Aspen Avionics Evolution EFD1000 PFD Service manual

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 1-36 Revision AD
© Copyright 2019 Aspen Avionics Inc.
EFD1000 and EFD500
Instructions
for
Continued Airworthiness
AIRCRAFT MAKE:
AIRCRAFT MODEL:
AIRCRAFT SERIAL NUMBER:
Modification of an aircraft under the EFD1000 AML Supplemental Type Certificate obligates the
aircraft operator to include the maintenance information provided by this document in the
operator’s ICA, Aircraft Maintenance Manual and operator’s Aircraft Scheduled Maintenance
Program.
Aspen Document # 900-00012-001 Revision AD

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 2-36 Revision AD
© Copyright 2019 Aspen Avionics Inc.
ICA –RECORD OF REVISION
Revision
Description of Change
ECO
ICA Revision IR
through
Revision Q
See ECO record
See ECO record
R
Added Operator Security safeguards information
3262
S
Improved Security Safeguards information. Presented checklist suggestions in Sections 11
and 12.
3298
T
Based on the EFD Extended Life Battery Test Report (Aspen document number 037-00042-
001) extended internal and external (EBB58) battery life to 2200hrs or 3 years
3360
U
Removed references to “XM” to cover additional datalink weather sensors. Fixed typo in
AFMS part number and updated the revision of the Installation Manual.
4251
V
Updated the Installation Manual references to the latest revision.
4392
W
Updated the Installation Manual references to the latest revision. Added instructions under
CM Replacement for Angle of Attack (AOA). Changed Copyright from 2012 to 2015.
4486
X
Rev X not employed
N/A
Y
Added Aspen Evolution Backup Display (EFD1000 EBD).
4709
Z
Added support for the EFD1000 E5 Dual EFI and internal battery.
5445
AA
Added EFD1000/500 MAX part numbers in Section 11. Added “Degraded Mode” to
troubleshooting table Section 13. Added words “or Audio” to Section 14, EFD Replacement.
Corrected typographical errors. Truncated the revision history. Added FAA-recommended
information regarding checks of heading performance after other modifications in section 2.
5707
AB
Revision Not Submitted
6130
AC
Revision Not Submitted
6158
AD
Extend internal battery and external battery (EBB-58) replacement interval to 2200 hours or
4 years (Section 11)
6169

EFD1000 and EFD500 Instructions for Continued Airworthiness
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EFD1000 and EFD500 Instructions for Continued Airworthiness
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Table of Contents
1INTRODUCTORY INFORMATION ................................................................................................. 5
2SYSTEM DESCRIPTION AND INFORMATION ABOUT THE INTERFACE OF THE EFD1000/500 SYSTEM
WITH THE AIRCRAFT ................................................................................................................ 7
3DESCRIPTION OF HOW THE EFD1000 SYSTEM OPERATES AND IS CONTROLLED, INCLUDING
SPECIAL PROCEDURES AND LIMITATIONS .................................................................................. 8
3.1 MAINTAINING SECURITY SAFEGUARDS WITH THE ASPEN CONNECTED PANEL................................. 8
3.1.1 Physical Security .....................................................................................................8
3.1.2 Operational Security................................................................................................8
3.1.3 Security Safeguards Monitoring ...............................................................................9
3.1.4 Management Procedures .........................................................................................9
3.1.5 Maintenance Procedures for Maintaining Security Safeguards ...................................9
4SYSTEM OPERATION AND PROCEDURES FOR SYSTEM TESTING DURING GROUND RUNNING .......... 9
5SERVICING AND SCHEDULING INFORMATION............................................................................ 10
6OVERHAUL PERIOD.................................................................................................................. 10
7COMMERCIAL PARTS ............................................................................................................... 10
8SPECIAL TOOLS ....................................................................................................................... 10
9AIRWORTHINESS LIMITATIONS ................................................................................................. 10
10 DISTRIBUTION OF REVISIONS ................................................................................................... 10
11 PERIODIC MAINTENANCE AND CALIBRATION AND STORAGE LIMITATIONS................................. 11
11.1 INSPECTION CHECKLIST ............................................................................................... 13
12 UNIT AND WIRING INSPECTION ................................................................................................ 14
12.1 INSPECTION CHECKLIST ............................................................................................... 15
13 TROUBLESHOOTING ................................................................................................................ 17
14 REMOVAL AND REPLACEMENT ................................................................................................. 26
15 WIRING AND COMPONENT LOCATION DATA ............................................................................ 32

