Aspen Avionics EFD1000 E5 Installation Manual Download

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EFD1000 E5 Dual Electronic Flight Instrument (EFI) Install Manual

DOCUMENT # 900-00041-001

PAGE 91-226

REVISION D

8.2.5.6

Volt Reference Output

An internally gen15Vdc reference for KI-525 emulation.
Output Voltage: ............. +15Vdc ±2Vdc
Load Current: ................ 30ma maximum

8.2.5.7

KI-525A Heading and Course Datum Output

Emulated KI-525A outputs to drive the heading and course datum inputs of an
autopilot.

BENDIX KING KI525A EMULATION

ACU HSI TYPE = 0

DATUM

SCALING

REFERENCE

VOLTAGE

ACU P3-23

DESCRIPTION

(with ACU DATUM = NORMAL)

HDG

ACU P3-22

500mVdc

per degree

up to a

maximum

angle of 30⁰,

or 15Vdc.

15Vdc

500mVdc per degree up to a maximum angle of

30⁰, or 15Vdc. The output remains at +15Vdc from

31⁰ to 180⁰. At 181⁰ it switches to -15Vdc.

Likewise for negative angles (HDG bug left of the

lubber line) the gradient is -500mVdc per degree

up to -30⁰. The output remains at -15Vdc from

-31⁰ to -179⁰. At 180⁰ it switches to +15Vdc.

CRS

ACU P3-3

167mVdc

per degree

up to 90⁰, or

15Vdc.

15Vdc

167mVdc per degree up to 90⁰, or +15Vdc. From

91⁰ to 180⁰ the output diminishes by 167mVdc per

degree, reaching 0Vdc at 180⁰. For negative angles

(CRS pointer left of the lubber line) the gradient is

-167mVdc per degree up to -90⁰. From -90⁰ to

-179⁰ the output diminishes by 167mVdc per

degree reaching 0Vdc at 180⁰.

Datum outputs are in reference to ACU P3-11, ACU reference ground.

15Vdc reference may come from ACU P3-9, ACU +15Vdc Out.

Table 8-5: KI525A Emulation Specifications

8.2.5.8

NSD-360 Heading and Course Datum Output

Emulated NSD-360 outputs to drive the heading and course datum inputs of an

autopilot.

NSD-360 EMULATION

ACU HSI TYPE = 1

DATUM

SCALING

REFERENCE

VOLTAGE

ACU P3-23

DESCRIPTION

(with ACU DATUM = NORMAL)

HDG

ACU P3-22

167mVdc per

degree up to

90⁰, or

15Vdc.

15Vdc

Reference

voltage may

be any

positive DC

or AC

reference

voltage

Assuming a reference voltage of 15Vdc, the

gradient is 167mVdc per degree up to 90⁰, or

+15Vdc. From 91⁰ to 180⁰ the output diminishes

by 167mVdc per degree, reaching 0Vdc at 180⁰.

For negative angles (HDG Bug left of the lubber

line) the gradient is -167mVdc per degree up to

-90⁰. From -90⁰ to -179⁰ the output diminishes by

167mVdc per degree reaching 0Vdc at 180⁰.

Summary of Contents for EFD1000 E5

Page 1: ...Dual Electronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 1 226 REVISION D Copyright 2019 Aspen Avionics Inc EFD1000 E5 Dual Electronic Flight Instrument EFI Installation Manual...

Page 2: ...truments must not be removed See Section 4 The existing turn bank instrument or a backup attitude indicator must be retained for all installations except Aircraft Limited to VFR See Section 4 5 The RS...

Page 3: ...rs 5578 C Corrected the transmit rate for the ARINC 429 outputs Added a date to the cover Updated paragraph 7 2 11 to add tubing 5588 D Added Figure 4 1A VFR Configuration Added Section 4 5 Special Co...

Page 4: ...e AML into any 14 CFR 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 This document is protected by the C...

Page 5: ...GULATORY COMPLIANCE 21 1 10 1 TECHNICAL STANDARD ORDER 21 1 10 2 PMA APPROVAL 21 1 10 3 SOFTWARE CERTIFICATION 22 1 10 4 ENVIRONMENTAL COMPLIANCE 22 1 10 5 INSTALLATION APPROVAL 22 1 11 FIELD REPLACEA...

Page 6: ...R UNIT 2 ACU2 32 3 7 SYSTEM ARCHITECTURE 33 4 STC SPECIFIC REQUIREMENTS AND LIMITATIONS 35 4 1 EFD1000 E5 SYSTEM LIMITATIONS 35 4 2 EA100 INSTALLATION LIMITATIONS EA100 IS OPTIONAL 35 4 3 AUTHORIZED C...

Page 7: ...R FIGURE 6 2 52 6 8 3 RECESS MOUNTING THE EFD AS PER FIGURE 6 4 54 6 8 3 1 RECESS MOUNT MODIFICATION PROCEDURE 54 6 8 4 EFD BONDING STRAP 59 6 8 5 PITOT AND STATIC CONNECTIONS 59 6 8 6 QUICK CONNECTOR...

Page 8: ...84 8 ELECTRICAL CONNECTIONS 86 8 1 EFD ELECTRICAL SPECIFICATIONS 86 8 1 1 POWER INPUT 86 8 1 2 RS 232 GPS INPUT 86 8 1 3 RS 232 ADC OUTPUT 86 8 1 4 ARINC 429 GPS INPUTS 86 8 1 5 ARINC 429 VLOC INPUT 8...

Page 9: ...IRING DIAGRAMS EFD1000 E5 102 9 2 OPTIONAL INTERFACES ACU AND ACU2 103 10 CONFIGURATION AND EQUIPMENT CHECKOUT 134 10 1 WIRING CHECKS 134 10 2 BONDING CHECK 14CFR 23 867 B 134 10 3 INITIAL SYSTEM TURN...

Page 10: ...NSTALLATION MENU PAGE NETWORK PAGE 148 10 4 6 27 INSTALLATION MENU PAGE DIAGNOSTICS 149 10 4 7 CONFIGURATION DEFINITIONS 149 10 4 7 1 IAS CONFIGURATIONS 149 10 4 7 2 PANEL TILT PITCH ADJ 150 10 4 7 3...

