Page 1 EFD1000 Installation Manual EFD1000 Installation Manual Includes Instructions for Continued Airworthiness Aspen Document #A-01-126-00 Revision H DOCUMENT # A-01-126-00 PAGE 1-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 2 EFD1000 Installation Manual Special Notes to the Installer It is important to review the entire Installation Manual before installing the EFD1000. The following items are of special note and should be considered for planning and installation. The integral EFD1000 ADAHRS uses air data and magnetic inputs as cross checks for the aircraft attitude solution.
Page 4 23.1309-1C) listed on the EFD1000 AML. Installation of the EFD1000 into US-registered 14CFR Part 23 Class I or II aircraft not included in the EFD1000 AML, Part 23 class III or IV aircraft, any part 25, 27, or 29 aircraft, or non-U.S. registered aircraft requires separate airworthiness approval.
Page 5: Table Of Contents
SYSTEM DESCRIPTION......................21 (PFD)..................21 RIMARY LIGHT ISPLAY (RSM) .................. 22 EMOTE ENSOR ODULE ................... 23 ONFIGURATION ODULE (ACU) ................. 23 NALOG ONVERTER ....................24 YSTEM RCHITECTURE DOCUMENT # A-01-126-00 PAGE 5-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 6 5.2.4 Back Up Nav Indicator ................36 5.2.5 GPS Annunciators..................37 5.2.6 Aircraft Power Requirements ..............37 5.2.7 EFD1000 Power Requirements ..............37 5.2.8 Special Considerations for Aircraft Limited to VFR ........38 “ ” A ..........38 ONVENTIONAL ANDING...
Page 7 Decision Height (DH) Input – PFD software version 1.1 or later....76 8.2.3 VLOC Receiver................... 77 8.2.4 GPS Receiver ..................... 77 8.2.5 Autopilot ....................79 8.2.6 ARINC 429 GPS Output ................82 PFD P ......................83 DOCUMENT # A-01-126-00 PAGE 7-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 8 ..................162 ASIC LIGHT HECKS 11.2 HSI/DG F .................. 162 ASIC LIGHT HECKS 11.3 ILS F 11.4)......163 LIGHT HECKS IF NO AUTOPILOT OTHERWISE JUMP TO ECTION DOCUMENT # A-01-126-00 PAGE 8-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 9 APPENDIX B........................207 ................208 NSTALLATION INAL HECK HEET APPENDIX C ........................213 ................. 214 PERATOR ONFIGURATION HECKLIST APPENDIX D ........................215 .............. 215 NSTRUCTIONS ONTINUED IRWORTHINESS DOCUMENT # A-01-126-00 PAGE 9-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 11: Introduction
This Installation Manual is FAA Approved and contains detailed installation instructions for installing the EFD1000 System into specific aircraft as listed in the EFD1000 AML-STC. There are required FARs that must be complied with and followed to insure an airworthy installation. Section 5 Pre Modification Planning will guide you through these requirements.
Page 12: Installation Kit Contents
DB15 pin EMI Back shell NorComp 970-015-030R121 A-06-409-00 DB25 EMI Back shell NorComp 970-025-030R121 A-06-410-00 DB37 EMI Back shell NorComp 970-037-030R121 A-06-574-00 Crimp Sockets (77) Positronics P/N FC6020D DOCUMENT # A-01-126-00 PAGE 12-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 13: Accessories Required But Not Supplied
A-06-566-00 conn. equivalent 1.5 Special Tools Required D-SUB connectors: Hand Crimp Tool: Positronics P/N 9507-0-0-0 or equivalent Insertion/Extraction Tools: Positronics P/N M81969/1-02 or equivalent DOCUMENT # A-01-126-00 PAGE 13-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 14: Vendor Information
Registration of LRU part numbers and serial numbers must be recorded on the dealer portal of the Aspen Avionics website at www.aspenavionics.com/dealerramp. Activating the warranty on the EFD1000 system is just one important aspect of providing a satisfying installation experience for our customers.
Page 15: Equipment Specifications And Limitations
Pitot / Static ......Quick Connect 2.1.4 Certification Specifications: Technical Standard Order: TSO-C2d ........Airspeed Instruments TSO-C3d ........Turn and Slip Instrument TSO-C4c ........Bank and Pitch Instruments DOCUMENT # A-01-126-00 PAGE 15-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 16: Design Eye Viewing Envelope
The following information defines the viewing envelope within which the EFD1000 complies with the Equipment standards: Minimum and maximum distance from the center of the EFD1000 display surface: 10 inches (25.4 cm) minimum to 45 inches (114.3 cm) maximum Total viewing angles: From -30º...
Page 17: Outline Drawing
0.2 lbs 2.2.2 Operational Specifications: Operating Temp ....... -55°C to +70°C Storage Temp ......-55°C to +85°C Max Operating Altitude....55,000 ft Unpressurized Cooling ........None Required DOCUMENT # A-01-126-00 PAGE 17-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 18: I/O Specifications
OAT........... Proprietary Digital GPS ........... Proprietary Digital 2.2.4 Certification Specifications: The RSM is certified as a component of the EFD1000 system Environmental: RTCA DO-160E......See Environmental Qualification Form Section 13 2.2.5 Outline Drawing: Figure 2.2 - RSM Outline Drawing (inches)
Page 19: Analog Converter Unit (Acu)
1 Active low input Flight Director ......1 output port Autopilot Interface..... 1 Analog port 2.3.4 Certification Specifications: The ACU is certified as a component of the EFD1000 system Environmental: RTCA DO-160E......See Environmental Qualification Form Section 13 DOCUMENT # A-01-126-00 PAGE 19-225 Revision H ©...
Page 20: Outline Drawing
EFD1000 Installation Manual 2.3.5 Outline Drawing: 1.60 Figure 2.3 - ACU Outline Drawing (inches) DOCUMENT # A-01-126-00 PAGE 20-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 21: System Description
EFD1000 Installation Manual 3 System Description The EFD1000 system is comprised of the Primary Flight Display (PFD), Remote Sensor Module (RSM), Configuration Module (CM) and optional Analog Converter Unit (ACU). The flight deck display is designed specifically for general aviation aircraft.