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 5-36 Revision AD
© Copyright 2019 Aspen Avionics Inc.
1Introductory Information
These Instructions for Continued Airworthiness (ICA) provides instructions necessary for
authorized personnel to inspect and maintain the EFD500 and EFD1000 system installed by the
EFD1000 AML-STC.
This document must be printed and included with the aircraft Instructions for Continued
Airworthiness, and arranged for easy and practical use.
Description of the Appliances and its Systems and Installations:
The Aspen Avionics EFD1000 and EFD500 systems are multi-purpose displays. The EFD1000
contains an internal Air Data and Heading Reference System (ADAHRS) that is used to provide
attitude, heading and air data for the display. The EFD500 is a variant of the EFD1000 and does
not contain the internal ADAHRS. The EFD1000 (except the Evolution Backup Display (EBD)
version) and the EFD500 come standard with an internal battery to provide a nominal 30 minute
operation in the event of power loss. These batteries (except for the EFD1000 E5) are not
designed to provide 30 minute operation under all foreseeable operating conditions, such as
extreme cold temperatures where battery operation is not assured. The EFD1000 E5 internal
battery does provide at least 30 minutes of operation under all foreseeable operating conditions.
An optional (standard on EBD) Emergency Backup Battery (EBB) is available that will provide at
least 30 minutes of operation under all foreseeable operating conditions. Typical EBB endurance
at 25 deg C will exceed two hours when the battery is fully charged. When an Aspen Primary
Flight Display (PFD) is installed, and the Emergency Backup Battery is connected to an EFD1000
Multi-Function Display (MFD), the legacy standby altimeter and airspeed indicators may be
removed from the aircraft. When the EFD1000 EBD is installed as backup instruments to non-
Aspen PFD, the legacy standby altimeter, airspeed and attitude indicators may be removed.
Additional equipment is normally installed in support of the displays, including the Remote
Sensor Module (RSM), Configuration Module (CM), optional Emergency Backup Battery (as noted
above) and optional Analog Converter Unit (ACU). Several external sensors can optionally be
connected to the displays, including GPS systems, datalink weather receivers, the Aspen CG100
Gateway, WX-500 Stormscope, GTX330 and certain other ARINC 735A protocol TAS and TCAS I
systems. The Avionik Straubing APS4A Altitude Preselect System can be installed for Altitude
Preselect capability. The EFD1000 E5 has required connections to an RSM, CM, and one GPS
receiver and optional connections to an ACU and one navigation receiver.
The EFD1000 system can be configured as a PFD or MFD or EBD or E5. In the PFD, EBD, or E5
configuration, the EFD1000 provides display of attitude, airspeed, altitude, direction of flight,
vertical speed, turn rate, and turn quality. The system can provide display of navigation
information, pilot-selectable indices (“bugs”), and annunciations to increase situational
awareness and enhance flight safety.
The “Pro” and “Pilot” configuration are available in software version 2.1 and later. The EBD
“Advanced” and “Basic” configuration are available in software 2.8.3 and later. The E5 is available
in software E5 2.10 and later. The EFD1000/500 MAX displays are available in software 2.10 and

EFD1000 and EFD500 Instructions for Continued Airworthiness
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© Copyright 2019 Aspen Avionics Inc.
later. The Pro and EBD “Advanced” System can display WX-500 data, datalink weather products
and traffic information from ARINC 735 compatible traffic systems. The Pilot and EBD Basic
systems provide a moving map; however they do not provide an HSI or second GPS navigation.
The E5 does not have a moving map but can display information from one GPS and one
navigation receiver.
The EFD1000 can also be purchased in a multi-function display configuration with reversion
capability to a Primary Flight Display. The EFD500 is a variant of the EFD family that does not
include an ADAHRS. The EFD500 may only be purchased in a multi-function display
configuration, and does not include reversion capability. The E5 is standalone with no second
display option.
For additional information, refer to Section 3 of the EFD1000 and EFD500 SW v2.X Installation
Manual, 900-00003-001 Rev BY or later. For additional information on the EFD1000 E5 see
Section 3 of the EFD1000 E5 Flight Display Installation Manual, 900-00041-001 Rev ( ) or later.
The following data may be necessary for maintenance or preventive maintenance:
Replacement Parts:
See Section 1 of the EFD1000 and EFD500 SW v2.X Installation Manual,
document 900-00003-001 Rev BY or later (or for the EFD1000 E5,
900-00041-001 Rev ( ) or later) for Aspen replacement parts.
For the APS4A Altitude Preselect System, contact:
Avionik Straubing Entwicklungs GmbH
Flugplatzstr. 5 Atting D-94348 Germany
www.avionik.de
Software Version Compatibility
Class III aircraft (typ. >6000 lbs. Maximum Gross Takeoff Weight (MGTOW),
see AC 23.1309-1X) require a PFD containing RTCA DO-178B Level B
software. Verify the software level on the EFD Data tag before installation.
See Section 5.2, “ICA Software Compatibility” of the EFD1000 and EFD500 SW
v2.X Installation Manual, document 900-00003-001 Rev BY or later.
Operating Instructions:
See the EFD1000 Aircraft Flight Manual Supplement (AFMS), document 900-
00008-001or the EFD1000 E5 Aircraft Flight Manual Supplement (AFMS),
document 900-00038-001.
Wire Routing Locations:
See attachment to this document (part of the permanent aircraft records).
Wiring Diagrams:
See attachment to this document (part of the permanent aircraft records).
Special Tools
For bonding checks, use a milliohm meter such as an Extech 380460 Portable
Precision Milliohm Meter or equivalent.
It may be required to align the EA100 Adapter to the autopilot computer using
a KTS-150 Test Set, a KTS-158 Test Set, a KTS-154 Test Set or equivalent and
following the autopilot manufacturer’s procedure for aligning the gyro (KI-
256) to the autopilot computer (these Test Sets are normally available at
autopilot-qualified Bendix-King dealers). The EA100 Alignment Tool
(acquired through the dealer ramp Section of the Aspen.com web site, see
Tech Note 2010-10) will be used to manipulate the gyro pitch and roll signals
and the autopilot Test Set will be used to measure the autopilot demodulated
gyro voltages. In the case of the KFC225 the Remote Terminal Interface
(normally available at autopilot-qualified Bendix-King dealers) will be required
in place of the test sets.

