
Source Select Buttons .....................................................................................................2-10
Source Selection ...................................................................................................4-40 - 4-42
Brightness Control .................................................................................................................5-16
See also Lighting
BRT ADJUST ................................................................................................................................2-17
BRT AUTO.....................................................................................................................................2-17
Buttons .........................................................................................................................................xxviii
C
Cautions .........................................................................................................................6-19 - 6-21
Altitude Caution..................................................................................................................6-20
Check Pitot Heat .................................................................................................................6-19
Cross Check Attitude .......................................................................................................6-19
Decision Height Caution ...............................................................................................6-20
Explained ....................................................................................................................................xxx
GPS Integrity Flag...............................................................................................................6-20
GPS Invalid..............................................................................................................................6-20
GPS Reversion ......................................................................................................................6-20
GPS Reversion Emergency ...........................................................................................6-20
GPSS Source Lost/Changed ........................................................................................6-21
Minimums Caution ...........................................................................................................6-21
RSM GPS...................................................................................................................................6-20
CDI
Course, Select .......................................................................................................................4-39
Navigation Source ...............................................................................................4-34 - 4-37
Radio Mode, GPS............................................................................................................4-36
Radio Source, VHF .........................................................................................................4-36
Select.........................................................................................................................3-10, 4-34
Nav Source Select Button ................................................................................................2-9
Selected Course ..................................................................................................................4-39
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
091-00019-001 REV B
Terminology .......................................................................................................................... xxvii
Warnings, Cautions, Notes...............................................................................................xxx
Copyrights, Trademarks and Patents ..............................................................................xxi
Course Deviation Indicator and Scale .......................................................................4-33
Course Pointer ..........................................................................................................................4-31
Course Pointer and Deviation Indicator ...................................................................2-32
Covered Functionality ......................................................................................................... xxvii
CROSS CHECK ATTITUDE ................................................................................ 4-3, 6-7, 6-19
CRS
................................................................................................................................. 2-5 - 2-8
Customizing the EFD1000 PFD ...........................................................................5-1 - 5-16
Customizing the Map ...............................................................................................5-8 - 5-10
D
Data Bar ............................................................................................................................2-27, 4-24
Decision Height .......................................................................................................................4-22
Alert ..........................................................................................................................................4-15
Caution .....................................................................................................................................6-20
Declutter
Settings.....................................................................................................................................5-10
Deviation
Indicator...................................................................................................................................4-27
Off Scale Indication...........................................................................................................2-33
Scale ..........................................................................................................................................4-27
Direction Indicator Fail ........................................................................................................6-17
Direction Indicator (Magnetic Compass).........................................2-30, 2-31, 4-27
Display .................................................................................................................. 1-5, 2-19 - 2-36
Attitude Display ....................................................................................................2-21 - 2-26
Cleaning the Display Screen .......................................................................................2-20
Lighting ....................................................................................................................................2-17
Dual Display ..................................................................................................................................1-2
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-13
CHAPTER 7 APPENDICES
Source Information Block..............................................................................................4-35
Source Label..........................................................................................................................4-35
Source Select Button .......................................................................................................4-35
Check Pitot Heat......................................................................................................................6-19
CHECK PITOT HEAT ...................................................................................................................4-4
Cleaning the Display Screen............................................................................................2-20
Color Philosophy.......................................................................................................................xxix
Compass ......................................................................................................................................4-28
360° Compass Mode ........................................................................................................4-28
ARC CDI/HSI Compass Mode, Select .....................................................................4-29
ARC Compass Mode ........................................................................................................4-28
Compass Scale .....................................................................................................................4-27
Compass Type, Select ......................................................................................................4-30
Modes: 360° vs. ARC .........................................................................................................2-30
Select .........................................................................................................................................3-20
Configuration Module ............................................................................................................1-6
Configuring V-speeds ............................................................................................5-11 - 5-15
Controls
Knobs..................................................................................................................................2-4–2-8
Left Knob Functions ........................................................................................................2-5
Right Knob Functions ....................................................................................................2-5
SYNC Function........................................................................................................ 2-6 - 2-7
Controls and Display .................................................................................................2-1 - 2-36
Controls .........................................................................................................................2-4 - 2-19
Elements ......................................................................................................................... 2-2 - 2-3
Conventions................................................................................................................. xxvii - xxxii
Color Philosophy ..................................................................................................................xxix
Covered Functionality ..................................................................................................... xxvii
Example Graphics ................................................................................................................xxxi
