Efd1000 Pfd and Efd1000 Mfd - Installation Manual

7/27/2019 Efd1000 Pfd and Efd1000 Mfd - Installation Manual

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EFD1000 Installation Manu

DOCUMENT # A-01-126-00 PAGE 1-202 Revision Copyright 2008 Aspen Avionics Inc.

EFD1000Installation Manual

Includes Instructions for Continued Airworthiness

Aspen Document #A-01-126-00 Revision C


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DOCUMENT REVISIONSRevision Description of Change

A INITIAL RELEASE

B INITIAL RELEASE FAA APPROVED

C Corrected Figure 9.17 STEC Autopilot Interface to add P1-12 CRS Datum Lo connection. Updated

Section 5.2.4 to add SL-30 limitations. Updated Figure 8.5 ACU Flight Director definitions. Added Table

10.1 EFD1000 Configuration Chart for inclusion in ICAs. Moved ICAs from Section 12 to Appendix D.

Updated Appendix D ICAs. Moved Section 13 Operation to Section 12. Moved Appendix D

Environmental Qualification Forms to Section 13.

Prepared By: TLM Release AuthorizationReviewed By: PDL

Original signatureson file. See ECO for

release date and

dispositions. Release Date: 3/28/08

Release Initials: DTSUsage Authorization / Master Control Number:

Release Signature David T.Stewart


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The conditions and tests required for TSO approval of the EFD1000 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 system under the EFD1000 AML STC for use as a primary electronic flight display

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 EFD1000 AML. Installation of the EFD1000 into part 23 Class I or II

aircraft not included in the EFD1000 AML, into any part 23 class III or IV aircraft, or into any part

25, 27, or 29 aircraft requires separate airworthiness approval.


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THIS PAGE IS INTENTIONALLY LEFT BLANK


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Table of Contents1 INTRODUCTION ................................................................................................................. 11

1.1 PART NUMBERS......................................................................................................... 111.2 INSTALLATION KIT CONTENTS.......................................................................................111.3 ACCESSORIES REQUIRED BUT NOT SUPPLIED ......................................................................121.4 OPTIONAL ACCESSORIES NOT SUPPLIED ...........................................................................131.5 SPECIAL TOOLS REQUIRED............................................................................................131.6 VENDOR INFORMATION ...............................................................................................131.7 WARRANTY REGISTRATION...........................................................................................141.8 REGULATORY COMPLIANCE ..........................................................................................14

1.8.1 ... Technical Standard Order .......................................................................... 141.8.2 ... Software Certification ................................................................................ 141.8.3 ... Environmental Compliance ........................................................................ 14

2 EQUIPMENT SPECIFICATIONS AND LIMITATIONS...................................................................152.1 PRIMARY FLIGHT DISPLAY (PFD)&CONFIGURATION MODULE (CM) ........................................ 15

2.1.1 ... General Specifications ............................................................................... 152.1.2 ... Operational Specifications: ........................................................................ 152.1.3 ... I/O Specifications:..................................................................................... 152.1.4 ... Certification Specifications: ....................................................................... 152.1.5 ... Outline Drawing: ....................................................................................... 16

2.2 REMOTE SENSOR UNIT (RSM):......................................................................................172.2.1 ... General Specifications ............................................................................... 172.2.2 ... Operational Specifications: ........................................................................ 172.2.3

...I/O Specifications:..................................................................................... 17

2.2.4 ... Certification Specifications: ....................................................................... 172.2.5 ... Outline Drawing: ....................................................................................... 18

2.3 ANALOG CONVERTER UNIT (ACU): ................................................................................192.3.1 ... General Specifications ............................................................................... 192.3.2 ... Operational Specifications: ........................................................................ 192.3.3 ... I/O Specifications:..................................................................................... 192.3.4 ... Certification Specifications: ....................................................................... 192.3.5 ... Outline Drawing: ....................................................................................... 20

3 SYSTEM DESCRIPTION......................................................................................................... 213.1 PRIMARY FLIGHT DISPLAY (PFD)....................................................................................213.2 REMOTE SENSOR MODULE (RSM) ..................................................................................223.3 CONFIGURATION MODULE ...........................................................................................233.4 ANALOG CONVERTER UNIT (ACU) .................................................................................233.5 SYSTEM ARCHITECTURE...............................................................................................24

4 SUPPORTED INSTALLED CONFIGURATIONS ..........................................................................254.1 PILOT CONFIGURATIONS..............................................................................................254.2 SIMPLE PRO CONFIGURATION........................................................................................26


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4.3 PRO CONFIGURATIONS WITH AUTOPILOT..........................................................................274.4 PRO CONFIGURATION WITH AUTOPILOT AND DIGITAL/ANALOG VLOC..................................... 284.5 PRO CONFIGURATION WITH AUTOPILOT AND DUAL ANALOG VLOC......................................... 29

5 PRE MODIFICATION PLANNING............................................................................................ 315.1 PRE MODIFICATION CHECKLIST .....................................................................................315.2 REQUIREMENTS AND LIMITATIONS ..................................................................................32

5.2.1 ... Standby Attitude Positioning...................................................................... 345.2.2 ... Standby Airspeed and Altimeter Positioning ............................................... 355.2.3 ... Directional Gyro/ HSI................................................................................. 355.2.4 ... Back Up Nav Indicator ............................................................................... 365.2.5 ... GPS Annunciators ...................................................................................... 375.2.6 ... Power Requirements.................................................................................. 37

5.3 PART135IFROPERATIONS........................................................................................375.4 SETTING V-SPEEDTEXTUAL MARKERS ...........................................................................375.5 OPTIONAL INTERFACES................................................................................................38