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 7-36 Revision AD
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See Appendix E of the EFD1000 and EFD500 SW v2.X Installation Manual,
document 900-00003-001 Rev BY or later or Appendix E of the EFD1000 E5
Dual Electronic Flight Instrument (EFI) Install Manual, 900-00041-001 Rev ( )
or later for detailed information.
It may be required to receive a WiFi signal from the CG100. A wireless-
enabled device such as a laptop computer, iPad, iPhone or Android device will
be suitable for this purpose.
Consumables
Loctite® 242® Threadlocker or equiv
Dow Corning 738, MIL-A-46146 or equiv
Pro-Seal PS 870B-1/2, MIL-PRF-81733D or equiv
2System Description and Information about the Interface of the
EFD1000/500 System with the Aircraft
The EFD1000 PFD, EFD1000 EBD, and EFD1000 E5 system is comprised of the Electronic Flight
Display (EFD), Remote Sensor Module (RSM), Configuration Module (CM) and optional Analog
Converter Unit (ACU or ACU2). Optionally one or two MFD displays of either the EFD500 or
EFD1000 may be installed with an accompanied PFD system. An optional EA100 Adapter
(autopilot attitude adapter) may be installed.
The EFD1000 PFD, EBD and E5 system provides display of attitude, airspeed, altitude, direction of
flight, vertical speed, turn rate, and turn quality. The system may optionally provide display of
navigation information through interfaces to GPS Receivers and/or VHF Navigation Receivers.
When interfaced with a compatible autopilot, the EFD1000 system provides heading and course
datum information to the autopilot, which enables the autopilot to follow the Course and
Heading values set by the pilot on the EFD1000.
If optional MFD displays are installed they can present terrain, traffic, weather, and WX-500
Stormscope data to the flight crew. The EFD1000 MFD can be used as backup instruments to the
PFD supporting reversionary capabilities. The EFD500 presents MFD data, but cannot be used for
backup or reversion.
The optional EA100 supplies pitch and roll stabilization signals to the autopilot. The article has
no direct pilot controls.
The Avionik Straubing TSO’d APS4A is integrated with the EFD1000 and provides Altitude
Preselect capability. The APS4A is not applicable to the EFD1000 E5.
The CG100 Gateway allows mobile devices to interface to other avionics through an EFD1000
MFD or EFD500 MFD.
NOTE: Other modifications to the aircraft could affect the EFD1000 PFD and MFD magnetic
sensors. The EFD1000 PFD and MFD heading performance should be checked after other
modifications. See Section 10.5.4, heading accuracy test in the EFD1000 and 500 SW 2.X
Installation Manual, document 900-00003-001 revision BY or later.

EFD1000 and EFD500 Instructions for Continued Airworthiness
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3Description of How the EFD1000 System Operates and is Controlled,
Including Special Procedures and Limitations
The EFD1000 system is controlled by a switch marked “EFD1000 PFD” or “PFD”, “ASPEN” (for EBD
system), “EFD” (for E5 system) and, (if installed) “EFD1000 MFD”. The system is ready to be
operated when the initialization screen disappears, and the EFD1000 attitude and heading
display is shown. See the EFD1000 Aircraft Flight Manual Supplement (AFMS), document 900-
00008-001 or EFD1000 E5 Aircraft Flight Manual Supplement (AFMS), document 900-00038-001
regarding which appliances are installed, how the EFD1000 system operates, and is controlled,
and special procedures and limitations.
An EBB58 Emergency Backup Battery is required for EBD installations and may be required in
some EFD1000 MFD installation configurations if it is being used as any required secondary
instruments.
See the attachment to this document (part of permanent aircraft records) for detailed interface
information.
3.1 Maintaining Security Safeguards With the Aspen Connected Panel
The Aspen Connected Gateway is an appliance not required by 14 CFR Part 23 that permits bi-
directional communication of data between wireless devices and the EFD1000 MFD. Security of
the communication link to the EFD1000 MFD is important and appropriate for these instructions.
Generally, the system automatically controls the security aspects of the communication link,
however the operator has responsibility to assure adequate security when it comes to the human
interaction.
3.1.1 Physical Security
The Connected Gateway System can be linked to several wireless devices at the same time. Only
devices that are within range of the Wi-Fi signal can be linked. Therefore the devices that can be
linked while in flight are limited to the devices in the aircraft. Physical security does not require
maintenance or assurance for continued airworthiness. This is an operator consideration.
3.1.2 Operational Security
When the aircraft is in operation, only those systems used for Connected Gateway should be
linked. Keep the password confidential. The operator should assure that only authorized devices
have access to the Connected Gateway. Operational security does not require maintenance or
assurance for continued airworthiness. This is an operator consideration. The password for the
Connected Gateway Wi-Fi for a particular aircraft should be safeguarded and only supplied to
those who are trusted. If an unexpected device is connected and a flight plan is sent, the choice
is simply to reject the flight plan.