Page 22: Remote Sensor Module (Rsm)
The RSM is powered by the PFD through a shielded wire harness and contains the following sub-systems: Outside Air Temperature (OAT) sensor • Emergency backup GPS engine • Heading “flux” sensors • DOCUMENT # A-01-126-00 PAGE 22-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 23: Configuration Module
If digital radios (i.e., Garmin 4XX/5XX series radios) are equipped in the aircraft and no other aircraft interfaces (such as an advanced autopilot) are to be used, then the “Pro Digital” configuration module can be used and the ACU is not required. DOCUMENT # A-01-126-00 PAGE 23-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 24: System Architecture
EFD1000 Installation Manual 3.5 System Architecture The system architecture in Figure 3.2 shows the relationships of the PFD, RSM, Configuration Module and ACU. Figure 3.2 - EFD1000 System Architecture DOCUMENT # A-01-126-00 PAGE 24-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 25: Supported Installed Configurations
VLOC or GPS navigation deviation, only the GPS flight plan and position is received and displayed. The Pilot model does not support the ACU and therefore autopilot interfaces are not available. Figure 4.1 - Pilot Configurations DOCUMENT # A-01-126-00 PAGE 25-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 26: Pro Digital Configuration
L/R output is switched to the autopilot. These installations will be wired as shown in Figure 4.3 minus the heading and course datum, flag, ILS Energize, and glide slope signals. Figure 4.2 – Pro Digital Configurations DOCUMENT # A-01-126-00 PAGE 26-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 27: Pro Configurations With Autopilot
CDI display on the GPS receiver or VLOC receiver. There must be one navigation indicator available to the pilot in the event of a PFD or ACU failure. Figure 4.3 – Pro Configurations with Autopilot DOCUMENT # A-01-126-00 PAGE 27-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 28: Pro Configuration With Autopilot And Digital/Analog Vloc
VLOC receiver. There must be one navigation indicator available to the pilot in the event of a PFD or ACU failure. Figure 4.4 - Pro Configuration with AP and VLOC DOCUMENT # A-01-126-00 PAGE 28-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 29: Pro Configuration With Autopilot And Dual Analog Vloc
There must be one navigation indicator available to the pilot in the event of a PFD or ACU failure. Figure 4.5 - Pro Configuration with AP and Dual VLOC DOCUMENT # A-01-126-00 PAGE 29-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 31: Pre Modification Planning
Complete Table 5.1 to insure that the aircraft to be modified is a candidate for installation of the EFD1000 system using this AML-STC. It is required to have a PASS or NA for all rows in order to use this AML-STC as the certification basis for the EFD1000 installation. NA means Not Applicable because no interface will be made to that device.
Page 32: Requirements And Limitations
Electric Standby Instruments Aircraft that are all electric must keep the EFD1000 PFD on an independent power source from the standby instruments as determined from the flow chart of Figure 5.1. The installer must verify that the standby instruments are electrically isolated from the PFD through either of the...
Page 33 The installation of dual independent electrical systems or a standby (emergency) battery is not authorized by this STC. Separate installation approval would be required. Figure 5.1 – Standby Instrument Power Requirements DOCUMENT # A-01-126-00 PAGE 33-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 34: Standby Attitude Positioning
If used as the autopilot mode controller then it must be located where it can be easily reached by the pilot while seated. DOCUMENT # A-01-126-00 PAGE 34-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 35: Standby Airspeed And Alt Meter Position Ng
Figure 5.3 – Basic T configuration 5.2.3 Directional Gyro/ HSI The EFD1000 Flight Display will replace the existing Directional Gyro or HSI in the panel. Provided the existing compass system is not driving a heading input to another device in the aircraft, it may be removed from the aircraft at the operator’s discretion.
Page 36: Back Up Nav Indicator
This will ensure that a failure of the EFD1000 system does not result in a complete loss of all navigation data to the flight crew. A backup navigation indicator is not required for an EFD1000 installation in aircraft limited to VFR.
Page 37: Gps Annunciators
EFD1000 Installation Manual 5.2.5 GPS Annunciators The EFD1000 is capable of displaying GPS annunciations on the HSI portion of the display from those ARINC 429 connected GPS receivers that output these labels. If using the PFD display for any required GPS annunciations verify that the GPS receiver outputs these messages on the ARINC 429 bus.
Page 38: Special Considerations For Aircraft Limited To Vfr
The following requirements must be met in order to install the EFD1000 without a backup attitude indicator in U.S. registered Part 23 aircraft limited to VFR: The aircraft should have a placard or equivalent acceptable means, stating “Operation of This Aircraft is Limited to VFR Only”, or similar phraseology acceptable to the...
Page 39: Part 135 Ifr Operations
5.6 Optional Interfaces 5.6.1 Autopilot The EFD1000 Pro with ACU emulates a KI-525A or NSD-360A HSI by providing HDG Datum, CRS Datum, and navigation L/R outputs to a connected autopilot. Any autopilot compatible with the KI-525A or NSD-360A HSI is compatible with the EFD1000 System.
Page 40: Gps Navigator Basemap Compatibility
ARINC 429 ARINC 429 This connection method presents curved GPS155 approaches. GPS155XL GPS300XL GPS165 GNC300 Garmin GNS-400 ARINC 429 ARINC 429 This connection method presents curved Series approaches. DOCUMENT # A-01-126-00 PAGE 40-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 41 TNL-3000 Table 5.2 – GPS Navigator Basemap Compatibility Other GPS navigators have not been evaluated and may be compatible. Contact Aspen Avionics for information regarding additional navigators. DOCUMENT # A-01-126-00 PAGE 41-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 42: Gpss
GPSS through the EFD1000 is only available if Label 121 is transmitted by the GPS over the ARINC 429 bus. RS-232 interfaces do not provide label 121;...
Page 43: Second Acu
NOTE: The Bendix/King KTA810/910 and KMH820/920 only accept High Speed A429 heading and therefore are not compatible with this output. Contact Aspen Avionics product support for suggestions on using an ARINC 429 low to high speed converter. 5.6.7 Second ACU A second ACU is required when two (2) analog VLOC receivers are installed.
Page 45: Mechanical Installation
Inspect the equipment for evidence of shipping damage. If a damage claim is to be filed save all shipping boxes and packing material to substantiate your claim. To avoid damage to the equipment, do not place the EFD1000 Display face down on the knobs CAUTION: The battery is normally disconnected for shipping and must be reconnected.
Page 46: Installation Limitations
STC. Separate FAA approval of pressure vessel penetrations required to accommodate RSM mounting is required prior to the installation of the remaining EFD1000 system components under the EFD1000 AML-STC. Mounting the RSM to a composite or fabric skinned aircraft is beyond the scope of this •...
Page 47: Pfd Installation
PFD and panel, and installing pitot and static connections to the two keyed quick release pressure fittings. NOTE: To avoid damage to the equipment, do not place the EFD1000 Display face down on the knobs 6.8.1 Connecting the Internal Battery The internal battery is normally disconnected for shipping and must be reconnected prior to the Post Installation Flight Check and maintenance release of the aircraft.
