Page 3 Page iii 091-00019-001 REV B EFD1000 C3 Pro PFD Pilot’s Guide...
Page 4 Document Revisions Revision Description of Change Initial Release Grammatical, pictorial, and technical updates. Revised to update for software v2.0, including the following: • 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. Page iv EFD1000 C3 Pro PFD Pilot’s Guide 091-00019-001 REV B...
Page 5: Table Of Contents
Technical Standard Orders: ............xxii 2.2.1. Left and Right Knobs ..............2-4 European Technical Standard Orders: ........xxii LIMITED WARRANTY 2.2.1.1. Left Knob Functions ............2-5 Aspen Avionics, Inc..............xxiii 2.2.1.2. Right Knob Functions ............2-5 SYNC Function............2-6 2.2.1.3. Conventions................xxvii 2.2.1.4.
Page 6 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.
Page 7 4.4.9. Heading Bug ..................4-43 4.2.3. Altimeter ....................4-15 4.4.10. Aircraft Heading Display ............4-44 4.2.3.1. Barometric Units of Measure ........4-16 4.4.11. Rate of Turn Indicator ..............4-44 4.2.3.2. Selected Altitude Field ..........4-17 4.4.12. Basemap Overlays ................4-45 4.2.3.3. Altitude Level-Off and Deviation Alert ....4-18 4.4.12.1.
Page 8 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.
Page 9 Table of Figures Figure 2-16 Menu Edit Mode ................2-15 Figure 1 C3 Pro PFD Display, Knobs, Buttons, and Keys .....xxviii Chapter 1 Figure 2-17 Menu ......................2-15 Figure 2-18 Menu Text - Editable ..............2-16 Figure 1-1 EFD1000 C3 Pro Display Unit ............1-1 Figure 2-19 Menu Text - Enabled for Editing..........2-16 Figure 1-2 Single Display EFD1000 PFD System .........1-2 Figure 2-20 Menu Text - Status Only ..............2-16...
Page 10 Chapter 3 Figure 2-36 360° Compass Mode ..............2-32 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 3-3 CDI Navigation Source Slashed Invalid ........3-6 Figure 2-39 Navigation Source Information Block .........2-33 Figure 2-40 Ground Track Marker ..............2-33 Figure 3-4 CDI Source Slashed Invalid ..............3-7...
Page 11 Figure 3-15 Current Range 20nm from Ownship to Figure 3-35 360º Mode Showing Procedure Turn, Edge of Compass Rose ..............3-12 GPSS Enabled..................3-22 Figure 3-16 Current Range 10nm from Ownship to 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...
Page 12 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...
Page 13 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...
Page 14 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...
Page 15 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...
Page 16 Table of Tables Table 1 C3 Pro PFD Display, Knobs , Buttons, and Keys ......xxviii Figure 6-32 Navigation Source Invalid or Unavailable ......6-24 Table 2 Color Guide .....................xxix Figure 6-33 Traffic Enabled ..................6-24 Table 3 Warning, Caution, and Note ..............xxx Figure 6-34 GPSS Disabled ..................6-24 Chapter 7 Chapter 2...
Page 17 Chapter 7 Chapter 5 Table 7-1 EFD1000 Display Unit Specifications ...........7-4 Table 5-1 Menu – GENERAL SETTINGS A ............5-1 Table 7-2 Remote Sensor Module (RSM) Specifications ......7-5 Table 5-2 Menu – GENERAL SETTINGS B ............5-2 Table 7-3 Analog Converter Unit (ACU) Specifications ......7-5 Table 5-3 Menu –...
Page 18 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...
Page 19 Activate Auto Range ....................4-47 Change Brightness Mode ..................5-16 Deactivate Auto Range ...................4-47 Adjust Display Brightness Manually ..............5-16 Chapter 6 Enable/Disable GPSS ....................4-55 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 –...
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Page 21: Copyrights, Trademarks And Patents
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.
Page 22: Approvals
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.
Page 23: Limited Warranty Aspen Avionics, Inc
LIMITED WARRANTY Aspen Avionics, Inc. Furnish proof sufficient to establish that the item is a YOUR WARRANTY. Aspen Avionics, Inc. (“Aspen”) warrants to you, Nonconforming Product, and the original purchaser, that its Products (if purchased from an authorized dealer) will comply with applicable specifications (as set forth in the Allow Aspen access to all relevant records in order to owner’s manual) in all material respects and will be free from material...
Page 24 Accident, contamination, damage from a foreign object or EXCLUSIVE WARRANTY. THIS WARRANTY IS EXCLUSIVE AND weather conditions, abuse, misuse, neglect, or negligence, IN LIEU OF ALL OTHER WARRANTIES. THE IMPLIED WARRANTY OF MERCHANTABILITY AND IMPLIED WARRANTY OF FITNESS FOR A Exposure of the product or the product’s host medium to any PARTICULAR PURPOSE, AS WELL AS ALL OTHER IMPLIED WARRANTIES computer virus or other intentionally disruptive, destructive, or...
Page 25 Aspen Customer Service at (505) 856-5034; offered by a dealer (“Dealer Warranty”) will be the sole responsibility by writing to Aspen Customer Service Department, Aspen Avionics, of the dealer, who will be solely responsible for all liability, loss, cost, Inc., 5001 Indian School Road NE, Albuquerque, New Mexico, 87110;...
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Page 27: Conventions
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.