Page 11: ...11 5 DOCUMENT OPERATIONAL CHECK 172 12 OPERATING INSTRUCTIONS 173 12 1 PILOT CONTROLS 173 12 1 1 OVERVIEW 173 12 1 2 POWER CONTROL 173 13 ENVIRONMENTAL QUALIFICATION FORMS 175 APPENDIX A TROUBLESHOOTI...

Page 12: ...5 3 Heading Sources 47 Table 5 4 Air Data Sources 47 Table 6 1 Component Weights 50 Table 6 2 Parts Required to Recess Mount each EFD 54 Table 6 3 Static Load Table 57 Table 6 4 RSM Mounting Hardware...

Page 13: ...Static Quick Connector 59 Figure 6 10 Pitot Static Line Connections 60 Figure 6 11 RSM External Mounting Locations Top Side View all aircraft types 63 Figure 6 12 RSM Internal Mounting Locations Comp...

Page 14: ...Figure 9 15 Analog NAV Interface 113 Figure 9 15A Narco and Cessna ARC Navigation Radios 114 Figure 9 16 KI525A Emulation Bendix King autopilot to ACU 115 Figure 9 17 S TEC Autopilot to ACU Interface...

Page 15: ...er of gravity 198 Figure E2 EA100 Block Diagram Bendix King Autopilots 198 Figure E3 EA100 Block Diagram Century Autopilots 198 Figure E4 EA100 Mounting 200 Figure E5 A P AHRS FAIL Annunciator Locatio...

Page 16: ...EFI Electronic Flight Instrument EHA Evolution Hazard Awareness ESV Evolution Synthetic Vision FAR Federal Aviation Regulations FD Flight Director FPM Flight Path Marker GNAV Combined GPS and VOR radi...

Page 17: ...EFD1000 E5 Evolution Flight Display PMA 910 00005 004 Configuration Module Assy TSO 910 00003 002 RSM Rev E or later Remote Sensor Module Top Mount TSO 910 00003 003 RSM Rev E or later Remote Sensor M...

Page 18: ...Connector 1 273 00003 001 Tee Fittings for Pitot Static 0 25 x 0 17 x 0 25 2 271 00001 001 Miniature Hose Clamps 8 412 00004 001 Configuration Module Cable Assembly 1 Table 1 4 903 00001 EFD1000 EFD...

Page 19: ...h density D Sub connector contacts back shell 1 116 00026 002 DB15 EMI Back shell 1 116 00026 003 DB25 EMI Back shell 1 116 00026 005 DB37 EMI Back shell 1 116 00015 001 Crimp Sockets 77 Table 1 8 903...

Page 20: ...Breaker Switch 7 5amp optional in lieu of separate C B and switch MS24509 A 7 Tinned Copper Over Braid used in lieu of double shielded wire MIL SPEC AA59569R36T0250 MIL SPEC AA59569R36T0500 RSM Double...

Page 21: ...le 2112 West Division St Arlington TX 76012 3693 817 461 9473 Info aepetsche com Wirenetics Thermax Cat 5e cable 27737 Avenue Hopkins Valencia CA 91355 661 257 2400 jtoy wirenetics com Positronic Indu...

Page 22: ...Section 13 1 10 5 Installation Approval Installation of the EFD1000 E5 is FAA approved under AML STC SA10822SC This installation manual contains FAA Approved Data but only when used to install the Asp...

Page 23: ...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 Operat...

Page 24: ...1 6 Design Eye Viewing Envelope The following information defines the viewing envelope within which the EFD1000 E5 complies with the equipment standards Minimum and maximum distance from the center of...

Page 25: ...1 in maximum Measured from Base Length 4 40 in Front to Rear Weight 0 5 lbs 2 2 2 Operational Specifications Operating Temp 55 C to 70 C Storage Temp 55 C to 85 C Max Operating Altitude 55 000 ft Unpr...

Page 26: ...e CM There is a single hardware part number Configuration Module which is then loaded with the appropriate configuration settings image file that establishes the functionality and feature set of the a...

Page 27: ...ty 95 at 50 C Input Voltage Provided by EFD Nominal Current Included in EFD Current 2 3 3 I O Specifications Proprietary Digital 2 3 4 Certification Specifications The Configuration Module is certifie...

Page 28: ...ng 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 4 3 I O Specifications ARINC 429 Inputs 2 Low Speed ARINC 429 Outp...

Page 29: ...mber 910 00004 101 102 Width 5 75 in including mounting flanges Height 2 25 in Length 4 28 in Weight 1 1 lbs 2 5 2 Operational Specifications Operating Temp 40 C to 55 C Storage Temp 55 C to 85 C Max...

Page 30: ...BS Interface 1 Output Autopilot Interface 1 Analog port G S and NAV Flag to A P low level 101 Discrete to drive Superflag 102 Heading Synchro 1 Output with 26Vac Reference 2 5 4 Certification Specific...

Page 31: ...rear portion of the EFD includes a non removable electronics module that contains a full air data computer attitude heading reference system power supplies internal battery and dual processor electron...

Page 32: ...tion data The Configuration Module connects to the EFD through a short fabricated harness and is fastened to the main wiring bundle of the display Each display has an associated Configuration Module t...

Page 33: ...system architecture in Figure 3 2 shows the relationships of the EFD1000 E5 with its associated RSM Configuration Module and optional ACU and EA100 Figure 3 1 EFD1000 E5 System Architecture EFD1000 E5...

Page 35: ...s not approved for aircraft with a maximum takeoff weight MTOW exceeding 6000lbs This installation is not authorized as a Flight Display for Category II Operations or RVSM Operations 4 2 EA100 Install...

Page 36: ...eter 1 existing Airspeed indicator 1 existing Turn Bank indicator 1 3 Magnetic Direction Indicator compass Secondary navigation indicator 2 when required see section 4 4 5 IFR GPS navigator input see...

Page 37: ...4 1A EFD1000 E5 Authorized VFR with Backups Configuration E5 RSM ACU optional CM Required Instruments existing IAS 1 ALT 1 Compass 1 Requires existing Altimeter 1 existing Airspeed indicator 1 Magneti...

