Garmin 420 GPS Receiver User 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)
£
Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
190-00140-02, Revision L
December 2002
© Copyright 1998 - 2002
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
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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. 151st Street
Olathe, KS 66062 USA
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
A
Revision
Date
6/19/98
B
10/22/98
General update
9891
C
11/11/98
10008
D
3/18/99
Add 18 AWG pin positioner and insertion/extraction
tools. Add King Serial DME tuning interface
description.
Add GNC 420, GPS 400, ARINC 429, GPS King Serial
OBI, RS-232 Fuel/Air Data Inputs
Reflect changes to configuration pages, Misc corrections
Add interface to BF Goodrich Stormscope and Skywatch
and Ryan TCAD
Update installation accessory kits
11871
Add unit versions with 14/28 volt transmitter. Update
configuration pages.
Update configuration pages.
14026
E
6/25/99
F
10/13/99
G
4/27/00
H
9/1/00
J
2/22/01
K
5/22/02
L
12/13/02
Description
ECO #
Initial Release
Insertion
Date
By
----
Add gray unit and 16 watt “A” versions. Update
configuration pages.
Add Fault Detection and Exclusion
10665
11243
13205
15207
18149
19779
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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
P/N 190-00140-02
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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.
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
LIST OF FIGURES
FIGURE 2-1. GPS ANTENNA AND UNIT INSTALLATION CONSIDERATIONS .............................................2-2
FIGURE 3-1.
FIGURE 3-2.
FIGURE 3-3.
FIGURE 3-4.
FIGURE 3-5.
FIGURE 3-6.
FIGURE 3-7.
FIGURE 3-8.
FIGURE 3-9.
COAXIAL CABLE INSTALLATION ................................................................................................3-5
GA 56 ANTENNA INSTALLATION DRAWING .............................................................................3-9
GNS 430 MOUNTING RACK DIMENSIONS ...................................................................................3-11
GNC 420 MOUNTING RACK DIMENSIONS...................................................................................3-13
GPS 400 MOUNTING RACK DIMENSIONS....................................................................................3-15
GNS 430 MOUNTING RACK INSTALLATION...............................................................................3-17
GNC 420 MOUNTING RACK INSTALLATION ..............................................................................3-19
GPS 400 MOUNTING RACK INSTALLATION ...............................................................................3-21
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
P/N 190-00140-02
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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.
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400 SERIES INSTALLATION MANUAL
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 01100280-00, 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
P/N 190-00140-02
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400 SERIES INSTALLATION MANUAL
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 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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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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
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)
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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)
400 SERIES INSTALLATION MANUAL
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
1.3.3
-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 VDC
22 to 33 VDC
11 to 33 VDC
28 VDC
0.72 A @ 27.5 VDC________or
1.44 A @ 13.75 VDC
1.5 A @ 27.5 VDC (maximum)
1.5 A @ 27.5 VDC (maximum)
15 mA @ 27.5 VDC (not transmitting);
3.0 A @ 27.5 VDC (transmitting)
15 mA @ 27.5 VDC (not transmitting);
3.0 A @ 27.5 VDC (transmitting)_______or
10 mA @ 13.75 VDC (not transmitting);
6.0 A @ 13.75 VDC (transmitting)
500 mA max. per superflag output @ 27.5 VDC.
1.0 A max. @ 27.5 VDC on P4001 (Main Superflags).
1.0 A max. @ 27.5 VDC on P4006 (VOR/LOC, G/S
Superflags).
RTCA DO-178B level C
RTCA DO-160C.
For more details see Environmental Qualification Forms.
GPS Specifications
Regulatory Compliance
Acquisition Time
Max Velocity
Dynamics
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
1000 kts.
6g
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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1.3.4
COM Transceiver Specifications (GNC 420 and GNS 430 Only) **
Regulatory Compliance
Audio Output
Audio Response
Audio Distortion
AGC Characteristics
Sensitivity
Squelch
Selectivity
Spurious Response
Transmitter Power
Transmitter Duty Cycle
Modulation Capability
Carrier Noise Level
Frequency Stability
Demodulated Audio Distortion
Sidetone
Demodulated Audio Response
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
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.
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.
(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.
2 µv ±6 dB for 25 kHz channels.
3 µv ±6 dB for 8.33 kHz channels.
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.
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.
Shall be at least 45 dB (S+N)/N.
0.0005%
Less than 10% distortion when the transmitter is modulated
at least 70%.
1.4 VRMS into a 500 Ω load when the transmitter is modulated
at least 70%.
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
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
1.3.5
VOR Specifications (GNS 430 Only)
Regulatory Compliance
Receiver Audio Sensitivity
Course Deviation Sensitivity
Flag
AGC Characteristics
Spurious Response
VOR OBS Bearing Accuracy
Audio Output
Audio Response
Audio Distortion
TSO C40c, JTSO-2C40c, RTCA DO-196, EuroCAE ED-22B
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.
From -99 dBm to -13 dBm input of a Standard VOR Audio
Test Signal, audio output levels shall not vary more than 3
dB.
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 DO-196
and EuroCAE ED-22B.
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.
The distortion in the receiver audio output shall not exceed
10% at all levels up to 100 mW.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 1-5
Page Rev L
1.3.6
LOC Specifications (GNS 430 Only)
Regulatory Compliance
Receiver Audio Sensitivity
Course Deviation Sensitivity
Flag
AGC Characteristics
Selectivity
Spurious Response
Centering Accuracy
Audio Output
Audio Response
Audio Distortion
1.3.7
TSO C36e, JTSO-C36e, RTCA DO-195 CLASS A, EuroCAE
ED-46B
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.
From -86 dBm and -33 dBm input of a Standard VOR Audio
Test Signal, audio output levels shall not vary more than 3
dB.
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.
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.
The distortion in the receiver audio output shall not exceed
10% at all levels up to 100 mW.
Glideslope Specifications (GNS 430 Only)
Regulatory Compliance
Sensitivity
Centering Accuracy
Selectivity
Standard deflection
Flag
Page 1-6
Page Rev L
TSO C34e, JTSO-C34e, RTCA DO-192, EuroCAE ED-47B
-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.
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.
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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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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.
1200 East 151st Street
Olathe, Kansas 66062, U.S.A.
Phone: 913/397.8200
FAX: 913/397.0836
Page 1-8
Page Rev L
Garmin (Europe) Ltd.
Unit 4, The Quadrangle, Abbey Park Industrial Estate
Romsey, SO51 9DL, U.K.
Phone: 44/1794.519944
FAX: 44/1794.519222
400 SERIES INSTALLATION MANUAL
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.
2.
3.
4.
5.
Obtain approved antenna installation design data from the aircraft manufacturer.
Obtain an FAA approved STC, pertaining to, and valid for the antenna installation.
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.
Obtain FAA Advisory Circular AC-183C and identify a DER from the roster of individuals in it.
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
P/N 190-00140-02
Page 2-1
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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.
2.
3.
Replace or clean the VHF COM rack connector to ensure good coax ground.
Place grounding straps between the 400 Series unit, VHF COM and a good ground.
Shield the VHF COM wiring harness.
Page 2-2
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400 SERIES INSTALLATION MANUAL
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.
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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 2-3
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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
Temperature
(operating)
(ground survival)
Altitude
Temperature Variation
Humidity
Vibration
Waterproofness
Fluids
Lightning
Icing
Category
F2
F2
F2
A
C
CLMY
S
F
2A
C
2. Electrical Characteristics
LNA Supply voltage
LNA Supply Current
LNA Operating Frequency
LNA Gain
LNA Noise Figure
LNA Output VSWR (50 Ω)
LNA Input power at -1 dB Gain Compression
LNA Bandwidth
(-3 dB)
(-20 dB)
(-40 dB)
Description
-55 to +70oC
-55 to +85oC
55,000 feet
10oC per minute
95% at +55oC
Turbo/Reciprocating/Helicopter
Continuous Stream
Deicing Fluid
Direct Effects
0.15” thick
4.5 ± 0.5 VDC
20 mA Maximum
1575.42 ± 2.00 MHz
20 dB Maximum, 12dB Minimum
3.0 dB Maximum
2:1 Maximum
-6 dB Minimum
40 MHz Maximum
100 MHz Maximum
250 MHz Maximum
3. Radiation Characteristics
Polarization
Operating Frequency
Gain
(on axis)
(at 160o beam width)
Cross Pole Gain (LHCP)
(on axis)
(at 160o beam width)
-8 dBic Maximum
-9 dBic Maximum
4. Mounting Requirements
Cable connection
Mounting studs
BNC Female
Four 8-32 UNC-2A studs 0.50” long
Page 2-4
Page Rev L
RHCP
1575.42 ± 2.00 MHz
2.0 dBic Minimum
-6.0 dBic Minimum
400 SERIES INSTALLATION MANUAL
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
010-00139-01
010-00139-10
010-00139-11
010-00139-30
010-00139-31
010-00286-00
010-00286-01
010-00286-10
010-00286-11
UNIT
P/N
011-00280-00
011-00280-00
011-00280-10
011-00280-10
011-00280-30
011-00280-30
011-00836-00
011-00836-00
011-00836-10
011-00836-10
GNS
430A
N
N
N
N
N
N
Y
Y
Y
Y
ACCESSORIES
(1)
N
Y
N
Y
N
Y
N
Y
N
Y
COLOR
BLACK
BLACK
BLACK
BLACK
GRAY
GRAY
BLACK
BLACK
GRAY
GRAY
OPERATING
VOLTAGE
28
28
14 or 28 Vdc
14 or 28 Vdc
14 or 28 V (2)
14 or 28 V (2)
28 Vdc
28 Vdc
28 Vdc (2)
28 Vdc (2)
MINIMUM
XMIT PWR
10 W
10 W
10 W
10 W
10 W
10 W
16 W
16 W
16 W
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)
2) Denotes alternate (secondary) power input available, (review installation drawing).