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 9-36 Revision AD
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3.1.3 Security Safeguards Monitoring
If there are attempts to violate security rules while in flight, as shown by an unexpected
candidate flight plan, reject the flight plan and turn off Aspen GTWY by the switch. Do not
operate it until the security breach is addressed.Security safeguards monitoring does not
require maintenance or assurance for continued airworthiness. This is an operator consideration.
3.1.4 Management Procedures
Measures should be established to prevent malicious introduction of unauthorized modifications
to the wireless device, including the operating system, the hosted applications and the databases
or data links. This might include maintaining a separate wireless device that is exclusively for
aircraft use and limiting the number of applications loaded to those that are known to be non-
malicious. Management procedures do not require maintenance or assurance for continued
airworthiness. This is an operator consideration.
3.1.5 Maintenance Procedures for Maintaining Security Safeguards
With the EFD1000 or EFD500 MFD and the CG100 operating, display the CG100 status by going
to the MFD Gateway page. Verify that Device: LINK STATUS CG100: is reported as LINKED. Use a
wireless enabled device to search for the SSID of the installed Gateway. By default, the SSID is
ASPENCG100. Verify that access requires a password. This also checks the functionality of the
CG100 Gateway software and hardware.
4System Operation and Procedures for System Testing During Ground
Running
Refer to the EFD1000 AFMS, document 900-00008-001 or EFD1000 E5 AFMS, document 900-
00038-001 for instructions on system operation. For System Testing refer to Section 10,
Appendix E (EA100), Appendix F (A/P Source Select), Appendix G (APS4A) and Appendix H
(CG100) of the EFD1000 and EFD500 SW v2.X Installation Manual, 900-00003-001 Rev BY or
later. For the EFD1000 E5 refer to Section 10 and Appendix E (EA100) of the EFD1000 E5 Dual
Electronic Flight Instrument (EFI) Install Manual, 900-00041-001 Rev ( ) or later.
NOTE: Appendix H of document 900-00008-001 directs the user to another supporting
document (900-000023-001, see “System Checkout”) information for the CG100. This is
because the primary document for the STC is document 900-00003-001, and information
regarding support documentation will be in this document.
To check the functionality of the CG100 Gateway software and hardware, see Section 3.1.5.

EFD1000 and EFD500 Instructions for Continued Airworthiness
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5Servicing and Scheduling Information
The EFD, RSM, ACU, ACU2, CM, EA100, APS4A, CG100, and EBB58 have no field serviceable
components. Return defective units to Aspen Avionics or an authorized dealer. No equipment is
required for servicing.
Recommended times for cleaning, inspecting, testing lubricating and adjusting each component of the
EFD1000 System. See the Periodic Maintenance and Calibration Section.
EA100
Verify the operation of the internal autopilot disconnect
relay annually (See Section 11)
Internal backup battery
Inspection every twelve months (See Section 11)
EBB58 Emergency Backup Battery
Inspection every twelve months (See Section 11)
A/P Source Select switch
Verify operation annually (See Section 11)
All other components
Refer to Section 12 for inspection requirements.
6Overhaul Period
None required.
7Commercial Parts
There are no commercial parts in the installed EFD1000/500 system.
8Special Tools
For bonding checks, use a milliohm meter such as an Extech 380460 Portable Precision Milliohm
Meter or equivalent.
It may be required to align the EA100 Adapter to the autopilot computer using a KTS-150 Test
Set, a KTS-158 Test Set, a KTS-154 Test Set or equivalent and following the autopilot
manufacturer’s procedure for aligning the gyro (KI-256) to the autopilot computer. The EA100
Alignment Tool will be used to manipulate the gyro pitch and roll signals and the autopilot Test
Set will be used to measure the autopilot demodulated gyro voltages. In the case of the KFC225
the Remote Terminal Interface will be required in place of the test sets.
9Airworthiness Limitations
There are no Airworthiness limitations associated with the installation of this appliance. The
Airworthiness Limitations Section is FAA approved and specifies maintenance required under 14
CFR § 43.16 and § 91.403 unless an alternate program has been FAA approved.
10 Distribution of Revisions
Notification of changes to this ICA will be sent to all owners on record. The changed document
will then be available in the Dealer Ramp section at www.aspenavionics.com. Paper copies are
available on request, contact Aspen Avionics at www.aspenavionics.com.