Page 38: ...e indicator may be removed unless it is required for autopilot or flight director purposes It may also be retained and used as the secondary source of attitude if it is desired to remove the turn and...

Page 39: ...any position in the instrument panel including the co pilot side as the turn and slip or turn coordinator is retained in its original location as part of the backup attitude solution Flight Director d...

Page 40: ...ion would not require a backup NAV indicator However a GPS with legacy VLOC radio that does not include an integral display with CDI indications approved for navigation will require a backup NAV indic...

Page 41: ...t placard that permits IFR operation 2 Permanently affix a placard in full view of the pilot stating Operation of This Aircraft is Limited to VFR Only in the same location as the obliterated statement...

Page 42: ...ield of view see Figure 4 2 NA if no flight director 5 Is a backup navigation indicator required see section 4 4 5 NA if no Backup NAV indicator is required If a backup indicator is required is there...

Page 43: ...ction 7 1 The EFD1000 E5 system uses an internal battery to permit operation of the EFD1000 E5 during an aircraft charging system failure If the aircraft bus voltage falls below a nominal 12 3V 14V el...

Page 44: ...Generally unless modified aircraft serial number 16084 and above have standard airspeed indicators and 16083 and below do not The pitot and static systems must still be connected to the EFD1000 E5 be...

Page 45: ...puts Heading Datum and Course Datum via the ACU the existing HSI DG is no longer required to provide this output to the autopilot When the EFD1000 E5 System is installed the ACU controls all analog na...

Page 46: ...4xx 5xx GTN 6xx 7xx RS 232 This configuration should not be used Garmin GNS 480 Software v2 0 and below ARINC 429 This configuration should not be used Garmin GNS 480 Software v2 3 ARINC 429 GAMA 429...

Page 47: ...Air data information is available in the following formats The ACU does not pass thru air data information to its output bus the ACU2 does See Section 8 for ARINC 429 and RS 232 air data output speci...

Page 48: ...r wiring connections 5 4 7 Flush or Recess Mounting the EFD If there is insufficient clearance between an EFD and the control column when the flight controls are in the full nose down position it will...

Page 50: ...the Instructions for Continued Airworthiness 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 t...

Page 51: ...r 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 requ...

Page 52: ...down on the knobs 6 8 1 EFD Mounting Location The EFD must be mounted approximately centered in the instrument panel per 14CFR 23 1321 d If the two existing instrument holes that contain the attitude...

Page 53: ...ews NAS1149FN632P washers and MS21044N06 6 32 Nuts It is also acceptable to use existing 6 nutplates 1 Burnish the back of the instrument panel around one of the 6 mounting holes to allow for bracket...

Page 54: ...ional data to accommodate individual differences in an aircraft can be presented to a Structural DER or Regulatory Authority for approval If the data package is satisfactory the DER or Regulatory Auth...

Page 55: ...EFD Cutout and Bracket Mounting Hole Locations Using the dimensions from Figure 6 3 as a guide mark the EFD cutout and four bracket mounting holes The clearance notch at the top see detail A is to per...

Page 56: ...and nuts to 12 in lbs anchoring the brackets to the panel NOTE Spacers A come in a strip of three which can be snapped apart The thickness of the instrument panel will determine how many spacers will...

Page 57: ...3 13 2B for additional Structural Data Direction of Pull push on bracket Load Factor Static Test Load load factor x EFD weight Forward toward firewall 9 0g 9 0 x 2 9 26 lbs Table 6 3 Static Load Table...

Page 58: ...ectronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 58 226 REVISION D Copyright 2019 Aspen Avionics Inc Figure 6 6 Recess Mounting Bracket Dimensions inches Figure 6 7 EFD Mounti...

Page 59: ...to the EFD1000 E5 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 conne...

Page 60: ...t can be secured away from flight controls Secure each end with the supplied hose clamps 5 Secure pitot and static lines as necessary to prevent interference with other aircraft structures and compone...

Page 61: ...ainst direct lightning effects 6 9 1 RSM Internal Mounting Typically the RSM will be internally mounted within an area of the aircraft fuselage or wing structure that is magnetically benign For alumin...

Page 62: ...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 permissi...

Page 63: ...Aspen Avionics Inc Figure 6 11 RSM External Mounting Locations Top Side View all aircraft types 12 Preferred Area Hat Rack Baggage Compartment NO ZONE NO ZONE Less Preferred Locations See Note 12 min...

Page 64: ...6 12 RSM Internal Mounting Locations Composite Fabric Aircraft Hat Rack Baggage Compartment NO ZONE 39 NO ZONE Acceptable Internal Mount Area Composite Fabric 12 12 NO ZONE NO ZONE Acceptable Interna...

Page 65: ...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 HMR2300 Smart Digital Magnet...

Page 66: ...Be sure to check for interference with the following systems operating Servos Alternator Generator and cabling to aircraft battery Blower motors Strobes beacons Pulse equipment DME transponder active...

Page 67: ...ores Operate flight controls from stop to stop and verify no more than 2 of compass needle movement Should the compass show excessive needle movement it would be required to find a new location or deg...

Page 68: ...hown in Figure 6 12 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 a...

Page 69: ...o 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 11 for shim fabrication Figure 6 17 RSM Side to Side Max Tilt...

Page 70: ...own 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 8 1 RSM Doubler Fabrication 1 Determin...

Page 71: ...within 4 see Figure 6 14 Figure 6 20 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 do...

Page 72: ...rs The supplied Brass hardware should be used NOTE The RSM contains a sensitive magnetometer Nearby ferrous components or hardware can magnetize the RSM and or cause erroneous indications 1 It is not...

Page 73: ...essary If the RSM exceeds the mounting limits of Section 6 9 7 a shim will be required Fabricate a shim with the dimensions of the RSM baseplate Optionally the shim can be made square and slightly lar...

Page 74: ...he 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 inside the outer footprint of the RSM mounting l...

Page 75: ...raphs 100 to 114 pages 1 to 8 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 brai...