Page 48: Mounting Bracket Installation
Verify less than 3 milliohms resistance to airframe ground at bonding strap connection point. DOCUMENT # A-01-126-00 PAGE 48-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 49 EFD1000 Installation Manual Bonding Strap Attachment Screw Rear View of PFD Figure 6.2 – PFD Bonding Strap Connection Figure 6.3 – PFD and Bracket Installation DOCUMENT # A-01-126-00 PAGE 49-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 51: Pitot And Static Connections
5) Secure pitot and static lines as necessary to prevent interference with other aircraft structures and components. CAUTION: Secure pitot and static lines so that they will not interfere with flight controls and are not at risk of mechanical damage. DOCUMENT # A-01-126-00 PAGE 51-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 52: Leak Check Requirements
The NO ZONE areas below are hot zones for a lightning strike and are not to be used for mounting the RSM. The RSM must not be mounted to the wing, the top of the vertical DOCUMENT # A-01-126-00 PAGE 52-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 53: Proposed Rsm Location Check
Steel-wound hose (e.g. SCAT d. Servos tube) e. Trim motors b. Steel hose clamps Poor bonding of electrical c. Magnetized or magnetic connections hardware g. Blower motors DOCUMENT # A-01-126-00 PAGE 53-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 54: Pressur Zed Aircraft
Contact Aspen Avionics product support for information on obtaining or using a handheld degaussing coil. A degaussing coil can be purchased at most audio and video stores.
Page 55: Rsm Mounting On Composite Or Fabric
Approval for the structural aspects of mounting the RSM to a composite or fabric skinned aircraft, including consideration for the direct effects of lightning, is beyond the scope of the EFD1000 AML STC. Separate FAA approval for structural and lightning direct effects considerations is required before mounting the RSM on these aircraft types.
Page 56 Maximum fore and aft tilt is in relation to the aircraft waterline. An aluminum shim might be required to keep orientation within limits (see Section 6.9.9 for shim fabrication). Figure 6.9 – RSM Fore or Aft Max Tilt DOCUMENT # A-01-126-00 PAGE 56-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 57: Rsm Doubler
The doubler is to be fabricated by the installer using the dimensions and rivet holes as shown. Should the installer wish to deviate from this doubler in size, rivet count, rivet spacing, or doubler thickness, they are required to seek separate approval. DOCUMENT # A-01-126-00 PAGE 57-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 58: Rsm Doubler Fabrication
1/2" on the down side of the doubler (see Figure 6.12). Prime that side with epoxy primer per MIL-P-23377 or equivalent. Do not prime the side that faces the aircraft DOCUMENT # A-01-126-00 PAGE 58-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 59 11) Mount a ground stud to the doubler for attachment of the RSM shield wire. Use an MS24693-C52 #8-32 flathead screw and AN364-832A locknut or equivalent as shown. Countersink Aircraft Skin Doubler Figure 6.13– Ground Stud Mounting DOCUMENT # A-01-126-00 PAGE 59-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 60 For aircraft skins 0.063 or thicker install with NAS1097AD5 rivets flush in the • fuselage skin. 13) Verify that the ground stud has less than 3 milliohms to ground. Figure 6.14 – Rivet Installation DOCUMENT # A-01-126-00 PAGE 60-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 61: Rsm Nstallation
AHRS attitude solution. Use only the specified hardware to mount the RSM. Aircraft Skin Doubler (installer fabricated) Figure 6.15 – RSM Mounting DOCUMENT # A-01-126-00 PAGE 61-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 62: Rsm Shim Fabrication (If Necessary)
2) Fabricate shim from 2024-T3 aluminum with the four (4) mounting holes and 0.625” cable pass-thru drilled through. 3) Remove burrs and break sharp edges (0.005” – 0.015”) 4) Finish with Alumiprep Etch and Alodine Conversion Coating, or equivalent. DOCUMENT # A-01-126-00 PAGE 62-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 63 7) Sandwich the shim between the aircraft skin and the RSM following the RSM installation procedure in Section 6.9.7. 8) Apply non corrosive sealant around shim and RSM. DOCUMENT # A-01-126-00 PAGE 63-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 64: Acu Installation
Mount ACU to existing shelf in any orientation using six (6) MS3506-X #6-32 screws, six (6) NAS1149FN632P washers, and six (6) MS21044N06 #6-32 self locking nuts or equivalent. Tighten nuts to 12 in-lbs. DOCUMENT # A-01-126-00 PAGE 64-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 65 Should a shelf or bracket need to be fabricated in order to install the ACU it is beyond the scope of this STC and will require separate FAA approval for that modification. Figure 6.18 – ACU Dimensions (inches) DOCUMENT # A-01-126-00 PAGE 65-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 66: Configuration Module Installation
PFD harness is manipulated during installation and subsequent removal/replacement. Figure 6.19 – Configuration Module Dimensions (inches) Cable Tie two (2) places Figure 6.20 – Configuration Module Tie Wrapped to Harness DOCUMENT # A-01-126-00 PAGE 66-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 67: Electrical Installation
Wires and wiring bundles must be secured in such a way to eliminate risk of mechanical damage and minimize exposure to heat and fluids per FAR 23.1365(e). DOCUMENT # A-01-126-00 PAGE 67-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 68: Hirf/Lightning Requirements
Wire as shown on Wiring Diagrams in MS27500-22TG2V64 2 conductor cable or equivalent Section 9. are required on the following inputs and outputs. Figure 7.1 – Over Braid/ Double Shield Requirements DOCUMENT # A-01-126-00 PAGE 68-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 69: Pfd To Gps/Vloc/Acu Wiring
If this is the case then use a piece of tinned copper over braid that extends at least 6 inches outside the back shell to cover all unshielded wires(see Figure 7.2). Figure 7.2 – PFD Back Shell Grounds DOCUMENT # A-01-126-00 PAGE 69-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 70: Rsm Wiring
4. Solder the seven (7) 24 AWG wires to the connector. 5. Thread metal cover onto connector. 6. Insert screw into metal cover so that it indents into metal clamper. 7. Put hood over metal cover. DOCUMENT # A-01-126-00 PAGE 70-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 71 Terminate the shield at the PFD end inside the back shell. Attach pigtail ground wire to shield and connect to ground screw as shown in Figure 7.4. Figure 7.4 – PFD Back Shell Grounds/RSM DOCUMENT # A-01-126-00 PAGE 71-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 72: Configuration Module Wir Ng
GPS and NAV receivers to autopilot. Only ARINC 429 wiring may remain between the GPS and autopilot for NAV mode GPSS. The ACU will perform all switching functions to autopilot for GPS1, GPS2, NAV1, and NAV2. DOCUMENT # A-01-126-00 PAGE 72-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 73: Electrical Connections
(Alternate format for ARNAV) dddddd = distance in nm X 100 Desired Track dddd dddd = track in degrees x 10 Active Waypoint Identifier ddd[dd] ddd = ASCII waypoint ID DOCUMENT # A-01-126-00 PAGE 73-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 74 Magnetic Variation dddddddd Packed unsigned binary dddddddd = LS Byte Magnetic Variation dddddddd Packed unsigned binary dddddddd = MS Byte Waypoint Terminator <CR> ASCII Character Packet terminator DOCUMENT # A-01-126-00 PAGE 74-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 75: Arinc 429 Gps Inputs
Label 312 GPS “Ground Speed” Label 313 GPS “Track” Label 326 GPS “Lateral Deviation Scale Factor” full precision Label 327 GPS “Vertical Deviation Scale Factor” full precision DOCUMENT # A-01-126-00 PAGE 75-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 76: Arinc 429 Vloc Input
A differential input from the DH output of a radar altimeter. DH on: Difference between +DH and –DH greater than 5Vdc DH off: Difference between +DH and –DH less than 1Vdc Load: 10000 ohms +DH to -DH DOCUMENT # A-01-126-00 PAGE 76-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 77: Vloc Receiver
Sine (D and E), Cosine (F and G) Output Gradient: Excitation * 0.408 (26Vac in = 10.6Vac out) DC Offset: 0Vdc to +5Vdc (Offset applied to Rotor C) DOCUMENT # A-01-126-00 PAGE 77-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 78 Active low discrete input from a GPS receiver when approach mode is activated. FCS-LOC Engage Input Active low discrete input from a GPS receiver when approach is selected. DOCUMENT # A-01-126-00 PAGE 78-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 79: Autopilot
Active low output to an autopilot when an ILS is selected or GPS approach is active. ILS/GPS APPR Active: Sink to ground ILS/GPS APPR Inactive: Open Load Current: 100ma maximum DOCUMENT # A-01-126-00 PAGE 79-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 80 ACU DATUM is set to NORMAL in the configuration. Bendix King Flight Director Input When the EFD1000 is configured for ACU FD TYPE = 1 the ACU will accept Bendix King Flight Director output levels emulating the KI-256 Artificial Horizon Indicator. Pitch Scaling: 0Vdc = null, -4.3Vdc = 10º...
