Efd 1000 Install Manual

EFD1000 and EFD500 SW v2.X Installation Manual EFD1000 and EFD500 Software Version 2.X Installation Manual Includes Instructions for Continued Airworthiness Aspen Document # 900-00012-001 Revision D in Appendix D Aspen Document # 900-00003-001 Rev G DOCUMENT # 900-00003-001 PAGE 1-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Special Notes to the Installer It is important to review the entire Installation Manual before installing the EFD1000/500. The following items are of special note and should be considered for planning and installation. 1. This manual covers the installation of a single PFD and also covers installations where a PFD is accompanied by an EFD1000 and/or EFD500 MFD. There are important limitations to the allowable configurations. To avoid unsatisfactory results, refer to the Requirements and Limitations in Section 5, Pre-Modification Planning before beginning the installation. 2. The integral EFD1000 ADAHRS uses accelerometer, rate gyro, air data and magnetic inputs to derive the attitude solution. Airspeed and altimeter maintenance checks will generate warnings on the EFD1000 display and produce changes in the displayed attitude. This is normal. 3. Correct replacement and proper placement of the aircraft instruments is critical to maintain the aircraft certification. Certain instruments can be removed. More importantly, certain instruments must not be removed. Installation of an EFD1000 MFD with EBB authorizes removal of standby airspeed and altitude instruments. In all cases, a standby attitude instrument must be retained. See Section 5. 4. The EFD1000 does not provide a synchro heading bootstrap output. If equipment remains on the aircraft that uses a bootstrap input and which can not accept a low speed ARINC 429 input from the EFD1000, then the bootstrap-enabled slaved compass system should be retained. 5. The EFD1000 PFD, EFD1000 MFD and/or EFD500 MFD are powered from the Battery Bus, not the Avionics Bus. Connection through the avionics bus is not approved, and is not eligible to be approved as a deviation to the STC. Separate EFD (1000 and 500) master switches are required for each display. 6. The RSM contains magnetic elements that are used to derive the aircraft heading and attitude. The RSM is sensitive to magnetic fields on the aircraft. Section 6.9 describes how to locate the RSM. Note that mounting over the cabin can be problematic due to the possibility of passengers using headsets with magnetic speakers. Exercise the control cables while validating a location. Consider all the magnetic field variations. A satisfactory RSM location is part of the Final Check Sheet. Use caution when installing the RSM connector to avoid damaging the connector or wiring. 7. The RSM can be damaged if exposed to a magnet. Do not install the RSM with magnetic tools. Caution: Some levels have a magnet in them. 8. Structural mounting and lightning direct effects approval for RSM installation on composite, fabric or aircraft requiring damage tolerance assessment (Certification basis of 14CFR Part 23 amendment 23- 48 or later) aircraft is not included under the AML STC. See Section 6.9.3 for installation inside a composite or fabric aircraft. Mounting the RSM on a pressure vessel also requires separate structural approval. 9. Avionics integrations are shown in Section 9. The manufacturer’s documentation for the integrated equipment must be used to verify and validate the operation of the integrated equipment. 10. The installer must determine whether the design changes described in this document are compatible with previously approved modifications. 11. To avoid damage to the equipment, do not place the EFD face down resting on the knobs. 12. The ICA requires installer-supplied wiring diagrams and equipment location information. See Appx. D. 13. Each EFD must be charged before release to the customer. See Section 10.6.19. DOCUMENT # 900-00003-001 PAGE 2-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The conditions and tests required for TSO approval of the EFD1000/500 System are minimum performance standards. It is the responsibility of those installing this article either on or within specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft. The article may be installed only if performed under 14 CFR Part 43 or the applicable airworthiness requirements. This manual contains FAA Approved installation instructions for installation of the Aspen™ EFD1000/EFD500 system under the AML STC for use as a primary electronic flight display and associated Multifunction display(s) (as applicable) during day/night IFR and VFR operations in those Part 23 Class I and II aircraft (as defined in AC 23.1309-1C) listed on the AML. Installation of the EFD1000/500 into part 23 Class I or II aircraft not included in the AML, into any part 23 class III or IV aircraft, or into any part 25, 27, or 29 aircraft, or non-U.S. registered aircraft requires separate airworthiness approval. DOCUMENT # 900-00003-001 PAGE 4-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Table of Contents 1 INTRODUCTION.................................................................................................... 13 1.1 PART NUMBERS......................................................................................................... 13 1.1.1 Authorized Display Configurations..................................................... 14 1.2 INSTALLATION KIT CONTENTS....................................................................................... 19 1.3 ACCESSORIES REQUIRED BUT NOT SUPPLIED – EFD1000 PFD............................................... 21 1.4 OPTIONAL ACCESSORIES NOT SUPPLIED – EFD1000 PFD.................................................... 21 1.5 OPTIONAL ACCESSORIES REQUIRED BUT NOT SUPPLIED – EFD1000 MFD ................................ 22 1.6 OPTIONAL ACCESSORIES REQUIRED BUT NOT SUPPLIED – EFD500 MFD .................................. 22 1.7 MFD DATABASE VERSIONS .......................................................................................... 22 1.8 SPECIAL TOOLS REQUIRED............................................................................................ 23 1.9 VENDOR INFORMATION ............................................................................................... 23 1.10 WARRANTY REGISTRATION........................................................................................... 23 1.11 REGULATORY COMPLIANCE .......................................................................................... 23 1.11.1 Technical Standard Order .................................................................. 23 1.11.2 Software Certification........................................................................ 24 1.11.3 Environmental Compliance ................................................................ 24 1.11.4 Installation Approval ......................................................................... 24 2 EQUIPMENT SPECIFICATIONS AND LIMITATIONS..................................................... 25 2.1 EFD1000 PFD AND MFD .......................................................................................... 25 2.1.1 General Specifications ....................................................................... 25 2.1.2 Operational Specifications: ................................................................ 25 2.1.3 I/O Specifications: ............................................................................. 25 2.1.4 Certification Specifications: ............................................................... 25 2.1.5 Outline Drawing: ............................................................................... 26 2.2 EFD500 MFD......................................................................................................... 27 2.2.1 General Specifications ....................................................................... 27 2.2.2 Operational Specifications ................................................................. 27 2.2.3 I/O Specifications.............................................................................. 27 2.2.4 Certification Specifications ................................................................ 27 2.2.5 EFD500 Outline Drawing.................................................................... 28 2.2.6 Design Eye Viewing Envelope............................................................. 28 2.3 REMOTE SENSOR MODULE (RSM): ................................................................................. 29 2.3.1 General Specifications ....................................................................... 29 2.3.2 Operational Specifications: ................................................................ 29 2.3.3 I/O Specifications: ............................................................................. 29 2.3.4 Certification Specifications: ............................................................... 29 2.3.5 Outline Drawing: ............................................................................... 30 2.4 CONFIGURATION MODULE (CM) .................................................................................... 30 2.4.1 General Specifications ....................................................................... 30 2.4.2 Operational Specifications: ................................................................ 31 2.4.3 I/O Specifications: ............................................................................. 31 DOCUMENT # 900-00003-001 PAGE 5-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.4.4 Certification Specifications: ............................................................... 31 2.4.5 Outline Drawing................................................................................ 31 2.5 ANALOG CONVERTER UNIT (ACU): ................................................................................ 32 2.5.1 General Specifications ....................................................................... 32 2.5.2 Operational Specifications: ................................................................ 32 2.5.3 I/O Specifications: ............................................................................. 32 2.5.4 Certification Specifications: ............................................................... 32 2.5.5 Outline Drawing: ............................................................................... 33 2.6 EBB58 EMERGENCY BACKUP BATTERY ............................................................................ 33 2.6.1 General Specifications ....................................................................... 33 2.6.2 Operating Specifications.................................................................... 33 2.6.3 I/O Specifications.............................................................................. 34 2.6.4 Certification Specifications: ............................................................... 34 2.6.5 Outline Drawing................................................................................ 34 3 SYSTEM DESCRIPTION........................................................................................... 35 3.1 EFD1000/EFD500 ................................................................................................. 35 3.2 REMOTE SENSOR MODULE (RSM) .................................................................................. 37 3.3 CONFIGURATION MODULE (CM) .................................................................................... 38 3.4 ANALOG CONVERTER UNIT (ACU) ................................................................................. 38 3.5 SYSTEM ARCHITECTURE............................................................................................... 39 4 SUPPORTED INSTALLED CONFIGURATIONS............................................................. 41 4.1 SINGLE DISPLAY CONFIGURATIONS ................................................................................. 41 4.1.1 Pilot Configurations........................................................................... 41 4.1.2 Pro Digital Configuration................................................................... 42 4.1.3 Pro Configurations with Autopilot ...................................................... 43 4.1.4 Pro Configuration with Autopilot and Digital/Analog VLOC................. 44 4.1.5 Pro Configuration with Autopilot and Dual Analog VLOC..................... 45 4.2 TWO DISPLAY SYSTEM - PFD WITH EFD1000 OR EFD500 MFD.......................................... 46 4.3 THREE DISPLAY SYSTEM - PFD WITH EFD1000 MFD AND EFD500 MFD............................... 47 5 PRE-MODIFICATION PLANNING............................................................................. 49 5.1 PRE-MODIFICATION CHECKLIST .................................................................................... 50 5.2 LIMITATIONS ............................................................................................................ 52 5.2.1 Standby Attitude Positioning.............................................................. 57 5.2.2 Standby Airspeed and Altimeter Positioning ....................................... 58 5.2.3 Directional Gyro/ HSI......................................................................... 59 5.2.4 Back Up Nav Indicator........................................................................ 59 5.2.5 GPS Annunciators.............................................................................. 60 5.2.6 Aircraft Power Requirements.............................................................. 60 5.2.7 Equipment Power Requirements......................................................... 61 5.2.8 Special Considerations for Aircraft Limited to VFR .............................. 61 5.3 CONVENTIONAL LANDING GEAR “TAIL DRAGGER” AIRCRAFT .................................................. 62 DOCUMENT # 900-00003-001 PAGE 6-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5.4 PART 135 IFR OPERATIONS........................................................................................ 62 5.5 SETTING V-SPEED TEXTUAL MARKERS ........................................................................... 62 5.6 OPTIONAL INTERFACES................................................................................................ 62 5.6.1 Autopilot .......................................................................................... 62 5.6.2 GPS Navigator Basemap Compatibility ................................................ 63 5.6.3 GPSS ................................................................................................. 65 5.6.4 GPS/ NAV Switching .......................................................................... 65 5.6.5 Discrete Output................................................................................. 65 5.6.6 Heading Output ................................................................................ 65 5.6.7 Air Data Outputs ............................................................................... 66 5.6.8 Second ACU ...................................................................................... 66 5.6.9 Decision Height................................................................................. 66 5.6.10 RS-232 Considerations (existing PFD installations)............................. 66 5.6.11 Flush or Recess Mounting the PFD ..................................................... 66 5.7 TRAFFIC SENSORS...................................................................................................... 67 5.8 WEATHER INFORMATION.............................................................................................. 67 6 MECHANICAL INSTALLATION ................................................................................ 69 6.1 UNPACKING AND INSPECTING EQUIPMENT......................................................................... 69 6.2 EQUIPMENT LOCATION DOCUMENTATION......................................................................... 69 6.3 LOG BOOK ENTRY ..................................................................................................... 69 6.4 WEIGHT AND BALANCE................................................................................................ 70 6.5 INSTALLATION LIMITATIONS ......................................................................................... 70 6.5.1 EFD1000 Installation Limitations........................................................ 70 6.5.2 RSM Mounting Limitations ................................................................. 70 6.5.3 EFD1000 MFD – RSM Limitations (Dual RSM Mounting)........................ 71 6.6 EQUIPMENT BONDING................................................................................................. 72 6.7 COOLING ................................................................................................................ 73 6.8 EFD INSTALLATION.................................................................................................... 73 6.8.1 Connecting the Internal Battery (does not apply to 910-00001-002) .. 73 6.8.2 PFD Mounting Location...................................................................... 73 6.8.3 MFD1000 Mounting Location............................................................. 74 6.8.4 EFD Mounting Bracket Installation...................................................... 75 6.8.5 EFD Bonding Strap............................................................................. 77 6.8.6 Pitot and Static Connections (EFD1000 only) ...................................... 78 6.8.7 Quick Connector Installation.............................................................. 79 6.8.8 Leak Check Requirements.................................................................. 79 6.9 RSM INSTALLATION................................................................................................... 80 6.9.1 Proposed RSM Location Check ........................................................... 84 6.9.2 Pressurized Aircraft........................................................................... 85 6.9.3 RSM mounting on Composite, Fabric or Damage-Tolerant Design Aircraft 86 6.9.4 Second RSM Placement (MFD1000)..................................................... 86 6.9.5 RSM Mounting Angles........................................................................ 87 DOCUMENT # 900-00003-001 PAGE 7-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.9.6 RSM External Mount – Aluminum Skin................................................ 89 6.9.7 RSM Internal Mount ........................................................................... 92 6.9.8 RSM Installation ................................................................................ 92 6.9.9 RSM Shim Fabrication (if necessary) ................................................... 93 6.10 ACU INSTALLATION................................................................................................... 96 6.10.1 ACU Mounting................................................................................... 97 6.11 CONFIGURATION MODULE INSTALLATION......................................................................... 98 6.12 EBB58 EMERGENCY BACKUP BATTERY INSTALLATION........................................................ 100 6.12.1 EBB58 Mounting.............................................................................. 100 7 ELECTRICAL INSTALLATION..................................................................................103 7.1 ELECTRICAL LOAD ANALYSIS....................................................................................... 103 7.2 ELECTRICAL INSTALLATION......................................................................................... 103 7.2.1 HIRF/Lightning Requirements .......................................................... 105 7.2.2 EFD to GPS/VLOC/ACU Wiring.......................................................... 106 7.2.3 RSM Wiring ..................................................................................... 107 7.2.4 Configuration Module Wiring........................................................... 109 7.2.5 ACU Wiring ..................................................................................... 109 7.2.6 Back Up NAV Indicator Wiring .......................................................... 109 7.2.7 Autopilot Wiring.............................................................................. 109 7.2.8 EBB58 Wiring................................................................................... 109 8 ELECTRICAL CONNECTIONS .................................................................................111 8.1 EFD ELECTRICAL SPECIFICATIONS ................................................................................ 111 8.1.1 Power Input..................................................................................... 111 8.1.2 Tone (PFD)/Reversion (MFD) Output ................................................. 111 8.1.3 RS-232 GPS Input............................................................................ 111 8.1.4 RS232 ADC Output.......................................................................... 111 8.1.5 ARINC 429 GPS Inputs ..................................................................... 112 8.1.6 ARINC 429 VLOC Input .................................................................... 113 8.1.7 ARINC 429 Output........................................................................... 113 8.2 ACU ELECTRICAL SPECIFICATIONS................................................................................ 114 8.2.1 Power Input..................................................................................... 114 8.2.2 Decision Height (DH) Input .............................................................. 114 8.2.3 VLOC Receiver................................................................................. 114 8.2.4 GPS Receiver ................................................................................... 115 8.2.5 Autopilot ........................................................................................ 116 8.2.6 ARINC 429 Output........................................................................... 119 8.3 EFD PIN OUT......................................................................................................... 120 8.4 RSM PIN OUT........................................................................................................ 121 8.5 CONFIGURATION MODULE PIN OUT.............................................................................. 121 8.6 ACU PIN OUT........................................................................................................ 122 9 INSTALLATION WIRING DIAGRAMS........................................................................125 DOCUMENT # 900-00003-001 PAGE 8-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10 CONFIGURATION AND EQUIPMENT CHECKOUT .....................................................167 10.1 POST INSTALLATION WIRING CHECKS ............................................................................ 167 10.1.1 Wiring Verification........................................................................... 167 10.1.2 Bonding Check – FAR 23.867(b) ....................................................... 167 10.2 DATABASE INSTALLATION .......................................................................................... 168 10.3 INITIAL SYSTEM TURN ON.......................................................................................... 168 10.4 SYSTEM CONFIGURATION........................................................................................... 169 10.4.1 Main Menu Access........................................................................... 169 10.4.2 Menu Navigation ............................................................................. 169 10.4.3 Edit Mode ....................................................................................... 169 10.4.4 Main Menu Configuration ................................................................ 169 10.4.5 INSTALLATION MENU – UNIT CONFIGURATION.................................. 170 10.4.6 EFD1000 Installation Menu Configuration ........................................ 172 10.4.7 EFD500 MFD Installation Menu Configuration................................... 179 10.5 RSM CALIBRATION .................................................................................................. 191 10.5.1 Calibration Overview ....................................................................... 191 10.5.2 RSM Calibration Procedure............................................................... 194 10.5.3 Heading Offset Adjustment ............................................................. 197 10.5.4 Heading Accuracy Test .................................................................... 198 10.5.5 Heading Interference Test................................................................ 198 10.6 GROUND TEST PROCEDURE (PFD, EFD500 MFD AND EFD1000 IN PFD REVERSION AND IN MFD MODE) 199 10.6.1 Indicated Airspeed Display .............................................................. 200 10.6.2 Altitude Display............................................................................... 200 10.6.3 System Leak Test ............................................................................ 200 10.6.4 Outside Air Temperature (if ENABLED).............................................. 200 10.6.5 AHRS Sensor Test............................................................................ 200 10.6.6 GPS Sensor Test .............................................................................. 200 10.6.7 NAV Receiver Sensor Test ................................................................ 201 10.6.8 Backup Navigation Indicator ............................................................ 202 10.6.9 Autopilot Sensor Test ...................................................................... 202 10.6.10 Flight Director Test ......................................................................... 203 10.6.11 Sonalert Test................................................................................... 203 10.6.12 Decision Height (DH) Test................................................................ 204 10.6.13 Traffic Display Test (if installed, applies to PFD, EFD500 MFD, and EFD1000 MFD) 204 10.6.14 XM Weather Display and Control Test (if installed, applies to PFD, EFD500 MFD, and EFD1000 MFD)..................................................................................... 204 10.6.15 WX-500 Display and Control Test (if installed, applies to PFD, EFD500 MFD, and EFD1000 MFD) ............................................................................................. 204 10.6.16 Ancillary Equipment Heading Check................................................. 204 10.6.17 Ancillary Equipment Air Data Check ................................................. 205 10.6.18 EFD Inter-System Communication Test ............................................ 205 DOCUMENT # 900-00003-001 PAGE 9-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.6.19 EBB58 Emergency Backup Battery Test (if installed) and internal battery tests 205 10.6.20 TAPES Configuration Check ............................................................. 205 10.6.21 EMI Test (test with all EFD units operating) ....................................... 206 10.6.22 Flight Control Interference Check..................................................... 206 10.7 WX-500 INSTALLATION AND MAINTENANCE .................................................................. 207 10.7.1 System Data.................................................................................... 207 10.7.2 Strike Test ...................................................................................... 208 10.7.3 Noise Monitor ................................................................................. 209 10.7.4 Antenna Mount ............................................................................... 210 11 POST INSTALLATION FLIGHT CHECK.....................................................................211 11.1 BASIC ADI FLIGHT CHECKS (PFD AND EFD1000 MFD IN REVERSION) .................................. 211 11.2 BASIC HSI/DG FLIGHT CHECKS (PFD AND EFD1000 MFD IN REVERSION)............................. 211 11.3 ILS FLIGHT CHECKS PFD (EFD1000 MFD AND EFD1000 SECONDARY HSI) ......................... 212 11.4 AUTOPILOT FLIGHT CHECKS (IF INSTALLED, PFD ONLY)...................................................... 212 11.5 DOCUMENT TEST FLIGHT........................................................................................... 213 12 OPERATING INSTRUCTIONS..................................................................................215 12.1 PILOT CONTROLS .................................................................................................... 215 12.1.1 Overview......................................................................................... 215 12.1.2 Power Control ................................................................................. 215 12.1.3 PFD Display and Control Layout ....................................................... 217 12.1.4 Control Knobs................................................................................. 218 12.2 TRAFFIC DISPLAY (OPTIONAL) ..................................................................................... 218 12.3 XM WEATHER DISPLAY (OPTIONAL) .............................................................................. 218 12.4 WX-500 DISPLAY (OPTIONAL) ................................................................................... 219 13 ENVIRONMENTAL QUALIFICATION FORMS.............................................................221 APPENDIX A TROUBLESHOOTING .......................................................................................225 APPENDIX B INSTALLATION FINAL CHECK SHEET ................................................................231 APPENDIX C OPERATOR CONFIGURATION CHECKLIST.........................................................237 APPENDIX D INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ...........................................241 DOCUMENT # 900-00003-001 PAGE 10-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual List of Tables Table 1.1 - TSO Part Numbers.............................................................................................................. 13 Table 1.2 - Authorized Display Configurations..................................................................................... 14 Table 1.3 - 903-00001-001 or A-08-130-00 EFD1000 Install Kit ....................................................... 19 Table 1.4 – 903-00004-001 or A-08-149-00 EFD500 Install Kit.......................................................... 20 Table 1.5 - 903-00002-001 or A-08-131-00 RSM Install Kit............................................................... 20 Table 1.6 - 903-00003-001 or A-08-132-00 ACU Install Kit .............................................................. 20 Table 1.7 – PFD Accessories Required but Not Supplied........................................................................ 21 Table 1.8 – PFD Optional Accessories Not Supplied............................................................................... 21 Table 1.9 - EFD1000 MFD Optional Accessories Required but Not Supplied.......................................... 22 Table 1.10 - EFD500 MFD Optional Accessories Required but Not Supplied.......................................... 22 Table 1.11 - MFD Database Versions.................................................................................................... 22 Table 5.1 - PFD Pre-Modification Checklist .......................................................................................... 51 Table 5.2 - MFD Pre-Modification Checklist ......................................................................................... 52 Table 5.3 - GPS Basemap Compatibility................................................................................................ 64 Table 6.1 – Component Weights........................................................................................................... 70 Table 7.1 – Current Draw ................................................................................................................... 103 Table 8.1 - EFD A429 GPS Input ......................................................................................................... 113 Table 8.2 - EFD A429 VLOC Input ...................................................................................................... 113 Table 8.3 - EFD1000 A429 GPS Output .............................................................................................. 113 Table 8.4 - ACU A429 Output ............................................................................................................ 119 Table 8.5 - PFD/MFD Pin Out ............................................................................................................. 120 Table 8.6 - RSM Pin Out ..................................................................................................................... 121 Table 8.7 - Configuration Module Pin Out .......................................................................................... 121 Table 8.8 - ACU J1 Pin Out................................................................................................................. 122 Table 8.9 - ACU J2 Pin Out................................................................................................................. 123 Table 8.10 - ACU J3 Pin Out............................................................................................................... 124 Table 13.1 - EFD1000 Environmental Qualification Form.................................................................... 221 Table 13.2 - RSM Environmental Qualification Form........................................................................... 222 Table 13.3 - ACU Environmental Qualification Form........................................................................... 223 DOCUMENT # 900-00003-001 PAGE 11-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual List of Definitions, Acronyms, Abbreviations ACU Analog Converter Unit ADAHRS Air Data Attitude Heading Reference System ADC Air Data Computer ADI Attitude Director Indicator AI Attitude Indicator AHRS Attitude and Heading Reference System AML Approved Model List A429 ARINC 429 interface CM Configuration Module DG Directional Gyro DH Decision Height EBB Emergency Backup Battery EFD Electronic Flight Display (refers to all versions) EFD500 EFD500 MFD Flight Display EFD1000 EFD1000 PFD or EFD1000 MFD EWR Evolution Weather Receiver FAA Federal Aviation Administration FAR Federal Aviation Regulations FD Flight Director GNAV Combined GPS and VOR radio (all A429 interface) GPS Global Positioning System GS Glide-slope or Groundspeed HSI Horizontal Situational Indicator ICA Instructions for Continued Airworthiness IFR Instrument Flight Rules LOC ILS Localizer LRU Line Replaceable Unit MFD Multi-Function Display (refers to EFD500 MFD or EFD1000 MFD) OAT Outside Air Temperature OBS Omni-Bearing Selector PFD Primary Flight Display (refers to EFD1000 PFD only) RSM Remote Sensor Module STC Supplemental Type Certificate TAS True Airspeed VFR Visual Flight Rules VLOC The VOR side of a GNAV radio VOR VHF Omni-directional Ranging WAAS Wide Area Augmentation System DOCUMENT # 900-00003-001 PAGE 12-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1 Introduction This Installation Manual contains FAA Approved Data, but only when used to install the Aspen Avionics EFD1000 and/or EFD500 display systems in accordance with AML STC SA10822SC. This document contains detailed instructions for installing the EFD1000/500 System into specific aircraft as listed in the AML-STC. There are regulations that must be complied with to ensure an airworthy installation. Section 5, Pre-Modification Planning will guide you through these requirements. 1.1 Part Numbers List of the major hardware components (by part number) that make up the EFD1000/500 system complying with the standards prescribed in this TSO. Part Number Description 910-00001-001 EFD1000, Evolution Flight Display, PFD/MFD 910-00001-002 EFD1000, Evolution Flight Display, MFD, for use with EBB58 Emergency Backup Battery 910-00001-003 EFD500, Evolution Flight Display, MFD 910-00005-004 Configuration Module, Assy 910-00003-001 RSM, Remote Sensor Module, Top Mount w/GPS 910-00003-002 RSM, Remote Sensor Module, Top Mount w/o GPS 910-00003-003 RSM, Remote Sensor Module, Bottom Mount w/o GPS 910-00004-001 ACU, Analog Converter Unit - optional 903-00001-001 EFD1000 Install Kit 903-00004-001 EFD500 Install Kit 903-00002-001 RSM Install Kit 903-00003-001 ACU Install Kit 413-00002-001 EBB58, Emergency Backup Battery 903-00006-001 EBB58 Installation Kit, 7ft cable, mounting tray Table 1.1 - TSO Part Numbers DOCUMENT # 900-00003-001 PAGE 13-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1.1.1 Authorized Display Configurations The following table identifies the only Authorized Display Configurations for software version 2.X equipment. Other combinations are not approved. See Section 5 for Installation Configurations Authorized by this STC and Figures 1.1 to 1.5 for Authorized System Components of each Display System. See Aspen Document A-01-126-00 for installation of software version 1.0 and 1.1 equipment. System Display Configurations Single Display EFD1000 PFD Pro EFD1000 PFD Pilot Two Display EFD1000 PFD Pro plus EFD1000 MFD Two Display EFD1000 PFD Pro plus EFD500 MFD Three Display EFD1000 PFD Pro plus EFD1000 MFD plus EFD500 MFD Table 1.2 - Authorized Display Configurations Note: Standalone MFD installations are not authorized at this time. An MFD must always be in installed with a PFD Pro. DOCUMENT # 900-00003-001 PAGE 14-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 1.1 - EFD1000 PFD PRO Authorized System Components DOCUMENT # 900-00003-001 PAGE 15-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual EFD1000 PFD PILOT, TSO 302-00008-( ) SOFTWARE EFD1000-500 IOP 302-00007-( ) SOFTWARE EFD1000-500 MAP 910-00001-001 DISPLAY w/ Internal Battery 910-00005-004 Configuration Module 300-00001-004 CM IMAGE PILOT 910-00003-001 RSM w/GPS, TOP MOUNT 910-00003-002 RSM w/o GPS, TOP MOUNT 910-00003-003 RSM w/o GPS, BOTTOM MOUNT Pick one RSM Figure 1.2 – EFD1000 PFD PILOT Authorized System Components DOCUMENT # 900-00003-001 PAGE 16-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 1.3 - EFD1000 MFD Authorized System Components DOCUMENT # 900-00003-001 PAGE 17-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual EFD1000 MFD, TSO Suitable for replacing standby Airspeed and Altimeter 302-00008-( ) SOFTWARE EFD1000-500 IOP 302-00007-( ) SOFTWARE EFD1000-500 MAP 910-00001-002 DISPLAY For use with EBB58 910-00005-004 Configuration Module 300-00001-009 CM IMAGE EFD1000 MFD 910-00003-001 RSM w/GPS, TOP MOUNT 910-00003-002 RSM w/o GPS, TOP MOUNT 910-00003-003 RSM w/o GPS, BOTTOM MOUNT Pick one RSM 413-00002-001 EBB58 Battery 903-00006-001 EBB58 Install Kit Figure 1.4 - EFD1000 MFD Authorized System Components (Suitable for replacing standby AS/ALT) DOCUMENT # 900-00003-001 PAGE 18-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 1.5 - EFD500 MFD Authorized System Components 1.2 Installation Kit Contents Aspen P/N Description Manufacturer’s P/N or equivalent A-08-125-00 403-00002-001 Panel Mounting Bracket Assembly Aspen A-06-564-00 116-00022-002 44 Pin HD D-Sub connector with contacts Positronics P/N DD44F10000 116-00026-001 EMI Metal Back shell Positronics P/N D25000GE0 A-06-507-00 275-00001-002 Pitot Quick Connector Aspen A-06-505-00 275-00001-001 Static Quick Connector Aspen A-08-144-00 412-00004-001 Configuration Module Cable Assembly Aspen 903-00007-001 EFD Recess Mount Installation Kit (optional– use Aspen Service Bulletin SB2009-03 for installation) Aspen Table 1.3 - 903-00001-001 or A-08-130-00 EFD1000 Install Kit DOCUMENT # 900-00003-001 PAGE 19-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Aspen P/N Description Manufacturer’s P/N or equivalent A-08-125-00 403-00002-001 Panel Mounting Bracket Assembly Aspen 116-00022-002 44 Pin HD D-Sub connector with contacts Positronics P/N DD44F10000 116-00026-001 EMI Metal Back shell Positronics P/N D25000GE0 A-08-144-00 412-00004-001 Configuration Module Cable Assembly Aspen Table 1.4 – 903-00004-001 or A-08-149-00 EFD500 Install Kit Aspen P/N Description Manufacturer’s P/N or equivalent A-08-148-00 412-00005-001 RSM 30ft cable assembly w/connector (optional) Aspen 201-00004-001 Screw, Machined, Pan, Phillips, Brass,8- 32 11/4”, Qty (4) req. MS35214-47 212-00001-001 Nut, Hex, Locking, Nylon Insert, Brass, 8- 32, Qty (4) req. MS21044B08 231-00001-001 Washer, Flat, #8, Brass, 11/64” ID, 3/8” OD, Qty (4) req. NAS1149B0832H 256-00001-001 O-Ring AS568A-120 116-00020-001 Connector, Threaded plug, In-Line, Male 7-pin Hirose SR30-10PF-7P(71) Table 1.5 - 903-00002-001 or A-08-131-00 RSM Install Kit Aspen P/N Description Manufacturer’s P/N (or equivalent) A-06-570-00 116-00014-001 15 pin D-Sub connector AMP P/N 205163-1 A-06-571-00 116-00014-002 25 pin D-Sub connector AMP P/N 205165-1 A-06-572-00 116-00014-003 37 pin D-Sub connector AMP P/N 205167-1 A-06-408-00 116-00026-002 DB15 pin EMI Back shell NorComp 970-015-030R121 A-06-409-00 116-00026-003 DB25 EMI Back shell NorComp 970-025-030R121 A-06-410-00 116-00026-005 DB37 EMI Back shell NorComp 970-037-030R121 A-06-574-00 116-00037-001 Crimp Sockets (77) Positronics P/N FC6020D Table 1.6 - 903-00003-001 or A-08-132-00 ACU Install Kit DOCUMENT # 900-00003-001 PAGE 20-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1.3 Accessories Required but Not Supplied – EFD1000 PFD Description Manufacturer’s P/N Tee Fittings for pitot/static (2 req.) Thogus Products P/N TT-9444 (1/4) or equiv. 