EFD1000 and EFD500 Instructions for Continued Airworthiness
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11 Periodic Maintenance and Calibration and Storage Limitations
All maintenance is considered “ON CONDITION” unless otherwise noted in this ICA. The EFD
Internal battery and the Emergency Backup Battery must be replaced in the interval identified
below. There are no other storage limitations.
EBB58 Emergency Backup Battery (use with EFD P/N 910-00001-002, -012, -007, and -017)
The EBB58 Emergency Backup Battery when installed must be visually inspected and tested as
described below once every 12 months and biannually (every 6 months) after 3 years (from date
of installation) to ensure it meets the minimum 30-minute requirement for powering the
EFD1000 MFD and EBD under all foreseeable conditions. The EBB58 must be replaced every 4
years (from the date of installation) or 2200 flight hours (from the time of installation) (whichever
occurs first), or if it fails the following visual or operational tests.
Remove the EBB from the tray and visually inspect for the following:
Leakage from the battery especially around the metal seams
Evidence of water contamination
Evidence of corrosion
If any of the above issues are noted return the EBB58 to Aspen Avionics for repair.
Re-install the battery and check the battery capacity as follows: (this test must be run at room
temperature approximately 25º C)
Turn on the EFD1000 MFD or EBD
Press MENU Key
Select POWER SETTINGS, Main Menu page
Press the BATTERY line select key
BAT LEVEL IN --.-- will be displayed for a short period of time as battery capacity is being
measured. This could take up to 10 minutes if the ambient temperature is below 0º C.
Once the capacity is measured ON BAT XX% REM will be displayed.
The “ON BAT” indication must read a minimum of 80% to continue. If the battery capacity is
below 80% then the battery should be charged by returning the MFD or EBD to aircraft power.
The EBB will charge as long as the display is turned on and aircraft power is supplied.
With the battery displaying greater than 80% charge set a timer for one (1) hour. After the one
hour time has elapsed the MFD or EBD must still be operating on battery. If the EBB will not

EFD1000 and EFD500 Instructions for Continued Airworthiness
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supply the minimum 1 hour operating time or fails to charge above 80% return the battery to
Aspen Avionics for repair.
Instructions for battery replacement are contained in Section 12.
Following the battery endurance test and while operating on battery power, switch the “EBB EMER
DISC” switch to “DISC”; verify the display powers OFF. Return the “EBB EMER DISC” switch to
“NORM”; verify the display powers ON and is on battery power.
Switch the MFD or EBD back to aircraft power and recharge the EBB to 80% or greater prior to
release to service.
EFD Internal Battery (EFD P/N 910-00001-001, -003, -004, -011, -013 and 900-00101-001)
The internal back-up battery in the EFD must be tested once every 12 months and biannually
(every 6 months) after 3 years (from date of installation) to ensure it operates properly. Each EFD
with an internal battery must have the battery replaced every 4 years or 2200 hours, or if it fails
the following operational test.
This test must be run at room temperature approximately 25º C.
Turn on the EFD1000 or EFD500
Press MENU Key
Select POWER SETTINGS page from the Main Menu
Press the BATTERY line select key
BAT LEVEL IN --.-- will be displayed for a short period of time as battery capacity is being
measured. This could take up to 10 minutes if the ambient temperature is below 0º C.
Once the capacity is measured ON BAT XX% REM will be displayed.
The “ON BAT” indication must read a minimum of 80% to continue. If the battery capacity is
below 80% then the battery should be charged by returning the EFD to aircraft power. The
battery will charge as long as the MFD is turned on and aircraft power is supplied.
With the battery displaying greater than 80% charge set a timer for 30 minutes (40 minutes for
the E5). After the 30 minute (40 min for E5) time has elapsed the EFD must still be operating on
battery. If the internal battery will not supply the minimum 30 minutes (40 min for E5) operating
time or fails to charge above 80%, replace the battery and return the failed battery to Aspen
Avionics.
Instructions for battery replacement are contained in Section 14.

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Switch the EFD back to aircraft power and recharge the internal battery to 80% or greater prior to
release to service.
Instructions for battery replacement are contained in Section 14. Contact customer service at
Aspen Avionics or an authorized Aspen Avionics Dealer for a replacement battery.
EA100 Autopilot Disconnect (if the EA100 is installed)
The ability of an EA100 to disconnect the autopilot must be tested annually. The test is
accomplished in the following manner:
Turn on the PFD, or EBD, or E5 and all MFD systems. Verify the “A/P AHRS FAIL” light
extinguishes. Engage the autopilot and then pull the “A/P AHRS” circuit breaker. If the autopilot
disengages immediately and the A/P AHRS light simultaneously illuminates, then the test was
successful. Restore the circuit breaker. If the autopilot fails to disengage then arrange for
repair of the EA100 or associated wiring.
A/P Source Select (if installed)
The switch must be tested annually. The test is accomplished in the following manner:
Turn on the PFD and all MFD systems. Engage the autopilot and verify the PFD heading bug will
steer the HDG mode of the autopilot. Disconnect the autopilot. Press the MFD “REV” button and
then momentarily push the A/P Source Select switch to the MFD REV position. Engage the
autopilot and verify the reverted MFD heading bug will steer the HDG mode of the autopilot.
EFD Display Backlight
The EFD display backlight has a median expected life of 50,000 operating hours. Replacement of
the lamp is on-condition as it may last longer or shorter than 50,000 hours. It is up to the
operator to determine whether the backlighting has become too dim for its intended use.
ACU, ACU2, RSM, APS4A, CM, CG100
The ACU, ACU2, RSM, APS4A, CG100 and the Configuration Module require no periodic
maintenance or calibration.
11.1 Inspection Checklist
FAR 43.15, Additional performance rules for inspections, Para. (c)(1) Annual and 100-hour
inspections, requires "Each person performing an annual or 100-hour inspection shall use a
checklist while performing the inspection." Depending on the options and thus the associated
complexity, it may be advantageous to prepare a checklist to be used when performing an
Annual or 100-hour inspection. For all installations, the information will be found in Sections 11
and 12 of this document. Those items marked “If Installed” means that the inspection should
only be conducted if the equipment is installed in the aircraft. Refer to the EFD1000 Aircraft
Flight Manual Supplement, document 900-00008-001 or EFD1000 E5 Aircraft Flight manual
Supplement, document 900-00038-001 for this aircraft to determine the equipment installed.