Page 28 Term Example Buttons REV Button, Range Buttons, MENU Button Hot Keys / Menu Keys Five keys on the lower right of the display Lower Left Button, CDI Navigation Source Select Button, Buttons Lower Right Button Knobs Left (CRS) Knob, Right (HDG) Knob Navigation Display Data Bar Attitude Display...
Page 29: Color Philosophy
Color Philosophy Table 2 provides the operational philosophy of color usage on the PFD display. COLOR PURPOSE COLOR PURPOSE Used for navigation information or mode data related to Used to indicate flight envelope and system limits, and or provided by the navigation source currently selected for for warning annunciations that require immediate pilot display on the Course Deviation Indicator (CDI) (i.e., navigation GREEN...
Page 30: Warnings, Cautions, And Notes
Warnings, Cautions, and Notes Where applicable warnings, cautions, and notes are given. Aspen Avionics uses the following icons and definitions (Table 3). Icon Definition Emphasizes a crucial operating or maintenance procedure, which, if not strictly observed, could result in injury to, or death of, personnel or long Warning term health hazards.
Page 31: Example Graphics
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).
Page 32: Information Covered In This Pilot's Guide
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. Page xxxii EFD1000 C3 Pro PFD Pilot’s Guide 091-00019-001 REV B...
Page 33: Welcome And Introduction
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.
Page 34: Figure 1-2 Single Display Efd1000 Pfd System
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.
Page 35 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.
Page 36: System Overview
1.1. System Overview Pitot Static The PFD system typically consists of four components: Existing Aircraft Existing Aircraft Pitot Line Static Line EFD1000 Display Unit (PFD) Configuration Module (CM) Remote Sensor Module (RSM) Aircraft Power EFD1000 Pro PFD Remote Analog Converter Unit (ACU) Sensor Module (Primary Flight Display)
Page 37: Primary Flight Display Unit (Pfd)
1.1.1. Primary Flight Display Unit (PFD) Pitot & Static System Connections 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: • A Sensor Board with solid-state Attitude and Heading Reference System (AHRS) and 44-pin D-Sub for Electrical Connections...
Page 38: Configuration Module (Cm)
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: • 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 Figure 1-7 Configuration Module (CM)
Page 39: Remote Sensor Module (Rsm)
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.
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Page 41: 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.
Page 42: Controls & Display Orientation
2.1. Controls & Display Orientation ATTITUDE DISPLAY Attitude Display CONTROLS Aircraft Reference Symbol Reversion and Power Button Single-Cue Flight Director Range Buttons Roll Pointer Menu Button Slip/Skid Indicator 1/2 Hot Key Menu 1 of 2 2/2 Hot Key Menu 2 of 2 1, 4 Altitude Tape MIN - Minimums...
Page 43 DATA BAR Vertical Speed Tape Single-Line Bearing Pointer True Airspeed (TAS) or Mach number Single-Line Bearing Pointer Source Barometric Pressure Setting Field Single-Line Bearing Pointer Source Info Block Wind Direction and Speed Double-Line Bearing Pointer Wind Direction Arrow Double-Line Bearing Pointer Source Outside Air Temperature (OAT) Double-Line Bearing Pointer Source Info Block Ground Speed...
Page 44: Controls
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.
Page 45: Left Knob Functions
2.2.1.1. Left Knob Functions NOTE The Left Knob is used to set the Course (CRS) and Airspeed Bug (IAS). Course (CRS) is the default setting for the Left Knob. MIN will only be shown if the MIN function is already active.
Page 46: Sync Function
SYNC Function 2.2.1.3. Knob SYNC Function 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.
Page 47: Table 2-2 Left And Right Knob Sync Description
LEFT KNOB Item SYNC Action Set to the current Indicated Airspeed. Course Pointer points to the VOR. CRS value is the VOR navigation reciprocal of the current VOR radial. The deviation bar centers with a “TO” indication. ILS navigation Current aircraft heading. Course Pointer points to the active GPS waypoint.
Page 48: Using The Knobs (Example)
2.2.1.4. Using the Knobs (Example) How to Set the Heading bug (HDG) 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.
Page 49: Cdi Nav Source Select Button
2.2.2.1. CDI Nav Source Select Button 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.
Page 50: Bearing Pointer Source Select Buttons
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.
Page 51: Hot Keys
2.2.3. Hot Keys NOTE The five Buttons along the lower right side of the PFD function as either single-action When the PFD is configured with the Evolution Hazard Hot Keys for frequently used commands or as Menu Keys when the Menu has been Awareness option, there are two levels of Hot Keys, activated.
Page 52 HOT KEY DESCRIPTION OPTIONS Hot Key Menu 1 of 2 Hot Key Menu selection Hot Key Menu 2 of 2 Minimums displayed and Enables and displays or alerter enabled disables and hides Minimums Alerter (see Section 4.2.3.4.) Minimums alerter Off 360°...
Page 53: Figure 2-9 Hot Key Menu 2 Of
Hot Key DESCRIPTION OPTIONS Hot Key Menu 2 of 2 Hot Key Menu selection Hot Key Menu 1 of 2 No function No function TFCN Normal Filter TFCU Unrestricted (No Filtering) Displays Traffic Overlay TRFC TFCA Above Filter (see Section 4.8.1.2.) TFCB Below Filter TRFC...
