Garmin GNC 420A, GNC 430A, GNC 420, GNC 430, GPS 400 Installation Manual

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)

190-00140-02, Revision N

February 2005

£

© Copyright 1998 - 2005

Garmin Ltd. or its subsidiaries

All Rights Reserved

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

st

Street

Telephone: [phone]

Aviation Dealer Technical Support Line (Toll Free): [phone]

Web Site Address: www.garmin.com

Garmin (Europe) Ltd.

Unit 5, The Quadrangle

Abbey Park Industrial Estate

Romsey, SO51 9DL U.K.

Telephone: [phone]

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

M 7/6/04 Added TSO limitation 26552

N 2/7/05 Added GDL 69 interface information 29560

Description ECO #

10008

10665

11871

14026

18149

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

This manual is written for software version 4.03, 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 Rev N

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 TSO LIMITATIONS .....................................................................................................................................1-7

1.5 LICENSE REQUIREMENTS .......................................................................................................................1-7

1.6 CERTIFICATION .........................................................................................................................................1-7

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

1.8 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...............................................................................................................................3-7

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

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

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

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 ................................................................................................................5-17

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

Appendix F. DRAWINGS AND INTERCONNECTS ...............................................................................................F-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

Rev N P/N 190-00140-02

LIST OF FIGURES

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

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

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

FIGURE F-1. GA 56 ANTENNA INSTALLATION DRAWING.............................................................................F-3

FIGURE F-2. GNS 430 MOUNTING RACK DIMENSIONS...................................................................................F-5

FIGURE F-3. GNC 420 MOUNTING RACK DIMENSIONS ..................................................................................F-7

FIGURE F-4. GPS 400 MOUNTING RACK DIMENSIONS....................................................................................F-9

FIGURE F-5. GNS 430 MOUNTING RACK INSTALLATION ..............................................................................F-11

FIGURE F-6. GNC 420 MOUNTING RACK INSTALLATION..............................................................................F-13

FIGURE F-7. GPS 400 MOUNTING RACK INSTALLATION ...............................................................................F-15

FIGURE F-8. 400 SERIES RECOMMENDED PANEL CUTOUT DIMENSIONS .................................................F-17

FIGURE F-9. 400 SERIES SYSTEM INTERFACE DIAGRAM ..............................................................................F-19

FIGURE F-10. GNS 430 TYPICAL INSTALLATION .............................................................................................F-21

FIGURE F-11. GNC 420 TYPICAL INSTALLATION.............................................................................................F-23

FIGURE F-12. GPS 400 TYPICAL INSTALLATION..............................................................................................F-25

FIGURE F-13. POWER, LIGHTING, AND ANTENNAS INTERCONNECT.........................................................F-27

FIGURE F-14. ALTIMETER INTERCONNECT......................................................................................................F-29

FIGURE F-15. MAIN INDICATOR INTERCONNECT...........................................................................................F-31

FIGURE F-16. KI 209A MAIN INDICATOR INTERCONNECT............................................................................F-33

FIGURE F-17. KI 208A MAIN INDICATOR INTERCONNECT............................................................................F-35

FIGURE F-18. ANNUNCIATORS/SWITCHES INTERCONNECT ........................................................................F-37

FIGURE F-19. RS-232 SERIAL DATA INTERCONNECT .....................................................................................F-39

FIGURE F-20. ARINC 429 EFIS INTERCONNECT................................................................................................F-41

FIGURE F-21. ARINC 429 SANDEL EHSI INTERCONN. (1 400 SERIES UNIT, 1 SANDEL SN3308)..............F-43

FIGURE F-22. ARINC 429 SANDEL EHSI INTERCONNECT (2 GNS 430, 1 SANDEL SN3308).......................F-45

FIGURE F-23. ARINC 429 SANDEL EHSI INTERCONNECT (2 GNS 430, 2 SANDEL SN3308).......................F-47

FIGURE F-24. ARINC 429/RS-232 AIR DATA/IRU/AHRS INTERCONNECT.....................................................F-49

FIGURE F-25. ARINC 429 FLIGHT CONTROL INTERCONNECT ......................................................................F-51