Page 76: ...000 E5 Dual Electronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 76 226 REVISION D Copyright 2019 Aspen Avionics Inc Figure 6 27 ACU Dimensions inches 15 20 1 1 14 37 19 13 25 1...

Page 78: ...EFD wire harness Leave just enough slack in the cable ties so that the configuration module can slide along the EFD cable This will prevent strain on the configuration module connector while the EFD...

Page 80: ...ion accessible to the pilot while seated The breaker will be powered from the switched battery or essential bus Label the switch and or breaker ASPEN EFD The switch must be rated for at least 7 5 amps...

Page 81: ...ielded single conductor wires EFD1000 E5 to RSM wiring does not require the over braid or double shield only what is specified in Section 7 2 6 ACU to GPS ACU to VLOC receiver and ACU to autopilot req...

Page 82: ...Red Green 3 32 White Orange Brown 4 33 White Yellow Orange White 5 34 White Green Orange 6 35 White Blue Blue Blue White 7 36 White Brown White 7 2 6 2 Assembly using M27500 A24SD7T23 Cable Terminate...

Page 83: ...screw as shown in Figure 7 3 Figure 7 3 EFD Back Shell Grounds RSM 7 2 7 Configuration Module Wiring The Configuration Module CM connector comes as an assembly with color coded wires within an over b...

Page 84: ...e is as close to the navigation receiver as practical Do not splice the connection at the back of the NAV indicator 7 2 10 Autopilot Wiring Wire the autopilot to ACU as shown in Section 9 Remove any e...

Page 86: ...60 65 configuration 8 1 3 RS 232 ADC Output The EFD1000 E5 Display outputs the following computed air data output signals over the RS 232 bus in Format Z Shadin ADC TYPE 1 and Format C Bendix King ADC...

Page 87: ...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 3 EFD A429 VLOC Input 8 1 6 ARINC 429 Output Th...

Page 88: ...5 Table 8 4 EFD1000 E5 A429 GPS Output 8 2 ACU Electrical Specifications 910 00004 all dash numbers 8 2 1 Power Input Nominal Input 14Vdc or 28Vdc Operating Range 11Vdc to 32Vdc 8 2 2 Reserved 8 2 3 V...

Page 89: ...6Vac in 10 4Vac out DC Offset 0Vdc to 5Vdc Offset applied to Rotor C 8 2 4 2 TO FROM FLAG Input Differential input from a GPS receiver indicating whether flying TO or FROM the active waypoint TO the w...

Page 90: ...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 NOTE ACU2 P N 910 00004 102 does not have a low level flag It pr...

Page 91: ...dc 167mVdc per degree up to 90 or 15Vdc From 91 to 180 the output diminishes by 167mVdc per degree reaching 0Vdc at 180 For negative angles CRS pointer left of the lubber line the gradient is 167mVdc...

Page 92: ...Reference voltage may be any AC reference voltage Assuming a reference voltage of 26Vac the gradient is 131mVac per degree up to 90 or 11 8Vac From 91 to 180 the output diminishes by 131mVac per degr...

Page 93: ...c Heading 200 Table 8 8 ACU A429 Output 8 3 ACU2 Electrical Specifications 910 00004 10x only The ACU2 has the same interfaces as the ACU above on connectors J1 J2 J3 plus it adds the following interf...

Page 94: ...tic heading air data and selected course Can be configured High or Low speed Note Except as shown in the wiring diagrams Section 9 no ARINC 429 interface is approved under the Aspen STC and must be ap...

Page 95: ...Receiver 5 26 ARINCTX1A OUTPUT ARINC Transmitter 1 27 ARINCTX1B OUTPUT ARINC Transmitter 1 28 Reserved Future Expansion 29 Reserved 30 RS 232TX0 OUTPUT RS 232 TX 31 RS 232RX0 INPUT RS 232 RX0 115kb 3...

Page 96: ...RSME RSM Connection 6 RSMF RSM Connection 7 RSMG RSM Connection Table 8 11 RSM Pin Out Male Pin Side Solder Cup Side Figure 8 2 RSM Mating Connector Install Side 8 6 Configuration Module Pin Out Pin...

Page 97: ...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 13 ACU J1 Pin Out Figure 8 4 ACU J1 Connector as viewed from front of unit Pin Nu...

Page 98: ...ING VALID OUTPUT Active Low Output when Heading Valid J2 26 DH INPUT N A J2 27 FD VALID INPUT N A J2 28 FD PITCH2 INPUT N A J2 29 ALT ENGAGE OUTPUT N A J2 30 VLOCFLG OUT Common J2 31 GS IN INPUT Glide...

Page 99: ...7 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 OB...

Page 100: ...external equipment J4 23 429TX3A OUTPUT ARINC 429 Port 3 Transmit A J4 24 429RX3A INPUT ARINC 429 Port 3 Receive A J4 25 400HZ REF HI OUTPUT 400Hz excitation for heading synchro J4 26 HDG X OUTPUT Hea...

Page 101: ...51 SPARE DISC10 INPUT Discrete Input J4 52 SYN HDG VALID OUTPUT Active Low output when synchro Hdg Valid J4 53 MK12D GS FLG INPUT High impedance Glideslope Flag Narco J4 54 MK12D GS FLG INPUT High im...

Page 102: ...0A and a PN 101 HSI by providing outputs for HDG Datum and CRS Datum to an autopilot The EFD1000 E5 is compatible with any autopilot that is compatible with a KI 525A NSD 360A or PN 101 HSI Should con...

Page 103: ...0B 800B 9 19A Cessna 300 400 800 IFCS 9 19B Cessna Navomatic 400 400A 9 19C Cessna Navomatic 300A 9 19D Cessna Navomatic 300 9 20 Bendix FCS 810 9 24 Back Up NAV Indicator internal converter 9 25 Back...

Page 104: ...D 1 All wires in this manual are 22 AWG unless otherwise noted 2 Connect ground lugs to airframe ground with as short a conductor as possible Connect to airframe ground with as short a conductor as po...

Page 105: ...Double Shield EFD1000 18 429 VLOC RX2A P2002 24 429 VLOC RX2B 19 23 GARMIN GNC255 1 A429 VLOC NONE I No GPS1 VLOC1 1 Over shield or over braid required on this wire bundle to comply with HIRF Lightnin...

