Garmin 420 User Manual

Page 1

400 SERIES

INSTALLATION MANUAL

GPS 400, GNC TM 420 (A), and GNS TM 430 (A)

GNC and GNS are trademarks of Garmin Ltd. or its subsidiaries and may not be used without the express permission of Garmin.

(GNS 430 Shown)

Garmin International, Inc.

1200 E. 151

Olathe, KS 66062 USA

190-00140-02, Revision L

December 2002

Street

Page 2

Garmin Ltd. or its subsidiaries

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin International, Inc.

1200 E. 151

Olathe, KS 66062 USA

Street

Telephone: 913-397-8200

Aviation Panel-Mount Technical Support Line (Toll Free): 1-888-606-5482

Web Site Address: www.garmin.com

RECORD OF REVISIONS

Revision Revision

Date

A 6/19/98 Initial Release ----

B 10/22/98 General update 9891

C 11/11/98 Add 18 AWG pin positioner and insertion/extraction

tools. Add King Serial DME tuning interface description.

D 3/18/99 Add GNC 420, GPS 400, ARINC 429, GPS King Serial

OBI, RS-232 Fuel/Air Data Inputs

E 6/25/99 Reflect changes to configuration pages, Misc corrections 11243

F 10/13/99 Add interface to BF Goodrich Stormscope and Skywatch

and Ryan TCAD

G 4/27/00 Update installation accessory kits 13205

H 9/1/00 Add unit versions with 14/28 volt transmitter. Update

configuration pages.

J 2/22/01 Update configuration pages. 15207

K 5/22/02 Add gray unit and 16 watt “A” versions. Update

configuration pages.

L 12/13/02 Add Fault Detection and Exclusion 19779

Description ECO # Insertion

Date

10008

10665

11871

14026

18149

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This manual is written for software version 3.00, and is not suitable for earlier software versions. Information in this document is subject to change without notice. Visit the Garmin web site (www.garmin.com) for current updates and supplemental information concerning the operation of this and other Garmin products.

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

This document may contain information which is subject to the Export Administration Regulations ("EAR") issued by the United States Department of Commerce (15 CFR, Chapter VII, Subchapter C) and which may not be exported, released, or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license. A violation of the EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to $1,000,000 under Section 2410 of the Export Administration Act of 1979. Include this notice with any reproduced portion of this document.

WARNING

This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.

400 SERIES INSTALLATION MANUAL Page i P/N 190-00140-02 Page Rev L

Page 4

TABLE OF CONTENTS

1. GENERAL DESCRIPTION

1.1 INTRODUCTION .........................................................................................................................................1-1

1.2 EQUIPMENT DESCRIPTION......................................................................................................................1-1

1.3 TECHNICAL SPECIFICATIONS.................................................................................................................1-2

1.4 LICENSE REQUIREMENTS .......................................................................................................................1-7

1.5 CERTIFICATION .........................................................................................................................................1-7

1.6 FAULT DETECTION AND EXCLUSION (FDE) ......................................................................................1-7

1.7 LIMITED WARRANTY ...............................................................................................................................1-8

2. INSTALLATION

2.1 INTRODUCTION .........................................................................................................................................2-1

2.2 ANTENNA CONSIDERATIONS .................................................................................................................2-1

2.3 RACK CONSIDERATIONS .........................................................................................................................2-3

2.4 CABLING AND WIRING ............................................................................................................................2-3

2.5 COOLING AIR..............................................................................................................................................2-3

2.6 MINIMUM INSTALLATION REQUIREMENTS .......................................................................................2-3

3. INSTALLATION PROCEDURE

3.1 UNIT AND ACCESSORIES.........................................................................................................................3-1

3.2 DATA BASE OPTIONS................................................................................................................................3-4

3.3 MISCELLANEOUS OPTIONS.....................................................................................................................3-4

3.4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED ...................................................3-4

3.5 ANTENNA INSTALLATION ......................................................................................................................3-4

3.6 CABLE INSTALLATION.............................................................................................................................3-5

3.7 RACK INSTALLATION...............................................................................................................................3-6

3.8 400 SERIES UNIT INSERTION AND REMOVAL.....................................................................................3-7

3.9 COM ANTENNA INSTALLATION CHECK (GNC 420 AND GNS 430)..................................................3-7

3.10 GA 56 ANTENNA INSTALLATION DRAWING.....................................................................................3-9

3.11 MOUNTING RACK DIMENSIONS...........................................................................................................3-11

3.12 MOUNTING RACK INSTALLATION ......................................................................................................3-17

3.13 RECOMMENDED PANEL CUTOUT DIMENSIONS ..............................................................................3-23

4. SYSTEM INTERCONNECTS

4.1 PIN FUNCTION LIST...................................................................................................................................4-1

4.2 POWER, LIGHTING, AND ANTENNAS....................................................................................................4-5

4.3 ALTIMETER.................................................................................................................................................4-6

4.4 MAIN INDICATOR......................................................................................................................................4-7

4.5 ANNUNCIATORS/SWITCHES ...................................................................................................................4-9

4.6 SERIAL DATA .............................................................................................................................................4-11

4.7 COM/VOR/ILS AUDIO (GNC 420 AND GNS 430 ONLY)........................................................................4-14

4.8 VOR/ILS INDICATOR (GNS 430 ONLY)...................................................................................................4-16

4.9 RMI/OBI........................................................................................................................................................4-18

4.10 DME TUNING (GNS 430 ONLY)..............................................................................................................4-19

4.11 400 SERIES INTERCONNECTS................................................................................................................4-21

5. POST INSTALLATION CONFIGURATION & CHECKOUT PROCEDURE

5.1 CONFIGURATION MODE OPERATIONS.................................................................................................5-1

5.2 INSTALLATION CONFIGURATION PAGES............................................................................................5-1

5.3 ADDITIONAL GROUND TESTS ................................................................................................................5-16

Appendix A. CERTIFICATION DOCUMENTS

A.1 CONTINUED AIRWORTHINESS..............................................................................................................A-1

A.2 ENVIRONMENTAL QUALIFICATION FORM—GNS 430......................................................................A-3

A.3 ENVIRONMENTAL QUALIFICATION FORM—GNC 420 .....................................................................A-4

A.4 ENVIRONMENTAL QUALIFICATION FORM—GPS 400 ......................................................................A-5

A.5 ENVIRONMENTAL QUALIFICATION FORM—GA 56..........................................................................A-6

Appendix B. STC PERMISSION ................................................................................................................................B-1

Appendix C. 400 SERIES RS-232 AVIATION DATA FORMAT .............................................................................C-1

Appendix D. 400 SERIES RS-232 FUEL/AIR DATA INPUT FORMAT..................................................................D-1

Appendix E. 400 SERIES LRU INTERFACE OVERVIEW ......................................................................................E-1

Note: Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A and GNC 420A except where specifically noted.

Page ii 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Page 5

LIST OF FIGURES

FIGURE 2-1. GPS ANTENNA AND UNIT INSTALLATION CONSIDERATIONS .............................................2-2

FIGURE 3-1. COAXIAL CABLE INSTALLATION ................................................................................................3-5

FIGURE 3-2. GA 56 ANTENNA INSTALLATION DRAWING .............................................................................3-9

FIGURE 3-3. GNS 430 MOUNTING RACK DIMENSIONS ...................................................................................3-11

FIGURE 3-4. GNC 420 MOUNTING RACK DIMENSIONS...................................................................................3-13

FIGURE 3-5. GPS 400 MOUNTING RACK DIMENSIONS....................................................................................3-15

FIGURE 3-6. GNS 430 MOUNTING RACK INSTALLATION...............................................................................3-17

FIGURE 3-7. GNC 420 MOUNTING RACK INSTALLATION ..............................................................................3-19

FIGURE 3-8. GPS 400 MOUNTING RACK INSTALLATION ...............................................................................3-21

FIGURE 3-9. 400 SERIES RECOMMENDED PANEL CUTOUT DIMENSIONS..................................................3-23

FIGURE 4-1. 400 SERIES SYSTEM INTERFACE DIAGRAM ..............................................................................4-21

FIGURE 4-2. GNS 430 TYPICAL INSTALLATION ...............................................................................................4-23

FIGURE 4-3. GNC 420 TYPICAL INSTALLATION...............................................................................................4-25

FIGURE 4-4. GPS 400 TYPICAL INSTALLATION................................................................................................4-27

FIGURE 4-5. POWER, LIGHTING, AND ANTENNAS INTERCONNECT...........................................................4-29

FIGURE 4-6. ALTIMETER INTERCONNECT........................................................................................................4-31

FIGURE 4-7. MAIN INDICATOR INTERCONNECT .............................................................................................4-33

FIGURE 4-8. KI 209A MAIN INDICATOR INTERCONNECT ..............................................................................4-35

FIGURE 4-9. KI 208A MAIN INDICATOR INTERCONNECT ..............................................................................4-37

FIGURE 4-10. ANNUNCIATORS/SWITCHES INTERCONNECT ........................................................................4-39

FIGURE 4-11. RS-232 SERIAL DATA INTERCONNECT .....................................................................................4-41

FIGURE 4-12. ARINC 429 EFIS INTERCONNECT................................................................................................4-43

FIGURE 4-13. ARINC 429 SANDEL EHSI INTERCONN. (1 400 SERIES UNIT, 1 SANDEL SN3308)..............4-45

FIGURE 4-14. ARINC 429 SANDEL EHSI INTERCONNECT (2 GNS 430, 1 SANDEL SN3308).......................4-47

FIGURE 4-15. ARINC 429 SANDEL EHSI INTERCONNECT (2 GNS 430, 2 SANDEL SN3308).......................4-49

FIGURE 4-16. ARINC 429 AIR DATA/IRU/AHRS INTERCONNECT..................................................................4-51

FIGURE 4-17. ARINC 429 FLIGHT CONTROL INTERCONNECT ......................................................................4-53

FIGURE 4-18. TRAFFIC ADVISORY SYSTEM INTERCONNECT ......................................................................4-55

FIGURE 4-19. WEATHER AND TERRAIN INTERCONNECT .............................................................................4-57

FIGURE 4-20. AUDIO PANEL INTERCONNECT..................................................................................................4-59

FIGURE 4-21. VOR/ILS INDICATOR INTERCONNECT ......................................................................................4-61

FIGURE 4-22. RMI/OBI INTERCONNECT.............................................................................................................4-63

FIGURE 4-23. KING SERIAL PANEL DME TUNING INTERCONNECT ............................................................4-65

FIGURE 4-24. KING SERIAL REMOTE DME TUNING INTERCONNECT.........................................................4-67

FIGURE 4-25. PARALLEL 2 OF 5 DME TUNING INTERCONNECT ..................................................................4-69

FIGURE 4-26. PARALLEL BCD/SLIP CODE DME TUNING INTERCONNECT ................................................4-71

Note: Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A and GNC 420A except where specifically noted.

400 SERIES INSTALLATION MANUAL Page iii P/N 190-00140-02 Page Rev L

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LIST OF FIGURES - CONTINUED

FIGURE 5-1. MAIN ARINC 429 CONFIG PAGE....................................................................................................5-1

FIGURE 5-2. MAIN RS232 CONFIG PAGE ............................................................................................................5-3

FIGURE 5-3. MAIN INPUTS 1 PAGE......................................................................................................................5-4

FIGURE 5-4. MAIN INPUTS 2 PAGE......................................................................................................................5-4

FIGURE 5-5. INSTRUMENT PANEL SELF TEST PAGE ......................................................................................5-5

FIGURE 5-6. MAIN LIGHTING PAGE....................................................................................................................5-5

FIGURE 5-7. MAIN LIGHTING PAGE (DISPLAY LIGHTING FROM LIGHTING BUS) ...................................5-6

FIGURE 5-8. DISPLAY PAGE (AUX GROUP) .......................................................................................................5-6

FIGURE 5-9. DATE/TIME SETUP PAGE................................................................................................................5-6

FIGURE 5-10. MAIN DISCRETE INPUTS PAGE...................................................................................................5-6

FIGURE 5-11. MAIN DISCRETE OUTPUTS PAGE ...............................................................................................5-7

FIGURE 5-12. MAIN CDI/OBS CONFIG PAGE......................................................................................................5-7

FIGURE 5-13. COM SETUP PAGE (GNC 420 AND GNS 430 ONLY) ..................................................................5-9

FIGURE 5-14. VOR DISCRETE INPUTS PAGE (GNS 430 ONLY).......................................................................5-10

FIGURE 5-15. VOR/LOC/GS CDI PAGE (GNS 430 ONLY)...................................................................................5-10

FIGURE 5-16. VOR/LOC/GS ARINC 429 CONFIG PAGE (GNS 430 ONLY).......................................................5-11

FIGURE 5-17. STORMSCOPE CONFIG PAGE.......................................................................................................5-12

FIGURE 5-18. STORMSCOPE TEST PAGE............................................................................................................5-12

FIGURE 5-19. STORMSCOPE DOWNLOAD DATA PAGE ..................................................................................5-12

FIGURE 5-20. TRAFFIC PAGE (SKYWATCH)......................................................................................................5-13

FIGURE 5-21. TRAFFIC PAGE (TCAD)..................................................................................................................5-13

FIGURE 5-22. RYAN TCAD CONFIG PAGE..........................................................................................................5-13

FIGURE 5-23. GAD 42 CONFIG PAGE ...................................................................................................................5-13

FIGURE 5-24. DATA LINK PAGE...........................................................................................................................5-14

Note: Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A and GNC 420A except where specifically noted.

Page iv 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Page 7

400 SERIES HARDWARE MOD LEVEL HISTORY

The following table identifies hardware modification (Mod) Levels for the GPS 400, GNC 420 and GNS 430. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice. Authorized Garmin Sales and Service Centers are encouraged to access the most up-to-date bulletin and advisory information on the Garmin Dealer Resource web site at www.garmin.com using their Garmin -provided user name and password.

MOD

LEVEL

1 9905 9/17/99 CDI/HSI deviation error; GNS 430, P/N 011-

1 0019 11/07/00 Replace fuse in COM circuit with a resistor;

2 0101 2/16/01 Remote COM transfer

3 0203, Rv B 8/12/02 Improve receiver audio compressor

4 0207 4/2/02 Remove excess solder from COM board

5 0211 6/4/02 Reduce input transients from Audio Panel

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF MODIFICATION

00280-00, GNC 420, P/N 011-00506-00, GPS 400, P/N 011-00504-00

GNS 430, P/N 011-00280-10, GNC 420, P/N 011-00506-10, GNS 530, P/N 011-00550-10

performance

Note: Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A and GNC 420A except where specifically noted.

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1. GENERAL DESCRIPTION

1.1 INTRODUCTION

This manual describes the physical, mechanical, and electrical characteristics and the installation requirements for the 400 Series (GPS 400, GNC 420, and GNS 430) Panel-mounted units. After installation of the 400 Series system, FAA Form 337 must be completed by an appropriately certificated agency to return the aircraft to service.

1.2 EQUIPMENT DESCRIPTION

The 400 Series units are mark width (6.25” wide) units, and 2.66” high. The display is a 128 by 240 pixel color LCD. The units include two removable data cards, one with a Jeppesen database, and the second being an optional custom data card.

The GPS 400 is a GPS receiver certifiable for IFR en route, terminal, and non-precision approach operations.

The GNC 420/ (A) includes all the features of the GPS 400, and also includes an IFR certified airborne VHF communications transceiver. The (A) model is a 28 Vdc unit with a 16 Watt COM transmitter.

The GNS 430/ (A) includes all the features of the GNC 420, and also includes IFR certified airborne VOR/Localizer and Glideslope receivers. The (A) model is a 28 Vdc unit with a 16 Watt COM transmitter.

GPS signals are received by Garmin's low profile GA 56 antenna (P/N 010-10040-0X).

CAUTION

The 400 Series product lens is coated with a special anti-reflective coating which is very sensitive to skin oils, waxes and abrasive cleaners. It is very important to clean the lens using an eyeglass lens cleaner which is specified as safe for anti-reflective coatings (one suitable product is Wal-Mart

Lens Cleaner) and a clean, lint-free cloth.

CAUTION

The use of cellular telephones while aircraft are airborne is prohibited by FCC rules. Due to potential interference with onboard systems, the use of cell phones while the aircraft is on the ground is subject to FAA regulations (Part 91.21).

FCC regulation 47 CFR Ch.1 (Section 22.925) prohibits airborne operation of cellular telephones installed in or carried aboard aircraft. Cellular telephones must not be operated while aircraft are off the ground. When any aircraft leaves the ground, all cellular telephones on board that aircraft must be turned off.

Cell phones that are on, even in a monitoring state, can disrupt GPS performance.

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1.3 TECHNICAL SPECIFICATIONS

The conditions and tests required for TSO approval of the 400 Series are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the administrator. For TSO Compliance, see Appendix A.

1.3.1 Physical Characteristics

Bezel Height 2.66 in. (67 mm) Bezel Width 6.25 in. (159 mm) Rack Height (Dimple-todimple) Rack Width 6.32 in. (160 mm) Depth Behind Panel with Connectors (Measured from face of aircraft panel to rear of connector backshells) GPS 400 Weight (Unit only) 3.8 lbs. (1.7 kg) GPS 400 Weight (Installed with rack and connectors) GNC 420 Weight (Unit only) 4.5 lbs. (2.0 kg) GNC 420 Weight (Installed with rack and connectors) GNS 430 Weight (Unit only) 5.1 lbs. (2.3 kg) GNS 430 Weight (Installed with rack and connectors)

2.69 in. (68 mm)

11.00 in. (279 mm)

4.9 lbs. (2.2 kg)

5.8 lbs. (2.6 kg)

6.5 lbs. (2.9 kg)

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1.3.2 General Specifications

Operating Temperature Range

-20°C to +55°C. For more details see Environmental Qualification Form.