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Section 11 Checklist
1. Check the EBB58 battery (if installed) in accordance with Section 11 of this document.
2. Check the EFD internal battery in accordance with Section 11 of this document. Note that
each EFD has a battery, unless the EFD1000 MFD or EBD which have an EBB58 battery.
3. Check the EA100 Autopilot disconnect switch (if installed) in accordance with Section 11 of
this document.
4. Check the A/P Source Select switch (if installed) in accordance with Section 11 of this
document.
5. Verify Security Safeguards in accordance with Section 3.1.5 of this document.
12 Unit and Wiring Inspection
All units, brackets, installation hardware and wiring of the EFD1000 system should be checked as
defined below during annual inspection. Items found to be defective should be repaired or
replaced prior to returning the aircraft to service. The performance of this inspection should not
create the need for additional protective treatment (Alodine, paint, etc) of surfaces within the
aircraft.
EFD Inspection
The EFD(s) should be inspected for damage and their operation should be verified using
documents identified in Section 1 of these ICA’s. The EFD wiring, pneumatic tubing, and quick
disconnects should be checked for integrity, damage, chafing, or excessive wear. The EFD
braided bonding strap should be checked for proper termination at the EFD and aircraft
grounding point to maintain HIRF and Lightning compliance.
Verify ≤ 3 milliohms from EFD ground stud to airframe ground. The installation of the EFD
should be inspected for corrosion on the EFD and the structure it is mounted on. The fasteners
should be inspected for tightness and general condition.
ACU/ACU2 Inspection –if installed
The ACU should be inspected for damage and its operation should be verified using documents
identified in Section 1 of these ICA’s. ACU wiring should be checked for damage, chafing, or
excessive wear. Verify ACU chassis bonding from the face of the unit (connector side) to
airframe ground is ≤ 3 milliohms to maintain HIRF and Lightning compliance. The installation of
the ACU should be inspected for corrosion on the ACU and the structure it is mounted on. The
fasteners should be inspected for tightness and general condition.
RSM Inspection
The RSM(s) should be visually inspected for damage and wear on the lightning strip. RSM wiring
should be checked for damage, chafing, or excessive wear. Verify RSM doubler plate bonding
from the ground stud to airframe ground is ≤ 3 milliohms to maintain HIRF and Lightning
compliance. The RSM installation and doubler should be inspected for corrosion on the RSM, the

EFD1000 and EFD500 Instructions for Continued Airworthiness
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© Copyright 2019 Aspen Avionics Inc.
RSM shim (optional), the fuselage skin, and the doubler. The installation should be inspected for
cracks in the fuselage, and loose or damaged fasteners.
Configuration Module Inspection
The Configuration Module(s) should be checked for damage. The Configuration Module wiring
should be checked for damage, chafing, or excessive wear.
EA100 Inspection –if installed
The EA100 should be inspected for damage and its operation should be verified using documents
identified in Section 1 of this document. The EA100 wiring should be checked for damage,
chafing, or excessive wear. Verify EA100 chassis bonding from the face of the unit (connector
side) to airframe ground is ≤ 3 milliohms to maintain HIRF and Lightning compliance. The
installation should be inspected for corrosion on the EA100 and the structure it is mounted
on. The fasteners should be inspected for tightness and general condition.
EBB58 Inspection –if installed
The EBB58 Emergency Backup Battery should be inspected for damage to the battery and
mounting tray. Battery operation should be verified using Section 9 of this ICA. Verify ≤ 3
milliohms from mounting tray to airframe ground. The wiring should be checked for damage,
chafing, or excessive wear.
APS4A Inspection–if installed
The APS4A should be inspected for damage and its operation should be verified using documents
identified in Section 4 of this document. The APS4A wiring should be checked for damage,
chafing, or excessive wear. Verify APS4A chassis bonding from one of the cover retaining cap
screws to airframe ground is ≤ 3 milliohms to maintain HIRF and Lightning compliance. The
installation should be inspected for corrosion on the APS4A and the structure it is mounted
on. The fasteners should be inspected for tightness and general condition.
CG100 Inspection–if installed
The CG100 should be inspected for damage and its operation should be verified using
documents identified in Section 4 of this document. The CG100 wiring should be checked for
damage, chafing, or excessive wear. Verify CG100 chassis bonding from face of the unit
(connector side) to airframe ground is ≤ 3 milliohms to maintain HIRF and Lightning compliance.
The installation should be inspected for corrosion on the CG100 and the structure it is mounted
on. The fasteners should be inspected for tightness and general condition.
12.1 Inspection Checklist
FAR 43.15, additional performance rules for inspections, Para. (c)(1) Annual and 100-hour
inspections, requires "Each person performing an annual or 100-hour inspection shall use a
checklist while performing the inspection." Depending on the options and thus the associated
complexity, it may be advantageous to prepare a checklist to be used when performing an
Annual or 100-hour inspection. For all installations, the information will be found in Sections 11
and 12 of this document. Those items marked “If Installed” means that the inspection should