Information Covered in this Pilot’s Guide ........................................................... xxxii
Pilot Familiarity.......................................................................................................................xxxi
CHAPTER 7 APPENDICES
E
EDIT VALUE..................................................................................................................................2-14
Electrical Power, Loss of Aircraft .......................................................................................6-9
Emergency and Abnormal Procedures .........................................................6-1 - 6-24
Pitot/Static System Blockage ............................................................................. 6-2 - 6-6
Evolution Flight Display (EFD) system ..........................................................................1-1
Dual Display..............................................................................................................................1-2
Single Display ..........................................................................................................................1-2
System Overview ..................................................................................................................1-4
Trio Display .......................................................................................................................1-3, 1-4
Evolution Hazard Awareness (EHA) .................................................................3-13, 4-64
Example Flight...............................................................................................................3-5 - 3-26
Arrival and Approach to Landing...............................................................3-21 - 3-26
Departure....................................................................................................................3-16, 3-17
En Route.....................................................................................................................3-18 - 3-20
Pre-Departure............................................................................................................3-6 - 3-16
Example Graphics.....................................................................................................................xxxi
External Voltage Status, View ..........................................................................................6-12
Extreme Pitch ............................................................................................................................6-18
Integrity Flag .........................................................................................................................6-20
Invalid ........................................................................................................................................6-20
Reversion .................................................................................................................................6-20
Reversion Emergency......................................................................................................6-20
GPSS ..........................................................................................................................................4-54
Disable ......................................................................................................................................6-16
Enable/Disable.....................................................................................................................4-55
Engage......................................................................................................................................3-18
Hot Key .....................................................................................................................................2-12
Off ..........................................................................................................................................6-23
On ..........................................................................................................................................6-22
Operation, Annunciations, and Autopilot Modes..........................................6-15
Source Lost/Changed .....................................................................................................6-21
Wings Level ............................................................................................................................6-16
Ground Speed ..............................................................................................................4-24, 4-25
Ground Track Marker ................................................................................................2-31, 4-49
H
Hazard Awareness ..................................................................................................................4-64
HDG ................................................................................................................................. 2-5 - 2-8
F
Heading ........................................................................................................................................4-27
Display.......................................................................................................................................4-44
Flight Director ..................................................................................................................4-9, 4-58
Heading and Heading Bug ..........................................................................................4-43
Flight Plan....................................................................................................................................4-48
Heading Bug, Set ............................................................................................. 2-8, 3-9, 4-43
Free Gyro Mode ..........................................................................................................................4-6
Horizontal Situation Indicator.........................................................................................2-32
G
Hot Keys ........................................................................................................... xxviii, 2-11 - 2-13
GENERAL SETTINGS A .............................................................................................................5-1
GENERAL SETTINGS B .............................................................................................................5-2 I
IAS
................................................................................................................................. 2-5 - 2-8
GPS
Annunciations ......................................................................................................................6-23 ILS Approaches ............................................................................................................4-63, 4-64
Examples ...................................................................................................................3-21 - 3-26
Failures ......................................................................................................................................6-11
Information Covered in this Pilot’s Guide ................................................................ xxxii
Page 7-14
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Initial Flap Extension Speed Marker ............................................................................4-10
Instrument Approach Indicators ..................................................................................2-26
Internal Battery Status, View ............................................................................................6-12
Introduction ...................................................................................................................... 1-1 - 1-3
K
L
Lateral Deviation Indicator ...............................................................................................4-50
Lighting ............................................................................................................................2-17, 5-16
Loss of Aircraft Electrical Power ........................................................................................6-9
LPV Approaches ..........................................................................................................4-62, 4-63
M
Menu ............................................................................................................................2-13 - 2-16
Brightness Control .............................................................................................................2-14
EDIT VALUE .............................................................................................................................2-14
Menu Text ...............................................................................................................................2-15
Overview ......................................................................................................................5-1 - 5-10
360° MAP SETTINGS ........................................................................................................5-3
ARC MAP SETTINGS.........................................................................................................5-4
GENERAL SETTINGS A ....................................................................................................5-1
GENERAL SETTINGS B.....................................................................................................5-2
POWER SETTINGS .............................................................................................................5-6
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-15
CHAPTER 7 APPENDICES
Knobs xxviii, 2-4–2-8
Left Knob Functions ............................................................................................................2-5
Right Knob Functions.........................................................................................................2-5
SYNC Function ............................................................................................................ 2-6 - 2-7
SYNC Function, Perform ...................................................................................................2-6
Using the Knobs (Example) ............................................................................................2-8
SYSTEM STATUS..................................................................................................................5-7
VSPEEDS A .............................................................................................................................5-5