Page 106: ...48 49 or 50 51 not both GNAV See Figure 9 27 for GNS GTN configuration GNS530 GNS480 and GTN650 750 use same config as GNS430 GPS500 and GTN625 635 725 uses same config as GPS400 4 Over shield or ove...

Page 107: ...uired on this wire bundle to comply with HIRF Lightning Extend within back shell Ground at both ends 4 Configuration Matrix see Section 10 6 Pins 4 24 may be swapped with pins 5 25 if configured accor...

Page 108: ...P1001 J101 J1 P3 4 5 16 17 GPS RX1A GPS RX1B 429 TX2A 429 TX2B 16 15 16 33 32 46 10 47 29 48 50 49 51 15 67 48 33 32 4 ID 1 Description D E ID 2 NONE NONE GPS1 No NAV1 GPS1 NAV1 5 3 See Figure 9 15 fo...

Page 109: ...B 9 14 for GX 50 60 GX 55 65 RS 232 Flight Plan To EFD1000 Pin 9 Analog VLOC 1 Optional Back Up Nav Indicator V L O C 1 See Figure 9 24 9 25 9 26 for Back Up NAV recommendations 2 1 2 3 1 ID 1 Descrip...

Page 110: ...t 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 HI...

Page 111: ...to comply with HIRF Lightning Extend within back shell Ground at both ends 1 2 16 Existing OBS LEG switch N C N C N C OBS LEG 3 2 3 4 If existing installation has external OBS LEG switch then splice...

Page 112: ...13 6 P2 OBS LEG APPR ACTIVE 7 24 31 30 29 10 14 13 12 11 28 29 Vert FLG Vert FLG Vert DN Vert UP 34 15 5 _ _ _ _ _ _ P1 GX 55 GX 50 GX 60 GX 65 OBS HOLD ACTIVE 2 3 The GX 50 60 share pin 29 between Ve...

Page 113: ...lope interface is for units with GS option 3 P2 P2 KX170A 170B 175B P171 3 4 See manufacturers documentation for KN 70 73 75 Glideslope connections 3 _ _ _ _ _ 4 2 2 See Figure 9 27 for SL 30 configur...

Page 114: ...placement radios Composite Phase VOR1 2 180 Note The composite output from these radios use a DC offset voltage A capacitor is required as shown below Note The Glide Slope output from some Narco radio...

Page 115: ...P3 17 ACU HSI TYPE 0 KFC 275 KCP220 P2201 KCP220 P2202 32 16 33 17 2 3 11 28 27 10 22 _ 38 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ KFC 250 275 HDG CRS Datum for 3 Instruments KCS 55A only 1 Configuration Ma...

Page 116: ...nnection between GPS and 55X When using the EFD1000 GPSS only this pin is left open 2 3 4 3 ACU Refer to autopilot manufacturers documentation for autopilot side integration information including auto...

Page 117: ...UM CRS HDG COM HDG CRS EXT Century Heading System Adapter CD175 2 17 20 ACU When replacing a DC version NSD 360 If the existing DG HSI is to remain in the aircraft do not parallel HDG CRS Datum with A...

Page 118: ...nufacturers 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 th...

Page 119: ...PARTS T1 Use Triad SP 66 MIL No TF5S21ZZ T2 T3 New Installations Use Triad SP 67 MIL No TF5S21ZZTY T2 T3 Existing Installations May continue to use a SP 66 unless performance was unacceptable then us...

Page 120: ...ter 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 d...

Page 121: ...o these units provided NAV1 and NAV2 inputs are jumpered together 300B 400B 800B CA 550A FD 3 4 Refer to autopilot manufacturers documentation for autopilot side integration information including auto...

Page 122: ...autopilot no matter the position of the Nav1 2 selector switch Z N P _ _ 5 Y S ILS ENERGIZE Cessna 300 400 800 IFCS Mode Controller S530A 3 4 Refer to autopilot manufacturers documentation for autopi...

Page 123: ...n line Verify 10Vac goes to ACU P3 23 and 4 5Vdc goes to ACU P3 25 before connecting the ACU Sometimes the 10Vac and 4 5Vdc signals are reversed at the mode controller 1 EXT OFFSET P3 CA 520 B AP Mode...

Page 124: ...5 Vdc 0 4 5Vdc 90 8 5Vdc Refer to autopilot manufacturers documentation for autopilot side integration information including autopilot STC compliance data and for autopilot and flight director checko...

Page 125: ...ence Autopilot can only be connected to ACU 1 in a dual ACU configuration 1 2 Refer to autopilot manufacturers documentation for autopilot side integration information including autopilot STC complian...

Page 126: ...lot 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 D t HDG LO CRS LO B A F E P2 18 37 16 35...

Page 127: ...lding as required Splice connections as close to NAV receiver as possible Do not splice from back of NAV indicator GS lines will only be connected on NAV units with this option Some Nav Receivers have...

Page 128: ...up is shown on Figure 9 15 2 3 4 NAV Indicator NAV FLG NAV FLG CDI RIGHT CDI LEFT TO FROM OBS RES A H OBS RES C OBS RES G OBS RES F OBS RES E OBS RES D 3 2 Parallel all lines shown maintaining shield...

Page 129: ...Figures 9 6 and 9 7 for EFD1000 to GNAV interface Refer to manufacturers documentation to verify the integration data and for information regarding checkout procedures This drawing as it pertains to t...

Page 130: ...NT ARINC 429 SETUP CH_IN SEL SPEED SDI 2 EFIS LOW See Note 1 CH_OUT SEL SPEED SDI 1 GAMA 429 GFX Int LOW 2 See Note 1 2 VOR ILS LOW 2 SYS1 or SYS2 GAMA 429 GFX Int this configuration has Flight Plan i...

Page 131: ...ADC TYPE 1 Format Z Garmin ADC TYPE 2 Format C King If ACU is installed parallel this EFD output with ACU and other device requiring A429 Heading and or Air Data 2 4 A429 TX2A A429 TX2B 5 P3 to optio...