5.5.1 ... Autopilot .................................................................................................. 385.5.2 ... GPSS ........................................................................................................ 385.5.3 ... GPS/ NAV Switching .................................................................................. 395.5.4 ... Sonalert .................................................................................................... 395.5.5 ... Heading Output ........................................................................................ 395.5.6 ... Second ACU .............................................................................................. 39

6 MECHANICAL INSTALLATION ..............................................................................................416.1 UNPACKING AND INSPECTING EQUIPMENT.........................................................................416.2 EQUIPMENT LOCATION DOCUMENTATION.........................................................................416.3 LOG BOOK ENTRY ..................................................................................................... 416.4 WEIGHT AND BALANCE................................................................................................416.5 INSTALLATION LIMITATIONS .........................................................................................426.6 EQUIPMENT BONDING .................................................................................................426.7 COOLING ................................................................................................................ 436.8 PFDINSTALLATION.................................................................................................... 43

6.8.1 ... PFD Mounting Location.............................................................................. 436.8.2 ... Mounting Bracket Installation .................................................................... 446.8.3 ... PFD Bonding Strap..................................................................................... 446.8.4

...

Pitot and Static Connections ...................................................................... 476.8.5 ... Quick Connector Installation...................................................................... 476.8.6 ... Leak Check Requirements.......................................................................... 48

6.9 RSMINSTALLATION...................................................................................................496.9.1 ... Proposed RSM Location Check ................................................................... 506.9.2 ... Pressurized Aircraft ................................................................................... 516.9.3 ... Second RSM Placement (MFD) .................................................................... 516.9.4 ... RSM Mounting Angles................................................................................ 516.9.5 ... RSM Doubler ............................................................................................. 53


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6.9.6 ... RSM Doubler Fabrication ........................................................................... 546.9.7 ... RSM Installation ........................................................................................ 576.9.8 ... RSM moun ting on Composite or Fabric ...................................................... 576.9.9 ... RSM Shim Fabrication (if necessary) ........................................................... 58

6.10 ACUINSTALLATION...................................................................................................606.10.1. ACU Mounting........................................................................................... 60

6.11 CONFIGURATION MODULE INSTALLATION .........................................................................627 ELECTRICAL INSTALLATION ................................................................................................ 63

7.1 ELECTRICAL LOAD ANALYSIS.........................................................................................637.2 ELECTRICAL INSTALLATION...........................................................................................63

7.2.1 ... HIRF/Lightning Requirements .................................................................... 647.2.2 ... PFD to GPS/VLOC/ACU W iring.................................................................... 657.2.3 ... RSM Wiring ............................................................................................... 667.2.4 ... Configuration Module Wiring ..................................................................... 677.2.5

...ACU Wiring ............................................................................................... 68

7.2.6 ... Back Up NAV Indicator Wiring .................................................................... 687.2.7 ... Autopilot Wiring ........................................................................................ 68

8 ELECTRICAL CONNECTIONS ................................................................................................ 698.1 PFDELECTRICAL SPECIFICATIONS ..................................................................................69

8.1.1 ... Power Input .............................................................................................. 698.1.2 ... Tone (Sonalert) Output .............................................................................. 698.1.3 ... RS-232 GPS Input...................................................................................... 698.1.4 ... ARINC 429 GPS Inputs ............................................................................... 718.1.5

...

ARINC 429 VLOC Input .............................................................................. 728.1.6 ... ARINC 429 GPS Output .............................................................................. 728.2 ACUELECTRICAL SPECIFICATIONS..................................................................................72

8.2.1 ... Power Input .............................................................................................. 728.2.2 ... VLOC Receiver........................................................................................... 738.2.3 ... GPS Receiver ............................................................................................. 738.2.4 ... Autopilot .................................................................................................. 758.2.5 ... ARINC 429 GPS Output .............................................................................. 77

8.3 PFDPIN OUT........................................................................................................... 788.4 RSMPIN OUT .......................................................................................................... 798.5 CONFIGURATION MODULE PIN OUT ................................................................................808.6 ACUPIN OUT .......................................................................................................... 80

9 INSTALLATION WIRING DIAGRAMS ......................................................................................8310 CONFIGURATION AND EQUIPMENT CHECKOUT..................................................................111

10.1 TEST EQUIPMENT.....................................................................................................11110.2 WIRING VERIFICATION...............................................................................................11110.3 BONDING CHECK FAR23.867(B).............................................................................11210.4 SYSTEM CONFIGURATION...........................................................................................113


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10.4.1. Main Menu Access................................................................................... 113 10.4.2. Menu Navigation ..................................................................................... 113 10.4.3. Edit Mode ............................................................................................... 113 10.4.4. Main Menu Configuration ........................................................................ 113 10.4.5. INSTALLATION MENU UNIT CONFIGURATION.......................................... 118

10.5 RSMCALIBRATION ..................................................................................................13310.5.1. Calibration Overview ............................................................................... 133 10.5.2. RSM Calibration Procedure....................................................................... 135 10.5.3. Heading Offset Adjustment ..................................................................... 137 10.5.4. Heading Accuracy Test ............................................................................ 138 10.5.5. Heading Interference Test ....................................................................... 138

10.6 GROUND TEST PROCEDURE ........................................................................................13910.6.1. Indicated Airspeed Display ...................................................................... 139 10.6.2. Altitude Display ...................................................................................... 139 10.6.3. System Leak Test .................................................................................... 139 10.6.4. Outside Air Tem perature ......................................................................... 140 10.6.5. AHRS Sensor Test.................................................................................... 140 10.6.6. GPS Sensor Test ...................................................................................... 140 10.6.7. NAV Receiver Sensor Test ........................................................................ 141 10.6.8. Backup Navigation Indicator .................................................................... 141 10.6.9. Autopilot Sensor Test .............................................................................. 141 10.6.10 Flight Director Test ......................................................................... 142 10.6.11 Sonalert Test................................................................................... 143 10.6.12 Ancillary Equipment Heading Check................................................. 143 10.6.13 TAPES Configuration Check ............................................................. 143 10.6.14 EMI Test.......................................................................................... 143