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 3-1
Page Rev L
3.1.2
GNC 420 (A)
CATALOG
P/N
010-00173-00
010-00173-01
010-00173-10
010-00173-11
010-00173-30
010-00173-31
010-00287-00
010-00287-01
010-00287-10
010-00287-11
UNIT
P/N
011-00506-00
011-00506-00
011-00506-10
011-00506-10
011-00506-30
011-00506-30
011-00837-00
011-00837-00
011-00837-10
011-00837-10
GNC
420A
N
N
N
N
N
N
Y
Y
Y
Y
ACCESSORIES
(1)
N
Y
N
Y
N
Y
N
Y
N
Y
COLOR
BLACK
BLACK
BLACK
BLACK
GRAY
GRAY
BLACK
BLACK
GRAY
GRAY
OPERATING
VOLTAGE
28
28
14 or 28 Vdc
14 or 28 Vdc
14 or 28 V (2)
14 or 28 V (2)
28 Vdc
28 Vdc
28 Vdc (2)
28 Vdc (2)
MINIMUM
XMIT PWR
10 W
10 W
10 W
10 W
10 W
10 W
16 W
16 W
16 W
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
010-00171-00
010-00171-01
010-00171-10
010-00171-11
011-00504-00
011-00504-00
011-00504-10
011-00504-10
N
Y
N
Y
BLACK
BLACK
GRAY
GRAY
ALT PWR
AVAILABL
E
N
N
Y
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
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400 SERIES INSTALLATION MANUAL
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
GA 56 ANTENNA SUB-ASSEMBLY
BACKING PLATE
NUT, SELF-LOCKING, #8-32
ANTENNA GASKET
•
QTY
1
1
4
1
GA 56 Flange Mount Antenna Kit (Mod 1 or later, Garmin P/N 010-10040-02). This kit
contains the following items:
ITEM
FLANGE MOUNT GA 56 ANTENNA
SUB-ASSEMBLY
NUT PLATE
SCREW, #10-32 x 5/8”
ANTENNA GASKET
2.
GARMIN P/N
011-00134-00
115-00031-00
210-10004-09
253-00002-00
GARMIN P/N
011-00147-00
QTY
1
115-00080-00
211-62212-14
253-00011-00
1
4
1
Other accessories include the following:
ITEM
MOUNTING RACK, 400/420/430
GPS 400 BACK PLATE ASSEMBLY
GPS 400 CONNECTOR KIT
GNC 420 BACK PLATE ASSEMBLY
GNC 420 CONNECTOR KIT
GNS 430 BACK PLATE ASSEMBLY
GNS 430 CONNECTOR KIT
400 SERIES ADDENDUM FOR TRAFFIC
& WEATHER INTERFACES
GPS 400 PILOT’S GUIDE
GPS 400 QUICK REFERENCE GUIDE
GPS 400 SAMPLE AIRPLANE FLIGHT
MANUAL SUPPLEMENT
GNC 420 PILOT’S GUIDE
GNC 420 QUICK REFERENCE GUIDE
GNC 420 SAMPLE AIRPLANE FLIGHT
MANUAL SUPPLEMENT
GNS 430 PILOT’S GUIDE
GNS 430 QUICK REFERENCE GUIDE
GNS 430 SAMPLE AIRPLANE FLIGHT
MANUAL SUPPLEMENT
GARMIN P/N
115-00243-00
011-00676-03
011-00351-03
011-00676-01
011-00351-01
011-00676-00
011-00351-00
190-00140-10
190-00140-60
190-00140-61
190-00140-64
190-00140-20
190-00140-21
190-00140-24
190-00140-00
190-00140-01
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
P/N 190-00140-02
Page 3-3
Page Rev L
3.2
DATA BASE OPTIONS
ITEM
DATA CARD, WORLD WIDE
DATA CARD, AMERICAS
DATA CARD, INTERNATIONAL
3.3
MISCELLANEOUS OPTIONS
ITEM
CONNECTOR, BNC, MALE, CLAMP
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
3.4
GARMIN P/N
010-10201-00
010-10201-01
010-10201-02
GARMIN P/N
330-00087-00
320-00003-00
320-00003-02
330-00067-00
INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED
The following installation accessories are required but not provided:
COM Antenna:
VOR/LOC Antenna:
Glideslope Antenna:
Headphones:
Microphone:
3.5
(GNC 420 and GNS 430 Only) Shall meet TSO C37() and C38(). Broad band, 50
Ω, vertically polarized with coaxial cable
(GNS 430 Only) Shall meet TSO C40() and C36(). Broad band, 50 Ω,
horizontally polarized with coaxial cable
(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
(GNC 420 and GNS 430 Only) 500 Ω nominal impedance
(GNC 420 and GNS 430 Only) Low impedance, carbon or dynamic, with
transistorized pre-amp
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.
Page 3-4
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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
Connector Type
Wire Gauge
Garmin P/N
Military P/N
AMP
Positronic
ITT Cannon
78 pin conn
44 pin conn
(P4001)
(P4006)
High Density Pin Contact
22-28 AWG
336-00021-00
M39029/58-360
204370-2
M39029/58-360
030-2042-000
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
25 pin connector (P4002)
Standard Density Socket Contact
18 AWG
20-24 AWG
336-00023-00
336-00022-00
N/A
M39029/63-368
N/A
205090-1
FC6018D
M39029/63-368
See Note 3
031-1007-042
Shield ground
connector
.1” Pitch Card-edge
20-24 AWG
336-00029-00
N/A
583853-4
N/A
N/A
Page 3-5
Page Rev L
Table 3-2. Recommended Crimp Tools (or equivalent)
Connector
Type
Wire Gauge
High Density
Standard Density
22-28 AWG
Hand
Crimping
Tool
M22520/2-01
9507
995-0001584
601966-1
AFM8
615717
Military P/N
Positronic
ITT Cannon
AMP
Daniels
Astro
Positioner
M22520/2-09
9502-3
995-0001739
601966-6
K42
615725
18 AWG
Insertion/
Extraction
Tool
M81969/1-04
M81969/1-04
N/A
Positioner
N/A
9502-11
N/A
Insertion/
Extraction
Tool
M81969/1-02
M81969/1-02
N/A
91067-1
M81969/1-04
M81969/1-04
N/A
K774
N/A
N/A
M81969/1-02
M81969/1-02
20-24 AWG
Positioner
M22520/2-08
9502-5
995-0001604
601966-5
K13-1
615724
Insertion/
Extraction
Tool
M81969/1-02
M81969/1-02
980-2000426
91067-2
M81969/1-02
M81969/1-02
NOTES
1.
2.
3.
4.
3.7
Insertion/extraction tools from ITT Cannon are all plastic; others are plastic with metal tip.
Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject
to change without notice.
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.
For the card-edge connector pin contacts, use AMP part number 90272-1 or equivalent
crimping tool.
RACK INSTALLATION
1.
2.
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.
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.
3.
4.
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.
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.
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
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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
P/N 190-00140-02
Page 3-7
Page Rev L
This page intentionally left blank.
Page 3-8
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
3.10
GA 56 Antenna Installation Drawing
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-2. GA 56 Antenna Installation Drawing
Page 3-9 (Page 3-10 blank)
Page Rev L
3.11
Mounting Rack Dimensions
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-3. GNS 430 Mounting Rack Dimensions
Page 3-11 (Page 3-12 blank)
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-4. GNC 420 Mounting Rack Dimensions
Page 3-13 (Page 3-14 blank)
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-5. GPS 400 Mounting Rack Dimensions
Page 3-15 (Page 3-16 blank)
Page Rev L
3.12
Mounting Rack Installation
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-6. GNS 430 Mounting Rack Installation
Page 3-17 (Page 3-18 blank)
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-7. GNC 420 Mounting Rack Installation
Page 3-19 (Page 3-20 blank)
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-8. GPS 400 Mounting Rack Installation
Page 3-21 (Page 3-22 blank)
Page Rev L
3.13
Recommended Panel Cutout Dimensions
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 3-9. 400 Series Recommended Panel Cutout Dimensions
Page 3-23 (Page 3-24 blank)
Page Rev L
4.