Page 81 EFD1000 Installation Manual Cessna ARC Flight Director Input When the EFD1000 is configured for ACU FD TYPE = 3 the ACU will accept Cessna ARC Flight Director output levels emulating the G-550 Artificial Horizon Indicator. NOTE: ACU Software Version A-02-178-1.1 or subsequent is required for the G- 550A Flight Director emulation.
Page 82: Arinc 429 Gps Output
The ACU transmits the following labels on P3 pins 4 and 5 for GPS receivers and systems that require low speed ARINC 429 magnetic heading and selected course. ARINC Label PFD Data Label 100 Selected Course Label 320 Magnetic Heading DOCUMENT # A-01-126-00 PAGE 82-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 83: Pfd Pin Out
RSM_D “ RSM_E “ RSM_F “ RSM_G “ Reserved Future Expansion “ “ “ “ “ “ CONFIG_A Configuration Module connection CONFIG_B “ CONFIG_C “ CONFIG_D “ DOCUMENT # A-01-126-00 PAGE 83-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 84: Rsm Pin Out
RSM Connection RSM_D RSM Connection RSM_E RSM Connection RSM_F RSM Connection RSM_G RSM Connection Male Pin Side.. Solder Cup Side Figure 8.2 - RSM Mating Connector –Install Side DOCUMENT # A-01-126-00 PAGE 84-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 85: Configuration Module Pin Out
GPS Vertical Dev Input (+) J1-14 GPS+TO INPUT GPS TO/FROM Input J1-15 GPS+VERTFLG INPUT GPS Vertical Flag (+) Figure 8.4 - J1 Connector (as viewed from front of unit) DOCUMENT # A-01-126-00 PAGE 85-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 86 Vertical output to autopilot (L) J2-36 -VERT-FLG OUTPUT Vertical output flag (L) J2-37 OUTPUT Lateral deviation output Figure 8.5 - J2 Connector (as viewed from front of unit) DOCUMENT # A-01-126-00 PAGE 86-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 87 INPUT Heading/Course Datum excitation input J3-24 Reserved Reserved INPUT Heading/Course Datum excitation J3-25 HDG-CRS-OFST offset input Figure 8.6 - J3 Connector (as viewed from front of unit) DOCUMENT # A-01-126-00 PAGE 87-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 89: Installation Wiring Diagrams
The EFD1000 Pro with ACU emulates a Bendix King KI-525A and NSD-360A HSI by providing outputs for HDG Datum and CRS Datum to an autopilot. The EFD1000 is compatible with any autopilot that is compatible with a KI-525A or NSD-360A HSI. Should connections be made to an autopilot not shown in these drawings the installer must verify the interface is fully functional by performing a complete ground and flight check of the system per the autopilot manufacturer’s...
Page 90 EFD1000 Installation Manual NOTE : Although the drawings show the complete interface of connected equipment to the EFD1000 System, they do not show the complete connections for non-EFD1000 equipment. Other manufacturers’ reference documents must be used to verify complete interface to the aircraft.
Page 95 This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.7 Pro Single Digital w/ Autopilot Interface DOCUMENT # A-01-126-00 PAGE 95-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 96 GNS480, No GPS2, NAV2 GNS480, GPS2, No NAV2 GNS480, GPS2, NAV2 *GNS530 uses same config as GNS430 Figure 9.8 Pro Digital & Analog Mix with and w/o Autopilot Interface DOCUMENT # A-01-126-00 PAGE 96-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 97 *GPS500 uses same config as GPS400 verify the integration data and for information Contact Aspen Avionics product support for 3 Use pins 48 & 49 or 50 & 51 not both. additional configurations ID’s if your regarding checkout procedures. This drawing, configuration is not shown.
Page 104 This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.13 KLN-90/A/B RS-232 and Analog to ACU Interface DOCUMENT # A-01-126-00 PAGE 104-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 105 The GX-50/60 share pin 29 between Vert FLG- for reference only. and NAV FLG-. Figure 9.14 GX-50/60 & GX-55/65 RS-232 and Analog to ACU Interface DOCUMENT # A-01-126-00 PAGE 105-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 106 2 See Figure 9.27 for SL-30 configuration. checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.15 ANALOG NAV Interface DOCUMENT # A-01-126-00 PAGE 106-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 109 STC compliance data) and for autopilot and flight director checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.17B S-TEC NSD-360 Emulation DOCUMENT # A-01-126-00 PAGE 109-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 110 This drawing, as it pertains to the pin 19 ARINC Ref Low. 9.6Vdc reference not non-Aspen equipment, is for reference only. used. Figure 9.18A NSD-360A Emulation Century 21/31/41/2000 DOCUMENT # A-01-126-00 PAGE 110-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 111 This radio coupler does not have CRS Datum interface. reference only. You must upgrade to 1C-388-2 coupler to gain this feature. Figure 9.18B NSD-360A Emulation Century IIB/III (Piper Altimatic/Autocontrol) DOCUMENT # A-01-126-00 PAGE 111-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 112 Existing DG installations must make CRS Datum it pertains to the non-Aspen equipment, is for connection as shown to gain full HSI features. reference only. Figure 9.19A NSD-360A Emulation Cessna 300B/400B/800B “IFCS” DOCUMENT # A-01-126-00 PAGE 112-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 117 This drawing, paralleling the 4 wires when available. as it pertains to the non-Aspen equipment, is for reference only. Figure 9.24 Back-up NAV Indicator (internal Converter) DOCUMENT # A-01-126-00 PAGE 117-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 118 Figure 9.15. regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.25 Back-up NAV Indicator (OBS Resolver) DOCUMENT # A-01-126-00 PAGE 118-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 119 This drawing, as it pertains to the non- Aspen equipment, is for reference only. Figure 9.26 Back-up NAV/GPS Indicator (GNS-430/530) Block Diagram DOCUMENT # A-01-126-00 PAGE 119-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 121: Configuration And Equipment Checkout
Log a Pass/Fail on check sheet then sign and date upon completion. Include copy of form in permanent aircraft records. NOTE: To avoid damage to the equipment, do not place the EFD1000 Display face down on the knobs 10.1 Test Equipment...