1/4” pitot and static tubing Imperial Eastman 44PN or equivalent Circuit Breaker pull to open (EFD1000) 7.5 amp MS 26574-7.5 or equivalent Circuit Breaker (ACU) 2 amp (1 for each ACU) MS26574-2 or equivalent EFD to GPS/ACU double shielded cable M27500-22TG2V64 or equivalent Hose Clamps (8 req) Aero Seal 6604 or equivalent Single stranded 24, 22, 20 AWG MIL-W-22759/16 or equivalent Shielded Wire 22 AWG MIL-C-27500 or equivalent EFD Mounting Screws #6-32, 6ea. MS24693-S30 or equivalent EFD and ACU Mounting Lock Nuts #6-32 MS21044N06 or equivalent EFD and ACU Mounting Washers NAS1149FN632P or equivalent ACU mounting Screw #6-32 MS35206-XXX or equivalent Misc. screws, washers, cable ties, etc. Installer supplied Table 1.7 – PFD Accessories Required but Not Supplied 1.4 Optional Accessories Not Supplied – EFD1000 PFD Description Manufacturer Sonalert (continuous type) Mallory SC648S or equivalent EFIS Master switch –rated for 7.5 amps cont. MS35058-22 or equivalent SPST switch Circuit Breaker/Switch 7.5amp (optional – in lieu of separate C/B and switch) Potter Brumfield W31M-7.5 or equivalent *Over Braid – light weight *Over Braid – medium weight *used in lieu of double shielded wire Alpha Wire P/N 2142 (1/4”), P/N 2146 (1/2”) Daburn P/N 2350-X, X=diameter (i.e., 1/2) RSM Doubler Installer fabricated per Section 6.9.5 RSM Shim – may be required on extreme mounting angles Installer fabricated per Section 6.9.9 RSM sealant non-pressure vessel mounting MIL-A-46146, Dow 738 or equiv. 7 conductor shielded cable, for installer fabricated harness using 116-00020-001 connector. M27500-A24SD7T23/ M27500-22TG7T14 or equivalent Table 1.8 – PFD Optional Accessories Not Supplied DOCUMENT # 900-00003-001 PAGE 21-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1.5 Optional Accessories Required but Not Supplied – EFD1000 MFD Description Manufacturer Tee Fittings for pitot/static (2 req) Thogus Products P/N TT-9444 (1/4x1/4x1/4) or equivalent 1/4” pitot and static tubing Imperial Eastman 44PN or equivalent Hose Clamps (8 req) Aero Seal 6604 or equivalent MFD Master switch – rated for 7.5A continuous MS35058-22 or equivalent SPST switch Circuit Breaker/Switch 7.5A (optional – in lieu of separate C/B and switch) Potter Brumfield W31M-7.5 or equivalent See RSM items in Table 1.3 and 1.4 EFD Mounting Screws #6-32, 6ea. MS24693-S30 or equivalent EFD Mounting Lock Nuts #6-32, 6ea. MS21044N06 or equivalent EBB Emergency Disconnect Switch – Locking Toggle Switch (used when EBB58 is installed) MS24658-22D or equivalent SPST switch. (required for EBB emergency disconnect) See Section 7.2 for labeling EBB Emergency Disconnect Switch & Switch Guard (option to locking toggle switch above) Switch – MS35058-22 or equivalent, SPST Guard - MS25224-1 or equivalent, capable of locking in an open position. Table 1.9 - EFD1000 MFD Optional Accessories Required but Not Supplied 1.6 Optional Accessories Required but Not Supplied – EFD500 MFD Description Manufacturer MFD Master switch –rated for 5A-7.5A cont. MS35058-22 or equivalent SPST switch Circuit Breaker EFD500 5A – 7.5A MS26574-5 or MS26574-7.5 or equiv. Circuit Breaker/Switch 5A -7.5A (optional – in lieu of separate C/B and switch) Potter Brumfield W31M-5 or W31M-7.5 or equivalent EFD Mounting Screws #6-32, 6ea. MS24693-S30 or equiv. EFD Mounting Lock Nuts #6-32, 6ea. MS21044N06 or equiv. Table 1.10 - EFD500 MFD Optional Accessories Required but Not Supplied 1.7 MFD Database Versions Database Part Number Database Coverage 430-00001-001 Americas - MicroSD Card with Jeppesen Data 430-00001-002 International - MicroSD Card with Jeppesen Data Table 1.11 - MFD Database Versions DOCUMENT # 900-00003-001 PAGE 22-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1.8 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 -ACU Positronics P/N M81969/1-01 or equivalent - PFD 1.9 Vendor Information Aspen Avionics Inc. EDMO Distributors, Inc – Wire, Cable, Sonalert 5001 Indian School Road NE 12830E Mirabeau Pkwy Albuquerque, NM 87110 Spokane Valley, WA 99216 (505) 856-5034 (800) 235-3300 [email protected] [email protected] A.E. Petsche Co. – Double Shielded & RSM Cable Jeppesen – JSUM Application Help 2112 West Division St. JSUM – Jeppesen Services Update Mgr Arlington, TX 76012-3693 (800) 732-2800 (817) 461-9473 (303) 328-4587 [email protected] [email protected] Positronic Industries Inc. - Crimpers Jeppesen – Database Accounts/passwords 423 N. Campbell Ave. -Connectors Customer Service Springfield, MO 65801 (800) 621-5377 (417) 866-2322 (303) 799-9090 [email protected] [email protected] 1.10 Warranty Registration 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 EFD1000/500 system is just one important aspect of providing a satisfying installation experience for our customers. 1.11 Regulatory Compliance 1.11.1 Technical Standard Order All components of the EFD1000/500 system are produced under Technical Standard Order Authorization (TSOA). DOCUMENT # 900-00003-001 PAGE 23-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1.11.2 Software Certification The software for the EFD1000/500 system was developed to RTCA DO-178B software Level C. The RSM GPS receiver software was developed to RTCA DO-178B level E. The RSM GPS is approved for emergency use only. 1.11.3 Environmental Compliance All system components meet the categories of RTCA/DO-160E as shown in the environmental qualification forms in Section 13. 1.11.4 Installation Approval Installation of the EFD1000 PFD and EFD1000 MFD and/or EFD500 MFD is FAA approved under AML STC SA10822SC. This installation manual contains FAA Approved Data, but only when used to install the Aspen Avionics EFD1000 and/or EFD500 display systems in accordance with this AML STC. The data in this manual may be used only by Authorized Aspen Avionics Dealers, and then only to support installation of the EFD1000 and/or EFD500, either under STC SA10822SC, or as a follow-on field approval for aircraft not included in the Approved Model List. Use of this data for any other purpose requires separate written approval from Aspen Avionics Inc. DOCUMENT # 900-00003-001 PAGE 24-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2 Equipment Specifications and Limitations 2.1 EFD1000 PFD and MFD 2.1.1 General Specifications Part Number .............................. 910-00001-001, 910-00001-002 Width/Height............................. 3.50 in./7.00 in. (Measured at Bezel) Can Depth................................. 4.15 in. (Rear of Bezel to Rear of Can) Overall Depth ............................ 6.35 in. (Knob to Rear Pressure Fitting) Weight....................................... 2.9 lbs with bracket (-002 part number is 2.1 lbs) Display Type.............................. 6.0 in. Diagonal TFT Active Matrix LCD (400x760) Display Colors ........................... 32,768 Face .......................................... Anti-Reflective Coated Glass Backlight ................................... High Intensity White LED Rotary Knobs............................. Optical Encoder with Momentary Push Dimming ................................... Manual & Automatic (Front Bezel Mounted Sensor) 2.1.2 Operational Specifications: Operating Temp: ...................... -20°C to +55°C Storage Temp: .......................... -55°C to +85°C Max Operating Altitude.............. 35,000 ft Unpressurized/ 55,000 ft Pressurized Cooling ..................................... Integral Fan Max Humidity............................ 95% at 50°C Input Voltage............................. +9 to +32 VDC (Note: Input power must transition >11VDC to turn on the unit) Nominal Current ........................ 2.4/4.8 Amps (28v/14v) 2.1.3 I/O Specifications: ARINC 429 Inputs ...................... 5 Low/High Speed ARINC 429 Outputs ................... 1 Low Speed RS-232 Inputs ........................... 5 RS-232 Outputs ........................ 3 Pitot / Static .............................. Quick Connect 2.1.4 Certification Specifications: Technical Standard Order (EFD1000): TSO-C2d .................................. Airspeed Instruments TSO-C3d .................................. Turn and Slip Instrument TSO-C4c .................................. Bank and Pitch Instruments TSO-C6d .................................. Direction Instrument Magnetic (Gyroscopically Stabilized) DOCUMENT # 900-00003-001 PAGE 25-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual TSO-C8d .................................. Vertical Velocity Instrument (Rate-of-Climb) TSO-C10b ................................ Altitude Pressure Activated Sensitive Type TSO-C106 ................................ Air Data Computer TSO–C113 ................................ Airborne Multipurpose Electronic Display Software: RTCA DO-178B ......................... Level C Environmental: RTCA DO-160E.......................... See Environmental Qualification Form Section 13 2.1.5 Outline Drawing: Figure 2.1 – EFD1000 Outline Drawing (inches) Not shown: The EFD1000 -002 variant with D-connector for the EBB DOCUMENT # 900-00003-001 PAGE 26-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.2 EFD500 MFD 2.2.1 General Specifications Part Number ........................ 910-00001-003 Width .................................. 3.50 in. (Measured at Bezel) Height ................................. 7.00 in. (Measured at Bezel) Can Depth........................... 4.15 in. (Rear of Bezel to Rear of Can) Overall Depth ...................... 5.70 in. (Knob to Rear of Can) Weight................................. 2.4 lbs with bracket Display Type........................ 6.0 in. Diagonal TFT Active Matrix LCD (400x760) Display Colors ..................... 32,768 Face .................................... Anti-Reflective Coated Glass Backlight ............................. High Intensity White LED Rotary Knobs....................... Optical Encoder with Momentary Push Dimming ............................. Manual & Automatic (Front Bezel Mounted Sensor) 2.2.2 Operational Specifications Operating Temp: ................ -20°C to +55°C Storage Temp: .................... -55°C to +85°C Max Operating Altitude........ 35,000 ft Unpressurized/ 55,000 ft Pressurized Cooling ............................... Integral Fan Max Humidity...................... 95% at 50°C Input Voltage....................... +9 to +32 Volts DC (Note: Input power must transition >11VDC to turn on the unit) Nominal Current.................. 0.8/1.6 Amps (28v/14v) 2.2.3 I/O Specifications ARINC 429 Inputs ................ 5 Low/High Speed ARINC 429 Outputs ............. 1 Low Speed RS-232 Inputs ..................... 5 RS-232 Outputs .................. 3 Pitot / Static ........................ N/A 2.2.4 Certification Specifications Technical Standard Order: TSO–C113 .......................... Airborne Multipurpose Electronic Display Software: RTCA DO-178B Level C Environmental: RTCA DO-160E See Environmental Qualification Form Section 13 DOCUMENT # 900-00003-001 PAGE 27-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.2.5 EFD500 Outline Drawing Figure 2.2 – EFD500 Outline Drawing (inches) 2.2.6 Design Eye Viewing Envelope The following information defines the viewing envelope within which the EFD1000 and EFD500 comply with the equipment standards: Minimum and maximum distance from the center of the EFD display surface: 10 inches (25.4 cm) minimum to 45 inches (114.3 cm) maximum Total viewing angles: From -30º to +30º (left/right), and +30º to -30º (top/bottom) perpendicular to the EFD front glass surface. DOCUMENT # 900-00003-001 PAGE 28-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.3 Remote Sensor Module (RSM): There are three versions of the Remote Sensor Module. One is designed for top mounting and contains the emergency GPS, the second is also designed for top or internal mounting and does not include the emergency GPS. The third version is designed for bottom or internal mounting and does not include the emergency GPS. 2.3.1 General Specifications Part Number .............................. A-05-111-00 or 910-00003-001 (RSM with GPS) ................................................. 910-00003-002, (RSM, top mount, no GPS) ................................................. 910-00003-003 (RSM, bottom mount, no GPS) Width ........................................ 2.65 in. (Measured at Base) Height ....................................... 1.00 in. (Measured from Base) Length....................................... 4.40 in. (Front to Rear) Weight....................................... 0.2 lbs 2.3.2 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 Max Humidity............................ 95% at 50°C Input Voltage............................. Provided by EFD Nominal Current ........................ Included in EFD Current 2.3.3 I/O Specifications: Magnetometer ........................... Proprietary Digital OAT........................................... Proprietary Digital GPS ........................................... Proprietary Digital 2.3.4 Certification Specifications: The RSM is certified as a component of the EFD1000 system Software: RTCA DO-178B ......................... Level E Environmental: RTCA DO-160E.......................... See Environmental Qualification Form Section 13 DOCUMENT # 900-00003-001 PAGE 29-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.3.5 Outline Drawing: Figure 2.3 - RSM Outline Drawing (inches) 2.4 Configuration Module (CM) For EFD1000/500 systems using Software Version 2.X, there is a single hardware part number Configuration Module, which is then loaded with the appropriate configuration settings image file that established the functionality and feature set of the attached EFD1000 or EFD500 system. 2.4.1 General Specifications Part Number .............................. A-05-114-00 (Original CM for Pro) ................................................. A-05-113-00 (Original CM for Pilot) ................................................. 910-00005-004 (common CM for Version 2.X software) Width ........................................ 1.0 in. Height ....................................... 0.55 in. Length....................................... 1.85 in. Weight....................................... 0.1 lbs DOCUMENT # 900-00003-001 PAGE 30-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.4.2 Operational Specifications: Operating Temp: ...................... -20°C to +55°C Storage Temp: .......................... -55°C to +85°C Max Operating Altitude.............. 35,000 ft Unpressurized/ 55,000 ft Pressurized Cooling ..................................... none required Max Humidity............................ 95% at 50°C Input Voltage............................. Provided by EFD Nominal Current ........................ Included in EFD Current 2.4.3 I/O Specifications: Proprietary digital 2.4.4 Certification Specifications: The Configuration Module is certified as a component of the EFD1000/500 system Environmental: RTCA DO-160E.......................... See Environmental Qualification Form Section 13 2.4.5 Outline Drawing Figure 2.4 - Configuration Module Outline Drawing (inches) DOCUMENT # 900-00003-001 PAGE 31-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.5 Analog Converter Unit (ACU): 2.5.1 General Specifications Part Number .............................. A-05-112-00, 910-00004-001 (These part numbers are equivalent) Width ........................................ 5.75 in. including mounting flanges Height ....................................... 1.60 in. Length....................................... 4.30 in. Weight....................................... 0.8 lbs 2.5.2 Operational Specifications: Operating Temp: ...................... -40°C to +55°C Storage Temp: .......................... -55°C to +85°C Max Operating Altitude.............. 35,000 ft Cooling ..................................... none required Max Humidity............................ 95% at 50°C Input Voltage............................. +11 to +32 VDC Nominal Current ........................ 0.5/1.0 Amps (28v/14v) 2.5.3 I/O Specifications: ARINC 429 Inputs ...................... 2 Low Speed ARINC 429 Outputs ................... 2 Low Speed RS-232 Inputs ........................... 1 (software loading only) VHF Nav Receiver....................... 1 Analog input GPS Receiver.............................. 1 Analog input GPS OBS Interface ...................... 1 Output GPS Discrete.............................. 4 Active low inputs DH Discrete ............................... 1 Active low input Flight Director ........................... 1 input port Autopilot Interface..................... 1 Analog port 2.5.4 Certification Specifications: The ACU is certified as a component of the EFD1000 system Environmental: RTCA DO-160E.......................... See Environmental Qualification Form Section 13 DOCUMENT # 900-00003-001 PAGE 32-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 2.5.5 Outline Drawing: Figure 2.5 - ACU Outline Drawing (inches) 2.6 EBB58 Emergency Backup Battery The EBB58 can only be installed with an EFD1000 MFD. 2.6.1 General Specifications Part Number .............................. 413-00002-001 Width ........................................ 3.6 in. (widest point on mounting clips) Height ....................................... 1.7 in. Length....................................... 8.52 in. (rear of mounting tray to connector) Weight....................................... 2.25 lbs (includes bracket) 2.6.2 Operating Specifications Operating Temp: ...................... -20°C to +55°C DOCUMENT # 900-00003-001 PAGE 33-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Storage Temp: .......................... -55°C to +85°C Max Operating Altitude ............. 35,000 ft Unpressurized/ 55,000 ft Pressurized Cooling..................................... None required Max Humidity............................ 95% at 50°C Input Voltage ............................ Powered by EFD1000 Nominal Current ....................... Powered by EFD1000 2.6.3 I/O Specifications Proprietary 2.6.4 Certification Specifications: The EBB58 is certified as a component of the EFD1000 system Environmental: RTCA DO-160E.......................... Contained within the EFD1000 Environmental Qualification Form. See Section 13 2.6.5 Outline Drawing Figure 2.6 – EBB58 Outline Drawing (inches) DOCUMENT # 900-00003-001 PAGE 34-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 3 System Description The Aspen Avionics EFD1000 and EFD500 systems are multi-purpose displays. The EFD1000 contains an internal 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 and the EFD500 come standard with an internal battery to provide a nominal 30 minute operation in the event of power loss. These batteries are not designed to provide 30 minute operation under all foreseeable operating conditions, such as extreme cold temperatures where battery operation is not assured. An optional 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 a PFD is installed, and the Emergency Backup Battery is connected to an EFD1000 MFD, the legacy standby altimeter and airspeed indicators may be removed from the aircraft. 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, the Aspen EWR50 XM weather receiver, WX-500 Stormscope, GTX330 and certain other ARINC 735A protocol TAS and TCAS I systems. The EFD1000 system can be configured as a PFD or MFD. In the PFD 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. The Pro System can display WX-500 data, XM datalink weather products and traffic information from ARINC 735 compatible traffic systems. The Pilot System provides a moving map; however it does not provide an HSI or second GPS navigation. 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. 3.1 EFD1000/EFD500 The EFD1000/EFD500 are digital systems that consists of a high resolution 6” diagonal color LCD display, user controls, photocell and Micro SD data card slot. The rear portion of the EFD1000 includes a non-removable electronics module which contains a full air data computer, attitude heading reference system, power supplies, backup battery, and dual processor electronics. Also on the rear of the unit, a fan is provided to cool the backlight and electronics. The EFD500 does not contain an air data computer or attitude heading reference system. DOCUMENT # 900-00003-001 PAGE 35-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The EFD1000/500 mounts to the front surface of most instrument panels. The electronics module and cooling fins on the back are sized to fit into existing instrument panel holes. A recess-mount bracket is available to mount the displays nearly flush with the instrument panel. The mechanical design allows the instrument to be installed in a vertically oriented pair of instrument openings, without interfering with the surrounding instruments. The installation requires minimal mechanical modifications to most general aviation aircraft instrument panels. The EFD1000 and EFD500 contain a microSD card port and reader at the bottom of the display bezel. When authorized, software updates and system upgrades can be installed using the card port. The port is also used for database information in the EFD1000 MFD and EFD500 MFD. Figure 3.1 – EFD1000 in a PFD view The EFD1000 is a digital system and supports both ARINC 429 and RS-232 digital interfaces. In installations with a modern digital radio installation, the PFD connects directly to the interfaced equipment. In installations that require interfaces to analog avionics (i.e., older VLOC navigation radios and autopilots) an ACU is required to digitize the analog signals into ARINC 429 for the PFD. The EFD1000 and EFD500 can be installed in the following configurations: • EFD1000 configured as a PFD Pro or Pilot DOCUMENT # 900-00003-001 PAGE 36-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual • PFD Pro plus EFD1000 configured as an MFD • PFD Pro plus EFD500 configured as an MFD • PFD Pro plus EFD1000 and EFD500, each configured as MFDs The MFDs are connected to the PFD and each other via an RS-232 digital cross- communications bus. NOTE: Version 1.X PFD is not compatible with the Version 2.X MFD. To be used in a multi- display configuration, the PFD must be upgraded to Version 2.X. 3.2 Remote Sensor Module (RSM) The RSM is required for each EFD1000 and connects directly to the display. It physically resembles a traditional GPS antenna and follows the industry standard mounting hole pattern. The RSM contains all of the sensors that must be remotely located from the PFD display unit. Certain versions of the RSM can be installed on the underside of the aircraft or internally. 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 (RSM GPS version) • Magnetic “flux” sensors All RSM versions must be mounted in a magnetically quiet environment. The emergency GPS version of the RSM is mounted in an area that will provide acceptable reception for the integral GPS antenna. The versions that do not have GPS can be mounted internally to the fuselage or wing structure, or in the case of the bottom-mount RSM, on the underside of the aircraft. Internally mounting the RSM requires disabling of the OAT on the associated EFD. This will also disable TAS and calculated winds for the associated PFD display. There are three versions of RSM: • Top Mount with Emergency Backup GPS • Top Mount without Emergency Backup GPS • Bottom Mount without Emergency Backup GPS CAUTION: Do not mount an RSM made for inverted operation on the top of the aircraft as reverse magnetic sensing will result, producing unacceptable AHRS performance. DOCUMENT # 900-00003-001 PAGE 37-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 3.3 Configuration Module (CM) The Configuration Module retains system configuration settings and calibration data. The Configuration Module connects to the EFD1000/500 through a short fabricated harness and is fastened to the main wiring bundle of the display. Each display has an associated Configuration Module that retains that display’s aircraft specific configuration, calibration data and user settings. This scheme permits the display hardware to be replaced without re-entering the installation settings or re-calibrating the EFD. 3.4 Analog Converter Unit (ACU) The optional Analog Converter Unit (ACU) provides compatibility with older, analog-based avionics when required. The ACU converts and concentrates multiple analog interfaces to digital signals supported by the EFD1000. Control parameters, such as desired heading and selected course, are also sent from the PFD to the ACU for conversion to analog format for autopilot support. The feature set of the “Pilot” system does not support interface to navigation equipment, and therefore does not support the ACU interface. The ACU is required when any of the following capabilities are required in a “Pro” installation: • Interface to supported autopilots • Interface to supported non-ARINC 429 VLOC navigation radios • Interface to supported non-ARINC 429 GPS navigators • Interface to supported radar altimeter decision height (discrete) If digital radios (i.e., Garmin 4XX/5XX series radios) are equipped in the aircraft and no other aircraft interfaces are to be used, then the ACU is not required. DOCUMENT # 900-00003-001 PAGE 38-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 3.5 System Architecture The system architecture in Figure 3.2 shows the relationships of a single EFD1000 with its associated RSM, Configuration Module and ACU. The EFD500 is identical to the EFD1000 but without the pitot/static, RSM, autopilot, tone generator, and DH connections. EFD-1000 PFD (Primary Flight Display) Existing Aircraft Pitot Line P i t o t Existing Aircraft Static Line S t a t ic Digital VLOC/GPS Sources ARINC 429 SPI Discrete I2C Analog Converter Unit (ACU) Analog NAV Sources AutoPilot Configuration Module Remote Sensor Module (RSM) Optional Tone Generator RS-232 Legacy GPS RS-232 Aircraft Power Radar Altimeter Digital GPS/VLOC (Optional) Analog GPS/ VLOC via ACU (Optional) WX-500 EWR50 XM Weather Traffic ARINC 429 RS-232 RS-232 Figure 3.2 - EFD1000 Single PFD System Architecture NOTE: The ARINC 429 data bus between the ACU and the EFD1000 contain proprietary data labels. Connecting other systems to this bus is not authorized as the other systems may incorrectly decode the data. DOCUMENT # 900-00003-001 PAGE 39-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual THIS PAGE IS INTENTIONALLY LEFT BLANK DOCUMENT # 900-00003-001 PAGE 40-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4 Supported Installed Configurations 4.1 Single Display Configurations The following diagrams show the different options for integrating the PFD and MFD with existing avionics in the installed fleet. Most common digital VLOC radios (such as the Garmin 4xx/5xx series), and “analog” VLOC radios are supported. The following diagrams show common installation configurations, but do not represent all possible combinations. 4.1.1 Pilot Configurations The following configurations show a basic Pilot installation. The Pilot model does not support the display of 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 # 900-00003-001 PAGE 41-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4.1.2 Pro Digital Configuration The following configuration shows a Pro Digital installation, without an advanced autopilot and flight director. No ACU is required for this installation. This installation would be used when there is no analog VLOC receiver and the autopilot L/R input is dedicated to the GPS. The PFD navigation source selection has no control over the autopilot input. Dual digital radios may also be connected with or without a “Tracker” autopilot. Tracker autopilots that use L/R steering can also be wired to an ACU so that the PFD displayed navigation source L/R output is switched to the autopilot. These installations are connected as shown in Figure 4.3. Figure 4.2 – Pro Digital Configuration DOCUMENT # 900-00003-001 PAGE 42-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4.1.3 Pro Configurations with Autopilot The following configurations show Pro installations with autopilot integration, but without analog VLOC interfaces. A backup means of navigation is required in single display installations where there is no integral CDI or moving map display on the GPS receiver or VLOC receiver. There must be one means of navigation available to the pilot in the event of a PFD or ACU failure. Figure 4.3 – Pro Configurations with Autopilot DOCUMENT # 900-00003-001 PAGE 43-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4.1.4 Pro Configuration with Autopilot and Digital/Analog VLOC The following configuration shows a Pro installation with autopilot integration, a single digital VLOC/GPS, a single analog VLOC, and a single RS-232/ analog GPS. A backup Navigation indicator is required in single-display installations where there is no integral CDI or moving map display on the GPS receiver or VLOC receiver. There must be one means of navigation available to the pilot in the event of a PFD or ACU failure. Figure 4.4 - Pro Configuration with AP and VLOC DOCUMENT # 900-00003-001 PAGE 44-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4.1.5 Pro Configuration with Autopilot and Dual Analog VLOC The following configuration shows a Pro installation with autopilot integration and dual analog VLOC interfaces. Two ACUs are required for this installation. A backup means of navigation is required in single-display installations where there is no integral CDI or moving map display on the GPS receiver or VLOC receiver. There must be one means of navigation available to the pilot in the event of a PFD or ACU failure. Figure 4.5 - Pro Configuration with AP and Dual VLOC DOCUMENT # 900-00003-001 PAGE 45-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4.2 Two Display System - PFD with EFD1000 or EFD500 MFD The following configuration shows an EFD1000 PFD Pro and an EFD1000 MFD or EFD500 MFD interfaced with optional traffic, XM weather, and the WX-500 Stormscope. Any combination of these sensors may be connected as well as the required RS-232 or ARINC 429 connections from a GPS receiver and or VLOC receiver for navigation, flight plan and moving map. The MFD1000 supports the reversion of PFD functions in the event of a PFD failure. The EFD1000 MFD with Emergency Backup Battery authorizes removal of legacy standby indicators for airspeed and altitude. P i t o t S t a t i c 4 2 9 R X 1 4 2 9 R X 2 4 2 9 R X 3 4 2 9 R X 4 4 2 9 R X 5 R S 2 3 2 R X 3 R S 2 3 2 R X 2 R S 2 3 2 R X 0 4 2 9 T X 1 R S 2 3 2 R X 4 R S 2 3 2 T X 2 R S 2 3 2 T X 0 D i g i t a l O u t 4 2 9 R X 1 4 2 9 R X 2 4 2 9 R X 3 4 2 9 R X 4 4 2 9 R X 5 R S 2 3 2 R X 3 R S 2 3 2 R X 2 R S 2 3 2 R X 0 4 2 9 T X 1 R S 2 3 2 R X 5 R S 2 3 2 T X 3 R S 2 3 2 T X 2 R S 2 3 2 T X 0 D i g i t a l O u t R S 2 3 2 R X 1 R S 2 3 2 R X 1 R S 2 3 2 T X 1 Figure 4.6 - Two Display System PFD/MFD DOCUMENT # 900-00003-001 PAGE 46-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 4.3 Three Display System - PFD with EFD1000 MFD and EFD500 MFD The following configuration shows an EFD1000 PFD Pro, an EFD1000 MFD, and an EFD500 MFD interfaced with optional traffic, XM weather, and the WX-500 Stormscope. Any combination of these sensors may be connected as well as the required RS-232 or ARINC 429 connections from a GPS receiver and or VLOC receiver for navigation, flight plan and moving map. The EFD1000 MFD supports the reversion of PFD functions in the event of a PFD failure. The EFD1000 MFD with Emergency Backup Battery in this configuration authorizes removal of legacy standby indicators for airspeed and altitude. P i t o t S t a t ic P i t o t S t a t ic 4 2 9 R X 1 4 2 9 R X 2 4 2 9 R X 3 4 2 9 R X 4 4 2 9 R X 5 R S 2 3 2 R X 3 R S 2 3 2 R X 0 4 2 9 T X 1 R S 2 3 2 R X 4 R S 2 3 2 R X 5 R S 2 3 2 T X 2 R S 2 3 2 T X 0 D ig it a l O u t 4 2 9 R X 1 4 2 9 R X 2 4 2 9 R X 3 4 2 9 R X 4 4 2 9 R X 5 R S 2 3 2 R X 3 R S 2 3 2 R X 0 R S 2 3 2 R X 4 R S 2 3 2 R X 5 R S 2 3 2 T X 3 R S 2 3 2 T X 2 R S 2 3 2 T X 0 D ig it a l O u t 4 2 9 R X 1 4 2 9 R X 2 4 2 9 R X 3 4 2 9 R X 4 4 2 9 R X 5 R S 2 3 2 R X 3 R S 2 3 2 R X 4 R S 2 3 2 R X 5 R S 2 3 2 T X 2 D ig it a l O u t R S 2 3 2 R X 1 R S 2 3 2 R X 1 R S 2 3 2 R X 1 R S 2 3 2 T X 1 Figure 4.7 - Three Display System PFD/MFD1000/MFD500 DOCUMENT # 900-00003-001 PAGE 47-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual THIS PAGE IS INTENTIONALLY LEFT BLANK DOCUMENT # 900-00003-001 PAGE 48-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5 Pre-Modification Planning General Limitations NOTE: The installer must provide the aircraft operator with copies of wiring diagrams (copy from Section 9 or draft ones not shown) and equipment locations (completed Figure D1 in the ICA’s) that are suitable for system troubleshooting. This section contains requirements that must be considered before installing the EFD1000/EFD500 systems. The EFD1000 MFD with the Emergency Backup Battery (must be installed with an EFD1000 PFD) can be used to replace the standby airspeed and altimeter. There are important limitations. See below. A standby attitude indicator is always required in accordance with 14CFR 23.1311, except for aircraft limited to VFR. See Section 5.2.8. The following are authorized configurations. Other configurations, such as stand alone MFD installations, are not authorized at this time: Single EFD1000 PFD Requires: Standby Attitude indicator Standby Altimeter Standby Airspeed indicator Magnetic Direction Indicator (compass) Secondary navigation indicator (when required – see section 5.2.4) EFD 1000 PFD and EFD500 MFD Requires: Standby Attitude indicator Standby Altimeter Standby Airspeed Magnetic Direction Indicator (compass) A GPS is required for an EFD500 installation EFD1000 PFD and EFD1000 MFD, or EFD1000 PFD and EFD1000 MFD and EFD500 MFD Requires: Standby Attitude indicator Standby Altimeter Standby Airspeed Magnetic Direction Indicator (compass) IFR GPS connected to each EFD1000 display Alternate Static Source DOCUMENT # 900-00003-001 PAGE 49-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The mechanical standby altimeter and airspeed indicator can be replaced by the EFD1000 MFD when the Emergency Backup Battery is installed with the EFD1000. EFD1000 PFD and EFD1000 MFD with Emergency Backup Battery, or EFD1000 PFD and EFD500 MFD and EFD1000 MFD with Emergency Backup Battery Requires: Standby Mechanical*Attitude indicator Magnetic Direction Indicator (compass) IFR GPS connected to each EFD1000 display Alternate Static Source Emergency Backup Battery with adequate level of charge, checked before each departure Instrument Panel Placard installed reading “EMER BAT DISPATCH LIMIT 80% - SEE EFD AFMS” *Note: This configuration has been FAA approved under an Equivalent Level of Safety and requires a mechanical standby attitude indicator. Important Limitations associated with backup airspeed and altitude instruments: Your customer must be aware of the limitations associated with replacing the backup altimeter and airspeed indicator. When the EFD1000 MFD with Emergency Backup Battery is used as the backup, the reliability of the aircraft electrical system drives the requirement for a backup battery charge level that will permit operation for at least 30 minutes, even in cold temperatures. This means the Emergency Backup Battery state of charge must be checked before flight, and if the state of charge is less than the percentage prescribed in the AFMS, takeoff is prohibited until the charge level is adequate. The EBB58 may only be installed in a multiple display configuration and may only be connected to the EFD1000 MFD. No other connections are permitted. 5.1 Pre-Modification Checklist Complete Table 5.1 and Table 5.2 (if installing MFD) to insure that the aircraft to be modified is a suitable candidate for installation of the EFD1000 PFD/MFD system(s) 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 is made to that device. Only Items designated with “– NA if no ____ “ may use NA in the PASS column. PRIMARY FLIGHT DISPLAY - PFD ITEM CRITERIA PASS 1 Is the aircraft to be modified on the Approved Model List (AML)? 2 Does aircraft have sufficient electrical capacity to supply all required equipment given the current draw in Table 7.1? 3 Is there an acceptable location to mount or relocate the required standby instruments in the pilot’s field of view? (see Figures 5.3 and 5.4) See the DOCUMENT # 900-00003-001 PAGE 50-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 51-256 Revision G © Copyright 2010 Aspen Avionics Inc. PRIMARY FLIGHT DISPLAY - PFD ITEM CRITERIA PASS beginning of this section to determine the required standby instruments. 4 Do the standby instruments meet the requirements of Figure 5.1 and 5.2? 5 Is there acceptable clearance between the control column (yoke or stick) and the PFD when the flight controls are in the full nose down position. 6 If removing an EFIS system - does the EFD1000 replace all required instrumentation previously displayed on the removed EFIS? - NA if no EFIS 7 Is a backup navigation indicator required (see section 5.2.4) - NA if no Backup NAV indicator is required. If a backup indicator is required, is there an acceptable location to mount or relocate a required backup NAV Indicator in the pilot’s field of view? (see Figure 5.4) 8 Is there an acceptable location to mount the RSM? (see Section 6.9) 9 Is there a location to mount the necessary circuit breakers that will be accessible to the pilot while seated? 10 Are there suitable locations to mount the necessary switches that are accessible to the pilot while seated? – NA if not installed. 11 Does the aircraft have a compatible GPS receiver or will one be installed? (see Electrical Interface Section 8 to determine compatibility) - NA if no GPS interface. 12 Does the aircraft have a compatible Navigation receiver or will one be installed? (see Electrical Interface Section 8 to determine compatibility) - NA if no NAV interface. 13 If the aircraft is equipped with an autopilot – is the Autopilot compatible? (see Electrical Interface Section 8 to determine compatibility) - NA if no autopilot interface. 14 If the aircraft is limited to VFR, is there a placard or equivalent acceptable means, stating “Operation of This Aircraft is Limited to VFR Only”, or similar phraseology acceptable to the FAA, as required by § 23.1525, § 23.1559 and § 91.9. Since the kinds of operations are limited to VFR, this placard or equivalent acceptable means should already be in place, but should be verified. Table 5.1 - PFD Pre-Modification Checklist MULTI FUNCTION DISPLAY - MFD ITEM CRITERIA PASS 1. If an EFD1000 MFD is installed and the standby airspeed and/or altimeter are to be removed, is there an acceptable location to mount the required EBB58 Emergency Backup Battery? NA if no backup instruments removed. 2. If an EFD1000 MFD is installed, does the aircraft have an IFR GPS installed? NA if EFD1000 MFD not installed. 3. If an EFD1000 MFD is installed, does the aircraft have an alternate static source? 4. Does the aircraft have a standby attitude indicator in the pilot’s primary maximum field of view (See Figure 5.3)? 5. If the standby airspeed indicator and altimeter are to be removed, is there an acceptable location to mount the required placard reading “EMER BAT DISPATCH LIMIT 80% - SEE EFD AFMS”? NA if EBB not required to be installed. 6. Is there an acceptable location to mount and label the EBB emergency disconnect EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 52-256 Revision G © Copyright 2010 Aspen Avionics Inc. MULTI FUNCTION DISPLAY - MFD ITEM CRITERIA PASS switch? NA if EBB not required to be installed. 7. Does aircraft have sufficient electrical capacity to supply all required equipment given the current draw in Table 7.1? 8. Is there an acceptable location to mount or relocate the required standby airspeed and altitude instruments, collocated with the standby attitude indicator, all within the pilot’s primary maximum field of view? (see Figure 5.3 and 5.4) 9. Do the standby instruments meet the requirements of Figure 5.1 and 5.2? 10. Is there acceptable clearance between the control column (yoke or stick) and the MFD(s) when the flight controls are in the full nose down position? 11. Is there an acceptable location to mount the EFD1000 MFD RSM? (see Section 6) - NA if EFD500 only installation 12. Is there a location to mount the MFD circuit breaker(s) that will be accessible to the pilot while seated? 