SYSTEM INTERCONNECTS
4.1
PIN FUNCTION LIST
4.1.1
P4001
View of J4001 connector from back of unit
60
40
61
41 42
21
1
Pin
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
62
22
2
63
43
23
3
64
44
24
4
65
45
25
5
66
46
26
6
67
47
27
7
68
48
28
8
69
49
29
9
30
10
70
50
71
72
51 52
31
11
32
12
73
53
33
13
74
54
34
14
75
55
35
15
76
56
36
16
77
57
37
17
78
58
38
18
59
39
19
20
Pin Name
VLOC ANNUNCIATE
GPS ANNUNCIATE
WAYPOINT ANNUNCIATE
TERMINAL ANNUNCIATE
APPROACH ANNUNCIATE
MESSAGE ANNUNCIATE
OBS ANNUNCIATE
AUTO ANNUNCIATE
INTEGRITY ANNUNCIATE
ANNUNCIATE D
ANNUNCIATE E
ALTITUDE ALARM ANNUNCIATE (Not implemented at time of publication)
ANNUNCIATE F (Not implemented at time of publication)
ILS/GPS APPROACH
AIRCRAFT POWER 2*
TIME MARK OUT
MAIN LATERAL SUPERFLAG
MAIN VERTICAL SUPERFLAG
AIRCRAFT POWER 1
AIRCRAFT POWER 1
MAIN +LEFT
MAIN +RIGHT (2.5V COMMON)
MAIN LATERAL +FLAG
MAIN LATERAL -FLAG (2.5V COMMON)
MAIN +TO
MAIN +FROM (2.5V COMMON)
MAIN +UP
MAIN +DOWN (2.5V COMMON)
MAIN VERTICAL +FLAG
MAIN VERTICAL -FLAG (2.5V COMMON)
MAIN OBS ROTOR C
MAIN OBS ROTOR H (GROUND)
MAIN OBS STATOR D
MAIN OBS STATOR E (2.5V COMMON OBS)
MAIN OBS STATOR F
MAIN OBS STATOR G (2.5V COMMON OBS)
I/O
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
In
Out
Out
Out
In
In
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
In
Out
In
Out
* 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
P/N 190-00140-02
Page 4-1
Page Rev L
Connector P4001, continued
Pin
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
Pin Name
ALTITUDE ALARM AUDIO HI (Not implemented at time of publication)
ALTITUDE ALARM AUDIO LO (Not implemented at time of publication)
LIGHTING BUS HI
LIGHTING BUS LO
GPS RS 232 OUT 3
GPS RS 232 IN 3
MAIN OBI CLOCK
MAIN OBI DATA
MAIN OBI SYNC
GPS ARINC 429 OUT A
GPS ARINC 429 OUT B
GPS ARINC 429 IN 1 A
GPS ARINC 429 IN 1 B
GPS ARINC 429 IN 2 A
GPS ARINC 429 IN 2 B
RESERVED
RESERVED
GPS RS 232 OUT 4
GPS RS 232 IN 4
GPS RS 232 OUT 1
GPS RS 232 IN 1
GPS RS 232 OUT 2
GPS RS 232 IN 2
ALTITUDE COMMON (GROUND)
ALTITUDE C4
ALTITUDE C2
ALTITUDE C1
ALTITUDE B4
ALTITUDE B2
ALTITUDE B1
ALTITUDE A4
ALTITUDE A2
ALTITUDE A1
ALTITUDE D4
OBS MODE SELECT
AIRCRAFT POWER 2*
CDI SOURCE SELECT
RESERVED
DEMO MODE SELECT
RESERVED
AIRCRAFT GROUND
AIRCRAFT GROUND
I/O
Out
Out
In
In
In
Out
Out
Out
Out
Out
Out
In
In
In
In
--Out
In
Out
In
Out
In
Out
In
In
In
In
In
In
In
In
In
In
In
In
In
-In
----
* 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
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
4.1.2
P4002 (GNC 420 and GNS 430 Only)
View of J4002 connector from back of unit
1
2
14
Pin
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
3
15
4
16
Pin Name
RESERVED
RESERVED
RESERVED
COM MIC KEY
INTERCOM MIC HI
COM MIC AUDIO HI
500Ω COM AUDIO HI
RESERVED
RESERVED
RESERVED
AIRCRAFT POWER
AIRCRAFT POWER
RESERVED
TRANSMIT INTERLOCK
COM REMOTE TRANSFER
SPARE
INTERCOM MIC LO
COM MIC AUDIO LO
500Ω COM AUDIO LO
RESERVED
AIRCRAFT GROUND
AIRCRAFT GROUND
RESERVED
RESERVED
RESERVED
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
5
17
6
18
7
19
8
20
9
10
21 22
11
23
12
24
13
25
I/O
---In
In
In
Out
---In
In
-In
In
-In
In
Out
-------
Page 4-3
Page Rev L
4.1.3
P4006 (GNS 430 Only)
View of J4006 connector from back of unit
15
14
30
13
29
44
Pin
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
12
28
43
11
27
42
10
26
41
9
25
40
8
24
39
38
7
23
37
6
22
36
5
4
21 20
35
3
19
34
2
18
33
1
17
32
16
31
Pin Name
VOR/LOC +TO
VOR/LOC +FROM (VOR/LOC COMMON)
VOR/LOC +FLAG
VOR/LOC -FLAG (VOR/LOC COMMON)
VOR/LOC +LEFT
VOR/LOC +RIGHT (VOR/LOC COMMON)
RESERVED
VOR/LOC COMPOSITE OUT
VOR OBS ROTOR C
VOR OBS ROTOR H (GROUND)
VOR OBS STATOR E/G (VOR/LOC COMMON)
VOR OBS STATOR F
VOR OBS STATOR D
PARALLEL DME - 8MHZ
VOR/LOC SUPERFLAG
500Ω VOR/ILS AUDIO HI
500Ω VOR/ILS AUDIO LO
SERIAL DME CLOCK
SERIAL DME DATA
SER DME - CHAN REQ/PAR DME - 4MHZ
SER DME - RNAV MODE/PAR DME - 2MHZ
DME COMMON
VOR/ILS ARINC 429 OUT B
VOR/ILS ARINC 429 OUT A
VOR OBI CLOCK
VOR OBI SYNC
VOR OBI DATA
VLOC REMOTE TRANSFER
ILS ENERGIZE
GLIDESLOPE +FLAG
GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE COMMON)
GLIDESLOPE +UP
PARALLEL DME - 1MHZ
RESERVED
VOR/ILS ARINC 429 IN B
VOR/ILS ARINC 429 IN A
PARALLEL DME - 800KHZ
GLIDESLOPE SUPERFLAG
PARALLEL DME - 400KHZ
PARALLEL DME - 200KHZ
AIRCRAFT GROUND
PARALLEL DME - 100KHZ
PARALLEL DME - 50KHZ
AIRCRAFT POWER
Page 4-4
Page Rev L
I/O
Out
Out
Out
Out
Out
Out
-Out
Out
Out
In
In
In
Out
Out
Out
Out
Out
Out
I/O
I/O
In
Out
Out
Out
Out
Out
In
Out
Out
Out
Out
Out
-In
In
Out
Out
Out
Out
-Out
Out
In
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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
AIRCRAFT POWER 1
AIRCRAFT POWER 1
AIRCRAFT POWER 2 *
AIRCRAFT POWER 2 *
AIRCRAFT POWER
AIRCRAFT POWER
AIRCRAFT POWER
AIRCRAFT GROUND
AIRCRAFT GROUND
AIRCRAFT GROUND
AIRCRAFT GROUND
AIRCRAFT GROUND
Connector
P4001
P4001
P4001
P4001
P4002
P4002
P4006
P4001
P4001
P4002
P4002
P4006
Pin
19
20
15
72
11
12
44
77
78
21
22
41
I/O
In
In
In
In
In
In
In
------
* 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 VDC. GNC 420 P/N 011-00506-10 and GNS 430 P/N 011-00280-10 accept 11-33
VDC 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
LIGHTING BUS HI
LIGHTING BUS LO
Connector
P4001
P4001
Pin
39
40
I/O
In
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
GPS ANTENNA
COM ANTENNA
VOR/LOC ANTENNA
GLIDESLOPE ANTENNA
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Connector
P4003
P4004
P4005
P4007
I/O
In
I/O
In
In
Page 4-5
Page Rev L
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
ALTITUDE D4
ALTITUDE A1
ALTITUDE A2
ALTITUDE A4
ALTITUDE B1
ALTITUDE B2
ALTITUDE B4
ALTITUDE C1
ALTITUDE C2
ALTITUDE C4
ALTITUDE COMMON
Connector
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
Pin
70
69
68
67
66
65
64
63
62
61
60
I/O
In
In
In
In
In
In
In
In
In
In
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 VDC.