FIGURE F-26. TRAFFIC ADVISORY SYSTEM INTERCONNECT......................................................................F-53

FIGURE F-27. WEATHER AND TERRAIN INTERCONNECT .............................................................................F-55

FIGURE F-28. AUDIO PANEL INTERCONNECT..................................................................................................F-57

FIGURE F-29. VOR/ILS INDICATOR INTERCONNECT ......................................................................................F-59

FIGURE F-30. RMI/OBI INTERCONNECT.............................................................................................................F-61

FIGURE F-31. KING SERIAL PANEL DME TUNING INTERCONNECT............................................................F-63

400 SERIES INSTALLATION MANUAL Page iii

P/N 190-00140-02 Rev N

LIST OF FIGURES - CONTINUED

FIGURE F-32. KING SERIAL REMOTE DME TUNING INTERCONNECT ........................................................F-65

FIGURE F-33. PARALLEL 2 OF 5 DME TUNING INTERCONNECT ..................................................................F-67

FIGURE F-34. PARALLEL BCD/SLIP CODE DME TUNING INTERCONNECT................................................F-69

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

Rev N P/N 190-00140-02

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

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF MODIFICATION

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

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

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

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

2 0101 2/16/01 Remote COM transfer

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

performance

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

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

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 v

P/N 190-00140-02 Rev N

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Page vi 400 SERIES INSTALLATION MANUAL

Rev N P/N 190-00140-02

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 reserved for future expansion.

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 GPS 400 Series product lens is coated with a special anti-reflective coating which is
very sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING
AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important
to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is
specified as safe for anti-reflective coatings.

CAUTION

The use of ground-based cellular telephones while aircraft are airborne is prohibited by
FCC rules. Due to potential interference with onboard systems, the use of ground-based
cell phones while the aircraft is on the ground is subject to FAA regulation 14 CFR

§91.21.

FCC regulation 41 CFR §22.925 prohibits airborne operation of ground-based cellular
telephones installed in or carried aboard aircraft. Ground-based cellular telephones must
not be operated while aircraft are off the ground. When any aircraft leaves the ground, all
ground-based cellular telephones on board that aircraft must be turned off.

Ground-based cell phones that are on, even in a monitoring state, can disrupt GPS
performance.

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

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
Bezel Width
Rack Height (Dimple-to­dimple)
Rack Width
Depth Behind Panel with
Connectors (Measured from
face of aircraft panel to rear of
connector backshells)
GPS 400 Weight (Unit only)
GPS 400 Weight (Installed with
rack and connectors)
GNC 420 Weight (Unit only)
GNC 420 Weight (Installed with
rack and connectors)
GNS 430 Weight (Unit only)
GNS 430 Weight (Installed with
rack and connectors)

2.66 in. (67 mm)

6.25 in. (159 mm)

2.69 in. (68 mm)

6.32 in. (160 mm)

11.00 in. (279 mm)

3.8 lbs. (1.7 kg)

4.9 lbs. (2.2 kg)

4.5 lbs. (2.0 kg)

5.8 lbs. (2.6 kg)

5.1 lbs. (2.3 kg)

6.5 lbs. (2.9 kg)

Page 1-2 400 SERIES INSTALLATION MANUAL
Rev N P/N 190-00140-02

1.3.2 General Specifications

Operating Temperature Range

Humidity
Altitude Range
Input Voltage Range (GPS 400)
Input Voltage Range
GNS 430 (011-00280-00) and
GNC 420 (011-00506-00)
Input Voltage Range
GNS 430 (011-00280-10, -30)
GNC 420 (011-00506-10, -30)
GNS 430 (A) (011-00836-00,-10)
GNC 420 (A) (011-00837-00,-10)
Power Requirements—P4001
(GPS 400 Main Connector)
Power Requirements—P4001
(GNC 420 Main Connector)
Power Requirements—P4001
(GNS 430 Main Connector)
Power Requirements—P4002
(COM Connector)
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)
Superflag Power Requirements

Software
Environmental Testing

-20°C to +55°C. For more details see Environmental
Qualification Form.
95% non-condensing