Humidity 95% non-condensing Altitude Range -1,500 ft to 50,000 ft Input Voltage Range (GPS 400) 11 to 33 V Input Voltage Range

22 to 33 V

GNS 430 (011-00280-00) and GNC 420 (011-00506-00) Input Voltage Range

11 to 33 V

GNS 430 (011-00280-10, -30) GNC 420 (011-00506-10, -30) GNS 430 (A) (011-00836-00,-10)

28 V

GNC 420 (A) (011-00837-00,-10) Power Requirements—P4001 (GPS 400 Main Connector) Power Requirements—P4001

0.72 A @ 27.5 VDC________or

1.44 A @ 13.75 V

1.5 A @ 27.5 VDC (maximum)

(GNC 420 Main Connector) Power Requirements—P4001

1.5 A @ 27.5 VDC (maximum)

(GNS 430 Main Connector) Power Requirements—P4002 (COM Connector)

15 mA @ 27.5 VDC (not transmitting);

3.0 A @ 27.5 V

(transmitting)

GNS 430 (011-00280-00) GNS 430A (011-00836-00, -10) and GNC 420 (011-00506-00) GNC 420A (011-00837-00, -10) Power Requirements—P4002 (COM Connector) GNS 430 (011-00280-10, -30) and GNC 420 (011-00506-10)

15 mA @ 27.5 VDC (not transmitting);

3.0 A @ 27.5 V 10 mA @ 13.75 V

6.0 A @ 13.75 V

(transmitting)_______or

(not transmitting);

(transmitting)

Superflag Power Requirements 500 mA max. per superflag output @ 27.5 V

1.0 A max. @ 27.5 VDC on P4001 (Main Superflags).

1.0 A max. @ 27.5 V

on P4006 (VOR/LOC, G/S

Superflags).

Software RTCA DO-178B level C Environmental Testing RTCA DO-160C.

For more details see Environmental Qualification Forms.

DC.

1.3.3 GPS Specifications

Regulatory Compliance TSO C129a, RTCA DO-208 Acquisition Time a) Search-the-Sky (without almanac, without initial position

or time): 5 minutes

b) AutoLocate™ (with almanac, without initial position or

time): 5 minutes

c) Cold Start (position known to 300 nm, time known to 10

minutes, with valid almanac): 45 seconds

d) Warm Start (position known to 10 nm, time known to 10

minutes, with valid almanac and ephemeris): 15 seconds

Max Velocity 1000 kts. Dynamics 6 g

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1.3.4 COM Transceiver Specifications (GNC 420 and GNS 430 Only) **

Regulatory Compliance TSO-C37d Class 4 & 6* (3 & 5 for “A” models), TSO-C38d

Class C & E, JTSO-2C37e, JTSO-2C38e, RTCA DO-186a ICAO Annex 10 Volume III (Part II – Voice Communications Systems) Par. 2.3.3

Audio Output

100 mW minimum into a 500 Ω load.

Audio Response Less than 6 dB of variation between 350 and 2500 Hz. Audio Distortion The distortion in the receiver audio output shall not exceed

15% at all levels up to 100 mW.

AGC Characteristics The audio output shall not vary by more than 6 dB when the

level of the RF input signal, modulated 30% at 1000 Hz, is varied from 5 µV to 450,000 µV.

Sensitivity (S+N)/N on all channels shall be greater than 6 dB when the

RF level is 2 µV (hard) modulated 30% at 1000 Hz at rated audio.

Squelch

2 µv ±6 dB for 25 kHz channels. 3 µv ±6 dB for 8.33 kHz channels.

Selectivity

6 dB BW is greater than ±8 kHz for 25 kHz channeling. 60 dB BW is less than ±25 kHz for 25 kHz channeling. 6 dB BW is greater than ±2.778 kHz for 8.33 kHz channeling. 60 dB BW is less than ±7.37 kHz for 8.33 kHz channeling.

Spurious Response Greater than 85 dB. Transmitter Power At Least 10 watts, 16 watts for “A” models Transmitter Duty Cycle Recommended 10% maximum. Modulation Capability The modulation shall not be less than 70% and not greater

than 98% with a standard modulator signal applied to the transmitter.

Carrier Noise Level Shall be at least 45 dB (S+N)/N. Frequency Stability 0.0005% Demodulated Audio Distortion Less than 10% distortion when the transmitter is modulated

at least 70%.

Sidetone

1.4 V

into a 500 Ω load when the transmitter is modulated

RMS

at least 70%.

Demodulated Audio Response Shall be less than 6 dB when the audio input frequency is

varied from 350 to 2500 Hz.

* C37d Class 4 & 6 may not provide suitable COM transmit range for some high-altitude aircraft.

** Specifications shown apply at nominal input voltages of 13.75 Vdc or 27.5 Vdc, as applicable, and with a nominal 50 ohm resistive load at the antenna connector.

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1.3.5 VOR Specifications (GNS 430 Only)

Regulatory Compliance TSO C40c, JTSO-2C40c, RTCA DO-196, EuroCAE ED-22B Receiver Audio Sensitivity At -103.5 dBm (S+N)/N shall not be less than 6 dB. Course Deviation Sensitivity -103.5 dBm or less for 60% of standard deflection. Flag The VOR Course Deviation Flag must be flagged:

a) in the absence of an RF signal. b) in the absence of the 9960 Hz modulation. c) in the absence of either one of the two 30 Hz

modulations.

d) When the level of a standard VOR deviation test signal

produces less than a 50% of standard deflection.

AGC Characteristics From -99 dBm to -13 dBm input of a Standard VOR Audio

Test Signal, audio output levels shall not vary more than 3 dB.

Spurious Response Greater than 80 dB. VOR OBS Bearing Accuracy The bearing information as presented to the pilot shall not

have an error in excess of 2.7° as specified by RTCA DO-196 and EuroCAE ED-22B.

Audio Output

A minimum 100 mW into a 500 Ω load.

Audio Response Less than 6 dB of variation between 350 and 2500 Hz.

Except the 1020 Hz Ident Tone is at least 20 dB down in voice mode.

Audio Distortion The distortion in the receiver audio output shall not exceed

10% at all levels up to 100 mW.

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1.3.6 LOC Specifications (GNS 430 Only)

Regulatory Compliance TSO C36e, JTSO-C36e, RTCA DO-195 CLASS A, EuroCAE

ED-46B

Receiver Audio Sensitivity At -103.5 dBm (S+N)/N shall not be less than 6 dB. Course Deviation Sensitivity -103.5 dBm or less for 60% of standard deflection. Flag The LOC Course Deviation Flag must be flagged:

a) in the absence of an RF signal. b) When either the 90 or 150 Hz modulating signals is

removed and the other is maintained at its normal 20%. c) In the absence of both 90 and 150 Hz modulation. d) When the level of a standard localizer deviation test

signal produces less than a 50% of standard deflection.

AGC Characteristics From -86 dBm and -33 dBm input of a Standard VOR Audio

Test Signal, audio output levels shall not vary more than 3 dB.

Selectivity Nose Bandwidth: The input signal level required to produce

the reference AGC voltage shall not vary more than 6 dB over the input signal frequency range of ± 9 kHz from the assigned channel frequency.

Skirt Bandwidth: The input signal level required to produce reference AGC voltage shall be at least 70 dB greater than the level required to produce reference AGC voltage at the assigned channel frequency at ± 36 kHz from the assigned channel frequency.

Spurious Response Greater than 80 dB. Centering Accuracy Audio Output

Typical 0 ± 3 mV (Max error 9.9 mV per RTCA DO-195). A minimum 100 mW into a 500 Ω load.

Audio Response Less than 6 dB of Variation between 350 and 2500 Hz.

Except the 1020 Hz Ident Tone is at least 20 dB down in voice mode.

Audio Distortion The distortion in the receiver audio output shall not exceed

10% at all levels up to 100 mW.

1.3.7 Glideslope Specifications (GNS 430 Only)

Regulatory Compliance TSO C34e, JTSO-C34e, RTCA DO-192, EuroCAE ED-47B Sensitivity -87 dBm or less for 60% of standard deflection. Centering Accuracy Selectivity

0 ± .0091 ddm or 0 ± 7.8 mV The course deviation shall be 0 ddm ± .0091ddm when using

the Glideslope Centering Test Signal as the RF frequency is varied ±17 kHz from the assigned channel. At frequencies displaced by ±132 kHz or greater, the input signal shall be at least 60 dB down.

Standard deflection a) With a standard deflection ‘FLY DOWN’ condition (90 Hz

dominant), the output shall be -78 mV ± 7.8 mV. b) With a standard deflection ‘FLY UP’ condition (150 Hz dominant), the output shall be +78 mV ± 7.8 mV.

Flag The unit Flags:

a) When the level of a standard deviation test signal produces 50% or less of standard deflection of the deviation indicator. b) In the absence of 150 Hz modulation. c) In the absence of 90 Hz modulation. d) In the absence of both 90 Hz and 150 Hz modulation. e) In the absence of RF.

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1.4 LICENSE REQUIREMENTS

The following guidance is provided to help ensure the proper licensing of the GNC 420/GNS 430 COM:

1. The Telecommunications Act of 1996 effective February 8, 1996 provides the FCC discretion to eliminate radio station license requirements for aircraft. At present, an individual license to operate the 400 Series aboard a private aircraft is not needed in many circumstances. Please see FCC Fact Sheet PR5000 or contact the FCC at 1-800-322-1117 for more information.

2. No license change is required for an aircraft which already has a station license per FCC 404 Instructions dated 1994.

3. If an aircraft license is required or desired, contact the FCC at 1-800-322-1117 to request FCC Form 404, “Application for Aircraft Radio Station License,” to apply for FCC authorization. The FCC also has a “Fax on Demand” service to provide forms by FAX at 202-418-0177.

This equipment has been type accepted by the FCC. The bandwidth/emission designator is 6K00 A3E.

CAUTION

THE VHF TRANSMITTER IN THIS EQUIPMENT IS GUARANTEED TO MEET FEDERAL COMMUNICATIONS COMMISSION ACCEPTANCE OVER THE OPERATING TEMPERATURE RANGE. MODIFICATIONS NOT EXPRESSLY APPROVED BY GARMIN COULD INVALIDATE THE LICENSE AND MAKE IT UNLAWFUL TO OPERATE THE EQUIPMENT.

1.5 CERTIFICATION

The GPS receivers in the 400 Series units are certified for IFR enroute, terminal, and non-precision approaches. The 400 Series initial certification was accomplished via STC’s by Garmin in a Piper PA32. See Appendix B for copies of the STC’s.

The 400 Series units have been qualified to RTCA/DO-160 Section 22 lightning requirements. Special installation considerations are required, refer to the Environmental Qualification Forms in Appendix A.

1.6 FAULT DETECTION AND EXCLUSION (FDE)

NOTE

The 400 Series equipment as installed has been found to comply with the requirements for GPS primary means of navigation in oceanic and remote airspace, when used in conjunction with the 400 Series Trainer Program incorporating the FDE Prediction Program. This does not constitute an operational approval.

The Garmin 400 Series Main and GPS Software version 3.00 and higher incorporate Fault Detection and Exclusion (FDE) display interface and control, satisfying the requirements for GPS as a Primary Means of Navigation for Oceanic/Remote Operations per FAA Notice N8110.60.

Fault Detection and Exclusion consists of two parts. The fault detection function detects a satellite failure that can affect navigation. The exclusion function refers to the capability of excluding one or more failed satellites and preventing them from affecting navigation.

FDE is provided for Oceanic and Remote Operations, non-precision approaches, en route and terminal phases of flight. FDE for non-oceanic flight phases adhere to the same missed alert probability, false alert probability, and failed exclusion probability specified by N8110.60.

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The FDE function is built into the GPS 400/GNC 420/GNS 430 and does not require pilot interaction. In contrast, the FDE Prediction Program does require pilot interaction and must be used prior to oceanic/remote area flights to predict FDE availability. The 400 Series Trainer software (Garmin Part Number 190-00176-00) includes an FDE Prediction Program to meet the requirements for GPS as a primary means of navigation for oceanic/remote operations per N8110.60. The oceanic flight phase occurs on the GPS 400/GNC 420/GNS 430 when more than 200 nautical miles from the nearest airport.

All operators using the GPS 400/GNC 420/GNS 430 as primary means of navigation in oceanic/remote areas under FAR parts 91, 121, 125 and 135 must utilize the FDE Prediction Program prior to conducting a flight in these areas.

1.7 LIMITED WARRANTY

This Garmin product is warranted to be free from defects in materials or workmanship for one year from the date of purchase. Within this period, Garmin will at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts or labor, provided that the customer shall be responsible for any transportation cost. This warranty does not cover failures due to abuse, misuse, accident or unauthorized alteration or repairs.

THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.

IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not allow the exclusion of incidental or consequential damages, so the above limitations may not apply to you.

Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.

To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center near you, call Garmin Customer Service at one of the numbers shown below.

Garmin International, Inc. Garmin (Europe) Ltd. 1200 East 151

Street Unit 4, The Quadrangle, Abbey Park Industrial Estate Olathe, Kansas 66062, U.S.A. Romsey, SO51 9DL, U.K. Phone: 913/397.8200 Phone: 44/1794.519944 FAX: 913/397.0836 FAX: 44/1794.519222

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Page 17

2. INSTALLATION

2.1 INTRODUCTION

Careful planning and consideration of the suggestions in this section are required to achieve the desired performance and reliability from the 400 Series unit. Any deviations from the installation instructions prescribed in this document shall be accomplished in accordance with the requirements set forth in FAA AC 43.13-2A, and 14 CFR Part 43 Maintenance, Preventive Maintenance, Rebuilding, and Alteration.

2.2 ANTENNA CONSIDERATIONS

Antenna installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such antenna installations incorporate alteration (penetration) of the cabin pressure vessel by connector holes and/or mounting arrangements. For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations, it is recommended that the installer proceed according to any of the following listed alternatives:

1. Obtain approved antenna installation design data from the aircraft manufacturer.

2. Obtain an FAA approved STC, pertaining to, and valid for the antenna installation.

3. Contact the FAA Aircraft Certification Office in the appropriate Region and request identification of

FAA Designated Engineering Representatives (DERs) who are authorized to prepare and approve the required antenna installation engineering data.

4. Obtain FAA Advisory Circular AC-183C and identify a DER from the roster of individuals in it.

5. Contact an aviation industry organization such as the Aircraft Electronics Association for assistance.

2.2.1 GPS ANTENNA LOCATION

The GA 56 Antenna must be mounted on top of the aircraft. For best performance, select a location with an unobstructed view of the sky above the aircraft when in level flight. Figure 2-1 illustrates a typical GPS antenna installation. The antenna should be located at least three feet from transmitting antennas such as VHF COM, HF transmitter, DME, Transponder and Radar.

For rotorcraft, locate the GA 56 Antenna as far as possible from the main rotor hub. This reduces the percentage of time the blade blocks the antenna. Also mount it as far below the blade surface as possible if installing the antenna under the blade. This reduces signal distortion caused by the blades.

2.2.2 COM ANTENNA LOCATION

The GNC 420 or GNS 430 COM antenna should be well removed from all projections, engines and propellers. The ground plane surface directly below the antenna should be a flat plane over as large an area as possible (18 inches square, minimum). The antenna should be mounted a minimum of six feet from any DME or other COM antennas, four feet from any ADF sense antennas, and three feet from the 400 Series and its GPS antenna.

If simultaneous use of two COM transceivers is desired (spit- COM or simulcomm), use of the TX interlock function is mandatory. In addition, the COM antennas should be spaced for maximum isolation. A configuration of one topside antenna and one bottom side antenna is recommended.

2.2.3 VOR/LOC ANTENNA LOCATION

The GNS 430 VOR/LOC antenna should be well removed from all projections, engines and propellers. It should have a clear line of sight if possible. The antenna must be mounted along the centerline of the aircraft, minimizing the lateral offset.

2.2.4 GLIDESLOPE ANTENNA LOCATION

The GNS 430 Glideslope antenna should be well removed from all projections, engines and propellers. It should have a clear line of sight if possible.

2.2.5 ELECTRICAL BONDING

No special precautions need to be taken to provide a bonding path between the GPS antenna and the aircraft structure. Follow the manufacturers’ instructions for the COM, VOR/LOC and Glideslope antennas.

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Page 18

2.2.6 ANTENNA LIMITATIONS

Garmin’s GA 56 Antennas are recommended for installations where the airspeed of the aircraft is subsonic. In such installations, GA 56—Mod 1 or later—must be used. See the COM, VOR/LOC, and Glideslope antenna specifications for their limitations.

2.2.7 VHF COM INTERFERENCE OF GPS

On many panel-mounted installations, VHF COM transceivers can radiate strong harmonics from the transceiver and its antenna. The 400 Series COM does not interfere with its own GPS section. However, placement of the GA 56 GPS antenna relative to a COM transceiver and COM antenna, including the GNC 420 or GNS 430 COM antenna, is critical.

Use the following guidelines, in addition to others in this document, when locating the 400 Series unit and its antennas.

• GPS Antenna—Locate as far as possible from all COM antennas and all COM transceivers (including the 400 Series COM). The GPS antenna is less susceptible to harmonic interference if a 1.57542 GHz notch filter is installed on the COM transceiver antenna output.

• Locate the 400 Series unit as far as possible from all COM antennas.