13. Is there a location to mount the MFD switch(s) that is accessible to the pilot while seated? Table 5.2 - MFD Pre-Modification Checklist 5.2 Limitations Software Version Multiple display configurations must use EFD1000/500 MAP and IOP software version 2.0, or later FAA approved version. All displays in a multi-display arrangement must be at the same software revision level. General Standby Instrument Requirements FAR 23.1311(a)(5) requires that independent secondary instruments be installed (existing units may be relocated) for Attitude, Altitude, Airspeed, and magnetic direction indicator “whisky compass” when an Electronic Display (i.e., EFD1000) is used as the primary instrument. These instruments are collectively and individually referred to as “standby instruments” throughout this document. IFR certificated Part 23 aircraft that do not have an existing attitude Indicator must install a standby attitude indicator along with the PFD as required by FAR 23.1311(a)(5). In accordance with FAA Policy, the secondary attitude indicator requirement of FAR 23.1311 (a)(5) does not always apply to aircraft limited to VFR. See Section 5.2.8, Special Considerations for Aircraft Limited to VFR. The existing outside air temperature probe (if installed) and magnetic direction indicator “whisky compass” may not be removed during the installation of the EFD1000 system. EFD1000 and EFD500 SW v2.X Installation Manual The 30 minute, internal battery in the PFD is not approved for use as a power source to meet the electrical power source requirement under 14 CFR 23.1353, or for single engine Part 135 IFR operations under 14 CFR 135.163. Pneumatic Standby Instruments (See Figure 5.1) Aircraft with existing pneumatic attitude, altitude, and airspeed instruments may relocate them as necessary as described in Section 5.2.1. The standby pneumatic airspeed and altimeter should be connected to an independent pitot and static line (independent from PFD) whenever available. 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 following two methods: A) Standby instruments are powered by a dedicated standby battery, separate from the aircraft starter battery, which meets the requirements of FAR 23.1353(h). [Note: The EFD1000 PFD internal battery does not qualify as an independent battery under FAR 23.1353(h)]. B) Dual independent electrical systems (dual alternators and dual batteries) with the PFD on one system and the standby instruments on the other system. The standby, electric attitude indicator must not rely on pitot/static inputs for its operation. Removal of pneumatic standby instruments and installation of electric standby instruments (other than the MFD1000) is not authorized by this STC. Separate installation approval would be required. The installation of dual independent electrical systems or a standby (emergency) aircraft battery is not authorized by this STC. Separate installation approval would be required. The EBB is authorized by this STC. Using EFD1000 MFD as Standby Airspeed and/or Altimeter (see Figure 5.2) The EFD1000 MFD may be used as the required standby airspeed and/or altimeter. If being used as the required standby instrument then the EFD1000 MFD must be connected to the EBB58 Emergency Backup Battery. The placard must be located near the EFD1000 MFD within the pilot’s maximum field of view (see figure 5.3). The placard must be in black and white (white letters on black background or black letters on white background) in a font no smaller than other placards in the aircraft which reads as follows: DOCUMENT # 900-00003-001 PAGE 53-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The placard requires the EBB58 battery capacity to be verified prior to each flight. If the aircraft has dual independent electrical systems then the PFD must be installed on one bus and the EFD1000 MFD must be installed on the other independent bus. If independent buses do not exist then the PFD and MFD are to be installed on the aircraft’s battery bus or essential bus. If the aircraft has dual independent pitot/static systems then the PFD must be installed on one system and the EFD1000 MFD must be installed on the other independent pitot/static system. Some altimeters have outputs for Baro set and encoded altitude to an autopilot pre-selector, transponder, traffic system, or other ancillary equipment. Verify no functions are being eliminated that cannot be replaced from another source (i.e., blind encoder, etc.) prior to removal of existing altimeter from aircraft. NOTE: It is advisable to keep standby instruments when space permits DOCUMENT # 900-00003-001 PAGE 54-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 5.1 –Standby Instrument Power Requirements DOCUMENT # 900-00003-001 PAGE 55-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 5.2 - MFD1000 as Standby Airspeed and/or Altimeter DOCUMENT # 900-00003-001 PAGE 56-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5.2.1 Standby Attitude Positioning The Attitude indicator must be relocated to a position within the pilot’s primary maximum field of view in accordance with FAR 23.1321(a). The requirements are ±35 degrees from the pilot’s center line horizontally (± 21 inches from centerline as defined by AC23-1311-1b) to an area just below the basic T configuration to the glare shield vertically (see Figure 5.3 below). It is recommended that the Standby instruments be mounted in the instrument panel immediately adjacent to the EFD1000/500 displays, but in no case may they be mounted outside the ±35º field of view requirement. NOTE: The standby instruments may be 2 inch instruments if they meet the placement requirements (installed under separate approval). NOTE: The standby instruments must be collocated with each other. One standby instrument cannot be 21 inches to the left of centerline and another 21 inches right of centerline. They must all be in the same region of the panel. Figure 5.3 – Standby Instrument Placement Also note that some attitude indicators (i.e., KI-256) are the primary pitch and roll reference for the autopilot and must remain in the aircraft but may be copilot or blind mounted provided a separate standby attitude indicator is installed in accordance with this section. For rate based autopilots the Turn and Bank Indicator will need to remain in the aircraft, and may be relocated to the copilot side or blind mounted provided it is not used as the autopilot mode controller. If used as the autopilot mode controller then it must be located where it can be easily reached by the pilot while seated. DOCUMENT # 900-00003-001 PAGE 57-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5.2.2 Standby Airspeed and Altimeter Positioning The airspeed indicator and altimeter must be within the pilot’s primary maximum field of view in accordance with FAR 23.1321(a). The requirements are +/- 35 degrees from the pilot’s center line horizontally (+/- 21 inches from centerline as defined by AC23.1311-1b), see Figure 5.4. Single Display Configuration In a single PFD installation the existing airspeed indicator and altimeter may remain in their original location. However, if the original location does not satisfy the basic “T” configuration per FAR 23.1321(d) it is required to “LOCK” the airspeed and altitude tape in the PFD to “ON” via the installation menu. Therefore if the airspeed indicator is not in position (AS) and the altimeter in position (AL) of Figure 5.4 below, then the TAPES must be locked on so that the pilot cannot de-clutter them from the display during flight. Likewise older aircraft panel layouts that do not have the airspeed indicator to the left, or the altimeter to the right of the attitude indicator (AI) must either relocate the instrument(s) to these positions or set the TAPES setting to “LOCK ON” in the installation configuration menu. NOTE: The standby instruments must be collocated with each other. One standby instrument cannot be 21 inches to the left of centerline and another 21 inches right of centerline. They must all be in the same region of the panel. Figure 5.4 – Basic T configuration DOCUMENT # 900-00003-001 PAGE 58-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Multi-Display Configuration In a two or three display configuration (PFD and one or two MFD), in which an MFD is positioned adjacent to the PFD, it is required by this STC for the TAPES to be locked on in the installation menu so that the pilot cannot de-clutter them from display during flight. This requirement is mandatory regardless of whether the EFD1000 MFD or the existing IAS/ALT indicators are being used as the required standby instruments. If an MFD is installed such that separate airspeed and altitude instruments are installed in the basic T arrangement described above, then the PFD tapes may remain unlocked. WARNING: Failure to adhere to these specific instrument layout requirements and EFD1000 configuration requirements will violate the STC. 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. If another device is “bootstrapped” from the compass then it will need to be determined whether RS232 or ARINC 429 heading is accepted by this device and rewired appropriately. If the other device only accepts ARINC 407 synchro heading then it may be necessary to keep the existing compass system in the aircraft and move the indicator to another location. A magnetic direction indicator “whisky compass” or equivalent is required as a secondary direction indicator per FAR 23.1311(a)(5). 5.2.4 Back Up Nav Indicator For certification reasons a backup navigation indicator is required for at least one type of operation for which the aircraft is certificated. This means that in any installation in an aircraft certified for IFR where the EFD1000 is the only display of navigation information in the cockpit, a backup navigation indicator is required. 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. Thus, for example, an installation that includes a panel mount GPS with an integral LCD display that includes a moving map or CDI indicator would not require a backup nav indicator. However, a configuration with no GPS and dual legacy VLOC radios that do not include an integral display with CDI indications will require a backup nav indicator. DOCUMENT # 900-00003-001 PAGE 59-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual In a two or three display configuration the EFD1000 or EFD500 MFD satisfies the requirement for a backup NAV indicator. If there is already a dedicated indicator wired to an existing NAV Receiver or GPS then it can be paralleled to the ACU as shown in Section 9. CNX-80/GNS480 It is not recommended that a backup NAV indicator be connected. If it is desired to connect a backup navigation indicator then it should only be wired to the dedicated VOR Composite output on connector P7. Connecting the NAV indicator to the AUX CDI output on P5 or to the Main Course Deviation output is not recommended. WARNING: Failure to provide a backup NAV indicator when required will violate the STC. 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. GPS Annunciations on PFD (if provided by the GPS): • MSG • WPT • TERM • APPR • INTEG NOTE: It is up to the installer to determine if the annunciations are sufficient for the GPS navigation application. 5.2.6 Aircraft Power Requirements An electrical load analysis must be performed to ensure the installed EFD1000 components do not exceed the current capacity of the aircraft’s charging system (see Section 7.1). The EFD1000 system uses either an internal battery or an EBB58 to permit operation of the EFD1000 during an aircraft charging system failure. If the aircraft bus voltage falls below a nominal 12.3V (14V electrical system) or 24.6V (28V electrical system), and the indicated airspeed is above 30 knots or mph (as configured), the EFD1000 will switch to the internal battery. The installer must ensure that the aircraft electrical system attains the minimum voltage when the electrical system is loaded to flight DOCUMENT # 900-00003-001 PAGE 60-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual configuration and engine RPM is at or above the level necessary for nominal alternator/generator output. The EBB58 may only be installed in a multiple display configuration and may only be connected to an EFD1000 MFD no other connections are permitted. 5.2.7 Equipment Power Requirements For first-time EFD installations, a switch or switch breaker to the PFD and to each MFD must be installed. These controls are used during emergency procedures, and also enable the PFD and MFD(s) to remain off during engine start. It is recommended that previous PFD installations that did not include an EFIS Master switch add a switch in the existing circuit, or replace the existing circuit breaker with a circuit breaker switch. For multiple installations, the same style of switch/breaker should be used on each EFD. All MFD and PFD switches must be separate to mitigate against potential single point failure of both primary and secondary instruments. When not using a switch style circuit breaker, each circuit breaker(s) must be a trip free pull type and must be connected to the main battery bus (after the Battery Master Switch) as shown in the EFD1000 wiring diagram. The switches should be arranged in the same order as the EFDs. For example, if the installed EFD arrangement is EFD 500 MFD, EFD1000 PFD, and EFD1000 MFD (from left to right), the switches should be arranged in that order, from left to right. Alternately, the switches may be arranged vertically, from top to bottom, in the same order. If available, connect the ACU to the avionics electrical bus. Otherwise, connecting the ACU to the switched battery bus is permissible. 5.2.8 Special Considerations for Aircraft Limited to VFR Relief from the requirement for a secondary attitude reference for VFR aircraft has been provided in an FAA memorandum dated December 8, 2008, “Certification of Electronic Displays in Part 23 Aircraft Limited to VFR (Visual Flight Rules) Operations; Project No. SA9024SC-A, Aspen Avionics, Inc. FAA Approved Model List.” The Policy within this Memorandum permits exclusion of 23.1311(a)(5) with respect to the requirement for a secondary attitude indicator for aircraft limited to VFR. It is not acceptable to use this FAA Policy to change the established kinds of operations authorized for a particular aircraft (see 14 CFR §23.1525). Rather, the policy may be applied for aircraft that are limited by their certification basis to VFR only operations. Changes to the kinds of operations authorized for any aircraft on the AML is beyond the scope of this modification and must be established separately. DOCUMENT # 900-00003-001 PAGE 61-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The following requirements must be met in order to install the EFD1000 without a standby attitude indicator in U.S. registered Part 23 aircraft limited to VFR: The aircraft must have a placard or equivalent acceptable means, stating “Operation of This Aircraft is Limited to VFR Only”, or similar phraseology acceptable to the FAA, as required by § 23.1525, § 23.1559 and § 91.9. Since the kinds of operations will have been limited to VFR by the aircraft certification basis, this placard should already be in place prior to installation of the EFD1000/500 system, but should be verified. For aircraft limited to VFR, magnetic compass information must remain independent of the aircraft’s primary electrical power. 5.3 Conventional Landing Gear “tail dragger” Aircraft The following precautions are necessary for installations in aircraft with conventional landing gear, due to the necessity of initializing the EFD1000 in a tail-down position: • The RSM must be P/N 910-00003-00X, or A-05-111-00, serial number 1301 or above. • The on ground heading accuracy of the EFD1000 must be within +/-4 degrees. A RSM shim might be required to meet this tolerance – see Section 6.9.9. • See Section 10.5.1.1 for a conventional gear specific RSM calibration procedure. 5.4 PART 135 IFR Operations The 30 minute internal battery in the PFD is not approved for use as a power source to meet the electrical power source requirement under 14 CFR 23.1353, or for single engine Part 135 IFR operations under 14 CFR 135.163. 5.5 Setting V-SPEED Textual Markers Have the aircraft operator complete “Operator Configuration Checklist” in Appendix C so that this data is available prior to configuring the system in Section 10. We suggest making a copy of this form and have it signed by owner/operator, then put a copy in Installation Package. The V-speeds must be set in the EFD1000 PFD and EFD1000 MFD. 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 DOCUMENT # 900-00003-001 PAGE 62-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual autopilot compatible with the KI-525A or NSD-360A HSI is compatible with the EFD1000 System. Similarly, the EFD1000 Pro with ACU emulates the KI-254, KI-256, G-550A, and 52C77 flight director indicators by accepting FD signals compatible with these indicators and displaying them on the EFD. Autopilots that output a flight director signal that is compatible with the KI-254/256, G-550A, or 52C77 are compatible with the EFD1000 System. Section 9 of this document shows interconnect diagrams for common autopilots that are compatible with the EFD1000. Because the EFD1000 outputs Heading Datum and Course Datum via the ACU the existing HSI/DG is no longer required to provide this output to the autopilot. In addition, some existing autopilots that have only a DG installed (i.e. no HSI) will gain full HSI features with the installation of the EFD1000 System. Please check the manufacturer’s installation data for any jumpers or hardware that need to be added or removed from the autopilot to add the HSI interface. When the EFD1000 System is installed, the ACU controls all analog navigation signals provided to the autopilot. Navigation signal output to the autopilot is switched depending on which sensor is coupled to the EFD1000 HSI. Therefore the LT/RT/UP/DN, flags, and ILS Energize must only be connected between the ACU and autopilot, and there should be no direct connection between the navigation receiver and the autopilot. The autopilot’s flight director output may be paralleled from the autopilot to the existing Flight Director and ACU so that it is displayed on both instruments. The FD may also be connected to just the ACU for Flight Director display on the PFD when there is no existing flight director. 5.6.2 GPS Navigator Basemap Compatibility Not all GPS navigator outputs are the same. Some navigators provide output to support curved flight plan segments. Other navigators can only provide the straight segments of a flight plan, and the curved segments are not depicted. Some navigators provide an output that result in a straight-line depiction of a curved flight plan segment, which should not be used. It is possible to connect the navigator in an incorrect configuration, resulting in potentially misleading information to the pilot. NOTE: Other GPS navigators have not been evaluated and may be compatible. Contact Aspen Avionics for information regarding additional navigators. DOCUMENT # 900-00003-001 PAGE 63-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The following table identifies the correct configuration of compatible systems: Navigator Navigator Mode and/or Type of Connection EFD1000 Mode and/or Type of Connection Basemap Depiction Apollo GX50 GX60 GX65 Standard Mode, RS- 232 GPS TYPE 3, RS-232 This connection method presents straight- leg portions of flight plans. An open segment is shown in lieu of a curved segment. Bendix King KLN 90/A/B, KLN900 Standard Mode, RS- 232 GPS TYPE 1, RS-232 This connection method presents straight- leg portions of flight plans. An open segment is shown in lieu of a curved segment. KLN 90/A/B ARINC 429 ARINC 429 This connection method displays straight- leg portions of flight plans. Bendix King KLN 94 KLN 89/B Standard Mode, RS- 232 GPS TYPE 1, RS-232 This connection method presents straight- leg portions of flight plans. An open segment is shown in lieu of a curved segment. Bendix King KLN94 Enhanced Mode Enhanced Mode, RS-232 GPS TYPE 2, RS-232 This connection method presents curved segments of flight plans. Garmin GPS155 GPS155XL GPS300XL GPS165 GNC300 ARINC 429 ARINC 429 This connection method presents curved approaches. The GPS155XL shows an open segment in lieu of a curved segment. Garmin GNS- 400/500 Series ARINC 429 ARINC 429 This connection method presents curved approaches. Garmin GNS- 400/500 Series RS-232 This configuration should not be used. This connection method can incorrectly display curved segments as straight lines and the displayed information can be misleading to the pilot in certain conditions. Garmin GNS-480 (Software v2.0 and below) ARINC 429 This configuration should not be used. This software version has not been tested with EFD software 2.X. GNS-480 should be upgraded to SW v2.3. Garmin GNS-480 (Software v2.3) ARINC 429 GAMA 429 GFX Int ARINC 429 This connection method presents curved approaches. Trimble TNL-2000 TNL-3000 RS-232 This configuration should not be used. This connection method can incorrectly display the map information. Table 5.3 - GPS Basemap Compatibility DOCUMENT # 900-00003-001 PAGE 64-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5.6.3 GPSS GPS Steering provides a steering command to the autopilot through the HDG Datum channel to provide for enroute, procedure turn, holding pattern, and turn anticipation operation. GPSS through the EFD1000 is only available if Label 121 is transmitted by the GPS over the ARINC 429 bus. 5.6.4 GPS/ NAV Switching Existing GPS/NAV switching from the GPS and VLOC receiver to the original HSI will be removed as the PFD will provide this capability. The existing GPS and VLOC receivers will be wired directly to the PFD or ACU(s) as per the installation drawings in Section 9. Analog connections from the GPS and/or VLOC receiver to the autopilot will be removed and wired per the ACU to autopilot interfaces shown in Section 9. 5.6.5 Discrete Output The discrete output from the EFD1000 PFD is used to drive an altitude reminder Sonalert. The MFD discrete output is for future use. 5.6.6 Heading Output It may be necessary to use a digital bus, in lieu of a synchro output, to supply an external device such as a TAS, TCAS or Stormscope system with heading. Label 320 is output from the ACU on P3 pins 4 & 5 via a low speed ARINC 429 bus, if no ACU is installed then label 320 is available from the PFD pins 26 and 27. Magnetic Heading is also available in RS-232 format from the EFD1000 Air Data outputs (See Section 5.6.7). Figure 5.5 – Low Speed ARINC 429 Heading NOTE: The Bendix/King KTA810/910 and KMH820/920 only accept High Speed A429 heading and therefore are not compatible with this output. DOCUMENT # 900-00003-001 PAGE 65-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5.6.7 Air Data Outputs ARINC 429 air data labels are available from the PFD when no ACU is installed. If an ACU is installed then an RS-232 connection must be made to the GPS or ancillary equipment that requires this information. The ACU does not pass-thru air data information to its output bus. See Section 8 for ARINC 429 air data output specifications. The EFD1000 PFD and MFD can each output air data information in an RS-232 format for specific GPS and ancillary equipment. See Section 8 for RS232 air data outputs in Format Z and Format C. The EFD500 does not have an integral air data computer and therefore does not output air data information. 5.6.8 Second ACU A second ACU is required when two (2) analog VLOC receivers are installed. 5.6.9 Decision Height A decision height (DH) input from a compatible radar altimeter may be connected to the ACU. “DH” will be displayed on the PFD when decision height is reached. 5.6.10 RS-232 Considerations (existing PFD installations) Several new RS-232 ports are enabled in v2.X software. When an EWR50 XM received is added to the installation during a v2.X upgrade, if there is an existing RS-232 GPS connection this will need to be moved to another port. See Section 9. 5.6.11 Flush or Recess Mounting the PFD If there is insufficient clearance between the PFD and control column when the flight controls are in the full nose down position, it will be required to flush mount or recess mount the PFD in the instrument panel. Also the installer may choose to flush mount the PFD for cosmetic reasons. Aspen Avionics Flush Mount Kit Aspen Avionics offers a specific Flush Mount Kit for this purpose. See Service Bulletin SB2009-03 document number 991-00018-001 for instructions. Locally Fabricated Brackets If the installer chooses to fabricate their own brackets for flush mounting the displays then this modification is beyond the scope of this manual and will require that the brackets and the instrument panel modification be separately approved. DOCUMENT # 900-00003-001 PAGE 66-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 5.7 Traffic Sensors The PFD and MFD systems are compatible with ARINC 735A protocol traffic systems, utilizing the ARINC 429 interconnection. The following systems are known to be compatible: • Ryan 9900BX - (TAS) • Avidyne TAS600/610/620 - (TAS) • Garmin GTX 330 - (TIS) • L3 Skywatch 497/899 - (TAS) • Bendix/King KTA 870/KMH880 - (TAS) Additional sensors (including TCAS I) will be added from time to time and will be identified in subsequent revisions of this manual or in Service Bulletins or Tech Notes. Traffic sensor control functions are performed using existing traffic equipment installations or other compatible equipment. TCAS II is incompatible with the EFD1000/500. TCAS II installations are not authorized. 5.8 Weather Information The PFD and MFD systems can interface with the following weather information products: • Aspen EWR50 XM Weather Receiver • WX-500 Stormscope Sensor EWR50 XM Weather See Aspen Avionics document 900-00007-001 “EWR50 Installation Manual” for installation data on installing the complete EWR50 system. WX-500 The EFD can be configured so that it is the control panel and the display for the WX-500. In this configuration the EFD will be configured for “CONTROL” which allows the installer to configure the WX-500 receiver, initiate various tests, and view system data from the WX-500 via the EFD. The EFD RS232 transmitter and receiver will be connected. If an existing WX-500 control panel exists and it is desired to keep that interface operational then the EFD will be configured as “DISPLAY” and only the EFD RS232 receiver will be connected. DOCUMENT # 900-00003-001 PAGE 67-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual THIS PAGE IS INTENTIONALLY LEFT BLANK DOCUMENT # 900-00003-001 PAGE 68-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6 Mechanical Installation The PFD and MFD installation will require mechanical modifications to the aircraft. The PFD, RSM (an RSM is required for each EFD1000 installation), and Configuration Module will be installed in all installations, while one (1) or two (2) ACU(s), and one (1) or two (2) MFD(s) may be installed in others. Most installations will require removing and relocating existing flight instruments to alternate locations in the instrument panel to be used as standby instrumentation. 6.1 Unpacking and Inspecting Equipment 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 EFD Displays face down on the knobs. 6.2 Equipment Location Documentation It is required by the AML-STC that the PFD, MFD, RSM, CM, and ACU mounting locations be recorded on Figures D1 and D2 of Appendix D. It is also required that an accurate description of wire and cable routing be noted on the figures. This information will be required later to comply with the ICAs. Make a copy of the form and give to owner for inclusion in permanent aircraft records. 6.3 Log Book Entry Make a log book entry at the completion of the installation indicating that the aircraft has been modified in accordance with the EFD1000 AML-STC. DOCUMENT # 900-00003-001 PAGE 69-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.4 Weight and Balance Using the component weights in Table 6.1 and the moment arm of the component mounting locations perform a weight and balance calculation per AC 43.13-1B Chapter 10. Also account for equipment removed during the modification process. Component Weight (Ibs.) EFD1000 with internal battery including bracket (910-00001-001) 2.9 EFD1000 without internal battery including bracket (910-00001-002) 2.1 EFD500 including bracket 2.4 RSM – Remote Sensor Module 0.2 ACU – Analog Converter Unit 0.8 Configuration Module 0.1 EBB58 Emergency Backup Battery including bracket 2.25 EBB Pre-Fabricated harness 7ft 1.0 Table 6.1 – Component Weights 6.5 Installation Limitations The following mounting limitations must not be exceeded during the installation of the EFD1000 and RSM. 6.5.1 EFD1000 Installation Limitations • The EFD1000 must be mounted within 20º nose down to -10º nose up of perpendicular to the aircraft waterline. • The EFD1000 must be mounted within 0.0±2.0º of the zero degree roll “wings level” axis. 6.5.2 RSM Mounting Limitations • The RSM must be mounted within ±4º to the longitudinal axis of the aircraft (see Figure 6.10) • The RSM must be mounted within ±10º to the zero degree roll “wings level” axis (see Figure 6.13) • The RSM must be mounted within ±10º to the zero pitch axis “waterline” of the airframe (see Figure 6.11). • RSM must be mounted to a relatively flat surface such that when installed it will not deform the aircraft skin and must not allow more than a .030” gap between RSM and skin. DOCUMENT # 900-00003-001 PAGE 70-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual • RSM must not be mounted to a NO ZONE as pictured in Figure 6.7, Figure 6.8, and Figure 6.9. • Mounting the RSM to, or making other penetrations through, the aircraft pressure vessel is beyond the scope of this 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 the exterior of a composite or fabric skinned aircraft structure is beyond the scope of this STC. To mount the RSM on composite or fabric skin aircraft structures, separate FAA approval of the RSM mounting is required prior to the installation of the remaining EFD1000 system components under the EFD1000 AML- STC. 6.5.3 EFD1000 MFD – RSM Limitations (Dual RSM Mounting) The RSM provides information required for the presentation of attitude, heading and OAT information for each EFD1000 display. If the EFD1000 MFD is used as backup for attitude (this is presently not permitted) then the redundant RSMs in a dual EFD1000 display installation are essential. If there is anticipation that the backup attitude indicator would eventually be a candidate for replacement by the EFD1000 MFD, then the following would apply: to ensure the RSM devices would remain redundant. NOTE: If the EFD1000 MFD is not used as a backup attitude indicator, these RSM separation requirements are only recommendations, and the minimum separation for RSMs is six inches, edge to edge. • To avoid possible common mode failures the PFD and EFD1000 MFD RSMs should be separated by aircraft structure and mounted in different regions of the airframe. For example, one RSM can be top mounted on the aft empennage region while the other is internal wing mounted (i.e., old flux sensor location). If this is not practical, the two RSMs must be separated by a minimum of 12 inches laterally (preferably separated by dorsal or keel structure), or if lined up longitudinally where one RSM is directly fore or aft of the other, the separation must be a minimum of 24 inches. Note that in future software releases it may be possible to remove the mechanical attitude indicator, provided that sufficient separation exists between the two RSMs. • Although each RSM’s wiring to its display is manufactured as individually shielded and continuous wiring, the redundant RSM wiring is specifically not permitted to share the same connector, nor the same shield throughout their entire installation. DOCUMENT # 900-00003-001 PAGE 71-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual • A minimum of 12” lateral separation is required for all wiring (with the limited exception of regions permitting benign bulkhead penetrations) unless physical partitions exist. • When the EBB58 is installed its wiring harness must also remain isolated/separate from the EFD1000 PFD’s RSM wiring to provide independence. This will ensure that any physical damage to a particular wiring bundle cannot damage both the PFD’s RSM input and the EBB’s ability to provide emergency power to the EFD1000 MFD. • Turbine Compressor Rotor burst considerations (not applicable to most Class I and II aircraft but included for completeness): If installed in a rotor burst zone the RSMs must be installed on the top and bottom of the fuselage and not within the multiple fragment region with corresponding wire routing. If the RSMs are outside of the rotor burst zone but their wire routing is within this threat area, then only the wiring installation must include this level of separation. • Bird strike considerations: If not shielded by the shadow of the fuselage, the RSMs must either be laterally separated or installed on the top and bottom of the aircraft. 6.6 Equipment Bonding Bond all metal components to the airframe. Prepare bonded surfaces for best contact (resistance of connections should not exceed 0.003 ohm). The EFD uses an installer fabricated braided bonding strap to ensure proper bonding to the panel. The bond strap is attached with supplied screw (3/8 th inch length) to the back of the EFD at a location just below and left of static port. The other end of the strap is attached to the EFD mounting bracket screw at the rear of the panel. Each EFD1000 display must have its own (i.e. not shared with another EFD1000) bonding strap ground location. The RSM does not require an RF ground plane, but it must be bonded to the airframe to meet compliance with DO-160E EMI and lightning certification requirements. Bonding of the RSM is achieved through the mounting fasteners. The attached ground wire on the RSM is not a bonding wire but is a shield ground for the pigtail over braid and must be connected to airframe ground. Each RSM harness shield must have its own (i.e. not shared with another RSM) bonding location. The ACU is bonded through its six (6) mounting holes and chassis when mounted to a metal surface, otherwise a braided or single stranded wire bonding strap to airframe ground will need to be fabricated for mounting on composite structures. The optional EBB58 bracket must be bonded to the airframe ground. DOCUMENT # 900-00003-001 PAGE 72-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.7 Cooling The EFD uses an integral fan for cooling. The area near the fan must be unobstructed to permit maximum airflow through the unit. Venting and cooling air circulating behind the EFD will improve heat dissipation and may improve equipment reliability, and is therefore a good installation practice. The RSM, ACU, Configuration Module, and EBB58 have no cooling requirements. 6.8 EFD Installation Mechanical installation of the EFD requires installing the included mounting bracket, connecting a braided bonding strap between the EFD and panel, and installing pitot and static connections (EFD1000 only) to the two keyed quick release pressure fittings. NOTE: To avoid damage to the equipment, do not place the EFD Display face down on the knobs. 6.8.1 Connecting the Internal Battery (does not apply to 910-00001-002) The internal battery may be disconnected for shipping and must be reconnected prior to the Post Installation Flight Check and maintenance release of the aircraft. Connection of the battery is performed as follows: 1. Remove the two screws that hold the battery cover in place. The battery cover is located below the 44 pin connector on the EFD cylinder. 2. Remove the battery cover. 3. Plug the battery connector into the mating connector within the battery compartment. 4. Re-install the battery cover. Be careful to avoid pinching the wires with the cover. 5. Re-install the two screws to hold the battery cover in place. 6. Verify “Bat:” status on page 10 of the Main Menu shows “Charging” when external power is supplied to the EFD. 6.8.2 PFD Mounting Location The PFD must be mounted approximately centered in the instrument panel per FAR 23.1321(d). If the two existing instrument holes that contain the attitude indicator and direction indicator are not exactly centered, but are the closest instruments to the center, then that position is acceptable for mounting the PFD. The PFD can be mounted on the non-pilot (typically right side) side of the instrument panel if it is not for use by any required pilot during takeoff, initial climb, final approach, and landing. Backup instruments are required on the pilot side only. See 14CFR 23.1311 and 14CFR 23.1321. DOCUMENT # 900-00003-001 PAGE 73-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual NOTE: Modification to the existing instrument panel is not authorized under this STC. Any modification must be approved separately. Figure 6.1 - PFD Mounting Location 6.8.3 MFD1000 Mounting Location Since the MFD1000 may become a PFD during MFD to PFD reversion, the EFD1000 MFD should be positioned adjacent to the right or left of the PFD. If this is not practical or permitted (such as with “Barber Pole” airspeed indicators, see note below), then the EFD1000 MFD must be mounted in the pilot’s primary maximum field of view in a position that meets FAR 23.1321(a) if it is to be used as a backup instrument or if the MFD is for use by any required pilot during takeoff, initial climb, final approach, and landing. The requirements are +/- 35 degrees from the pilot’s center line horizontally (+/- 21 inches from centerline as defined by AC23.1311-1b). See Figure 5.3. NOTE: Aircraft with V MO “barber pole” airspeed indicators must keep the airspeed indicator and altimeter in the original positions (to preserve the basic “T”) and the airspeed/altitude tapes on the PFD (and reverted MFD) must be locked off. This will require any MFD to be positioned outside of the airspeed indicator or altimeter. NOTE: The standby instruments must be co-located with each other. One standby instrument cannot be 21 inches to the left of centerline and another 21 inches right of centerline. The instruments must all be in the same region of the panel. This applies to the EFD1000 MFD when used as the standby airspeed and altitude – the standby AI must be co-located with the EFD1000 MFD. DOCUMENT # 900-00003-001 PAGE 74-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.8.4 EFD Mounting Bracket Installation The pre-drilled holes in the mounting bracket (see Figure 6.3) support both standard 3” round instrument holes, and 3ATI square cutouts. The bracket is centered on the upper instrument hole. The lower portion of the bracket is provisioned with screw slots, allowing variable vertical spacing configurations. If the lower cutout is a 3ATI or other larger standard cutout, a commercially available metal blanking plate should be used to flush fill the cutout. Use the EFD Mounting Bracket as a template to cut the 2.10” diameter cutout for the fan and two 0.150” diameter mounting holes. All cut edges should be treated to prevent corrosion. Aircraft with tilted instrument panels of 20º or less can install the EFD flat against the panel. The tilt will later be removed electronically in the system configuration using the Panel Tilt Pitch Adjustment. The EFD is attached to the instrument panel in 6 places with MS24693-S30 (#6-32 flathead screws), NAS1149FN632P (washers), and MS21044N06 (#6-32 Nuts). It is also acceptable to use existing #6 nutplates or equivalent. 1) Burnish the back of the instrument panel around one of the 6 mounting holes to allow for bracket to instrument panel bonding through the screw/washer/nut. 2) Loosely install the bracket with the upper two mounting screws/nuts/washers as shown in Figure 6.2. 3) Use an inclinometer on the top of the EFD bracket with the aircraft level to make this adjustment. It may be necessary to slot the existing holes to align the bracket in the roll axis. 4) The PFD must be mounted within 0.0±2.0º of the zero degree roll “wings level” axis. 5) Fabricate an 8” bonding strap from braid and two ground lugs. Attach one ground lug to a mounting screw on the backside of the panel (see Figure 6.4). 6) Install remaining EFD mounting bracket screws and nuts. 7) Tighten all six (6) mounting screws and nuts to 12 in-lbs anchoring the bracket to the panel. DOCUMENT # 900-00003-001 PAGE 75-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.2 – EFD and Bracket Installation DOCUMENT # 900-00003-001 PAGE 76-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.3 - EFD Mounting Bracket (inches) 6.8.5 EFD Bonding Strap An 8” or shorter braided bonding strap is required between the screw (below and left of the static port- see Figure 6.4) on the backside of the EFD to a location on the backside of the instrument panel using one of the mounting screws and nuts. Each RSM harness shield must have its own (i.e. not shared with another RSM) bonding location. Verify ≤ 3 milliohms resistance to airframe ground at bonding strap connection point. DOCUMENT # 900-00003-001 PAGE 77-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.4 – EFD Bonding Strap Connection 6.8.6 Pitot and Static Connections (EFD1000 only) Pitot and Static connections are made to the EFD1000 via two keyed quick connect fittings. These connections will typically require a “T fitting” to be installed in-line with the existing altimeter and airspeed indicators. The quick connectors are keyed such that they cannot be interchanged. Once the correct quick connector is fastened to the pitot and static lines, they cannot be inadvertently swapped on the rear of the EFD unit. Installations that include an EFD1000 MFD require that there be an alternate static valve accessible to the pilot while seated in the normal position. Installation of an alternate static valve is outside the scope of the EFD1000 STC. If the aircraft has dual pitot/static systems then connect the PFD to one system and the EFD1000 MFD (if installed) to the other independent pitot/static system. NOTE: The pitot quick connector will fit on the EFD static port but the static quick connector cannot be inadvertently connected to the EFD pitot port due to the keying. Each connector has a 0.256” diameter barbed fitting that accepts a ¼” hose. Figure 6.5 - Pitot & Static Quick Connector DOCUMENT # 900-00003-001 PAGE 78-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 79-256 Revision G © Copyright 2010 Aspen Avionics Inc. 6.8.7 Quick Connector Installation 1) Insert “T” fitting into existing aircraft Pitot line and secure with Aero Seal 6604 or equivalent hose clamp (see Figure 6.6). 