Page 132: ...synchro heading input must use the same 400HZ reference Either wire the 400HZ from the external source in to both the ACU2 and the device or use ACU2 400HZ output as reference to device Note if a ext...

Page 133: ...EFD1000 E5 Dual Electronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 133 226 REVISION D Copyright 2019 Aspen Avionics Inc THIS PAGE IS INTENTIONALLY LEFT BLANK...

Page 134: ...red wiring bundles 3 Apply aircraft power and close the EFD and ACU circuit breakers and the EFD master switch if installed 4 Verify proper voltage on EFD main connector pins 1 2 and 3 and that there...

Page 135: ...ious 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 e...

Page 136: ...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 the Instructions for C...

Page 137: ...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 1...

Page 138: ...H or other legal form of documentation e g Placard 10 4 6 1 Installation Menu Page IAS CONFIG A All standard airspeed indicators that use a Vne will set the MOL TYPE to 1 and then enter the Vne in the...

Page 139: ...is 226 KIAS to 15 500 feet and then Vmo decreases 4 KIAS per 1 000 feet Known values Vmo 226 ALT1 15500 KNOTS 4 ALT2 1000 MAX ALT A C service ceiling Use MOL PARAM SEL to select Vmo ALT1 KNOTS ALT2 Us...

Page 140: ...Notes 10 4 6 4 Installation Menu Page IAS CONFIG D NOTE These selections are rotorcraft only and are grayed out Does not apply to EFD1000 E5 10 4 6 5 Installation Menu Page IAS CONFIG E This menu is u...

Page 141: ...N VSPD EDIT UNLOCKED LOCKED Not Used Not Used Notes 10 4 6 7 Installation Menu Page IAS CONFIG G IAS DISPLAY DISABLE will remove the airspeed bug from the tape the upper left window and the left knob...

Page 142: ...have a Configuration Matrix table that will be used to set ID 1 and ID 2 INSTALLATION MENU PAGE NAV SETUP A Feature Options Actual Setting GPS NAV 1 NONE A B C D E G H I M GPS NAV 2 NONE Not Used Not...

Page 143: ...EFD because if it was running low speed when powered up it will continue to run low speed even if changed to high above until it boots back up 10 4 6 11 Installation Menu Page RS 232 CONFIG A The fol...

Page 144: ...1 NONE ADC TYPE 1 ADC TYPE 2 232 OUT PORT 2 NONE ADC TYPE 1 ADC TYPE 2 232 OUT PORT 3 NONE ADC TYPE 1 ADC TYPE 2 Notes ADC TYPE 1 Z Shadin format ADC TYPE 2 C Bendix King C format 10 4 6 13 Installat...

Page 145: ...01 and 002 RSM BOTTOM 003 RSM INSTALLATION MENU PAGE MISC CONFIG A Feature Options Actual Setting RSM Orientation TOP BOTTOM Inverted orientation RSM GPS Enable Not applicable RSM GPS USAGE Not applic...

Page 146: ...e Options Actual Setting COMPOSITE PHASE VOR1 2 0 0 180 0 GPSS GAIN 0 5 to 2 0 0 1 increments CRS SDI COMMON NAV 1 2 OBS DISPLAY Not applicable Pitch Sync for Helicopters Not applicable 10 4 6 19 Inst...

Page 147: ...ble 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...

Page 148: ...Menu Page AOA CONFIG This page not applicable to the EFD1000 E5 10 4 6 26 Installation Menu Page NETWORK PAGE This menu is for diagnostic purposes only unless an EA100 is installed For EA100 installat...

Page 149: ...ENU 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 10 4 7 Con...

Page 150: ...configured to look exactly like the mechanical indicator Tapes are turned off and cannot be turned on by pilot LOCK ON Tapes are always enabled and cannot be turned off by pilot NOTE Tapes cannot be l...

Page 151: ...he 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 Figure 10 4 Illustration of aircraft 2 nos...

Page 152: ...FD1000 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 10 4 8 NAV Setup Confi...

Page 153: ...nance 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...

Page 154: ...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 30 starting from North to verify that...

Page 155: ...ed to the Vertical Component on the EFD1000 E5 Diagnostic Page in the installation menu Obtaining Vertical Component Z from EFD1000 E5 Enter the EFD1000 E5 installation menu and navigate to the last m...

Page 156: ...Z Z2 to the NOAA value When level the RSM Z value should be within 0 03 of the NOAA value 10 5 1 2 Conventional Gear RSM Calibration Procedure Perform the RSM calibration procedure per Section 10 5 2...

Page 157: ...2 B CR R Imaginary pivot point R Radius to pivot point approximately equal to wingspan 30ft 1 Starting Point A Established Constant Rate turn 10 seconds after 1 CR Constant Rate Turn must continue unt...

Page 158: ...ding 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 Cali...

Page 159: ...meter Calibration Complete message occurs between B D of Figure 10 10 then REJECT the results and re run the procedure Figure 10 13 Aircraft Turning At the end of the calibration routine the ACCEPT CA...

Page 160: ...for 5 seconds and return the RSM CALIBRATION menu page to its initial state Figure 10 15 Results Accepted Pressing the REJECT CALIBRATION selection shall reject the calibration results Reject the resu...

Page 161: ...on Installation Final Check Sheet of Appendix B and verify heading viewed on compass card is within 4 degrees using a calibrated heading source i e sight compass compass rose Record the actual EFD he...

Page 162: ...UTION 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 a...

Page 163: ...ully functional interface 10 6 5 1 All GPS interfaces 1 Allow the GPS1 receiver to acquire a valid position and enter a Direct To waypoint or a Flight Plan 2 Verify GPS groundspeed is displayed on the...

Page 164: ...lling the EFD and ACU circuit breakers 10 6 8 Autopilot Sensor Test Refer to autopilot manufacturer s post installation check out procedures for complete autopilot post installation ground checks At a...

Page 165: ...Verify that the external power voltage the power to the EFD is at the appropriate level for the aircraft and the last line on the Menu page shows BATT CHARGING 3 With the EFD Menu displayed press the...