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 16-36 Revision AD
© Copyright 2019 Aspen Avionics Inc.
only be conducted if the equipment is installed in the aircraft. Refer to the EFD1000 Aircraft
Flight Manual Supplement, document 900-00008-001 for this aircraft to determine the
equipment installed.
Section 12 Checklist
1. Inspect the EFD(s) for damage and their operation in accordance with Section 12 of this
document.
2. Inspect the ACU or ACU2 (if installed) for damage and its operation in accordance with
Section 12 of this document.
3. Inspect the RSMs for damage and wear in accordance with Section 12 of this document.
4. Inspect the Configuration Module(s) for damage in accordance with Section 12 of this
document.
5. Inspect the EA100 (if installed) for damage and its operation in accordance with Section 12 of
this document.
6. Inspect the EBB58 (if installed) for damage in accordance with Section 12 of this document.
7. Inspect the APS4A (if installed) for damage and its operation in accordance with Section 12 of
this document.
8. Inspect the CG100 (if installed) for damage and its operation in accordance with Section 12 of
this document.

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 17-36 Revision AD
© Copyright 2019 Aspen Avionics Inc.
13 Troubleshooting
NOTE:
For more information about recognizing malfunctions, see the checkout procedure Sections 10 and
11 in the EFD1000 and EFD500 SW v2.X Installation Manual, 900-00003-001 Rev BY or later or
EFD1000 E5 Dual Electronic Flight Instrument (EFI) Install Manual, 900-00041-001 Rev ( ) or later.
EFD1000 Startup Page Faults (SW v2.0 and above)
Malfunction & How
to Recognize the
Malfunction
Cause
Remedy
IOP initialization
failure
a) Fail
b) System reboots after IOP test
a) Replace EFD
b) Replace EFD
ARINC initialization
failure
a) Fail
a) Replace EFD
RS232 initialization
failure
a) Fail
a) Replace EFD
Config Module
initialization failure
a) Fail
b) Wrong CM version
c) System reboots after Config
Module Test
d) displays “Initializing” for more
than 20 seconds
a) Check Config Module wiring. Replace
Config Module.
b) Install correct SW version CM.
c) v2.0 or v2.1 display installed with a
v2.2 CM. Install correct CM or EFD.
d) Config Module unplugged or mis-
wired.
RSM initialization
failure
a) Fail (x)
a) Check RSM to PFD wiring for shorts or
opens. Repair or replace RSM. Repair or
replace PFD.
IMU initialization
failure
a) Fail
a) Replace EFD
ADC initialization
failure
a) Fail
a) Replace EFD
ADAHRS initialization
failure
a) Fail
b) “Initializing” for more than 3
minutes
c) “Initializing” for more than 3
minutes with a RSM Fail above.
a) Replace EFD
b) Remove Pitot and Static line from
back of EFD and reboot. If problem
still exists then replace the EFD. If
problem clears then repair Pitot or
Static obstruction/kink.
c) Repair RSM wiring or replace RSM.

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 18-36 Revision AD
© Copyright 2019 Aspen Avionics Inc.
EFD1000 General Faults (SW v2.0 and above)
Malfunction & How to
Recognize the Malfunction
Cause
Remedy
Display does not power on
(Note: there can be up to a
20 second delay from the
application of power to a
visible display)
a) EFD missing A/C power
b) EFD may have been
improperly shut down
c) EFD missing A/C ground
d) EFD is defective
a) Check EFD circuit breaker, EFD on/off
switch on panel, wiring, and A/C
battery voltage > 11.5 volts.
b) Switch unit off using “REV” button or
“SHUT DOWN” command from Main
Menu page 6.
c) Check wiring to EFD
d) Repair or replace EFD
Display does not power off
(Note: EFD will switch to
battery if airspeed is
greater than 30kts.)
a) Airspeed is above 30kts
b) EFD may have been
switched to internal
battery
c) EFD may have been
improperly shut down
d) EFD is defective
a) Normal operation
b) Switch unit off using “REV” button or
“SHUT DOWN” command from Main
Menu page 6.
c) Hold “REV” button for 20 seconds or
unplug EFD internal battery for 3
seconds
d) Repair or replace EFD
Display flashes on/off,
black/white or blue/white
repetitively
a) Configuration Module
unplugged or miswired
b) RSM or CM wiring short
c) Configuration module
defective
d) EFD defective
a) Check CM plug and wiring from EFD
to CM
b) Verify RSM pin 6 or CM pin 1 is not
shorted to aircraft ground or another
pin.
c) Repair or replace CM
d) Repair or replace EFD
“CONFIG MODULE LINK
FAIL” message (SW v1.X)
a) Configuration Module
unplugged or mis-wired
b) Configuration module
defective
c) PFD defective
a) Check CM plug and wiring from PFD
to CM
b) Repair or replace CM
c) Repair or replace PFD
“INITIALIZING” message for
more than 60 seconds
(SW v1.X)
a) RSM to PFD
communication lost
b) RSM failed
c) PFD failed
a) Check RSM to PFD wiring for shorts or
opens.
b) Repair or replace RSM
c) Repair or replace PFD
“RSM LINK FAIL” message
(SW v1.X)
a) RSM to PFD
communication lost
b) RSM failed
c) PFD failed
a) Check RSM to PFD wiring for shorts or
opens.
b) Repair or replace RSM
c) Repair or replace PFD
“WRONG CONFIG MODULE”
message (SW v1.X)
a) PFD is at one software
level and config module is
at a different software level
a) Convert config module per
appropriate service bulletin.