Page 54: Menu
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 Press the MENU Button to activate the Menu (Ref. 3). The current Menu page name is Figure 2-15 shown on the bottom center of the Navigation Display.
Page 55: Figure 2-16 Menu Edit Mode
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.
Page 56: Figure 2-18 Menu Text - Editable
The MENU text will display in one of the four colors listed and described in Table 2-5. Figure 2-18 Menu Text - Editable DISPLAY TEXT DESCRIPTION DISPLAY WHITE Editable option Figure 2-18 Figure 2-19 MAGENTA Figure 2-19 Editable option enabled Menu Text - Enabled for Editing GREEN Status Only...
Page 57: Figure 2-23 Edit Value Displays Above Right Knob
Edit Menu Items NOTE Press the MENU Button. Navigate to the desired Menu Page. Pressing the Right Knob returns to Navigation mode Press the Menu Key of the desired option. The Menu label turns magenta, and and allows selection of other menu options on different the EDIT VALUE label displays above the Right Knob (Figure 2-23).
Page 58: Display Lighting
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).
Page 59: Range Buttons
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.
Page 60: 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.
Page 61: Cleaning The Display Screen
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.
Page 62: Attitude Display
2.3.2. Attitude Display The Attitude Display includes an Attitude Director Indicator (ADI) with a single- cue 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).
Page 63 ATTITUDE DISPLAY Attitude Display Decision Height Annunciation Aircraft Reference Symbol Selected Minimums Field Single-Cue Flight Director Radio Altitude Roll Pointer MINIMUMS Marker Slip/Skid Indicator LDI Navigation Source Indication Altitude Tape Airspeed Tape Selected Altitude Field Selected Airspeed Field Altitude Alerter Airspeed Bug Numerical Altitude Value, Numerical Airspeed Value, Airspeed...
Page 64: Attitude Director Indicator (Adi)
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.
Page 65: Airspeed Tape And Bug
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.
Page 66: 2.A. Mach Number Display For Mmo Aircraft
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;...
Page 67: Altitude Tape, Altitude Alerter, And
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.
Page 68: Instrument Approach Indicators
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.
Page 69: Data Bar
2.3.3. Data Bar The Data Bar visually separates the upper and lower halves of the PFD display. When Figure 2-34 available, True Airspeed (TAS) or Mach Number, GPS Ground Speed (GS), Outside Air Data Bar Components 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).
Page 70: Navigation Display
2.3.4. Navigation Display 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: NOTE • Horizontal Situation Indicator (HSI), with Course Pointer and Deviation The Vertical Deviation Indicator (VDI) and Lateral Indicator (CDI), and Heading Bug.
Page 71: Figure 2-35 Navigation Display Components
NAVIGATION DISPLAY Navigation Display Single-Line Bearing Pointer Ownship Symbol Single-Line Bearing Pointer Navigation Source Course Pointer Single-Line Bearing Pointer Navigation Source Info Block TO/FROM Indicator Double-Line Bearing Pointer Rate of Turn Indicator Double-Line Bearing Pointer Navigation Source Ground Track Marker Double-Line Bearing Pointer Navigation Source Info Block Magnetic Heading...
Page 72: Direction Indicator (Magnetic Compass)
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.
Page 73: Navigation Information
Navigation Information 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 Figure 2-38 is always visible even if the HDG Bug itself is only partially visible in ARC Compass Mode.
Page 74: Horizontal Situation Indicator (Hsi)
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...
Page 75: Deviation Off Scale Indication
2.3.4.4. Deviation Off Scale Indication 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”.
Page 76: Bearing Pointers
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.
Page 77: Rate Of Turn Indicator
2.3.4.7. Rate of Turn Indicator 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 Figure 2-46 direction of the turn, along the outer curve of the compass card.
Page 78: Situational Awareness Map
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.
Page 79: Chapter 3 Flying The 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 step- by-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.
Page 80: Table 3-1 Basic Efd1000 Settings
FEATURE SETTING FEATURE SETTING Barometric Selected Pressure Allows for BARO Set as desired Altitude (BARO) Hot adjustment Lower Left and Right Map RNG Buttons, (Range) Set as desired Select as desired Bearing Buttons Pointers Nav Source Barometric Pressure on/off Navigation Select as desired Setting Field Source Select...
Page 81: Quick Controls Overview
3.1. Quick Controls Overview 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.
Page 82 Navigation Source buttons • 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).
Page 83: Example Flight Scenario
3.2. Example Flight Scenario 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 NOTE airways to the ILS16R approach into KRNO. This scenario uses one pilot’s technique for The tasks and procedures you will use in your airplane setting up the navigation instruments, but there are many other valid possibilities.
Page 84: Pre-Departure (Startup)
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).
Page 85: Figure 3-4 Cdi Source Slashed Invalid
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.
Page 86 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 WARNING 4xx/5xx Instrument Panel Self-Test Page does not send an Approach Mode signal to the PFD. Whenever there is a new altimeter setting, set both the PFD and the standby altimeter.
Page 87: Figure 3-8 Selected Heading Field Enabled
Next, since we’ll be departing from Runway 8, we set our Heading Bug to runway heading, 080°. Set the Heading bug 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).
Page 88: Figure 3-10 Cdi Navigation Source Selection Button
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 •...
Page 89: Figure 3-13 Changing The Map Declutter Level
Select Map Declutter Level NOTE 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 The Basemap symbols and flight plan legs rendered on the bottom left of the Nav Display (Figure 3-13a) The Declutter settings can be for each of the map’...