Figure 2-1. GPS Antenna and Unit Installation Considerations

If a COM antenna is found to be the problem, a 1.57542 GHz notch filter (Garmin P/N 330-00067-00) may be installed in the VHF COM coax, as close to the COM as possible. This filter is not required for the GNC 420 and GNS 430 transmitters.

If a COM is found to be radiating, the following can be done:

1. Replace or clean the VHF COM rack connector to ensure good coax ground.

2. Place grounding straps between the 400 Series unit, VHF COM and a good ground.

3. Shield the VHF COM wiring harness.

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Page 19

2.2.8 COM, VOR/LOC, and Glideslope Antenna Installation Instructions

Install the COM, VOR/LOC, and Glideslope antennas according to the manufacturer’s recommendations. Avoid running other wires and coaxial cables near the VOR/LOC antenna cable.

2.3 RACK CONSIDERATIONS

Plan a location which gives the pilot complete and comfortable access to the entire keypad and which is plainly visible from the pilot’s perspective. Installation of remote switches and annunciators may not be required if the 400 Series unit is installed in the pilot’s normal field of view (refer to the FAA letter in Appendix B).

Check that there is adequate depth for the rack in the instrument panel. A location away from heating vents or other sources of heat generation is optimal.

2.4 CABLING AND WIRING

Coaxial cable with 50 Ω nominal impedance and meeting applicable aviation regulations should be used for the installation. A typical maximum cable length for the GPS antenna is 40 feet. The installer should insure that the attenuation does not exceed 10 dB at 1.5 GHz for the specific installation.

Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling, particularly the COM antenna cable, and routing near aircraft control cables. Cabling for the 400 Series unit should not be routed near components or cabling which are sources of electrical noise. Do not route the COM antenna coax near any ADF antenna cables. Route the GPS, VOR/LOC, and Glideslope antenna cables as far as possible away from all COM transceivers and antenna cables.

2.5 COOLING AIR

The 400 Series units meet all TSO requirements without external cooling. However, as with all electronic equipment, lower operating temperatures extend equipment life. On the average, reducing the operating temperature by 15-20 °C (25 to 35 °F) doubles the mean time between failure (MTBF). Recommended airflow rating is 1 CFM (cubic foot per minute) at a pressure equivalent to 0.1 inches of water. Potential damage to your 400 Series unit may occur by using outside forced air to cool the equipment. Therefore, it is recommended that an electric forced air fan be installed, of the indicated rating, to cool this equipment.

Units tightly packed in the avionics stack heat each other through radiation, convection, and sometimes by direct conduction. Even a single unit operates at a much higher temperature in still air than in moving air. Fans or some other means of moving the air around electronic equipment are usually a worthwhile investment. A 5/8” diameter air fitting is provided on the rear of the mounting rack for the purpose of admitting cooling air under such conditions. If a form of forced air cooling is installed, make certain that rainwater cannot enter and be sprayed on the equipment.

2.6 MINIMUM INSTALLATION REQUIREMENTS

Below is a list of required devices for TSO C129a category A1 and A2 certification. For a specific list of equipment used in the initial STC, obtain a copy of “GNS 430 in Piper PA32 Documented Installation” (P/N 190-00140-06). The FAA or the governing organization should approve deviations from that set of equipment.

Pressure Altitude Device

This device delivers pressure altitude data to the 400 Series unit. This data can come from a parallel encoding altimeter, blind encoder, serializer, or an air data system.

Manual Course Device (Required for GNS 430 Only)

This device delivers the manual course select to the 400 Series unit, which is required for the GNS 430 VOR receiver, and optional for the 400/420/430 GPS receiver. Course information can come from an analog resolver, or from an EFIS/EHSI via ARINC 429 serial data.

HSI/CDI Indicator or EFIS

This device displays Nav Flag, Left/Right, To/From, Glideslope Flag, and Up/Down. The indicator(s) used in conjunction with the GNS 430 VOR/ILS receivers shall be TSO'd.

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Page 20

Qualified GPS Antenna

This antenna must be one of those listed in the accessories list, or meet the following requirements:

1. DO-160C Environmental Conditions

The antenna shall meet the environmental conditions listed below and shall conform to the test requirements of RTCA DO-160C.

Environmental Condition Category Description

Temperature (operating) F2 -55 to +70oC

(ground survival) F2 -55 to +85 Altitude F2 55,000 feet Temperature Variation A 10

Humidity C 95% at +55

C per minute

C Vibration CLMY Turbo/Reciprocating/Helicopter Waterproofness S Continuous Stream Fluids F Deicing Fluid Lightning 2A Direct Effects Icing C 0.15” thick

2. Electrical Characteristics

LNA Supply voltage 4.5 ± 0.5 V

LNA Supply Current 20 mA Maximum LNA Operating Frequency 1575.42 ± 2.00 MHz LNA Gain 20 dB Maximum, 12dB Minimum LNA Noise Figure 3.0 dB Maximum LNA Output VSWR (50 Ω)2:1 Maximum LNA Input power at -1 dB Gain Compression -6 dB Minimum LNA Bandwidth (-3 dB) 40 MHz Maximum (-20 dB) 100 MHz Maximum (-40 dB) 250 MHz Maximum

3. Radiation Characteristics

Polarization RHCP Operating Frequency 1575.42 ± 2.00 MHz Gain (on axis) 2.0 dBic Minimum

(at 160

beam width) -6.0 dBic Minimum

Cross Pole Gain (LHCP)

(on axis) -8 dBic Maximum

(at 160

beam width) -9 dBic Maximum

4. Mounting Requirements

Cable connection BNC Female Mounting studs Four 8-32 UNC-2A studs 0.50” long

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Page 21

3. INSTALLATION PROCEDURE

3.1 UNIT AND ACCESSORIES

The 400 Series units are available under the following part numbers:

3.1.1 GNS 430 (A)

CATALOG

P/N

010-00139-00 011-00280-00 N N BLACK 28 10 W 010-00139-01 011-00280-00 N Y BLACK 28 10 W 010-00139-10 011-00280-10 N N BLACK 14 or 28 Vdc 10 W 010-00139-11 011-00280-10 N Y BLACK 14 or 28 Vdc 10 W 010-00139-30 011-00280-30 N N GRAY 14 or 28 V (2) 10 W 010-00139-31 011-00280-30 N Y GRAY 14 or 28 V (2) 10 W 010-00286-00 011-00836-00 Y N BLACK 28 Vdc 16 W 010-00286-01 011-00836-00 Y Y BLACK 28 Vdc 16 W 010-00286-10 011-00836-10 Y N GRAY 28 Vdc (2) 16 W 010-00286-11 011-00836-10 Y Y GRAY 28 Vdc (2) 16 W

1) The following accessories are included with the GNS 430 (A) for those indicated with a “Y” above:

MOUNTING RACK (115-00243-00) CONNECTOR KIT (011-00351-00) BACK PLATE ASSEMBLY (011-00676-00) GNS 430 PRODUCT INFO KIT (K00-00055-00)

UNIT

P/N

GNS

430A

ACCESSORIES

(1)

COLOR OPERATING

VOLTAGE

MINIMUM

XMIT PWR

2) Denotes alternate (secondary) power input available, (review installation drawing).

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3.1.2 GNC 420 (A)

CATALOG

P/N

UNIT

P/N

GNC

420A

ACCESSORIES

(1)

COLOR OPERATING

VOLTAGE

MINIMUM

XMIT PWR

010-00173-00 011-00506-00 N N BLACK 28 10 W 010-00173-01 011-00506-00 N Y BLACK 28 10 W 010-00173-10 011-00506-10 N N BLACK 14 or 28 Vdc 10 W 010-00173-11 011-00506-10 N Y BLACK 14 or 28 Vdc 10 W 010-00173-30 011-00506-30 N N GRAY 14 or 28 V (2) 10 W 010-00173-31 011-00506-30 N Y GRAY 14 or 28 V (2) 10 W 010-00287-00 011-00837-00 Y N BLACK 28 Vdc 16 W 010-00287-01 011-00837-00 Y Y BLACK 28 Vdc 16 W 010-00287-10 011-00837-10 Y N GRAY 28 Vdc (2) 16 W 010-00287-11 011-00837-10 Y Y GRAY 28 Vdc (2) 16 W

1) The following accessories are included with the GNS 420 (A) for those indicated with a “Y” above:

MOUNTING RACK (115-00243-00) CONNECTOR KIT (011-00351-01) BACK PLATE ASSEMBLY (011-00676-01) GNC 420 PRODUCT INFO KIT (K00-00057-00)

2) Denotes alternate (secondary) power input available, (review installation drawing).

3.1.3 GPS 400

CATALOG

P/N

UNIT

P/N

ACCESSORIES

(1)

COLOR ALT PWR

AVAILABL

010-00171-00 011-00504-00 N BLACK N 010-00171-01 011-00504-00 Y BLACK N 010-00171-10 011-00504-10 N GRAY Y 010-00171-11 011-00504-10 Y GRAY Y

1) The following accessories are included with the GPS 400 for those indicated with a “Y” above:

MOUNTING RACK (115-00243-00) CONNECTOR KIT (011-00351-03) BACK PLATE ASSEMBLY (011-00676-03) GPS 400 PRODUCT INFO KIT (K00-00056-00)

Alternate (secondary) power input available (review installation drawing).

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Page 23

The following installation accessories are available:

1. GPS Antenna Options:

• GA 56 Antenna Kit, without cable (Mod 1 or later, Garmin P/N 010-10040-01). This kit contains the following items:

ITEM GARMIN P/N QTY

GA 56 ANTENNA SUB-ASSEMBLY 011-00134-00 1 BACKING PLATE 115-00031-00 1 NUT, SELF-LOCKING, #8-32 210-10004-09 4 ANTENNA GASKET 253-00002-00 1

• GA 56 Flange Mount Antenna Kit (Mod 1 or later, Garmin P/N 010-10040-02). This kit contains the following items:

ITEM GARMIN P/N QTY

FLANGE MOUNT GA 56 ANTENNA SUB-ASSEMBLY NUT PLATE 115-00080-00 1 SCREW, #10-32 x 5/8” 211-62212-14 4 ANTENNA GASKET 253-00011-00 1

2. Other accessories include the following:

ITEM GARMIN P/N

MOUNTING RACK, 400/420/430 115-00243-00 GPS 400 BACK PLATE ASSEMBLY 011-00676-03 GPS 400 CONNECTOR KIT 011-00351-03 GNC 420 BACK PLATE ASSEMBLY 011-00676-01 GNC 420 CONNECTOR KIT 011-00351-01 GNS 430 BACK PLATE ASSEMBLY 011-00676-00 GNS 430 CONNECTOR KIT 011-00351-00 400 SERIES ADDENDUM FOR TRAFFIC & WEATHER INTERFACES GPS 400 PILOT’S GUIDE 190-00140-60 GPS 400 QUICK REFERENCE GUIDE 190-00140-61 GPS 400 SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT GNC 420 PILOT’S GUIDE 190-00140-20 GNC 420 QUICK REFERENCE GUIDE 190-00140-21 GNC 420 SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT GNS 430 PILOT’S GUIDE 190-00140-00 GNS 430 QUICK REFERENCE GUIDE 190-00140-01 GNS 430 SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT

190-00140-10

190-00140-64

190-00140-24

190-00140-04

011-00147-00 1

NOTE

A mounting rack is required for approved installations. The following hardware is required for installation of the mounting rack, but is not provided--#6-32 Flat Head Screw (6 ea.), #6-32 Self-locking Nut (6 ea.).

400 SERIES INSTALLATION MANUAL Page 3-3 P/N 190-00140-02 Page Rev L

Page 24

3.2 DATA BASE OPTIONS

ITEM GARMIN P/N

DATA CARD, WORLD WIDE 010-10201-00 DATA CARD, AMERICAS 010-10201-01 DATA CARD, INTERNATIONAL 010-10201-02

3.3 MISCELLANEOUS OPTIONS

ITEM GARMIN P/N

CONNECTOR, BNC, MALE, CLAMP 330-00087-00 LOW-LOSS AVIATION ANTENNA EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR, 15 FT. LOW-LOSS AVIATION ANTENNA EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR, 30 FT. GPS 1.57542 GHz NOTCH FILTER 330-00067-00

320-00003-00

320-00003-02

3.4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED

The following installation accessories are required but not provided:

COM Antenna: (GNC 420 and GNS 430 Only) Shall meet TSO C37() and C38(). Broad band, 50

Ω, vertically polarized with coaxial cable

VOR/LOC Antenna: (GNS 430 Only) Shall meet TSO C40() and C36(). Broad band, 50 Ω,

horizontally polarized with coaxial cable

Glideslope Antenna: (GNS 430 Only) Shall meet TSO C34(). Broad band, 50 Ω, horizontally polarized

with coaxial cable or low-loss splitter used with the VOR/LOC antenna Headphones: (GNC 420 and GNS 430 Only) 500 Ω nominal impedance Microphone: (GNC 420 and GNS 430 Only) Low impedance, carbon or dynamic, with

transistorized pre-amp

3.5 ANTENNA INSTALLATION

For the COM, VOR/LOC, and Glideslope antennas, follow the manufacturers’ instructions.

The remainder of this section applies to the GPS antenna. The GA 56 antenna outline and footprint dimensions are shown in Figure 3-2, page 3-9. Also refer to 190-00094-00 GA 56 Antenna Installation Instructions.

1. Using the backing plate as a template, mark the location of the mounting holes and the through hole for coaxial cable. Drill or punch the holes.

2. The antenna installation must provide adequate support for the antenna, considering a maximum drag load of 5 lbs. for the GA 56 antennas (at subsonic speed). Install a doubler plate to reinforce thin-skinned aircraft. Observe guidelines for acceptable installation practices as outlined in AC 43.13-2A.

Seal the antenna and gasket to the fuselage using a good quality electrical grade sealant. Use caution to insure that the antenna connector is not contaminated with sealant. Insure that the mounting screws are fully tightened and that the antenna base is well seated against the gasket.

CAUTION

Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may damage the electrical connections to the antenna. Use of these type sealants may void the antenna warranty.

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Page 25

3.6 CABLE INSTALLATION

1. Route the coaxial cable to the rack location keeping in mind the recommendations of Section 2. Secure the cable in accordance with good aviation practice.

2. Trim the coaxial cable to the desired length and install the BNC connector (330-00087-00) per the cabling instructions on Figure 3-1. If the connector is provided by the installer, follow the connector manufacturer’s instructions for cable preparation.

Figure 3-1. Coaxial Cable Installation

3. The card-edge connector may be used to terminate shield grounds to the 400 Series back plate.

CAUTION

4. Feed wires through the connector backshells before insertion into the 78, 44, and 25 pin connectors.

5. Contacts for the 78, 44 and 25 pin connectors must be crimped onto the individual wires of the aircraft wiring harness. The following tables list contact part numbers (for reference) and recommended crimp tools:

Table 3-1. Pin Contact Part Numbers

78 pin conn

(P4001) Connector Type High Density Pin Contact Standard Density Socket Contact .1” Pitch Card-edge Wire Gauge 22-28 AWG 18 AWG 20-24 AWG 20-24 AWG Garmin P/N 336-00021-00 336-00023-00 336-00022-00 336-00029-00 Military P/N M39029/58-360 N/A M39029/63-368 N/A AMP 204370-2 N/A 205090-1 583853-4 Positronic M39029/58-360 FC6018D M39029/63-368 N/A ITT Cannon 030-2042-000 See Note 3 031-1007-042 N/A

400 SERIES INSTALLATION MANUAL Page 3-5 P/N 190-00140-02 Page Rev L

44 pin conn

(P4006)

25 pin connector (P4002) Shield ground

connector

Page 26

Table 3-2. Recommended Crimp Tools (or equivalent)

Connector Type Wire Gauge 22-28 AWG 18 AWG 20-24 AWG

Hand

Crimping

Tool

Military P/N M22520/2-01 M22520/2-09 M81969/1-04 N/A M81969/1-02 M22520/2-08 M81969/1-02 Positronic 9507 9502-3 M81969/1-04 9502-11 M81969/1-02 9502-5 M81969/1-02 ITT Cannon 995-0001-

584 AMP 601966-1 601966-6 91067-1 N/A N/A 601966-5 91067-2 Daniels AFM8 K42 M81969/1-04 K774 M81969/1-02 K13-1 M81969/1-02 Astro 615717 615725 M81969/1-04 N/A M81969/1-02 615724 M81969/1-02

High Density Standard Density

Positioner Insertion/

995-0001-

739

Extraction

Tool

N/A N/A N/A 995-0001-

Positioner Insertion/

Extraction

Tool

Positioner Insertion/

604

Extraction

Tool

980-2000-

426

NOTES

1. Insertion/extraction tools from ITT Cannon are all plastic; others are plastic with metal tip.

2. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.

3. Alternate contacts for 18 AWG wire: As an alternative to the Positronic contacts listed (and provided in the installation kit), the installer may use contacts made by ITT Cannon under P/N 031-1007-001. These contacts require the use of a different crimp tool positioner than shown in the table, with the part numbers as follows: Daniels P/N K250, Astro P/N 616245, or ITT Cannon P/N 980-0005-722.

4. For the card-edge connector pin contacts, use AMP part number 90272-1 or equivalent crimping tool.

3.7 RACK INSTALLATION

1. The back plate of the rack may optionally be removed for ease of mounting in the aircraft panel. To do so, remove the two #4-40 screws, tilt the back plate away from the tray, and then slide the back plate to the side.