Page 122: Bonding Check - Far
Verify ACU(s) chassis is bonded to airframe with less than 3 milliohms resistance. • Verify RSM base plate or doubler plate is bonded to airframe with less than 3 • milliohms resistance. DOCUMENT # A-01-126-00 PAGE 122-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 123: System Configuration
EFD1000 Installation Manual 10.4 System Configuration Configure the EFD1000 system prior to running the ground test procedure. The configuration pages are accessed through the PFD display using the MENU button and the lower Right Control Knob labeled MODE/SYNC. 10.4.1 Main Menu Access The Main Menu operation is accessed by pushing the “MENU”...
Page 124 Figure 10.1 – Main Menu Page 1 MAIN MENU PAGE 2 – 360 MAP Settings Set as desired or use factory defaults settings. Figure 10.2 – Main Menu Page 2 DOCUMENT # A-01-126-00 PAGE 124-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 125 NOTE: VSPEEDs may be locked by Installation Menu 3. To change these values go to Installation Menu 3 and change VSPD EDIT from LOCKED to UNLOCKED. Make DOCUMENT # A-01-126-00 PAGE 125-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 126 Figure 10.5 – Main Menu Page 5 MAIN MENU PAGE 6 – Power Settings Power Settings page requires no configuration. Figure 10.6 - Main Menu Page 6 DOCUMENT # A-01-126-00 PAGE 126-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 127 EFD1000 Installation Manual MAIN MENU PAGE 7 – System Status System Status page requires no configuration. Figure 10.7 – Main Menu Page 7 DOCUMENT # A-01-126-00 PAGE 127-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 128: Installation Menu - Unit Configuration
To exit the Installation Menu at any time press the MENU button. All data will be saved as displayed. The system will reboot and “INITIALIZING” will appear on the display for approximately 15 seconds. DOCUMENT # A-01-126-00 PAGE 128-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 129 : No Flap Stall speed (bottom of green band) : Full Flap Stall speed (bottom of white band) - set to V on aircraft with no flaps DOCUMENT # A-01-126-00 PAGE 129-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 130 Initial Flap Extension Speed – set to zero “0” on aircraft without a published initial flap extension speed. For aircraft that have a published speed at which the first notch of flap may be deployed, set to that published value. DOCUMENT # A-01-126-00 PAGE 130-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 131 VSPD EDIT: UNLOCKED = pilot can modify value of VSPEED textual markers in Main Menu. LOCKED = the pilot cannot modify the values of the VSPEED textual markers in the Main Menu. DOCUMENT # A-01-126-00 PAGE 131-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 132 LOCK OFF TAPES can be configured to UNLOCKED or any other customer preference TAPES must be configured to LOCK ON STOP Figure 10.13 – TAPES Configuration Flow Chart DOCUMENT # A-01-126-00 PAGE 132-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 133 PITCH ATT TRIM: Pitch Attitude Trim is used to compensate for aircraft instrument panels that are inclined with respect to the aircraft leveling indices. The EFD1000 AHRS performance and the RSM calibration depend on the AHRS sensor orientation to the aircraft waterline using the aircraft leveling indices.
Page 134 Horizons attitude pitch indication being equal to the inclinometer. It may also be set to the amount of panel tilt as determined through measurement. 2) Press the PITCH ATT TRIM line select key. Method 2 – Leveling the Aircraft DOCUMENT # A-01-126-00 PAGE 134-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 135 (EFD1000 PFD Software version 1.1 and later). INSTALLATION MENU PAGE 5 – NAV SET UP The following menu will be used to configure the EFD1000 system for the installed GPS, NAV and autopilot interfaces. The installation wiring diagrams in Section 9 have a Configuration Matrix table that will be used to set ID#1 and ID#2.
Page 136 If you have the above installation without a NAV2 then select ID#1 = H and ID#2 = NONE. If you have the above installation with no NAV1 or NAV2 (just GPS and autopilot) then select ID#1 = G and ID#2 = NONE. DOCUMENT # A-01-126-00 PAGE 136-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 137 VOR1 and VOR2 will have VOR composite outputs with zero degree phase shift. For receivers with VOR composite outputs that are 180º out of phase (i.e., ARC RT-385) set to 180 as required (EFD1000 PFD Software version 1.1 and later). INSTALLATION MENU PAGE 6 – A429 CONFIG Installation Menu pages 6 and 7 are not editable and are for status only.
Page 138 INSTALLATION MENU PAGE 8 – NAV CONFIG For RS-232 GPS Navigators the RS-232 mode is set below using line select key 5. Line select keys 1-4 are for status only. DOCUMENT # A-01-126-00 PAGE 138-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 139 EFD1000 Installation Manual Figure 10.20 – Installation Menu Page 8 RS-232 SETUP: Set to NORMAL per Table 5.1. WPT ONLY is authorized. DOCUMENT # A-01-126-00 PAGE 139-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 140 Below is an example from Figure 9.16 showing a KI-525A Emulation with a Bendix King autopilot. In this case you would set the ACU HSI TYPE =0: DOCUMENT # A-01-126-00 PAGE 140-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 141 Installation Menu when the autopilot’s flight director is valid and engaged. This will assist you in aligning the PFD flight director to the mechanical flight director indicator. DOCUMENT # A-01-126-00 PAGE 141-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 142 ADJUSTED IN 30º INCREMENTS HEADING CORRECTION HDG ADJ: 0.0º VALUE +/- 6.0º Max. RSM CALIBRATION PAGE 10 OF 11 SEL PAGE Figure 10.22B – Installation Menu Page 10 DOCUMENT # A-01-126-00 PAGE 142-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 143 To exit the Installation Menu press the MENU button. All data will be saved as it was displayed on each page. The system will reboot and “INITIALIZING” will appear on the display for approximately 15 seconds. Normal operation continues. DOCUMENT # A-01-126-00 PAGE 143-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 144 Airspeed Display Units KEY 1 kts/mph Airspeed and Altitude KEY 2 UNLOCKED / LOCK OFF/LOCK ON Tapes Display Lock UNLOCKED/ Airspeed Textual Markers KEY 3 LOCKED Lockout DOCUMENT # A-01-126-00 PAGE 144-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 145 KEY 3 NORMAL, REVERSED FD ROLL OFFSET ADJ: KEY 4 +/- 7.5 units (0.5 unit increments) FD PITCH OFFSET ADJ: KEY 5 +/- 7.5 units (0.5 unit increments) DOCUMENT # A-01-126-00 PAGE 145-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 146 KEY 5 Editable: -10 to +10 degrees EFD1000 PFD Software Version 1.1 and later requires that the “HDG ADJ” field for each 30º heading increment between 30º to 360º, as described in section 10.5.3.2, be recorded below. RSM CALIBRATION PAGE 10:11 PAGE 10 OF 11 (PFD Software 1.1 and...