Page 90: Figure 3-14 Range Button
Change the Map Range 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...
Page 91: Figure 3-17 Traffic Overlay On
Evolution Hazard Awareness and Traffic Overlay 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. Display the Traffic Overlay Display the 2/2 Hot Key menu. Press the TRFC Hot Key to select the desired Altitude Filter.
Page 92: Figure 3-18 Altitude Bug Enabled
Set the Altitude Alerter 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). Rotate the Right Knob to change the value of the Selected Altitude field. Rotate clockwise to increase, or counterclockwise to decrease, the value.
Page 93: Figure 3-21 Selected Airspeed Field Enabled
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. Set the Airspeed bug Figure 3-22 Press the Right Knob until ALT displays above the Right Knob and the...
Page 94: Departure
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.
Page 95 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.
Page 96: Enroute
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. • 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”...
Page 97: Figure 3-28 Gpss Enabled Legend In Green
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.
Page 98: Figure 3-30 360° Compass Mode
Select a Compass Mode • 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.
Page 99: Arrival And Approach To Landing
3.2.4. Arrival and Approach to Landing As we near Reno, we prepare for our arrival. Within range, we pick up the ATIS: 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.
Page 100: Gpss Enabled
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: Press the Right Knob twice to select ALT for editing.
Page 101 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.
Page 102 Even though the PFD Navigation Source for the CDI has switched to VLOC1 and the ILS, CAUTION 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 The Garmin 400/500 series navigators continue to ILS, required for this approach.
Page 103: Showing Glide Slope
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.
Page 104 3.3. Conclusion 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.
Page 105: 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.
Page 106: Air Data, Attitude And Heading Reference System (Adahrs)
4.1. Air Data, Attitude and Heading Reference System (ADAHRS) 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.
Page 107: Attitude
4.1.1. Attitude 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.
Page 108: Pitot Obstruction Monitor
4.1.2. Pitot Obstruction Monitor 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.
Page 109: Heading
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.
Page 110: Free Gyro Mode
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.
Page 111: Degraded Adahrs Performance
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. ...
Page 112: Attitude Display
4.2. Attitude Display 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.
Page 113: Roll Scale
4.2.1.1. Roll Scale 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. 4.2.1.2.
Page 114: Airspeed Indicator
4.2.2. Airspeed Indicator 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...
Page 115: Ground Speed >50Kts Annunciation
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.
Page 116: Selected Airspeed
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.
Page 117: Airspeed Display
4.2.2.2. Airspeed Display NOTE 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 Altitude Tape can also be turned off for screen the PFD system is turned off then powered on again.
Page 118: Mach Number Display For Mmo Aircraft
4.2.2.3. MACH Number Display for Mmo Aircraft 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.
Page 119: Altimeter
4.2.3. Altimeter 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). Altitude Alerter Altitude Tape MINIMUMS Annunciation/ Selected Altitude Field Selected MINIMUMS Field...
Page 120: Barometric Units Of Measure
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.
Page 121: Selected Altitude Field
Set the barometric Pressure Press the BARO Hot Key. The BARO label above the Right Knob and Barometric Pressure Setting Field appear in magenta (Figure 4-21). 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.
Page 122: Altitude Level-Off And Deviation Alert
4.2.3.3. Altitude Level-Off and Deviation Alert NOTE 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 Rotating the knob quickly will change the altitude feet or 15 seconds of reaching the selected altitude (Figure 4-23).
Page 123: Minimums Annunciation
4.2.3.4. MINIMUMS Annunciation 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.
Page 124: And Markers Disabled
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.
Page 125: Set Altitude Minimum
Set Altitude Minimum Press the MIN Hot Key to set the altitude minimum. 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).
Page 126: Radio Altitude Display
4.2.3.5. Radio Altitude Display 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 Figure 4-32b the radio altimeter, the Radio Altimeter display window is removed.
Page 127: Altitude Display
4.2.3.6. Altitude Display NOTE 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 A typical PFD only installation sets the tapes display are affected by this action.
Page 128: Data Bar
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.
Page 129: Ground Speed
Select the Transition Setting 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. 4.3.2.
Page 130: Wind Speed, Direction And Arrow (When Enabled)
4.3.4. Wind Speed, Direction and Arrow (when enabled) The Wind Direction Arrow, Wind Direction and Wind Speed are displayed in the lower Figure 4-38 right portion of the Data Bar (Figure 4-36). Wind Direction Arrow The Wind Speed has a range of 10 to 999 knots or mph, using the same unit of measure as the Airspeed Indicator.
Page 131: Navigation Display
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). 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.
Page 132: Compass
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 The PFD offers three Compass Modes: 360°, ARC HSI, and ARC CDI. The default Compass Mode is 360.
Page 133: Select Arc Cdi/Hsi Compass Mode
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). Select ARC CDI/HSI Compass Mode Press the MENU Button.
Page 134: Select Compass Type
Select Compass Type Press the 360/ARC Hot Key (Figure 4-46) to alternately select either the 360° or ARC Compass Mode. The Navigation Display changes and the Hot Key label reflects the currently selected Compass Mode (Figures 4-47 and 4-48). Figure 4-46 Figure 4-47 Figure 4-48 360/ARC Hot Key...