VSPEEDS B .............................................................................................................................5-5
Page graphical bar.............................................................................................................2-14
Page Name .............................................................................................................................2-14
Page number and mode ...............................................................................................2-14
SEL PAGE ......................................................................................................................2-14, 2-15
Using the Menus ................................................................................................................2-14
Access and Navigate ...................................................................................................2-16
Edit Menu Items .............................................................................................................2-17
Map
Auto Range ............................................................................................................................4-47
Data Source and Reversion ..........................................................................................4-48
Declutter
Settings ................................................................................................................................5-10
Declutter and Range ........................................................................................................4-46
Declutter Level, Select.........................................................................................3-11, 4-46
Feature Group & Layer Order ......................................................................................5-10
Flight Plan ...............................................................................................................................4-48
Max Range..............................................................................................................................5-10
Range, Change ........................................................................................................3-12, 4-46
Symbol Display, Set..............................................................................................................5-9
Underlays ................................................................................................................................4-45
MEMS .............................................................................................................................................4-2
Menu Keys .................................................................................................................................xxviii
Micro Electro-Mechanical Systems.................................................................................4-2
MINIMUMS ......................................................................................................................4-15, 4-19
Adjustment ............................................................................................................................4-21
Alert ..............................................................................................................................4-15, 4-18
Caution .....................................................................................................................................6-21
Display/Hide..........................................................................................................................4-20
CHAPTER 7 APPENDICES
MIN, Hot Key..........................................................................................................................2-12
Vertical Speed Indicator .................................................................................................2-37
Set ..........................................................................................................................................4-21 Navigation Source
Select Buttons
N
Bearing Pointer Source Select Buttons ............................................................2-10
CDI Nav Source Select Button ..................................................................................2-9
Navigation
Notes
Information ............................................................................................................................2-33
Explained ...............................................................................................................................xxx
Source ...........................................................................................................................4-27, 4-34
See also Advisory
Source Info Block ....................................................................................................4-35, 4-36
Source Invalid or Unavailable .....................................................................................6-23 Numerical Airspeed Value .................................................................................................4-10
Source Select Buttons ..........................................................................................2-9 - 2-10 Numerical Altitude Value ...................................................................................................4-15
Navigation Display .......................................................................................2-28 - 2-36, 4-27
Aircraft Heading Display ................................................................................................4-44 O
Auto Course...........................................................................................................................4-38 Operating Limitations.............................................................................................................7-1
Auto Course Select............................................................................................................2-35 Outside Air Temperature ........................................................................................4-24, 4-25
Bearing Pointers ..................................................................................................................2-36
OAT Units of Measure, Set.............................................................................................4-25
Bearing Pointer Source Selection.............................................................................4-40
CDI Navigation Source......................................................................................4-34 - 4-37 P
CDI Selected Course.........................................................................................................4-39 Pilot Familiarity ...........................................................................................................................xxxi
Compass ..................................................................................................................................4-28 Pitch Scale ......................................................................................................................................4-9
Components .............................................................................................................2-30, 4-31 Pitot and/or Static System Failures, Identifying ......................................................6-4
Course Deviation Indicator and Scale ...................................................................4-33 Pitot Obstruction Monitor....................................................................................................4-4
Course Pointer......................................................................................................................4-31 Pitot/Static System Blockage .................................................................................6-2, 6-20
Course Pointer and Deviation Indicator...............................................................2-34
Suspected ..................................................................................................................................6-3
Deviation Off Scale Indication ...................................................................................2-35 Power On Manually ..................................................................................................................6-8
Direction Indicator (Magnetic Compass) ............................................................2-32 Power Override ........................................................................................................................6-12
Heading and Heading Bug ..........................................................................................4-43
Horizontal Situation Indicator ....................................................................................2-34 R
Map Underlays.....................................................................................................................4-45 Range Button ............................................................................................................................2-19
Rate of Turn Indicator ..........................................................................................2-37, 4-44 Rate of Turn Indicator...................................................................................2-27, 4-37, 4-44
Situational Awareness Map .........................................................................................2-38 Rear Connections ......................................................................................................................1-5
TO/FROM Indicator ...........................................................................................................4-32 Remote Sensor Module .........................................................................................................1-6
Track Marker ..............................................................................................................2-31, 4-49
Page 7-16
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
REV Button ..................................................................................................................................2-19
Off ..........................................................................................................................................6-23
Power On Manually .............................................................................................................6-8
Shutdown EFD1000 PFD (on ground) .....................................................................6-8