11 POST INSTALLATION FLIGHT CHECK..................................................................................14511.1 BASIC ADIFLIGHT CHECKS ........................................................................................14511.2 BASIC HSI/DGFLIGHT CHECKS ..................................................................................14511.3 ILSFLIGHT CHECKS (IF NO AUTOPILOT, OTHERWISE JUMP TO SECTION 11.4)............................ 14511.4 AUTOPILOT FLIGHT CHECKS (IF INSTALLED).....................................................................146

12 OPERATION...................................................................................................................... 14912.1 PILOT CONTROLS ....................................................................................................149

12.1.1.

Overview................................................................................................. 149 12.1.2. Power Control ......................................................................................... 150 12.1.3. Display and Control Layout...................................................................... 151 12.1.4. Control Knobs......................................................................................... 152

12.2 SETTING FLIGHT INSTRUMENTS....................................................................................15212.3 KNOB SYNC FUNCTION .............................................................................................15312.4 HOT KEY OPERATION ...............................................................................................15412.5 CDI AND BEARING POINTER SOURCE SELECTION ..............................................................15612.6 BACK LIGHT CONTROL..............................................................................................157


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12.7 MAP RANGE CONTROL..............................................................................................15812.8 DISPLAY REVERSION CONTROL AND ABNORMAL SHUTDOWN................................................ 15812.9 PRIMARY FLIGHT INSTRUMENTS ...................................................................................158

12.9.1. Attitude Indicator .................................................................................... 158 12.9.2. Airspeed Indicator................................................................................... 160 12.9.3. Altimeter ................................................................................................ 162 12.9.4. Vertical Speed Indicator (VSI) ................................................................... 163 12.9.5. Rate of Turn Indicator ............................................................................. 164 12.9.6. Data Bar (TAS, GS, OAT, Winds, Barometric pressure Set) .......................... 164 12.9.7. Horizontal Situation Indicator .................................................................. 164 12.9.8. Bearing Pointers ...................................................................................... 168

12.10 SITUATIONAL AWARENESS MAP DISPLAY ........................................................................16812.11 AUTOPILOT INTEGRATION ..........................................................................................17112.12 MAIN MENU........................................................................................................... 175

12.12.1 Menu Controls ................................................................................ 175 12.12.2 Menu Options ................................................................................. 176

13 ENVIRONMENTAL QUALIFICATION FORMS .........................................................................179

APPENDIX A ..................................................................................................................... 183TROUBLESHOOTING.................................................................................................. 184

APPENDIX B...................................................................................................................... 187INSTALLATION FINAL CHECK SHEET .............................................................................. 188

APPENDIX C ..................................................................................................................... 191OPERATOR CONFIGURATION CHECKLIST......................................................................... 192

APPENDIX D..................................................................................................................... 193INSTRUCTIONSFOR CONTINUED AIRWORTHINESS.............................................................. 193


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1 IntroductionThis Installation Manual is FAA Approved and contains detailed installation instructions for

installing the EFD1000 System into specific aircraft as listed in the EFD1000 AML-STC. There are

required FARs that must be complied with and followed to insure an airworthy installation.Section 5 Pre Modification Planning will guide you through these requirements.

1.1Part NumbersThe EFD1000 Electronic Flight Display System consists of the following components:

A-05-110-00 EFD1000, TSO

A-05-111-00 REMOTE SENSOR MODULE (RSM)

A-05-112-00 ANALOG CONVERTER UNIT (ACU) optional

A-05-113-00 CONFIGURATION MODULE, PFD PILOT

OR A-05-114-00 CONFIGURATION MODULE, PFD PRO

A-08-130-00 INSTALLATION KIT, EFD1000

A-08-131-00 INSTALLATION KIT, RSM

A-08-132-00 INSTALLATION KIT, ACU - optional

1.2 Installation Kit ContentsA-08-130-00 EFD1000 Install Kit

Aspen P/N Description Manufacturers P/NA-08-125-00-A PFD Mounting Bracket Aspen

A-06-564-00 44 Pin HD D-Sub connector with

contacts

Positronics P/N DD44F10000

A-06-573-00 EMI Metal Back shell Positronics P/N D25000GE0A-06-505-00 Pitot Quick Connector Aspen

A-06-507-00 Static Quick Connector Aspen

A-08-144-00-A Configuration Module Connector

Assembly with pigtail

Aspen


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A-08-131-00 RSM Install Kit

Aspen P/N Description Manufacturers P/NA-06-566-00 RSM Circular Connector Hirose P/N SR30-10JF-7S(71)

A-06-567-00 8-32 Stainless Steel screws (4) MS27039C08-17

A-06-568-00 Stainless Steel locking nuts (4) MS21044C08

A-06-569-00 Stainless Steel washers (4) Cad Plated NAS1149EN0832P

A-08-132-00 ACU Install Kit

Aspen P/N Description Manufacturers P/NA-06-570-00 15 pin D-Sub connector AMP P/N 205163-1

A-06-571-00 25 pin D-Sub connector AMP P/N 205165-1

A-06-572-00 37 pin D-Sub connector AMP P/N 205167-1

A-06-408-00 DB15 pin EMI Back shell NorComp 970-015-030R121

A-06-409-00 DB25 EMI Back shell NorComp 970-025-030R121

A-06-410-00 DB37 EMI Back shell NorComp 970-037-030R121

A-06-574-00 Crimp Sockets (77) Positronics P/N FC6020D

1.3Accessories Required but Not SuppliedDescription Manufacturers P/N

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

Over Braid tinned copper light

Over Braid tinned copper med

Alpha Wire P/N 2142 (1/4), P/N 2146 (1/2)

Daburn P/N 2350-X, X=diameter (i.e., 1/2)

Circuit Breaker pull to open (PFD) 7.5 amp MS 26574-7.5 or equivalent

Circuit Breaker (ACU) 2 amp (1 for each ACU) MS26574-2 or equivalent

PFD to GPS/ACU double shielded cable M27500-22TG2V64 or equivalent

Hose Clamps (8 req) Aero Seal 6604 or equiv.