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
Page Rev L
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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
MAIN +LEFT
MAIN +RIGHT (2.5V COMMON)
MAIN +UP
MAIN +DOWN (2.5V COMMON)
Connector
P4001
P4001
P4001
P4001
Pin
21
22
27
28
I/O
Out
Out
Out
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 mVDC ±10%.
4.4.2.2 TO/FROM
Pin Name
MAIN +TO
MAIN +FROM (2.5V COMMON)
Connector
P4001
P4001
Pin
25
26
I/O
Out
Out
The output is capable of driving up to three 200 Ω meter loads. When indicating TO, MAIN +TO is
+190 ±40 mVDC with respect to MAIN +FROM. When indicating FROM, MAIN +TO is -190 ±40 mVDC
with respect to MAIN +FROM. When invalid information is present (Flag IN VIEW) the TO/FROM
output is 0 ±10 mVDC.
4.4.2.3 Flag
Pin Name
MAIN LATERAL +FLAG
MAIN LATERAL -FLAG (2.5V COMMON)
MAIN VERTICAL +FLAG
MAIN VERTICAL -FLAG (2.5V COMMON)
Connector
P4001
P4001
P4001
P4001
Pin
23
24
29
30
I/O
Out
Out
Out
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 mVDC. When invalid information is present (Flag IN
VIEW) the Flag output is 0 ±25 mVDC.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-7
Page Rev L
4.4.2.4 Superflags
Pin Name
MAIN LATERAL SUPERFLAG
MAIN VERTICAL SUPERFLAG
Connector
P4001
P4001
Pin
17
18
I/O
Out
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 VDC) when the flag is to be OUT OF VIEW. The
output voltage with respect to ground is less than 0.25 VDC when the flag is to be IN VIEW.
4.4.2.5 OBS
Pin Name
MAIN OBS ROTOR C
MAIN OBS ROTOR H (GROUND)
MAIN OBS STATOR D
MAIN OBS STATOR E (2.5V COMMON OBS)
MAIN OBS STATOR F
MAIN OBS STATOR G (2.5V COMMON OBS)
Connector
P4001
P4001
P4001
P4001
P4001
P4001
Pin
31
32
33
34
35
36
I/O
Out
Out
In
Out
In
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
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-9
Page Rev L
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
VLOC ANNUNCIATE
GPS ANNUNCIATE
WAYPOINT ANNUNCIATE
TERMINAL ANNUNCIATE
APPROACH ANNUNCIATE
MESSAGE ANNUNCIATE
OBS ANNUNCIATE
AUTO ANNUNCIATE
INTEGRITY ANNUNCIATE
ILS/GPS APPROACH
All outputs sink up to 500 mA when activated.
4.5.2.2 Switch Inputs
Pin Name
OBS MODE SELECT
CDI SOURCE SELECT
DEMO MODE SELECT
Connector
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
Pin
1
2
3
4
5
6
7
8
9
14
I/O
Out
Out
Out
Out
Out
Out
Out
Out
Out
Out
Connector
P4001
P4001
P4001
Pin
71
73
75
I/O
In
In
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 VDC.
4.5.2.3 TIME MARK OUT
Pin Name
TIME MARK OUT
Connector
P4001
Pin
16
I/O
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.
Page 4-10
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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
1 2 3 4
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
• • •
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-11
Page Rev L
Label #
251
251G
252
260G
261G
275G
300G
303
304G
305G
306G
307G
310
311
312
313
314
315
316
320
321
326G
330
331
332
333
334
335
340
351G
352G
371G
377
Parameter Name
Distance to Go
Distance to Go
Time to Go
Date (BCD)
GPS Discrete Word 1
LRN Status Word
Station Declination, Type, and Class
Message Length/Type/Number
Message Characters 1-3
Message Characters 4-6
NAV/Waypoint/Airport Latitude
NAV/Waypoint/Airport Longitude
Present Position Latitude
Present Position Longitude
Ground Speed
Track Angle (True)
True Heading
Wind Speed
Wind Angle (True)
Magnetic Heading
Drift Angle
Lateral Scale Factor
Conic Arc Inbound Course
Conic Arc Radius
Conic Arc Course Change Angle
Airport Runway Azimuth
Airport Runway Length in Feet
Left/Right Hand Holding Pattern Azimuth
Left/Right Hand Procedure Turn Azimuth
Distance To Destination (Via Flight Plan)
Estimated Time To Destination (Via Flight Plan)
Specific Equipment ID
Equipment Hex ID Code
1 2
•
•
• •
•
•
•
•
•
•
•
•
•
• •
• •
• •
• •
• •
• •
• •
• •
• •
•
•
•
•
•
•
3 4
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
The following labels are output on the VOR/ILS ARINC 429 OUT port:
Label #
034G
035G
100G
173
174
222
371G
377
Parameter Name
VOR/ILS Frequency (BCD)
DME Frequency (BCD)
Selected Course #1
Localizer Deviation
Glideslope Deviation
VOR Omnibearing
Specific Equipment ID
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.
Page 4-12
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
4.6.2
Serial Data Electrical Characteristics
4.6.2.1 RS-232
Pin Name
GPS RS 232 OUT 1
GPS RS 232 IN 1
GPS RS 232 OUT 2
GPS RS 232 IN 2
GPS RS 232 OUT 3
GPS RS 232 IN 3
GPS RS 232 OUT 4
GPS RS 232 IN 4
Connector
P4001
P4001
P4001
P4001
P4001
P4001
P4001
P4001
Pin
56
57
58
59
41
42
54
55
I/O
Out
In
Out
In
Out
In
Out
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
GPS ARINC 429 OUT A
GPS ARINC 429 OUT B
GPS ARINC 429 IN 1 A
GPS ARINC 429 IN 1 B
GPS ARINC 429 IN 2 A
GPS ARINC 429 IN 2 B
VOR/ILS ARINC 429 OUT A
VOR/ILS ARINC 429 OUT B
VOR/ILS ARINC 429 IN A
VOR/ILS ARINC 429 IN B
Connector
P4001
P4001
P4001
P4001
P4001
P4001
P4006
P4006
P4006
P4006
Pin
46
47
48
49
50
51
24
23
36
35
I/O
Out
Out
In
In
In
In
Out
Out
In
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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-13
Page Rev L
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
COM MIC KEY
Connector
P4002
Pin
4
I/O
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 VDC.
4.7.2.2 COM MIC AUDIO, INTERCOM MIC AUDIO
Pin Name
COM MIC AUDIO HI
COM MIC AUDIO LO
INTERCOM MIC HI
INTERCOM MIC LO
Connector
P4002
P4002
P4002
P4002
Pin
6
18
5
17
I/O
In
In
In
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 mVRMS to modulate the transmitter at 80% nominally. The
microphone gain adjustment is accessible through the top cover.
When a 125 mVRMS signal at 1000 Hz is applied to the INTERCOM MIC input, the level on the COM
AUDIO output is not less than 7.07 VRMS.
Page 4-14
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
4.7.2.3 COM AUDIO, VOR/ILS AUDIO
Pin Name
500Ω COM AUDIO HI
500Ω COM AUDIO LO
500Ω VOR/ILS AUDIO HI
500Ω VOR/ILS AUDIO LO
Connector
P4002
P4002
P4006
P4006
Pin
7
19
16
17
I/O
Out
Out
Out
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
TRANSMIT INTERLOCK
COM REMOTE TRANSFER
VLOC REMOTE TRANSFER
Connector
P4002
P4002
P4006
Pin
14
15
28
I/O
In
In
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 VDC.
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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-15
Page Rev L
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
VOR/LOC SUPERFLAG
GLIDESLOPE SUPERFLAG
Connector
P4006
P4006
Pin
15
38
I/O
Out
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 VDC) when the flag is to be OUT OF VIEW. The
output voltage with respect to ground is less than 3 VDC when the flag is to be IN VIEW.
4.8.2.2 Deviation
Pin Name
VOR/LOC +LEFT
VOR/LOC +RIGHT (VOR/LOC COMMON)
GLIDESLOPE +UP
GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE
COMMON)
Connector
P4006
P4006
P4006
P4006
Pin
5
6
32
31
I/O
Out
Out
Out
Out
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 mVDC ±10%.
4.8.2.3 TO/FROM
Pin Name
VOR/LOC +TO
VOR/LOC +FROM (VOR/LOC COMMON)
Connector
P4006
P4006
Pin
1
2
I/O
Out
Out
The output is capable of driving up to three 200 Ω meter loads. When indicating TO, the output is
+225 ±75 mVDC. When indicating FROM, output is -225 ±75 mVDC. When invalid information is present
(Flag IN VIEW) the TO/FROM output is 0 ±10 mVDC.
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
4.8.2.4 Flag
Pin Name
VOR/LOC +FLAG
VOR/LOC -FLAG (VOR/LOC COMMON)
GLIDESLOPE +FLAG
GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE
COMMON)
Connector
P4006
P4006
P4006
P4006
Pin
3
4
30
31
I/O
Out
Out
Out
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 mVDC. When invalid information is present (Flag IN
VIEW) the Flag output is 0 ±25 mVDC.