Page 166: ...nt for 20 seconds each 4 Operate all aircraft lighting including position lights strobe lights navigation lights and all other forms of lighting for 20 seconds each 5 Operate all environmental equipme...

Page 167: ...MARKER BEACON Verify the operation of each Marker Beacon Receiver while monitoring the effects of the Threat equipment No 1 No 2 ADF If Installed Verify the operation of each ADF receiver while monito...

Page 168: ...eral Threat equipment SAFETY EQUPIMENT WEATHER RADAR If Installed Verify the function of the weather radar system while monitoring the effects of the Threat equipment Prior to ground operation of the...

Page 169: ...rference while monitoring the effects of the Threat equipment 10 6 14 Flight Control Interference Check CAUTION Verify control surfaces are free and clear With the EFD mounted in the instrument panel...

Page 170: ...lectronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 170 226 REVISION D Copyright 2019 Aspen Avionics Inc 10 6 16 EA100 Adapter Testing See Appendix E for EA100 Adapter configura...

Page 171: ...ect with reference to the horizon 11 2 Heading Card Flight Checks a Make a 180 degree coordinated turn to the right and verify that the compass scale and numerical heading indication correctly track t...

Page 172: ...and verify the aircraft tracks to the VOR d Enter a valid flight plan or Direct To on the GPS Couple the GPS to the E5 Engage the autopilot in NAV Mode verify the autopilot tracks the GPS Note GPSS is...

Page 173: ...y that allows the system to continue to operate in the event of a failure of the aircraft electrical system The typical EFD1000 E5 installation receives aircraft power from the battery bus via a dedic...

Page 174: ...019 Aspen Avionics Inc 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 holdi...

Page 175: ...st 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...

Page 176: ...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 EFD display Voltage Spike 17 0 n a Powered from EFD display Audio Freq Conduc...

Page 177: ...ent 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 F...

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Page 180: ...wired RSM a Fail x a Check RSM to EFD wiring for shorts or opens Repair or replace RSM Repair or replace EFD IMU a Fail a Replace EFD ADC a Fail a Replace EFD ADAHRS a Fail a Replace EFD b Initializin...

Page 181: ...EV button for 20 seconds or unplug EFD internal battery for 3 seconds d EFD is defective d Repair or replace EFD Display flashes on off black white or blue white repetitively a Configuration Module un...

Page 182: ...t have a valid TO waypoint and position b Allow GPS to acquire a position and enter a flight plan or Direct To c GPS or VLOC receiver failed c See GPS VLOC manufacturer s instructions for troubleshoot...

Page 183: ...ation away from buildings and other ferrous objects d Ferrous hardware used to mount RSM d Only non ferrous screws nuts washers may be used on RSM e Airframe or external magnetic interference e Check...

Page 184: ...low the autopilot manufacturer s guidelines for adjusting roll null centering No VDI or glide slope display on EFD a CRS pointer more than 100 from lubberline b ILS frequency not selected a Rotate CRS...

Page 185: ...EFD1000 E5 Dual Electronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 185 226 REVISION D Copyright 2019 Aspen Avionics Inc Appendix B Installation Final Check Sheet...

Page 186: ...EFD Heading Calibrated Heading Source Tolerance Actual EFD 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 IAS Setting Band...

Page 187: ...ilot Sensor Test if installed 10 6 9 10 6 10 Ancillary Equipment Heading and Air Data if connected List equipment interfaced 10 6 11 Battery Capacity Check Internal battery 80 Charge 10 6 12 TAPES Con...

Page 188: ...ring cabling from the backup turn and bank altimeter or airspeed indicator is routed directly behind the fan on rear of the EFD1000 E5 display 6 9 4 RSM location are 2 degrees of needle deflection on...

Page 189: ...ata package is to be given to owner operator for inclusion in aircraft permanent records EA100 Adapter Installations Only Appendix E A P AHRS FAIL annunciator installed in the pilot primary field of v...

Page 190: ...ual Electronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 190 226 REVISION D Copyright 2019 Aspen Avionics Inc Appendix C Sample of AFMS Section 1 2 Installed Equipment Configura...

Page 191: ...ting the installed equipment and backup equipment type Sample Installed Equipment Configuration Matrix The following sample installation is an EFD1000 E5 with a GNS 430W and an EA100 It is using the T...

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Page 193: ...EFD1000 E5 Dual Electronic Flight Instrument EFI Install Manual DOCUMENT 900 00041 001 PAGE 193 226 REVISION D Copyright 2019 Aspen Avionics Inc Appendix D Component Maintenance Manual CMM...

Page 194: ...that which is described Aspen Avionics document 900 00012 001 Instructions for Continued Airworthiness Service Life None Specified Field Replaceable Parts Description Aspen Part Number EFD Internal Ba...

Page 195: ...right 2019 Aspen Avionics Inc Appendix E EA100 Adapter Optional Autopilot Attitude Adapter Replaces the Bendix King KG258 KI254 KI255 KI256 to the KAP100 150 and KFC150 200 250 autopilots And Replaces...

Page 196: ...s approved by this STC when an EA100 is installed KI 255 KI256 and Century AI FD indicators must not be removed as the EFD1000 E5 cannot display FD commands Therefore these indicators must be relocate...

Page 197: ...equired Max Humidity 95 at 50 C Input Voltage 14 and 28 VDC Nominal Current 0 25 0 5 Amps 28v 14v I O Specifications Ethernet Port 1 Digital Autopilot Pitch gyro Out 1 Analog Autopilot Roll gyro Out 1...

Page 198: ...t Flight Computer Ethernet Pitch Hi Roll Hi Ref Voltage 2A 14 28v A P AHRS Fail Lamp A P C B A P Disconnect Switch Existing Relay COMM Relay Energized Relay Relaxed A P Disconnect A P AHRS A P INTRLK...

Page 199: ...on It is recommended to mount the EA100 as close to the autopilot computer as possible The EA100 has no user interface and therefore can be remote mounted in any orientation as long as it is accessibl...

Page 200: ...STC and will require separate FAA approved data Structural DER analysis or static testing should be accomplished to the following ultimate load factors for items of mass within the cabin or cockpit u...