7 conductor shielded cable (PFD to RSM) M27500-A24SD7T23/ M27500-22TG7T14 or

equivalent

Single stranded 24, 22, 20 AWG MIL-W-22759/16 or equiv.

Shielded Wire 22 AWG MIL-C-27500 or equiv.

PFD Mounting Screws #6-32 MS24693-S30 or equiv.

PFD and ACU Mounting Lock Nuts #6-32 MS21044N06 or equiv.

PFD and ACU Mounting Washers NAS1149FN632P or equiv.

ACU mounting Screw #6-32 MS24694-X or equiv.

Miscellaneous screws, washers, cable ties,

etc.

Installer supplied


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1.4Optional Accessories Not SuppliedDescription Manufacturer

Sonalert (continuous type) Mallory PK or PS series or equivalent

EFIS Master switch rated for 7.5 amps cont. MS35059-22 or equivalent

Circuit Breaker/Switch 7.5amp (PFD) Potter Brumfield W31M-7.5 or equivalent

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.

RSM sealant pressure vessel mounting MIL-PRF-81733D, PS 870B-1/2 or equiv.

1.5Special Tools RequiredD-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

1.6Vendor InformationAspen Avionics Inc. Alpha Wire Company Over Braid

5001 Indian School Road NE 711 Liderwood Ave.

Albuquerque, NM 87110 Elizabeth, NJ 07207

(505) 856-5034 (908) 925-8000

[email protected] [email protected]

A.E. Petsche Co. Double Shielded & RSM Cable Daburn Electronics & Cable Corp Over Braid

2112 West Division St. 224 Pegasus Ave.

Arlington, TX 76012-3693 Northvale, NJ 07647

(817) 461-9473 (201) 768-5400

[email protected] [email protected]

Positronic Industries Inc. - Crimpers, Connectors

423 N. Campbell Ave.

Springfield, MO 65801

(417) 866-2322

[email protected]
mailto:[email protected]:[email protected]:[email protected]:[email protected]:[email protected]:[email protected]:[email protected]:[email protected]


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1.7Warranty RegistrationRegistration of LRU part numbers and serial numbers must be recorded on the dealer portal of

the Aspen Avionics website atwww.aspenavionics.com/dealerramp. Activating the warranty on

the EFD1000 system is just one important aspect of providing a satisfying installation

experience for our customers.

1.8Regulatory Compliance1.8.1 Technical Standard Order

All components of the EFD1000 system are produced under Technical Standard Order

Authorization (TSOA).

1.8.2 Software CertificationAll software components of the EFD1000 system are developed to RTCA DO-178B

criticality Level C with the exception of the GPS receiver software, which is for

emergency use only.

1.8.3 Environmental ComplianceAll system components meet the categories of RTCA/DO-160E according to the

environmental qualification form in Section 13.
http://www.aspenavionics.com/http://www.aspenavionics.com/


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2 Equipment Specifications and Limitations2.1Primary Flight Display (PFD) & Configuration Module (CM)

2.1.1 General SpecificationsPart Number.............................. A-05-110-00

Width ........................................ 3.50 in. (Measured at Bezel)

Height ....................................... 7.00 in. (Measured at Bezel)

Can Depth ................................. 4.15 in. (Rear of Bezel to Rear of Can)

Overall Depth ............................ 6.35 in. (Knob to Rear Pressure Fitting)

Weight....................................... 2.9 lbs 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 LEDRotary Knobs............................. Optical Encoder with Momentary Push

Dimming ................................... Manual & Automatic (Front Bezel Mounted Sensor)

2.1.2 Operational Specifications:Operating Temp: ...................... -20C to +55C

Storage Temp: .......................... -55C to +85C

Max Operating Altitude.............. 35,000 ft Unpressurised/ 55,000 ft Pressurized

Cooling ..................................... Integral Fan

Max Humidity ............................ 95% at 50CInput Voltage............................. +8 to +32 Volts DC

Nominal Current ........................ 2.4/4.8 Amps (28v/14v)

2.1.3 I/O Specifications:ARINC 429 Inputs ...................... 5 Low 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:

TSO-C2d .................................. Airspeed Instruments

TSO-C3d .................................. Turn and Slip Instrument

TSO-C4c .................................. Bank and Pitch Instruments


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TSO-C6d .................................. Direction Instrument Magnetic (Gyroscopically

Stabilized)

TSO-C8d .................................. Vertical Velocity Instrument (Rate-of-Climb)

TSO-C10b ................................ Altitude Pressure Activated Sensitive Type

TSO-C106 ................................ Air Data Computer

TSOC113 ................................ 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 - PFD Outline Drawing (inches)


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2.2Remote Sensor Unit (RSM):2.2.1 General Specifications

Part Number.............................. A-05-111-00

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

2.2.2 Operational Specifications:Operating Temp ....................... -55C to +70C

Storage Temp ........................... -55C to +85C

Max Operating Altitude.............. 55,000 ft Unpressurized

Cooling ..................................... None RequiredMax Humidity ............................ 95% at 50C

Input Voltage............................. Provided by PFD

Nominal Current ........................ Included in PFD Current

2.2.3 I/O Specifications:Magnetometer ........................... Proprietary Digital

OAT........................................... Proprietary Digital

GPS ........................................... Proprietary Digital

2.2.4 Certification Specifications:The RSM is certified as a component of the EFD1000 system

Environmental:



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24 inches

4.36

0.99

2.64

1.750

1.625

4 X 0.194

CABLE FEEDTHRU

0.75

Figure 2.2 - RSM Outline Drawing (inches)


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2.3Analog Converter Unit (ACU):2.3.1 General Specifications

Part Number.............................. A-05-112-00

Width ........................................ 5.75 in. including mounting flanges

Height ....................................... 1.60 in.