4.8.2.5 OBS
Pin Name
VOR OBS ROTOR C
VOR OBS ROTOR H (GROUND)
VOR OBS STATOR D
VOR OBS STATOR F
VOR OBS STATOR E/G (VOR/LOC
COMMON)
Connector
P4006
P4006
P4006
P4006
P4006
Pin
9
10
13
12
11
I/O
Out
Out
In
In
Out
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
VOR/LOC COMPOSITE OUT
Connector
P4006
Pin
8
I/O
Out
With a Standard VOR Test Signal applied, VOR/LOC COMPOSITE OUT is 0.5 ±0.1 VRMS into a 10 kΩ
load. With a Standard Localizer Centering Test Signal applied, VOR/LOC COMPOSITE OUT is 0.350
±0.05 VRMS into a 10 kΩ load.
4.8.2.7 ILS ENERGIZE
Pin Name
ILS ENERGIZE
Connector
P4006
Pin
29
I/O
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.
400 SERIES INSTALLATION MANUAL
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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
MAIN OBI CLOCK
MAIN OBI SYNC
MAIN OBI DATA
Connector
P4001
P4001
P4001
Pin
43
45
44
I/O
Out
Out
Out
Pin Name
VOR OBI CLOCK
VOR OBI SYNC
VOR OBI DATA
Connector
P4006
P4006
P4006
Pin
25
26
27
I/O
Out
Out
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 µADC.
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.
Page 4-18
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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 VDC.
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 VDC.
NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling
the DME.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-19
Page Rev L
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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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
4.11
400 SERIES INTERCONNECTS
4.11.1 400 Series System Interface Diagram
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-1. 400 Series System Interface Diagram
Page 4-21 (Page 4-22 blank)
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4.11.2 400 Series Typical Installations
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-2. GNS 430 Typical Installation
Page 4-23 (Page 4-24 blank)
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-3. GNC 420 Typical Installation
Page 4-25 (Page 4-26 blank)
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P/N 190-00140-02
Figure 4-4. GPS 400 Typical Installation
Page 4-27 (Page 4-28 blank)
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4.11.3 Power, Lighting, and Antennas Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-5. Power, Lighting, and Antennas Interconnect
Page 4-29 (Page 4-30 blank)
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4.11.4 Altimeter Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-6. Altimeter Interconnect
Page 4-31 (Page 4-32 blank)
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4.11.5 Main Indicator Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-7. Main Indicator Interconnect
Page 4-33 (Page 4-34 blank)
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4.11.6 KI 209A Main Indicator Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-8. KI 209A Main Indicator Interconnect
Page 4-35 (Page 4-36 blank)
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4.11.7 KI 208A Main Indicator Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-9. KI 208A Main Indicator Interconnect
Page 4-37 (Page 4-38 blank)
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4.11.8 Annunciators/Switches Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-10. Annunciators/Switches Interconnect
Page 4-39 (Page 4-40 blank)
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4.11.9 RS-232 Serial Data Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-11. RS-232 Serial Data Interconnect
Page 4-41 (Page 4-42 blank)
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4.11.10 ARINC 429 EFIS Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-12. ARINC 429 EFIS Interconnect
Page 4-43 (Page 4-44 blank)
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4.11.11 ARINC 429 Sandel EHSI Interconnect (1 400 Series Unit, 1 Sandel SN3308)
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-13. ARINC 429 Sandel EHSI Interconnect (1 400 Series Unit, 1 Sandel SN3308)
Page 4-45 (Page 4-46 blank)
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4.11.12 ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 1 Sandel SN3308)
400 SERIES INSTALLATION MANUAL
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Figure 4-14. ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 1 Sandel SN3308)
Page 4-47 (Page 4-48 blank)
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4.11.13 ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 2 Sandel SN3308)
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-15. ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 2 Sandel SN3308)
Page 4-49 (Page 4-50 blank)
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4.11.14 ARINC 429 Air Data/IRU/AHRS Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-16. ARINC 429 Air Data/IRU/AHRS Interconnect
Page 4-51 (Page 4-52 blank)
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4.11.15 ARINC 429 Flight Control Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-17. ARINC 429 Flight Control Interconnect
Page 4-53 (Page 4-54 blank)
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4.11.16 Traffic Advisory System Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-18. Traffic Advisory System Interconnect
Page 4-55 (Page 4-56 blank)
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4.11.17 Weather and Terrain Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-19. Weather and Terrain Interconnect
Page 4-57 (Page 4-58 blank)
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4.11.18 Audio Panel Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 4-59 (Page 4-60 blank)
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4.11.19 VOR/ILS Indicator Interconnect
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Figure 4-21. VOR/ILS Indicator Interconnect
Page 4-61 (Page 4-62 blank)
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4.11.20 RMI/OBI Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-22. RMI/OBI Interconnect
Page 4-63 (Page 4-64 blank)
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4.11.21 King Serial Panel DME Tuning Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-23. King Serial Panel DME Tuning Interconnect
Page 4-65 (Page 4-66 blank)
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4.11.22 King Serial Remote DME Tuning Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-24. King Serial Remote DME Tuning Interconnect
Page 4-67 (Page 4-68 blank)
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4.11.23 Parallel 2 OF 5 DME Tuning Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-25. Parallel 2 OF 5 DME Tuning Interconnect
Page 4-69 (Page 4-70 blank)
Page Rev L
4.11.24 Parallel BCD/Slip Code DME Tuning Interconnect
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 4-26. Parallel BCD/Slip Code DME Tuning Interconnect
Page 4-71 (Page 4-72 blank)
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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).
Figure 5-1.
MAIN ARINC 429 CONFIG Page
SPEED
Selection
Description
Low
High
Standard low-speed ARINC 429 (nominally 12.5 kilobits per second)
High-speed ARINC 429 (nominally 100 kilobits per second)
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 5-1
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DATA IN 1, DATA IN 2
Selection
Description
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
Airdata/AHRS
system.
Traffic information from the following traffic advisory systems:
Traffic Advisory
BF Goodrich SKY497 Skywatch/Skywatch HP
Bendix/King KTA 870, KMH 880
Selected course, heading, and joystick waypoint information from the
EFIS
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
EFIS/Airdata
information from the following systems:
Collins Pro Line 21
Selected course information from the following Flight Control systems:
Flight control
Bendix/King KFC 400
DATA IN 1, DATA IN 2, cont.
Selected course, heading, and true airspeed data from the GARMIN GAD 42.
GARMIN GAD 42
Selected course, heading, and joystick waypoint information from the
Honeywell EFIS
following EFIS systems:
Honeywell Primus 1000
Heading information from the following Inertial systems:
INS/IRU
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.
Radar graphics
Selected course and heading information from the following EHSI system:
Sandel EHSI
Sandel SN3308
Off
Airdata
Page 5-2
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
DATA OUT
Selection
Description
Off
ARINC 429
GAMA 429
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, 2nd Edition. The output data
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, 2nd
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, 2nd
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, 2nd
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, 2nd
Edition. The output data includes navigation and flight plan information to
the following EFIS systems:
Sextant SMD 45
GAMA 429 Graphics
GAMA 429 Graphics
w/Int
GAMA 429
Pro Line 21
GAMA 429 Sextant
SDI
Selection
Description
Common
LNAV 1
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.
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.
Figure 5-2. MAIN RS232 CONFIG Page
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 5-3
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CHANNEL INPUTS
Selection
Description
Off
Arnav/ei-fuel
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.
Crossfill
GDL 49
Icarus-alt
Ryan TCAD
Shadin-adc
Shadin-alt
Shadin-fadc
Shadin-fuel
WX-500
CHANNEL OUTPUTS
Selection
Description
Off
Aviation
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.
Avtn no alt
Crossfill
HW EGPWS
Ryan TCAD
WX-500
FUEL TYPE
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.)
Page 5-4
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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.
Figure 5-3. MAIN INPUTS 1 Page
Field
Description
OAT
SAT
TAT
IAS
TAS
WSPD
HDG
WDIR
B ALT
D ALT
P ALT
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
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.
Field
Description
L FF
R FF
T FF
T FOB
GPS SC
VLC SC
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.
CDI
JOYSTICK
WPT
5.2.5
Figure 5-4. MAIN INPUTS 2 Page
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.
Figure 5-5. INSTRUMENT PANEL
SELF-TEST Page
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Page 5-5
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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.
Figure 5-6. MAIN LIGHTING Page
SOURCE
Selection
Description
PHOTO
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.
14V DC
28V DC
5V DC
5V AC
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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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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)
Figure 5-7. MAIN LIGHTING Page
These fields are equivalent to the SLOPE/OFFSET fields
(Display Lighting from Lighting Bus)
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 5-8.
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 510) if the encoding altimeter input is used. Verify that the
DECODED ALTITUDE field indicates the correct
altitude.
EXTERNAL SWITCH STATE
Figure 5-10.
MAIN DISCRETE INPUTS Page
Selection
Verify That:
RMT CDI
RMT OBS
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.
400 SERIES INSTALLATION MANUAL
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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.