2) Connect a length of pitot line tubing between the “T” fitting and the “P” quick connector. Verify the length of tubing can be installed with no drip loop and that it can be secured away from flight controls. Secure each end with Aero Seal 6604 or equivalent hose clamps. 3) Insert “T” fitting into existing aircraft Static line and secure with Aero Seal 6604 or equivalent hose clamp (see Figure 6.6). 4) Connect a length of static line tubing between the “T” fitting and the “S” quick connector. Verify the length of tubing can be installed with no drip loop and that it can be secured away from flight controls. Secure each end with Aero Seal 6604 or equivalent hose clamps. 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. STATIC PITOT STATIC QUICK CONNECTOR A-06-505-00 PITOT QUICK CONNECTOR A-06-507-00 (KEYED) EFD1000 ¼” ID TUBING PITOT STATIC “T” FITTING SPLICE INTO PITOT LINE HOSE CLAMP (4 PLACES) “T” FITTING SPLICE INTO STATIC LINE ¼” ID TUBING Figure 6.6 – Pitot & Static Line Connections 6.8.8 Leak Check Requirements A pitot static leak check is required after the installation of the quick connectors and the EFD1000 is installed. The quick connectors are designed such that they seal when disconnected. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 80-256 Revision G © Copyright 2010 Aspen Avionics Inc. 6.9 RSM Installation CAUTION: The RSM is an integral part of the attitude function of the AHRS. A stable and magnetically quiet location for the RSM is essential for proper AHRS operation. CAUTION: There are special considerations for mounting the RSM on composite, fabric and pressurized aircraft. See §§6.9.2 and 6.9.3. There are three versions of RSM available for mounting in different orientations. The –001 version includes an internal emergency use GPS and is generally for external top mounting, although may also be internally mounted. The –002 version does not include the internal GPS and is for external or internal mounting in a top-mounted orientation. The –003 version also does not include the internal GPS and is for external or internal mounting in a bottom- mounted orientation. NOTE: If the RSM is mounted internally the OAT sensor must be disabled which will result in no TAS and wind display. If the RSM is mounted on the bottom, or internally mounted in an aluminum aircraft, then the emergency GPS sensor will be disabled. The RSM includes magnetic flux sensors which is why it is important to locate the RSM as far away from the cabin and baggage (or “hat rack”) compartment as practical as these areas may have varying magnetic fields (baggage, passengers, etc.). The RSM should not be mounted within 18 inches of a VHF Comm antenna, 6 inches of a GPS or ELT antenna, or within 12 inches of an active traffic antenna or DME antenna. The RSM should be mounted to a relatively flat surface such that there is less than .030” gap surrounding the RSM when installed. The RSM must not be mounted to an excessively curved area which could deform the RSM or aircraft skin. The RSM must not be mounted within a composite fairing such as a fiberglass wingtip cover, or vertical fin cover as these do not protect against direct lightning effects. RSM External Top Mounting See Figure 6.7. The RSM is typically installed near the tail of the aircraft on an unpressurized portion of the airframe. To take advantage of the OAT sensor and internal GPS (-001 only) the RSM must be mounted on the top outside of the airframe. Any RSM may be mounted internally if an outside location is impractical. Whenever an RSM is internally mounted, the OAT must be configured “off” and the internal GPS (-001 only) may need to be disabled if GPS signal reception is problematic. For a top external mount the preferred RSM installation area is a minimum of 12 inches behind a typical baggage or (hat rack) compartment to no closer than 39” from the end of the fuselage. The “Less Preferred” areas over the cabin should only be selected if impossible to find an acceptable location within the “Preferred” area of Figure 6.7. EFD1000 and EFD500 SW v2.X Installation Manual Unlike a GPS antenna that is used for primary navigation, the backup GPS usage and inherent sensitivity do not require a full view of the sky. Therefore, the vertical stabilizer may partially mask the antennas view of the sky/horizon. Installation on either side of the vertical fin is acceptable. When externally mounted, the NO ZONE areas are hot zones for a lightning strike and are not to be used for mounting the RSM. The RSM must not be mounted externally to the wing, the top of the vertical stabilizer, the horizontal stabilizer, the fuselage forward of the cabin, or within 39” of the tail as measured from the fuselage aft end as shown. If it is impossible to find a suitable external mounting location in the preferred area, and internal mounting is not possible, it may be permissible to mount the RSM above the cabin. A location will need to be found that is a minimum of 18 inches from any small cabin speakers or electronic device that can cause compass fluctuations. Large cabin speakers may cause RSM interference at distances up to 3 feet. Use the procedure in Section 6.9.1 to locate a quiet area. During operation of the electrical systems concentrate on those devices that are in the cabin and within the headliner. Be aware that headsets and other items worn by and operated by the flight crew and passengers could potentially interfere with the RSM. Typically this would be when the headset is within 12” of the RSM location. Find a location that cannot be affected by passenger and flight crew headsets while seated or moving about the cabin. RSM Internal Mounting With software version 2.X it is also possible to internally mount the RSM within an area of the aircraft fuselage or wing structure that is magnetically benign. For aluminum aircraft, the RSM may be mounted anywhere inside the aluminum structure. For composite or fabric covered aircraft, the RSM must not be mounted forward of the windscreen, or within 39” of the aft end of the fuselage. It may be mounted within the wing but no closer than 39” of the wingtip. It must not be mounted within the horizontal stabilizer, or within the vertical stabilizer. See Figure 6.8. NOTE: If internally mounting the RSM a mounting plate must be locally fabricated and approved separately. All mounting instructions for a magnetically quiet location still apply. RSM External Bottom Mounting Figure 6.9. The–003 version of the RSM is designed for external bottom mounting. This version may be mounted to any magnetically quiet area on the underside of the fuselage. Mounting this RSM to the underside of an aerodynamic surface, such as the wing or the horizontal stabilizer is not approved. Any location that results in the OAT sensor becoming heated from engine exhaust requires that the OAT sensor be disabled in configuration menus. See Figure 6.9. DOCUMENT # 900-00003-001 PAGE 81-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 82-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 6.7 - RSM-External Mounting Locations (Top/Side View) – all aircraft types NO ZONE NO ZONE NO ZONE Preferred Area Less Preferred Area (See Note) NO ZONE EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.8 - RSM Internal Mounting Locations – Composite/Fabric Aircraft DOCUMENT # 900-00003-001 PAGE 83-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.9 - RSM-003 External Mounting Locations (Bottom view) 6.9.1 Proposed RSM Location Check The installer must determine the best RSM location given the above factors. A navigation quality handheld compass (i.e., hiking compass) can be used to find a magnetically quiet area free from the effects of magnetic disturbances from flight controls, autopilot servos, strobes, or any other large magnetic field appliance. The RSM can detect magnetic fields in three dimensions. This means that magnetic influences below the RSM can also affect performance. Be sure to evaluate potential magnetic influences above and below the RSM. DOCUMENT # 900-00003-001 PAGE 84-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual NOTE: Changes to the magnetic field around the RSM can affect the RSM calibration and require revalidation of the RSM performance. Known sources of interference include (but are not limited to) the following types of material located near the RSM (normally, these materials within 12 inches can cause interference): a. Steel-wound hose (e.g. SCAT tube) b. Steel hose clamps c. Magnetized or magnetic hardware d. Servos e. Trim motors f. Poor bonding of electrical connections g. Blower motors Place a small handheld compass in the proposed RSM mounting location and move the compass around the location looking for needle deflection. There should be no more than 2º of compass needle movement within an area 18” x 18” around the proposed location. Should the compass show excessive needle movement it will be required to find a new location or, if feasible, treat the affected area with a degaussing coil. 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. Operate flight controls from stop to stop and verify no more than 2º of compass needle movement. Should the compass show excessive needle movement it will be required to find a new location or degauss the flight control cables and or flight control hardware. Operate all electrical systems. The compass needle should not deflect more than 2 degrees during testing. If a location cannot be found with less than 2 degrees of deflection then the electrical device causing the interference will need to be determined. The device causing the interference may need to be re-bonded or the wiring may need to be relocated. If the compass does not show any deflection from electrical or mechanical sources then that location should be acceptable to mount the RSM. 6.9.2 Pressurized Aircraft On pressurized aircraft it will be necessary for the RSM wiring to penetrate the aircraft pressure vessel. The installer is responsible for obtaining proper documentation and DOCUMENT # 900-00003-001 PAGE 85-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual FAA approvals from either the airframe manufacturer or from a DER or FAA field office for any penetrations of the pressure vessel or bulkhead. CAUTION: Penetration of the pressure vessel is not approved under this STC and will require separate approval. CAUTION: Mounting the RSM on the pressure vessel is beyond the scope of this STC and requires separate approval. 6.9.3 RSM mounting on Composite, Fabric or Damage-Tolerant Design Aircraft 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. RSM installation on aircraft certified to 14CFR Part 23 Amendment 23-48 or later (such as the Gippsland GA-8) must be evaluated for damage tolerance. Therefore the installation of the RSM on these aircraft is beyond the scope of this manual and requires separate approval. The installation information for the RSM in this manual is satisfactory to meet the requirements for the direct effects of lightning for all metal aircraft. It is not possible to determine the lightning direct effects on equipment mounted internally in composite and fabric aircraft. Therefore, the only acceptable areas for RSM internal mounting are shown in Figure 6.8. The same bonding requirements for an external mounting must be adhered to. Though separate approval must be obtained for the RSM structural and, in the case of fabric and composite aircraft, lightning direct effects; installation of the remaining EFD1000 system components is approved under the EFD1000 AML-STC. This includes HIRF and lightning induced transient susceptibility approval of the EFD1000 system installation (i.e. display, RSM, CM, ACU, and associated wiring). Each RSM harness shield must have its own (i.e. not shared with another RSM) bonding location. 6.9.4 Second RSM Placement (MFD1000) Use the EFD1000 MFD’s RSM mounting limitations in Section 6.5.3. DOCUMENT # 900-00003-001 PAGE 86-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.9.5 RSM Mounting Angles For RSM mounting the following maximum mounting angles apply. Longitudinal Axis Figure 6.10 – RSM Top View longitudinal Alignment Pitch Axis 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 6.11 – RSM Fore or Aft Max Tilt DOCUMENT # 900-00003-001 PAGE 87-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.12 – RSM Fore or Aft Max Tilt (Shim installed) Roll Axis Maximum side to side tilt is 10 degrees in relation to wings level. An aluminum shim might be required to keep orientation within limits (see Section 6.9.9 for shim fabrication). Figure 6.13 – RSM Side to Side Max Tilt Figure 6.14 – RSM Side to Side Max Tilt (Shim installed) DOCUMENT # 900-00003-001 PAGE 88-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.9.6 RSM External Mount – Aluminum Skin This STC approves the use of the doubler shown in 6.15 for Aluminum Skinned aircraft only. Mounting the RSM to a composite or fabric aircraft is not approved by this STC and will require that the installer obtain separate approval of the RSM mounting on these classes of aircraft. After the RSM mounting has been approved, this STC may be subsequently installed. 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. 6.9.6.1 RSM Doubler Fabrication 1) Determine the thickness of aircraft skin. 2) For aircraft skins 0.050” thick and less the doubler should be made from 0.050” material. For aircraft skins thicker than 0.050 the doubler should be made from material the same thickness as the skin. Figure 6.15 – RSM Doubler DOCUMENT # 900-00003-001 PAGE 89-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 3) Fabricate the doubler from 2024-T3 AMS-QQ-A-250/5 to the dimensions in Figure 6.15, Tolerances ± 0.030 4) Remove burrs and break sharp edges (0.005” – 0.015”) 5) Finish with Alumiprep Etch and Alodine Conversion Coating, or equivalent. 6) Mask around the four (4) mounting holes the diameter of the mounting washers or 1/2" on the down side of the doubler (see Figure 6.16). Prime that side with epoxy primer per MIL-P-23377 or equivalent. Do not prime the side that faces the aircraft skin. This allows for a doubler to aircraft skin bond and mounting washer to doubler bond. 7) Mark forward direction on doubler because pattern is not symmetrical. 8) Using the doubler as a template match drill holes in aircraft fuselage at location determined from Section 6.9.1. Doubler must be aligned to the longitudinal axis of the aircraft to within ±4º (see Figure 6.10). Figure 6.16 - Masking of Doubler 9) Remove burrs and break sharp edges on the aircraft skin (0.005” – 0.015”) 10) Burnish the aircraft skin on the inner surface in the area where the doubler will mount. Apply Alodine 1201 and do not prime. DOCUMENT # 900-00003-001 PAGE 90-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 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. Figure 6.17 - Ground Stud Mounting 12) The doubler is attached to the inside surface of the aircraft skin with solid rivets. • For aircraft skin less than 0.032 thick install with MS20470AD4 protruding head rivets. • For aircraft skin thickness of 0.032 install with NAS1097AD4 rivets flush in the fuselage skin. Carefully control the countersink depth to not knife edge the fuselage skin. • For aircraft skin thicknesses 0.040 to 0.050 install with NAS1097AD4 rivets flush in the fuselage skin. • For aircraft skins 0.063 or thicker install with NAS1097AD5 rivets flush in the fuselage skin. 13) Verify that the ground stud has ≤ 3 milliohms to ground. Figure 6.18 - Doubler Installation DOCUMENT # 900-00003-001 PAGE 91-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.9.7 RSM Internal Mount The installer must use a suitable existing shelf or fabricate a suitable mounting bracket for internally mounting the RSM. Use AC43.13-2B Chapter 1 for additional structural data. 6.9.8 RSM Installation CAUTION: Do not use a magnetic tipped screw driver to mount the RSM as this may magnetize the RSM and cause heading errors. CAUTION: Only use stainless steel or brass mounting hardware (i.e., screws, nuts, washers, nutplates) to mount the RSM. Use of any other ferrous screws or hardware may cause compass errors. 1) It is not required to remove aircraft surface paint below RSM unless an aluminum shim was required on extreme mounting angles. The shim must be bonded to the fuselage. Bonding of RSM is through four (4) mounting screws to doubler. 2) Install ring terminal to RSM shield ground wire. 3) Install RSM on aircraft and secure using four (4) screws, four (4) washers, and four (4) nuts as identified below. Installer may substitute nut plates for washers and nuts provided the nutplates are attached to the doubler only and not the aircraft skin. Nutplates must be stainless steel and non-ferrous. Description (equivalent hardware may be used) Description (equivalent hardware may be used) 8-32 Brass screw 1¼” MS35214-47 8-32 Stainless Steel screw 1¼” MS27039C08-17 Brass locking nuts MS21044B08 (formerly AN365-B832) Stainless Steel locking nuts MS21044C08 Brass Washer NAS1149B0832H (formerly AN960-B8) OR Stainless Steel washer NAS1149EN0832P or NAS1149CN0832R Figure 6.19 - RSM Mounting Hardware 4) Torque hardware to 12-15 in-lbs. 5) Attach ring terminal to ground stud on RSM doubler. 6) Apply a bead of non-corrosive sealant around the RSM and over each mounting screw. DOCUMENT # 900-00003-001 PAGE 92-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Doubler (installer fabricated) Aircraft Skin FWD Figure 6.20– RSM Mounting 6.9.9 RSM Shim Fabrication (if necessary) If the RSM exceeds the mounting limits of Section 6.9.5 a shim will be required. Fabricate a shim with the dimensions of the RSM baseplate. Optionally the shim can be made square and slightly larger than the RSM baseplate for ease of construction (see Figure 6.21). Figure 6.21 – Example Shim Top View The shim must not exceed the minimum and maximum thickness as shown in Figure 6.22. DOCUMENT # 900-00003-001 PAGE 93-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.22 – Example Shim Side View 1) Use RSM doubler as a template to mark shim stock. 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. 5) Mask off top side of shim 1/4” inside mounting surface of RSM and mask off a similar area on the bottom so that these areas remain Alodine only (see Figure 6.23). Prime unmasked areas with epoxy primer per MIL-P-23377 or equivalent. Paint to match aircraft color if desired. Figure 6.23 – Masking of Shim for Priming DOCUMENT # 900-00003-001 PAGE 94-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6) The shim must be bonded to the aircraft skin by removing the paint and prepping the aircraft surface where the shim and RSM will be mounted. Remove paint ½” inside the outer footprint of the RSM mounting location. Burnish the aircraft skin and apply Alodine 1201, do not prime. 7) Sandwich the shim between the aircraft skin and the RSM following the RSM installation procedure in Section 6.9.8. 8) Apply non corrosive sealant around shim and RSM. DOCUMENT # 900-00003-001 PAGE 95-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.10 ACU Installation The ACU has no user interface, and therefore can be remote mounted. The optimum mounting location is an area that minimizes wire runs to interfacing equipment. This typically means near the autopilot computer if installed. When mounting the ACU find a location in the aircraft of known load carrying capabilities such as: • Existing Avionics Shelf • Baggage compartment • Radio Rack • Cockpit Floor Figure 6.24 – ACU Mount to Flat Metal Shelf DOCUMENT # 900-00003-001 PAGE 96-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.10.1 ACU Mounting Mount ACU to existing shelf in any orientation using six (6) MS35206 #6-32 screws, six (6) NAS1149FN632P washers, and six (6) MS21044N06 #6-32 self locking nuts or equivalent. Tighten nuts to 12 in-lbs. An unpainted surface of the ACU case must be bonded to aircraft ground either through mounting to a metal shelf or with an installer fabricated bonding strap of wire braid or single stranded wire no more than 12 inches in length. Attach ground lug of bonding strap to one of the mounting screws if required. Verify ACU case to airframe ground has ≤ 3 milliohms of resistance. 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. DOCUMENT # 900-00003-001 PAGE 97-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 15 20 1 1 14 37 19 13 25 1 9 8 Figure 6.25– ACU Dimensions (inches) 6.11 Configuration Module Installation The Configuration Module will be cable tied to the PFD wire harness. Leave just enough slack in the cable ties so that the configuration module can slide along the PFD cable. This will prevent strain on the configuration module connector while the PFD harness is manipulated during installation and subsequent removal/replacement. DOCUMENT # 900-00003-001 PAGE 98-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 6.26 – Configuration Module Dimensions (inches) Cable Tie two (2) places Figure 6.27 – Configuration Module Tie Wrapped to Harness DOCUMENT # 900-00003-001 PAGE 99-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 6.12 EBB58 Emergency Backup Battery Installation The EBB58 has no user interface so it can be remote mounted. A location within the cabin will need to be selected so that it can be securely mounted and still be close enough to the EFD1000 MFD to fall within the maximum cable length. It should not be mounted where it can be disturbed by the occupants. The EBB58 must be mounted within the temperature controlled part of the aircraft. It must not be mounted to the firewall. The battery warms during operation and therefore should not be mounted under a seat. The installer must use an existing shelf with suitable load carrying capabilities or fabricate a suitable mounting bracket for mounting the EBB58. Use AC43.13-2B Chapters 1 for additional structural data. Figure 6.28 - EBB58 Mounting Bracket Installation 6.12.1 EBB58 Mounting Secure EBB58 bracket to existing structure or fabricated bracket using four (4) MS35206 #6-32 screws, four (4) NAS1149FN632P washers, and four (4) MS21044N06 #6-32 self locking nuts or equivalent. Tighten nuts to 12 in-lbs. Install the EBB58 in the rack so that the rear tab is properly retained and the spring clips are fully seated (see Figure 6.29). DOCUMENT # 900-00003-001 PAGE 100-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual NOTE: If the spring clip(s) are sprung so the pins do not fully seat, the mounting bracket must be replaced. Figure 6.29 - EBB58 Attachment locations DOCUMENT # 900-00003-001 PAGE 101-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual THIS PAGE IS INTENTIONALLY LEFT BLANK DOCUMENT # 900-00003-001 PAGE 102-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 7 Electrical Installation 7.1 Electrical Load Analysis Perform an electrical load analysis to verify the aircraft complies with FAR 23.1351(a) using the current draw of each installed component as determined from Table 7.1 below. Component Current Draw (amps) EFD1000 2.4 nominal @ 28Vdc 4.8 nominal @ 14Vdc EFD500 0.8 nominal @ 28Vdc 1.6 nominal @ 14Vdc RSM – Remote Sensor Module Current Draw included in EFD1000 ACU – Analog Converter Unit 0.5 nominal @28Vdc 1.0 nominal @ 14Vdc Configuration Module Current draw included in EFD1000 Table 7.1 – Current Draw 7.2 Electrical Installation EFD1000 PFD A dedicated 7.5 amp pull type circuit breaker or breaker/switch combination for the EFD1000 PFD must be installed in a location accessible to the pilot while seated. The breaker will be powered from the switched battery or essential bus. Label the switch and/or breaker “EFD1000 PFD.” Note – the switch may be labeled “PFD” in a PFD only configuration. The switch must be rated for at least 7.5 amps continuous duty. Record the location of circuit breaker and switch on Figure D3 of Appendix D. EFD1000 MFD A dedicated 7.5 amp pull type circuit breaker and separate switch or breaker/switch combination for the EFD1000 MFD must be installed in a location accessible to the pilot while seated. The breaker will be powered by the switched battery or essential bus. Label the switch and/or breaker “EFD1000 MFD.” Note - The switch must be rated for at least 7.5 amps continuous duty. Record the location of circuit breaker and switch on Figure D3 of Appendix D. If the aircraft has independent electrical systems then the PFD will be connected to one bus and the MFD must be connected to the other independent bus. DOCUMENT # 900-00003-001 PAGE 103-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual EFD500 MFD A dedicated 5A to 7.5A pull type circuit breaker and separate switch or breaker/switch combination for the EFD500 MFD must be installed in a location accessible to the pilot while seated. The breaker will be powered by the switched battery or essential bus. Label the switch and/or breaker “EFD500 MFD”. The switch must be rated for at least 7.5 amps continuous duty. The EFD500 MFD must have its own independent switch. Record the location of circuit breaker and switch on Figure D3 of Appendix D. ACU (optional) A two (2) amp pull type circuit breaker for the ACU must be installed in a location accessible to the pilot while seated. Wire the power source from the avionics bus (switched battery bus if no avionics bus exists). The breaker is to be labeled “ACU” or “ACU #1” in a dual ACU installation. If a second ACU is installed it will require its own two (2) amp breaker labeled “ACU #2”. Record the location of circuit breaker(s) on Figure D3 of Appendix D. EBB58 (optional) The EBB58 connects via a prefabricated harness to the back of the EFD1000 MFD (P/N 910- 00001-002 only). A “Locking Toggle” switch rated for at least 0.5A continuous duty must be installed in a location accessible to the pilot while seated. The switch must be labeled “EBB EMER DISC” and have a “DISC” and “NORM” position. The NORM position is when the switch is in the open position. The switch will be connected to the EBB D-sub connector as shown in Figure 7.5. Record the location of the switch on Figure D3 of Appendix D. Miscellaneous Wiring Use of MIL-C-27500 shielded wire and MIL-W-22759 single conductor wire is recommended. All wires should be fabricated as shown in Section 9 keeping all grounds as short as possible. Wires and connectors must be clearly marked per FAR 23.1365(d). DOCUMENT # 900-00003-001 PAGE 104-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 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). 7.2.1 HIRF/Lightning Requirements In order to meet HIRF and Lightning requirements it is required that the following cable runs use either an over braid applied during fabrication or double shielded wires. The over braid or double shield should extend within the back shell and must be grounded at both ends. • All ARINC 429 and RS-232 wiring into or out of the EFD require either a double shielded wire or a tinned copper over braid be applied over the twisted shielded pair. See Figure 7.1 below and NOTE 1 on Wiring Diagrams 9.4 through 9.14. Figure 7.1 – Over Braid/ Double Shield Requirements DOCUMENT # 900-00003-001 PAGE 105-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The following wires require single shields to comply with HIRF and Lightning requirements: • Aircraft power to the EFD requires a single stranded shielded wire from circuit breaker to EFD. See Figure 9.1. • The discrete output from the EFD to the Sonalert (or relay) and the power wire from circuit breaker to Sonalert (or relay) require a single stranded shielded wire. See Figure 9.1. • EFD to Configuration Module comes as an assembly with color coded wires and uses an over braid over non-shielded single conductor wires. EFD1000 to RSM wiring does not require the over braid or double shield, only what is specified in Section 7.2.3. ACU to GPS, ACU to VLOC receiver, and ACU to autopilot require no additional shielding just what is specified in the wiring diagrams of Section 9. 7.2.2 EFD to GPS/VLOC/ACU Wiring Use tinned copper over braid or double shielded wires on all ARINC 429 and RS-232 wires entering or exiting the EFD back shell. Ground the over braid and wire shields within the back shell. If using double shielded wire it may be difficult to terminate all shields within the back shell. 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– EFD Back Shell Grounds DOCUMENT # 900-00003-001 PAGE 106-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual At the GPS/VLOC/ACU terminate the over braid within the back shell or as close as possible. Ground the over braid at this end using a pigtail as short as possible. If using double shielded wires then ground both shields at the GPS/VLOC/ACU with pigtail as short as possible. 7.2.3 RSM Wiring The EFD1000 to RSM wiring run is made with a single cable seven (7) conductor shielded wire. M27500-A24SD7T23, M27500-22TG7T14 or equivalent 22 or 24AWG seven (7) conductor shielded cable can be used. Assembly using Aspen P/N A-08-148-00-A 30ft cable This cable assembly is prefabricated with the following wire color markings and will be cut to length at the EFD1000. Pin 1 White/Black Pin 2 White/Red Pin 3 White/Orange Pin 4 White/Yellow Pin 5 White/Green Pin 6 White/Blue Pin 7 White Assembly using M27500-A24SD7T23 or equivalent Cable: Terminate the aircraft side of the RSM wiring with the Hirose circular connector from installation kit as shown in Figure 7.3 below. Due to the compact design of the Hirose connector it may be easier to solder the wires to the solder cups on the bench versus inside the tail of the aircraft. Use a fine tip soldering iron for this procedure. 1. Pass the cable through the hood and metal cover. Strip back the insulation to expose the shielding and wires with the dimensions that are shown. 2. Stake the metal clamper to the shield in the location shown. A hexagonal crimper such as the ones used for BNC Coax connector assembly work can be used to crimp it to approximately 5.2mm outside diameter. 3. Assemble the two pieces of the connector such that the solder cup piece is retained by the ring. Discard the washer as it is not required. 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 # 900-00003-001 PAGE 107-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 7.3 – RSM Connector assembly CAUTION: Do not run RSM wiring near high current devices such as strobes and air conditioners and avoid running RSM wiring in same wire bundle as strobe and air conditioning wiring bundles if at all practical. EFD END 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 – EFD Back Shell Grounds/RSM DOCUMENT # 900-00003-001 PAGE 108-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 7.2.4 Configuration Module Wiring The Configuration Module (CM) connector comes as an assembly with color coded wires within an over braid. The wires are inserted into the appropriate pins as shown in Figure 9.1. The green wire with ground lug is attached to back shell. PFD Pin Color CM Pin 41 Black 1 42 Brown 2 43 Orange 4 44 Red 3 -- Green 5 7.2.5 ACU Wiring Wire the ACU as shown in Section 9 keeping all grounds as short as possible. No additional HIRF shielding is required. The ACU case must be grounded to airframe ground for proper operation. 7.2.6 Back Up NAV Indicator Wiring Wire the Nav indicator as shown in Figures 9.24, 9.25, and 9.26. Do not parallel more than one NAV Indicator to each ACU. When paralleling the wiring make the splice is as close to the navigation receiver as practical. Do not splice the connection at the back of the NAV indicator. 7.2.7 Autopilot Wiring Wire the autopilot to ACU as shown in Section 9. Remove any existing connections and switching between 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, NAV2. 7.2.8 EBB58 Wiring The EBB58 Wiring harness comes prefabricated with connectors both at the battery and the MFD end. The twisted pair for the Emergency Battery Disconnect switch should be cut to length and connected across the required SPST locking toggle type emergency battery disconnect switch. Optionally a SPST switch and integral guard may be installed in place of the locking toggle switch. The guard would be installed so the switch is normally open. When the guard is lifted and the switch is enabled, the switch will close, disconnecting the relay in the EBB. The shield is not grounded at the switch end. DOCUMENT # 900-00003-001 PAGE 109-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual The switch must be installed in a position so that is accessible to the pilot while seated. Be sure the switch guard can remain open so the guard does not return to the resting position and inadvertently open the switch. NOTE: When in the DISC position, the EBB Emergency Disconnect switch energizes a relay powered by the EBB. Thus, when the switch is in the DISC position, the Emergency battery will gradually discharge through the relay. Plug prefabricated wiring harness in to EBB58 and secure the connector by tightening the jackscrews. Connect the other end to the back of the EFD1000 MFD (P/N 910- 00001-002 only) and secure the connector by tightening the jackscrews. The EBB battery cable must be routed separately from the MFD main power wiring and the PFD RSM wiring.   Figure 7.5 - EBB Wiring Harness Switch Connections Figure 7.6 - EBB EMER DISC switch labeling DOCUMENT # 900-00003-001 PAGE 110-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 111-256 Revision G © Copyright 2010 Aspen Avionics Inc. 8 Electrical Connections 8.1 EFD Electrical Specifications 8.1.1 Power Input Nominal Input: 14Vdc or 28Vdc Operating Range: 9Vdc to 32Vdc (Note: Input power must transition >11VDC to turn on the unit) 8.1.2 Tone (PFD)/Reversion (MFD) Output Active on: Ground Inactive off: Open Load Current: 100ma maximum 8.1.3 RS-232 GPS Input Data is accepted in packets coded in the industry standard "avionics" format at a baud rate of 9600, 8 data bits, 1 stop bit, no parity. Packets are accepted at approximately 1 Hz. In Software version 2.X the following GPS configuration options are available in the Installation menu: • GPS TYPE 1 – KLN94 and KLN90B Standard RS-232 configuration. • GPS TYPE 2 – KLN94 Enhanced configuration. Allows the KLN94 to be configured for Enhanced RS-232. Curved flight paths can be displayed. • GPS TYPE 3 – GX-50/55/60/65 configuration. 8.1.4 RS232 ADC Output The EFD1000 Display outputs the following computed air data output signals over the RS-232 bus in Format Z (ADC TYPE 1) and Format C (ADC TYPE 2). Aspen makes no claim as to the suitability of this data for any purpose: True Air Speed Indicated Air Speed Pressure Altitude OAT (Format Z only) Wind Direction Wind speed Rate of Turn (Format Z only) Vertical speed Heading data EFD1000 and EFD500 SW v2.X Installation Manual 8.1.5 ARINC 429 GPS Inputs The EFD receives the following labels on pins (16, 17) and (20, 21) when transmitted from a GPS receiver. ARINC 429 word definitions are implemented per GAMA Pub 11. The GPS input ports can be configured either HIGH or LOW but must match the VLOC input port speed. ARINC Label(s) EFD Parameter 074 Data Record Header 075, bit 9 set OBS/HOLD Mode 075, bit 9 not set Auto Course Select Label 100, bits 13(0) and 12(1) CDI Select (GPS) [GNAV installation only] Label 100, bits 13(1) and 12(0) CDI Select (VLOC) [GNAV installation only] Label 114 GPS “Desired Track” Label 115 GPS “Waypoint Bearing” Label 116 GPS “Crosstrack” Label 117 GPS “Vertical Deviation” Label 147 GPS “Magnetic Variation” Label 121 GPS “Horizontal Command” Label 251 GPS “Distance to Go” Label 252 GPS “Time to Go” Label 261G, bits 25 (0), 26(0), 27(0) GPS “ENROUTE” Label 261G, bits 25(1), 26(0), 27(0) GPS “ TERMINAL” Label 261G, bits 25(0), 26(1), 27(0) GPS “APPR Active” Label 300 GPS “Mag. Station Decl, Wpt Type, Class Label 303 GPS “Message Length, Type, Number Label 304 GPS “Message Characters 1-3” Label 305 GPS “Message Characters 4-6” Label 306 GPS NAV Waypoint Latitude” Full precision Label 307 GPS NAV Waypoint Longitude” Full precision Labels 310 GPS “Present Position Latitude” Label 311 GPS ”Present Position Longitude” Label 275, bit 23 GPS “TO” Flag Label 275, bit 24 GPS “FROM” Flag Label 275, bit 11 set GPS “WPT ALERT” Label 275, bit 22 set GPS “INTEGRITY” Label 275, bit 27 set GPS “MSG ALERT” DOCUMENT # 900-00003-001 PAGE 112-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual ARINC Label(s) EFD Parameter 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 Label 330 GPS FPL Curved “CONIC Arc Inbound Course” Label 331 GPS FPL Curved “CONIC Arc Radius” Label 332 GPS FPL Curved “CONIC ARC Course Change Angle” Label 333 GPS FPL Curved “Airport Runway Azimuth Label 334 GPS FPL Curved “Airport Runway Length Label 335 GPS FPL Curved “Holding Pattern Azimuth” Label 340 GPS FPL Curved “Procedure Turn Azimuth” Table 8.1 - EFD A429 GPS Input 8.1.6 ARINC 429 VLOC Input The EFD receives the following labels on Pins (18, 19) and (22, 23) when transmitted from a VLOC receiver. The VLOC input ports can be configured either HIGH or LOW but must match the GPS input port speed. ARINC (Label) EFD Parameter Label 34 Tuned Frequency Label 34, bit 14 set ILS Energize Label 173 Localizer deviation and validity flags Label 174 Glide Slope deviation and validity flags Label 222 VOR Omni bearing Table 8.2 - EFD A429 VLOC Input 8.1.7 ARINC 429 Output The EFD1000 transmits the following labels on pins 26 and 27 (only when the installation is configured for no ACU) for ancillary equipment that require low speed ARINC 429 Heading, OBS, and Air Data. Note - if an ACU is installed then the connections will be made at ACU P3 pins 4 and 5 for heading and selected course. Aspen makes no claim as to the suitability of this data for any purpose. ARINC Label EFD Parameter Software Version Label 100 Selected Course 2.0 and subsequent Label 320 Magnetic Heading 2.0 and subsequent Label 203 Pressure Altitude 2.0 and subsequent Label 204 Pressure Altitude (Baro corrected) 2.0 and subsequent Label 210 True Airspeed 2.0 and subsequent Table 8.3 - EFD1000 A429 GPS Output DOCUMENT # 900-00003-001 PAGE 113-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 8.2 ACU Electrical Specifications 8.2.1 Power Input Nominal Input: 14Vdc or 28Vdc Operating Range: 11Vdc to 32Vdc 8.2.2 Decision Height (DH) 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 8.2.3 VLOC Receiver NAV Composite Input An input connected to the composite output of a VHF Navigation receiver. Nominal Input: 0.5Vrms VOR 0.35Vrms Localizer Input Impedance: 10K ohms ILS Energize Discrete Input Low impedance to ground supplied from a Navigation receiver when it is tuned to a localizer frequency. Active: Less than 500 ohms to ground or less than 1.5Vdc Inactive: Open circuit sinking less than 1 ma to ground at 28Vdc Glide Slope Deviation Input A low level differential input that accepts a glide slope signal from an external VHF Nav receiver. Input Range: ±150mVdc full scale Max Input Range: ±300mVdc Load: 1000 ohm Glide Slope Flag Input A low level valid input from an external VHF Navigation receiver. Valid: Greater than 260mV across a 1000 ohm load Invalid: Less than 100mV across a 1000 ohm load DOCUMENT # 900-00003-001 PAGE 114-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 8.2.4 GPS Receiver OBS Sine, Cosine, Rotor An OBS resolver output for GPS receivers that require an OBS input. The resolver output electrical zero is set to -60º (300º ORZ) for compatibility with most legacy resolvers. The ACU accommodates OBS excitation with DC offset. Excitation Amplitude: 26Vac max (H to C) Excitation Frequency: 20Hz to 5000Hz Output Format: 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) TO/ FROM FLAG Input Differential input from a GPS receiver indicating whether flying TO or FROM the active waypoint. TO the waypoint: +40mV or greater FROM the waypoint: -40mV or greater LEFT/ RIGHT Input Differential input from a GPS receiver indicating LEFT or RIGHT of GPS course. Input Range: ±150mVdc full scale Load: 1000 ohm Lateral Flag Input Validity flag from the GPS receiver indicating valid LEFT and RIGHT data. Valid: 260mV to 800mVdc Invalid: Less than 260mVdc Vertical Deviation Input Differential input from a GPS receiver indicating a fly UP or DOWN command. Input Range: ±150mVdc full scale Load: 1000 ohm Vertical Deviation Flag Input Validity flag from the GPS receiver indicating valid UP and DOWN data. Valid: 260mV to 800mVdc Invalid: Less than 260mVdc DOCUMENT # 900-00003-001 PAGE 115-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual OBS/ LEG (HOLD) Input Active low discrete input from a GPS receiver when in the OBS or HOLD mode. APPR Active Input 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. 