Page 147: Rsm Calibration
SB2009-02 applied by referring to the EFD1000 Configuration Chart or the aircraft logs. If so, do not replace the Configuration Module or RSM without completing the calibrations as identified in the SB2009-02. Contact an Aspen Avionics FSE for more information.
Page 148 After the calibration is accepted headings are checked using a calibrated • reference (i.e., a sight compass) every 30º (starting from North) to verify that the heading accuracy is within ±4º. EFD1000 PFD software version 1.1 and subsequent will allow the heading to be • calibrated every 30º. 10.5.1.1 Conventional Gear RSM Calibration Procedure Perform the RSM calibration procedure per Section 10.5.2 with the tail wheel on the...
Page 150: Rsm Calibration Procedure
(magnetic interference) in the vicinity of the RSM. Should the CAL HDG be greater than 25 degrees then the RSM location should be re- surveyed per Section 6.9.1. DOCUMENT # A-01-126-00 PAGE 150-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 151 TIME REMAINING: ## SECS Figure 10.27 – Aircraft Turning At the end of the calibration routine the “ACCEPT CALIBRATION?” and “REJECT CALIBRATION?” menu options will be enabled. DOCUMENT # A-01-126-00 PAGE 151-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 152 Pressing the “REJECT CALIBRATION” selection shall reject the calibration results. Reject the results if the calibration was poor or a previously stored calibration has better heading accuracies. DOCUMENT # A-01-126-00 PAGE 152-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 153: Heading Offset Adjustment
Figure 10.30 – Results Rejected 10.5.3 Heading Offset Adjustment EFD1000 PFD software version 1.0 - go to Section 10.5.3.1 EFD1000 PFD software version 1.1 or subsequent - go to Section 10.5.3.2 10.5.3.1 Heading Offset Adjustment (PFD software version 1.0 ) Monitor current aircraft heading on the PFD and compare it to actual aircraft heading.
Page 154: Heading Accuracy Test
Blowers, fans, heaters, air conditioner • Deice boots, fuel pump(s), backup vacuum pumps • Landing, logo, NAV lighting • Operate pulse equipment – transponder, WX radar, DME • DOCUMENT # A-01-126-00 PAGE 154-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 155: Ground Test Procedure
CROSS CHECK ATTITUDE annunciation. This behavior is the result of the Kalman Filter algorithms employed in the EFD1000 attitude solution. These changes in pitch, roll or heading are normal and do NOT indicate a system failure. The integrated...
Page 156: Indicated Airspeed Display
EFD1000 Installation Manual nature of the EFD1000 AHRS algorithms is such that AHRS performance can only be properly evaluated during flight or ground maneuvers. 10.6.1 Indicated Airspeed Display WARNING: This test must be performed by a certified mechanic. a) Using Installation Final Check Sheet of Appendix B record the aircraft speed settings from the Aircraft Flight Manual in the IAS Setting column.
Page 157: Nav Receiver Sensor Test
Check GPS vertical deviation for proper polarity (if connected). NOTE: The EFD1000 system will not display a VDI (GPS LPV Glide Slope) indicator without an activated valid LPV approach with APPROACH mode active. g) Verify that the OBS resolver output (if available) reads correctly on the GPS.
Page 158: Backup Navigation Indicator
GS deviation for Fly Up and Fly Down on the PFD. NOTE: The EFD1000 system will not display a VDI (Glide Slope) indicator without both valid localizer and Glide Slope signals. e) Repeat procedure for NAV2 if installed.
Page 159: Flight Director Test
Then adjust the BARO setting (increasing altitude on the tape) until the solid yellow altitude flag is seen on the PFD (just left of Selected Altitude window). The Sonalert should sound before reaching the selected altitude. DOCUMENT # A-01-126-00 PAGE 159-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 160: Decision Height Dh) Test - Pfd Software Version 1.1 Or Later
Ancillary Equipment Heading Check a) Verify proper operation of any ancillary components that are using the Low Speed ARINC 429 heading output from the EFD1000 system. b) Use ancillary equipment manufacturers’ installation tests procedures to perform ground check on their equipment.
Page 161: Flight Control Nterference Check
To ensure that the battery is connected perform the following: Go to the EFD1000 Main Menu Page 6 of 7 and verify “BAT: CHARGING” is displayed at the bottom of the display. If it displays “Charging” then test is complete.
Page 162: Post Installation Flight Check
East to North (In the southern Hemisphere, also turn east to South). g) If the difference between the heading on rollout and the heading after stabilizing is more than 7°, refer to the Troubleshooting Guide, Appendix A. DOCUMENT # A-01-126-00 PAGE 162-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 163: Ils Flight Checks (If No Autopilot, Otherwise Jump To Section 11.4)
GPS into OBS (HOLD) Mode (some GPS installations may require manual disabling of AUTOCRS). Use the CRS Pointer on the HSI to steer the autopilot via the GPS. DOCUMENT # A-01-126-00 PAGE 163-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 164 Repeat with GPS2, if installed. This completes the flight test. If everything was satisfactory then document the completion of the Test Flight in aircraft log book in accordance with FAR 91.407(b). DOCUMENT # A-01-126-00 PAGE 164-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 166: Operation
12.1 Pilot Controls 12.1.1 Overview Pilot interaction with the EFD1000 is accomplished through two knobs with push/rotate function and 11 buttons located on the display bezel. Refer to Figure 12.1. Two control knobs are used to control pilot settable bugs and references.
Page 167: Power Control
Electrical System) or 25.6V (28V Electrical System) the EFD will automatically switch to its internal battery (e.g. aircraft charging system failure). The EFD1000 internal battery will provide at least 30 minutes of power when it is fully charged. The battery provides power to the display head, RSM and emergency GPS.