2. Figures 3-3, 3-4 and 3-5, starting on pages 3-11, 3-13, and 3-15, show outline dimensions for the aviation rack for the various 400 Series units. Install the rack in a rectangular 6.320” x

2.700” hole (or gap between units) in the instrument panel (refer to Figure 3-9, page 3-23). The lower-front lip of the rack should be flush with, or extend slightly beyond, the finished aircraft panel.

CAUTION

If the front lip of the mounting rack is behind the surface of the aircraft panel, the 400 Series unit connectors may not fully engage.

Make sure that no screw heads or other obstructions prevent the unit from fully engaging in the rack (refer to the “Connector Engagement Test,” section 5.3.1, page 5-15). Exercise caution when installing the rack into the instrument panel. The rack is designed to facilitate removal of the 400 Series for use in Demo Mode outside the aircraft. Deformation of the rack may make it difficult to install and remove the 400 Series unit.

3. Install the rack in the aircraft panel using six #6-32 flat head screws and six self-locking nuts. The screws are inserted from the inside through the holes in the sides of the rack.

4. If the back plate was previously removed (see step #1), replace the back plate by positioning the tabs on the back plate in the slots of the left side of the rack (viewing it from the cockpit) and attaching it by replacing the two #4-40 screws.

Page 3-6 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Page 27

3.8 400 SERIES UNIT INSERTION AND REMOVAL

The 400 Series unit is installed in the rack by sliding it straight in until it stops, about 1 inch short of the final position. A 3/32“ hex drive tool is then inserted into the access hole at the bottom of the unit face. Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly seated in the rack. It may be necessary to insert the hex drive tool into the access hole and rotate the mechanism 90° counterclockwise to insure correct position prior to placing the unit in the rack.

To remove the unit from the rack, insert the hex drive tool into the access hole on the unit face and rotate counterclockwise until the unit is forced out about 3/8 ” and can be freely pulled from the rack.

Be sure not to over tighten the unit into the rack. The application of hex drive tool torque exceeding 15 in•lbs can damage the locking mechanism.

3.9 COM ANTENNA INSTALLATION CHECK (GNC 420 AND GNS 430)

Check for insertion loss and VSWR (voltage standing wave ratio). VSWR should be checked with an inline type VSWR/wattmeter inserted in the coaxial transmission line between the transceiver and the antenna. The VSWR should be inserted as close to the transceiver as possible. When rack and harness buildup is performed in the shop, the coax termination may be provisioned by using a 6” inline BNC connection. This would be an acceptable place to insert the VSWR. Any problem with the antenna installation is most likely seen as high reflected power. A VSWR of 3:1 may result in up to a 50% loss in transmit power.

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P/N 190-00140-02 Page Rev L

400 SERIES INSTALLATION MANUAL Page 3-9 (Page 3-10 blank)

3.10 GA 56 Antenna Installation Drawing

Figure 3-2. GA 56 Antenna Installation Drawing

Page 30

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400 SERIES INSTALLATION MANUAL Page 3-11 (Page 3-12 blank)

3.11 Mounting Rack Dimensions

Figure 3-3. GNS 430 Mounting Rack Dimensions

Page 31

P/N 190-00140-02 Page Rev L

400 SERIES INSTALLATION MANUAL Page 3-13 (Page 3-14 blank)

Figure 3-4. GNC 420 Mounting Rack Dimensions

Page 32

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400 SERIES INSTALLATION MANUAL Page 3-15 (Page 3-16 blank)

Figure 3-5. GPS 400 Mounting Rack Dimensions

Page 33

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400 SERIES INSTALLATION MANUAL Page 3-17 (Page 3-18 blank)

3.12 Mounting Rack Installation

Figure 3-6. GNS 430 Mounting Rack Installation

Page 34

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400 SERIES INSTALLATION MANUAL Page 3-19 (Page 3-20 blank)

Figure 3-7. GNC 420 Mounting Rack Installation

Page 35

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400 SERIES INSTALLATION MANUAL Page 3-21 (Page 3-22 blank)

Figure 3-8. GPS 400 Mounting Rack Installation

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400 SERIES INSTALLATION MANUAL Page 3-23 (Page 3-24 blank)

3.13 Recommended Panel Cutout Dimensions

Figure 3-9. 400 Series Recommended Panel Cutout Dimensions

Page 37

4. SYSTEM INTERCONNECTS

4.1 PIN FUNCTION LIST

4.1.1 P4001

View of J4001 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

21 22 23 24 25 26 27

1 2 3 4 5 6 7 8 9 10 111213 14151617181920

Pin Pin Name I/O

1 VLOC ANNUNCIATE Out 2 GPS ANNUNCIATE Out 3 WAYPOINT ANNUNCIATE Out 4 TERMINAL ANNUNCIATE Out 5 APPROACH ANNUNCIATE Out 6 MESSAGE ANNUNCIATE Out 7 OBS ANNUNCIATE Out 8 AUTO ANNUNCIATE Out

9 INTEGRITY ANNUNCIATE Out 10 ANNUNCIATE D Out 11 ANNUNCIATE E Out 12 ALTITUDE ALARM ANNUNCIATE (Not implemented at time of publication) Out 13 ANNUNCIATE F (Not implemented at time of publication) Out 14 ILS/GPS APPROACH Out 15 AIRCRAFT POWER 2* In 16 TIME MARK OUT Out 17 MAIN LATERAL SUPERFLAG Out 18 MAIN VERTICAL SUPERFLAG Out 19 AIRCRAFT POWER 1 In 20 AIRCRAFT POWER 1 In 21 MAIN +LEFT Out 22 MAIN +RIGHT (2.5V COMMON) Out 23 MAIN LATERAL +FLAG Out 24 MAIN LATERAL -FLAG (2.5V COMMON) Out 25 MAIN +TO Out 26 MAIN +FROM (2.5V COMMON) Out 27 MAIN +UP Out 28 MAIN +DOWN (2.5V COMMON) Out 29 MAIN VERTICAL +FLAG Out 30 MAIN VERTICAL -FLAG (2.5V COMMON) Out 31 MAIN OBS ROTOR C Out 32 MAIN OBS ROTOR H (GROUND) Out 33 MAIN OBS STATOR D In 34 MAIN OBS STATOR E (2.5V COMMON OBS) Out 35 MAIN OBS STATOR F In 36 MAIN OBS STATOR G (2.5V COMMON OBS) Out

43 44 45 46 47 48 49 50 51 52 53 54 55 565758 59

41 42

30 31 32 33 34 35 36 37 38 39

28 29

* Applies only to part numbers 011-00280-30 (GNS 430), 011-00836-10 (GNS 430A), 011-00506-30 (GNC 420), 011-00837-10 (GNC 420A) and 011-00504-10 (GPS 400). For applications requiring secondary or alternate power bus input.

400 SERIES INSTALLATION MANUAL Page 4-1 P/N 190-00140-02 Page Rev L

Page 38

Connector P4001, continued

Pin Pin Name I/O

37 ALTITUDE ALARM AUDIO HI (Not implemented at time of publication) Out 38 ALTITUDE ALARM AUDIO LO (Not implemented at time of publication) Out 39 LIGHTING BUS HI In 40 LIGHTING BUS LO In 41 GPS RS 232 OUT 3 In 42 GPS RS 232 IN 3 Out 43 MAIN OBI CLOCK Out 44 MAIN OBI DATA Out 45 MAIN OBI SYNC Out 46 GPS ARINC 429 OUT A Out 47 GPS ARINC 429 OUT B Out 48 GPS ARINC 429 IN 1 A In 49 GPS ARINC 429 IN 1 B In 50 GPS ARINC 429 IN 2 A In 51 GPS ARINC 429 IN 2 B In 52 RESERVED -53 RESERVED -54 GPS RS 232 OUT 4 Out 55 GPS RS 232 IN 4 In 56 GPS RS 232 OUT 1 Out 57 GPS RS 232 IN 1 In 58 GPS RS 232 OUT 2 Out 59 GPS RS 232 IN 2 In 60 ALTITUDE COMMON (GROUND) Out 61 ALTITUDE C4 In 62 ALTITUDE C2 In 63 ALTITUDE C1 In 64 ALTITUDE B4 In 65 ALTITUDE B2 In 66 ALTITUDE B1 In 67 ALTITUDE A4 In 68 ALTITUDE A2 In 69 ALTITUDE A1 In 70 ALTITUDE D4 In 71 OBS MODE SELECT In 72 AIRCRAFT POWER 2* In 73 CDI SOURCE SELECT In 74 RESERVED -75 DEMO MODE SELECT In 76 RESERVED -77 AIRCRAFT GROUND -78 AIRCRAFT GROUND --

Page 4-2 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Page 39

4.1.2 P4002 (GNC 420 and GNS 430 Only)

View of J4002 connector from back of unit

4321

161514

12111098765

23222120191817

Pin Pin Name I/O

1 RESERVED --

2 RESERVED --

3 RESERVED --

4 COM MIC KEY In

5 INTERCOM MIC HI In

6 COM MIC AUDIO HI In

500Ω COM AUDIO HI 8 RESERVED -9 RESERVED --

10 RESERVED -11 AIRCRAFT POWER In 12 AIRCRAFT POWER In 13 RESERVED -14 TRANSMIT INTERLOCK In 15 COM REMOTE TRANSFER In 16 SPARE -17 INTERCOM MIC LO In 18 COM MIC AUDIO LO In 19

500Ω COM AUDIO LO

20 RESERVED -21 AIRCRAFT GROUND -22 AIRCRAFT GROUND -23 RESERVED -24 RESERVED -25 RESERVED --

Out

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Page 40

4.1.3 P4006 (GNS 430 Only)

View of J4006 connector from back of unit

123456789101112131415

161718192021222324252627282930

404142

313233343536373839

Pin Pin Name I/O

1 VOR/LOC +TO Out 2 VOR/LOC +FROM (VOR/LOC COMMON) Out 3 VOR/LOC +FLAG Out 4 VOR/LOC -FLAG (VOR/LOC COMMON) Out 5 VOR/LOC +LEFT Out 6 VOR/LOC +RIGHT (VOR/LOC COMMON) Out 7 RESERVED -8 VOR/LOC COMPOSITE OUT Out 9 VOR OBS ROTOR C Out

10 VOR OBS ROTOR H (GROUND) Out 11 VOR OBS STATOR E/G (VOR/LOC COMMON) In 12 VOR OBS STATOR F In 13 VOR OBS STATOR D In 14 PARALLEL DME - 8MHZ Out 15 VOR/LOC SUPERFLAG Out 16

500Ω VOR/ILS AUDIO HI

500Ω VOR/ILS AUDIO LO

18 SERIAL DME CLOCK Out 19 SERIAL DME DATA Out 20 SER DME - CHAN REQ/PAR DME - 4MHZ I/O 21 SER DME - RNAV MODE/PAR DME - 2MHZ I/O 22 DME COMMON In 23 VOR/ILS ARINC 429 OUT B Out 24 VOR/ILS ARINC 429 OUT A Out 25 VOR OBI CLOCK Out 26 VOR OBI SYNC Out 27 VOR OBI DATA Out 28 VLOC REMOTE TRANSFER In 29 ILS ENERGIZE Out 30 GLIDESLOPE +FLAG Out 31 GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE COMMON) Out 32 GLIDESLOPE +UP Out 33 PARALLEL DME - 1MHZ Out 34 RESERVED -35 VOR/ILS ARINC 429 IN B In 36 VOR/ILS ARINC 429 IN A In 37 PARALLEL DME - 800KHZ Out 38 GLIDESLOPE SUPERFLAG Out 39 PARALLEL DME - 400KHZ Out 40 PARALLEL DME - 200KHZ Out 41 AIRCRAFT GROUND -42 PARALLEL DME - 100KHZ Out 43 PARALLEL DME - 50KHZ Out 44 AIRCRAFT POWER In

Out Out

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Page 41

4.2 POWER, LIGHTING, AND ANTENNAS

4.2.1 Power, Lighting, and Antennas Function

The section covers the Power Input requirements, Lighting Bus input, and Antenna connections.

4.2.2 Power, Lighting, and Antennas Electrical Characteristics

4.2.2.1 Aircraft Power

Pin Name Connector Pin I/O

AIRCRAFT POWER 1 P4001 19 In AIRCRAFT POWER 1 P4001 20 In AIRCRAFT POWER 2 * P4001 15 In AIRCRAFT POWER 2 * P4001 72 In AIRCRAFT POWER P4002 11 In AIRCRAFT POWER P4002 12 In AIRCRAFT POWER P4006 44 In AIRCRAFT GROUND P4001 77 -AIRCRAFT GROUND P4001 78 -AIRCRAFT GROUND P4002 21 -AIRCRAFT GROUND P4002 22 -AIRCRAFT GROUND P4006 41 --

* Optional alternate power, applies only to part numbers 011-00280-30 GNS 430, 011-00836-10 GNS 430(A, 01100506-30 GNC 430, 011-00837-10 GNC 420(A), and 011-00504-10 (GPS 400).

CAUTION

To operate the GNC 420 P/N 011-00506-00 or GNS 430 P/N 011-00280-00 COM transceiver in a 14-volt aircraft, a 14 to 28 volt converter such as a KGS Electronics models RB-126 or UC-14-28 or equivalent must be used. The voltage converter should include a circuit breaker on its output to supply power to P4002-11 and P4002-12 for the COM transmitter. The other power input pins (P4001-19, P4001-20, and P4006-44) accept 11-33 V

on all power inputs. Refer to Figure 4-5 on page 4-29.

A power connection on P4006-44 is only required if NAV SUPERFLAG and/or G/S SUPERFLAG is utilized.

The power inputs P4001-19 and P4001-20 provide power for all functions of the 400 Series unit except the COM transmitter and the NAV & G/S SUPERFLAG outputs.

4.2.2.2 Lighting Bus

Pin Name Connector Pin I/O

LIGHTING BUS HI P4001 39 In LIGHTING BUS LO P4001 40 In

The 400 Series unit can be configured to track 28 VDC, 14 VDC, 5 VDC or 5 VAC lighting buses using these inputs. Alternatively, the 400 Series unit can automatically adjust for ambient lighting conditions based on the photocell. Refer to section 5.2.5.

4.2.2.3 Antennas

Pin Name Connector I/O

GPS ANTENNA P4003 In COM ANTENNA P4004 I/O VOR/LOC ANTENNA P4005 In GLIDESLOPE ANTENNA P4007 In

. GNC 420 P/N 011-00506-10 and GNS 430 P/N 011-00280-10 accept 11-33

400 SERIES INSTALLATION MANUAL Page 4-5 P/N 190-00140-02 Page Rev L

Page 42

4.2.3 Power, Lighting, and Antennas Configuration

Refer to section 5.2.6 for lighting configuration.

4.2.4 Power, Lighting, and Antennas Calibration and Checkout

Refer to section 3.9 for the COM antenna checkout.

4.2.5 Power, Lighting, and Antennas Interconnect

Refer to Figure 4-5 on page 4-29 for the power, lighting, and antennas interconnect.

4.3 ALTIMETER

4.3.1 Altimeter Function

Altitude input is required for GPS RAIM calculations, and is useful for advisory vertical navigation (VNAV) calculations.

4.3.2 Altimeter Electrical Characteristics

Pin Name Connector Pin I/O

ALTITUDE D4 P4001 70 In ALTITUDE A1 P4001 69 In ALTITUDE A2 P4001 68 In ALTITUDE A4 P4001 67 In ALTITUDE B1 P4001 66 In ALTITUDE B2 P4001 65 In ALTITUDE B4 P4001 64 In ALTITUDE C1 P4001 63 In ALTITUDE C2 P4001 62 In ALTITUDE C4 P4001 61 In ALTITUDE COMMON P4001 60 In

These inputs are considered active if either the voltage to ground is < 1.9 V or the resistance to ground is< 375 Ω. These inputs are considered inactive if the voltage to ground is 11-33 V

NOTE

Some transponders and other altitude encoder receivers do not have internal isolation diodes to prevent the unit from pulling the encoder lines to ground when the unit is off. These units require a diode added to the installation harness for each encoder line. The anode should be connected on the receiving unit’s side and the cathode should be connected on the encoder side. A set of diodes is required for each unit without internal diodes. The 400 Series unit includes internal diodes for isolation of the encoder lines.

4.3.3 Altimeter Configuration

Refer to section 5.2.2, MAIN RS232 CONFIG page configuring various serial data equipment.

4.3.4 Altimeter Checkout

Refer to section 5.2.3, MAIN INPUTS 1 Page.

4.3.5 Altimeter Interconnect

Refer to Figure 4-2, 4-3, 4-4 and 4-11 for the altimeter interconnect using gray code or RS232.

Page 4-6 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Page 43

4.4 MAIN INDICATOR

4.4.1 Main Indicator Function

The Main Indicator displays both lateral and vertical deviation from selected course, To/From indications, lateral and vertical flags and superflags.

The “CDI” key on the bezel of the GNS 430 takes the place of remote “NAV/GPS” switches, and is used to toggle between display of GPS and VOR/ILS navigation display on a remote indicator. The Navigation source is annunciated on the display above the ‘CDI’ key. The Navigation method is optionally annunciated externally by connecting to the VLOC ANNUNCIATE output (P4001-1) and GPS ANNUNCIATE output (P4001-2). GPS and VOR/ILS navigation may be toggled externally when the CDI SOURCE SELECT input (P4001-73) is momentarily grounded. See section 4.5 for more information on the external annunciators and switches.

An OBS resolver connection to the GPS is preferred, but not required. For the GNS 430, an OBS resolver typically is connected to the MAIN OBS inputs for use with the GNS 430 VOR receiver.