Figure 5-11.
MAIN DISCRETE OUTPUTS Page
DISCRETE TOGGLE
Selection
Verify That:
APR
GPS
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).
INTEG
MSG
OBS
TERM
VLOC
WPT
ILS/GPS APR
5.2.10 MAIN CDI/OBS CONFIG Page
Select the MAIN CDI/OBS CONFIG Page (see Figure 512). 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:
Figure 5-12.
MAIN CDI/OBS CONFIG Page
CDI (LAT/VERT)
Selection
Verify That:
Max left/up
Full left/up
Center
Full right/down
Max right/down
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.
NAV FLAG (LAT/VERT)
Selection
Verify That:
Hidden
In view
The LAT/VERT flag is hidden.
The LAT/VERT flag is in view.
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400 SERIES INSTALLATION MANUAL
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TO-FROM
Selection
Verify That:
FROM
Hidden
TO
The FROM flag is in view.
The TO/FROM flag is hidden.
The TO flag is in view.
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.
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
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.
VLOC
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
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.
Track CDI
V-FLAG STATE
Selection
Description
Declutter
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.
Normal
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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
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.
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400 SERIES INSTALLATION MANUAL
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5.2.12 VOR DISCRETE INPUTS Page (GNS 430 Only)
Select the VOR DISCRETE INPUTS Page (see Figure 514). This page allows you to verify the operation of an
external VLOC transfer switch that may be present in the
installation.
Figure 5-14.
VOR DISCRETE INPUTS Page
Selection
Verify That:
REMOTE XFR
The box is filled in while a remote VLOC transfer switch is pressed.
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:
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
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.
FLAG (LAT/VERT)
Selection
Verify That:
Hide
View
The LAT/VERT flag is hidden.
The LAT/VERT flag is in view.
S-FLG (LAT/VERT)
Selection
Verify That:
Hide
View
The LAT/VERT superflag is hidden.
The LAT/VERT superflag is in view.
TO-FR
Selection
Verify That:
FROM
Hide
TO
The FROM flag is in view.
The TO/FROM flag is hidden.
The TO flag is in view.
400 SERIES INSTALLATION MANUAL
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Page 5-11
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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
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
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.
Figure 5-16. VOR/LOC/GS ARINC 429
CONFIG Page
SPEED
Selection
Description
Low
High
Standard low-speed ARINC 429 (nominally 12.5 kilobits per second)
High-speed ARINC 429 (nominally 100 kilobits per second)
SDI
Selection
Description
Common
VOR/ILS 1
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.
VOR/ILS 2
DME MODE
Selection
Description
Directed freq 1
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.
Directed freq 2
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400 SERIES INSTALLATION MANUAL
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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 517). 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.
Figure 5-17.
When a 400 Series unit is used with a WX-500
STORMSCOPE
CONFIG Page
Stormscope, the “Synchro” or “Serial” heading formats
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.
Figure 5-18.
STORMSCOPE TEST Page
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 WX500. 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.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Figure 5-19. STORMSCOPE
DOWNLOAD DATA Page
Page 5-13
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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)
Figure 5-20. TRAFFIC Page (Skywatch)
3. Current altitude (ALT)
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.
Figure 5-22. RYAN TCAD CONFIG
P
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 5-23. GAD 42 CONFIG Page
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400 SERIES INSTALLATION MANUAL
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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 5-15
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5.3
ADDITIONAL GROUND TESTS
5.3.1 Connector Engagement Test
1.
2.
3.
4.
Turn on the 400 Series unit, and turn on the avionics master switch (if applicable).
Place the 400 Series unit in the rack and engage the pawl mechanism.
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.
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
Half-scale left deviation, TO indication, flag pulled
Half-scale up deviation, flag pulled
135º
149.5º
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
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).
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400 SERIES INSTALLATION MANUAL
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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
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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
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Appendix A. CERTIFICATION DOCUMENTS
A.1
Continued Airworthiness
This section provides assistance to the installing agency in preparing Instructions for Continued
Airworthiness (ICA) in response to Bulletin Number HBAW 98-18, “Checklist for Instructions for
Continued Airworthiness for Major Alterations Approved Under the Field Approval Process”, effective
10/7/98.
Aviation Authority approved installers are hereby granted permission to reference appropriate service
instructions and excerpts from this Installation Manual to accomplish the Instructions for Continued
Airworthiness. This permission does not construe suitability of the documents. It is the applicant’s
responsibility to determine the suitability of the documents for the ICA.
Following is a suggested ICA for a GARMIN 400 Series unit installation. Some of the checklist items do
not apply, in which case they should be marked “N/A” (Not Applicable). In this sample, square braces are
used to indicate instances where explicit words should be substituted (e.g., replace “[400 Series unit]” with
“GNS 430”).
Instructions for Continued Airworthiness, GARMIN [400 Series unit]
1.
Introduction
[Aircraft that has been altered: Registration (N-) number, Make, Model and Serial Number]
Content, Scope,
Purpose and Arrangement:
This document identifies the Instructions for Continued Airworthiness
for the modification of the above aircraft by installation of a GARMIN
[400 Series unit].
Applicability:
Applies to aircraft altered by installation of the GARMIN [400 Series
unit].
Definitions and Abbreviations: None, N/A.
Precautions:
None, N/A.
Units of Measurement:
None, N/A.
Referenced Publications:
GARMIN 400 Series Installation Manual, P/N 190-00140-02
GARMIN 400 Series Maintenance Manual, P/N 190-00140-05
GARMIN STC # [applicable STC number for the specific model
installed, refer to Appendix B of this manual].
GARMIN Sample Flight Manual Supplement, P/N [part number of the
applicable SAFMS, refer to section 3.1 of this manual].
GARMIN [400 Series unit] Pilot’s Guide, P/N [part number of the
applicable Pilot’s Guide].
Distribution:
This document should be a permanent aircraft record.
2.
Description of the Alteration
Installation of the GARMIN [400 Series unit], with interface to external altitude encoder and CDI
[include other equipment/systems as appropriate]. Refer to section 1.2, and sections 4.x.1 of this
manual for interconnect information. Antenna installation, removal and replacement should be in
accordance with applicable provisions of AC43.13-1B and 43.13-2A.
3.
Control, Operation Information
Refer to the [400 Series unit] Pilot’s Guide.
4.
Servicing Information
N/A
5.
Maintenance Instructions
Maintenance of the [400 Series unit] is ‘on condition’ only. Periodic maintenance is not required.
Refer to the 400 Series Maintenance Manual.
400 SERIES INSTALLATION MANUAL
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6.
Troubleshooting Information
Refer to the 400 Series Maintenance Manual.
7.
Removal and Replacement Information
Refer to section 3.8 of this manual. If the unit is removed and reinstalled, a functional check of the
equipment should be conducted in accordance with section 5.3 of this manual.
8.
Diagrams
Refer to sections 3 and 4 of this manual.
9.
Special Inspection Requirements
N/A
10. Application of Protective Treatments
N/A
11. Data: Relative to Structural Fasteners
Antenna installation, removal and replacement should be in accordance with applicable provisions of
AC43.13-1A and 43.13-2A. Also, refer to section 3.7 of this manual.
12. Special Tools
N/A
13. This Section is for Commuter Category Aircraft Only
A. Electrical loads: Refer to section 1.3.2 of this manual.
B. Methods of balancing flight controls: N/A.
C. Identification of primary and secondary structures: N/A.
D. Special repair methods applicable to the airplane: Antenna installation, removal, and replacement
should be in accordance with applicable provisions of AC43.13-1B and 43.13-2A.
14. Overhaul Period
No additional overhaul time limitations.
15. Airworthiness Limitation Section
Refer to the [400 Series unit] Sample Flight Manual Supplement.
16. Revision
To revise this ICA, a letter must be submitted to the local FSDO with a copy of the revised FAA Form
337, and revised ICA. The FAA inspector accepts the change by signing Block 3 and including the
following statement:
“The attached revised/new Instructions for Continued Airworthiness (date ______) for the above
aircraft or component major alteration have been accepted by the FAA, superseding the Instructions
for Continued Airworthiness (date ______).”
17. Assistance
Flight Standards Inspectors have the resources to respond to questions regarding the ICA.
18. Implementation and Record Keeping
For major alterations performed in accordance with FAA field approval policy, the owner/operator
operating under Part 91 is responsible for ensuring that the ICA is made part of the applicable section
91.409 inspection program for their aircraft. This is accomplished when a maintenance entry is made
in the aircraft’s maintenance record in accordance with section 43.9. This entry records the major
alteration and identifies the original ICA location (e.g., Block 8 of FAA Form 337, dated ______)
along with a statement that the ICA is now part of the aircraft’s inspection/maintenance requirements.