Page 168: Display And Control Layout
6) “360/ARC” HSI View Control Double-Needle Bearing Pointer 7) “MAP” Map declutter logic Control Heading Bug 8) “GPSS” GPS Steering ON/OFF Control Airspeed Bug 9) Right Control Knob Altitude Bug DOCUMENT # A-01-126-00 PAGE 168-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 169: Control Knobs
To adjust the “MIN” field, the field must first be enabled using the MINs hot key. 12.2 Setting Flight Instruments The following procedures are used to adjust pilot editable data on the EFD1000: Heading Bug Set To set the heading bug, repeatedly PUSH the right control knob until the HDG field is enabled for editing.
Page 170: Knob Sync Function
ILS CRS The CRS is set to the current BARO The barometric pressure is aircraft heading. set to standard pressure of 29.92 in Hg or 1013 mB. DOCUMENT # A-01-126-00 PAGE 170-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 171: Hot Key Operation
Hot key 1 enables/disables the display of the airspeed and altitude tapes. In some installation where the backup airspeed and altitude instruments are not installed adjacent to the EFD1000 system the TPS hot key will be disabled and it will not be possible for the pilot to disable the airspeed and altitude tapes.
Page 172 GPSS (PRO model) Hot Key 5 is used to enable or disable GPS Steering (GPSS) outputs to the autopilot. See Section 12.11 for more information about GPSS. DOCUMENT # A-01-126-00 PAGE 172-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 173: Cdi And Bearing Pointer Source Selection
(i.e. GPS or VLOC) coupled to HSI course deviation indicator (but not for bearing pointers) is controlled by the radio. When coupled to a radio of this type, the EFD1000 will not toggle the operating state of the radio, but will annunciate the radio’s current operating state in the CDI Nav Source display field.
Page 174: Back Light Control
65ºC. Should this occur the pilot should take steps to reduce the cockpit ambient temperature. Figure 12.5 – Lighting Control adjustment DOCUMENT # A-01-126-00 PAGE 174-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 175: Map Range Control
Map Range Control The EFD1000 basemap range may be set to ranges of 2.5, 5, 10, 15, 20, 30, 40, 60, 80, 100, and 200 nautical miles. Map range is measured from the own ship position to the outside of the compass arc.
Page 176 Red chevrons are presented on the pitch ladder to guide in unusual attitude recovery. The Chevrons come in to view at pitch attitudes greater than 15º nose up or 10º nose down). The Chevrons indicate the direction of the horizon. DOCUMENT # A-01-126-00 PAGE 176-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 177: Airspeed Indicator
The range of these markings are determined by the Federal Regulations, and correspond to the aircraft limiting speeds that are identified in the Aircraft Flight Manual. DOCUMENT # A-01-126-00 PAGE 177-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 178 Multi Engine Aircraft Only. (multi A red line is displayed across the airspeed tape at the engine aircraft single engine minimum control speed. only) Blue Line Multi Engine Aircraft Only. DOCUMENT # A-01-126-00 PAGE 178-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 179: Altimeter
The range of the altimeter is -1,600 to +51,000 feet Selected Altitude Altitude Bug Altitude Pointer/Drum “MINIMUMS” Set Figure 12.12 – Altimeter Markings DOCUMENT # A-01-126-00 PAGE 179-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 180: Vertical Speed Indicator (Vsi)
In the ARC compass mode only the digital vertical speed value is presented. Figure 12.15 – Positive Rate of Climb Figure 12.16 – Rate Exceeding 2000 fpm DOCUMENT # A-01-126-00 PAGE 180-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 181: Rate Of Turn Indicator
The traditional HSI is an instrument which combines a Direction Indicator overlaid with a rotating Course Deviation Indicator (CDI). The HSI on the EFD1000 can be presented in either a full 360 degree compass rose mode, or in a 100 deg ARC format. Within the ARC mode, the pilot may select (via the main menu) between two different formats of CDI presentation –...
Page 182 A Vertical Deviation Indicator (VDI) is presented on the attitude indicator whenever the LDI is shown and valid vertical guidance is provided, such as from an ILS or WAAS GPS DOCUMENT # A-01-126-00 PAGE 182-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 183 CDI and the deviation diamond of the LDI or VDI is rendered as a hollow ghosted image “pegged” on the corresponding side. Figure 12.24 – Off Scale CDI Figure 12.25 – Off Scale VDI and LDI DOCUMENT # A-01-126-00 PAGE 183-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 184 EFD1000 Installation Manual Auto Course Control The pilot may configure the EFD1000 via the main menu to enable Auto Course Select so that a connected GPS will automatically set the course (CRS) value whenever the GPS is auto sequencing between waypoints. This capability relieves the pilot from manually setting the course at each waypoint transition along a GPS route.
Page 185: Bearing Pointers
The basemap presents map symbols for nearby navaids, intersections, airports, GPS flight plan waypoints, including curved and straight flight legs. Basemap data is presented whenever the EFD1000 system is connected to a compatible GPS system. The DOCUMENT # A-01-126-00 PAGE 185-225 Revision H ©...
Page 186 Depending on the range and selected feature display level, waypoint identifiers are displayed adjacent to their associated waypoints. Flight plan depictions are rotated within the display to maintain their correct compass orientations at all times. DOCUMENT # A-01-126-00 PAGE 186-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 187 When an alternate GPS is being used as the Base map position source, the message “GPS# REVERSION” (where “#” indicates the source of the reversionary GPS position, either “1” or “2” ) is presented. Figure 12.32 – GPS1 Failure, Reversionary Navigation DOCUMENT # A-01-126-00 PAGE 187-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 188: Autopilot Integration
Autopilot Integration General The EFD1000 can connect with many legacy autopilot systems that are typically found in general aviation aircraft. The EFD1000 emulates the HSI and/or Flight Director (FD) indicator with which the autopilot was originally certified. Autopilot integration is limited to heading bug and navigation integration, including vertical approach modes.
Page 189 Typical Autopilot Operations Whenever the EFD1000 installed configuration includes connections to GPS, VLOC and autopilot systems, the EFD1000 acts as a conduit of data between the navigation radios and the autopilot system. This configuration enables any navigation sensor available for display on the EFD system to be coupled to the autopilot.
Page 190 1. With a valid flight plan programmed in the GPS, use the CDI Nav Source Select Switch to couple the GPS to the HSI. 2. With GPSS OFF, set the EFD1000 heading bug to a value that will intercept the active leg of the flight plan.
Page 191 1. With a valid GPS Approach programmed in the GPS, use the CDI Nav Source Select switch to couple the GPS to the HSI. 2. With GPSS OFF, set the EFD1000 heading bug to a value that will intercept the active leg of the flight plan.
Page 192: Main Menu
12.12.1 Menu Controls The EFD1000 Main Menu is used to adjust various system configuration settings and preferences. To select the Main Menu, press the MENU button on the right side of the display bezel. To exit the Menu, press the MENU button again.