8.2.5 Autopilot Lateral Deviation Output A low level lateral deviation output that is connected to an autopilot lateral deviation (RT/LT) input. The low side of the differential output is referenced to ground. Before connecting this output verify the receiving equipment’s left/right input can accommodate a ground potential on the low side. Lateral Deviation: ±15mVdc for ± 10º of course error Sense: Positive voltage for fly right Load: Will drive up to three 1000 ohm loads Lateral Flag Output A low level valid output to the autopilot indicating the Lateral (LT/RT) signal from the ACU is valid. Valid: 0.4 to 0.8Vdc Invalid: Less than 0.05Vdc Load: Will drive up to three 1000 ohm loads Vertical Deviation Output A low level vertical deviation output that is connected to an autopilot vertical (UP/DN) input. The low side of the differential output is referenced to ground. Output Voltage: ±150mVdc nominal, tracks the glide slope deviation input signal to within 5% Loading: Up to three 1000 ohm loads Vertical Flag Output A low level output to the autopilot indicating the UP/DN from the ACU is valid. Valid: 0.4 to 0.8Vdc Invalid: Less than 0.05Vdc Load: Will drive up to three 1000 ohm loads DOCUMENT # 900-00003-001 PAGE 116-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual ILS Energize Output 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 15 Volt Reference Output An internally generated +15Vdc reference for KI-525 emulation. Output Voltage: +15Vdc ±2Vdc Load Current: 30ma maximum KI-525A Heading and Course Datum Output Emulated KI-525A outputs to drive the heading and course datum inputs of an autopilot. Reference Input: DC (DC may be supplied by the autopilot or ACU +15Vdc reference) Heading Datum zero: zero volts when heading bug on the lubber line. Heading Datum sense: +voltage when the heading bug is to the right of the lubber line and ACU DATUM is set to NORMAL in the configuration. Course Datum zero: zero volts when heading bug on the lubber line. Course Datum sense: +voltage when the heading bug is to the right of the lubber line and ACU DATUM is set to NORMAL in the configuration. NSD-360 Heading and Course Datum Output Emulated NSD-360 outputs to drive the heading and course datum inputs of an autopilot. Reference Input: AC or DC reference voltage supplied by autopilot Heading Datum zero: zero volts plus any offset voltage applied to ACU P3-25 Heading Datum sense: +voltage when the heading bug is to the right of the lubber line and ACU DATUM is set to NORMAL in the configuration. Course Datum zero: zero volts plus any offset voltage applied to ACU P3-25 Course Datum sense: +voltage when the heading bug is to the right of the lubber line and ACU DATUM is set to NORMAL in the configuration. DOCUMENT # 900-00003-001 PAGE 117-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 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. 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. Century Flight Director Input When the EFD1000 is configured for ACU FD TYPE = 4 the ACU will accept Century Flight Director output levels emulating the 52C77 Artificial Horizon Indicator. NOTE: ACU Software Version A-02-178-1.1 or subsequent is required for the 52C77 Flight Director emulation. Flight Director Valid Input A single high level valid discrete supplied by the flight director computer indicating validity of the command bar signals to the ACU. Valid: Greater than 5Vdc Invalid: Less than 2Vdc Flight Director Engaged Input A single high level valid discrete indicating the pilot has engaged the flight director. Engaged: Greater than 5Vdc Disengaged: Less than 2Vdc Heading Valid Output Active low discrete output indicating the PFD directional gyro is valid. Valid: Sinks to ground Invalid: Open Load Current: 100ma maximum GPS Selected Output Active low discrete output indicating GPS1 or GPS2 is the current coupled sensor on the HSI. GPS coupled: Sinks to ground GPS not coupled: Open DOCUMENT # 900-00003-001 PAGE 118-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Load Current: 100ma maximum 8.2.6 ARINC 429 Output The ACU transmits the following labels on P3 pins 4 and 5 for GPS receivers and systems that require ARINC 429 magnetic heading and selected course. ARINC Label PFD Data Rate (ms) Software Version Label 100 Selected Course 200 2.0 and subsequent Label 320 Magnetic Heading 200 2.0 and subsequent Table 8.4 - ACU A429 Output DOCUMENT # 900-00003-001 PAGE 119-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 8.3 EFD Pin Out Pin Number Name Input / Output Function 1 POWER - Main DC power input for the unit 2 POWER - “ 3 POWER - “ 4 GND - Main DC ground for the unit 5 GND - “ 6 GND - “ 7 Digital_Discrete OUTPUT Tone Alert (PFD)/Reversion Relay (MFD) 8 RS232_RX1 INPUT RS232 RX1 (115kb) 9 RS232_RX2 INPUT RS232 RX2 10 RS232_RX3 INPUT RS232 RX3 11 RS232RX4 INPUT RS232 RX4 12 RS232RX5 INPUT RS232 RX5 13 RS232_TX1 OUTPUT RS232 TX1 14 RS232_TX2 OUTPUT RS232 TX2 15 RS232_TX3 OUTPUT RS232 TX3 16 ARINC_RX1A INPUT ARINC Receiver 1 17 ARINC_RX1B INPUT ARINC Receiver 1 18 ARINC_RX2A INPUT ARINC Receiver 2 19 ARINC_RX2B INPUT ARINC Receiver 2 20 ARINC_RX3A INPUT ARINC Receiver 3 21 ARINC_RX3B INPUT ARINC Receiver 3 22 ARINC_RX4A INPUT ARINC Receiver 4 23 ARINC_RX4B INPUT ARINC Receiver 4 24 ARINC_RX5A INPUT ARINC Receiver 5 25 ARINC_RX5B INPUT ARINC Receiver 5 26 ARINC_TX1A OUTPUT ARINC Transmitter 1 27 ARINC_TX1B OUTPUT ARINC Transmitter 1 28 Reserved - Future Expansion 29 Reserved - “ 30 RS232_TX0 OUTPUT RS232 TX 31 RS232_RX0 INPUT RS232 RX0 (115kb) 32 RSM_C - RSM data (EFD1000 only) 33 RSM_D - RSM data (EFD1000 only) 34 RSM_E - RSM data (EFD1000 only) 35 RSM_F - RSM data (EFD1000 only) 36 RSM_G - RSM data (EFD1000 only) 37 Reserved - Future Expansion 38 “ - “ 39 “ - “ 40 “ - “ 41 CONFIG_A - Configuration Module connection 42 CONFIG_B - “ 43 CONFIG_C - “ 44 CONFIG_D - “ Table 8.5 - PFD/MFD Pin Out DOCUMENT # 900-00003-001 PAGE 120-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 8.1– PFD/MFD Connector (as viewed from rear of unit) 8.4 RSM Pin Out Pin Number Name Input / Output Function 1 RSM_A - RSM Connection 2 RSM_B - RSM Connection 3 RSM_C - RSM Connection 4 RSM_D - RSM Connection 5 RSM_E - RSM Connection 6 RSM_F - RSM Connection 7 RSM_G - RSM Connection Table 8.6 - RSM Pin Out Male Pin Side Solder Cup Side Figure 8.2 - RSM Mating Connector –Install Side 8.5 Configuration Module Pin Out Pin Number Name Input / Output Function 1 Config_A - CM Connection 2 Config_B - CM Connection 3 Config_D - CM Connection 4 Config_C - CM Connection 5 Config_S - Shield Ground Table 8.7 - Configuration Module Pin Out DOCUMENT # 900-00003-001 PAGE 121-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 8.3 - Configuration Module Connector (Install side) 8.6 ACU Pin Out Pin Number Name Input / Output Function J1-1 429RX2A INPUT ARINC 429 Port 2 Receive A J1-2 429RX2B INPUT ARINC 429 Port 2 Receive B J1-3 PWR-COM - Power Common J1-4 GPS+LT INPUT GPS Lateral Dev Input (-) J1-5 GPS-LATFLG INPUT GPS Lateral Flag Input (-) J1-6 GPS+DN INPUT GPS Vertical Dev Input (-) J1-7 GPS+FR INPUT GPS TO/FROM Input J1-8 GPS-VERTFLG INPUT GPS Vertical Dev Flag (-) J1-9 Reserved - Reserved J1-10 +11 to 32Vdc - Aircraft Primary Power J1-11 GPS+RT INPUT GPS Lateral Dev Input (+) J1-12 GPS+LATFLG INPUT GPS Lateral Flag Input (+) J1-13 GPS+UP INPUT GPS Vertical Dev Input (+) J1-14 GPS+TO INPUT GPS TO/FROM Input J1-15 GPS+VERTFLG INPUT GPS Vertical Flag (+) Table 8.8 - ACU J1 Pin Out Figure 8.4-ACU J1 Connector (as viewed from front of unit) DOCUMENT # 900-00003-001 PAGE 122-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Pin Number Name Input / Output Function J2-1 COMPOSITE INPUT VOR/LOC Composite input J2-2 /ILS-ENERGIZE INPUT Active Low input from VHF Nav Rx J2-3 /Spare-Disc1 INPUT Spare Discrete Input J2-4 /BACK-CRS-OUT OUTPUT Open collector output to drive the back course sense circuit of an autopilot J2-5 /ILS-ENERGIZE-OUT OUTPUT Active Low Output when ILS Selected or GPS Appr Active J2-6 /FCS-LOC-IN INPUT Low Input from GPS when Appr Selected J2-7 /OBS-LEG-IN INPUT Active Low from GPS when GPS OBS mode selected J2-8 -DH INPUT Differential –DH input J2-9 FD-ENGAGED INPUT Flight Director Engaged (command bars in view when active) J2-10 FD-ROLL2 INPUT Roll input for ARC and Bendix J2-11 +VLOCFLG-OUT OUTPUT Valid VHF Nav VOR or Localizer signal J2-12 +GS-IN INPUT Glideslope deviation from VHF Nav Rx J2-13 +GSFLG-IN INPUT Glideslope flag from VHF Nav Rx J2-14 FD-PITCH-COM INPUT Pitch Signal common for all FD types J2-15 FD-ROLL-COM INPUT Roll Signal common for all FD types J2-16 +UP OUTPUT Vertical output to autopilot (H) J2-17 +VERT-FLG OUTPUT Vertical output flag (H) J2-18 +RT OUTPUT Lateral deviation output J2-19 ACU #1/#2 INPUT Spare Discrete Input J2-20 COMPOSITE-COM - VOR/LOC common J2-21 Reserved - Spare Discrete Input J2-22 Reserved - Spare Discrete Input J2-23 Reserved - Reserved J2-24 APPR-ACT INPUT Active Low input from GPS when GPS approach mode activated J2-25 HEADING VALID OUTPUT Active Low Output when Heading Valid J2-26 +DH INPUT Differential +DH Input J2-27 FD-VALID INPUT Flight Director Active High valid J2-28 FD-PITCH2 INPUT Pitch Input for ARC Flight Director J2-29 Reserved - J2-30 -VLOCFLG-OUT - Common J2-31 -GS-IN INPUT Glideslope deviation from VHF Nav Rx J2-32 -GSFLG-IN INPUT Glideslope flag from VHF Nav Rx J2-33 FD-PITCH1 INPUT Pitch Input for Century and Bendix FD J2-34 FD-ROLL1 INPUT Roll Input for Century FD J2-35 +DN OUTPUT Vertical output to autopilot (L) J2-36 -VERT-FLG OUTPUT Vertical output flag (L) J2-37 +LT OUTPUT Lateral deviation output Table 8.9 - ACU J2 Pin Out Figure 8.5 –ACU J2 Connector (as viewed from front of unit) DOCUMENT # 900-00003-001 PAGE 123-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Pin Number Name Input / Output Function J3-1 429RX1A INPUT ARINC 429 Port 1 Receive A J3-2 429TX1A OUTPUT ARINC 429 Port 1 Transmit A J3-3 CRS-DATUM OUTPUT Course Datum output J3-4 429TX2A OUTPUT ARINC 429 Port 2 Transmit A J3-5 429TX2B OUTPUT ARINC 429 Port 2 Transmit B J3-6 OBS SIN - OUTPUT Sin of selected course angle (L) J3-7 OBS COS - OUTPUT Cos of selected course angle (L) J3-8 ROTOR C OUTPUT OBS sin/cos excitation (L) J3-9 +15V-EXT-OUT OUTPUT Internal +15Vdc reference J3-10 SIGNAL-COM - Signal ground J3-11 HDG/CRS-COM - Signal ground J3-12 Reserved - Reserved J3-13 Reserved - Reserved J3-14 429RX1B INPUT ARINC 429 Port 1 Receive B J3-15 429TX1B OUTPUT ARINC 429 Port 1 Transmit B J3-16 SIGNAL-COM - Signal ground J3-17 GPS SELECTED OUTPUT Active Low signal to drive GPS and Autopilot inputs. J3-18 OBS SIN + OUTPUT Sin of selected course angle (H) J3-19 OBS COS + OUTPUT Cos of selected course angle(H) J3-20 ROTOR H INPUT OBS sin/cos excitation (H) J3-21 ARINC-HDG-CRS-EXT - 26Vac reference to emulate an ARINC synchro interface J3-22 HDG-DATUM OUTPUT Heading Datum output J3-23 HDG-CRS-DATUM-EXT INPUT Heading/Course Datum excitation input J3-24 Reserved - Reserved J3-25 HDG-CRS-OFST INPUT Heading/Course Datum excitation offset input Table 8.10 - ACU J3 Pin Out Figure 8.6 -ACU J3 Connector (as viewed from front of unit) DOCUMENT # 900-00003-001 PAGE 124-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 9 Installation Wiring Diagrams The following Section contains wiring diagrams for common interfacing equipment to the PFD, MFD, ACU, RSM, and Configuration Module. Although the list of interfacing equipment is quite extensive it does not cover all compatible equipment. For interfaces that are installed but not shown it is required by the ICAs that a drawing be made and inserted into Appendix D of this document. All other drawings used from this section by the installer must be copied and inserted into Appendix D. There will be some GPS receivers not shown on these drawings that will be compatible with the EFD1000 system. The EFD1000 is compatible with ARINC 429, RS-232, and analog GPS receivers. For flight plan information to be presented on the PFD an RS-232 or ARINC 429 interface is required. Should an RS-232 or ARINC 429 bus not be available or incompatible then the GPS can still be connected to the EFD1000 system using analog signals to drive the HSI deviation indications. In this situation, GPS flight plan data will not be available. It will be up to the installer to verify the interface is fully functional by performing a complete ground check of the system. There are also VLOC receivers not shown in these drawings that can be connected either by ARINC 429 to the PFD or through VOR composite video into the ACU. Any radio with a nominal output of 0.5Vrms VOR or 0.35Vrms Localizer composite video format are supported. It will be up to the installer to verify the interface is fully functional by performing a complete ground check of the system. 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 installation manual or maintenance instructions. The EFD1000 Pro with ACU also emulates the Bendix King KI-254/256, ARC G-550A, and Century 52C77 flight director indicators. All autopilots that output flight director signals that are KI- 254/256, G-550A, or 52C77 compatible are also compatible with the EFD1000 flight director display. To begin planning the electrical installation, select the drawing in the list below preceded by an “*” that matches the aircraft equipment configuration, and then wire as shown. GPS1, GPS2, NAV1, NAV2, and the autopilot are options on each page. Simply make the connections to the equipment you plan to install and omit the units from the drawing you don’t. You will configure the system later based upon the Configuration ID#s shown in the Configuration Matrix on each drawing. Aspen Avionics Inc. uses the terms “GNAV” when referring to a combination GPS/VLOC Receiver with an integral CDI source select (i.e., GNS-430), “GPS” for a standalone GPS Receiver (i.e., GNS- 400, KLN90B), and “VLOC” for stand alone VOR/Localizer equipment (i.e. KX-155, SL30). DOCUMENT # 900-00003-001 PAGE 125-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X 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. Please consult other manufacturers’ reference documents for their complete interface to the aircraft. List of Wiring Diagrams – PFD Figure Installation Drawing 9.1 EFD1000 Main Connections 9.2 ACU Main Power 9.3 Decision Height (DH) *9.4 Pilot Digital RS-232 Interface *9.5 Pilot Digital ARINC 429 Interface *9.6 Pro Single Digital with “Tracker” or No autopilot *9.7 Pro Single Digital with autopilot *9.8 Pro Digital/Analog Mix with and w/o autopilot *9.9 Pro Dual Digital without autopilot *9.9A Pro Dual Digital with autopilot *9.10 Pro ARINC 429 GPS & Dual Analog VLOC with and w/o autopilot *9.11 Pro Legacy GPS & Analog VLOC with and w/o autopilot 9.11A This Figure does not apply to SW v2.0 and later 9.11B This Figure does not apply to SW v2.0 and later 9.12 KLN89/B & KLN94 Interface 9.13 KLN-90/A/B Interface 9.14 Apollo GX-55/65 Interface 9.15 Analog NAV/VLOC Interface 9.15A Analog Narco and ARC Navigation Radio Interface 9.16 KI-525A Emulation Bendix/King autopilots 9.17 S-TEC autopilot interface 9.17A S-TEC KI-525A Emulation 9.17B S-TEC NSD-360A Emulation 9.18 Century autopilot interface 9.18A NSD-360A Emulation Century 21/31/41/2000 9.18B NSD-360A Emulation Century IIB/III 1C388/M & 1C388-2 9.18C NSD-360A Emulation Century IIB/II 1C388-3 9.18D NSD-360A Emulation Century IV 9.19 Cessna ARC autopilot interface 9.19A NSD-360A Emulation Cessna ARC 300B/400B/800B 9.19B NSD-360A Emulation Cessna ARC 300A 9.20 KI-256 Flight Director Emulation Bendix/King 9.21 52C77 Flight Director Emulation Century 41/2000 9.21A 52C77 Flight Director Emulation Century IV 9.22 G-550A Flight Director Emulation ARC 9.23 KI-256 Flight Director Emulation S-TEC 55/55X 9.23A KI-256 Flight Director Emulation S-TEC 60/65 9.24 Back-Up NAV Indicator (internal converter) 9.25 Back-Up NAV Indicator (OBS Resolver) 9.26 Back-Up NAV/GPS Indicator (OBS Resolver) DOCUMENT # 900-00003-001 PAGE 126-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 9.27 Additional Configuration Notes 9.28 Traffic/XM Wx/WX-500/ADC Sensor Interfaces List of Wiring Diagrams – MFD Two “Generic” drawings (Figure 9.29 and 9.30) are provided that will work with any interface. It will be necessary to use other drawings from Section 9 to complete the wiring interface to the GPS receiver, NAV receiver, and ACU. Two configuration specific drawings (Figure 9.31 and 9.32) are provided that show the most common system configurations. These drawings show the complete NAV/GPS and ACU interfaces to the EFD1000 and EFD500 systems. Figure Installation Drawing 9.29 GENERIC: PFD with MFD 9.30 GENERIC: PFD with MFD1000 and MFD500 9.31 PFD with MFD, GNAV1 and Analog NAV2 and/or GPS2 9.32 PFD with MFD, GNAV1 and GNAV2 DOCUMENT # 900-00003-001 PAGE 127-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 1 P 1 P O W E R P O W E R 2 P O W E R 3 G N D 4 G N D 5 G N D 6 E F D 1 0 0 0 C O N N E C T O R 4 4 P I N F D - S U B P / N D D 4 4 F 1 0 0 0 0 R S M _ A 3 0 R S M _ B 3 1 R S M _ C 3 2 R S M _ D 3 3 R S M _ E 3 4 R S M _ F 3 5 R S M _ G 3 6 C O N F I G _ A 7 C O N F I G _ B C O N F I G _ C C O N F I G _ D 12345 C O N F I G _ A C O N F I G _ B C O N F I G _ D C O N F I G _ C C O N F I G _ S S I N G L E U N S H I E L D E D M I L - W - 2 2 7 5 9 o r E q u i v . G R O U N D T E R M I N A L W I R E L E N G T H 1 2 I N C H E S M A X C O N F I G U R A T I O N M O D U L E C O N N E C T O R M o le x P / N 5 0 - 5 7 - 9 0 4 5 B R E A K E R W i r e T y p e s i n t h i s M a n u a l D I G I T A L _ O U T S I N G L E S H I E L D E D 2 2 A W G M 2 7 5 0 0 - 2 2 S D 1 T 2 3 o r E q u i v . T W I S T E D S H I E L D E D P A I R 2 2 A W G M 2 7 5 0 0 - 2 2 S D 2 T 2 3 o r E q u i v . 4 1 4 2 4 4 4 3 C H A S S I S S T U D 1 A l l w i r e s i n t h i s m a n u a l a r e 2 2 A W G u n l e s s o t h e r w i s e n o t e d . 2 C o n n e c t g r o u n d l u g s t o a i r f r a m e g r o u n d w i t h a s s h o r t a c o n d u c t o r a s p o s s i b l e . C o n n e c t t o a i r f r a m e g r o u n d w i t h a s s h o r t a c o n d u c t o r a s p o s s i b l e . 3 E F D 1 0 0 0 M F D 1 4 - 2 8 V d c B a t t e r y B u s 1234567 R S M _ A R S M _ B R S M _ C R S M _ D R S M _ E R S M _ F R S M _ G 7 C O N D U C T O R S H I E L D E D W I R E R S M S H I E L D I N G E X T E N D S W I T H I N B A C K S H E L L S H I R O S E S R 3 0 - 1 0 P F - 7 P ( 7 1 ) T I N N E D C O P P E R O V E R B R A I D D A B U R N P / N 2 3 5 0 - X o r E q u i v . C O N N E C T T O B O L T O N P F D B R A C K E T ( B A C K S I D E O F P A N E L ) - A I R F R A M E G R O U N D G R O U N D S T R A P 8 I N C H E S P ig t a il A s s e m b ly A - 0 8 - 1 4 4 - 0 0 - A 2 0 A W G 2 0 A W G 2 4 A W G 2 4 A W G 2 2 o r 2 4 A W G X 7 W I R E S P F D t o R S M S H I E L D T E R M I N A T E S T O “ M E T A L C L A M P E R ” W I T H I N C O N N E C T O R R S M C O N N E C T O R 4 4 N o t e w i r e s c r o s s a n d a r e n o t i n n u m e r i c a l o r d e r H I R F / L I G H T N I N G O V E R B R A I D O R D O U B L E S H I E L D E D W I R E B l a c k B r o w n O r a n g e R e d 5 5 E a c h E F D m u s t u s e i t s o w n i n d i v i d u a l s w i t c h f o r r e d u n d a n c y . L a b e l a c c o r d i n g l y . P F D m a y b e l a b e l e d “ P F D ” i n a P F D o n l y i n s t a l l a t i o n . W h it e / B la c k W h it e / R e d W h it e / O r a n g e W h it e / Y e llo w W h it e / G r e e n W h it e / B lu e W h it e 6 6 P F D m a y u s e o p t i o n a l “ s o n a l e r t ” . M F D i s n o c o n n e c t . E F D 1 0 0 0 o n l y 7 T h e E F D 1 0 0 0 i s n o r m a l l y s h i p p e d w i t h t h e i n t e r n a l b a t t e r y d i s c o n n e c t e d . C o n n e c t t h e b a t t e r y p r i o r t o i n s t a l l a t i o n . S e e S e c t i o n 6 . 8 . 1 . E F D 5 0 0 M F D S o n a le r t - P F D 7 . 5 A ( E F D 1 0 0 0 ) 5 A – 7 . 5 A ( E F D 5 0 0 ) E F D 1 0 0 0 P F D 8 8 P F D R S M a n d M F D R S M w i r i n g m u s t b e i s o l a t e d / s e p a r a t e f r o m e a c h o t h e r . A l s o P F D R S M w i r i n g m u s t b e i s o l a t e d / s e p a r a t e f r o m E B B 5 8 w i r i n g . S e e S e c t i o n 6 . 5 . 3 . Figure 9.1 – EFD1000/500 Main Connections DOCUMENT # 900-00003-001 PAGE 128-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.2 – ACU Input Power Figure 9.3 – Decision Height (DH) Interface DOCUMENT # 900-00003-001 PAGE 129-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 130-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.4 – PILOT Digital RS232 Interface Over Braid or Double Shield EFD1000 16 429 GPS RX1A P4001 P5001 P1 46 46 16 429 GPS RX1B 17 47 47 15 Configure Garmin ARINC 429 port for “Low GAMA 429 Graphics w/Int” GNS400 GNS500 GNC300 GPS150 155/165 P1 15 16 1 2 1 Apollo 2001 P1 41 40 ID#1 Description C NONE ID#2 GPS1, No GPS2 No GPS1, No GPS2 NONE NONE 2 2 2 Over shield or over braid required on this wire bundle to comply with HIRF & Lightning. Extend within back shell if possible. Ground at both ends. 3 Configuration Matrix (see Section 10) 4 Back-up NAV indicator maybe required for IFR use. Consult manufacturers’ installation manual. 3 Configure GPS for “King EFS 40/50” 5 4 Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.5 – PILOT Digital ARINC 429 Interface EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.6 - PRO Single Digital with "Tracker" or no Autopilot Interface DOCUMENT # 900-00003-001 PAGE 131-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Over Braid or Double Shield Over Braid or Double Shield EFD1000 16 429 GPS RX1A P4001 P4006 P5006 P5001 46 46 24 429 GPS RX1B 17 47 24 47 23 GNS430(W)(AW) GNS530(W)(AW) 23 1 2 P1 P3 4 5 48(50) 49(51) 48(50) 49(51) ACU P3 18 19 26 27 14 1 15 2 VLOC/ACU RX2A VLOC/ACU RX2B PFD 429 TX1A PFD 429 TX1B Autopilot See Figure: 9.16 for Bendix King 9.17 for S-TEC 9.18 for Century 9.19 for Cessna ARC 9.20 – 9.23A Flight Director _ _ _ _ _ _ _ _ _ _ _ _ 429 RX1B 429 RX1A 429 TX1B 429 TX1A A U T O P I L O T 429 RX2A 429 TX2A 429 TX2B 429 RX2B 1 ID#1 Description B ID#2 NONE GNS430, No GPS2 No NAV2 With Autopilot 2 GNAV Use pins 48 & 49 or 50 & 51 not both. 3 1 *GNS530 and GNS480 use same config as GNS430 1 Over shield or over braid required on this wire bundle to comply with HIRF & Lightning. Extend within back shell if possible. Ground at both ends. 4 2 3 3 Configuration Matrix (see Section 10) CNX-80 GNS-480 P5 4 24 5 25 8 28 2 6 Pins 4 & 24 may be swapped with pins 5 & 25 if configured accordingly. Requires GNS-480 SW v2.3. See Figure 9.27 for GNS- 480 configuration. 5 4 4 5 See Figure 9.27 for GNS-430/530 configuration. Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. This drawing is used for a single GNAV and autopilot interface only. Use Figure 9.8 if adding a second GPS or Analog Nav2 receiver. Figure 9.7 – PRO Single Digital with Autopilot Interface DOCUMENT # 900-00003-001 PAGE 132-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Over Braid or Double Shield Over Braid or Double Shield EFD1000 16 429 GPS RX1A P4001 P4006 P5006 P5001 46 46 24 429 GPS RX1B 17 47 24 47 23 GNS430(W)(AW) GNS530(W)(AW) 23 P3 4 5 48(50) 49(51) 48(50) 49(51) ACU P3 18 19 26 27 14 1 15 2 ACU RX4A ACU RX4B PFD 429 TX1A PFD 429 TX1B Autopilot-optional See Figure: 9.16 for Bendix King 9.17 for S-TEC 9.18 for Century 9.19 for Cessna ARC 9.20 – 9.23A Flight Director _ _ _ _ _ _ _ _ _ _ _ _ 429 RX1B 429 RX1A 429 TX1B 429 TX1A G P S # 2 I N P U T 22 23 V L O C # 2 I N P U T A U T O P I L O T Analog VLOC #2 - optional RS-232/Analog GPS #2 - optional See Figure: 9.12 for KLN89/B & KLN94 9.13 for KLN-90/A/B 9.14 for GX-50/60 & GX-55/65 429 VLOC RX2A 429 VLOC RX2B GNAV #1 RS-232 Flight Plan To EFD1000 Pin 8 429 TX2A 429 TX2B 1 Optional Back-Up Nav Indicator See Figure 9.24, 9.25, 9.26 for Back-Up NAV recommendations. 2 3 ID#1 Description A A A ID#2 D F H GNS430, No GPS2, NAV2 GNS430, GPS2, No NAV2 GNS430, GPS2, NAV2 4 See Figure 9.15 for: KX-155(A) &165(A) KN-53 KX-170A/170B/175/175B SL-30 Use pins 48 & 49 or 50 & 51 not both. 2 *GNS530 and GNS480 use same config as GNS430 3 1 1 1 Over shield or over braid required on this wire bundle to comply with HIRF & Lightning. Extend within back shell if possible. Ground at both ends. 5 3 Configuration Matrix (see Section 10) CNX-80 GNS-480 P5 4 24 5 25 8 28 4 4 See Figure 9.27 for GNS430/530 configuration. 6 Pins 4 & 24 may be swapped with pins 5 & 25 if configured accordingly. Requires GNS-480 SW v2.3. See Figure 9.27 for GNS-480 configuration. 5 2 Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non- Aspen equipment, is for reference only. This drawing is used for a single GNAV with a GPS2 and/or NAV2 and with or w/o autopilot interface. Use Figure 9.7 if No GPS2 and No Analog Nav2 receiver. Figure 9.8 – PRO Digital & Analog Mix with and w/o Autopilot Interface DOCUMENT # 900-00003-001 PAGE 133-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.9 - PRO Dual Digital w/o Autopilot Interface DOCUMENT # 900-00003-001 PAGE 134-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.9A – PRO Dual Digital with Autopilot DOCUMENT # 900-00003-001 PAGE 135-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.10 – PRO ARINC 429 GPS & Analog VLOC (1 or 2) with and w/o Autopilot DOCUMENT # 900-00003-001 PAGE 136-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Over Braid or Double Shield Over Braid or Double Shield Over Braid or Double Shield EFD1000 GPS/VLOC RX2A GPS/VLOC RX2B ACU #1 P3 18 19 26 27 14 1 15 2 PFD 429 TX1A PFD 429 TX1B Autopilot - optional See Figure: 9.16 for Bendix King 9.17 for S-TEC 9.18 for Century 9.19 for Cessna ARC 9.20 – 9.23A Flight Director 429 RX1B 429 RX1A 429 TX1B 429 TX1A G P S I N P U T 22 23 A U T O P I L O T Analog VLOC #2 RS-232/Analog GPS #1 See Figure: 9.12 for KLN89/B & KLN94 9.13 for KLN-90/A/B 9.14 for GX-50/60 & GX-55/65 429 VLOC RX4A 429 VLOC RX4B RS-232 Flight Plan To EFD1000 Pin 8 Analog VLOC #1 ACU #2 14 1 15 2 P3 429 RX1A 429 RX1B Optional Back-Up Nav Indicator Optional Back-Up Nav Indicator V L O C # 2 V L O C # 1 429 TX1B 429 TX1A Autopilot must be connected to ACU #1 See Figure 9.24, 9.25, 9.26 for Back-Up NAV recommendations. If no GPS installed then One backup NAV indicator is required. 2 2 1 2 3 4 Omit ACU #2 if using only 1 Analog Nav. 1 ID#1 Description G H H ID#2 NONE NONE D GPS1, No NAV1, No NAV2 GPS1,NAV1, No NAV2 GPS1, NAV1, NAV2 See Figure 9.15 for: KX-155(A) &165(A) KN-53 KX-170A/170B/175/175B SL-30 See Figure 9.15 for: KX-155(A) &165(A) KN-53 KX-170A/170B/175/175B SL-30 1 1 Over shield or over braid required on this wire bundle to comply with HIRF & Lightning. Extend within back shell if possible. Ground at both ends. 5 3 4 Configuration Matrix (see Section 10) 1 Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.11 – PRO RS232 GPS & Analog VLOC (1 or 2) with and w/o Autopilot DOCUMENT # 900-00003-001 PAGE 137-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 138-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.11A – CNX-80/GNS-480 RS232 with and w/o NAV2 & Autopilot GNS480/CNX80 RS-232 connections are Not Authorized in EFD1000 software version 2.X. Use ARINC 429 connections. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 139-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.11B – CNX-80/GNS-480 RS232 and Analog Interface GNS480/CNX80 RS-232 connections are Not Authorized in EFD1000 software version 2.X. Use ARINC 429 connections. EFD1000 and EFD500 SW v2.X Installation Manual Over Braid or Double Shield EFD1000 9 (8) RS232 IN PORT 2 (1) P3 19 7 ACU GPS +TO /FCS-LOC /OBS-LEG /APPR ACTIVE OBS COS + OBS COS - 1 2 KLN89/B KLN94 6 18 20 8 36 37 35 34 P2 6 7 24 17 18 P1 4 13 6 12 5 15 11 13 14 12 10 OBS SIN - OBS SIN + ROTOR (H) ROTOR (C) APPR ACTIVE FCS LOC /ENG RS-232 OUT OBS RESOLVER COS OBS RESOLVER OUT AC GROUND OBS RESOLVER SIN +TO +FROM LAT FLG + D-BAR +RT D-BAR +LT GPS +UP GPS +RT GPS +LT GPS LAT FLG + GPS LAT FLG - GPS DISPLAYED P1 P2 Vert +UP Vert +DN 12 33 32 P1 31 11 13 8 11 7 14 LAT FLG - Vert FLG + Vert FLG - GPS +DN GPS Vert FLG + GPS +FR GPS Vert FLG - N/C P2 P1 17 /GPS MODE SEL Over shield or over braid required on this wire bundle to comply with HIRF & Lightning. Extend within back shell if possible. Ground at both ends. 1 2 ACFT PWR NO NC K1 3 2 GPS selected on PFD requires open to GPS. NAV1 or NAV2 selected on PFD requires ground to GPS. Use 14V or 28V SPDT relay for K1. 4 KLN-94 may be configured for Standard RS-232 or Enhanced RS-232. See Table 5.3 for corresponding EFD1000 config. 3 Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. 5 Pin 8 may be used provided the interface does not include XM Wx 4 Optionally a twisted pair (22TG2V64 or equiv) may be used with the second conductor grounded at both ends. 6 5 Figure 9.12 – KLN89B & KLN94 RS232 and Analog to ACU Interface DOCUMENT # 900-00003-001 PAGE 140-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 141-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.13 – KLN-90/A/B RS232 and Analog to ACU Interface EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 142-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.14 – GX-50/60 & GX-55/65 RS232 and Analog to ACU Interface EFD1000 and EFD500 SW v2.X Installation Manual ACU 1 NAV Composite P401 P901 A2 A1 H _ KX155/165 Nav units have dual GS outputs. Use “Numbered” or Lettered pins, not both. Use unused pins independent from those driving a backup NAV indicator if possible. Otherwise parallel as close to NAV receiver as possible (see Figure 9.24 & 9.25) KX155 KX165 KX155A KX165A 20 2 32 13 31 12 H 8 8 15 - S 15 - S 14 - R 17 - U 16 - T 17 - U 14 - R 16 - T _ _ _ _ _ _ _ _ _ _ Composite GND /ILS Engage GS +UP GS +DN GS -FLG GS +FLG 1 1 1 ACU 1 NAV Composite P532 P1 B KN-53 SL-30 20 2 32 13 31 12 12 15 32 28 31 13 14 P R Composite GND /ILS Engage GS +UP GS +DN GS -FLG GS +FLG 1 30 33 37 19 2 2 Glideslope interface is for units with GS option. 3 P2 P2 KX170A/ 170B/175B P171 3 4 See manufacturers’ documentation for KN-70 and KN-73 Glideslope connections. 3 _ _ _ _ _ 4 2 2 See Figure 9.27 for SL-30 configuration. If paralleling GS signals with backup NAV indicator then splice wires as close to NAV receiver as possible. Do not parallel at back of NAV indicator (see Figures 9.24 & 9.25) 3 4 Diode required when paralleling ILS Energize wire with backup NAV indicator. See Figure 9.24. Use 1N4005 or equivalent. 5 4 Diode required when paralleling ILS Energize wire with backup NAV indicator. See Figure 9.24. Use 1N4005 or equivalent. Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. 3 Refer to manufacturers’ documentation to verify the integration data and for information regarding checkout procedures. This drawing, as it pertains to the non-Aspen equipment, is for reference only. Figure 9.15 – Analog NAV Interface DOCUMENT # 900-00003-001 PAGE 143-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual   Figure 9.15A – Narco and Cessna ARC Navigation Radios DOCUMENT # 900-00003-001 PAGE 144-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.16 – KI525A Emulation (Bendix/King autopilot to ACU) DOCUMENT # 900-00003-001 PAGE 145-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.17 – STEC Autopilot to ACU Interface (minus HDG/CRS Datum) Figure 9.17A – KI525A Emulation (STEC Autopilot) DOCUMENT # 900-00003-001 PAGE 146-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.17B – NSD360A Emulation (STEC Autopilot) DOCUMENT # 900-00003-001 PAGE 147-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.18 – Century Autopilot to ACU Interface (minus HDG/CRS Datum) Figure 9.18A – NSD360A Emulation (Century 21/31/41/2000) DOCUMENT # 900-00003-001 PAGE 148-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual C F ROLL EXC ROLL EXC A B D E 21 22 3 HDG SIG ROLL COM N/C ( DATUM EXCITATION HDG DATUM CRS DATUM CD33 TO AMP (connector on Radio Coupler) PARALLEL WITH EXISTING WIRES CD33 TO DG (pigtail) T1 T2 10K :10K 10K :10K C1 = .027uF min 50V L1 = 27mH The value of R1 can range from 0K to 300K. A value for R1 should be selected that sets the NAV intercept angle at 45 degrees. Consult autopilot manufacturers’ reference documents for post install checkout procedures. P3 ACU CENTURY 1C-388 & 1C388-M RADIO COUPLERS (5Khz) 10k 1/4W 10k 1/4W T1/T2/T3 - Use MAGNETEC TY-141P, DigiKey # 237-1118-ND or equivalent. L1 - JW Miller PN: 9250A-276-RC, Digikey # M10108-ND or equivalent. C1 – Panasonic ECQE2273KS, Digikey # 2273-ND or equivalent. ROLL EXC ROLL EXC 23 22 3 HDG SIG CRS SIG DATUM EXCITATION HDG DATUM CRS DATUM T1 T2 10K :10K 10K :10K P3 ACU CENTURY 1C-388-2 RADIO COUPLER (5Khz) 10k 1/4W 10k 1/4W D E A B B T3 ROLL COM 10K :10K R1 R1 10k 1/4W This radio coupler does not have CRS Datum interface. You must upgrade to 1C-388-2 coupler to gain this feature. Set ACU HSI TYPE = 1 Set ACU DATUM = REVERSED Set ACU HSI TYPE = 1 Set ACU DATUM = REVERSED 10 SIGNAL COMMON 10 11 11 CRS/HDG COM CRS/HDG COM SIGNAL COMMON 1 1 1 2 2 3 Refer to autopilot manufacturers’ documentation for autopilot- side integration information (including autopilot 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. CD33 TO DG (pigtail) PARALLEL WITH EXISTING WIRE CD33 TO AMP (connector on Radio Coupler) Figure 9.18B – NSD360A Emulation Century 1C388/M and 1C388-2 Radio Couplers DOCUMENT # 900-00003-001 PAGE 149-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 150-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.18C - NSD360A Emulation Century 1C388-3 Radio Coupler 3 CRS DATUM 23 22 49 P3 HDG DATUM HDG-CRS EXT 48 ACU CD-66 Century IV (DC Version) 13 +14Vdc reference ID496 Computer Configuration Matrix (see Section 10) Refer to autopilot manufacturers’ documentation for autopilot-side integration information (including autopilot 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. Set ACU HSI TYPE = 1 Set ACU DATUM = REVERSED Heading Signal Course Signal In order to use this interconnect the ID496 Computer Amplifier must have Roll Module 1C695-1 installed to be NSD-360 compatible. 1 1 2 Figure 9.18D - NSD-360A Emulation Century IV (DC version) EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 151-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.19 – Cessna ARC Autopilot to ACU Interface (minus HDG/CRS Datum) 3 CRS DATUM 17 23 22 11 24 21 _ _ P3 HDG DATUM CRS/HDG COM HDG-CRS EXT _ If the existing DG/HSI is to remain in the aircraft do not parallel HDG/CRS Datum with ACU. Cap and Stow at DG/HSI or use switch. Existing DG installations must make CRS Datum connection as shown to gain full HSI features. Remove Jumper from J2-17 to J1-21 if installed. ACU J1-P4 J2-P5 CA-550/FD 300B/400B/ 800B When replacing IG-832A/IG-895A or NSD-360A Set ACU HSI TYPE = 1 Configuration Matrix (see Section 10) 10 _ 2 2 1 3 Refer to autopilot manufacturers’ documentation for autopilot-side integration information (including autopilot 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. CA-550/FD J1-24 and J2-17 may have been 4 previously connected to ground if they were unused. These prior connections must be removed. 3 Figure 9.19A - NSD-360A Emulation (Cessna ARC 300B/400B/800B) IFCS EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.19B – NSD-360A Emulation (Cessna ARC 300A “AC” & DC”) DOCUMENT # 900-00003-001 PAGE 152-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.20 – KI-256 Emulation (Bendix King Autopilot) DOCUMENT # 900-00003-001 PAGE 153-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.21 – 52C77 Emulation (Century 41/2000 Autopilot) Fi gure 9.21A – 52C77 Emulation (Century IV Autopilot) DOCUMENT # 900-00003-001 PAGE 154-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.22 – G550A Emulation (Cessna ARC Autopilot) DOCUMENT # 900-00003-001 PAGE 155-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.23 – KI256 Emulation (STEC 55/55X Autopilot) Figure 9.23A – KI256 Emulation (STEC 60/65 Autopilot) DOCUMENT # 900-00003-001 PAGE 156-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.24 – Back-up NAV Indicator (Internal Converter) DOCUMENT # 900-00003-001 PAGE 157-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.25 – Back-up NAV Indicator (OBS Resolver) DOCUMENT # 900-00003-001 PAGE 158-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 9.26 – Back-up NAV/GPS Indicator (GNS-430/530) DOCUMENT # 900-00003-001 PAGE 159-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 160-256 Revision G © Copyright 2010 Aspen Avionics Inc. GNS-430/530(W) & GPS-400/500(W) MAIN ARINC 429 CONFIG Page IN 1 Low Honeywell EFIS (when using pins 48/49) IN 2 As required OUT Low GAMA 429 Graphics w/INT SDI COMMON VNAV ENABLE LABELS (W models only) VOR/LOC/GS ARINC 429 CONFIG Page SPEED Low RX Low TX SDI COMMON Garmin SL-30 The SL-30 can be connected to the EFD1000 in one of two ways. The Resolver configuration is preferred. The composite output from the SL-30 to the PFD will become invalid whenever VOR monitor mode or localizer back course is selected on the SL-30. The navigation source will show as failed on the PFD if either of these two modes is entered and the SL-30 is the selected navigation source. If connected, the backup NAV indicator will continue to function if either of these two modes is selected. VOR monitor mode or localizer back course mode are disabled from selection on the SL-30. A backup NAV indicator (GI-106) cannot be connected without a KN- 72 between the SL-30 and indicator due to the fact that the OBS resolver inputs become invalid with this configuration. CNX-80/ GNS-480 (software 2.0 and below) This configuration is not authorized. The GNS-480 should be upgraded to software version 2.3 (see below) GPS 155XL 429 IN = SELECTED COURSE 429 OUT = KING EFS 40/50 KLN-94 MAINTENANCE PAGE 7: *STANDARD RS-232 or *ENHANCED RS-232 *See Table 5.3 for details CNX-80/ GNS-480 (software 2.3) GND MAINT - ARINC 429 SETUP CH_IN SEL SPEED SDI 2 EFIS LOW SYS1 or SYS2 CH_OUT SEL SPEED SDI 1 *GAMA 429 GFX Int LOW SYS1 or SYS2 2 VOR/ILS LOW SYS1 or SYS2 *GAMA 429 GFX Int – this configuration has Flight Plan information. GND MAINT – MISCELLANEOUS SETUP CDI SELECT: USE With this configuration the EFD1000 will read the GNS480 CDI logic state on the A429 bus and toggle between GPS and VLOC on the PFD when pressing the GNS480 CDI button. EFD1000 will use GPS/NAV ID’s A and B Figure 9.27 – Additional Configuration Notes EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 161-256 Revision G © Copyright 2010 Aspen Avionics Inc. Figure 9.28 – Traffic/XM Wx/WX500/ADC Sensor Interfaces EFD1000 and EFD500 SW v2.X Installation Manual 44 PIN 7 D IG I T A L _ O U T 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B ARINC 429 Traffic Sensor (TAS or TIS) ARINC 429 OUT B ARINC 429 OUT A EWR50 RS-232_RX RS232_TX WX-500 RS-232_RX RS232_TX 2 1 3 4 5 6 PFD or ACU A429 TX may be connected to the traffic sensor for Label 320 “Magnetic Heading” only. No traffic control panel functions are output by EFD1000 system. 7 8 9 See the EFD1000 Installation Manual for Sonalert option. ARINC 429 IN B ARINC 429 IN A Existing WX-500 Display See the existing Display’s Installation Manual for specifications. Existing Traffic Display See the existing Sensor’s Installation Manual for pin connections and complete interface to aircraft. 20 8 22 4 3 1 1 See the EFD1000 Installation Manual for GPS/NAV connections. Parallel connections to both the PFD and MFD for full reversion capability. 8 8 9 10 RS-232 GPS 9 Note, pre-existing RS232 GPS installations may be connected to PFD pin 8. These must be re-pinned to PFD pin 9 when installing XM weather. 2 EFD1000 MFD EFD500 MFD PFD with EFD1000 MFD or EFD500 MFD (optional) (optional) (optional) (optional) (optional) (optional) Carry shielding though all wire splices. RS232 wiring only - Optionally a twisted pair (22TG2V64 or equiv) may be used with the second conductor grounded at both ends in lieu of single conductor shown. See Figure 9.1 for CM and RSM wiring connections 7 7 ARINC 429 TX to the ACU or GPS A429 IN. See the EFD1000 Installation Manual Figures 9.6 to 9.10 for connections 4 See EWR50 Installation Manual for complete interface to aircraft. 5 10 10 10 10 10 10 6 EFD1000 PFD 44 PIN 7 D I G IT A L _ O U T 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B Inter-System Bus Configuration 232 IN PORT 4 EFD1000 MFD* or EFD500 MFD* 232 OUT PORT 2 EFD PFD MFD 500 or MFD 1000 232 OUT PORT 2 232 IN PORT 5 EFD1000 PFD EFD DISPLAY RS232 PORT PORT SETTING * Set to EFD1000 MFD or EFD500 MFD as per installed Figure 9.29 - Two Display System PFD/MFD, Generic DOCUMENT # 900-00003-001 PAGE 162-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual EFD500 MFD 44 PIN 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R I N C 4 2 9 _ R X 1 A A R I N C 4 2 9 _ R X 1 B A R I N C 4 2 9 _ R X 2 A A R I N C 4 2 9 _ R X 2 B A R I N C 4 2 9 _ R X 3 A A R I N C 4 2 9 _ R X 3 B A R I N C 4 2 9 _ R X 4 A A R I N C 4 2 9 _ R X 4 B A R I N C 4 2 9 _ R X 5 A A R I N C 4 2 9 _ R X 5 B EFD1000 PFD 44 PIN 7 D I G IT A L _ O U T 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B EFD1000 MFD 44 PIN 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B ARINC 429 Traffic Sensor (TAS or TIS) ARINC 429 OUT B ARINC 429 OUT A EWR50 RS-232_RX RS232_TX WX-500 RS-232_RX RS232_TX 6 PFD or ACU A429 TX may be connected to the traffic sensor for Label 320 “Magnetic Heading” only. No traffic control panel functions are output by EFD1000 system. 