4.4.2 Main Indicator Electrical Characteristics

4.4.2.1 Deviation

Pin Name Connector Pin I/O

MAIN +LEFT P4001 21 Out MAIN +RIGHT (2.5V COMMON) P4001 22 Out MAIN +UP P4001 27 Out MAIN +DOWN (2.5V COMMON) P4001 28 Out

The deviation output is capable of driving up to three 1000 Ω meter loads with ±150 mVDC±10% for fullscale deflection. The drive circuit provides for more than full-scale deflection with a maximum course deviation output voltage of ±300 mV

±10%

4.4.2.2 TO/FROM

Pin Name Connector Pin I/O

MAIN +TO P4001 25 Out MAIN +FROM (2.5V COMMON) P4001 26 Out

The output is capable of driving up to three 200 Ω meter loads. When indicating TO, MAIN +TO is +190 ±40 mV

with respect to MAIN +FROM. When indicating FROM, MAIN +TO is -190 ±40 mV

with respect to MAIN +FROM. When invalid information is present (Flag IN VIEW) the TO/FROM output is 0 ±10 mV

DC.

4.4.2.3 Flag

Pin Name Connector Pin I/O

MAIN LATERAL +FLAG P4001 23 Out MAIN LATERAL -FLAG (2.5V COMMON) P4001 24 Out MAIN VERTICAL +FLAG P4001 29 Out MAIN VERTICAL -FLAG (2.5V COMMON) P4001 30 Out

The Flag output is capable of driving up to three 1000 Ω meter loads. When valid information is present (Flag OUT OF VIEW) the Flag output is 375 ±80 mV VIEW) the Flag output is 0 ±25 mV

DC.

When invalid information is present (Flag IN

DC.

400 SERIES INSTALLATION MANUAL Page 4-7 P/N 190-00140-02 Page Rev L

Page 44

4.4.2.4 Superflags

Pin Name Connector Pin I/O

MAIN LATERAL SUPERFLAG P4001 17 Out MAIN VERTICAL SUPERFLAG P4001 18 Out

The output supplies not less than 500 mA on a 28 volt system and 250 mA on a 14 volt system with the output voltage not less than (AIRCRAFT POWER –1.5 V output voltage with respect to ground is less than 0.25 V

) when the flag is to be OUT OF VIEW. The

when the flag is to be IN VIEW.

4.4.2.5 OBS

Pin Name Connector Pin I/O

MAIN OBS ROTOR C P4001 31 Out MAIN OBS ROTOR H (GROUND) P4001 32 Out MAIN OBS STATOR D P4001 33 In MAIN OBS STATOR E (2.5V COMMON OBS) P4001 34 Out MAIN OBS STATOR F P4001 35 In MAIN OBS STATOR G (2.5V COMMON OBS) P4001 36 Out

MAIN OBS ROTOR C and H are a buffered output that is intended to drive the OBS rotors. MAIN OBS STATOR D and MAIN OBS STATOR F are each phase and amplitude shifted version of the MAIN ROTOR C output. Each pair is intended to read one of the two windings of the indicator’s OBS stator.

4.4.3 Main Indicator Configuration

Refer to section 5.2.10 for the main CDI/OBS configuration.

4.4.4 Main Indicator Calibration and Checkout

Refer to section 5.2.10 for the main CDI/OBS checkout.

4.4.5 Main Indicator Interconnect

Refer to Figure 4-7 on page 4-33 for the generic main indicator interconnect. Refer to Figure 4-8 on page 4-35 for the interconnect between a GNS 430 and a Bendix/King KI 209A. Refer to Figure 4-9 on page 437 for the interconnect between a GPS 400 or GNC 420 and a Bendix/King KI 208A.

Page 4-8 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Page 45

4.5 ANNUNCIATORS/SWITCHES

4.5.1 Annunciators/Switches Function

NOTE

Initial certification of the 400 Series units was accomplished without use of any remote switches or annunciators, since the same switching and annunciation is available on the front panel of the 400 Series unit. However, if the 400 Series unit is not installed in the pilot’s normal field of view, some or all

of the remote switches and annunciators may be required by your certification agency. Appendix B includes an FAA letter granting permission to install GNS 430 without external switches and annunciators.

4.5.1.1 MESSAGE ANNUNCIATE

When a new status message is available, the Message Annunciator flashes. When status messages remain effective, the Message Annunciator illuminates.

4.5.1.2 WAYPOINT ANNUNCIATE

The waypoint annunciator output is driven in the following manner:

1. When the aircraft is within 10 seconds of reaching the turning point for a course change, the waypoint annunciator flashes.

2. When the aircraft is in a turn, the waypoint annunciator illuminates and remains illuminated until the turn is completed.

3. When a user arrival alarm is set and the aircraft is within the circle defined by the arrival alarm radius at the arrival waypoint, the waypoint annunciator flashes for 10 seconds.

4. When a user arrival alarm is not set and the aircraft is within 10 seconds of reaching the arrival waypoint, the waypoint annunciator flashes.

4.5.1.3 CDI SOURCE SELECT (GNS 430 Only)

This discrete input may be used to toggle between display of GPS and VOR/LOC/Glideslope information on the MAIN external CDI/HSI. A momentary low on this pin performs the same function as pressing the ‘CDI’ key on the GNS 430 bezel.

4.5.1.4 VLOC ANNUNCIATE (GNS 430 Only)

This annunciator output is driven when the unit is configured with a single CDI/HSI and the VOR/ILS data is being displayed on the CDI/HSI. This output parallels the VLOC annunciator on the display.

4.5.1.5 GPS ANNUNCIATE (GNS 430 Only)

This annunciator output is driven when the unit is configured with a single CDI/HSI and the GPS data is being displayed on the CDI/HSI. This output parallels the GPS annunciation on the display.

4.5.1.6 OBS MODE SELECT

This discrete input may be used to toggle between GPS OBS and GPS AUTO modes of operation. A momentary low on this pin performs the same function as pressing the ‘OBS’ key on the 400 Series unit.

4.5.1.7 AUTO ANNUNCIATE

This annunciator output is driven to indicate GPS AUTO mode of operation. This output is active when neither the OBS nor SUSP annunciations are on the display.

4.5.1.8 OBS ANNUNCIATE

This annunciator output is driven to indicate GPS OBS mode of operation. This output is active when the OBS or SUSP annunciation is on the display.

4.5.1.9 TERMINAL ANNUNCIATE

When performing approach navigation, the terminal annunciator is illuminated when operating within 30 nautical miles of the departure or arrival airport and the CDI scale is the equivalent or 1.0 nm or less.

4.5.1.10 APPROACH ANNUNCIATE

When performing approach navigation, the approach annunciator illuminates when approach is active.

4.5.1.11 INTEGRITY ANNUNCIATE

The integrity annunciator illuminates when the GPS receiver detects a position error, or is unable to calculate the integrity of the position.

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Page 46

4.5.1.12 ILS/GPS APPROACH Output

Sinks 500 mA when GPS navigation is selected and GPS approach is active or when VLOC navigation is selected and an ILS channel has been selected. This output may be connected to the ILS Engage input of an autopilot or flight director to provide higher autopilot gain while the 400 Series unit is operating in the ILS or GPS Approach modes of operation.

4.5.1.13 DEMO MODE SELECT

This discrete input may be used to select Demo Mode on the 400 Series unit. A low on this pin at time of unit power-up invokes the Demo Mode. Demo Mode allows the 400 Series unit to simulate reception of GPS satellite signals.

CAUTION

Do not connect DEMO MODE SELECT in an aircraft installation.

4.5.1.14 TIME MARK OUT

Time Mark Out is a time reference pulse output once per second, derived from GPS satellite signals.

4.5.2 Annunciators/Switches Electrical Characteristics

4.5.2.1 Annunciators

Pin Name Connector Pin I/O

VLOC ANNUNCIATE P4001 1 Out GPS ANNUNCIATE P4001 2 Out WAYPOINT ANNUNCIATE P4001 3 Out TERMINAL ANNUNCIATE P4001 4 Out APPROACH ANNUNCIATE P4001 5 Out MESSAGE ANNUNCIATE P4001 6 Out OBS ANNUNCIATE P4001 7 Out AUTO ANNUNCIATE P4001 8 Out INTEGRITY ANNUNCIATE P4001 9 Out ILS/GPS APPROACH P4001 14 Out

All outputs sink up to 500 mA when activated.

4.5.2.2 Switch Inputs

Pin Name Connector Pin I/O

OBS MODE SELECT P4001 71 In CDI SOURCE SELECT P4001 73 In DEMO MODE SELECT P4001 75 In

These inputs are considered active if either the voltage to ground is < 1.9 V or the resistance to ground is < 375 Ω. These inputs are considered inactive if the voltage to ground is 11-33 V

4.5.2.3 TIME MARK OUT

Pin Name Connector Pin I/O

TIME MARK OUT P4001 16 Out

TIME MARK OUT outputs a 1 ms ± 1 µs wide pulse once every 1.0 s ± 2 ms. TIME MARK OUT is a logic level output, capable of sourcing 1 mA at up greater than 3.8 V and sinking 1 mA at less than 0.4 V.

4.5.3 Annunciators/Switches Configuration

None.

4.5.4 Annunciators/Switches Calibration and Checkout

Refer to section 5.2.8 for the switches checkout. Refer to section 5.2.9 for the annunciators checkout.

4.5.5 Annunciators/Switches Interconnect

Refer to Figure 4-10 on page 4-39 for the annunciators/switches interconnect.

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Page 47

4.6 SERIAL DATA

4.6.1 Serial Data Function

4.6.1.1 RS-232

The 400 Series unit is capable of interfacing with other aviation instruments by transmitting RS-232 Type 1 (often known as ARNAV format) and Type 2 (often known as Northstar format) data on the GPS RS 232 OUT 1 port. The data consists of the following (refer to Appendix C for a detailed data format description):

Current latitude, longitude, and GPS altitude in feet (see Note below) Current velocity vector (ground speed and direction of velocity vector over the ground) Distance, bearing, desired track, and cross track error to destination waypoint Destination waypoint identifier, sequence in route, position (latitude and longitude), and magnetic variation Magnetic variation and navigation and warning status

NOTE

Aviation RS-232 data may be transmitted with or without the current GPS altitude in feet. Refer to section

5.2.2.

The 400 Series unit can receive pressure altitude, air data, and fuel data from certain systems on the GPS RS 232 IN 1 port.

The 400 Series unit can communicate with a Ryan TCAD 9900B system using the GPS RS 232 OUT 2 and GPS RS 232 IN 2 lines to display traffic information on the 400 Series unit.

If two 400 Series units are installed in an aircraft, the GPS RS 232 OUT 3 and GPS RS 232 IN 3 lines may be cross-connected to crossfill flight plans and user-defined waypoints from one 400 Series unit to the other.

The 400 Series unit can communicate with a BF Goodrich WX-500 Stormscope using the GPS RS 232 OUT 4 and GPS RS 232 IN 4 lines to display lightning strike information on the 400 Series unit.

4.6.1.2 ARINC 429

The data output on the GPS ARINC 429 OUT port depends on the configuration (refer to section 5.2.1). Below is a list of the configurations and the labels output for each one:

1. ARINC 429

2. GAMA 429

3. GAMA 429 Graphics

4. GAMA 429 Graphics w/Int

Label # Parameter Name 1234

001 Distance to Go (BCD) •••• 002 Time to Go (BCD) ••••

012 Ground Speed (BCD) •••• 074G Data Record Header • • • 075G Active Wpt From/To Data • • •

100 Selected Course 1 • 100G Selected Course 1 • • • 113G Message Checksum • • •

114 Desired Track (True) ••••

115 Waypoint Bearing (True) ••••

116 Cross Track Distance • 116G Cross Track Distance • • •

121 Horizontal Command (to Autopilot) ••••

125 Greenwich Mean Time (BCD) •••• 147G Magnetic Variation • • •

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Label # Parameter Name 1234

251 Distance to Go • 251G Distance to Go • • •

252 Time to Go •••• 260G Date (BCD) • • • 261G GPS Discrete Word 1 • • • 275G LRN Status Word • • • 300G Station Declination, Type, and Class • • •

303 Message Length/Type/Number • • • 304G Message Characters 1-3 • • • 305G Message Characters 4-6 • • • 306G NAV/Waypoint/Airport Latitude • • • 307G NAV/Waypoint/Airport Longitude • • •

310 Present Position Latitude ••••

311 Present Position Longitude ••••

312 Ground Speed ••••

313 Track Angle (True) ••••

314 True Heading ••••

315 Wind Speed ••••

316 Wind Angle (True) ••••

320 Magnetic Heading ••••

321 Drift Angle •••• 326G Lateral Scale Factor • • •

330 Conic Arc Inbound Course • •

331 Conic Arc Radius • •

332 Conic Arc Course Change Angle • •

333 Airport Runway Azimuth • •

334 Airport Runway Length in Feet • •

335 Left/Right Hand Holding Pattern Azimuth • •

340 Left/Right Hand Procedure Turn Azimuth • • 351G Distance To Destination (Via Flight Plan) • • • 352G Estimated Time To Destination (Via Flight Plan) • • • 371G Specific Equipment ID • • •

377 Equipment Hex ID Code ••••

The following labels are output on the VOR/ILS ARINC 429 OUT port:

Label # Parameter Name

034G VOR/ILS Frequency (BCD) 035G DME Frequency (BCD) 100G Selected Course #1

173 Localizer Deviation 174 Glideslope Deviation 222 VOR Omnibearing

371G Specific Equipment ID

377 Equipment Hex ID Code

The labels recognized on the GPS ARINC 429 IN 1 or GPS ARINC 429 IN 2 ports depend on the configuration (refer to section 5.2.1).

The 400 Series unit can receive traffic data from a BF Goodrich SKY497 Skywatch system using the GPS ARINC 429 IN 1 or GPS ARINC 429 IN 2 lines, in order to display traffic information on the 400 Series unit.

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4.6.2 Serial Data Electrical Characteristics

4.6.2.1 RS-232

Pin Name Connector Pin I/O

GPS RS 232 OUT 1 P4001 56 Out GPS RS 232 IN 1 P4001 57 In GPS RS 232 OUT 2 P4001 58 Out GPS RS 232 IN 2 P4001 59 In GPS RS 232 OUT 3 P4001 41 Out GPS RS 232 IN 3 P4001 42 In GPS RS 232 OUT 4 P4001 54 Out GPS RS 232 IN 4 P4001 55 In

The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ± 5 V when driving a standard RS-232 load.

4.6.2.2 ARINC 429

Pin Name Connector Pin I/O

GPS ARINC 429 OUT A P4001 46 Out GPS ARINC 429 OUT B P4001 47 Out GPS ARINC 429 IN 1 A P4001 48 In GPS ARINC 429 IN 1 B P4001 49 In GPS ARINC 429 IN 2 A P4001 50 In GPS ARINC 429 IN 2 B P4001 51 In VOR/ILS ARINC 429 OUT A P4006 24 Out VOR/ILS ARINC 429 OUT B P4006 23 Out VOR/ILS ARINC 429 IN A P4006 36 In VOR/ILS ARINC 429 IN B P4006 35 In

The GPS and VOR/ILS ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers.

4.6.3 Serial Data Configuration

Refer to section 5.2.1 for the main (GPS) ARINC 429 configuration. Refer to sections 5.2.15, 5.2.16, and

5.2.1.7 for the Stormscope configuration. Refer to section 5.2.18 for the Skywatch configuration. Refer to sections 5.2.18 and 5.2.19 for the TCAD configuration. If the GDL 49 satellite data link transceiver has been installed, refer to the GDL 49 Installation Manual (190-00231-00) for Configuration Mode Operations.

4.6.4 Serial Data Calibration and Checkout

Refer to section 5.3.2 for the serial data checkout. Refer to sections 5.2.15, 5.2.16, and 5.2.17 for the Stormscope checkout. Refer to section 5.2.18 for the Skywatch checkout. Refer to sections 5.2.18 and

5.2.19 for the TCAD checkout.

4.6.5 Serial Data Interconnect

Refer to Figure 4-11 on page 4-41 for the RS-232 serial data interconnect. Refer to Figure 4-12 on page 443 for the ARINC 429 Bendix/King EFS 40/50 interconnect. Refer to Figures 4-13, 4-14 and 4-15 starting on page 4-45 for the ARINC 429 Sandel EHSI interconnects. Refer to Figure 4-16 on page 4-51 for the ARINC 429 air data/IRU/AHRS interconnect. Refer to Figure 4-17 on page 4-53 for the ARINC 429 flight control interconnect. Refer to Figure 4-18 on page 4-55 for the Traffic Advisory System Interconnect. Refer to Figure 4-19 on page 4-57 for the Weather and Terrain Interconnect. Refer to Figure 4-19 on page 4-57 for RS-232 serial data interconnects with the GARMIN GDL 49 Satellite Data Link Transceiver.

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4.7 COM/VOR/ILS AUDIO (GNC 420 AND GNS 430 ONLY)

4.7.1 COM/VOR/ILS Audio Function and Emergency Mode

Activation of COM MIC KEY enables COM MIC AUDIO and causes the transceiver to transmit.

500Ω COM AUDIO and 500Ω VOR/ILS AUDIO are 100 mW audio outputs that are intended to drive a headset or an audio panel.

Momentarily depressing the COM REMOTE TRANSFER button toggles the active and standby COM frequencies. Momentarily depressing the VLOC REMOTE TRANSFER button toggles the active and standby VLOC frequencies.