Page 135: Course Pointer
4.4.2. Course Pointer 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. COMPASS DESCRIPTION Figure 4-49...
Page 136: To/From Indicator
4.4.3. TO/FROM Indicator 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.
Page 137: Course Deviation Indicator And Scale
4.4.4. Course Deviation Indicator and Scale 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. The 360° and ARC HSI Compass Modes show the CDI as a green line centered on the display and parallel with the Course Pointer.
Page 138: Localizer Back Course (Bc) Operation
4.4.4.a. Localizer Back Course (BC) Operation 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”...
Page 139: Select The Cdi Navigation Source
NOTE There are many radio configurations available. Your Figure 4-63 authorized Aspen Avionics Dealer can explain the CDI Source selection and Information configuration used on your aircraft. EFD1000 C3 Pro PFD Pilot’s Guide Page 4-35...
Page 140: Table 4-4 Vhf Nav Radio Modes
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. Radio Mode Information Block Label GPS1 or GPS2 VOR1 or VOR2...
Page 141 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).
Page 142: Auto Course
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).
Page 143: Cdi Selected Course
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). Rotate the Right Knob to select DISABLE (Figure 4-74).
Page 144: Bearing Pointer Source Selection
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.
Page 145 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.
Page 146: Select The Single-Line Bearing Pointer Source
Select the Single-Line bearing Pointer Source NOTE Press the Single-Line Bearing Pointer Button (Lower Left Button, Figure 4-80) until the desired navigation source is shown above the Button. A VOR that is tuned to a localizer frequency is Select the Double-Line bearing Pointer Source considered an invalid Bearing Pointer source since Localizer signals provide no bearing information.
Page 147: Heading Bug
4.4.9. Heading Bug 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). When the Selected HDG Field value is outside the visible compass scale range in the Figure 4-82 ARC Compass mode, only a portion of the Heading Bug is shown at the edge of the Heading Bug and Selected...
Page 148: Aircraft Heading Display
4.4.10. Aircraft Heading Display 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, Figure 4-85 including the CDI and bearing pointers (if previously displayed), is removed and Direction of Flight replaced with a single red X covering the entire lower display area, along with the Numerical Display...
Page 149: Basemap Overlays
4.4.12. Basemap Overlays 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.
Page 150: Basemap Declutter And Range
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. 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.
Page 151: Enable Auto Range
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).
Page 152: Flight Plan
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.
Page 153: Ground Track Marker
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). 4.4.13. Ground Track Marker When configured with a GPS that provides ground track data, a Ground Track Marker is Figure 4-99 displayed on the compass scale to indicate the aircraft’...
Page 154: Lateral And Vertical Deviation Indicator
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.
Page 155: Vertical Deviation Indicator
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 Figure 4-103 displayable range of 2.5 dots, the Course Deviation Diamond becomes dim and hollow, Lateral Deviation Diamond and is parked at the extreme edge of the LDI scale (Figure 4-103).
Page 156: Vertical Speed Indicator
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.
Page 157: Autopilot Integration
4.7. Autopilot Integration 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) NOTE with which the autopilot was originally certified. Autopilot integration is limited to heading and navigation modes, including vertical approach modes.
Page 158: Gps Steering (Gpss)
4.7.1. GPS Steering (GPSS) WARNING 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 GPS Steering is a powerful automation tool that between waypoints. can substantially reduce pilot workload.
Page 159: Enable/Disable Gpss
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 NOTE on the PFD and the Heading mode of the autopilot, the autopilot is able to fly GPSS commands.
Page 160 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;...
Page 161 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 NOTE 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...
Page 162: Flight Director
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.
Page 163: Hdg Mode Operation - Heading Bug Steering
HDG Mode Operation – Heading bug Steering NOTE Set the PFD Heading Bug to the desired heading (Section 4.4.9). Verify that GPSS is not selected. When GPSS is enabled, the HSI Heading Bug is not Select the autopilot’s Heading (HDG) mode. coupled to the autopilot.
Page 164: Nav Mode Operation - Gps Navigation
NAV Mode Operation – GPS Navigation NOTE 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.). Not all autopilots operate in the manner described If AUTOCRS is disabled, set the Course Pointer to the desired course (CRS) (see here for intercepting courses.
Page 165: Appr Mode Operation - Ils Approach With Vectors To Final
APPR Mode Operation – ILS Approach with Vectors to Final 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).
Page 166: Gps/Rnav Apv Waas Approach
APPR Mode Operation – GPS or GPS/RNAV APV WAAS Approach NOTE 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.). WAAS GPS navigators can provide vertical guidance 2.
Page 167: Gps Appr Mode Operation - Waas Gps Underlay To Ils Approach Using Pilot Navigation And Gpss
GPS APPR Mode Operation – WAAS GPS Underlay to ILS Approach Using Pilot Navigation and GPSS NOTE 1. With a valid ILS approach loaded and activated in the GPS, use the CDI Source The PFD supports GPS LPV approaches (Approaches Select Button to couple the GPS to the PFD CDI (see Section 4.4.5.).
Page 168: Hazard Awareness
GPS APPR Mode Operation – WAAS GPS Underlay to ILS Approach With ATC Vectors to Final 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.
Page 169: Traffic Overlay
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: • Avidyne TAS 600/610/620 series (TAS) • Bendix/King KMH 880 (TAS) • Bendix/King KTA 870 (TAS) • Garmin GTX 330 (TIS) Figure 4-114 • RYAN 9900BX (TAS)
Page 170: Traffic Symbols
4.8.1.1. Traffic Symbols 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 Traffic Advisory (hollow cyan diamond).
Page 171 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.