Length....................................... 4.30 in.

Weight....................................... 0.8 lbs

2.3.2 Operational Specifications:Operating Temp: ...................... -20C to +55C

Storage Temp: .......................... -55C to +85C

Max Operating Altitude.............. 35,000 ft Unpressurized/ 55,000 ft Pressurized

Cooling ..................................... none requiredMax Humidity ............................ 95% at 50C

Input Voltage............................. +11 to +32 Vdc

Nominal Current ........................ 0.5/1.0 Amps (28v/14v)

2.3.3 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 output port

Autopilot Interface..................... 1 Analog port

2.3.4 Certification Specifications:The ACU is certified as a component of the EFD1000 system

Environmental:



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4.72

4.30

Figure 2.3 - ACU Outline Drawing (inches)


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3 System DescriptionThe EFD1000 system is comprised of the Primary Flight Display (PFD), Remote Sensor Module

(RSM), Configuration Module (CM) and optional Analog Converter Unit (ACU). The flight deck

display is designed specifically for general aviation aircraft.

The EFD1000 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, pilot-selectable indices (bugs), and annunciations to increase situational awareness

and enhance flight safety.

Two configurations, Pilot and Pro are available, which support different software feature sets.

3.1Primary Flight Display (PFD)The PFD is a digital system 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 unit consists of 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 PFD mounts to the front surface of most instrument panels. The electronics module and

cooling fins on the back are sized to fit into existing mechanical attitude and heading

indicator instrument panel holes.

The mechanical design allows the instrument to be installed in the place of the mechanical

gyroscopic attitude and heading indicators, without interfering with the surrounding

instruments. The installation will require minimal, if any, mechanical modifications to most

general aviation aircraft instrument panels.

The PFD contains a microSD card port and reader at the bottom of the display bezel. In the

future, software updates and system upgrades will be loaded via this port.


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Figure 3.1 - PFD

The PFD is a pure digital system and natively 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 non-ARINC avionics (i.e., older VLOC radios and

autopilots) the ACU is required to convert these signals into ARINC 429 for the PFD.

3.2Remote Sensor Module (RSM)The RSM is required and connects directly to the PFD. It physically resembles a traditional GPS

antenna and follows the industry standard mounting hole pattern.

However, internally it is substantially more complex in that it contains all of the sensors thatmust be remotely located from the PFD display unit.

The RSM is powered by the PFD through a shielded wire harness and contains the following

sub-systems:

Outside Air Temperature (OAT) sensor

Emergency backup GPS engine

Heading flux sensors


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The RSM is mounted externally in a magnetically quite environment to provide acceptable

reception for the integral GPS antenna and to minimize magnetic disturbances that would

impact accurate magnetometer operation.

3.3Configuration ModuleThe Configuration Module contains an EEPROM device which retains system configuration and

calibration data. The Configuration Module connects to the PFD through a short fabricated

harness and is fastened to the main wiring bundle of the PFD.

The Configuration Module provides two primary functions:

Retains aircraft specific configuration, calibration data and user settings, allowing the

PFD to be swapped for service purposes without re-entering or re-calibrating the

installation.

Contains a license key that configures the PFD software to either the Pilot or Pro

feature set.

3.4Analog Converter Unit (ACU)For the Pro model only, 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 ARINC 429 buses supported by the PFD. Control parameters, suchas desired heading, 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

If digital radios (i.e., Garmin 4XX/5XX series radios) are equipped in the aircraft, and no other

aircraft interfaces are desired, the ACU is not required.


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3.5System ArchitectureThe system architecture in Figure 3.2 shows the relationships of the PFD, RSM, Configuration

Module and ACU.

Figure 3.2 - EFD1000 System Architecture

Note: Radar Altimeter DH will be functional infuture software release


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4 Supported Installed ConfigurationsThe following diagrams show the different options for integrating 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.

4.1Pilot ConfigurationsThe 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


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4.2Simple Pro ConfigurationThe following configuration shows a simple Pro installation, without an advanced autopilot

and flight director. No ACU is required for this installation. This installation would be usedwhen 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.

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 will be wired as

shown in Figure 4.3 minus the heading and course datum, flag, ILS Energize, and glide slope

signals.

Figure 4.2 - Simple Pro Configurations


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4.3Pro Configurations with AutopilotThe following configurations show Pro installations with autopilot integration, but without

analog VLOC interfaces. A backup Navigation indicator is required in installations that do not

have an integral CDI display on the GPS receiver or VLOC receiver. There must be one

navigation indicator available to the pilot in the event of a PFD or ACU failure.

Figure 4.3 Pro Configurations with Autopilot


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4.4Pro Configuration with Autopilot and Digital/Analog VLOCThe 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 installations that do not have an integral CDI display on the GPS

receiver or VLOC receiver. There must be one navigation indicator available to the pilot in the

event of a PFD or ACU failure.