The COM REMOTE TRANSFER input may be used for EMERGENCY operation of the COM transmitter. If the remote transfer switch is depressed for two seconds, the active COM frequency changes to 121.50 MHz. Once the emergency frequency is activated through COM REMOTE TRANSFER, GNS 430 and GNC 420 COM transceivers with Mod 2 incorporated ignores inputs from the front panel controls for COM selections only. The pilot may exit this independent mode—restoring COM selection control to the front panel knobs and buttons—by momentarily depressing the COM REMOTE TRANSFER switch.

When TRANSMIT INTERLOCK is active, the GNC 420 or GNS 430 COM receiver sensitivity is decreased. This input is intended to reduce interference from other transmitters in the aircraft. The TRANSMIT INTERLOCK input should be connected to the PTT input of other transmitters in the aircraft. If connected to multiple PTT inputs, these connections must include diode isolation or multiple radios transmit simultaneously.

4.7.2 COM/VOR/ILS Audio Electrical Characteristics

4.7.2.1 COM MIC KEY

Pin Name Connector Pin I/O

COM MIC KEY P4002 4 In

This input is considered active if either the voltage to ground is < 1.9 V or the resistance to ground is< 375 Ω. This input is considered inactive if the voltage to ground is 11-33 V

4.7.2.2 COM MIC AUDIO, INTERCOM MIC AUDIO

Pin Name Connector Pin I/O

COM MIC AUDIO HI P4002 6 In COM MIC AUDIO LO P4002 18 In INTERCOM MIC HI P4002 5 In INTERCOM MIC LO P4002 17 In

COM MIC AUDIO and INTERCOM MIC each have a 520 Ω AC input impedance and supply the microphone with a 9 V bias through 620 Ω.

COM MIC AUDIO is set in the factory for 275 mV

to modulate the transmitter at 80% nominally. The

RMS

microphone gain adjustment is accessible through the top cover.

When a 125 mV AUDIO output is not less than 7.07 V

signal at 1000 Hz is applied to the INTERCOM MIC input, the level on the COM

RMS

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Page 51

4.7.2.3 COM AUDIO, VOR/ILS AUDIO

Pin Name Connector Pin I/O

500Ω COM AUDIO HI 500Ω COM AUDIO LO 500Ω VOR/ILS AUDIO HI 500Ω VOR/ILS AUDIO LO

P4002 7 Out P4002 19 Out P4006 16 Out P4006 17 Out

500Ω COM AUDIO and 500Ω VOR/ILS AUDIO each supply 100 mW into a 500 Ω load. These are balanced outputs and the LO output must be connected.

500Ω COM AUDIO is the summation of the COM receiver audio, COM sidetone audio, and INTERCOM MIC audio.

4.7.2.4 DISCRETE INPUTS

Pin Name Connector Pin I/O

TRANSMIT INTERLOCK P4002 14 In COM REMOTE TRANSFER P4002 15 In VLOC REMOTE TRANSFER P4006 28 In

These inputs are considered active if either the voltage to ground is < 1.9 V or the resistance to ground is < 375 Ω. These inputs are considered inactive if the voltage to ground is 11-33 V

COM REMOTE TRANSFER and VLOC REMOTE TRANSFER are momentary inputs.

4.7.3 COM/VOR/ILS Audio Configuration

None.

4.7.4 COM/VOR/ILS Audio Calibration and Checkout

Refer to section 5.2.11 for the COM calibration.

4.7.5 COM/VOR/ILS Audio Interconnect

Refer to Figure 4-20 on page 4-59 for the audio panel interconnect.

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4.8 VOR/ILS INDICATOR (GNS 430 ONLY)

4.8.1 VOR/ILS Indicator Function

NOTE

Because the GNS 430 includes a “CDI” button that performs switching between GPS and VOR/ILS on a remote indicator, it is seldom necessary to use these outputs to drive an indicator. It is only necessary when it is desired for a separate indicator to display VOR/ILS deviation full-time (regardless of the “CDI” button status).

The VOR/ILS indicator displays both lateral and vertical, To/From indications, lateral and vertical flags and superflags. GNS 430 connector 4006 always outputs the VOR/Localizer/Glideslope navigation information. The VOR/ILS pins on GNS 430 connector 4006 are used to drive an indicator that displays VOR/ILS information at all times, regardless of the CDI selection on the GNS 430.

VOR/LOC COMPOSITE OUT is a standard VOR/Localizer Composite output signal which may be used to drive the Left/Right, TO/FROM, and Flag indications of certain navigation indicators that contain an internal converter.

The ILS ENERGIZE output goes low when the VLOC frequency is channeled to a localizer channel.

4.8.2 VOR/ILS Indicator Electrical Characteristics

4.8.2.1 Superflags

Pin Name Connector Pin I/O

VOR/LOC SUPERFLAG P4006 15 Out GLIDESLOPE SUPERFLAG P4006 38 Out

The output supplies not less than 500 mA on a 28 volt system and 250 mA on a 14 volt system with the output voltage not less than (AIRCRAFT POWER - 3 V output voltage with respect to ground is less than 3 V

) when the flag is to be OUT OF VIEW. The

when the flag is to be IN VIEW.

4.8.2.2 Deviation

Pin Name Connector Pin I/O

VOR/LOC +LEFT P4006 5 Out VOR/LOC +RIGHT (VOR/LOC COMMON) P4006 6 Out GLIDESLOPE +UP P4006 32 Out GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE

P4006 31 Out

COMMON)

The deviation outputs are each capable of driving up to three 1000 Ω meter loads with ±150 mVDC±10% with respect to 2.5V Common for full-scale deflection. The drive circuit provides for more than full-scale deflection with a maximum course deviation output voltage of ±300 mV

±10%.

4.8.2.3 TO/FROM

Pin Name Connector Pin I/O

VOR/LOC +TO P4006 1 Out VOR/LOC +FROM (VOR/LOC COMMON) P4006 2 Out

The output is capable of driving up to three 200 Ω meter loads. When indicating TO, the output is +225 ±75 mV

When indicating FROM, output is -225 ±75 mV

DC.

(Flag IN VIEW) the TO/FROM output is 0 ±10 mV

DC.

When invalid information is present

DC.

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4.8.2.4 Flag

Pin Name Connector Pin I/O

VOR/LOC +FLAG P4006 3 Out VOR/LOC -FLAG (VOR/LOC COMMON) P4006 4 Out GLIDESLOPE +FLAG P4006 30 Out GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE

P4006 31 Out

COMMON)

The Flag output is capable of driving up to three 1000 Ω meter loads. When valid information is present (Flag OUT OF VIEW) the Flag output is 375 ±80 mV VIEW) the Flag output is 0 ±25 mV

DC.

When invalid information is present (Flag IN

DC.

4.8.2.5 OBS

Pin Name Connector Pin I/O

VOR OBS ROTOR C P4006 9 Out VOR OBS ROTOR H (GROUND) P4006 10 Out VOR OBS STATOR D P4006 13 In VOR OBS STATOR F P4006 12 In VOR OBS STATOR E/G (VOR/LOC

P4006 11 Out

COMMON)

VOR OBS ROTOR C and H are a buffered 500 Hz output that is intended to drive the OBS rotors. VOR OBS STATOR D and VOR OBS STATOR F are each phase and amplitude shifted version of the VOR ROTOR C output. Each pair is intended to read one of the two windings of the indicator’s OBS stator.

4.8.2.6 VOR/LOC COMPOSITE

Pin Name Connector Pin I/O

VOR/LOC COMPOSITE OUT P4006 8 Out

With a Standard VOR Test Signal applied, VOR/LOC COMPOSITE OUT is 0.5 ±0.1 V

into a 10 kΩ

RMS

load. With a Standard Localizer Centering Test Signal applied, VOR/LOC COMPOSITE OUT is 0.350 ±0.05 V

into a 10 kΩ load.

RMS

4.8.2.7 ILS ENERGIZE

Pin Name Connector Pin I/O

ILS ENERGIZE P4006 29 Out

The driver output voltage is not more than 1.0 V when sinking 20 mA. The maximum off state leakage current with respect to GND is less than 10 µA.

4.8.3 VOR/ILS Indicator Configuration

Refer to section 5.2.13 for the VOR/LOC/GS configuration.

4.8.4 VOR/ILS Indicator Calibration and Checkout

Refer to section 5.2.13 for the VOR/LOC/GS checkout.

4.8.5 VOR/ILS Indicator Interconnect

Refer to Figure 4-21 on page 4-61 for the VOR/ILS indicator interconnect.

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4.9 RMI/OBI

4.9.1 RMI/OBI Function

The MAIN OBI output provides bearing information from the active waypoint for Bendix/King Serial OBI devices based upon the 400 Series unit’s GPS navigation. For the GNS 430, the MAIN OBI output may be configured so that it sends VOR/ILS bearing information when VLOC is selected by the GNS 430 CDI key.

The VOR OBI output provides bearing information from the active waypoint for Bendix/King Serial OBI devices based upon the GNS 430 VOR receiver.

When a localizer channel is tuned on the VLOC window, there is a bit in the data stream set to indicate that a localizer frequency is tuned which stows the needle or drives it to the 3 o’clock position.

4.9.2 RMI/OBI Electrical Characteristics

Pin Name Connector Pin I/O

MAIN OBI CLOCK P4001 43 Out MAIN OBI SYNC P4001 45 Out MAIN OBI DATA P4001 44 Out

Pin Name Connector Pin I/O

VOR OBI CLOCK P4006 25 Out VOR OBI SYNC P4006 26 Out VOR OBI DATA P4006 27 Out

The output driver is active low. The driver output voltage is not more than 1.0 V when sinking 20 mADC. The maximum off state leakage current with respect to ground is less than 10 µA

4.9.3 RMI/OBI Configuration

For the GNS 430, refer to section 5.2.10 for the MAIN OBI source configuration.

4.9.4 RMI/OBI Calibration and Checkout

None.

4.9.5 RMI/OBI Interconnect

Refer to Figure 4-22 on page 4-63 for the RMI/OBI interconnect.

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4.10 DME TUNING (GNS 430 ONLY)

4.10.1 DME Tuning Function

The GNS 430 can channel a DME based on the tuned VLOC frequency. The GNS 430 outputs 2 of 5, BCD or Slip parallel DME and King Serial DME channeling format. When DME COMMON is held low, the GNS 430 actively tunes the DME.

4.10.2 DME Tuning Electrical Characteristics

4.10.2.1 Parallel DME Tuning

Pin Name Connector Pin I/O

NAV PAR DME - 8MHZ P4006 14 Out SER DME – CHAN REQ/PAR DME - 4MHZ P4006 20 Out* SER DME – RNAV MODE/PAR DME - 2MHZ P4006 21 Out* NAV PAR DME - 1MHZ P4006 33 Out NAV PAR DME - 800KHZ P4006 37 Out NAV PAR DME - 400KHZ P4006 39 Out NAV PAR DME - 200KHZ P4006 40 Out NAV PAR DME - 100KHZ P4006 42 Out NAV PAR DME - 50KHZ P4006 43 Out NAV DME COMMON P4006 22 In

* These pins are outputs when the GNS 430 is configured for 2 of 5 parallel DME tuning.

For each of the parallel DME tuning discrete outputs, the driver output voltage is not more than 1.0 V while sinking 20 mA. The maximum off state leakage current with respect to ground is less than 10 µA.

NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling the DME.

NAV DME COMMON is considered active if either the voltage to ground is < 1.9 V or the resistance to ground is< 375 Ω. These inputs are considered inactive if the voltage to ground is 11-33 V

4.10.2.2 King Serial DME Tuning

Pin Name Connector Pin I/O

NAV SER DME - DATA P4006 19 Out NAV SER DME - CLOCK P4006 18 Out SER DME – CHAN REQ/PAR DME - 4MHZ P4006 20 In* SER DME – RNAV MODE/PAR DME – 2MHZ P4006 21 In* NAV DME COMMON P4006 22 In

* These pins are inputs when the GNS 430 is configured for King Serial DME tuning

When NAV SER DME – DATA or NAV SER DME – CLOCK is asserted high and driving a 360 Ω load, the driver output voltage is not less than 8 V, and when asserted low shall not be greater than 10 mV.

SER DME – CHAN REQ/PAR DME – 4MHZ, SER DME – RNAV MODE/PAR DME – 2MHz, and NAV DME COMMON are considered active if either the voltage to ground is < 1.9 V or the resistance to ground is< 375 Ω. These inputs are considered inactive if the voltage to ground is 11-33 V

NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling the DME.

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4.10.3 DME Tuning Configuration

Refer to section 5.2.12 for the DME tuning configuration.

4.10.4 DME Tuning Calibration and Checkout

None.

4.10.5 DME Tuning Interconnect

Refer to Figure 4-23 on page 4-65 for the King Serial Panel DME tuning interconnect. Refer to Figure 424 on page 4-67 for the King Serial Remote DME tuning interconnect. Refer to Figure 4-25 on page 4-69 for the parallel 2 of 5 DME tuning interconnect. Refer to Figure 4-26 on page 4-71 for the parallel BCD/Slip Code DME tuning interconnect.

NOTE

For the GNS 430 to tune a Narco DME 890 or IDME 891 or an ARC (Cessna) RTA-576A using parallel 2 of 5, unique wiring and configuration are required. Refer to section 5.2.13 on page 5-11 and Figure 4-25 on page 4-69.

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4.11 400 SERIES INTERCONNECTS

4.11.1 400 Series System Interface Diagram

Figure 4-1. 400 Series System Interface Diagram

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4.11.2 400 Series Typical Installations

Figure 4-2. GNS 430 Typical Installation

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Figure 4-3. GNC 420 Typical Installation

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Figure 4-4. GPS 400 Typical Installation

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4.11.3 Power, Lighting, and Antennas Interconnect

Figure 4-5. Power, Lighting, and Antennas Interconnect

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4.11.4 Altimeter Interconnect

Figure 4-6. Altimeter Interconnect

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4.11.5 Main Indicator Interconnect

Figure 4-7. Main Indicator Interconnect

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4.11.6 KI 209A Main Indicator Interconnect

Figure 4-8. KI 209A Main Indicator Interconnect

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4.11.7 KI 208A Main Indicator Interconnect

Figure 4-9. KI 208A Main Indicator Interconnect

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4.11.8 Annunciators/Switches Interconnect

Figure 4-10. Annunciators/Switches Interconnect

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4.11.9 RS-232 Serial Data Interconnect

Figure 4-11. RS-232 Serial Data Interconnect

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4.11.10 ARINC 429 EFIS Interconnect

Figure 4-12. ARINC 429 EFIS Interconnect

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4.11.11 ARINC 429 Sandel EHSI Interconnect (1 400 Series Unit, 1 Sandel SN3308)

Figure 4-13. ARINC 429 Sandel EHSI Interconnect (1 400 Series Unit, 1 Sandel SN3308)

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4.11.12 ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 1 Sandel SN3308)

Figure 4-14. ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 1 Sandel SN3308)

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4.11.13 ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 2 Sandel SN3308)

Figure 4-15. ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 2 Sandel SN3308)

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4.11.14 ARINC 429 Air Data/IRU/AHRS Interconnect

Figure 4-16. ARINC 429 Air Data/IRU/AHRS Interconnect

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4.11.15 ARINC 429 Flight Control Interconnect

Figure 4-17. ARINC 429 Flight Control Interconnect

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4.11.16 Traffic Advisory System Interconnect

Figure 4-18. Traffic Advisory System Interconnect

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4.11.17 Weather and Terrain Interconnect

Figure 4-19. Weather and Terrain Interconnect

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4.11.18 Audio Panel Interconnect

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4.11.19 VOR/ILS Indicator Interconnect

Figure 4-21. VOR/ILS Indicator Interconnect

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4.11.20 RMI/OBI Interconnect

Figure 4-22. RMI/OBI Interconnect

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4.11.21 King Serial Panel DME Tuning Interconnect

Figure 4-23. King Serial Panel DME Tuning Interconnect

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4.11.22 King Serial Remote DME Tuning Interconnect

Figure 4-24. King Serial Remote DME Tuning Interconnect

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4.11.23 Parallel 2 OF 5 DME Tuning Interconnect

Figure 4-25. Parallel 2 OF 5 DME Tuning Interconnect

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4.11.24 Parallel BCD/Slip Code DME Tuning Interconnect

Figure 4-26. Parallel BCD/Slip Code DME Tuning Interconnect

Page 83

5. POST INSTALLATION CONFIGURATION & CHECKOUT PROCEDURE

5.1 CONFIGURATION MODE OPERATIONS

With power applied to the aviation rack and the 400 Series unit turned off, press and hold the ENT key and turn the unit on. Release the ENT key when the display activates, the unit is now in the configuration mode. After the data base pages, the first page displayed is the MAIN ARINC 429 CONFIG page. While in Configuration Mode, pages can be selected by ensuring the cursor is off and rotating the small right knob.

To change data on the displayed Configuration Page, press the small right knob (CRSR) to turn on the cursor. Turn the large right knob to change between data fields. Turn the large or small right knob to change a field that the cursor is on. Once you have made the desired selection, press the ENT key to accept the entry.

5.2 INSTALLATION CONFIGURATION PAGES

The Configuration Pages described in the following sections are in the order found when rotating the right small knob clockwise starting at the MAIN ARINC 429 CONFIG page. Use the procedure described in section 5.1 to get to this page.

NOTE

The configuration pages shown here reflect MAIN software version 2.25. All Configuration Pages shown apply to the GNS 430, but not all apply to the GPS 400 or GNC 420. Those pages and fields that apply only to certain 400 Series units are denoted as such.

5.2.1 MAIN ARINC 429 CONFIG Page

Select the MAIN ARINC 429 CONFIG Page (see Figure 5-1). This page configures the GPS ARINC 429 output port, and the two GPS ARINC 429 input ports. The two input ports can each be configured independently for the desired function(s).