7 8 9 ARINC 429 IN B ARINC 429 IN A Existing WX-500 Display See the existing Display’s Installation Manual for specifications. Existing Traffic Display See the existing Sensor’s Installation Manual for pin connections and complete interface to aircraft. 20 8 22 4 3 1 1 1 8 8 9 10 RS-232 GPS 9 Note, pre-existing RS232 GPS installations may be connected to PFD pin 8. These must be re-pinned to PFD pin 9 when installing XM weather. 2 1 3 4 ARINC 429 TX to the ACU or GPS A429 IN. See the EFD1000 Installation Manual Figures 9.6 to 9.10 for connections 5 See the EFD1000 Installation Manual Figure 9.1 for Sonalert option. See the EFD1000 Installation Manual Figures 9.6 to 9.15 for GPS/NAV connections. Parallel connections to both the PFD and MFD. (optional) (optional) (optional) (optional) (optional) (optional) See Figure 9.1 for CM and RSM wiring connections 7 7 7 2 4 6 10 10 10 10 10 10 10 10 10 10 5 See EWR50 Installation Manual for complete interface to aircraft. PFD with EFD1000 MFD and EFD500 MFD Inter-System Bus Configuration 232 IN PORT 4 EFD1000 MFD 232 OUT PORT 2 EFD500 MFD PFD MFD 1000 DISPLAY RS232 PORT PORT SETTING MFD 500 232 IN PORT 5 EFD 232 IN PORT 4 EFD1000 MFD 232 OUT PORT 2 EFD1000 PFD 232 IN PORT 5 EFD 232 IN PORT 4 EFD500 MFD 232 OUT PORT 2 EFD1000 PFD 232 IN PORT 5 EFD Carry shielding though all wire splices. RS232 wiring only - Optionally a twisted pair (22TG2V64 or equiv) may be used with the second conductor grounded at both ends in lieu of single conductor shown. Figure 9.30 - Three Display System PFD/MFD1000/MFD500, Generic DOCUMENT # 900-00003-001 PAGE 163-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual EFD1000 PFD 44 PIN 7 D IG IT A L _ O U T 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B EFD1000 MFD 44 PIN 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B P3 ACU ARINC 429_TX1A 2 ARINC 429_TX1B 15 ARINC 429_RX1A 1 ARINC 429_RX1B 14 ARINC 429_TX2A 4 ARINC 429_TX2B 5 ARINC 429 Traffic Sensor (TAS or TIS) ARINC 429 OUT B ARINC 429 OUT A EWR50 RS-232_RX RS232_TX WX-500 RS-232_RX RS232_TX 2 1 3 4 Existing PFD installation may have used pin 8 for the RS232 GPS connection. This wire must be moved to pin 9 when adding the optional EWR50 XM receiver 5 6 ACU A429 TX2 (pins 4,5) may be connected to the traffic sensor for Label 320 “Magnetic Heading” only. No traffic control panel functions are output by EFD1000 system 7 8 9 See the EFD1000 Installation Manual for Sonalert option ARINC 429 IN B ARINC 429 IN A See the existing Display’s Installation Manual for specifications See the existing Sensor’s Installation Manual for pin connections and complete interface to aircraft 20 8 22 4 See Figure 9.2 for ACU power and ground connections 3 This drawing is used for existing PFD installations that wired to Figure 9.8 or have one GNAV with Analog NAV and/or GPS. Other configurations must use their appropriate drawing. 9 10 10 11 9 PFD with EFD1000 or EFD500 MFD Config: (1A-2D) GNAV and Analog NAV#2 Config: (1A-2H) GNAV and Analog NAV#2 and RS232 GPS#2 Config: (1A-2F) GNAV and RS232 GPS#2 (optional) (optional) (optional) See Figure 9.1 for PFD/MFD power and CM/RSM wiring connections 7 7 PX001 PX006 47 46 23 24 GNS430/530 48(50) 49(51) _ _ _ _ _ _ Autopilot-optional See Figure: 9.16 for Bendix King 9.17 for S-TEC 9.18 for Century 9.19 for Cessna ARC 9.20 – 9.23A Flight Director Analog VLOC #2 - optional RS-232/Analog GPS #2 - optional RS-232 Flight Plan To PFD and MFD Pin 9 See Figure 9.15 for: KX-155(A) &165(A) KN-53 KX-170A/170B/175/175B SL-30 See Figure: 9.12 for KLN89/B & KLN94 9.13 for KLN-90/A/B 9.14 for GX-50/60/55/65 GNS480 P5 24 4 25 5 8 28 GNAV 1 2 5 6 See Figure 9.3 for DH wiring connections 11 11 11 11 11 C O N F IG _ A C O N F IG _ B C O N F IG _ C C O N F IG _ D 4 1 4 2 4 3 4 4 C O N F IG _ A C O N F IG _ B C O N F IG _ C C O N F IG _ D 4 1 4 2 4 3 4 4 7 7 3 2 R S M _ C 3 3 R S M _ D 3 4 R S M _ E 3 5 R S M _ F 3 6 R S M _ G 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 3 2 R S M _ C 3 3 R S M _ D 3 4 R S M _ E 3 5 R S M _ F 3 6 R S M _ G 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 EFD500 MFD 4 EFD500 installations do not use an RSM. Inter-System Bus Configuration 232 IN PORT 4 EFD1000 MFD* or EFD500 MFD* 232 OUT PORT 2 EFD PFD MFD 500 or MFD 1000 232 OUT PORT 2 232 IN PORT 5 EFD1000 PFD EFD DISPLAY RS232 PORT PORT SETTING * Set to EFD1000 MFD or EFD500 MFD as per installed Carry shielding though all wire splices. RS232 wiring only - Optionally a twisted pair (22TG2V64 or equiv) may be used with the second conductor grounded at both ends in lieu of single conductor shown. Figure 9.31 - Two Display System PFD/MFD, GNAV1 and Analog NAV#2 or GPS#2 Configurations (1A-2D) or (1A-2H) or (1A-2F) DOCUMENT # 900-00003-001 PAGE 164-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 165-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 PFD 44 PIN 7 D IG IT A L _ O U T 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B EFD500 MFD 44 PIN 8 R S 2 3 2 _ R X 1 9 R S 2 3 2 _ R X 2 1 0 R S 2 3 2 _ R X 3 1 1 R S 2 3 2 _ R X 4 1 2 R S 2 3 2 _ R X 5 1 3 R S 2 3 2 _ T X 1 1 4 R S 2 3 2 _ T X 2 1 5 R S 2 3 2 _ T X 3 2 6 2 7 A R IN C 4 2 9 _ T X 1 A A R IN C 4 2 9 _ T X 1 B 1 6 1 7 1 8 1 9 2 0 2 1 2 2 2 3 2 4 2 5 A R IN C 4 2 9 _ R X 1 A A R IN C 4 2 9 _ R X 1 B A R IN C 4 2 9 _ R X 2 A A R IN C 4 2 9 _ R X 2 B A R IN C 4 2 9 _ R X 3 A A R IN C 4 2 9 _ R X 3 B A R IN C 4 2 9 _ R X 4 A A R IN C 4 2 9 _ R X 4 B A R IN C 4 2 9 _ R X 5 A A R IN C 4 2 9 _ R X 5 B P3 ACU ARINC 429_TX1A 2 ARINC 429_TX1B 15 ARINC 429_RX1A 1 ARINC 429_RX1B 14 ARINC 429_TX2A 4 ARINC 429_TX2B 5 ARINC 429 Traffic Sensor (TAS or TIS) ARINC 429 OUT B ARINC 429 OUT A EWR50 RS-232_RX RS232_TX WX-500 RS-232_RX RS232_TX 2 1 3 4 VLOC #2 wiring is a no connect if GNAV #2 is an A429 GPS only (i.e, GPS400) 5 6 ACU A429 TX2 (pins 4,5) may be connected to the traffic sensor for Label 320 “Magnetic Heading” only. No traffic control panel functions are output by EFD1000 system 7 8 9 See the EFD1000 Installation Manual for Sonalert option ARINC 429 IN B ARINC 429 IN A See the existing Display’s Installation Manual for specifications See the existing Sensor’s Installation Manual for pin connections and complete interface to aircraft 20 8 22 4 See Figure 9.2 for ACU power and ground connections 3 This drawing is used for existing PFD installations that are wired to Figure 9.9A or new installations of dual GNAV radios. Other configurations must use their appropriate drawing 9 10 10 11 9 PFD with EFD1000 or EFD500 MFD Config: (1B-2A) GNAV #1 and GNAV #2 Config: (1B-2C) GNAV #1 and A429 GPS #2 (optional) (optional) (optional) See Figure 9.1 for PFD/MFD power and CM/RSM wiring connections 7 7 PX001 PX006 47 46 23 24 GNS430/530 48(50) 49(51) _ _ _ _ _ _ GNS480 P5 24 4 25 5 8 28 GNAV #1 See Figure 9.3 for DH wiring connections 11 11 11 11 11 C O N F IG _ A C O N F IG _ B C O N F IG _ C C O N F IG _ D 4 1 4 2 4 3 4 4 C O N F IG _ A C O N F IG _ B C O N F IG _ C C O N F IG _ D 4 1 4 2 4 3 4 4 7 PX001 PX006 47 46 23 24 GNS430/530 48(50) 49(51) _ _ _ _ _ _ GNS480 P5 24 4 25 5 8 28 GNAV #2 P1 1 2 11 11 ARINC 429_RX2A ARINC 429_RX2B 2 5 6 1 3 2 R S M _ C 3 3 R S M _ D 3 4 R S M _ E 3 5 R S M _ F 3 6 R S M _ G 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 EFD1000 MFD 3 2 R S M _ C 3 3 R S M _ D 3 4 R S M _ E 3 5 R S M _ F 3 6 R S M _ G 3 1 R S 2 3 2 _ R X 0 3 0 R S 2 3 2 _ T X 0 4 EFD500 installations do not use an RSM. Inter-System Bus Configuration 232 IN PORT 4 EFD1000 MFD* or EFD500 MFD* 232 OUT PORT 2 EFD PFD MFD 500 or MFD 1000 232 OUT PORT 2 232 IN PORT 5 EFD1000 PFD EFD DISPLAY RS232 PORT PORT SETTING * Set to EFD1000 MFD or EFD500 MFD as per installed Carry shielding though all wire splices. RS232 wiring only - Optionally a twisted pair (22TG2V64 or equiv) may be used with the second conductor grounded at both ends in lieu of single conductor shown. Figure 9.32 - Two Display System PFD/MFD, GNAV1 and GNAV2 Configurations (1B-2A) or (1B-2C) EFD1000 and EFD500 SW v2.X Installation Manual THIS PAGE IS INTENTIONALLY LEFT BLANK DOCUMENT # 900-00003-001 PAGE 166-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10 Configuration and Equipment Checkout Print a copy of Appendix B – Installation Final Check Sheet prior to starting any tests. 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. The following Test Equipment will be required to complete the remaining steps in the ground test procedure: • Pitot Static Test Set • NAV/ILS Signal Generator • Digital Multimeter 10.1 Post Installation Wiring Checks 10.1.1 Wiring Verification a) Do not install the EFD, ACU, RSM or configuration module until instructed to do so in Section 10.3. b) Perform a continuity check on all wires between the EFD, ACU, RSM, Configuration Module and their associated connections per wiring diagrams. c) Verify over shields or over braids are installed on required wiring bundles. d) Apply aircraft power and close the EFIS, MFD, and ACU circuit breakers and the EFIS and MFD master switch if installed. e) Verify proper voltage on EFD main connector pins 1, 2, and 3 and that there are proper grounds on pins 4, 5, and 6. f) If installed, verify proper voltage on ACU P1-10 and ground on P1-3. 10.1.2 Bonding Check – FAR 23.867(b) a) Verify braided bonding strap is installed between EFD ground stud and airframe ground. b) Verify EFD mounting bracket is bonded to instrument panel with no greater than 3 milliohms resistance. c) Verify ACU(s) chassis is bonded to airframe with no greater than 3 milliohms resistance. d) Verify RSM base plate or doubler plate is bonded to airframe with no greater than 3 milliohms resistance. e) Verify EBB58 Emergency Backup Battery mounting bracket (if installed) is bonded to airframe with no greater than 3 milliohms resistance. DOCUMENT # 900-00003-001 PAGE 167-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.2 Database Installation Each EFD1000 MFD and EFD500 MFD comes with a data card which must be installed during operation. The EFD1000 PFD does not require a data card. See Section 1 “MFD Database Versions” for data card types available. If the data card is removed a “Database Failure” message will be shown when the system loads additional data (normally the aircraft has flown some distance). The data card contains Terrain, Obstacle, Cultural, and NavData. The NavData, Obstacle, and Cultural data is available for download on a 28 day cycle from Jeppesen. The Terrain data cannot be downloaded and ships on the microSD card. Extra and replacement cards are purchased directly from Jeppesen at 1-800-621-5377 or email [email protected]. The data card is inserted in the card slot at the base the MFD. The data card (microSD card) is inserted with the metal contacts facing down and toward the display. The card is inserted until it is almost flush with the display bezel and locks into place. To remove the data card simply push in on the card and it will eject part way. It then may be removed from the MFD. 10.3 Initial System Turn On Remove power by pulling applicable circuit breakers. Install all EFD(s), ACU(s), RSM(s), and Configuration Module(s). Push in all applicable circuit breakers and apply power. Verify the EFD displays the initialization page after 5 seconds. The MFD will display database loading information in a small window at the bottom of the Navigation Map screen. Configure all systems using Section 10.4 prior to system check out. NOTE: AHRS Flags may take up to 3 minutes to clear. Airspeed and Altitude flags may take up to 20 minutes to clear at temperatures below -20ºC. NOTE: The MFD’s may require up to 3 minutes to completely load all database features. Menu pages and configuration pages may be accessed during this time. DOCUMENT # 900-00003-001 PAGE 168-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.4 System Configuration Configure the EFD1000/500 system(s) prior to running the ground test procedure. The configuration pages are accessed through the EFD 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” button. See PFD Pilot Guide and MFD Pilot Guide for Main Menu operation. 10.4.2 Menu Navigation When no fields are enabled for editing, rotating the right control knob clockwise advances to the next menu page and counterclockwise advances to a previous menu page. Editable menu items are displayed in white text on a blue background, non-editable menus items are green text on a blue background while grey text on a blue background is disabled from editing. 10.4.3 Edit Mode Pushing the line select key adjacent to an editable field enables the associated field for editing. The field turns magenta when enabled and the right control knob reads “Edit Value”. When the field is enabled for editing rotating the right control knob will adjust the value. Pushing the right control knob or the adjacent line select key will exit from the editable field. 10.4.4 Main Menu Configuration The Main Menu consists of pages that are pilot selectable. Refer to the PFD Pilot Guide and MFD Pilot Guide for Main Menu configuration if necessary. DOCUMENT # 900-00003-001 PAGE 169-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.4.5 INSTALLATION MENU – UNIT CONFIGURATION The Installation Menu is entered from the Main Menu’s “SYSTEM STATUS PAGE” (page 11 of 11. Simultaneously push and hold the MENU key, Line Select Key #1 and Line Select Key #2 for 3 seconds while the airspeed is below 30 units. Figure 10.1 – Installation Menu Access Whenever the warning message in Figure 10.2 is displayed, pressing either control knob shall advance the Installation menu. WARNING: THE INSTALLATION MENU CONFIGURATION SETTINGS MUST BE SET IN ACCORDANCE WITH THE APPROVED INSTALLATION INSTRUCTIONS. UNAUTHORIZED MODIFICATION OF THESE INSTALLATION SETTINGS MAY INVALIDATE THE TYPE CERTIFICATED STATUS OF THIS AIRCRAFT AND/OR RENDER IT UNAIRWORTHY. PRESS EITHER CONTROL KNOB TO ACCEPT Figure 10.2 – Installation Menu Warning 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 40 seconds. DOCUMENT # 900-00003-001 PAGE 170-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Select the appropriate section from the following pages that applies to your system or systems. The EFD1000 PFD, EFD1000 MFD, and the EFD500 MFD have identical page layouts and configuration options. The EFD500 MFD pages are unique in that some configuration options are grayed out because they refer to a depopulated ADAHRS function. • Section 10.4.6 EFD1000 PFD and MFD (print twice for dual EFD1000 systems) • Section 10.4.7 EFD500 MFD Record aircraft information at the beginning of the section and record the configuration in each table as shown below. Make a copy of the appropriate section with the information recorded for inclusion into Appendix D – Instructions for Continued Airworthiness. Use section 10.4.7.1 – Configuration Definitions, to assist with configuration “Options” selection. EXAMPLE: Installation Date: Aircraft Model: EFD1000 S/N: Aircraft Type: RSM S/N: Aircraft S/N: ACU S/N: CM S/N: EXAMPLE: INSTALLATION MENU PAGE 9 – ACU CONFIG SW v1.0 Feature Options Actual Setting ACU HSI TYPE 0,1 (0=KI525A, 1=NSD360) ACU FD TYPE 0,1,3,4 (0=NONE,1=KI256, 3=G550) ACU DATUM NORMAL,REVERSED FD PITCH OFFSET ADJ -10.0 to +10.0 (degrees) FD ROLL OFFSET ADJ -10.0 to +10.0 (degrees) Notes: Record Aircraft and Equipment Data Record installation as configured and wired DOCUMENT # 900-00003-001 PAGE 171-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.4.6 EFD1000 Installation Menu Configuration Use this form for both the EFD1000 PFD and EFD1000 MFD INSTALLATION MENU Configuration – EFD1000 Installation Date: Aircraft Model: EFD1000 S/N: Aircraft Type: RSM S/N: Aircraft S/N: ACU S/N: CM S/N: WARNING: Only a Certified Mechanic may set the values on Installation Menu pages 1 and 2. The values must match the certified speeds in the Aircraft Flight Manual (AFM), Pilot Operating Handbook (POH), or other legal form of documentation (e.g., Placard). INSTALLATION MENU PAGE 1 - IAS CONFIG A Set Speed Bands per Aircraft Flight Manual. INSTALLATION MENU PAGE 1 – IAS CONFIG A SW v2.0 Feature Options Actual Setting Vne 0 to 450 Vno 0 to 450 Vfe 0 to 450 Vs 0 to 450 Vso 0 to 450 Notes: INSTALLATION MENU PAGE 2 – IAS CONFIG B Set Speed Markers per Aircraft Flight Manual. INSTALLATION MENU PAGE 2 – IAS CONFIG B SW v2.0 Feature Options Actual Setting Vyse 0 to 450 Vmc 0 to 450 Triangle 0 to 450 Not Used Not Used Notes: INSTALLATION MENU PAGE 3- IAS CONFIG C Set IAS UNITS per Aircraft Flight Manual. Configure TAPES based on Flowchart in Figure 10.3. VPSD EDIT is set based on “Operator Configuration Checklist” of Appendix C or to owner/operator preference. INSTALLATION MENU PAGE 3 – IAS CONFIG C SW v2.0 Feature Options Actual Setting IAS UNITS kts, mph TAPES UNLOCKED, LOCK OFF, LOCK ON VSPD EDIT UNLOCKED, LOCKED Not Used Not Used Notes: DOCUMENT # 900-00003-001 PAGE 172-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD1000 (continued) INSTALLATION MENU PAGE 4 – 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. The GPS A429 Rx Port speed will be set to HIGH or LOW. Set NAV#2 Position Source to GPS1 if it is desired to have GPS1 map data displayed when VLOC#2 is selected. Set to GPS2 if GPS2 map data is to be displayed when VLOC#2 is selected. INSTALLATION MENU PAGE 4 – NAV SET UP SW v2.0 Feature Options Actual Setting GPS/NAV #1 NONE,A,B,C,D,E,F,G,H,I,J,K,L,M,P,Q,R GPS/NAV #2 NONE,A,B,C,D,E,F,G,H,I,J,K,L,M GPS/NAV#1 Speed HIGH, LOW GPS/NAV#2 Speed HIGH, LOW NAV#2 POSITION SOURCE: GPS1, GPS2 1 Notes: (1) Set to GPS2 for dual integrated GPS units (i.e. dual GNS-430/530’s) INSTALLATION MENU PAGE 5 – RS232 PORT CONFIG A The following menu is used to configure the RS-232 RX IN sensor ports. Options include GPS TYPE X, WX500, XM Weather, RSM, EFD1000 PFD, EFD1000 MFD, and EFD500 MFD inter- system communication. Note - some ports do not include all interface options. (See wiring diagrams in sections 9 to determine how each port was wired and configure port accordingly) INSTALLATION MENU PAGE 5 – RS232 PORT CONFIG A SW v2.0 Feature Options Actual Setting 232 IN PORT 0 NONE, RSM 232 IN PORT 1 NONE, GPS TYPE 1, GPS TYPE 2, GPS TYPE 3, XM 232 IN PORT 2 NONE, GPS TYPE 1, GPS TYPE 2, GPS TYPE 3 232 IN PORT 3 NONE, WX500 232 IN PORT 4 NONE, EFD1000 MFD, EFD1000 PFD, EFD500 MFD Notes: GPS TYPE 1= KLN94/90B, GPS TYPE 2= KLN94 Enhanced, GPS TYPE 3= GX50/55/60/65 and GNS480 INSTALLATION MENU PAGE 6 – RS232 PORT CONFIG B The following menu is used to configure the RS-232 RX IN 5 sensor port and the four RS- 232 TX OUT ports. Options include XM Weather, WX500, ADC (two types) and PFD or MFD inter-system communications. Note - some ports do not include all interface options. (See wiring diagrams in sections 9 to determine how each port was wired and configure port accordingly) DOCUMENT # 900-00003-001 PAGE 173-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD1000 (continued) INSTALLATION MENU PAGE 6 – RS232 PORT CONFIG B SW v2.0 Feature Options Actual Setting 232 IN PORT 5 NONE, EFD1000 MFD, EFD1000 PFD, EFD500 MFD 232 OUT PORT 0 NONE, RSM 232 OUT PORT 1 NONE, XM, ADC TYPE 1, ADC TYPE 2 232 OUT PORT 2 NONE, EFD, ADC TYPE 1, ADC TYPE 2 232 OUT PORT 3 NONE, WX500, ADC TYPE 1, ADC TYPE 2 Notes: ADC TYPE 1=”Z” format, ADC TYPE 2=”C” format Note: EFD is any PFD or MFD INSTALLATION MENU PAGE 7 – ACU CONFIG The following menu configures the emulation modes for the Flight Director and HDG and CRS Datum interfaces. The installation wiring diagrams in Section 9 have a Configuration Matrix table that will be used to set ACU HSI TYPE and ACU FD TYPE. (See Section 10.4.7.1 for example). Flight Director display pitch and roll offset adjustments are also made. INSTALLATION MENU PAGE 7 – ACU CONFIG SW v2.0 Feature Options Actual Setting ACU HSI TYPE 0,1 (0=KI525A, 1=NSD360) ACU FD TYPE 0,1,3,4 (0=NONE,1=KI256, 3=G550, 4=52C77) ACU DATUM NORMAL,REVERSED FD PITCH OFFSET ADJ -10.0 to +10.0 (degrees) FD ROLL OFFSET ADJ -10.0 to +10.0 (degrees) Notes: These settings do not apply to the EFD500 MFD INSTALLATION MENU PAGE 8 – MISC CONFIG A The following menu will be used to configure the RSM orientation, enable or disable the emergency GPS sensor located in the RSM, and configure the OAT sensor. INSTALLATION MENU PAGE 8 – MISC CONFIG A SW 2.0 Feature Options Actual Setting RSM Orientation TOP, BOTTOM (Inverted orientation) RSM GPS Enable DISABLE, ENABLE OAT Enable DISABLE, ENABLE Notes: INSTALLATION MENU PAGE 9 – MISC CONFIG B The following menu will be used to set the aircraft electrical system voltage. EFD Battery Config will be set to INTERNAL for all -001 displays and REMOTE for all -002 displays. The pitch attitude zero reference point is aligned for tilted instrument panels and the roll attitude trim is adjusted to compensate for slightly misaligned EFD mounting in the instrument panel. (See Section 10.4.5.4 for Panel Tilt Pitch Adj, Panel Roll Adj, and Attitude Ref Symbol adjustments) DOCUMENT # 900-00003-001 PAGE 174-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD1000 (continued) INSTALLATION MENU PAGE 9 – MISC CONFIG B SW 2.0 Feature Options Actual Setting ELEC SYSTEM 14 VOLT, 28 VOLT EFD BATTERY CONFG: INTERNAL, REMOTE* ATTITUDE REF SYMBOL ADJ: -5.0 to +5.0 degrees PANEL TILT PITCH ADJ -10.0 to +20.0 degrees PANEL ROLL ADJ -2.0 to +2.0 degrees Notes: * REMOTE is for EFD1000 MFD with EBB58 only INSTALLATION MENU PAGE 10 – MISC CONFIG C The following menu will be used to configure the analog VOR receiver composite phase to either 0 or 180 degrees. The GPSS Gain can be increased or decreased from the default setting of 1.0 should this setting not be acceptable. If a traffic receiver is connected then set the 429 IN PORT 5 to TRAFFIC, otherwise set to NONE. INSTALLATION MENU PAGE 10 – MISC CONFIG C SW 2.0 Feature Options Actual Setting COMPOSITE PHASE(VOR1,2) (0,0) (180,0) (0,180) (180,180) GPSS GAIN: 0.5 to 2.0 (0.1 increments) 429 IN PORT 5 NONE. TRAFFIC Not Used Not Used Notes: INSTALLATION MENU PAGE 11 – RSM CALIBRATION The following menu will be used in the next section to calibrate and validate the magnetometer in the RSM. Heading errors of up to +/- 6.0º can be calibrated at 30º increments beginning with North. (Follow RSM Cal procedure in Section 10.5) INSTALLATION MENU PAGE 11 – RSM CALIBRATION SW v2.0 Feature Options START CALIBRATION Press to Initiate ACCEPT CALIBRATION? Press to ACCEPT Cal REJECT CALIBRATION? Press to REJECT Cal HDG SEL 030º to 360º (in 30º increments) HDG ADJ -6.0 to +6.0 (degrees) Notes: DOCUMENT # 900-00003-001 PAGE 175-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD1000 (continued) This table is used to record the HDG ADJ values used to bring the compass heading values in to specification. RSM CALIBRATION (PFD Software 1.1 and later PAGE 12 Options Actual Setting HDG SEL: 030 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 060 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 090 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 120 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 150 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 180 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 210 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 240 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 270 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 300 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 330 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 HDG SEL: 360 KEY 4 HDG ADJ: KEY 5 Editable: -6 to +6 INSTALLATION MENU PAGE 12 – ACCEL BIAS CAL Installation Page 12 is for Factory Calibration only and has no installation purpose. INSTALLATION MENU PAGE 12 – ACCEL BIAS CAL SW v2.0 Feature Options BIASES (x,y,z) Factory Use Only START CALIBRATION Factory Use Only ACCEPT CALIBRATION? Factory Use Only REJECT CALIBRATION? Factory Use Only Notes: DOCUMENT # 900-00003-001 PAGE 176-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD1000 (continued) INSTALLATION MENU PAGE 13 – WX-500 The following menu is used for WX-500 configuration, system status, and system test. HEAD TYPE is configuration status. It will display NONE if there is no WX-500 connection, DISPLAY when a RS232 RX Port is set to WX500, and CONTROL when a RS232 TX Port is set to WX500. INSTALLATION MENU PAGE 13 – WX-500 SW v2.0 Feature Options Actual Setting HEAD TYPE NONE, DISPLAY, CONTROL SYSTEM DATA PAGE1,PAGE2,PAGE3,PAGE4 STRIKE TEST Press to Initiate NOISE MONITOR Press to Initiate ANTENNA MOUNT TOP,BOTTOM Notes: The HEAD Type menu entry is status only. It is necessary to exit and re-enter the menu to view the updated information. INSTALLATION MENU PAGE 14 – NETWORK PAGE This menu is for diagnostic purposes only. INSTALLATION MENU PAGE 14 – NETWORK PAGE SW v2.0 Feature Options IP ADDR 0-255 SUBNET MASK 0-255 GATEWAY 0-255 PORT 0-9999 Not Used Notes: Repeated presses of top 3 line select keys will select one of 4 selectable fields INSTALLATION MENU PAGE 15 - DIAGNOSTICS This menu is for diagnostic purposes only. Note – Operational Time and Flight Time are stored in the configuration module of the aircraft and these times are cumulative for the installation not the EFD unit itself. INSTALLATION MENU PAGE 15 – DIAGNOSTICS SW v2.0 Feature Options Not Used Not Used Not Used Not Used Not Used Notes: DOCUMENT # 900-00003-001 PAGE 177-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual EXITING / SAVING DATA 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 40 seconds. Normal operation continues. DOCUMENT # 900-00003-001 PAGE 178-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.4.7 EFD500 MFD Installation Menu Configuration INSTALLATION MENU Configuration – EFD500 Installation Date: Aircraft Model: EFD500 S/N: Aircraft Type: RSM S/N: Aircraft S/N: ACU S/N: CM S/N: NOTE: Some menus are grayed out as they do not apply to the EFD500 MFD. The EFD500 is depopulated of the ADC and AHRS sensors. INSTALLATION MENU PAGE 1 - IAS CONFIG A INSTALLATION MENU PAGE 1 – IAS CONFIG A SW v2.0 and subsequent Feature Options Actual Setting Vne Vno Vfe Vs Vso Notes: INSTALLATION MENU PAGE 2 – IAS CONFIG B INSTALLATION MENU PAGE 2 – IAS CONFIG B SW v2.0 and subsequent Feature Options Actual Setting Vyse Vmc Triangle Not Used Not Used Notes: INSTALLATION MENU PAGE 3- IAS CONFIG C INSTALLATION MENU PAGE 3 – IAS CONFIG C SW v2.0 and subsequent Feature Options Actual Setting IAS UNITS TAPES VSPD EDIT Not Used Not Used Notes: Does Not Apply to EFD500 Does Not Apply to EFD500 Does Not Apply to EFD500 DOCUMENT # 900-00003-001 PAGE 179-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD500 (continued) INSTALLATION MENU PAGE 4 – 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. (See Section 10.4.7.1 for example). Set NAV#2 Position Source to GPS1 if it is desired to have GPS1 map data displayed when VLOC#2 is selected. Set to GPS2 if GPS2 map data is to be displayed when VLOC#2 is selected. INSTALLATION MENU PAGE 4 – NAV SET UP SW v2.0 Feature Options Actual Setting GPS/NAV #1 NONE,A,B,C,D,E,F,G,H,I,J,K,L,M,P,Q,R GPS/NAV #2 NONE,A,B,C,D,E,F,G,H,I,J,K,L,M GPS/NAV#1 Speed HIGH, LOW GPS/NAV#2 Speed HIGH, LOW NAV#2 POSITION SOURCE GPS1, GPS2 1 Notes: (1) Set to GPS2 for dual integrated GPS units (i.e. dual GNS-430/530’s) INSTALLATION MENU PAGE 5 – RS232 PORT CONFIG A The following menu is used to configure the RS-232 RX IN sensor ports. Options include GPS, WX500, XM Weather, RSM, and MFD or PFD inter-system communication. Note - some ports do not include all interface options. (See wiring diagrams in sections 9 to determine how each port was wired and configure accordingly) INSTALLATION MENU PAGE 5 – RS232 PORT CONFIG A SW v2.0 Feature Options Actual Setting 232 IN PORT 0 NONE, RSM 232 IN PORT 1 NONE, XM 232 IN PORT 2 NONE, GPS TYPE 1, GPS TYPE 2, GPS TYPE 3, 232 IN PORT 3 NONE,WX500 232 IN PORT 4 NONE, EFD1000 MFD, EFD1000 PFD, EFD500 MFD Notes: GPS TYPE 1= KLN94/90B, GPS TYPE 2= KLN94 Enhanced, GPS TYPE 3= GX50/55/60/65 and GNS480 INSTALLATION MENU PAGE 6 – RS232 CONFIG B The following menu is used to configure the RS-232 RX5 IN sensor port and the four RS-232 TX OUT ports. Options include XM Weather, WX500, and PFD or MFD inter-system communications. Note - some ports do not include all interface options. (See wiring diagrams in sections 9 to determine how each port was wired and configure accordingly) INSTALLATION MENU PAGE 6 – RS232 PORT CONFIG B SW v2.0 Feature Options Actual Setting 232 IN PORT 5 NONE, EFD1000 MFD, EFD1000 PFD, EFD500 MFD 232 OUT PORT 0 NONE, RSM 232 OUT PORT 1 NONE, XM 232 OUT PORT 2 NONE, EFD, ADC TYPE 1, ADC TYPE 2 232 OUT PORT 3 NONE, WX500 Notes: DOCUMENT # 900-00003-001 PAGE 180-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD500 (continued) INSTALLATION MENU PAGE 7 – ACU CONFIG INSTALLATION MENU PAGE 7 – ACU CONFIG SW v2.0 Feature Options Actual Setting ACU HSI TYPE ACU FD TYPE ACU DATUM FD PITCH OFFSET ADJ FD ROLL OFFSET ADJ Notes: INSTALLATION MENU PAGE 8 – MISC CONFIG A Note – RSM GPS ENABLE must be set to DISABLE or the “RSM GPS” message will always be displayed. INSTALLATION MENU PAGE 8 – MISC CONFIG A SW 2.0 Feature Options Actual Setting RSM Orientation Does not apply to EFD500 RSM GPS Enable Must be set to disable. RSM GPS Usage Does not apply to EFD500 OAT Enable Does not apply to EFD500 OAT Display Does not apply to EFD500 Notes: INSTALLATION MENU PAGE 9 – MISC CONFIG B INSTALLATION MENU PAGE 9 – MISC CONFIG B SW 2.0 and SW v1.1 Feature Options Actual Setting ELEC SYSTEM 14 VOLT, 28 VOLT EFD BATTERY CONFG: INTERNAL, REMOTE* Panel Tilt Pitch Adjustment Does not apply to EFD500 Panel Roll Adjustment Does not apply to EFD500 Not Used Notes: INSTALLATION MENU PAGE 10 – MISC CONFIG C The following menu configures the analog VOR receiver composite phase. If a traffic receiver is connected then set the 429 IN PORT 5 to TRAFFIC, otherwise set to NONE. INSTALLATION MENU PAGE 10 – MISC CONFIG C SW 2.0 and SW v1.1 Feature Options Actual Setting Composite Phase Does not apply to EFD500 GPSS Gain Grayed Out “Does Not Apply to EFD500* 429 IN PORT 5 NONE, TRAFFIC Not Used Not Used Notes: Does Not Apply to EFD500 DOCUMENT # 900-00003-001 PAGE 181-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU Configuration – EFD500 (continued) INSTALLATION MENU PAGE 11 – RSM CALIBRATION INSTALLATION MENU PAGE 11 – RSM CALIBRATION SW v2.0 Feature Options START CALIBRATION ACCEPT CALIBRATION? REJECT CALIBRATION? HDG SEL HDG ADJ Notes: Does Not Apply to EFD500 INSTALLATION MENU PAGE 12 – ACCEL BIAS CAL INSTALLATION MENU PAGE 12 – ACCEL BIAS CAL SW v2.0 Feature Options BIASES (x,y,z) Factory Use Only START CALIBRATION Factory Use Only ACCEPT CALIBRATION? Factory Use Only REJECT CALIBRATION? Factory Use Only Notes: Does Not Apply to EFD500 INSTALLATION MENU PAGE 13 – WX500 The following menu is used for WX-500 configuration, system status, and system test. HEAD TYPE is configuration status. It will display NONE if there is no WX-500 connection, DISPLAY when a RS232 RX Port is set to WX500, and CONTROL when a RS232 TX Port is set to WX500. INSTALLATION MENU PAGE 13 – WX-500 SW v2.0 Feature Options Actual Setting HEAD TYPE NONE, DISPLAY, CONTROL SYSTEM DATA PAGE1,PAGE2,PAGE3,PAGE4 STRIKE TEST Press to Initiate NOISE MONITOR Press to Initiate ANTENNA MOUNT TOP,BOTTOM Notes: The HEAD Type menu entry is status only. It is necessary to exit and re-enter the menu to view the updated information. DOCUMENT # 900-00003-001 PAGE 182-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual INSTALLATION MENU PAGE 14 – NETWORK PAGE This menu is for diagnostic purposes only. INSTALLATION MENU PAGE 14 – NETWORK PAGE SW v2.0 Feature Options IP ADDR 0-255 SUBNET MASK 0-255 GATEWAY 0-255 PORT 0-9999 Not Used Notes: Repeated presses of top 3 line select keys will select one of 4 selectable fields INSTALLATION MENU PAGE 15 – DIAGNOSTICS This menu is for diagnostic purposes only. INSTALLATION MENU PAGE 15 – DIAGNOSTICS SW v2.0 Feature Options Not Used Not Used Not Used Not Used Not Used Notes: EXITING / SAVING DATA 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 40 seconds. Normal operation continues. DOCUMENT # 900-00003-001 PAGE 183-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.4.7.1 CONFIGURATION DEFINITIONS This section contains an expanded definition of each menu feature and detailed instructions for the available configuration options. Note not all PFD and MFD versions have every option as defined below. IAS Configurations V ne : Never Exceed speed (beginning of red band) V no : Maximum Structural Cruise speed (beginning of yellow band). For aircraft with no published yellow speed band set V no = V ne . V fe : Maximum Flap Extend speed (top of white band) - set to V fe = V s on aircraft with no flaps V s : No Flap Stall speed (bottom of green band) V so : Full Flap Stall speed (bottom of white band) - set to V so = V s on aircraft with no flaps V yse : Single Engine best rate of climb (blue marker) on multi engine aircraft – set to zero “0” on single engine aircraft. V mc : Single Engine minimum control speed (red marker) on multi engine aircraft – set to zero “0” on single engine aircraft. 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. IAS UNITS: Set to Knots or MPH as defined in the AFM TAPES: UNLOCKED = Must only be set when Airspeed and Altimeter are still in basic T configuration. With this setting the pilot can turn airspeed and altitude tapes on or off via “TPS” Hot Key. LOCK OFF = Must be used when aircraft has VMO “Barber Pole” airspeed indicator. Tapes are turned off and cannot be turned on by pilot LOCK ON = This setting required whenever Altimeter or Airspeed Indicator has been relocated from basic T configuration. Tapes are always enabled and cannot be turned off by pilot. DOCUMENT # 900-00003-001 PAGE 184-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Use the following flowchart to determine the proper configuration for the TAPES setting of Installation Menu 3. Figure 10.3 – TAPES Configuration Flow Chart DOCUMENT # 900-00003-001 PAGE 185-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 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. Miscellaneous Configuration A, B, C RSM Orientation: Set to TOP if top or mounted. Set to INVERTED if bottom mounted. RSM GPS Enable: Set to ENABLE if top mounted or internally mounted within a composite or fabric structure that allows for GPS signal transmission. Set to DISABLE if bottom mounted or internally mounted within an aluminum structure. OAT Enable: Set to ENABLE if the RSM is top mounted or bottom mounted and not in the exhaust stream. Set to DISABLE if the RSM is in the exhaust stream or internally mounted as the OAT reading will be inaccurate. Note - setting OAT Enable to DISABLE will also disable the TAS and Wind display. ELEC SYSTEM: Set to 14V or 28V as per aircraft electrical system. PANEL TILT PITCH ADJ: This setting 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. CAUTION: Do not use the “PANEL TILT PITCH ADJ” adjustment to align the Aircraft Reference Symbol to a zero pitch mark for level flight. Though such an adjustment appears to be a natural step, incorrect adjustment may result in incorrect pitch, roll and heading values. For non-tilted panel installations, the EFD1000 AHRS must show zero degrees pitch when the aircraft is leveled using the aircraft leveling indices. Adjustment of the PANEL TILT PITCH ADJ to set the Aircraft Reference Symbol to a zero pitch mark for level-flight may result in improper PFD alignment. If the level flight level zero pitch reference needs adjustment, proceed in accordance with the ATTITUDE REF SYMBOL ADJ procedure described below. NOTE: Once the PFD is installed and properly aligned, the Aircraft Reference Symbol’s level-flight pitch attitude indication changes with speed and aircraft loading and cannot be adjusted by the pilot. See 14CFR 23.1303(f). See ATTITUDE REF SYMBOL ADJ adjustment to determine if further action is required. DOCUMENT # 900-00003-001 PAGE 186-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Adjust the PANEL TILT PITCH ADJ value using one of the two methods shown below. Method 1 — Using an Inclinometer Using an inclinometer and the aircraft leveling indices, measure the offset angle in degrees (±0.5°), from aircraft level. This reading should be taken when a technician is seated in the cockpit since the angle could shift when the technician boards the aircraft. This measurement will be entered in the EFD1000 as CORRECTED PITCH ATTITUDE. Nose high is + degrees. CORRECTED PITCH ATTITUDE: 2.0° CORRECTED ROLL ATTITUDE: 0.3° Figure 10.4 – Illustration of aircraft 2º nose high 1) Set the ATTITUDE REF SYMBOL ADJ to 0.0º. 2) Press the PANEL TILT PITCH ADJ line select key and use the bottom right knob to enter a value for PANEL TILT PITCH ADJ that results in the CORRECTED PITCH ATTITUDE (Figure 10.4) equaling the value read on the inclinometer. It may also be set to the amount of panel tilt as determined through measurement. 3) Press the PANEL TILT PITCH ADJ line select key. Method 2 – Leveling the Aircraft Level the airplane in pitch in accordance with the aircraft manufacturer’s procedure. Then change the PANEL TILT PITCH ADJ adjustment to make the CORRECTED PITCH ATTITUDE equal to 0.0°. 1) Level the aircraft in pitch using the aircraft manufacturer’s procedure. CORRECTED PITCH ATTITUDE: 0.0° CORRECTED ROLL ATTITUDE: 0.0° 2) Set the ATTITUDE REF SYMBOL ADJ to 0.0º. Figure 10.5 – Illustration of Zero degree pitch adjustment 3) Press the PANEL TILT PITCH ADJ line select key and use the bottom right knob to enter a value for PANEL TILT PITCH ADJ that will result in the CORRECTED PITCH ATTITUDE (F ) equaling 0.0º. igure 10.5 4) Press the PANEL TILT PITCH ADJ line select key. DOCUMENT # 900-00003-001 PAGE 187-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual PANEL ROLL ADJ: Panel Roll Adjust is used to align the roll reference mark of the EFD1000 to zero degrees when the aircraft is wings level. With the aircraft wings level change the Panel Roll Adjust adjustment to make the CORRECTED ROLL ATTITUDE equal to 0.0º. Should more than 2º of correction be required the mechanical mounting of the EFD1000 for level in the panel should be re-verified. CAUTION A RSM Calibration must be performed before first flight after changing either the PANEL TILT PITCH ADJ or PANEL ROLL ADJ values. ATTITUDE REF SYMBOL ADJ: This is used to make small changes to the pitch attitude reference mark on the EFD1000 should the aircraft fly consistently slightly nose high or nose low in cruise trim. It is not necessary to perform the RSM Calibration after making changes to this setting. NAV Setup Configuration GPS/NAV#1 (ID#1): Ranges from A to R as specified on the wiring diagrams of Section 9. See example below GPS/NAV#2 (ID#2): Ranges from A to M as specified on the wiring diagrams of Section 9. See example below. Using the Configuration Table from Figure 9.11 as an example; If you wired the drawing exactly as shown you would select ID#1 = H and ID#2 = D. This would mean you have a RS-232/Analog GPS1 (i.e., KLN-94, GX-55) with an Analog NAV1 (i.e., KX-155A) and an Analog NAV2 (i.e., KX-155A). 