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
A.2
Environmental Qualification Form—GNS 430
NOMENCLATURE:
GNS 430 Airborne GPS/VOR/ILS/COM System
TYPE/MODEL/PART NO.:
TSO/JTSO COMPLIANCE:
010-00139-(), which includes 011-00280-00
TSO-C129a Class A (1) (GPS)
TSO-C37d Class 4 & 6, JTSO-2C37e (COM TX, GNS 430)
TSO-C37d Class 3 & 5, JTSO-2C37e (COM TX, GNS 430A)
TSO-C38d Class C & E, JTSO-2C38e (COM RECEIVER)
TSO-C40c, JTSO-2C40c
(VOR RECEIVER)
TSO-C36e, JTSO-C36e
(LOCALIZER RECEIVER)
TSO-C34e, JTSO-C34e
(GLIDESLOPE RCVR.)
MANUFACTURER’S SPECIFICATION AND/OR OTHER
APPLICABLE SPECIFICATION: 004-00044-00
MANUFACTURER:
GARMIN International, Inc.
ADDRESS:
1200 E. 151st Street, Olathe, Kansas 66062
NOTE: The following information provides examples only. It is not intended to be a comprehensive
listing of all test conditions.
Conditions
Section
Description of Conducted Tests
Temperature and Altitude
4.0
Equipment tested to Categories A1 & D1
Low Temperature
4.5.1
High Temperature
4.5.2. & 4.5.3
In-flight Loss of Cooling
4.5.4
Equipment tested to Category Y
Altitude
4.6.1
Decompression
4.6.2
Overpressure
4.6.3
Temperature Variation
5.0
Equipment tested to Category C
Humidity
6.0
Equipment tested to Category A
Shock
7.0
Operational
7.2
Equipment tested per DO-160C, Par. 7.2.1
Crash Safety
7.3
Equipment tested per DO-160C, Par. 7.3.1 and 7.3.2
Vibration
8.0
Explosion
9.0
Equipment tested without shock mounts
to Categories B, M & N
Equipment identified as Category X, no test required
Waterproofness
10.0
Equipment identified as Category X, no test required
Fluids Susceptibility
11.0
Equipment identified as Category X, no test required
Sand and Dust
12.0
Equipment identified as Category X, no test required
Fungus
13.0
Equipment identified as Category X, no test required
Salt Spray
14.0
Equipment identified as Category X, no test required
Magnetic Effect
15.0
Equipment tested is Class Z
Power Input
16.0
Equipment tested to Category B
Voltage Spike
17.0
Equipment tested to Category A
Audio Frequency Susceptibility
18.0
Equipment tested to Category B
Induced Signal Susceptibility
19.0
Equipment tested to Category A
Radio Frequency Susceptibility
20.0
Equipment tested to Category T
Radio Frequency Emission
21.0
Equipment tested to Category Z
Lightning Induced Transient Susc.
22.0
Lightning Direct Effects
23.0
Equipment tested to Category ZZZZ per DO-160D.
See report 005-00096-72 for details
Equipment identified as Category X, no test required
Icing
24.0
Equipment identified as Category X, no test required
400 SERIES INSTALLATION MANUAL
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A.3
Environmental Qualification Form—GNC 420
NOMENCLATURE:
GNC 420 Airborne GPS/COM System
TYPE/MODEL/PART NO.:
TSO/JTSO COMPLIANCE:
010-00173-(), which includes 011-00506-00
TSO-C129a Class A (1) (GPS)
TSO-C37d Class 4 & 6, JTSO-2C37e (COM TX, GNC 420)
TSO-C37d Class 3 & 5, JTSO-2C37e (COM TX, GNC 420A)
TSO-C38d Class C & E, JTSO-2C38e (COM RECEIVER)
MANUFACTURER’S SPECIFICATION AND/OR OTHER
APPLICABLE SPECIFICATION: 004-00044-00
MANUFACTURER:
GARMIN International, Inc.
ADDRESS:
1200 E. 151st Street, Olathe, Kansas 66062
NOTE: The following information provides examples only. It is not intended to be a comprehensive
listing of all test conditions.
Conditions
Section
Description of Conducted Tests
Temperature and Altitude
4.0
Equipment tested to Categories A1 & D1
Low Temperature
4.5.1
High Temperature
4.5.2. & 4.5.3
In-flight Loss of Cooling
4.5.4
Equipment tested to Category Y
Altitude
4.6.1
Decompression
4.6.2
Overpressure
4.6.3
Temperature Variation
5.0
Equipment tested to Category C
Humidity
6.0
Equipment tested to Category A
Shock
7.0
Operational
7.2
Equipment tested per DO-160C, Par. 7.2.1
Crash Safety
7.3
Equipment tested per DO-160C, Par. 7.3.1 and 7.3.2
Vibration
8.0
Explosion
9.0
Equipment tested without shock mounts
to Categories B, M & N
Equipment identified as Category X, no test required
Waterproofness
10.0
Equipment identified as Category X, no test required
Fluids Susceptibility
11.0
Equipment identified as Category X, no test required
Sand and Dust
12.0
Equipment identified as Category X, no test required
Fungus
13.0
Equipment identified as Category X, no test required
Salt Spray
14.0
Equipment identified as Category X, no test required
Magnetic Effect
15.0
Equipment tested is Class Z
Power Input
16.0
Equipment tested to Category B
Voltage Spike
17.0
Equipment tested to Category A
Audio Frequency Susceptibility
18.0
Equipment tested to Category B
Induced Signal Susceptibility
19.0
Equipment tested to Category A
Radio Frequency Susceptibility
20.0
Equipment tested to Category T
Radio Frequency Emission
21.0
Equipment tested to Category Z
Lightning Induced Transient Susc.
22.0
Lightning Direct Effects
23.0
Equipment tested to Category ZZZZ per DO-160D.
See report 005-00096-72 for details
Equipment identified as Category X, no test required
Icing
24.0
Equipment identified as Category X, no test required
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
A.4
Environmental Qualification Form—GPS 400
NOMENCLATURE:
GPS 400 Airborne GPS System
TYPE/MODEL/PART NO.:
010-00171-(), which includes 011-00504-00
TSO/JTSO COMPLIANCE:
TSO-C129a Class A (1) (GPS)
MANUFACTURER’S SPECIFICATION AND/OR OTHER
APPLICABLE SPECIFICATION: 004-00044-00
MANUFACTURER:
GARMIN International, Inc.
ADDRESS:
1200 E. 151st Street, Olathe, Kansas 66062
NOTE: The following information provides examples only. It is not intended to be a comprehensive
listing of all test conditions.
Conditions
Section
Description of Conducted Tests
Temperature and Altitude
4.0
Equipment tested to Categories A1 & D1
Low Temperature
4.5.1
High Temperature
4.5.2. & 4.5.3
In-flight Loss of Cooling
4.5.4
Equipment tested to Category Y
Altitude
4.6.1
Decompression
4.6.2
Overpressure
4.6.3
Temperature Variation
5.0
Equipment tested to Category C
Humidity
6.0
Equipment tested to Category A
Shock
7.0
Operational
7.2
Equipment tested per DO-160C, Par. 7.2.1
Crash Safety
7.3
Equipment tested per DO-160C, Par. 7.3.1 and 7.3.2
Vibration
8.0
Explosion
9.0
Equipment tested without shock mounts
to Categories B, M & N
Equipment identified as Category X, no test required
Equipment identified as Category X, no test required
Waterproofness
10.0
Fluids Susceptibility
11.0
Equipment identified as Category X, no test required
Sand and Dust
12.0
Equipment identified as Category X, no test required
Fungus
13.0
Equipment identified as Category X, no test required
Salt Spray
14.0
Equipment identified as Category X, no test required
Magnetic Effect
15.0
Equipment tested is Class Z
Power Input
16.0
Equipment tested to Category B
Voltage Spike
17.0
Equipment tested to Category A
Audio Frequency Susceptibility
18.0
Equipment tested to Category B
Induced Signal Susceptibility
19.0
Equipment tested to Category A
Radio Frequency Susceptibility
20.0
Equipment tested to Category T
Radio Frequency Emission
21.0
Equipment tested to Category Z
Lightning Induced Transient Susc.
22.0
Lightning Direct Effects
23.0
Equipment tested to Category ZZZZ per DO-160D.
See report 005-00096-72 for details
Equipment identified as Category X, no test required
Icing
24.0
Equipment identified as Category X, no test required
400 SERIES INSTALLATION MANUAL
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A.5
Environmental Qualification Form—GA 56
NOMENCLATURE:
GA 56, GPS Aviation Antenna
TYPE/MODEL/PART NO.:
011-00134-00 (Stud Mount)
011-00147-00 (Flange Mount)
TSO COMPLIANCE:
C129 Class A (1)
MANUFACTURER’S SPECIFICATION AND/OR OTHER
APPLICABLE SPECIFICATION: 004-00015-00
MANUFACTURER:
GARMIN International, Inc.
ADDRESS:
1200 E. 151st Street, Olathe, Kansas 66062
NOTE: The following information provides examples only. It is not intended to be a comprehensive
listing of all test conditions.