Page 201: ...w A two ampere trip free resettable push pull type circuit breaker must be installed for the EA100 in a location accessible to the pilot while seated The power source for the EA100 is the same as that...

Page 202: ...bels in the panel and be readable and discernible lit at night Primary Field of View for the purpose of this STC uses the location of the EFD as the measuring point The A P AHRS FAIL light must be wit...

Page 203: ...onnector DB 15 is suggested with the wires connected per Figure E7 or E7A below c Select the appropriate TR Junction box i TR1 Century 21 31 41 2000 4000 the three 3 transformers are Triad SP 66 MIL T...

Page 204: ...21 31 41 2000 4000 Figure E7A TR2 Century IIB III IV E5 6 Electrical Connection EA100 P1 Connector PIN NAME INPUT OUTPUT FUNCTION 1 ETHERNET TX OUTPUT ETHERNET TX OUT TO EFD1000 2 ETHERNET TX OUTPUT...

Page 205: ...4 38 RESERVED 39 A P INTRLK COMM INPUT COMM CONTACT ON RELAY 40 A P INTRLK RELAXED OUTPUT RELAXED STATE OF RELAY 41 A P INTRLK ENERGIZED OUTPUT ENERGIZED STATE OF RELAY 42 A P AHRS VALID OUTPUT ENERGI...

Page 206: ...EFD1000 39 ENET TX ENET RX 2A 8 15 7 14 P N 412 00013 00x 37 1 EA100 to EFD1000 Ethernet connection must use Aspen P N 412 00013 00x cable Shields must be terminated within the EA100 and EFD back shel...

Page 207: ...NO NC A P DISC Existing AP DISC Relay A P DISC IN 19X1 19X2 B EA100 41 39 18 3 16 1 P2 AP EXCITE HI AP EXCITE LO AP ROLL HI AP ROLL LO A P INTRLK COMM A P INTRLK ENERGIZED 17 2 AP PITCH HI AP PITCH LO...

Page 208: ...sures the autopilot cannot be engaged or will disengage if the EA100 attitude is invalid The autopilot sonalert or disconnect tone must not be interrupted with this relay Wire as shown 20 AWG wire may...

Page 209: ...circuit must be run through an internal relay within the EA100 This ensures the autopilot cannot be engaged or will disengage if the EA100 attitude is invalid The autopilot sonalert or disconnect tone...

Page 210: ...t be engaged or will disengage if the EA100 attitude is invalid Wire as shown P2992 After w 10 GYRO REF KCP299 Flight Computer with KA141 with P N 065 5016 XX Adapter Board for 3 instruments Only KCP2...

Page 211: ...KCP299 flight computers with adapter board 065 5016 XX may use this drawing Flight computers with 065 5015 XX adapter boards not approved 18 AWG wire may be spliced to a 22 AWG wire of no more than 4...

Page 212: ...om Computer AMP pin N or relay and install new pin wire or cut wire and splice on new wire Run new wire from AMP pin N or relay to EA100 P2 41 3 Before A P Disc and Relay partial equals Existing Wires...

Page 213: ...shown CD18 Remove wire from CD76 B Relay Box and install new pin wire or cut wire and splice on new wire Run new wire from CD76 B to EA100 P2 41 3 Before Trim Enable Ap Disc and Century Relay Box par...

Page 214: ...s shown CD64 Remove wire from CD81 B 1A544 Relay Box and install new pin wire or cut wire and splice on new wire Run new wire from CD81 B to EA100 P2 41 3 After TR2 Transformer Interface box must be f...

Page 215: ...e from CD186 4 and install new pin wire or cut wire and splice on new wire Run new wire from CD186 4 to EA100 P2 41 3 Before A P DISC Switch OR No previous switch Existing Wire A P DISC After A P DISC...

Page 216: ...isconnect tone must not be interrupted with this relay Wire as shown CD176 Remove wire from CD200 19 and install new pin wire or cut wire and splice on new wire Run new wire from CD200 19 to EA100 P2...

Page 217: ...cannot be engaged or will disengage if the EA100 attitude is invalid The autopilot sonalert or disconnect tone must not be interrupted with this relay Wire as shown CD176 CD144 Remove wire from CD184...

Page 218: ...the autopilot cannot be engaged or will disengage if the EA100 attitude is invalid The autopilot sonalert or disconnect tone must not be interrupted with this relay Wire as shown CD176 Remove wire fro...

Page 219: ...autopilot cannot be engaged or will disengage if the EA100 attitude is invalid The autopilot sonalert or disconnect tone must not be interrupted with this relay Wire as shown CD176 Remove wire from C...

Page 220: ...r the resistor divider network Century A P excitation is 28Vp p before network Use 2 90 as the setting for all Century IIB III and IV autopilots regardless of what is measured Voltage is noted for tro...

Page 221: ...reaker Power up the autopilot a Verify the AP AHRS FAIL light extinguishes b Press Menu on the EFD and then press the AHRS RESET button twice on the EFD Verify the AP AHRS FAIL light turns on and then...

Page 222: ...9 Autopilot Gyro Alignment See Tech Note 2010 10 for instructions on using the EA100 Alignment Tool and the autopilot manufacturer s alignment procedure to make these adjustments Bendix King Autopilo...

Page 223: ...aft does not lose more than 100ft during the turn Verify the autopilot rolls out on the HDG bug with little overshoot e Turn the HDG Bug 90 degrees right During the turn record the maximum bank angle...

Page 224: ...Using the Pitch Modifier pitch rocker switch press the up side of the switch to initiate a climb attitude of about 5 degrees Verify the aircraft climbs and maintains a consistent 5 degree 2 degree att...

Page 225: ...ft Bank Angle HDG ALT Maximum Right Bank Angle ATT ALT Maximum Left Bank Angle with Roll Knob if applicable ATT ALT Maximum Right Bank Angle with Roll Knob if applicable HDG ALT ALT HOLD mode does it...

Page 226: ...formed Salt Fog Test 14 0 Equipment identified as Category X no test performed Magnetic Effect 15 0 Equipment is Category Z Power Input 16 0 Equipment tested to Category B Voltage Spike 17 0 Equipment...

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