SPEED

MAIN ARINC 429 CONFIG Page

Figure 5-1.

Selection Description

Low High

Standard low-speed ARINC 429 (nominally 12.5 kilobits per second) High-speed ARINC 429 (nominally 100 kilobits per second)

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DATA IN 1, DATA IN 2

Selection Description

Off Airdata

Airdata/AHRS

Traffic Advisory

EFIS

EFIS/Airdata

Flight control

DATA IN 1, DATA IN 2, cont.

GARMIN GAD 42 Honeywell EFIS

INS/IRU

Radar graphics Sandel EHSI

No unit connected to this ARINC 429 input Altitude, temperature, and speed information from the following Airdata systems:

B & D 2600, 2601, 2800, 90004-003, Bendix/King KAD 280/480, Shadin ADC 2000

Heading, altitude, temperature, and speed information from an Airdata/AHRS system. Traffic information from the following traffic advisory systems:

BF Goodrich SKY497 Skywatch/Skywatch HP Bendix/King KTA 870, KMH 880

Selected course, heading, and joystick waypoint information from the following EFIS systems:

Bendix/King EFS 40/50

Certain versions of Collins EFIS may also be compatible with this format. Selected course, heading, joystick waypoint, altitude, temperature, and speed information from the following systems:

Collins Pro Line 21

Selected course information from the following Flight Control systems:

Bendix/King KFC 400

Selected course, heading, and true airspeed data from the GARMIN GAD 42. Selected course, heading, and joystick waypoint information from the following EFIS systems:

Honeywell Primus 1000

Heading information from the following Inertial systems:

Bendix/King KAH 460 Collins AHC 85 Honeywell Laseref Litef LTR 81 Litton LTN 90-100, LTN 91, LTN 92

Joystick waypoint information from a RADAR graphics unit. Selected course and heading information from the following EHSI system:

Sandel SN3308

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DATA OUT

Selection Description

Off ARINC 429 GAMA 429

GAMA 429 Graphics

GAMA 429 Graphics w/Int

GAMA 429 Pro Line 21

GAMA 429 Sextant

No unit(s) connected to ARINC 429 output Standard ARINC 429 output data (non-GAMA). ARINC 429 data as defined by the General Aviation Manufacturers’

Association (GAMA) General Aviation Subset, 2

includes navigation and flight plan information to the following systems:

GARMIN GAD 42 Interface Adapter Bendix/King EFS 40/50 Sandel SN3308 Collins EFIS 84

Certain other of Collins EFIS systems may also be compatible with this format. ARINC 429 data as defined by the GAMA General Aviation Subset, 2 Edition including GAMA Graphics Protocol ‘A’. This format outputs intersection symbols as generic waypoint symbols. The output data includes navigation and flight plan information (including graphical representation of flight plan procedures) to the following EFIS systems:

Honeywell Primus 1000 ARINC 429 data as defined by the GAMA General Aviation Subset, 2

Edition including GAMA Graphics Protocol ‘A’. The output data includes

navigation and flight plan information (including graphical representation of flight plan procedures).

ARINC 429 data as defined by the GAMA General Aviation Subset, 2 Edition. The output data includes navigation and flight plan information to the following EFIS systems:

Collins Pro Line 21 ARINC 429 data as defined by the GAMA General Aviation Subset, 2

Edition. The output data includes navigation and flight plan information to

the following EFIS systems:

Sextant SMD 45

Edition. The output data

SDI

Selection Description

Common LNAV 1

LNAV 2

5.2.2 MAIN RS232 CONFIG Page

Select the MAIN RS232 CONFIG Page (see Figure 5-2). If necessary, change the selectable RS-232 inputs and/or outputs to match that of the equipment installed in the aircraft.

Common long-range navigator (only 429 data with SDI=0 is used) Number 1 (Pilot) long-range navigator. Only 429 data with SDI=0 or SDI=1 is used. Number 2 (Copilot) long-range navigator. Only 429 data with SDI=0 or SDI=2 is used.

Figure 5-2. MAIN RS232 CONFIG Page

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CHANNEL INPUTS

Selection Description

Off Arnav/ei-fuel

Crossfill

GDL 49 Icarus-alt

Ryan TCAD Shadin-adc

Shadin-alt

Shadin-fadc

Shadin-fuel

WX-500

No unit(s) connected to input of this channel. Serial fuel flow information from the following units:

ARNAV FC-10, FT-10 Electronics International FP-5L

Serial transfer of flight plans and user waypoints between two 400 Series units. If Crossfill is selected for a channel output, then Crossfill is automatically selected for that channel’s input. Serial data input for in-flight access to weather and messaging. Serial altitude data from the following units:

Garmin GTX 327, Icarus Instruments 3000

Traffic information from a Ryan TCAD 9900B Series system. Serial air data information from the following units:

Shadin ADC 200, 200+, 2000

Serial altitude data from the following units:

Shadin 8800T, 9000T, 9200T

Serial air data and fuel flow information from the following units:

Shadin 9628XX-X Fuel/Air Data Computer

Serial fuel flow information from the following units:

Shadin 91204XM Digital Fuel Management System Shadin 91053XM Digital Fuel Management System JP Instruments EDM-700 or EDM-760 Engine Monitor

Lightning strike information from a BF Goodrich WX-500 Stormscope.

CHANNEL OUTPUTS

Selection Description

Off Aviation

Avtn no alt

Crossfill

HW EGPWS Ryan TCAD WX-500

FUEL TYPE

No unit(s) connected to output of this channel Serial position, altitude, velocity, and navigation data to the following units:

GARMIN GPSMAP 195 or GPS III Pilot Argus 3000, 5000, or 7000 Moving Map Electronics International FP-5L Fuel Flow Computer (non-TSO’d) JP Instruments EDM-700 or EDM-760 Engine Monitor Shadin 91204XM Digital Fuel Management System Shadin 91053XM Digital Fuel Management System Shadin 9628XX-X Fuel/Air Data Computer Stormscope Series II (with Navaid) Moving Map GARMIN GDL 49 Satellite data link transceiver GARMIN GTX 327 Transponder

Serial position, velocity, and navigation data to the following units:

Horizon DDMP

Serial transfer of flight plans and user waypoints between two 400 Series units Serial communication to a Bendix/King (Honeywell) KGP 560 EGPWS. Serial communication with a Ryan TCAD 9900B Series system. Serial communication to a BF Goodrich WX-500 Stormscope.

Selection Description

AV gas Jet A Jet B

The aircraft is using Aviation gas (5.8 lbs./gal.) The aircraft is using Jet A or Jet A-1 fuel (6.7 lbs./gal.) The aircraft is using Jet B (JP-4) fuel (6.5 lbs./gal.)

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5.2.3 MAIN INPUTS 1 Page

Select the MAIN INPUTS 1 Page (see Figure 5-3). This page (along with the MAIN INPUTS 2 Page) allows you to monitor the data on ARINC 429, RS-232 and other electrical inputs. This is used for verifying electrical interfaces during installation and troubleshooting. Information that is not being received by the 400 Series unit is dashed out.

Field Description

OAT SAT TAT IAS TAS WSPD HDG WDIR B ALT D ALT P ALT

5.2.4 MAIN INPUTS 2 Page

Select the MAIN INPUTS 2 Page (see Figure 5-4). This page is also used for verifying electrical interfaces during installation and troubleshooting. Information that is not being received by the 400 Series unit is dashed out.

Outside Air Temperature Static Air Temperature Total Air Temperature Indicated Airspeed True Airspeed Wind Speed Heading (True or Magnetic) Wind Direction Barometric-corrected Altitude Density Altitude Pressure Altitude

Figure 5-3. MAIN INPUTS 1 Page

Field Description

L FF R FF T FF T FOB GPS SC VLC SC

CDI

JOYSTICK WPT

5.2.5 INSTRUMENT PANEL SELF-TEST Page

Select the INSTRUMENT PANEL SELF-TEST Page (see Figure 5-5). This page allows verification that the 400 Series unit is communicating properly with other instruments. Compare on-screen indications with the information depicted on connected instruments, such as the CDI, HSI, RMI and/or external annunciators. It also displays fuel capacity, amount on-board, and flow.

Left Engine Fuel Flow Right Engine Fuel Flow Total Fuel Flow Total Fuel on Board GPS Selected Course VOR/LOC Selected Course (GNS 430 Only) Status of the CDI key (GNS 430 Only) Latitude and longitude of a joystick waypoint sent by an EFIS or RADAR indicator.

Figure 5-4. MAIN INPUTS 2 Page

Figure 5-5. INSTRUMENT PANEL

SELF-TEST Page

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5.2.6 MAIN LIGHTING Page

Select the MAIN LIGHTING Page (see Figure 5-6). This page allows you to set display parameters that affect the display backlight and key lighting brightness. The DISPLAY and KEY lighting characteristics are adjusted separately, each with the following fields:

LIGHTING

Shows the current level of display backlighting, based on the lighting input source (lighting bus voltage, or the ambient light if the source is PHOTO) and the settings on this configuration page. This field has a range of 0 (zero) to 9999.

SOURCE

Figure 5-6. MAIN LIGHTING Page

Selection Description

PHOTO

14V DC 28V DC 5V DC 5V AC

Backlight level is determined by the ambient light level as measured by the photocell on the 400 Series unit. Backlight level tracks a 14 volt DC aircraft lighting bus. Backlight level tracks a 28 volt DC aircraft lighting bus. Backlight level tracks a 5 volt DC aircraft lighting bus. Backlight level tracks a 5 volt AC aircraft lighting bus.

NOTE

If a lighting bus (any selection other than PHOTO) is selected, and the lighting bus control is turned to its minimum (daytime) setting, the display brightness tracks the 400 Series unit’s photocell using additional parameters (PHOTO TRANS % and PHOTO SLP/OFFST) described below.

RESP TIME - (Response Time) Sets the speed with which the brightness responds to the input level (bus voltage or ambient light) changes. The higher the number the slower the display responds. This field has a range of 3 to 7, and is set to 4 at the factory.

MIN - (Minimum) Sets the minimum brightness of the display. The higher the number, the brighter the minimum brightness. Display minimum brightness has a range of 35 to 999, and is set to 80 at the factory. Key minimum brightness has a range of 20 to 99, and is set to 40 at the factory. It is prudent to verify that display and key lighting characteristics match those of other equipment in the panel under night lighting conditions.

SLOPE

Sets the sensitivity of the display brightness in proportion to changes in the input level. The higher the number, the brighter the display is for a given increase in the input level. This field has a range of 0 (zero) to 99, and is set to 50 at the factory.

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OFFSET

Adjusts the lighting level up or down for any given input level. This field has a range of 0 (zero) to 99, and is set to 50 at the factory. This may also be used to match lighting curves with other equipment in the panel.

PHOTO TRANS % - (Photocell Transition Percentage) When a lighting bus is used to control the lighting of the display (see Figure 5-7), this parameter sets the point on the lighting bus control below which the display brightness tracks the 400 Series unit’s photocell. This field has a range of 0 (zero) to 99, and is set to 25 at the factory.

PHOTO SLP/OFFST - (Photocell Slope/Offset) These fields are equivalent to the SLOPE/OFFSET fields described above, with the exception that they only control the display lighting characteristics when the lighting bus control is below the level specified in the PHOTO TRANS % field. Both fields have a range of 0 (zero) to 99, and are set to 50 at the factory.

CONTRAST

If contrast isn’t acceptable, place unit in Normal Mode. On the AUX menu SETUP page 2, highlight DISPLAY and press ENTER. The DISPLAY page is shown (see Figure 5-8). Confirm that CONTRAST MODE is “Auto”. Highlight CONTRAST LEVEL and adjust to best viewable color. Press ENTER to confirm change.

Figure 5-7. MAIN LIGHTING Page

(Display Lighting from Lighting Bus)

Figure 5-8.

DISPLAY Page (AUX Group)

NOTE

Note: Leave CONTRAST MODE in “Auto”.

5.2.7 DATE/TIME SETUP Page

Select the DATE/TIME SETUP Page (see Figure 5-9). Very infrequently, it may be desirable to set the date and time of the 400 Series unit to aid in acquiring a GPS position. Configuration mode is the only means by which the date and time for the 400 Series unit may be adjusted. Note that the time must be UTC time, and that the UTC date may be different from the date in the local time zone.

Figure 5-9.

DATE/TIME SETUP Page

5.2.8 MAIN DISCRETE INPUTS Page

Select the MAIN DISCRETE INPUTS Page (see Figure 5-

10) if the encoding altimeter input is used. Verify that the DECODED ALTITUDE field indicates the correct altitude.

EXTERNAL SWITCH STATE

MAIN DISCRETE INPUTS Page

Figure 5-10.

Selection Verify That:

RMT CDI RMT OBS

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The box is filled in while a remote CDI source select switch is pressed. The box is filled in while a remote OBS switch is pressed.

Page 90

5.2.9 MAIN DISCRETE OUTPUTS Page

Select the MAIN DISCRETE OUTPUTS Page (see Figure 5-11). This page allows you to verify the operation of any external annunciators and switches that are present in the installation.

DISCRETE TOGGLE

Selection Verify That:

APR GPS

INTEG MSG OBS TERM VLOC

WPT ILS/GPS APR

The APR annunciator is active and inactive as selected on this page. The GPS source select annunciator is active and inactive as selected on this page. The INTEG annunciator is active and inactive as selected on this page. The MSG annunciator is active and inactive as selected on this page. The OBS annunciator is active and inactive as selected on this page. The TERM annunciator is active and inactive as selected on this page. The VLOC source select annunciator is active and inactive as selected on this page. The WPT annunciator is active and inactive as selected on this page. The ILS/GPS APPROACH output is active and inactive as selected on this page (NOTE: This output is connected to the autopilot ILS ENGAGE input, not to an annunciation, and therefore this is for bench testing purposes only).

Figure 5-11.

MAIN DISCRETE OUTPUTS Page

5.2.10 MAIN CDI/OBS CONFIG Page

Select the MAIN CDI/OBS CONFIG Page (see Figure 5-

12). This page allows you to verify the MAIN CDI outputs, both lateral (LAT) and vertical (VERT), and verify and calibrate the MAIN OBS input. Using the controls on the 400 Series unit front panel, make the selections below and verify the interfaces as appropriate:

CDI (LAT/VERT)

Selection Verify That:

Max left/up Full left/up Center Full right/down Max right/down

NAV FLAG (LAT/VERT)

The CDI is “pegged” to the left/up. The CDI is deflected full scale to the left/up. The CDI is centered. The CDI is deflected full scale to the right/down. The CDI is “pegged” to the right/down.

Selection Verify That:

Hidden In view

The LAT/VERT flag is hidden. The LAT/VERT flag is in view.

Figure 5-12.

MAIN CDI/OBS CONFIG Page

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TO-FROM

Selection Verify That:

FROM Hidden TO

SELECTED COURSE

Select 150° on the CDI/HSI that is connected to the 400 Series unit’s MAIN OBS inputs. The SELECTED COURSE field indicates near to 150° and a Calibrate to 150°? field appears. Selecting this field calibrates the 400 Series unit to match the input source. Verify OBS operation by checking that the course displayed on the 400 Series unit is within 2° of the selected course. Do this at 30° intervals around the OBS card.

The FROM flag is in view. The TO/FROM flag is hidden. The TO flag is in view.

NOTE

If it is desired to ignore a selected course input (either analog resolver or ARINC 429) for GPS operation in OBS mode, press MENU on the MAIN CDI/OBS CONFIG page and select “Ignore SEL CRS for GPS?”. When OBS mode is selected, the selected course is entered on the controls of the 400 Series unit. If ignoring the selected course input such that the VOR valid flag is dependent only on a valid VOR signal, with lateral deviation calculated by another display device, press MENU on the MAIN CDI/OBS CONFIG page and select “Ignore SEL CRS for VLOC?”.

CDI (GNS 430 Only)

Selection Description

GPS

VLOC

The GNS 430 CDI button is in the GPS state, and the GPS ANNUNCIATE output is active. This annunciator output may be required to be active for some installations. The GNS 430 CDI button is in the VLOC state, and the VLOC ANNUNCIATE output is active.

NOTE

If it is desired to disable the GNS 430 CDI key, press MENU on the MAIN CDI/OBS CONFIG page and select “Ignore CDI Key?”. This causes the field above the CDI key to always display GPS, regardless of CDI key presses. This may be necessary for certain EFIS systems where navigation sensor selection must be accomplished on the EFIS or its control panel.

OBI SOURCE (GNS 430 Only)

Selection Description

Always GPS

Track CDI

V-FLAG STATE

The MAIN King Serial OBI outputs are always GPS. This is useful if it is desired to switch a Bendix/King KI 229 or KNI 582 RMI pointer independently from the GNS 430 CDI button. The MAIN King Serial OBI outputs are GPS or VOR, and switchable by the GNS 430 CDI button. This is useful if it is desired the Bendix/King KI 229 or KNI 582 RMI pointer to display the same navigation source as the GNS 430 CDI outputs.

Selection Description

Declutter

Normal

The vertical deviation bar is parked in the full-scale up position when GPS or VOR navigation is selected for output. The exception is when the CDI is in VLOC mode and an ILS frequency is tuned, in which case the vertical deviation bar parks in the centered position. The vertical deviation bar parks in the centered position whenever it is flagged.

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5.2.11 COM SETUP Page (GNC 420 and GNS 430 Only)

Select the COM SETUP Page (see Figure 5-13). These values are set at the factory and seldom require calibration.