Page 172: Traffic Altitude Filter
When a traffic symbol and the Ownship Symbol partially or completely overlap, the traffic symbol and data block will overlay the ownship symbol. NOTE Depending on the position of the Traffic Advisory at the 4.8.1.2. Traffic Altitude Filter edge of the screen, the traffic symbol data block may or There are five Traffic Altitude Filter settings: Off, Normal, Unrestricted, Above, and Below may not display.
Page 173: Traffic Unavailable
4.8.1.3. Traffic Unavailable When the TAS (Traffic Advisory System) sensor’s status is STANDBY, TEST or FAIL: • An Invalid Traffic Sensor annunciation (Figure 4-131) is displayed and the Traffic symbols are removed from view Figure 4-118 When the Traffic interface is a TIS (Traffic Information Service) and the Traffic data is: Traffic Sensor Invalid • Unavailable –...
Page 174 This Page Intentionally Left Blank Page 4-70 EFD1000 C3 Pro PFD Pilot’s Guide 091-00019-001 REV B...
Page 175: Chapter 5 Customizing The Pfd
Chapter 5 Customizing the PFD 5.1. Menu Overview The following tables and figures provide a brief overview of each menu page and its menu options. KEY DESCRIPTION OPTIONS Displays Airspeed and DISABLE or ENABLE Altitude Tapes Figure 5-1 Radio Altitude DISABLE or ENABLE GENERAL SETTINGS A Auto Course Select...
Page 176: Table 5-2 Menu – General Settings B
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: OFF, ON>5K, ON>6K, ON>7K, ON>8K, ON>9K, ON>10K, ON>11K, ON>12K, ON>13K, ON>14K, Figure 5-2 ON>15K, ON>16K, ON>17K, GENERAL SETTINGS B ON>18K...
Page 177: Table 5-3 Menu – 360° Map Settings
KEY DESCRIPTION OPTIONS 360° Declutter Level 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 –...
Page 178: Table 5-4 Menu – Arc Map Settings
KEY DESCRIPTION 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 Figure 5-4 ARC MAP SETTINGS Table 5-4 Menu –...
Page 179: Table 5-5 Menu – Vspeeds A
KEY DESCRIPTION OPTIONS KEY DESCRIPTION OPTIONS V SPEEDS DISABLE or ENABLE 0 to 450 or LOCKED 0 to 450 or LOCKED 0 to 450 or LOCKED 0 to 450 or LOCKED 0 to 450 or LOCKED Vref 0 to 450 or LOCKED 0 to 450 or LOCKED Figure 5-5 Table 5-6...
Page 180: Table 5-7 Menu – Power Settings
KEY DESCRIPTION OPTIONS Operating from or Switch to Battery Power. Green when current state (Pressing key performs no action). White if selection is Status or Action possible. Operating from or Switch to External Power. Green when current state (Pressing key performs no action). White if selection is Status or Action possible.
Page 181: Table 5-8 Menu – System Status
KEY DESCRIPTION OPTIONS Main Application Processor Software Versions 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 091-00019-001 REV B EFD1000 C3 Pro PFD Pilot’s Guide Page 5-7...
Page 182: Customizing Basemap Symbol Declutter Settings
5.2. Customizing Basemap Symbol Declutter Settings 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.
Page 183: Set Map Symbol Display
Set Map Symbol Display 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).
Page 184: Figure 5-13 Level 4
Feature Group & Layer Order Max Range Declutter Setting (top to bottom) Figure 5-13 Level 4 Figure 5-14 Level 3 Figure 5-15 Level 2 Figure 5-16 Level 1 Figure 5-17 Level 0 (Off) Overlay — enabled Traffic Overlay Symbol Always ON regardless of declutter level via Hot Key Ownship Symbol Always ON regardless of declutter level...
Page 185: Configuring Vspeeds
5.3. Configuring Vspeeds Vspeeds are used to designate different operating speeds of the aircraft and are defined in Table 5-10. Vspeed DEFINITION PRE-SET ADJUSTABLE PRE-SET BANDS TEXT LABELS MARKERS Never exceed (Red Line) Maximum structural cruising speed Maximum full flap extension speed No flap stall NOTE...
Page 186 Vspeed DEFINITION PRE-SET ADJUSTABLE PRE-SET BANDS TEXT LABELS MARKERS Maximum landing gear operating speed (Multi-engine) Single-engine minimum control airspeed (Red Line) (Multi-engine) Best single-engine rate Vyse of climb (Blue Line) Maximum initial flap extension speed Table 5-10 Vspeed Definitions Page 5-12 EFD1000 C3 Pro PFD Pilot’s Guide 091-00019-001 REV B...
Page 187: Figure 5-18 Speed Bands
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.
Page 188: Display Or Hide The Vspeed Textual Markers
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. When using the Vspeed textual markers, the pilot must first ENABLE the display of the markers and then set values for each Vspeed.
Page 189: Set Textual Vspeed Labels
Set Textual Vspeed Labels 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).
Page 190: Lcd Brightness Control
5.4. LCD Brightness Control 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. LCD MODE DESCRIPTION AUTOMATIC LCD backlight intensity is automatically adjusted based on the ambient...
Page 191: Expanded Emergency And Abnormal Procedures
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.