Shutdown Procedure, Abnormal ................................................................................6-8
Right Knob Functions ................................................................................................... 2-5, 2-6
RNAV Instrument Approaches........................................................................................4-62
Roll Scale .........................................................................................................................................4-9
RSM Emergency GPS Use ..................................................................................................6-11
RSM GPS .......................................................................................................................................6-20
System Overview .......................................................................................................................1-4
T
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Page 7-17
CHAPTER 7 APPENDICES
Terminology ................................................................................................................xxvii - xxviii
Buttons ....................................................................................................................................xxviii
Hot Keys ..................................................................................................................................xxviii
Knobs........................................................................................................................................xxviii
Menu Keys .............................................................................................................................xxviii
TO/FROM Indicators .................................................................................................4-27, 4-32
Track Marker...................................................................................................................4-26, 4-48
Traffic
S
Altitude Filter ........................................................................................................................4-66
Overlay .......................................................................................................................3-13, 4-65
SEL PAGE ..........................................................................................................................2-14, 2-15
Symbols....................................................................................................................................4-68
Shutdown Procedure, Abnormal .....................................................................................6-8
Single Display...............................................................................................................................1-2 Trio Display ....................................................................................................................................1-3
Situational Awareness Map ..............................................................................................2-38 True Airspeed ............................................................................................................................4-23
Slip/Skip Indicator .....................................................................................................................4-9
Software Versions .......................................................................................................... 7-1 - 7-2 U
Input/Output Processor Software Version, View ...............................................7-2 Unit Serial Number, View ......................................................................................................7-2
Main Application Processor Software Version, View .......................................7-2 Using the Menus.....................................................................................................................2-14
Specifications ................................................................................................................... 7-3 - 7-6
Analog Converter Unit.......................................................................................................7-5 V
EFD1000 Display Unit .........................................................................................................7-3 Vertical Deviation Indicator ..............................................................................................4-51
Operational ...............................................................................................................................7-6 Vertical Speed Indicator .........................................................................................2-37, 4-52
Remote Sensor Module ....................................................................................................7-5 Voltage Status, View ..............................................................................................................6-12
Speed Bands ..................................................................................................................2-25, 4-10 Vspeeds.............................................................................................................................4-10, 4-11
Ranges ......................................................................................................................................5-13
Configuring..............................................................................................................5-11 - 5-15
Speed Markers ..............................................................................................................2-25, 4-10
Definitions ................................................................................................................5-11 - 5-12
Startup Splash Screen.............................................................................................................3-6
Initial Flap Extension ........................................................................................................5-12
SYNC Function................................................................................................................. 2-6 - 2-7
Textual Labels, Enable .....................................................................................................5-14
System Architecture.................................................................................................................1-4
Textual Vspeed Labels, Set............................................................................................5-15
CHAPTER 7 APPENDICES
W
WAAS Approaches .................................................................................................................4-62
Warning, Caution, and Advisory Summary ..............................................6-17 - 6-24
Warnings ........................................................................................................................6-17 - 6-18
Attitude Fail............................................................................................................................6-17
Battery Countdown ..........................................................................................................6-17
Battery Operational...........................................................................................................6-17
Direction Indicator Fail....................................................................................................6-17
Explained ....................................................................................................................................xxx
Extreme Pitch........................................................................................................................6-18
Warranty .............................................................................................................................xxiii - xxv
Card ............................................................................................................................................xxiv
Conditions ................................................................................................................................xxiii
Dealer ...........................................................................................................................................xxv
Exclusions..................................................................................................................................xxiii
Exclusive ....................................................................................................................................xxiv
Extension of ..............................................................................................................................xxv
Incidental Damages ...........................................................................................................xxiv
Invalidation ..............................................................................................................................xxiv
Limitation of Liability .........................................................................................................xxiv
Procedure...................................................................................................................................xxv
Remedy ......................................................................................................................................xxiii
Transportation Costs ...........................................................................................................xxv
Wind
Direction ..................................................................................................................................4-24
Direction Arrow ...................................................................................................................4-24
Speed.........................................................................................................................................4-24
Speed, Direction, and Arrow .......................................................................................4-26
Wings Level ................................................................................................................................4-58
Page 7-18
EFD1000 C3 Pro PFD Pilot’s Guide
091-00019-001 REV B
Aspen Avionics, Inc.
5001 Indian School Road NE
Albuquerque, NM 87110
Phone: 888-99ASPEN (888-992-7736)
Phone, International: (505) 856-5034
Fax: (505) 314-5440
[email protected]
www.aspenavionics.com
091-00019-001 REV B
EFD1000 C3 Pro PFD Pilot’s Guide
Printed in USA

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