-1,500 ft to 50,000 ft
11 to 33 V
22 to 33 V

11 to 33 V

28 V

0.72 A @ 27.5 V

1.44 A @ 13.75 V

1.5 A @ 27.5 V

1.5 A @ 27.5 V

15 mA @ 27.5 V

3.0 A @ 27.5 V

15 mA @ 27.5 V

3.0 A @ 27.5 V
10 mA @ 13.75 V

6.0 A @ 13.75 V
500 mA max. per superflag output @ 27.5 V

DC

DC

DC

DC

________or

DC

DC

(maximum)

DC

(maximum)

DC

(not transmitting);

DC

(transmitting)

DC

(not transmitting);

DC

(transmitting)_______or

DC

(not transmitting);

DC

(transmitting)

DC

DC.

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

1.0 A max. @ 27.5 V

on P4006 (VOR/LOC, G/S

DC

Superflags).
RTCA DO-178B level C
RTCA DO-160C.
For more details see Environmental Qualification Forms.

1.3.3 GPS Specifications

Regulatory Compliance
Acquisition Time

TSO C129a, RTCA DO-208
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
Dynamics

1000 kts.
6 g

400 SERIES INSTALLATION MANUAL Page 1-3
P/N 190-00140-02 Rev N

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 (ETSO-2C37e for the GNS 430A),
JTSO-2C38e (ETSO-2C38e for the GNS 430A),
RTCA DO-186a
ICAO Annex 10 Volume III (Part II – Voice Communications
Systems) Par. 2.3.3

Audio Output
Audio Response
Audio Distortion

100 mW minimum into a 500 Ω load.
Less than 6 dB of variation between 350 and 2500 Hz.
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
Transmitter Power
Transmitter Duty Cycle
Modulation Capability

Greater than 85 dB.
At Least 10 watts, 16 watts for “A” models
Recommended 10% maximum.
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
Frequency Stability
Demodulated Audio Distortion

Shall be at least 45 dB (S+N)/N.

0.0005%
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.

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

1.3.5 VOR Specifications (GNS 430 Only)

Regulatory Compliance

TSO C40c, JTSO-2C40c (ETSO-2C40c for the GNS 430A),
RTCA DO-196, EuroCAE ED-22B

Receiver Audio Sensitivity
Course Deviation Sensitivity
Flag

At -103.5 dBm (S+N)/N shall not be less than 6 dB.

-103.5 dBm or less for 60% of standard deflection.
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
VOR OBS Bearing Accuracy

Greater than 80 dB.
The bearing information as presented to the pilot shall not
have an error in excess of 2.7° as specified by RTCA DO­196 and EuroCAE ED-22B.

Audio Output
Audio Response

A minimum 100 mW into a 500 Ω load.
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.

400 SERIES INSTALLATION MANUAL Page 1-5
P/N 190-00140-02 Rev N

1.3.6 LOC Specifications (GNS 430 Only)

Regulatory Compliance

TSO C36e, JTSO-C36e (ETSO-C36e for the GNS 430A),
RTCA DO-195 CLASS A, EuroCAE ED-46B

Receiver Audio Sensitivity
Course Deviation Sensitivity
Flag

At -103.5 dBm (S+N)/N shall not be less than 6 dB.

-103.5 dBm or less for 60% of standard deflection.
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
Centering Accuracy
Audio Output
Audio Response

Greater than 80 dB.
Typical 0 ± 3 mV (Max error 9.9 mV per RTCA DO-195).
A minimum 100 mW into a 500 Ω load.
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 (ETSO-C34e for the GNS 430A),
RTCA DO-192, EuroCAE ED-47B

Sensitivity
Centering Accuracy
Selectivity

-87 dBm or less for 60% of standard deflection.
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.

Page 1-6 400 SERIES INSTALLATION MANUAL
Rev N P/N 190-00140-02

1.4 TSO LIMITATIONS

A limitation exists pertaining to TSO-C36e (Localizer) and TSO-C34e (Glideslope). The main board
lateral deviation (J4001 Pin 21 MAIN +LEFT and J4001 Pin 22 MAIN +RIGHT) and vertical deviation
(J4001 Pin 27 MAIN +UP and J4001 Pin 28 MAIN +DOWN) outputs exceed the respective TSO MOPS
requirement for current response time due to 120 milliseconds of internal transport delay. Except for this
transport delay, the output characteristics meet the TSO MOPS requirement. Consequently, these outputs
should be used only in applications where the transport delay has been evaluated and found to meet
installation requirements.