Figure 4.4 - Pro Configuration with AP and VLOC


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4.5Pro Configuration with Autopilot and Dual Analog VLOCThe following configuration shows a Pro installation with autopilot integration and dual analog

VLOC interfaces. Two ACUs are required for this installation. A backup Navigation indicator

is required in installations that do not have an integral CDI display on the GPS receiver or

VLOC receiver. There must be one navigation indicator available to the pilot in the event of a

PFD or ACU failure.

Figure 4.5 - Pro Configuration with AP and Dual VLOC


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5 Pre Modification PlanningThis section contains requirements that must be considered before installing the EFD1000. This

section will guide you through the requirements to ensure FAR compliance; including required

equipment, required secondary equipment, secondary equipment relocation and placement, and

optional equipment.

5.1Pre Modification ChecklistComplete Table 5.1 to insure that the aircraft to be modified is a candidate for installation of

the EFD1000 system using this AML-STC. It is required to have a PASS or NA for all rows in

order to use this AML-STC as the certification basis for the EFD1000 installation. NA means

Not Applicable because no interface will be made to that device. Only items 5, 8, 9, 10, 11 &

12 below may use NA in the PASS box.

ITEM Criteria PASS1 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 pilots field of view? (see Figure 5.2)

4 Do the standby instruments meet the requirements of Figure 5.1?

5 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 pilots field of view? (see Figure 5.2)

6 Is there an acceptable location to mount the RSM? (see Section 6.9)

7 Is there a location to mount a PFD circuit breaker that will be accessible

to the pilot while seated?

8 If mounting an optional PFD Master switch is there a mounting location

accessible to the pilot while seated? NA if not installed.

9 If installing an optional ACU or ACUs is there a location to mount a

circuit breaker or breakers that is accessible to the pilot while seated? -

NA if no ACU installed.

10 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.

11 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.

12 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.

Table 5.1 Pre Modification Checklist


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5.2Requirements and LimitationsFAR 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.

Part 23 aircraft that have no existing attitude Indicator must install a standby attitude

indicator along with the PFD as required by FAR 23.1311(a)(5) even though the aircraft

operates under VFR rules as per 91.205(b). Any deviation from this regulation requires

separate FAA approval.

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.

Pneumatic Standby InstrumentsAircraft with existing pneumatic attitude, altitude, and airspeed instruments may relocate

them as necessary as described in Section 5.2.1. The standby airspeed and altimeter should

be connected to an independent pitot and static line (independent from PFD) whenever

available.

Electric Standby InstrumentsAircraft 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. [Note: The EFD1000 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.

Removal of pneumatic standby instruments and installation of electric standby instruments is

not authorized by this STC. Separate installation approval would be required.

The installation of dual independent electrical systems or a standby (emergency) battery is not

authorized by this STC. Separate installation approval would be required.


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Figure 5.1 Standby Instrument Power Requirements


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5.2.1 Standby Attitude PositioningThe Attitude indicator must be relocated to a position that meets FAR 23.1321(a). The

requirements are 35 degrees from the pilots center line horizontally ( 21 inches

from centerline as defined by AC23-11) to an area just below the basic T configuration

to the glare shield vertically (see Figure 5.2 below). Standby instruments should be

mounted as close as practical to the primary instruments, but in no case outside 35.

NOTE: The existing instrument holes for the Turn and Bank and the Vertical Speedindicator meet this requirement.

Figure 5.2 Standby Instrument Placement

Also note that some attitude indicators are the primary pitch and roll reference for the

autopilot and must remain in the aircraft (i.e., KI-256). For rate based autopilots the

Turn and Bank Indicator will need to remain in the aircraft, and may be relocated to the

co-pilot 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.


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5.2.2 Standby Airspeed and Altimeter PositioningIn 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 will be required to LOCK the airspeed and

altitude tape in the PFD to ON via the installation menu. If the airspeed indicator is

not in position (AS) and the altimeter in position (AL) of Figure 5.3 below then the

TAPES must be LOCKED ON so that the pilot cannot de-clutter them from the display

during flight.

WARNING: Failure to adhere to the specific instrument layout requirements andEFD1000 configuration requirements will violate the STC.

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.

Figure 5.3 Basic T configuration

5.2.3 Directional Gyro/ HSIThe 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 operators discretion.

If another device is bootstrapped off of the compass then it will need to be

determined whether low speed ARINC 429 heading is accepted by this device and


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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 IndicatorFor certification reasons a backup navigation indicator is required in any installation

where the EFD1000 is the only display of navigation information in the cockpit. 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

Thus, for example, an installation that includes a panel mount GPS with an integral LCD

display that includes a 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.

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.

WARNING: Failure to provide a backup Nav indicator when required will violate theSTC.

Garmin SL-30 InterfaceThe Garmin SL-30 when connected to the EFD1000 system through the composite

video input requires that the SL-30 be configured for Converter in the set-up mode.

When you configure the SL-30 for Converter it disables the OBS input to the radio

thereby disabling the Left/Right/To/From analog outputs and it also disables VOR

Monitor mode and Back Course mode. Therefore the SL-30 cannot be used to directly

drive a backup HSI or Nav indicator without an internal converter. If you desire to

connect the SL-30 to the EFD1000 you must do one of the following: use one of thebackup Nav indicators in Figure 9.24, use a KN-72 VLOC Converter between the SL-30

composite out and Nav indicator analog in, or use a backup Nav indicator connected to

another navigation receiver in the aircraft.


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5.2.5 GPS AnnunciatorsThe 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 GPS):

MSG

WPT

TERM

APPR

INTEG

5.2.6 Power RequirementsAn electrical load analysis must be performed to ensure the installed EFD1000

components do not exceed the current capacity of the aircrafts charging system (see

Section 7.1).