Page 192: Pitot/Static System Blockage
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. A static line blockage will result in altitude remaining fixed and a zero vertical speed despite aircraft pitch and/or power setting changes.
Page 193: Blocked Pitot Or Static Line Suspected
blocked Pitot or Static Line Suspected 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 CAUTION Most light aircraft have only a single pitot and static port available for flight instrument use.
Page 194: Identifying And Handling Suspected Pitot And/Or Static System Failures
6.1.1. Identifying and Handling Suspected Pitot and/or Static System Failures 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.
Page 195 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.
Page 196 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).
Page 197: Frequent Or Persistent
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 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.
Page 198: Abnormal Shutdown Procedure
6.4. Abnormal Shutdown Procedure 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.
Page 199: Loss Of Aircraft Electrical Power
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.
Page 200 NOTE WARNING When operating on the internal battery, the display When fully charged, the internal battery will power the PFD to provide ADAHRS and backlight intensity is limited to a value of 70. emergency RSM GPS position (if enabled) for approximately 30 minutes. When continued safe operation depends on the PFD’...
Page 201: Gps Failures And Rsm Emergency Gps Use
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.
Page 202 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).
Page 203: Power Override
6.7. Power Override NOTE In the event that the pilot wishes to override the PFD’s automatic power configuration, When airborne, if the PFD’ s input voltage is below the proceed as follows: 12.8V (14V Electrical System) or 25.6V (28V Electrical Power Override System) automatic battery transition threshold, and EXT PWR is selected through the POWER SETTINGS...
Page 204: In-Flight Ahrs Reset
6.8. In-Flight AHRS Reset 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 Figure 6-5 slip information is removed from the Attitude Display (Figure 6-6).
Page 205: Perform An In-Flight Ahrs Reset
Perform an In-Flight AHRS Reset 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).
Page 206: Gpss Operation, Annunciations, And Autopilot Modes
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.
Page 207: When Gpss Automatically Changes To Wings Level Mode
When GPSS Automatically Changes to Wings Level Mode 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).
Page 208: Warning, Caution, And Advisory Summary
6.10. Warning, Caution, and Advisory Summary 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 6-13 If the battery temperature is less than 0°...
Page 209 WARNINGS When the Attitude Indicator display extreme pitch up or extreme pitch down attitudes, the red chevrons indicate the direction to restore level flight. Figure 6-16 Figure 6-17 Chevrons indicate Pitch Down Chevrons indicate Pitch Up Table 6-1 Warning Annunciations 091-00019-001 REV B EFD1000 C3 Pro PFD Pilot’s Guide Page 6-19...
Page 210: Figure 6-18 Cross Check Attitude
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...
Page 211: Figure 6-24 Gps Integrity Flag
CAUTION Figure 6-21 Figure 6-20 RSM GPS GPS Invalid Presented when a configured GPS source’s data is invalid or unavailable. GPS# or RSM REVERSION annunciations indicate the current GPS basemap source. Figure 6-22 Figure 6-23 GPS Reversion 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)..
Page 212: Figure 6-27 Gpss Source Lost/Changed
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.
Page 213: Figure 6-29 Rev Button Off
ADVISORY Presented when the REV Button is pressed. Figure 6-29 REV Button Off 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.
Page 214: Figure 6-31 Gps Annunciations
ADVISORY 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 A horizontal red line through the Selected CDI Navigation Source indicates that the data from the Navigation Source Invalid or source is invalid or unavailable.
Page 215: Chapter 7 Appendices
7.1. Operating Limitations 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.
Page 216: View The Main Application Processor Software Version
View the Main Application Processor Software Version 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.
Page 217: Specifications
7.3. Specifications 7.3.1. Primary Flight Display Unit (PFD) GENERAL SPECIFICATIONS Width 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.
Page 218 I/O SPECIFICATIONS ARINC 429 Inputs ARINC 429 Outputs RS-232 Inputs RS-232 Outputs Pitot / Static Quick Connect CERTIFICATION SPECIFICATIONS Technical Standard Order TSO-C2d / ETSO-C2D...............Airspeed Instruments TSO-C3d / ETSO-C3D..............Turn and Slip Instrument FAA and EASA (European Aviation TSO-C4c / ETSO-C4C............Bank and Pitch Instruments Safety Agency) TSO-C6d / ETSO-C6D............Direction Instrument Magnetic (Gyroscopically Stabilized)
Page 219: Remote Sensor Module (Rsm)
7.3.2. Remote Sensor Module (RSM) Width 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 Table 7-2 Remote Sensor Module (RSM) Specifications 7.3.3. Analog Converter Unit (ACU) Width 5.75 in.
Page 220: Operational Specifications
7.3.4. Operational Specifications Airspeed Range Minimum displayed airspeed 20 KIAS Maximum displayed airspeed 500 KIAS Altitude Range Minimum displayed altitude -1,600 ft. MSL Maximum displayed altitude 51,000 ft. MSL Vertical Speed Maximum displayed vertical speed rates (tape) +/-2,000 fpm Range Maximum displayed vertical speed rates (numerical +/- 9,990 fpm value)
Page 221: Glossary
7.4. Glossary AWOS Automated Weather Observation System Back Course Localizer back course approach where the °C Degrees Celsius signal on the back side of the localizer is used °F Degrees Fahrenheit for alignment to the runway opposite of normal localizer alignment. Accuracy Estimated position accuracy in feet or meters Battery Time...