FREQ

Selects a VHF communication frequency. For purposes of setting the squelch and sidetone levels, only the frequencies 118.000, 127.000, and 136.975 MHz can be used.

Figure 5-13. COM SETUP Page

SPACING

Selection Description

25.0 kHz

8.33 kHz

Selects traditional 25 kilohertz spacing (760 channel). Selects 8.33 kilohertz channel spacing, which is required in some areas of the world.

CAUTION

8.33 kHz channels are not authorized for use in the United States.

SQ 250

Sets the squelch threshold for 25 kHz channel spacing operation. May be set to any value between 0 (zero) and 63. The higher the number, the less signal is required to break squelch.

NOTE

For GNS 430 units with serial number 200 or lower, the operation of the SQ 250 setting is reversed. The higher the SQ 250 number, the more signal is required to break squelch.

SQ 833

Sets the squelch threshold for 8.33 kHz channel spacing operation. May be set to any value between 0 (zero) and 63. The higher the number, the more signal is required to break squelch.

SIDE

Sets the sidetone audio output level. May be set to any value between 0 (zero) and 63.

MIC

Sets the Mic Gain output level. May be set to any value between 0 (zero) and 63. This adjusts the output for differences in microphones used. Should adjustment be necessary refer to the maintenance manual. This Mic Gain software adjustment is effective for GNS 430 s/n 97107371 and above, and GNC 420 s/n 97202086 and above.

NOTE

The sidetone audio output level is independent of the COM volume knob on the 400 Series unit.

Store Calibration?

Select this field and press the ENT key to accept the squelch threshold and sidetone audio settings on this page. If you wish for the squelch and sidetone settings to return to their previous values, do not select this field. Simply change to the next configuration page, or turn off the unit if you are done with configuration.

Selection Verify That:

PTT XFR RX TX

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The box is filled in while the COM push-to-talk switch is pressed. The box is filled in while a remote COM transfer switch is pressed. The box is filled in while the COM is receiving a signal. The box is filled in while the COM push-to-talk switch is pressed.

Page 93

5.2.12 VOR DISCRETE INPUTS Page (GNS 430 Only)

Select the VOR DISCRETE INPUTS Page (see Figure 5-

14). This page allows you to verify the operation of an external VLOC transfer switch that may be present in the installation.

Selection Verify That:

REMOTE XFR

5.2.13 VOR/LOC/GS CDI Page (GNS 430 Only)

Select the VOR/LOC/GS CDI Page (see Figure 5-15). This page allows you to verify and calibrate the CDI outputs, both lateral (LAT) and vertical (VERT) from the VOR/LOC/Glideslope receiver, as well as the OBS resolver input to the VOR receiver. It also allows you to select the format for DME tuning data. Using the controls on the GNS 430 front panel, make the selections below and verify the interfaces as appropriate:

The box is filled in while a remote VLOC transfer switch is pressed.

Figure 5-14.

VOR DISCRETE INPUTS Page

Figure 5-15.

VOR/LOC/GS CDI Page

NOTE

The LAT, VERT, and SELECTED COURSE configurations only apply to installations where a CDI/HSI is connected to the VOR/LOC/GLIDESLOPE pins on connector P4006.

CDI (LAT/VERT)

Selection Verify That:

Max left/up Full left/up Center Full right/down Max right/down

FLAG (LAT/VERT)

Selection Verify That:

Hide View

S-FLG (LAT/VERT)

The LAT/VERT flag is hidden. The LAT/VERT flag is in view.

Selection Verify That:

Hide View

TO-FR

The LAT/VERT superflag is hidden. The LAT/VERT superflag is in view.

Selection Verify That:

FROM Hide TO

The FROM flag is in view. The TO/FROM flag is hidden. The TO flag is in view.

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SELECTED COURSE

Select 150° on the CDI/HSI that is connected to the 400 Series VOR/LOC/GS OBS inputs. The SELECTED COURSE field should indicate near to 150° and a Calibrate to 150°? field appears. Selecting this field calibrates the 400 Series to match the input source. Verify OBS operation by checking that the course displayed on the 400 Series is within 2° of the selected course. Do this at 30° intervals around the OBS card.

DME CHNL MODE

This configuration allows you to set the format for DME tuning data output.

Selection Description

King Serial

Parallel 2x5 Parallel BCD

Parallel slip

Narco 890/891

5.2.14 VOR/LOC/GS ARINC 429 CONFIG Page (GNS 430 Only)

Select the VOR/LOC/GS ARINC 429 CONFIG Page (see Figure 5-16). This page configures the VOR/ILS ARINC 429 output and input ports.

King Serial DME tuning data (not operational for MAIN software versions

2.02 and lower). 2 of 5 parallel DME tuning. Shifted BCD (Binary Coded Decimal) parallel DME tuning (not operational for MAIN software versions 2.02 and lower). Slip-code parallel DME tuning (not operational for MAIN software versions

2.02 and lower). 2 of 5 parallel DME tuning, compatible with the following DME units:

Narco DME 890 Narco DME 891 ARC (Cessna) RTA-476A

SPEED

Selection Description

Low High

SDI

Standard low-speed ARINC 429 (nominally 12.5 kilobits per second) High-speed ARINC 429 (nominally 100 kilobits per second)

Selection Description

Common VOR/ILS 1

VOR/ILS 2

DME MODE

Common VOR/ILS receiver (only 429 data with SDI=0 is used) Number 1 (Pilot) VOR/ILS receiver. Only 429 data with SDI=0 or SDI=1 is used. Number 2 (Copilot) VOR/ILS receiver. Only 429 data with SDI=0 or SDI=2 is used.

Selection Description

Directed freq 1

Directed freq 2

If the GNS 430 is connected to a multi-channel ARINC 429 DME, channel 1 of that DME is tuned. “Directed freq 1” should be selected if a singlechannel ARINC 429 DME is tuned. If the GNS 430 is connected to a multi-channel ARINC 429 DME, channel 2 of that DME is tuned.

Figure 5-16. VOR/LOC/GS ARINC 429

CONFIG Page

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5.2.15 STORMSCOPE CONFIG Page (Only if 400 Series unit configured for BFG WX-500 Stormscope interface)

Select the STORMSCOPE CONFIG Page (see Figure 5-

17). This page shows the BF Goodrich WX-500

Stormscope configuration as reported by the WX-500 through RS-232 data.

Verify that the STATUS field indicates “Ok”, and that the other displayed parameters are correct. Verify that all the boxes in the lower portion of the page are green.

When a 400 Series unit is used with a WX-500 Stormscope, the “Synchro” or “Serial” heading formats

STORMSCOPE CONFIG Page

Figure 5-17.

may be used. If another heading format is used, lightning strike information is visible on the Weather Page, but not on the Map Page.

5.2.16 STORMSCOPE TEST Page (Only if 400 Series unit configured for BFG WX-500 Stormscope interface)

Select the STORMSCOPE TEST Page (see Figure 5-18). This page shows current strike activity, WX-500 status, and the heading supplied by the WX-500. The WX-500 mode may be changed to ‘Demo’, ‘Noise monitor’, ‘Self test’, ‘Strike test’, or ‘Weather’.

Verify that the WX-500 mode can be changed. Refer to the WX-500 manual for specific installation test procedures for the WX-500, using this page to view strike data, change the WX-500 mode, view WX-500 status, trigger count, and heading.

STORMSCOPE TEST Page

Figure 5-18.

5.2.17 STORMSCOPE DOWNLOAD DATA Page (Only if 400 Series unit configured for BFG WX-500 Stormscope interface)

Select the STORMSCOPE TEST Page (see Figure 5-19). This page shows raw data downloadable from the WX-

500. Optional sets of data include WX-500 software

version, environmental conditions, configuration, and fault data.

Verify that the configuration data is correct as intended. To request which packet of data to display, highlight the data group title and use the small right knob to select the desired group.

Figure 5-19. STORMSCOPE

DOWNLOAD DATA Page

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Page 96

5.2.18 TRAFFIC Page (Only if 400 Series unit configured for BFG Skywatch or Ryan TCAD interfaces)

Select the TRAFFIC Page (see Figure 5-20). This page shows the BFG Skywatch or Ryan TCAD modes of operation and current traffic situation.

For BFG Skywatch, this page shows:

1. The altitude mode—below (BLW), normal (NORM),

above (ABV), or unrestricted (UNR)

2. The operating mode—standby (STBY) or operating

(OPER)

3. Current altitude (ALT)

Figure 5-20. TRAFFIC Page (Skywatch)

4. Altitude limits being imposed (LIM A and LIM B)

5. Heading, and barometric (BARO) and radio (RAD) altitude status.

For BFG Skywatch (see Figure 5-20), verify that the 400 Series unit can change the Skywatch operating mode (STBY or OPER). In standby mode, verify that the Skywatch may be placed in self-test mode by highlighting “Test Mode?” and pressing ENTER on the 400 Series unit. Refer to the BFG Skywatch installation manual for system checkout.

For Ryan TCAD (see Figure 5-21), this page shows the current shield mode and altitude. Verify that the TCAD shield mode may be changed—Ground (GND), Terminal (TML), Standard (STD), En Route (ENR), or Unrestricted (UNR), and that the TCAD is reporting the correct altitude. Refer to the Ryan TCAD installation manual for system checkout.

Figure 5-21. TRAFFIC Page (TCAD)

5.2.19 RYAN TCAD CONFIG Page (Only if 400 Series unit configured for Ryan TCAD interface)

Select the RYAN TCAD CONFIG Page (see Figure 5-22). This page shows the TCAD’s current shield settings for the selected mode, approach mode status, volume, mute status, mute duration, voice alert selection, and system status.

Verify that the TCAD system status is GREEN. Also, verify that shield settings and volume, mute duration, and voice alert selection can be modified. Verify that changes in mute (if a mute switch is installed) are shown. Refer to the Ryan TCAD installation manual for system checkout.

5.2.20 GAD 42 CONFIG Page (Only if 400 Series unit configured for GAD 42 interface)

Select the GAD 42 CONFIG Page (see Figure 5-23). This page allows remote configuration of a GAD 42 Interface Adapter Unit. For details of this function, please refer to Section 5 of the GAD 42 Installation Manual (P/N 19000159-00).

Figure 5-22. RYAN TCAD CONFIG

Figure 5-23. GAD 42 CONFIG Page

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5.2.21 MONITORING THE DATA LINK

The Data Link is monitored on the Data Link Page. There are four main page groups in the 400 Series software version 2.25 or higher: NAV, WPT, AUX, and NRST (see the 400 Series unit Pilot’s Guide for detailed information on the unit’s Page Groups). The Data Link Page (Figure 5-24) appears in the sequence of AUX Pages. To select the Data Link Page, rotate the large right knob until a page from the AUX group is displayed. To select the Data Link Page, rotate the small right knob until the Data Link Page is displayed. Select “Data Link Status” (Figure 5-24). For complete installation and configuration information refer to the GDL 49 installation manual, GARMIN P/N 190-00231-00.

Figure 5-24. DATA LINK Page

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Page 98

5.3 ADDITIONAL GROUND TESTS

5.3.1 Connector Engagement Test

1. Turn on the 400 Series unit, and turn on the avionics master switch (if applicable).

2. Place the 400 Series unit in the rack and engage the pawl mechanism.

3. Turn the Allen screw of the locking pawl slowly clockwise until the 400 Series unit just comes on. A

“T” handle makes the turns easy to count, but do not over-tighten.

4. Count the number of complete revolutions you can turn the Allen screw until it can not turn any more

(but take care not to over-tighten). Three turns is the minimum for proper installation. If fewer than three turns are possible, the mounting rack should be moved aft such that the aircraft panel does not obstruct the unit from engaging in the rack.

5.3.2 Verification of Self-Test Data

Following normal power-up, the Self-Test Page is displayed followed by the Data Base Page. Pressing the ENT key once then displays the Instrument Panel Self-Test page (refer to Figure 5-5 on page 5-5). During this time, many of the electrical outputs are activated so the installation, configuration, and wiring may be verified. Before approving the Data Base Page, verify that the following parameters are displayed on equipment in the aircraft as listed below:

NOTE

Electronic displays which monitor the 400 Series unit’s ARINC 429 output may vary in how and where annunciations are displayed. Generally, it is not required to verify every data field with an ARINC 429 interface. Correct display of a subset of the data without noting any discrepancies is typically adequate evidence of correct ARINC 429 operation.

Parameter Self-test Value

Course Deviation Glideslope/Vert. Deviation Bearing to Waypoint Desired Track Selected Course Distance to Go Time to Go Active Waypoint Groundspeed Present Position Waypoint Alert Phase of Flight Message Alert Leg/OBS Mode GPS Integrity

5.3.3 Signal Acquisition Test

Upon approval of the Data Base Page, the Satellite Status Page is displayed. If the unit is unable to acquire satellites, relocate the aircraft away from obstructions which might be interfering with GPS reception. If the situation does not improve, check the GPS antenna installation.

Once GPS position information is available, use the DIRECT-TO key to activate the navigation function to a nearby airport, NAVAID, or intersection. Ensure that any connected equipment is transmitting and or/receiving data from the 400 Series unit and is functioning properly (see the Pilot’s Guide for more information on the direct-to function).

Half-scale left deviation, TO indication, flag pulled Half-scale up deviation, flag pulled 135º

149.5º

10.0 nautical miles 4 minutes “GARMN” 150 knots N 39º04.05’, W 94º53.86’ Active En Route Active Leg Mode Reflects actual GPS integrity

Page 5-16 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

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5.3.4 Deviation & Flags Check

5.3.4.1 Analog Deviation & Flags

The analog deviation (LEFT/RIGHT and UP/DOWN), TO/FROM, and FLAG (lateral and vertical) outputs to a CDI or HSI should be verified in flight with potential sources of electrical noise such as autopilot, flaps, gear, heater blowers, etc. operating. Lateral deviation and flags may be checked with either GPS or VOR/ILS, and vertical deviation and flags must be checked with Glideslope. Verify that the flags are hidden at the correct times, and that the flag is in view at the correct times.

5.3.4.2 EHSI Deviation Scaling (Only if HSI/CDI is driven by the 400 Series unit via serial data)

With the 400 Series unit locked onto a GPS fix, activate an OBS waypoint about 20 nautical miles from the present position.

1. With 5.0 nautical mile CDI sensitivity, adjust the OBS course for approximately half-scale deflection on the 400 Series unit’s Default Navigation page. Verify that the EHSI displays a similar half-scale deviation.

2. Repeat step 1 with 1.0 nautical mile CDI sensitivity. The CDI sensitivity may be manually set on the AUX SETUP page, using the “CDI / ALARMS” menu item.

3. Repeat step 1 with 0.3 nautical mile CDI sensitivity.

5.3.5 Crossfill Check (Only if dual units installed with RS-232 crossfill connected)

Turn on both 400 Series units in the aircraft. For each 400 Series unit:

1. Select the first AUX page (titled “FLIGHT PLANNING”).

2. Select “CROSSFILL”.

3. Verify that the displayed status is “Ready”. If “Not Available” is displayed, there may be an RS232 wiring problem between the two 400 Series units.

5.3.6 VHF COM Interference Check (GNC 420 and GNS 430 Only)

Once the Signal Acquisition Test has been completed successfully, perform the following steps:

1. View the Satellite Status Page and verify that 7 to 8 satellites have been acquired.

2. Verify that the GPS “NAV” flag is out of view.

3. Select 121.150 MHz on the 400 Series COM transceiver.

4. Transmit for a period of 20 seconds.

5. Verify that the GPS “NAV” flag does not come into view.

6. Repeat steps 4 and 5 for the following frequencies:

• 121.175 MHz

• 121.200 MHz

• 131.250 MHz

• 131.275 MHz

• 131.300 MHz

7. Repeat steps 3 through 6 for all COM transceivers installed in the aircraft.

8. If the GPS “NAV” flag comes into view, refer to Section 2.2.7 for options to improve performance.

400 SERIES INSTALLATION MANUAL Page 5-17 P/N 190-00140-02 Page Rev L

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5.3.7 VHF COM Check (GNC 420 and GNS 430 Only)

A flight test is recommended after the installation is complete to ensure satisfactory performance. To check the communications transceiver, maintain an appropriate altitude and contact a ground station facility at a range of at least 50 nautical miles. Contact a close ground station. Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical noise which would increase the squelch threshold. If possible, verify the communications capability on both the high and low ends of the VHF COM band. It may be required by the governing regulatory agency to verify operation of the COM transmitter and receiver at the extents of a ground facility’s service volume (e.g., FAA AC 238A)

5.3.8 VOR/ILS Check (GNS 430 Only)

Select a VOR channel within a 40 nautical mile range. Listen to the VOR audio and verify that no electrical interference such as magneto noise is present. Check the tone identifier filter operation. Fly inbound or outbound on a selected VOR radial and check for proper LEFT/RIGHT, TO/FROM, and FLAG indications. Check the VOR accuracy. Verify that the flag is hidden with a valid received station, and that the flag is in view when there is not a received station. It may be required by the governing regulatory agency to verify operation of the VOR receiver at the extents of a ground facility’s service volume (e.g., FAA AC 23-8A).

5.3.9 DME Tuning Check (GNS 430 Only)

Select a VOR/ILS channel that corresponds to (1) a DME station within a 40 nautical mile range, or (2) the frequency of a DME ground tester. Verify that the DME locks on to the signal and a valid distance, groundspeed and time are displayed.

Page 5-18 400 SERIES INSTALLATION MANUAL Page Rev L P/N 190-00140-02

Garmin 420 User Manual

Specifications and Main Features

Frequently Asked Questions

User Manual