An EFIS MASTER switch or switch breaker to the PFD may be installed if the customer

desires to isolate the PFD during engine starts. The PFD breaker must be a pull type

breaker and should be connected to the switched battery bus. A location will need to

be found for the ACU breaker(s) and they should be connected to the avionics bus

(switched battery bus if no avionics bus).

5.3PART 135 IFR OperationsThe 30 minute back-up battery in the PFD is not approved for use as a power source to meet

the electrical power source requirement for single engine Part 135 IFR operations under 14

CFR 135.163.

5.4Setting V-SPEED Textual MarkersHave 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.


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5.5Optional Interfaces5.5.1 Autopilot

The EFD1000 Pro with ACU emulates a KI-525A HSI by providing HDG Datum, CRS

Datum, and navigation L/R outputs to a connected autopilot. Any autopilot compatible

with the KI-525 HSI is compatible with the EFD1000 System.

Similarly, the EFD1000 Pro with ACU emulates the KI-254/KI-256 flight director

indicator by accepting FD signals compatible with these indicators and displaying them

on the EFD. Any autopilots that output a flight director signal that is compatible with

the KI-254/256 is compatible with the EFD1000 System.

Section 9 of this document shows interconnect diagrams for common autopilots that

are KI-525A and KI 254/256 compatible, and therefore also 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

manufacturers installation data for any jumpers or hardware that needs 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 autopilots 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.

5.5.2 GPSSGPS 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. RS-232 interfaces do not provide label 121;

therefore, for RS-232 GPS systems GPSS functionality is not provided.


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5.5.3 GPS/ NAV SwitchingExisting 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.

Any 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.

5.5.4 SonalertA Sonalert may be installed to provide an audio tone to the pilot whenever an altitude

or minimums advisory is generated by the system.

5.5.5 Heading OutputIt may be necessary to use a digital bus, in lieu of a synchro output, to supply an

external device such as a 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.

Figure 5.4 Low Speed ARINC 429 Heading

(Note- the Bendix/King KTA810/910 and KMH820/920 only accept High Speed A429

and therefore are not compatible with this output). Contact Aspen Avionics product

support for suggestions on using an ARINC 429 low to high speed converter.

5.5.6 Second ACUA second ACU is required when two (2) analog VLOC receivers are installed.


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THIS PAGE IS INTENTINALLY LEFT BLANK


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6 Mechanical InstallationThe EFD1000 installation will require mechanical modifications to the aircraft. The PFD, RSM, and

Configuration Module will be installed in all installations, while one (1) or two (2) ACU(s) may be

required in others. Most installations will require removing and relocating existing flightinstruments to alternate locations in the instrument panel to be used as standby instrumentation.

6.1Unpacking and Inspecting EquipmentPerform a visual inspection of all equipment for evidence of damage that might have occurred

during shipment. If a damage claim is to be filed save all shipping boxes and packing

material to substantiate your claim.

6.2Equipment Location DocumentationIt is required by the AML-STC that the PFD, RSM, CM, and ACU mounting locations be

recorded on Figure D1 of Appendix D. It is also required that an accurate description of wire

and cable routing be noted on the figure. 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.

6.3Log Book EntryMake a log book entry at the completion of the installation indicating that the aircraft has

been modified in accordance with the EFD1000 AML-STC.

6.4Weight and BalanceUsing 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. Also account for

equipment removed during the modification process.

Component Weight (Ibs)EFD1000 including bracket 2.9

RSM Remote Sensor Module 0.2

ACU Analog Converter Unit 0.8

Configuration Module 0.1

Table 6.1 Component Weights


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6.5 Installation LimitationsThe following mounting limitations must not be exceeded during the installation of the PFD

and RSM:

The PFD must be mounted within 8 of perpendicular to the aircraft waterline.

The PFD must be mounted within 0.00.1 of the zero degree roll wings level axis.

The RSM must be mounted within 4 to the longitudinal axis of the aircraft (see

Figure 6.8)

The RSM must be mounted within 10 to the zero degree roll wings level axis (see

Figure 6.10)

The RSM must be mounted within 10 to the zero pitch axis waterline of the

airframe (see Figure 6.9). In no case may the PFD to RSM difference be greater than

18 (8 of PFD tilt plus 10 of RSM tilt).

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.

RSM must not be mounted to a NO ZONE as pictured in Figure 6.7.

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 vesselpenetrations required to accommodate RSM mounting is required prior to the

installation of the remaining EFD1000 system components under the EFD1000 AML-

STC.

Mounting the RSM to a composite or fabric skinned aircraft is beyond the scope of this

STC. On composite and fabric skin aircraft, separate FAA approval of the RSM

mounting is required prior to the installation of the remaining EFD1000 system

components under the EFD1000 AML-STC.

6.6Equipment BondingAll metal components must be grounded and bonded to the airframe with less than 3

milliohms resistance in accordance with FAR 23.867(a).

The PFD uses an installer fabricated braided bonding strap to ensure proper bonding to the

panel. The bond strap is attached with supplied screw (3/8th inch length) to back of PFD at

location just below and left of static port. The other end of strap is attached to PFD mounting

bracket screw at backside of panel.


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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. 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.

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.

6.7CoolingThe PFD has an integral fan mounted to the lower backside of the unit. The fan must not be

covered as to restrict airflow through the unit. The RSM, ACU, and Configuration Module have

no specific cooling requirements.

6.8PFD InstallationMechanical installation of the PFD requires installing the included mounting bracket,

connecting a braided bonding strap between the PFD and panel, and installing pitot and static

connections to the two keyed quick release pressure fittings.

6.8.1 PFD Mounting LocationThe PFD must be mounted in the center position of 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.

NOTE: Modification to the existing instrument panel is not authorizedunder this STC. Any modification must be approved separately.