Page 222 Crosstrack Error The distance the aircraft is off the desired course. Evolution Flight Display Course EFIS Electronic Flight Instrument System Course to Steer Elevation The height above mean sea level. decibels ‘Z’ (radar return) ETA (Destination) Estimated Time of Arrival. The estimated time you will reach a Go To destination or the final Direct Current waypoint in a route.
Page 223 Ground Speed The velocity that the aircraft is travelling relative Latitude to a ground position. Liquid Crystal Display Glide Slope or Ground Speed Lateral Deviation Indicator Heading The direction an aircraft is pointed, based upon The portion of a flight plan between two indications from a magnetic compass or a waypoints.
Page 224 Secure Digital Traffic Advisory System TACAN Tactical Air Navigation System True Air Speed TCAS Traffic Collision Avoidance System TERM Terminal Mode Traffic Information System Track Direction of aircraft movement relative to a ground position; also ‘Ground Track’ Technical Standard Order Volts, Alternating Current Volts, Direct Current Vertical Deviation Indicator...
Page 225: Index
7.5. Index Altimeter ........................4-15 - 4-23 ADAHRS ..........................4-2 - 4-7 Attitude ............................4-3 Decision Height ........................4-22 MINIMUMS .......................4-19 - 4-21 Free Gyro Mode ........................4-6 Heading............................4-5 Altitude ...........................4-15 - 4-18 Alerter ............................4-15 Pitot Obstruction Monitor ....................4-4 Advisory ..........................6-23, 6-24 Alerter, Set ........................3-14, 4-17 Bug ............................4-17 GPS Annunciations ......................6-23 GPSS On ...........................6-22...
Page 226 Auto Course ........................2-34, 4-38 Nav Sources, Select ......................3-10 Disable ............................4-39 Single-Line Bearing Pointer Source, Select ............4-42 Enable............................4-38 Source Select Buttons .....................2-10 Autopilot Integration ......................4-53 Source Selection ....................4-40 - 4-42 Autopilot Operations, Typical ..................4-58 Brightness Control .........................5-16 APPR Mode Operation - GPS or GPS/RNAV APV WAAS Approach ..4-62 See also Lighting APPR Mode Operation - ILS Approach with Vectors to Final ....4-61 BRT ADJUST ..........................2-17...
Page 227 Source Information Block ....................4-35 Terminology .......................... xxvii Source Label ..........................4-35 Warnings, Cautions, Notes ....................xxx Source Select Button .......................4-35 Copyrights, Trademarks and Patents ................xxi Check Pitot Heat ........................6-19 Course Deviation Indicator and Scale ...............4-33 CHECK PITOT HEAT ........................4-4 Course Pointer ..........................4-31 Cleaning the Display Screen ....................2-20 Course Pointer and Deviation Indicator ..............2-32 Color Philosophy ........................xxix...
Page 228 Integrity Flag .........................6-20 Invalid ............................6-20 EDIT VALUE ..........................2-14 Reversion ..........................6-20 Electrical Power, Loss of Aircraft ..................6-9 Reversion Emergency......................6-20 Emergency and Abnormal Procedures ............6-1 - 6-24 GPSS ............................4-54 Pitot/Static System Blockage ................6-2 - 6-6 Disable ............................6-16 Evolution Flight Display (EFD) system ................1-1 Enable/Disable ........................4-55 Dual Display ..........................1-2 Engage ............................3-18...
Page 229 Initial Flap Extension Speed Marker ................4-10 SYSTEM STATUS........................5-7 Instrument Approach Indicators ..................2-26 VSPEEDS A ..........................5-5 Internal Battery Status, View ....................6-12 VSPEEDS B ..........................5-5 Introduction ........................1-1 - 1-3 Page graphical bar ......................2-14 Page Name ..........................2-14 Page number and mode ....................2-14 SEL PAGE ........................2-14, 2-15 Knobs xxviii, 2-4–2-8 Using the Menus ........................2-14...
Page 230 MIN, Hot Key..........................2-12 Vertical Speed Indicator ....................2-37 ............................4-21 Navigation Source Select Buttons 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 Numerical Airspeed Value ....................4-10 Source Invalid or Unavailable ..................6-23 Numerical Altitude Value ....................4-15...
Page 231 REV Button ..........................2-19 System Overview ........................1-4 ............................6-23 Power On Manually ......................6-8 Shutdown EFD1000 PFD (on ground) ..............6-8 Terminology ........................xxvii - xxviii Shutdown Procedure, Abnormal ................6-8 Buttons ............................xxviii Right Knob Functions ....................2-5, 2-6 Hot Keys ..........................xxviii RNAV Instrument Approaches..................4-62 Knobs ............................xxviii Roll Scale ............................4-9 Menu Keys ..........................xxviii RSM Emergency GPS Use ....................6-11...
Page 232 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...
Page 234 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 info@aspenavionics.com www.aspenavionics.com 091-00019-001 REV B EFD1000 C3 Pro PFD Pilot’s Guide Printed in USA...

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

Table of Contents

Table of Contents

Chapter 1 Welcome and Introduction

Chapter 2 Controls and Display

Chapter 3 Flying the PFD

Chapter 4 Reference Guide

Chapter 5 Customizing the PFD

Chapter 6 Expanded Emergency and Abnormal Procedures

Chapter 7 Appendices

Quick Links

Chapters

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