1.5 LICENSE REQUIREMENTS

The Telecommunications Act of 1996, effective February 8, 1996, provides the FCC discretion to eliminate
radio station license requirements for aircraft and ships. The 400 Series unit installation must comply with
current transmitter licensing requirements. To find out the specific details on whether a particular
installation is exempt from licensing, please visit the FCC web site http://wireless.fcc.gov/aviation.

If an aircraft license is required, make application for a license on FCC form 404, Application for Aircraft
Radio Station License. The FCC also has a fax-on-demand service to provide forms by fax. The 400
Series unit owner accepts all responsibility for obtaining the proper licensing before using the transponder.

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.

1.6 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.

1.7 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.

400 SERIES INSTALLATION MANUAL Page 1-7
P/N 190-00140-02 Rev N

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.

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.

1.8 LIMITED WARRANTY

This Garmin product is warranted to be free from defects in materials or workmanship for two years 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

st

Street Unit 4, The Quadrangle, Abbey Park Industrial Estate
Olathe, Kansas 66062, U.S.A. Romsey, SO51 9DL, U.K.
Phone: [phone] Phone: [phone]
FAX: [phone] FAX: [phone]

Page 1-8 400 SERIES INSTALLATION MANUAL
Rev N P/N 190-00140-02

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.

400 SERIES INSTALLATION MANUAL Page 2-1
P/N 190-00140-02 Rev N

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 GPS INTERFERENCE

On some installations VHF COM transceivers, Emergency Locator Transmitter (ELT) antennas, and
Direction Finder (DF) receiver antennas can re-radiate through the GPS 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), ELT antenna,
and DF receiver 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), ELT antennas, and DF receiver antennas. 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.

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

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.

400 SERIES INSTALLATION MANUAL Page 2-3
P/N 190-00140-02 Rev N

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.

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

o

Humidity C 95% at +55

o

C

C per minute

o

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

DC

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

o

beam width) -6.0 dBic Minimum

Cross Pole Gain (LHCP)

(on axis) -8 dBic Maximum

o

(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

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

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

010-00139-31 011-00280-30 N Y GRAY 14 or 28 V

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

(2)

(2)

MINIMUM

XMIT
PWR

10 W

10 W

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

400 SERIES INSTALLATION MANUAL Page 3-1
P/N 190-00140-02 Rev N

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

10 W

(2)

010-00173-31 011-00506-30 N Y GRAY 14 or 28 V

10 W

(2)
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

AVAILABLE

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).

Page 3-2 400 SERIES INSTALLATION MANUAL
Rev N P/N 190-00140-02

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

011-00147-00 1

190-00140-10

190-00140-64

190-00140-24

190-00140-04

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 Rev N

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 F-1, page F-3. 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.

Page 3-4 400 SERIES INSTALLATION MANUAL
Rev N P/N 190-00140-02

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.

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:

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

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

44 pin conn

(P4006)

25 pin connector (P4002) Shield ground

connector

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.

To prevent a possible short across the pins in the wiring harness, Teflon shrink tubing P/N
312-00005-05, provided in Connector Kit 011-00351-00 (P4002) covers the oversized
power and ground pin contacts P/N 336-00023-00 (pins 11, 12, 21, 22) that protrude from
the back of the connector shell. Before crimping the pins onto the wire:

1. Cut the tubing (312-00005-05) into 4 equal lengths.

2. Slide a short piece of the tubing over the wire.

3. Strip the wire and crimp the pin (336-00023-00) onto the wire.

4. Insert the pin into the connector shell.

5. Slide the tubing over the exposed portion of the pin and shrink using a heat gun.

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

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.

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.

400 SERIES INSTALLATION MANUAL Page 3-7
P/N 190-00140-02 Rev N

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Page 3-8 400 SERIES INSTALLATION MANUAL
Rev N P/N 190-00140-02

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

40

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 Rev N

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 --

* 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.

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