PFD

PFD Mounting Location

Figure 6.1 - PFD Mounting Location


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6.8.2 Mounting Bracket InstallationThe pre-drilled holes in the mounting bracket (see Figure 6.4) 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 PFD 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.

The PFD 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 6.3.

3) Use an inclinometer on the top of the PFD 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 0.00.1 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 6.2).

6) Install remaining PFD mounting bracket screws and nuts.

7) Tighten all six (6) mounting screws and nuts to 12 in-lbs anchoring the bracket to

the panel.

Aircraft with tilted instrument panels of 8 or less can install the PFD flat against the

panel. The tilt will later be removed electronically in the system configuration using

the Pitch Attitude Trim adjustment.

6.8.3 PFD Bonding StrapAn 8 or shorter braided bonding strap is required between the screw (below and left

of the static port- see Figure 6.2) on the backside of the PFD to a location on the

backside of the instrument panel using one of the mounting screws and nuts. Verify

less than 3 milliohms resistance to airframe ground at bonding strap connection point.


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Bonding Strap

Attachment Screw

Rear View of PFD

Figure 6.2 PFD Bonding Strap Connection

Figure 6.3 PFD and Bracket Installation


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Figure 6.4 - PFD Mounting Bracket (inches)


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6.8.4 Pitot and Static ConnectionsPitot and Static connections are made to the PFD 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 PFD unit.

NOTE: The pitot quick connector will fit on the PFD static port but the static quickconnector cannot be inadvertently connected to the PFD pitot port due to thekeying.

Each connector has a 0.256 diameter barbed fitting that accepts a hose.

Figure 6.5 - Pitot & Static Quick Connector

6.8.5 Quick Connector Installation1) 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 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.

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 flightcontrols and are not at risk of mechanical damage.


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Figure 6.6 Pitot & Static Line Connections

6.8.6 Leak Check RequirementsA pitot static leak check is required after the installation of the quick connectors and

the PFD is installed. The quick connectors are designed such that they seal when

disconnected.


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6.9RSM InstallationThe RSM is typically installed near the tail of the aircraft on an unpressurized portion of the

airframe. As the RSM incorporates both the OAT sensor and the emergency GPS antenna, it

must be mounted on the top outside of the airframe. In addition, the RSM includes the

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.

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.

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 (see Figure 6.7).

The NO ZONE areas below are hot zones for a lightning strike and are not to be used for

mounting the RSM. The RSM must not be mounted to the wing, the top of the vertical

stabilizer, the horizontal stabilizer, the fuselage forward of the cabin, or within 39 as

measured from the fuselage aft end as shown.

The RSM should not be mounted within 18 inches of a VHF Comm antenna, 6 inches of a GPS

or ELT antenna, and within 2 inches of another RSM.

The RSM will need to 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 become deformed upon mounting the RSM.

12"

Prefered Area

Hat Rack

Baggage

Compartment

NO ZONE

NO ZONE

Al ternate Locat ions

12" minimum

separation

39"

NO ZONE

12" minimum

separation

Figure 6.7 - RSM Mounting Location


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6.9.1 Proposed RSM Location CheckThe 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.

Place a small handheld compass in the proposed RSM mounting location and 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.

Once an area is located free from electrical interference the flight controls will need to

be moved from stop to stop to determine if there is any compass deflection.

If the compass does not show any deflection from electrical or mechanical sources then

that location is acceptable to mount the RSM.

If the proposed location is free of electrical interference but shows deflection from the

flight controls it may be possible to degauss the flight control cables and or flight

control hardware. Large ferric moveable objects that have become magnetized can

cause compass deflection.

Fixed ferric objects can be compensated for by the AHRS during the RSM alignment. A

degaussing coil can be purchased at most audio and video stores.

NOTE: If it is impossible to find a suitable mounting location in the preferred areait may be permissible to mount the RSM above the cabin. A locationwill need to be found that is a minimum of 12 inches from any cabinspeakers or electronic device that can cause compass fluctuations at the RSMlocation. Use the above procedure with the handheld compass to locatea quiet area. During operation of the electrical systems concentrate onthose devices that are in the cabin and within the headliner. Be awarethat headsets and other items worn by and operated by the flight crewand passengers could potentially interfere with the RSM. Typically this wouldbe when the headset is within 12 of the RSM location. Find a locationthat cannot be affected by the passenger and flight crew headsets whileseated and moving about the cabin.


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6.9.2 Pressurized AircraftOn 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

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 willrequire separate approval.

CAUTION: Mounting the RSM on the pressure vessel is beyond the scope of this STCand requires separate approval.

6.9.3 Second RSM Placement (MFD)A second RSM may be installed in preparation for a MFD1000 installation. It is

preferred to mount RSM #2 on either side of RSM #1 with a spacing of 2 inches or

more. A typical install would place the RSMs on opposite sides of the vertical

stabilizer. RSMs may be mounted fore and aft if a side by side orientation is

impractical.

6.9.4 RSM Mounting AnglesFor RSM mounting the following maximum mounting angles apply.

Figure 6.8 RSM Top View longitudinal Alignment


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Maximum fore and aft tilt is in relation to the aircraft waterline. An aluminum shim

might be required to keep orientation within limits (see Section 6.9.9 for shim

fabrication).

Figure 6.9 RSM Fore or Aft Max Tilt


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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 6.10 RSM Side to Side Max Tilt

6.9.5 RSM DoublerThis STC approves the use of the doubler shown in Figure 6.11 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.


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6.9.6 RSM Doubler Fabrication1) 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.

3) Fabricate the doubler from 2024-T3 AMS-QQ-A-250/5 to the dimensions in Figure

6.11, Tolerances 0.030

Figure 6.11 RSM Doubler

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

Documents

Efd1000 Pfd and Efd1000 Mfd - Installation Manual