Page 193: Menu Options
For example, when set to “AUTO” Terminal VOR/DMEs are shown at range scales less than 30nm on the HIGH feature display level setting, but would not otherwise be shown. Similar logic is employed for all basemap features. DOCUMENT # A-01-126-00 PAGE 193-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 194 • View the Internal Battery Status • System Status The SYSTEM STATUS page is used to display information about the EFD1000 system and software. From the SYSTEM STATUS page the pilot may: View the Main Application Processor software version •...
Page 196: Environmental Qualification Forms
EFD1000 Installation Manual 13 Environmental Qualification Forms Nomenclature: EFD1000 Primary Flight Display (PFD) Part Number: A-05-110-00 TSO Numbers: TSO-C2d, TSO-C3d, TSO-C4c, TSO-C6d, TSO-C8d, TSO-C10b, TSO-C106, TSO–C113 Manufacturer: Aspen Avionics, Inc Address: 5001 Indian School Road NE, Albuquerque, NM 87110 DO-160 Revision:...
Page 197 26.0 Equipment identified as Category X, no test performed Other Tests Fire resistance was conducted by analysis in accordance with Federal Aviation Regulations Part 25, Appendix F. DOCUMENT # A-01-126-00 PAGE 197-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 198 EFD1000 Installation Manual Nomenclature: EFD1000 Remote Sensor Module (RSM) Part Number: A-05-111-00 TSO Numbers: TSO-C113 Manufacturer: Aspen Avionics, Inc Address: 5001 Indian School Road NE, Albuquerque, NM 87110 DO-160 Revision: DO-160E Date Tested: 2/2008 CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTED...
Page 200 26.0 Equipment identified as Category X, no test performed Other Tests Fire resistance was conducted by analysis in accordance with Federal Aviation Regulations Part 25, Appendix F. DOCUMENT # A-01-126-00 PAGE 200-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 203 Pitot/static lines reversed b) Connect pitot line to “P” port and c) Air data sensor failed static line to “S” port on PFD c) Repair or replace PFD DOCUMENT # A-01-126-00 PAGE 203-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 204 ACU to PFD wiring e) ACU fault d) Check ACU to PFD A429 wiring f) PFD fault e) Repair or replace ACU f) Repair or replace PFD DOCUMENT # A-01-126-00 PAGE 204-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 205 Sluggish compass card b) RSM has become b) With power removed from EFD1000 magnetized. system degauss RSM and general area (Note: may or may not be using degausser. associated with “Cross Check c) “Pitch Attitude Trim”...
Page 206 GPS A429 IN bus configured a) See Figure 9.27 for GPS configuration wrong notes b) ARINC 429 “A” and “B” lines b) Correct wiring error to GPS A429 IN reversed DOCUMENT # A-01-126-00 PAGE 206-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 209 EFD1000 Installation Manual EFD1000 Installation Final Check Sheet (page 1 of 4) Aircraft Type: Date: Aircraft Serial Number: Tail Number: The following pages must be printed and used during checkout. The Section number refers to the section in the manual where the test is performed. This form must be included in document package to be included in aircraft maintenance records.
Page 210 EFD1000 Installation Manual EFD1000 Installation Final Check Sheet (page 2 of 4) SECTION POST INSTALLATION TESTS PASS FAIL 10.5.4 Heading Accuracy Check 10.5.5 Heading Interference Test 10.6.1 Indicated Airspeed Test 10.6.2 Altitude Display Test 10.6.3 System Leak Test 10.6.4 OAT- Outside Air Temperature Test 10.6.5...
Page 211 Log book entry stating aircraft has been modified in accordance with EFD1000 AML-STC. Misc Complete cover page of EFD1000 AFMS Aspen document # A-01-175-00 (Pro & Pro Digital) or A-01-179-00 (Pilot) and insert in Airplane Flight Manual. Misc Complete wire routing diagram Figure D1in Appendix D...
Page 212 EFD1000 Installation Manual EFD1000 Installation Final Check Sheet (page 4 of 4) SECTION COMPLIANCE CHECK PASS FAIL Misc Copy of ICAs Appendix D with copy of wiring diagrams (Section 9 or installer drafted), copy of Configuration Chart Table 10.1, and copy of Pre-Modification Checklist Table 5.1 inserted.
Page 215 Aircraft Tail #: Owner/Operator: I request that the following settings be configured into my EFD1000 PFD as described below. These airspeeds must match the requirements for the aircraft above and must match the values in the Aircraft Flight Manual (AFM), Pilot Operating Handbook (POH), or other legal form of documentation (e.g., Placard).
Page 216: Instructions For Continued Airworthiness
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 Aircraft Maintenance Manual and operator’s Aircraft Scheduled Maintenance Program.
Page 217 EFD1000 Installation Manual ICA – RECORD OF REVISION Revision Date Description of Change 3/28/08 INITIAL RELEASE DOCUMENT # A-01-126-00 PAGE 217-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 218 EFD1000 Installation Manual D.1 Introductory Information This ICA provides instructions necessary for authorized personnel to inspect and maintain the EFD1000 system installed by the EFD1000 AML-STC. The following data may be required for this maintenance: Replacement Parts: A-01-126-00 Rev. C or later EFD1000 Installation...
Page 219 CFR § 43.16 and § 91.403 unless an alternate program has been FAA approved. D.8 Distribution of Revisions Any revision to this document will be available on the Aspen Avionics website at www.aspenavionics.com. Significant changes or revisions will be electronically mailed to dealers on record at the time the revision is available.
Page 220 EFD1000 Installation Manual D.10 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.
Page 221 Verify power is off. Install ACU in mounting location and install six (6) 6-32 mounting screws through holes in ACU mounting tabs. Install all three (3) D-sub connectors securing each with the two jackscrews per connector. DOCUMENT # A-01-126-00 PAGE 221-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 222 Verify power is off. Verify O-ring on RSM is in good condition with no cracking or flattening. Contact Aspen Avionics for replacement O-ring if required. Verify RSM shim is installed between aircraft skin and RSM if required. Feed circular connector down through ½...
Page 223 (CM is wired within 12” of PFD) ACU#1 circuit breaker location - optional ACU#1 – optional ACU#2 circuit breaker location – optional ACU#2 – optional Autopilot computer location DOCUMENT # A-01-126-00 PAGE 223-225 Revision H © Copyright 2009 Aspen Avionics Inc.
Page 225 INSERT THE FOLLOWING AFTER THIS PAGE COMPLETED - CONFIGURATION CHART - TABLE 10.1 COMPLETED - PRE MODIFICATION CHECKLIST – TABLE 5.1 COMPLETED - OPERATOR CONFIGURATION CHECKLIST FROM APPENDIX C COMPLETED - EFD1000 INSTALLATION FINAL CHECKSHEET FROM APPENDIX B DOCUMENT # A-01-126-00 PAGE 225-225 Revision H...

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