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DOCUMENT # 900-00012-001 PAGE 19-36 Revision AD
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Malfunction & How to
Recognize the Malfunction
Cause
Remedy
ALTIMETER, AIRSPEED, VSI
FAIL (RED-X)
a) Air data sensor has not
had sufficient warm-up
time.
b) Pitot/static lines reversed
c) Air data sensor failed
a) Allow up to 20 minutes at temps
below -20ºC for flags to clear
b) Connect pitot line to “P” port and
static line to “S” port on EFD
c) Repair or replace EFD
ATTITUDE FAIL or
DIRECTION FAIL ( RED-X)
(Note: Attitude flags could
take up to 3 minutes to
clear at temps below -20
ºC)
a) AHRS sensor has not
completed initialization.
b) RSM failed/data missing.
c) Pitot and/or Static lines
crossed, unplugged, or
blocked.
d) EFD is defective
a) Allow up to 3 minutes for AHRS to
initialize.
b) Check RSM to EFD wiring. Repair or
replace RSM.
c) Correct pitot/static plumbing issue.
d) Repair or replace EFD.
ATTITUDE FAIL and
DIRECTION FAIL associated
with “CHECK PITOT HEAT”
message
a) In Flight, Normal if pitot
blockage due to ice or
other.
b) On Ground, Normal if
GPS reception is marginal
and GPS GS ramps above
50Kts intermittently.
a) Use pitot heat or check pitot system
for blockage.
b) No further action required unless
message is due to faulty GPS system,
then repair GPS system.
DEGRADED MODE (sw 2.10
and later) –GPS
groundspeed is above
50kts and airspeed is below
30kts
a) In Flight, Normal if pitot
blockage due to ice or
other.
a) Use pitot heat or check pitot system
for blockage.
b) On Ground, Normal if
GPS reception is marginal
and GPS GS ramps above
50Kts intermittently.
b) No further action required unless
message is due to faulty GPS system,
then repair GPS system.
CROSS CHECK ATTITUDE
message (yellow)
(also see sluggish AHRS
performance
troubleshooting)
a) If it occurred on system
start.
b) Normal after abrupt
maneuvers on ground or
in air
a) RESET AHRS
b) RESET AHRS

EFD1000 and EFD500 Instructions for Continued Airworthiness
DOCUMENT # 900-00012-001 PAGE 20-36 Revision AD
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Malfunction & How to
Recognize the Malfunction
Cause
Remedy
Red Slash through
Navigation Sensor (i.e.,
GPS1, NAV2)
a) GPS or VLOC receiver
turned off.
b) GPS does not have a valid
“TO” waypoint and
position
c) GPS or VLOC receiver
failed
d) ACU not powered
e) Wiring fault between
sensor and ACU or EFD
f) ACU to EFD wiring fault.
g) ACU is defective.
h) EFD is defective.
a) Turn on GPS or VLOC receiver
b) Allow GPS to acquire a position and
enter a flight plan or Direct To
c) See GPS/VLOC manufacturer’s
instructions for troubleshooting
d) Check ACU circuit breaker
e) Check wiring between GPS/VLOC and
ACU or EFD
f) Check ACU circuit breaker, check ACU
to EFD A429 wiring and ACU to sensor
wiring
g) Repair or replace ACU
h) Repair or replace EFD
GPS1 or GPS2 selection not
available on Display
(GNS430/GNS530/GNS480
only)
a) GPS receiver turned off
b) GPS does not have a valid
“TO” waypoint and
position
c) GNS CDI is selected to
VLOC.
d) GPS to EFD A429 wiring
issue.
e) GPS defective.
f) EFD defective.
a) Turn on GPS and initialize
b) Allow GPS to acquire a position and
enter a flight plan or Direct To
c) Verify the GNS CDI is selected to GPS.
d) Check A429 wiring for shorts, opens
or crossed A and B lines.
e) Repair or replace GPS
f) Repair or replace EFD
Autopilot or analog
NAV/GPS inoperative
a) ACU chassis not
grounded
b) ACU not powered
c) ACU to sensor wiring
d) ACU to EFD wiring
e) ACU fault
f) EFD fault
a) Ground ACU chassis to airframe
ground
b) Check ACU circuit breaker and
power/grounds
c) Check ACU to sensor wiring
d) Check ACU to EFD A429 wiring
e) Repair or replace ACU
f) Repair or replace EFD