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 # 900-00003-001 PAGE 188-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual COMPOSITE PHASE (VOR1, VOR2): Most modern navigation receivers will be set to (0, 0) as 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. ACU Configuration ACU HSI TYPE: 0= KI-525A, Emulates the KI-525A HSI 1= NSD-360A, Emulates the NSD-360A HSI 2= reserved 3= reserved 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: ACU HSI TYPE = 0 Configuration Matrix (see Section 10) ACU FD TYPE: 0= None, no flight director installed 1= KI-254/KI-256, Emulates the KI-254/256 Flight Director 2= Reserved 3= G-550A, Emulates the G-550A Flight Director 4= 52C77, Emulates the 52C77 Flight Director Below is an example from Figure 9.20 showing a KI-256 Emulation. In this case you would set the ACU FD TYPE =1: ACU DATUM: 0 = Normal 1 = Reversed. It may be necessary to select “Reversed” if the HDG or CRS Datum drives the autopilot in the opposing direction. Some HSI units use reversed logic for CRS and HDG Datum. Verify through DOCUMENT # 900-00003-001 PAGE 189-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual ground test the proper setting. FD ROLL OFFSET ADJ: Flight Director Roll Offset is used to align the PFD Command Bars to the Command Bars on the mechanical FD instrument in the roll axis. Positive number increases roll in RIGHT (clockwise) direction. Negative number increases roll in LEFT (counterclockwise) direction. FD PITCH OFFSET ADJ: Flight Director Pitch Offset is used to align the PFD Command Bars to the Command Bars on the mechanical FD instrument in the pitch axis. Positive number increases pitch in UP direction. Negative number increases pitch in DOWN direction. The value of the command bars position is digitally shown in the top portion of the 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. EXITING / SAVING DATA 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 40 seconds. Normal operation continues. DOCUMENT # 900-00003-001 PAGE 190-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.5 RSM Calibration 10.5.1 Calibration Overview The Remote Sensor Module must be calibrated by performing a compass swing in the aircraft for any new installations and any follow up maintenance activities that could affect RSM accuracy. Such activities might include but are not limited to the replacement of the RSM, replacement of the Configuration Module, installation of a mechanical or electrical device in the vicinity to the RSM, installation of an appliance that might generate a magnetic interference. NOTE: Before replacing the RSM and/or the Configuration Module, determine if the current installation has had 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. An overview of the RSM Calibration procedure is as follows (see Figure 10.8): CAUTION: When a Calibration is initiated, the aircraft must be turned as described below. If the calibration is initiated and then accepted without moving the aircraft, an erroneous calibration will be written to the Configuration Module, potentially resulting in failure to initialize. • A heading will be checked to verify the reasonableness of PFD heading prior to calibration. • The aircraft will be taxied to a magnetically quiet and level area at least 200ft from metal buildings and clear of metal grates, manhole covers and rebar within the concrete. A Compass Rose is ideal for this procedure. • The aircraft can start from any heading. • With engines running, all electrical equipment operating, and the aircraft stationary the RSM CAL page will be entered and Start Calibration will be initiated (see Figure 10.7). • After a 15 second countdown timer the pilot/operator will begin to taxi the aircraft in a circle (cw or ccw) with the radius of approximately twice the length of the aircraft’s wing as viewed from the cockpit (≈ 30ft). • The aircraft will be taxied under its own power at a constant rate around a circle until a 60 second timer elapses. The aircraft must not stop until the timer has exhausted. • At the completion of the 60 seconds the aircraft will have made at least a 450º circle (360º + 90º) to approximately two complete circles (720º). DOCUMENT # 900-00003-001 PAGE 191-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual • At the end of the 60 second timer four headings about 90º apart will be checked against a calibrated heading source (i.e., site compass, compass rose). • If PFD heading is acceptable then the calibration is Accepted. • If the PFD heading is not within tolerance then it is Rejected and the calibration procedure is re-run. • 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 ground. Verify heading accuracy is within +/- 4º. If the heading accuracy cannot be brought within +/- 4º tolerance then try temporarily shimming the rear of the RSM up. Perform another RSM calibration. If a shim corrects the heading accuracy then install permanent shim per Section 6.9.9. In some installations it might not be possible to achieve +/- 4º accuracy during the RSM calibration with the aircraft tail wheel on the ground. If feasible and necessary, the RSM calibration can be performed in the aircraft flight attitude (with the aircraft tail wheel lifted off the ground). Contact Aspen Avionics product support for tail dragger RSM calibration assistance. DOCUMENT # 900-00003-001 PAGE 192-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 10.6 – RSM Calibration Graphic DOCUMENT # 900-00003-001 PAGE 193-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.5.2 RSM Calibration Procedure The RSM calibration routine is accomplished using the Installation Menu “RSM CALIBRATION” menu page. See Section 10.4.5 (Installation Menu Access) for instructions on entering the INSTALLATION MENU. CAUTION: The “PANEL TILT PITCH ADJ” and “ROLL ATT TRIM” must be set correctly on the Installation Menu page prior to calibrating the RSM. Figure 10.7 – RSM Calibration Page On the “RSM CALIBRATION” menu page the current calibrated heading (to the nearest 0.1 degrees) will be continuously displayed adjacent to the “CAL HDG:” menu field. NOTE: Verify CAL HDG is within 25 degrees of a calibrated compass source prior to starting the RSM Calibration. This is a rough check of the hard and soft iron effects (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 # 900-00003-001 PAGE 194-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual With aircraft stationary at (POSITION 1) of Figure 10.8 press the “START CALIBRATION” line select key. The annunciation shown in Figure 10.10 will be displayed with a countdown timer that begins with 15 secs and counts down to 0 secs. CAUTION: Do not press ACCEPT Calibration without moving the aircraft in the procedure below as corruption to the configuration module could occur. When the menu of is displayed immediately begin taxiing the aircraft clockwise or counter-clockwise at a constant rate of no faster than 1 turn every 30 seconds. About half normal taxi speed or a brisk walking speed is about right. Approximately 10 seconds after initial movement (see POSITION A) the aircraft should be taxiing at a constant rate (CR) throughout the rest of the procedure. When the countdown timer is reached between one and a quarter turns (450º) (POSITION B) and two turns (720º) (POSITION D) should have been completed. While turning the aircraft do not stop the aircraft until the end of the 60 second timer and appears. Figure 10.9 Figure 10.10 If you find that the timing of the turns was not right such that “Magnetometer Calibration Complete” message occurs between B & D of Figure 10.6, then REJECT the results and re-run the procedure. MAGNETOMETER CALIBRATION IN PROGRESS TURN THE AIRCRAFT NO FASTER THAN 1 CIRCLE IN 30 SECS UNTIL TIMER STOPS TIME REMAINING: ## SECS MAGNETOMETER CALIBRATION IN PROGRESS Figure 10.8 - Calibration in Process DO NOT MOVE THE AIRCRAFT FOR THE NEXT 7 SECS Figure 10.9 – Aircraft Turning At the end of the calibration routine the “ACCEPT CALIBRATION?” and “REJECT CALIBRATION?” menu options will be enabled. DOCUMENT # 900-00003-001 PAGE 195-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual NOTE: If the message “Erroneous Calibration Values” is displayed then magnetic interference exists in the vicinity of the calibration area or the RSM is mounted in a magnetically noisy area. Try the calibration process again in a flat magnetically quiet area. If the message is displayed again the RSM location must be surveyed for magnetic interference. To determine whether to ACCEPT or REJECT the results check four headings approximately 90º apart against a known good heading source (i.e., aircraft compass, sight compass, compass rose). If the headings are within ±10º then press ACCEPT and use the Heading Offset Adjustment in Section 10.5.3 to align each heading value to actual. Pressing the “ACCEPT CALIBRATION” selection shall accept the calibration results, display the annunciation shown in Figure 10.13 for 5 seconds, and return the “RSM CALIBRATION” menu page to its initial state. MAGNETOMETER CALIBRATION ACCEPTED MAGNETOMETER CALIBRATION COMPLETE Figure 10.10 - Accept/Reject Results PLEASE ACCEPT OR REJECT RESULTS Figure 10.11 – Results Accepted 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 # 900-00003-001 PAGE 196-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual MAGNETOMETER CALIBRATION REJECTED Figure 10.12– Results Rejected 10.5.3 Heading Offset Adjustment 10.5.3.1 Heading Offset Adjustment When the calibration routine is complete and the results have been accepted the CAL HDG value will be displayed. MAGNETOMETER CALIBRATION CAL HDG: 032.7º Figure 10.13 – Calibration Heading before adjustment Position the aircraft so that it is at a heading of 30º as verified by a sight compass or other calibrated means. Press the line select key next to “HDG SEL” and then turn the right knob until HDG SEL: 030º is displayed. Now press the line select key next to “HDG ADJ” and turn the right knob until the CAL HDG of figure 10.15 displays exactly 030.0º as shown in figure 10.16 or as close to 030º as possible within a ±4º tolerance. The HDG ADJ field will display the amount of correction (+/- 6.0 degrees) that was required. Press the HDG ADJ line select key to accept the setting. MAGNETOMETER CALIBRATION CAL HDG: 030.0º Figure 10.14 – Calibrated Heading after adjustment Now repeat the process above for all other headings in 30º increments from 60º to 360º. Press the MENU key to exit the Installation Menu. Continue with heading accuracy tests in Section 10.5.4. DOCUMENT # 900-00003-001 PAGE 197-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual NOTE: In some aircraft, prop wash and wind during ground operations can create inconsistent pressures in the pitot-static system. The pressures can affect the ADAHRS, resulting in small pitch and heading perturbations. Before reading the aircraft headings for the purposes of calibration, ensure the attitude solution has stabilized and is not influenced by external winds and pressures. The disturbances normally settle out over a period of 15 to 60 seconds. Idle power or temporarily selecting the alternate static source can sometimes eliminate the effect. 10.5.4 Heading Accuracy Test As a final check, position the aircraft on the headings shown on “Installation Final Check Sheet” of Appendix B and verify heading (viewed on HSI display) is within +/- 4 degrees using a calibrated heading source (i.e., sight compass, compass rose). Record the actual PFD headings in the table for inclusion in the aircraft maintenance records. If any heading is outside ±4º then rerun the Calibration Procedure and or Heading Offset adjustment. 10.5.5 Heading Interference Test With aircraft engine(s) running monitor current aircraft heading on PFD and exercise flight controls stop to stop including flaps and any electric trim tabs. Verify the heading (viewed on HSI display) does not change on the PFD by more than 2º. If movement of flight controls causes more than a 2º heading change then it may be necessary to degauss the flight controls including the cables. A handheld degausser can be found at most audio and video stores. Operate all electrical and environmental equipment including: • Blowers, fans, heaters, air conditioner • Deice boots, fuel pump(s), backup vacuum pumps • Landing, logo, NAV lighting • Operate pulse equipment – transponder, WX radar, DME • Key all VHF communication radios. • Operate autopilot so that all servos run (roll, pitch, yaw, trim) If the operation of any electrical system causes the heading to change by more than 2º the RSM wiring may need to be relocated away from the offending system. The offending system may also have a bonding issue to the airframe that needs to be corrected. Run engine(s) from idle to take off power and verify that the heading does not change by more than 2º. Prop wash at higher RPMs may cause a heading shift, try an alternate static source if this is a issue. This completes all RSM calibration and heading tests. DOCUMENT # 900-00003-001 PAGE 198-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.6 Ground Test Procedure (PFD, EFD500 MFD and EFD1000 in PFD Reversion and in MFD Mode) The ground test procedure will consist of checking for proper operation of the following items. Check the PFD and the EFD1000 MFD in reverted mode simultaneously. Check the EFD1000 MFD and EFD500 MFD using the sections marked for these devices: a) Airspeed Tape, Altitude Tape, and OAT Sensor b) AHRS Sensor c) GPS Sensor Inputs (including Backup RSM GPS Sensor) d) Navigation Sensor Inputs (if installed) e) Backup Navigation Indicator f) Autopilot Sensor Outputs (if installed) g) Flight Director (if installed) h) Sonalert (if installed) i) Decision Height (if installed) j) Traffic Display (if installed) k) XM Weather Display and Control (if installed) l) WX500 Display and Control (if installed) m) Reversion Mode (EFD1000 MFD only) n) Ancillary Equipment Heading Check (if using ARINC 429 heading from EFD1000) o) Ancillary Equipment Air Data Check (if connected) p) Inter-Display Communication Test q) EMI Test r) Flight Control Interference Check CAUTION: Do not exceed the aircraft’s maximum Airspeed, Altitude, or Vertical Speed at anytime during the testing. Damage could result to the pre-existing aircraft instruments. NOTE: When changing indicated airspeed or altitude on the ground using pitot/static test equipment, changes in the AHRS display of pitch, roll and heading will result, possibly accompanied by a 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 nature of the EFD1000 AHRS algorithms is such that AHRS performance can only be properly evaluated during flight or ground maneuvers. DOCUMENT # 900-00003-001 PAGE 199-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 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. Set the Pitot/Static test set for 5000 ft above field elevation. Increase airspeed to V ne and check all Speed Bands and Speed Markers listed in table. 10.6.2 Altitude Display a) With the Pitot/Static tester still set for 5000 ft above field elevation and with BARO Set to 29.92 in. Hg. on the PFD (see Section 12), verify altitude tape displays altitude within ±40ft of the calibrated test set altitude. 10.6.3 System Leak Test a) Perform a pitot-static system leak test per the aircraft manufacturer’s maintenance manual or set the Pitot Static Test Set to 1000ft above field elevation and without additional pumping for a period of 1 minute the aircraft static system should not lose more than 100ft of altitude in a non-pressurized aircraft. 10.6.4 Outside Air Temperature (if ENABLED) a) Verify the OAT displays on the Data Bar and is not dashed. 10.6.5 AHRS Sensor Test a) Verify that correct aircraft attitude information is presented on the Attitude Indicator portion of the PFD. The Flags may take up to 5 minutes to clear when the ambient temperature is below -20° C. Typically the attitude solution will be available in less than 3 minutes. 10.6.6 GPS Sensor Test Refer to GPS manufacturer’s instructions for operating GPS receiver and verifying a complete and fully functional interface. All GPS interfaces a) Allow the GPS receiver to acquire a valid position and enter a Direct To waypoint or a Flight Plan. Verify the flight plan data appears on the PFD (if wired) and that it is correctly oriented on the magnetic compass card. NOTE: If the basemap does not correctly orient on the compass card, ensure that the GPS is configured for magnetic north reference. DOCUMENT # 900-00003-001 PAGE 200-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual b) Ensure GPS2 (if installed) is OFF. c) Select GPS1 on the PFD and verify the CRS pointer auto-slews (if enabled) to the desired track (DTK). To enable AUTOCRS go to Main Menu page 1. d) Select OBS or Hold Mode (if available) on the GPS and verify that the CRS knob on the PFD has control over the CRS pointer (manual-slew). e) Verify the To/From and Left/Right deflection has the correct polarity. f) 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. h) Turn off the GPS receiver and verify GPS1 is red slashed and goes invalid on PFD. i) Verify that RSM GPS Reversion is correctly annunciated. j) Repeat procedure for GPS2 if installed. Analog GPS interfaces a) Verify OBS accuracy on GPS and calibrate if necessary using GPS manufacturer’s instructions. RSM GPS (if ENABLED) a) With RSM GPS enabled verify RSM GPS in yellow box does not appear on left side of HSI display. Absence of RSM annunciation verifies correct operation of RSM GPS. See Installation Menu 4 for instructions on enabling the RSM GPS module. 10.6.7 NAV Receiver Sensor Test a) Select NAV1 on the PFD and create a valid and invalid condition with a Nav Signal Generator verifying that the NAV Flag is displayed (Red Slash) when invalid. b) Tune an ILS frequency on the Nav Receiver and verify the LDI (Localizer) scale is displayed on the ADI portion of the PFD. c) Tune the Nav Signal Generator to the ILS test frequency and generate a valid Glide Slope signal. Verify the VDI (Glide Slope) scale appears on the right side of the ADI. DOCUMENT # 900-00003-001 PAGE 201-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual d) Generate a signal above and below the Glide Slope beam and verify proper polarity of the 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. 10.6.8 Backup Navigation Indicator a) Verify the backup navigation indicator continues to function after pulling the PFD and ACU circuit breakers. 10.6.9 Autopilot Sensor Test Refer to autopilot manufacturer’s post installation check out procedures for complete autopilot post installation ground checks. At a minimum complete the following checks to verify the EFD1000 interface is satisfactory. NOTE: For attitude based autopilots it might be necessary to level the autopilot gyro to get proper FD and autopilot response from the test. CAUTION: Verify control surfaces are free and clear. a) If installed, center the HDG Bug under the lubber line and engage the autopilot and select HDG Mode. b) The FD (if installed) should be level and the yoke should not turn. c) Move the HDG Bug left of the lubber line and the FD and or yoke should bank left. d) Move the HDG Bug to right of lubber line and the FD and or yoke should bank right. e) With NAV1 selected on the PFD and a valid Nav Signal generated engage the autopilot in NAV Mode and verify that the FD and/or yoke follow the CRS Pointer in phasing. f) Verify that the autopilot responds to correct Left/Right phasing by generating left and right needle deflection. For autopilots that monitor the NAV FLAG, generate an invalid Nav Signal and verify autopilot responds accordingly. DOCUMENT # 900-00003-001 PAGE 202-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual g) Engage APPR Mode and verify that the autopilot responds correctly to a generated Fly Up and Fly Down command. For autopilots that monitor the GS FLAG, generate an invalid GS Signal and verify autopilot responds accordingly. 10.6.10 Flight Director Test a) If installed, engage the Flight Director (FD) in HDG Mode and verify that the command bars are in view. NOTE: Some rate based autopilots may require a valid vertical and lateral mode be engaged to view the flight director. b) Adjust the HDG Bug to the right of the lubber line. Verify the command bars indicate bank right. Adjust the HDG Bug to the left of the lubber line and verify the command bars indicate bank left. c) Compare the FD bars to the mechanical FD instrument, if installed. Note the degrees of difference between displays, if any, and adjust “FD Roll Offset Adj” as necessary on Installation Menu page 9 to closely match both displays. For example, if PFD FD bars need 2 more degrees of right bank then set FD Roll Offset Adj = +2. d) Generate a pitch up command with the flight director and verify FD bars indicate pitch up. Generate a pitch down command with the flight director and verify FD bars indicate pitch down. e) Compare the FD bars to the mechanical FD instrument, if installed. Note degrees of difference between displays, if any, and adjust “FD Pitch Offset Adj” as necessary on Installation Menu page 9 to closely match both displays. For example, if PFD FD bars need 3 more degrees of pitch up then set FD Pitch Offset Adj = +3 10.6.11 Sonalert Test a) If installed, verify the Sonalert is operational by generating a Selected Altitude alert on the PFD. This can be done by setting the Selected Altitude to 300ft above current altitude. b) 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). c) The Sonalert should sound before reaching the selected altitude. DOCUMENT # 900-00003-001 PAGE 203-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.6.12 Decision Height (DH) Test a) If installed, set Decision Height on Radar Altimeter indicator to less than 50ft. b) Press the Test button on the Radar Altimeter Indicator and verify that the DH annunciation displays on the PFD. c) For KRA-10A installations it may be necessary to turn the DH off and then push and hold the DH Test knob while turning it clockwise until the DH light comes on. 10.6.13 Traffic Display Test (if installed, applies to PFD, EFD500 MFD, and EFD1000 MFD) a) Turn on traffic processor and initiate TAS self test through traffic control unit. Verify traffic test pattern appears correctly on the EFD. The traffic interface may also be verified by observing aircraft in the vicinity on the EFD display. 10.6.14 XM Weather Display and Control Test (if installed, applies to PFD, EFD500 MFD, and EFD1000 MFD) a) Turn on XM weather receiver and allow it to acquire satellite data. A clear view of the southern sky will be required. b) Select the XM STATUS page on the EFD and verify the XM Serial Number and the Signal Quality is reported. c) Select various weather options from EFD to verify control bus functionality. 10.6.15 WX-500 Display and Control Test (if installed, applies to PFD, EFD500 MFD, and EFD1000 MFD) a) Turn on WX500 receiver. b) Select WX500 display on EFD and initiate a strike test through EFD (if configured for “Control”) or initiate the strike test through the WX-500 control unit if configured for “Display”. c) Verify strike test data appears on the EFD display. 10.6.16 Ancillary Equipment Heading Check a) Verify proper operation of any ancillary components that are using the ARINC 429 heading output from the EFD1000 system. DOCUMENT # 900-00003-001 PAGE 204-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual b) Use ancillary equipment manufacturers’ installation test procedures to perform ground check on their equipment. 10.6.17 Ancillary Equipment Air Data Check a) Verify proper operation of any ancillary components that are using the ARINC 429 or RS-232 air data output from the EFD1000 system. Use ancillary equipment manufacturers’ installation test procedures to perform ground checks on their equipment. 10.6.18 EFD Inter-System Communication Test For all multi display interfaces the RS232 inter-system communications should be checked as follows: a) Begin with all displays powered on. b) Pull the circuit breaker to the PFD display and verify that the MFD display(s) annunciate “Cross Link Failure”. Reset PFD breaker. c) In a Three display installation pull each MFD circuit breaker individually and verify the other MFD displays “Cross Link Failure”. d) In EFD1000 MFD installations press the REV button on the MFD and adjust the Baro setting on the EFD1000 MFD and verify the Baro changes on the PFD to match. 10.6.19 EBB58 Emergency Backup Battery Test (if installed) and internal battery tests a) On each EFD, press MENU key and rotate right knob until Main Menu page 10 of 11 is displayed. b) Press line select key next to Battery. c) After timer has elapsed verify the battery capacity is a minimum of 80%. If the capacity is below 80% then charge the EBB or internal battery to 80% or above by leaving the EFD powered on from external power. Follow step d) to return the EFD to external power for charging. d) Press line select key next to EXT PWR to return system to external power. 10.6.20 TAPES Configuration Check Verify the tapes are “LOCKED” or “UNLOCKED” as required by the flowchart in Figure 10.3. DOCUMENT # 900-00003-001 PAGE 205-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual a) If TAPES are locked on (LOCK ON) - IAS and Altitude tapes should be visible and pressing the “TPS” line select key should have no effect. b) If TAPES are locked off (LOCK OFF) – IAS and Altitude tapes should not be displayed on PFD and “TPS” line select key has no effect. c) If TAPES are UNLOCKED – then pressing “TPS” line select key will de-clutter IAS and Altitude tapes from PFD. 10.6.21 EMI Test (test with all EFD units operating) Monitor the EFD for Flags, Red-X’s, Red Slashes, heading changes, altitude changes, airspeed changes, attitude changes or any error messages while performing the following Test: a) Transmit on all Comm radios for 20 seconds each at 118.000MHz, 126.900MHz, and 136.950MHz. b) Turn on all transponders, DMEs, Wx Radar, and all other pulse type equipment for 20 seconds each. c) Operate all aircraft lighting including position lights, strobe lights, navigation lights, and all other forms of lighting for 20 seconds each. d) Operate all environmental equipment including fans, air conditioning, heaters, and all other forms of environmental control equipment for 20 seconds each. e) Operate Fuel pump(s), deice boots, windshield heat, prop heat, etc. f) Operate engine(s) and verify no interference. 10.6.22 Flight Control Interference Check CAUTION: Verify control surfaces are free and clear. a) With all EFD mounted in the instrument panel push the control column (yoke or stick) all the way forward (nose down) and verify there is sufficient clearance between all EFD, and their knobs, and the control column. With the control column fully forward move it from lock to lock (full right to full left) and verify there is sufficient clearance between all EFD, and their knobs, and the control column. DOCUMENT # 900-00003-001 PAGE 206-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 10.7 WX-500 Installation and Maintenance When an EFD is configured as “CONTROL” the following functions are accessed through the WX-500 page of the installation menus. They are intended to assist maintenance personnel in performing installation or repair of the WX-500. Consult manufacturer’s data for troubleshooting and repair of the WX-500 sensor and peripheral equipment. When the WX-500 Mode is Control, the WX-500 Installation Menu shall display and enable the SYSTEM DATA, STRIKE TEST, NOISE MONITOR, and ANTENNA MOUNT menu keys. When the WX-500 Mode is Display or None, the WX-500 Installation Menu shall disable (gray) the SYSTEM DATA, STRIKE TEST, NOISE MONITOR, and ANTENNA MOUNT menu keys. Note - Use other installed WX-500 control panel to access these functions. 10.7.1 System Data When the System Data display is selected (line select key depressed), information regarding the WX-500 is requested by the EFD and displayed in the upper portion of the screen. There are four pages of data which are selected by rotating the right knob. • Software Versions – Page 1 • Configuration Inputs and Heading – Page 2 • Environmental Data – Page 3 • Fault Log – Page 4 Figure 10.15 – WX-500 System Data Page 1 DOCUMENT # 900-00003-001 PAGE 207-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 10.16 – WX-500 System Data Page 2 Figure 10.17 – WX-500 System Data Page 3 Figure 10.18 – WX-500 System Data Page 4 10.7.2 Strike Test When the Strike Test display is selected, the EFD sends a Strike Test mode control message to the WX-500 and displays the test strikes in the upper portion of the screen. The outer ring of the Strike Test display shall represent 25 nm. The sides of the Strike Test mode acceptance box shall be drawn at 18±3 nm and 45±10 degrees. Test strikes shall be displayed for one second and appear as a cross at the reported range and bearing as shown above DOCUMENT # 900-00003-001 PAGE 208-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual Figure 10.19 – WX-500 Strike Test Page 10.7.3 Noise Monitor When the Noise Monitor display is selected, the EFD sends a Noise Monitor mode control message to the WX-500 and displays the noise strikes in the upper portion of the screen as shown. Figure 10.20 – WX-500 Noise Monitor Page DOCUMENT # 900-00003-001 PAGE 209-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 210-256 Revision G © Copyright 2010 Aspen Avionics Inc. The noise monitor mode shall display triggers, out to 400 nm, until the noise monitor mode is exited. The noise monitor mode shall display the number of triggers received since entering this mode. Pressing and holding the noise monitor line select key shall activate the clear strike function. 10.7.4 A a e detected by in the WX-500, the Antenna Jumper Error condition is cleared. Otherwise the Antenna Jumper Error condition is set and no weather data will be transmitted. ntenna Mount When the Antenna Mount menu item is selected, the installer can edit the Antenn Mount setting to be Top or Bottom. When the Antenna Mount menu item is deselected, the EFD1000 EFD sends an Antenna Mount message to the WX-500. If the value transmitted by the EFD1000 EFD matches the jumper valu EFD1000 and EFD500 SW v2.X Installation Manual 11 Post Installation Flight Check CAUTION: Only perform flight test in day VFR conditions with an appropriately rated pilot for the aircraft type to be flown. For MFD1000 installations press the REV button on the MFD to revert the MFD to a PFD. Observe both the PFD and MFD1000 during the flight checks below. 11.1 Basic ADI Flight Checks (PFD and EFD1000 MFD in reversion) Fly the aircraft in straight and level flight and verify that the ADI roll indication is level with reference to the horizon. Observe the Slip Indicator is centered under the Roll pointer and adjust rudder trim if available to center. a) Make a coordinated 30 degree banked turn to the right and verify that the ADI roll indication is correct with reference to the horizon. b) Make a coordinated 30 degree banked turn to the left and verify the ADI roll indication is correct with reference to the horizon. c) Pitch the aircraft up 10 degrees and verify the ADI pitch indication is correct with reference to the horizon. d) Pitch the aircraft down 10 degrees and verify the ADI pitch indication is correct with reference to the horizon. 11.2 Basic HSI/DG Flight Checks (PFD and EFD1000 MFD in reversion) a) Make a 180 degree coordinated turn to the right and verify that the compass scale and numerical heading indication correctly track the aircraft heading during the turn. b) Make a 180 degree coordinated turn to the left and verify that the compass scale and numerical heading indication correctly track the aircraft heading during the turn. c) Then turn from West to North (30° Angle of Bank) and, using an outside reference, roll out to a northerly heading. (In the Southern Hemisphere, also turn West to South) d) Immediately after the aircraft rolls out, record the heading indication. e) Maintain the same heading by outside visual reference. There may be some movement of the heading indicator as the heading system stabilizes. f) When the heading stabilizes, record the heading again. Then perform the test from East to North (In the southern Hemisphere, also turn east to South). DOCUMENT # 900-00003-001 PAGE 211-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual If the difference between the heading on rollout and the heading after stabilizing is more than 7°, refer to the Troubleshooting Guide, Appendix A. 11.3 ILS Flight Checks PFD (EFD1000 MFD and EFD1000 Secondary HSI) a) Hand fly an ILS approach and verify that the raw data on the PFD and MFD for Lateral and Vertical Deviation Indicators are correctly displayed. Check the CDI indication for correct needle displacement. Momentarily verify the MFD Secondary HSI also shows the lateral and vertical deviation indicators correctly. b) Check ILS2 if installed. 11.4 Autopilot Flight Checks (if installed, PFD only) WARNING: Remember to disconnect the Autopilot immediately if it is not performing its intended function. With wings level and the HDG Bug centered under the lubber line, deselect GPSS and engage the autopilot in HDG Mode and ALT Hold Mode (if available). Verify that the aircraft makes no abrupt turns during engagement and the aircraft continues to track straight. a) Now turn the HDG Bug 10 degrees to the right and verify the aircraft smoothly turns to the right with a bank angle not exceeding 10 degrees. If 10 degrees was acceptable in performance then proceed by turning the HDG Bug 90 degrees to the right and verify the aircraft makes a standard rate turn and smoothly rolls out on to the correct Heading. b) Now repeat the test to the left. c) With VLOC1 selected (VOR1 source indication) and a VOR Station tuned. Adjust the CRS pointer to center the CDI. Engage the autopilot in NAV Mode and verify the aircraft tracks to the VOR. d) Repeat with NAV2, if installed. e) Enter a valid flight plan or Direct To on the GPS. Couple the GPS to the HSI. Engage the autopilot in NAV Mode, verify the autopilot tracks the GPS. (Note: GPSS is disabled for this test, this test is verifying the GPS deviations to the autopilot) f) Repeat with GPS2, if installed. DOCUMENT # 900-00003-001 PAGE 212-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual g) For GPS receivers using ARINC 429 interfaces, enable GPSS and engage the autopilot in HDG Mode. Verify the autopilot tracks the GPS flight plan. Place the 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. With the HDG Bug centered, press the GPSS button again and verify the HDG Bug controls the autopilot as before. h) Perform an ILS approach using VLOC1 (ILS1 source indication). Verify that the autopilot tracks the localizer, then captures and tracks the glideslope if installed. i) Now repeat with ILS2 if installed. j) If your GPS supports GPS WAAS LPV approaches, perform an LPV approach using GPS1. Verify that the autopilot tracks the GPS lateral approach guidance, then captures and tracks the GPS LPV vertical guidance. k) Repeat with GPS2, if installed. 11.5 Document Test Flight 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 # 900-00003-001 PAGE 213-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual THIS PAGE IS INTENTIONALLY LEFT BLANK DOCUMENT # 900-00003-001 PAGE 214-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual 12 Operating Instructions The operation section describes all of the features of the PRO model with all available sensor options configured. Should your installation not include a particular sensor (i.e., NAV2, autopilot) then that system feature will be not available. The PRO DIGITAL model has all the features of the PRO minus the autopilot interface. Basic operation of the EFD1000 MFD and EFD500 MFD are covered in this section. For detailed operating instructions see the MFD pilot’s guide. 12.1 Pilot Controls 12.1.1 Overview Pilot interaction with the EFD1000/EFD500 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. Three lower push buttons, located between the control knobs, are used to select navigation sources for the bearing pointers and the HSI. Three dedicated buttons on the upper side of the right bezel control map range, display reversion, and provide access the main menu. Five soft keys on the lower half of the right bezel control frequently used commands, such as the HSI mode or map de-clutter setting. These five keys are also used when navigating the main menu. 12.1.2 Power Control To enhance safety, the EFD1000/EFD500 includes an internal or Emergency Backup Battery (Optional, EFD1000 MFD) that allows the system to continue to operate in the event of a failure of the aircraft electrical system. This ensures that in addition to the standby instruments, the EFD1000 primary flight instrument and the EFD1000 MFD continues to remain available for a period of time following the loss of all external supply power. If the EFD1000 MFD is being used for required standby instruments then the EBB58 Emergency Backup Battery is required by regulation. See AFMS for instructions on testing prior to flight DOCUMENT # 900-00003-001 PAGE 215-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 216-256 Revision G © Copyright 2010 Aspen Avionics Inc. The typical EFD1000 installation receives aircraft power from the battery bus via a dedicated circuit breaker and EFIS Master and optional MFD Master switch. Whenever indicated airspeed is invalid or below 30 KIAS the EFD1000 will power up and power down with the application or removal of external power. A message is presented during the normal power down sequence to enable the pilot to abort the shutdown and switch to internal battery. When IAS is greater than 30 KIAS and the input voltage drops below 12.3V (14V Electrical System) or 24.6V (28V Electrical System) the EFD will automatically switch to its internal battery (e.g. aircraft charging system failure). The EFD1000 internal battery (or Emergency Backup Battery in the case of the 910- 00001-002 EFD) 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. Reducing the backlight intensity will extend the battery operating time. When operating from battery, a red “ON BAT” annunciation and battery charge status indication is presented in the lower portion of the Attitude Indicator. A unit operating from battery may be powered off using the “Shut Down” command available in the Power Settings Menu. In the unlikely event that the normal power control is not working, the EFD may be forced to shut down by first pulling its associated circuit breaker and then pressing and holding the REV button for at least 5 seconds. Battery charge status may be viewed from the “Power Settings” page of the Main Menu. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 217-256 Revision G © Copyright 2010 Aspen Avionics Inc. 12.1.3 PFD Display and Control Layout NOTE: The MFD control layout is similar to the PFD. The display button (#9) selects the view. Figure 12.1 – Bezel and Display Features PFD Controls 1) Reversion Control 2) Range Control 3) Menu Control 4) “TPS” Tapes ON/OFF Control 5) “MIN” Minimums ON/OFF Control 6) “360/ARC” HSI View Control 7) “MAP” Map declutter logic Control 8) “GPSS” GPS Steering ON/OFF Control 9) Right Control Knob 10) Left Control Knob 11) Single-Line Bearing Pointer Source Select 12) CDI Source Control 13) Dual-Line Bearing Pointer Source Select 14) Micro SD Card slot 15) Automatic Dimming Photocell 16) Attitude Indicator 17) Aircraft Symbol 18) Single Cue Flight Director (optional – compatible autopilot required) 19) Roll Pointer 20) Slip / Skid Indicator 21) Airspeed Indicator Tape 22) Selected Airspeed Field 23) Airspeed Drum/Pointer 24) Altitude Alert 25) Selected Altitude Field 26) Altitude Drum/Pointer 27) Altitude Tape 28) MINIMUMS annunciation 29) Selected Minimums Field 30) Decision Height “DH” Annunciation 31) LDI Navigation Source Indication 32) Lateral Deviation Indicator 33) Vertical Deviation Indicator 34) True Airspeed 35) Barometric Pressure Setting Field 36) Ground Speed 37) OAT 38) Wind Direction Arrow 39) Wind Direction and Speed 40) Selected Source Information Field 41 Selected Course (CRS)Field 42) Selected Heading Field 43) Vertical Speed Digital Value 44) Vertical Speed Tape 45) Left Control Knob state 46) Right Control Knob state 47) Single-Needle Bearing Pointer Source 48) Single-Needle Source Info Block 49) Dual-Needle Bearing Pointer Source 50) Dual-Needle Source Info Block 51) CDI Navigation Source 52) Magnetic Heading 53) Compass Scale 54) Hot Key legend 55) CRS Pointer 56) Single-Needle Bearing Pointer 57) Double-Needle Bearing Pointer 58) Heading Bug 59) Airspeed Bug 60) Altitude Bug EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 218-256 Revision G © Copyright 2010 Aspen Avionics Inc. 12.1.4 Control Knobs General Two control knobs on the EFD bezel are used to adjust pilot editable data fields on the EFD. The left knob adjusts data fields on the left side of the display, and the right knob adjusts data fields on the right side of the display. The knob logic includes active and inactive states to prevent inadvertent adjustment of editable fields. After 10 seconds of inactivity, the knob returns to an inactive “home” state. A single push activates an inactive knob. Pushing the knob again will advance the knob to the next editable field in a round-robin sequence. When inactive, the knob legend is rendered in Cyan. Once activated, the knob legend and associated data field and bug (where appropriate) are rendered in magenta. The MFD control knobs select the views and the pages. 12.2 Traffic Display (optional) Traffic is displayed on the PFD as an overlay on the HSI display. To enable traffic press the TRFC line select key to highlight. To remove the overlay press the TRFC line select key again. Traffic may be displayed on the MFD as either a dedicated traffic display or as an overlay with other data. See the PFD and MFD Pilot’s Guides for additional operational information. 12.3 XM Weather Display (optional) XM Weather on the PFD is an overlay on the HSI display. To enable XM Wx press the NXRD line select key to highlight. To remove the overlay press the NXRD line select key again. XM Weather may be displayed on the MFD as either a dedicated XM Weather display or as an overlay with other data. See the PFD and MFD Pilot’s Guides for additional operational information. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 219-256 Revision G © Copyright 2010 Aspen Avionics Inc. 12.4 WX-500 Display (optional) WX-500 data is displayed on the PFD as an overlay on the HSI display. To enable lightning press the LTNG line select key to highlight. To remove the overlay press the LTNG line select key again. STRK and CELL indications show the WX-500 functions. Lightning may be displayed on the MFD as either a dedicated lightning display or as an overlay with other data. See the PFD and MFD Pilot’s Guides for additional operational information. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 220-256 Revision G © Copyright 2010 Aspen Avionics Inc. THIS PAGE IS INTENTIONALLY LEFT BLANK EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 221-256 Revision G © Copyright 2010 Aspen Avionics Inc. 13 Environmental Qualification Forms Nomenclature: EFD1000/500 Evolution Flight Display with Configuration Module Part Number: A-05-110-00, 910-00001-001, 910-00001-002 (including EBB58), 910-00001-003, and CM: A-05-113-00 and 910-00005-004 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: DO-160E Date Tested: 2/2008 CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTED Temperature and Altitude (Pressurized) 4.0 Equipment tested to Category A1, Decompress to 55,000”, Controlled temp and pressurized to <15,000’ Temperature and Altitude (Unpressurized) 4.0 Equipment tested to Category C1, Controlled temp and non-pressurized to 35,000’ Loss of Cooling 4.5.5 Equipment tested to Category Y, 300 minutes min. Temperature Variation 5.0 Equipment tested to Category C Humidity 6.0 Equipment tested to Category A, standard humidity environment Operational Shock and Crash Safety 7.0 Equipment tested to Category B, standard operational shock and crash safety Vibration (Fixed Wing) 8.0 Equipment tested to Category S, aircraft Zone 2 for Fixed Wing Reciprocating & Turboprop Engines, Multi Eng over 5700 KG (12,500 lbs), Multi Eng Less than 5700 KG (12,500 lbs), and Single Eng Less than 5700 KG (12,500 lbs) using vibration test curve M. Explosive Atmosphere 9.0 Equipment identified as Category X, no test performed Waterproofness 10.0 Equipment identified as Category X, no test performed Fluids Susceptibility 11.0 Equipment identified as Category X, no test performed Sand and Dust 12.0 Equipment identified as Category X, no test performed Fungus 13.0 Equipment identified as Category X, no test performed Salt Fog Test 14.0 Equipment identified as Category X, no test performed Magnetic Effect 15.0 Equipment tested to Category Z, causes < 0.5 deg deflection to compass 0.3 meter away Power Input 16.0 Equipment tested to Category B Voltage Spike 17.0 Equipment tested to Category A Audio Freq Conducted Susceptibility 18.0 Equipment tested to Category B Induced Signal Susceptibility 19.0 Equipment tested to Category ZC RF Susceptibility 20.0 Equipment tested for conducted susceptibility to Category W and for radiated susceptibility Category W. Bench test to show compliance with interim HIRF rules. 100V/m RF Emissions 21.0 Equipment tested to Category M, significant EM apertures, not in direct view of radio receiver antenna (Equipment mounted in cockpit or cabin area) Lighting Induced Transient 22.0 Equipment tested to Category B3K33, moderately exposed all-metal airframes, airframes composed of metal framework and all composite skin panels or carbon fiber composite airframes whose major surface areas have been protected with metal meshes or foils Lightning Direct Effects 23.0 Equipment identified as Category X, no test performed Icing 24.0 Equipment identified as Category X, no test performed ESD 25.0 Equipment tested to Category A Fire, Flammability 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. Table 13.1 - EFD1000 Environmental Qualification Form EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 222-256 Revision G © Copyright 2010 Aspen Avionics Inc. Nomenclature: EFD1000 Remote Sensor Module (RSM) Part Number: A-05-111-00, 910-00003-001, 910-00003-002, 910-00003-003 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 Temperature and Altitude 4.0 Equipment tested to Category F2, non-controlled temp and non-pressurized to 55,000’ Temperature Variation 5.0 Equipment tested to Category A, external, non-temperature controlled - 10 deg. C/minute Humidity 6.0 Equipment tested to Category C, external humidity environment Operational Shocks 7.0 Equipment tested to Category A Vibration 8.0 Equipment tested to Category S, aircraft Zone 1 for Fixed Wing Reciprocating & Turboprop Engines, Multi Eng Less than 5700 KG (12,500 lbs) (does not include structure directly affected by jet efflux), and Single Eng Less than 5700 KG (12,500 lbs) using vibration test curve M. Explosive Atmosphere 9.0 Equipment identified as Category X, no test performed Waterproofness 10.0 Equipment tested to Category S Fluid Susceptibility 11.0 Equipment tested to Category F, deicing fluids and aircraft cleaning compounds only Sand and Dust 12.0 Equipment identified as Category X, no test performed Fungus 13.0 Equipment identified as Category X, no test performed Salt Fog Test 14.0 Equipment identified as Category X, no test performed Magnetic Effect 15.0 Equipment tested to Category Z, causes < 0.5 deg deflection to compass 0.3 meter away Power Input 16.0 n/a - Powered from PFD display Voltage Spike 17.0 n/a - Powered from PFD display Audio Freq Conducted Susceptibility 18.0 n/a - Powered from PFD display Induced Signal Susceptibility 19.0 Equipment tested to Category ZC RF Susceptibility 20.0 Equipment tested to Category WW, (Conducted/Radiated) Bench test to show compliance with interim HIRF rules. 100V/m RF Emissions 21.0 Equipment tested to Category H, direct view of radio receiver antenna. (equipment mounted outside airframe) Lighting Induced Transient 22.0 Equipment tested to Category B3K33, moderately exposed all-metal airframes, airframes composed of metal framework and all composite skin panels or carbon fiber composite airframes whose major surface areas have been protected with metal meshes or foils Lightning Direct Effects 23.0 Equipment tested to Category 2A, mounted in area with sweptback attachment, but no hang on Icing 24.0 Equipment tested to Category C, external environment ESD 25.0 Equipment tested to Category A Fire, Flammability 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. Table 13.2 - RSM Environmental Qualification Form EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 223-256 Revision G © Copyright 2010 Aspen Avionics Inc. Nomenclature: Analog Converter Unit Part Number: A-05-112-00, 910-00004-001 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 Temp/ Altitude (Pressurized) 4.0 Equipment tested to Category C4, controlled temp and pressurized to <15,000’ Temp/ Altitude 4.0 Equipment tested to Category C4, Operating low temperature -40C, Operating High +55C, Short Time Operating Low -40C, Short-Time Operating High +70C, Loss of Cooling, N/A, Ground Survival Low -55C, Ground Survival High +85C and non-pressurized to 35,000’ Temperature Variation 5.0 Equipment tested to Category C, internal, temperature controlled - 2 deg. C/minute Humidity 6.0 Equipment tested to Category A Operational Shocks and Crash Safety 7.0 Equipment tested to Category B Vibration (Fixed Wing) 8.0 Equipment tested to Category S, aircraft Zone 2 for Fixed Wing Reciprocating & Turboprop Engines, Multi Eng over 5700 KG (12,500 lbs), Multi Eng Less than 5700 KG (12,500 lbs), and Single Eng Less than 5700 KG (12,500 lbs) using vibration test curve M. Explosive Atmosphere 9.0 Equipment identified as Category X, no test performed Waterproofness 10.0 Equipment identified as Category X, no test performed Fluids Susceptibility 11.0 Equipment identified as Category X, no test performed Sand and Dust 12.0 Equipment identified as Category X, no test performed Fungus 13.0 Equipment identified as Category X, no test performed Salt Fog Test 14.0 Equipment identified as Category X, no test performed Magnetic Effect 15.0 Equipment tested to Category Z , causes < 1.0 deg deflection to compass 0.3 meter away Power Input 16.0 Equipment tested to Category B Voltage Spike 17.0 Equipment tested to Category A Audio Freq Conducted Susceptibility 18.0 Equipment tested to Category B Induced Signal Susceptibility 19.0 Equipment tested to Category ZC RF Susceptibility 20.0 Equipment tested to Category WW, (Conducted/Radiated) Bench test to show compliance with interim HIRF rules. 100V/m RF Emissions 21.0 Equipment tested to Category M, significant EM apertures, not in direct view of radio receiver antenna (Equip mounted in cockpit or cabin area) Lighting Induced Transient 22.0 Equipment tested to Category B3K33, moderately exposed all-metal airframes, airframes composed of metal framework and all composite skin panels or carbon fiber composite airframes whose major surface areas have been protected with metal meshes or foils Lightning Direct Effects 23.0 Equipment identified as Category X, no test performed Icing 24.0 Equipment identified as Category X, no test performed ESD 25.0 Equipment tested to Category A Fire, Flammability 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. Table 13.3 - ACU Environmental Qualification Form EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 224-256 Revision G © Copyright 2010 Aspen Avionics Inc. THIS PAGE IS INTENTIONALLY LEFT BLANK EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 225-256 Revision G © Copyright 2010 Aspen Avionics Inc. APPENDIX A TROUBLESHOOTING EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 226-256 Revision G © Copyright 2010 Aspen Avionics Inc. System Troubleshooting Fault Cause Corrective Action 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) PFD missing A/C power b) PFD may have been improperly shut down c) PFD missing A/C ground d) PFD is defective a) Check PFD circuit breaker, PFD 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 PFD d) Repair or replace PFD Display does not power off (Note: PFD will switch to internal battery if airspeed is greater than 30kts.) a) Airspeed is above 30kts b) PFD may have been switched to internal battery c) PFD may have been improperly shut down d) PFD 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 PFD internal battery for 3 seconds d) Repair or replace PFD Display flashes on/off, black/white or blue/white repetitively a) Configuration Module unplugged or miss wired b) RSM or CM wiring short c) Configuration module defective d) PFD defective a) Check CM plug and wiring from PFD 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 PFD “CONFIG MODULE LINK FAIL” message a) Configuration Module unplugged or miss 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 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 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 a) PFD is at one software level and config module is at a different software level a) Convert config module per appropriate service bulletin. 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 PFD c) Repair or replace PFD EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 227-256 Revision G © Copyright 2010 Aspen Avionics Inc. System Troubleshooting –continued Fault Cause Corrective Action 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) PFD is defective a) Allow up to 3 minutes for AHRS to initialize. b) Check RSM to PFD wiring. Repair or replace RSM. c) Correct pitot/static plumbing issue. d) Repair or replace PFD. 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. 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 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 PFD f) ACU to PFD wiring fault. g) ACU is defective. h) PFD 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 PFD f) Check ACU circuit breaker, check ACU to PFD A429 wiring and ACU to sensor wiring g) Repair or replace ACU h) Repair or replace PFD GPS1 or GPS2 selection not available on Display (GNS430 and GNS530 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 PFD A429 wiring issue. e) GPS defective. f) PFD 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 PFD EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 228-256 Revision G © Copyright 2010 Aspen Avionics Inc. System Troubleshooting – continued Fault Cause Corrective Action Autopilot or analog NAV/GPS inoperative a) ACU chassis not grounded b) ACU not powered c) ACU to sensor wiring d) ACU to PFD wiring e) ACU fault f) PFD 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 PFD A429 wiring e) Repair or replace ACU f) Repair or replace PFD “ERRONEOUS CALIBRATION VALUES” message during RSM Cal (SW v2.0 and later) or Excessive Heading errors in one quadrant, or errors that are higher than actual in some quadrants and lower than actual in other quadrants. a) RSM is tilted more than allowed per Section 6 of this manual b) Poor RSM calibration c) RSM calibrated too close to buildings or ferrous objects d) Ferrous hardware used to mount RSM e) Airframe or external magnetic interference a) Shim RSM to within limits defined in Section 6 of this manual b) Re-run RSM calibration at constant rate turns on flat ground. c) Re-run RSM calibration away from buildings and other ferrous objects d) Only stainless screws, nuts, washers may be used on RSM e) Check for magnetized areas on airframe close to RSM. Verify no ferrous hardware is near RSM. Degauss magnetized area(s) Sluggish or Poor AHRS (ADI) performance Poor AHRS performance in steep bank turns Sluggish compass card (Note: may or may not be associated with “Cross Check Attitude” message) a) RSM magnetic interference b) RSM has become magnetized. c) “Pitch Attitude Trim” or “Panel Tilt Pitch Compensation” adjustment made without performing a subsequent RSM Calibration. d) Pitot and/or Static line connections at PFD blocked, kinked, or unplugged. e) Normal after abrupt maneuvers. a) Survey RSM location using handheld compass per Section 6.9.1. Verify there are no cabin speakers within 3ft of RSM. Degauss any areas found to be magnetized or remove magnetism by other methods. b) With power removed from EFD1000 system degauss RSM and general area using degausser. c) Perform an RSM Calibration per Section 10.5.2 d) Check pitot/static connections and plumbing for blockage. Check IAS and ALT sensor per Section 10. e) Perform AHRS Reset Excessive Heading Lead / Lag during or after turns (>7°) Magnetic Interference Verify that all steps have been accomplished to remove magnetic interference (see §6.9.1), then contact an Aspen Field Service Engineer EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 229-256 Revision G © Copyright 2010 Aspen Avionics Inc. System Troubleshooting – continued Fault Cause Corrective Action Autopilot has lateral offset in GPSS or APPR mode (HDG Bug may also be out of center) a) Autopilot roll “null” centering out of adjustment a) Follow the autopilot manufacturer’s guidelines for adjusting roll “null” centering Century II/III autopilot performance poor in all modes a) Value of R1 set incorrectly a) Follow the autopilot manufacturer’s instructions for checking NAV intercept angle. Larger value for R1 will raise angle and smaller value of R1 will lower intercept angle. See Tech Note 2009-06. OAT Display dashed a) Wiring fault between PFD and RSM b) RSM is defective a) Check wiring b) Repair or replace RSM WIND vector, velocity, and direction display dashed (Note: wind readout will dash when velocity is < 10 kts) a) Groundspeed < 20kts b) No GPS ground track c) Airspeed failed a) Normal operation b) GPS not computing GTK c) See AIRSPEED FAIL troubleshooting procedure OBS mode inoperative on GPS a) GPS A429 IN bus configured wrong b) ARINC 429 “A” and “B” lines reversed a) See Figure 9.27 for GPS configuration notes b) Correct wiring error to GPS A429 IN bus “CROSS LINK FAILURE” message a) PFD or MFD not powered up b) PFD or MFD inter-system bus wiring fault c) PFD or MFD is defective a) Power up all EFD displays b) Check wiring per diagrams in Section 9 c) Repair or Replace defective EFD “DATABASE FAILURE” message a) Data Card (microSD) is not inserted in MFD display. b) Wrong Data Card inserted c) Data Card is bad d) MFD card slot is defective a) Insert Data Card in display b) Insert correct Data Card See Section 1 for authorized database part numbers c) Replace data card with new d) Repair or replace MFD display “TERRAIN FAIL” message a) Data Card not inserted b) Data Card failed c) Heading fail d) GPS position fail e) Altitude fail a) Insert valid MFD Database b) Insert valid MFD Database c) Verify EFD1000 MFD Direction Indicator is valid and repair if needed. EFD500 MFD inter-communication bus to PFD may have failed or is not configured. d) Verify GPS has good position data e) Verify EFD1000 Altitude is valid. EFD500 MFD intercommunication bus to PFD may have failed or is not configured. “TRFC FAIL” message a) Traffic sensor is configured but not valid. a) Verify traffic processor is turned on and is operational. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 230-256 Revision G © Copyright 2010 Aspen Avionics Inc. System Troubleshooting – continued Fault Cause Corrective Action Dedicated Traffic Display page messages See AFMS or pilots guide Dedicated WX500 Display page messages See AFMS or pilots guide Dedicated XM Weather Display page messages See AFMS or pilots guide EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 231-256 Revision G © Copyright 2010 Aspen Avionics Inc. APPENDIX B INSTALLATION FINAL CHECK SHEET EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 232-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000/500 Installation Final Check Sheet (page 1 of 4) Aircraft Type: Date: Aircraft Serial Number: Tail Number: The following four (4) 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. Complete by performing test of Section 10.5.4(EFD1000) Calibrated Heading Source TOLERANCE Actual PFD Heading Calibrated Heading Source TOLERANCE Actual PFD Heading Actual MFD Heading 30 +/- 4 210 +/- 4 60 +/- 4 240 +/- 4 90 +/- 4 270 +/- 4 120 +/- 4 300 +/- 4 150 +/- 4 330 +/- 4 180 +/- 4 360 +/- 4 Complete by performing test of Section 10.6.1(EFD1000) IAS Setting Band Color Band Range Description Pass V ne = Red >V ne Red arc displayed at all speeds above V ne V no = Yellow V no - V ne Yellow arc extending from V no to V ne V s = Green V s - V no Green arc extending from V s to V no V fe = White V so - V fe Top of White arc V so = White Bottom of White Arc V yse = Blue Marker = V yse Blue Marker at V yse V mc = Red Marker = V mc Red Marker at V mc = Triangle (White) = White triangle at initial flap extension airspeed NOTE: Single engine aircraft and aircraft with no flaps will not use all parameters above EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 233-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000/500 Installation Final Check Sheet (page 2 of 4) SECTION POST INSTALLATION TESTS PASS FAIL 10.5.4* Heading Accuracy Check (from Page 1 of 4) 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 (if ENABLED) 10.6.5* AHRS (attitude solution) Test 10.6.6 GPS Sensor Test - GPS1 (if installed) 10.6.6 GPS Sensor Test – GPS2 (if installed) 10.6.6* RSM GPS Sensor Test 9if ENABLED) 10.6.7 NAV Receiver Sensor Test – NAV1 (if installed) 10.6.7 NAV Receiver Sensor Test – NAV2 (if installed) 10.6.8* Back-up NAV Indicator Test (if installed) 10.6.9* Autopilot Sensor Test (if installed) 10.6.10* Flight Director Test (if installed 10.6.11* Sonalert Test (if installed) 10.6.12* Decision Height Test (if installed) 10.6.13 Traffic Display Test (if installed) 10.6.14 XM Weather Display and Control Test (if installed) 10.6.15 WX-500 Display and Control Test (if installed) 10.6.16* 10.6.17* Ancillary Equipment Heading and Air Data (if connected) List equipment interfaced: 10.6.18 EFD Inter-System Communication Check (if multi-display) 10.6.19 Battery Capacity Check – EBB and Internal batteries > 80% Charge 10.6.20* TAPES Configuration Check 10.6.21 EMI Test 10.6.22 Flight Control Interference Check *Does not apply to an EFD500 EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 234-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000/500 Installation Final Check Sheet (page 3 of 4) SECTION COMPLIANCE CHECK PASS FAIL 6.4 Weight and Balance performed 7.1 Electrical Load Analysis performed for each EFD 5.2.1 For aircraft not limited to VFR, a Standby Attitude indicator must be installed in accordance with section 5.2.1 5.2.2 Standby Airspeed, Altimeter must be installed in accordance with section 5.2.2 5.2 Is the EBB58 Emergency Backup Battery installed for installations that removed standby Airspeed Indicator and/or Altimeter and replaced them with the MFD1000. 6.5.3 Verify the EBB58 wiring harness and the EFD1000 MFD’s RSM wiring is isolated/separated from the EFD1000 PFD’s RSM wiring to provide independence. 5.2.8 For aircraft limited to VFR, a placard or equivalent acceptable means, stating “Operation of This Aircraft is Limited to VFR Only”, or similar phraseology acceptable to the FAA. Note: This placard should be pre-existing under TC or STC. This step is to verify that the placard is still present 5.2.4 Backup Navigation Indicator (if required) connected to a navigation source installed in pilot’s field of view. The indicator must continue to function if the PFD and/or ACU circuit breaker is pulled 7.2 Circuit breaker installed for each EFD and each ACU. 6.9.1 RSM location(s) shows less than 2 degrees of needle deflection on hand held compass within 18”x18” survey area 10.1.2 Each EFD braided ground strap is installed between unit and panel, RSM ground wire attached to ground stud, RSM doubler/mounting plate bonded to airframe ground and ACU(s) chassis bonded to airframe ground. All measure no greater than .003 ohms to ground. 7.2 Wires, cables, and connectors clearly marked or stamped 7.2, 5.2.7 When installed, EFD1000/500 master switch(s) and/or circuit breakers and “EBB58 EMER DISC” switch must be easily accessible to flight crew and clearly marked. One switch exists for each display. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 235-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000/500 Installation Final Check Sheet (page 4 of 4) SECTION COMPLIANCE CHECK PASS FAIL 11 Post Installation Flight Test 11.4 Document successful completion of flight test in aircraft log book per FAR 91.407b 5.2 In aircraft with independent pitot/static systems each EFD1000 must be connected to different systems. 5 If an EFD1000 MFD is installed then each EFD1000 display is connected to an IFR GPS 6.8.5 EFD1000 PFD and EFD1000 MFD (if installed) do not share the same ground strap location. 6.6 Dual RSMs harness shielding (if installed) does not share the same ground path (bonding strap location). 6.8.6 If an EFD1000 MFD is installed there is an alternate static source available to the pilot. 5.2 The EFD displays all have the same software version. 5.2.6 The EBB58 may only be installed in a multiple display configuration and may only be connected to an EFD1000 MFD no other connections are permitted. 6.3 Log book entry stating aircraft has been modified in accordance with EFD1000 AML-STC. 1.10 Update warranty records on Aspen Avionics website at www.aspenavionics.com/dealerramp Misc Complete the Installed Equipment Configuration Matrix in Section 1.2 of the EFD1000 AFMS (900-00008-001) and insert the completed AFMS in the Airplane Flight Manual. (See sample Appendix C) Misc Complete wire routing diagram Figure D1& D2 in Appendix D. Complete circuit breaker and switch location diagram Figure D3 in Appendix D. Misc Copy of ICA Appendix D with copy of wiring diagrams (Section 9 or installer drafted), copy of Configuration Pages Section 10.4.6 and 10.4.7 for each installed EFD, and copy of Pre-Modification Checklist Table 5.1 and 5.2 inserted. This data package is to be given to owner/operator for inclusion in aircraft permanent records. Inspected by (print & sign) Installer/ Inspector Date EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 236-256 Revision G © Copyright 2010 Aspen Avionics Inc. THIS PAGE IS INTENTIONALLY LEFT BLANK EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 237-256 Revision G © Copyright 2010 Aspen Avionics Inc. APPENDIX C OPERATOR CONFIGURATION CHECKLIST And Sample of AFMS Section 1.2 (Installed Equipment Configuration Matrix) EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 238-256 Revision G © Copyright 2010 Aspen Avionics Inc. EFD1000 Operator Configuration Checklist Aircraft Type: Aircraft S/N: 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). V ne V no V fe V s V so V yse Multi engine only V mc Multi engine only initial flap extension speed I also would like my V-Speed Textual Markers set as per below: (Note – these may be edited by the pilot unless LOCKED). Insert a zero “0” in any field you wish not to appear on display. V a V bg V ref V r V x V y V lo Retractable Gear only V le Retractable Gear only I would like my Airspeed Textual Markers above: LOCKED / UNLOCKED (circle one) Owner/ Operator Date EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 239-256 Revision G © Copyright 2010 Aspen Avionics Inc. How to Fill Out AFMS Section 1.2 The Aircraft Flight Manual Supplement Section 1.2 contains information about the installed configuration of the EFD systems in the customer aircraft. The installer must complete the table in the AFMS before giving the complete AFMS document to the customer. Enter a “Yes” in all applicable boxes noting the installed equipment. The backup Instrument type and configurations are to be circled. Sample - Installed Equipment Configuration Matrix The following sample installation is of an EFD1000 PFD, EFD1000 MFD, EFD500 MFD with a -001 RSM connected to the PFD and a -003 RSM connected to the EFD1000 MFD. It has a EWR50 XM receiver connected to all three displays, a WX-500 connected to both MFDs, and no Traffic. The EBB58 Emergency Backup Battery is installed because the standby airspeed and altimeter where removed and replaced with the EFD1000 MFD. EFD500 MFD EFD1000 PFD EFD1000 MFD Installed Evolution Flight Displays Yes Yes Yes RSM with GPS N/A Yes RSM without GPS, top mount N/A RSM without GPS, bottom mount N/A Yes EBB Emergency Backup Battery Not Authorized Not Authorized Yes Traffic Interface Stormscope © Interface Yes Yes XM Weather Interface (Requires optional EWR50) Yes Yes Yes Backup Instruments: Backup Attitude Indicator Required Backup Attitude Power Source Battery Vacuum Standby Airspeed Indicator YES NO* Standby Altimeter YES NO* *EBB Emergency Backup Battery and EFD1000 MFD are required if standby Airspeed indicator and Altimeter are not installed. EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 240-256 Revision G © Copyright 2010 Aspen Avionics Inc. THIS PAGE IS INTENTIONALLY LEFT BLANK Instructions for Continued Airworthiness APPENDIX D INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Aspen Document # 900-00012-001 Revision D 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 Aircraft Maintenance Manual and operator’s Aircraft Scheduled Maintenance Program. This ICA consists of 15 pages not including the wiring and placement diagrams ICA Document # 900-00012-001 REV D Page D1 of 15 © Copyright 2010 Aspen Avionics Inc. Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D2 of 15 © Copyright 2010 Aspen Avionics Inc. ICA – RECORD OF REVISION Revision Date Description of Change ICA Revision IR 8/25/09 INITIAL RELEASE - for TSO Approval ICA Revision A 9/21/09 Made the ICA document stand-alone ICA Revision B 9/25/09 Added bonding checks. Added pagination. ICA Revision C 9/28/09 Added Procedures for System Testing During Ground Running FAA Accepted ICA Revision D 1/15/10 Increased battery replacement interval to three years or 800 hours, section D9 FAA Accepted Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D3 of 15 © Copyright 2010 Aspen Avionics Inc. D.1 Introductory Information This ICA provides instructions necessary for authorized personnel to inspect and maintain the EFD500 and EFD1000 system installed by the EFD1000 AML-STC. The following data may be required for this maintenance: Replacement Parts: See Section 1 of the EFD1000 and EFD500 SW v2.X Installation Manual, document 900-00003-001 Rev D or later. Operating Instructions: See the EFD1000 AFMS, document 900-00008-001 Wire Routing Locations: See attachment to this document Figure D1 & D2 (part of permanent aircraft records). Wiring Diagrams: See attachment to this document (part of permanent aircraft records). Special Tools For bonding checks, use a milliohm meter such as an Extech 380460 Portable Precision Milliohm Meter or equivalent. D.2 System Description The EFD1000 PFD system is comprised of the Primary Flight Display (PFD), Remote Sensor Module (RSM), Configuration Module (CM) and optional Analog Converter Unit (ACU). Optionally one or two MFD displays of either the EFD500 or EFD1000 may be installed. The EFD1000 PFD 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, XM 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. An EBB58 Emergency Backup Battery may be required in some EFD1000 MFD installation configurations if it is being used as any required secondary instruments. Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D4 of 15 © Copyright 2010 Aspen Avionics Inc. D.3 System Operation and Procedures for System Testing During Ground Running Refer to the EFD1000 AFMS, document 900-00008-001 for instructions on system operation. For System Testing refer to Section 10.6 of the EFD1000 and EFD500 SW v2.X Installation Manual, 900- 00003-001 Rev D or later. D.4 Servicing The PFD, MFD, RSM, ACU, CM, and EBB58 have no field serviceable components. Return defective units to Aspen Avionics or an authorized dealer. D.5 Overhaul Period None required. D.6 Special Tools For bonding checks, use a milliohm meter such as an Extech 380460 Portable Precision Milliohm Meter or equivalent. D.7 Airworthiness 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. D.8 Distribution of Revisions Notification of changes to this ICA will be sent to all owners on record. The changed document will then be available at www.aspenavionics.com. Paper copies are available on request, contact Aspen Avionics at www.aspenavionics.com. D.9 Periodic Maintenance and Calibration All maintenance is considered “ON CONDITION” unless otherwise noted in this ICA. EBB58 Emergency Backup Battery (use with MFD P/N 910-00001-002) The EBB58 Emergency Backup Battery when installed must be visually inspected and tested as described below once every 12 months to ensure it meets the minimum 30 minute requirement for powering the EFD1000 MFD under all foreseeable conditions. The EBB58 must be replaced every 3 years or 800 hours (whichever occurs first), or if it fails the following visual or operational tests. Instructions for Continued Airworthiness 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 • Press MENU Key • Select POWER SETTINGS, Main Menu page 10 of 11 • 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 to external power. The EBB will charge as long as the MFD is turned on and external 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 must still be operating on battery. If the EBB will not 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 D.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 back to external power and recharge the EBB to 80% or greater prior to release to service. ICA Document # 900-00012-001 REV D Page D5 of 15 © Copyright 2010 Aspen Avionics Inc. Instructions for Continued Airworthiness EFD Internal Battery (EFD P/N 910-00001-001, and -003) The internal back-up battery in the EFD must be tested once every 12 months to ensure it operates properly. Each EFD with an internal battery must have the battery replaced every 3 years or 800 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 external power. The battery will charge as long as the MFD is turned on and external power is supplied. With the battery displaying greater than 80% charge set a timer for 30 minutes. After the 30 minute time has elapsed the EFD must still be operating on battery. If the internal battery will not supply the minimum 30 minutes 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 D.12. Switch the EFD back to external power and recharge the internal battery to 80% or greater prior to release to service. Instructions for battery replacement are contained in Section D.12. Contact customer service at Aspen Avionics or an authorized Aspen Avionics Dealer for a replacement battery. ICA Document # 900-00012-001 REV D Page D6 of 15 © Copyright 2010 Aspen Avionics Inc. Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D7 of 15 © Copyright 2010 Aspen Avionics Inc. 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, RSM, CM The ACU, RSM, and Configuration Module require no periodic maintenance or calibration. 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. EFD Inspection The EFD(s) should be inspected for damage and their operation should be verified using documents from Section D1 of these ICA’s. The EFD wiring should be checked for 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 PFD 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 Inspection – if installed The ACU should be inspected for damage and its operation should be verified using documents from Section D1 of these ICA’s. ACU wiring should be checked for damage, chafing, or excessive wear. Verify ACU chassis bonding 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 RSM shim (optional), the fuselage skin, and the doubler. The installation should be inspected for cracks in the fuselage, and loose or damaged fasteners. Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D8 of 15 © Copyright 2010 Aspen Avionics Inc. 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. 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 D.9 of this ICA. Verify ≤ 3 milliohms from mounting tray to airframe ground. The wiring should be checked for damage, chafing, or excessive wear. D.11 Troubleshooting See Appendix A of the EFD1000 and EFD500 SW v2.X Installation Manual, 900-00003-001 Rev D or later for troubleshooting procedures. D.12 Removal and Replacement This section provides instructions for removal and replacement of LRUs that have been previously installed in the aircraft. No special tools are required for the removal and replacement of any system LRUs. If an LRU is found to be defective it should be removed and returned to Aspen Avionics for repair or replacement. EFD Removal Verify power is off. Carefully insert a flat blade screw driver into the locking mechanism on the top center of the EFD. While gently prying pull back the top of the EFD and extract from bracket. Remove nut securing braided ground strap to EFD. Remove pitot and static quick connectors (EFD1000 only) by pulling back outer spring loaded locking sleeve while unplugging connectors. To remove 44 pin D-sub connector unscrew both jackscrews fully and pull connector straight back. EFD Replacement Verify power is off. Install 44 pin D-sub connector and tighten jackscrews until connector is fully seated. Install pitot and static lines (EFD1000 only) to back of EFD by firmly pressing the fitting until fully seated (pitot and static quick connectors are keyed and cannot be crossed). Gently pull on connector to ensure proper connection. Connect braided bonding strap to EFD with nut. Insert bottom of EFD into bracket and pivot top forward until it locks into place on bracket. Using Section 10.6 of the EFD1000 and EFD500 SW v2.X Installation Manual, 900-00003- 001 Rev D or later, verify all system interfaces are functional. Verify proper bonding per Section 10.1.2. Perform a System Leak Test (Section 10.6.3, EFD1000 systems only) and Sonalert Test (Section 10.6.11, PFD only). Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D9 of 15 © Copyright 2010 Aspen Avionics Inc. EFD Battery Replacement EFD battery replacement must only be performed by a properly certified individual or facility. Remove EFD from panel as above. Remove two screws on each end of the football shaped cover plate on rear of the EFD. Unplug electrical connector and slide battery out of EFD. Install new battery in EFD then connect battery plug. Replace cover plate and tighten the cover screws. Tighten to 12 in-lbs. Reinstall and test EFD as above. ACU Removal Verify power is off. Remove ACU by unscrewing the jackscrews of all three D-sub connectors. Gently remove the connectors by pulling straight out. Remove the six (6) 6-32 mounting screws securing the ACU to the aircraft and remove unit from aircraft. ACU Replacement Verify power is off. Install ACU in mounting location and install six (6) 6-32 mounting screws through holes in ACU mounting tabs. Tighten to 12 in-lbs. Install all three (3) D- sub connectors securing each with the two jackscrews per connector. Verify proper bonding per Section 10.1.2, then perform post installation tests in Sections 10.6.6, 10.6.7, 10.6.9, 10.6.10 of the EFD1000 and EFD500 SW v2.X Installation Manual 900-00003-001 Rev D or later. CAUTION: Do not use a magnetic tipped screw driver when removing and replacing the RSM. RSM Removal Verify power is off. It will be necessary to gain access to the underside of the RSM mounting location in order to unplug the RSM connector. Unscrew RSM electrical connector from inside and undo shield ground wire from ground stud. Remove sealant from around base of RSM and on mounting screws. Remove four (4) 8-32 non-ferrous mounting screws from RSM and remove RSM from aircraft taking care to guide 24 inch “pigtail” connector out through ½ inch hole in aircraft skin. RSM Replacement Verify power is off. Replace the O-ring on the RSM. Contact Aspen Avionics for replacement O-ring (256-00001-001). Verify RSM shim is installed between aircraft skin and RSM if required. Feed circular connector down through ½ inch hole in aircraft skin and mount RSM (vent hole faces aft) with four (4) 8-32 non-ferrous screws. Tighten to 12-15 in-lbs. It is critical that the screws be non-ferrous to prevent the introduction of compass errors. Connect the circular electrical connector and cable tie harness to prevent chaffing and interference. Connect shield ground wire to ground stud. For RSM locations that are external or in a wet environment seal around base and on top of four mounting screws of the RSM using one of the following non-corrosive sealants: Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D10 of 15 © Copyright 2010 Aspen Avionics Inc. Non-pressure vessel mounting Dow Corning 738, MIL-A-46146 or equiv. Pressure vessel mounting Pro-Seal PS 870B-1/2, MIL-PRF-81733D, or equiv. Verify proper bonding per Section 10.1.2, and perform RSM Calibration per Section 10.5 of the EFD1000 and EFD500 SW v2.X Installation Manual, 900-00003-001 Rev D or later. Also check OAT operation per Section 10.6.4 and check RSM GPS operation per Section 10.6.6. CM Removal Verify power is off. Cut the two (2) cable ties affixing the CM to the PFD wiring harness. Unplug the Molex connector by pressing down on the locking tab and gently pulling the connector from the module. CM Replacement Verify power is off. Plug the Molex connector into the module until it clicks. Cable tie the module to the PFD wiring harness. Perform the Installation Menu Unit Configuration per section 10.4.5 of the EFD1000 Installation Manual, 900-00003-001 Rev D or later. Perform RSM Calibration per Section 10.5 of the EFD1000 and EFD500 SW v2.X Installation Manual, 900-00003- 001 Rev D or later. EBB58 Removal Verify power is off. Unscrew two jackscrews that secure the D-sub connector to the battery and then unplug the connector. Spread battery tray hold down clips outward to release battery and slide battery out of tray. EBB58 Replacement Verify power is off. Slide battery into tray until hold down clips lock into place. Install D- sub connector and secure with both jackscrews. NOTE: If the spring clip(s) are sprung so the pins do not fully seat, the mounting bracket must be replaced. Turn on EFD1000 MFD and switch unit to battery. Verify charge of 80% or greater. If battery is below 80% then charge battery to above 80% by switching MFD back to external power. EBB58 battery will recharge as long as MFD is powered up on external power. EBB58 Tray Removal Verify power is off. Remove the battery. Remove the four screws securing the tray to the airframe. Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D11 of 15 © Copyright 2010 Aspen Avionics Inc. EBB58 Tray Replacement Replace the four screws securing the tray to the airframe. Tighten to 12 in-lbs. Verify proper bonding per Section 10.1.2 of the EFD1000 Installation Manual, 900-00003-001 Rev D or later. Instructions for Continued Airworthiness INSTRUCTIONS: 1. Draw in MFD, RSM and optional ACU and autopilot locations as done for PFD (Figure D1 and D2) 2. Draw in circuit breaker and switch locations on instrument panel (Figure D3) 3. Draw in PFD and MFD to RSM cable routing. 4. Draw in ACU to PFD and ACU to autopilot cable routing. Figure D1 – EFD1000 Components and cable routing (top view) ICA Document # 900-00012-001 REV D Page D12 of 15 © Copyright 2010 Aspen Avionics Inc. Instructions for Continued Airworthiness A Figure D2 – EFD1000 Components and cable routing (side view) LRU Definitions A) PFD (CM is wired within 6” of PFD) F) RSM (MFD) - optional B) RSM (PFD) G) EBB58 Emergency Backup Battery – optional C) ACU#1 – optional H) Autopilot computer location -optional D) ACU#2 – optional J) EWR50 location - optional E) MFD#1 and MFD#2 -optional Figure D3 – Circuit Breaker and Switch Locations Circuit Breaker and Switch Definitions K) PFD/MFD circuit breakers M) ACU circuit breaker(s) - optional L) PFD/MFD switch(s) O) EBB58 Emergency Disconnect Switch – when required ICA Document # 900-00012-001 REV D Page D13 of 15 © Copyright 2010 Aspen Avionics Inc. Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D14 of 15 © Copyright 2010 Aspen Avionics Inc. INSERT WIRING DIAGRAMS AFTER THIS PAGE (The drawings must include detailed information on the interface of the EFD1000 system suitable for system troubleshooting) Instructions for Continued Airworthiness ICA Document # 900-00012-001 REV D Page D15 of 15 © Copyright 2010 Aspen Avionics Inc. INSERT THE FOLLOWING AFTER THIS PAGE COMPLETED - CONFIGURATION CHART – Section 10.4.6 & 10.4.7 COMPLETED - PRE-MODIFICATION CHECKLIST – TABLE 5.1 & 5.2 COMPLETED - OPERATOR CONFIGURATION CHECKLIST FROM APPENDIX C COMPLETED - EFD1000/500 INSTALLATION FINAL CHECKSHEET FROM APPENDIX B EFD1000 and EFD500 SW v2.X Installation Manual DOCUMENT # 900-00003-001 PAGE 256-256 Revision G © Copyright 2010 Aspen Avionics Inc. END This Page Intentionally Left Blank