Conditions
Temperature and Altitude
Low Temperature
High Temperature
In-flight Loss of Cooling
Section
4.0
4.5.1
4.5.2. & 4.5.3
4.5.4
Altitude
4.6.1
Decompression
4.6.2
Description of Conducted Tests
Equipment tested to Category F2
Cooling air not required
Not tested
Overpressure
4.6.3
Not tested
Temperature Variation
5.0
Equipment tested to Category A
Humidity
6.0
Equipment tested to Category C
Shock
7.0
Equipment tested per DO-160C, Par. 7.2.1
Operational
7.2
Crash Safety
7.3
Not Applicable
Vibration
8.0
Explosion
9.0
Equipment tested without shock mounts
to Categories C, L, M & Y
Equipment identified as Category X, no test required
Waterproofness
10.0
Equipment tested to Category S
Fluids Susceptibility
11.0
Sand and Dust
12.0
Equipment tested to Category F
with Ethylene Glycol De-Icing Fluid
Equipment identified as Category X, no test required
Fungus
13.0
Equipment identified as Category X, no test required
Salt Spray
14.0
Equipment identified as Category X, no test required
Magnetic Effect
15.0
Equipment identified as Category X, no test required
Power Input
16.0
Equipment identified as Category X, no test required
Voltage Spike
17.0
Equipment identified as Category X, no test required
Audio Frequency Susceptibility
18.0
Equipment identified as Category X, no test required
Induced Signal Susceptibility
19.0
Equipment tested to Category A
Radio Frequency Susceptibility
20.0
Equipment tested to Category T
Radio Frequency Emission
21.0
Equipment tested to Category Z
Lightning Induced Transient Susc.
22.0
Equipment identified as Category XXXX, no test required
Lightning Direct Effects
23.0
Equipment tested to Category 2A
Icing
24.0
Equipment tested to Category C
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Appendix B. STC Permission
Consistent with N8110.69 or Order 8110.4, Aviation Authority approved installers are hereby granted
permission to use STC’s #SA00705WI (GNS 430), #SA00801WI (GNC 420), and #SA00800WI
(GPS 400) data to modify aircraft.
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P/N 190-00140-02
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P/N 190-00140-02
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P/N 190-00140-02
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Appendix C. 400 Series RS-232 Aviation Data Format
C.1
ELECTRICAL INTERFACE
The output signals shall be compatible with RS-232C. Data shall be generated at 9600 baud with a word
length of 8 bits, one stop bit, and no parity.
C.2
GENERAL OUTPUT FORMAT
The 400 Series RS-232 data shall have the following general format:
STX
- ASCII start-of-text character (02 hex)
C.3
t1s
- Type 1 output sentences (see following paragraphs for description)
t2s
- One or more type 2 output sentences (see following paragraphs for description)
ETX
- ASCII end-of-text character (03 hex)
OUTPUT SENTENCE TYPE 1
The Type 1 output sentences shall have the following general format:
id
- item designator (single ASCII alphabetic character)
dddd
- item data (1 to 10 printable ASCII characters)
CR
- ASCII carriage return character (0D hex)
LF
- ASCII line feed character (0A hex)*
Each Type 1 sentence shall be output by the 400 Series unit approximately once every second.
The track, desired track, and bearing to waypoint angles, and the magnetic variation are output according
to the current mode of the 400 Series unit (automatic magnetic heading, magnetic variation computed at
last known position; true heading, magnetic variation of E00.0°; or user-defined magnetic heading,
magnetic variation as entered by user).
400 SERIES INSTALLATION MANUAL
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The following table describes the Type 1 output sentence item designator (id) and item data (dddd) fields.
If data for these sentences is invalid or unavailable, dashes ("-") are used to fill in all non-blank character
positions.
Ident (1 byte)
Data (10 bytes)
1 2 3 4 5 6 7 8 9 0
Description
z
a a a a a
Current GPS altitude in feet *
A
s
d d
m m h h
Current latitude, where:
s - N (north) or S (south)
dd - degrees
mm - minutes
hh - hundredths of minutes
B
s
d d d
m m h h
Current longitude, where:
s - E (east) or W (west)
ddd
- degrees
mm
- minutes
hh - hundredths of minutes
C
d d d
Track in whole degrees
D
s s s
Ground speed in knots
E
d d d d d
Distance to waypoint in tenths of nautical miles
G
s n n n n
Cross track error, where:
s - L (left) or R (right) of course
nnnn - error in hundredths of nautical miles
I
d d d d
Desired track in tenths of degrees
K
c c c c c
Destination waypoint identifier (will be blank filled on
right if less than 5 characters in identifier)
L
d d d d
Bearing to destination waypoint in tenths of degrees
Q
s d d d
Magnetic variation, where:
s - E (east) or W (west)
ddd
S
- - - - f
- tenths of degrees
Nav valid flag status, where:
f - N (nav flagged) or - (nav valid)
T
l (lower case
Lima)
- - - - - - - - -
Warnings status, only data transmitted are dashes (-).
Used to indicate end of Type 1 sentences.
d d d d d d
Distance to destination waypoint in tenths of nautical
miles.
* The line feed character is not output if the RS-232 port is configured as “Avtn no alt”.
* The altitude is not output if the RS-232 port is configured as “Avtn no alt”.
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
C.4
OUTPUT SENTENCE TYPE 2
The 400 Series Type 2 output sentence shall have the following general format:
id
- item designator (3 ASCII characters)
seq
- sequence number (1 binary byte)
wpt
- waypoint identifier (5 ASCII characters)
lat
- waypoint latitude (3 binary bytes)
lon
- waypoint longitude (4 binary bytes)
mvar
- magnetic variation at waypoint (2 binary bytes)
CR
- ASCII carriage return character (0D hex)
LF
- ASCII line feed character (0A hex)
Each waypoint in the route being navigated by the 400 Series unit shall have a Type 2 sentence output by
the 400 Series unit approximately once every second.
If no route is being navigated by the 400 Series unit (i.e., the active route is empty), the following Type 2
sentence is output approximately once every second:
id
- item designator (3 ASCII characters; route sequence number is "01")
seq
- sequence number (1 binary byte; last waypoint flag is set; route sequence number is 1)
CR
- ASCII carriage return character (0D hex)
LF
- ASCII line feed character (0A hex)
400 SERIES INSTALLATION MANUAL
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The following table describes the Type 2 output sentence item designator (id), sequence number (seq),
waypoint identifier (wpt), waypoint latitude (lat), waypoint longitude (lon), and magnetic variation at
waypoint (mvar) fields.
Field
Byte
id
1
Format
7 6 5 4 3 2 1 0
ASCII character 'w' (77 hex)
2-3
seq
1
Description
Two ASCII numeric characters representing route
sequence number of waypoint (01 to 31)
x l a n n n n n
x
- undefined
l
- 1 if last waypoint in route
a
- 1 if active to waypoint
nnnnn - route sequence number of waypoint
(unsigned binary)
wpt
1-5
lat
1
2
Destination waypoint identifier (will be blank filled on
right if less than 5 characters in identifier)
s d d d d d d d
x x m m m m m m
s
- 0 (north) or 1 (south)
ddddddd
- latitude degrees (unsigned binary)
xx
- undefined
mmmmmm - latitude minutes (unsigned binary)
3
lon
1
x h h h h h h h
s x x x x x x x
x
- undefined
hhhhhhh
- hundredths of latitude minutes
(unsigned binary)
s
- 0 (north) or 1 (south)
xxxxxxx
- undefined
d d d d d d d d
dddddddd - longitude degrees (unsigned binary)
x x m m m m m m
xx
- undefined
mmmmmm - latitude minutes (unsigned binary)
x h h h h h h h
mvar
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1-2
x
- undefined
hhhhhhh
- hundredths of latitude minutes
(unsigned binary)
Two's complement binary in 16ths of degrees.
Easterly variation is positive. MSB output first.
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Appendix D. 400 Series RS-232 Fuel/Air Data Input Format
D.1
ELECTRICAL INTERFACE
The input signals shall be compatible with RS-232C. Data shall be input at 9600 baud with a word length
of 8 bits, one stop bit, and no parity. One message is received per second.
D.2
SHADIN ALTITUDE SENTENCE
The GARMIN 400 Series units shall be capable of receiving the following 17-byte message from Shadin
Altitude Encoders, Altitude Serializers, and Altitude Converters:
RMS<sp><+/->12345T<+/->12ul<CR>
Where:
RMS
ASCII characters
<sp>
space (0x20)
<+/->
sign indicator (0x2b["+"] or 0x2d["-"])
12345
altitude in feet
T
ASCII character
<+/->
sign indicator
12
sensor temperature
ul
checksum of bytes 1 through 14 in hex ASCII (i.e., "FA")
<CR>
carriage return (0x0d)
Note: Checksum is calculated by adding each byte in the message (1 through 14).
D.3
ICARUS ALTITUDE SENTENCE
The GARMIN 400 Series units shall be capable of receiving the following 10-byte message from the
Icarus Altitude Serializer:
ALT<sp>12345<CR>
Where:
ALT ASCII characters
<sp> space (20 hex)
12345 altitude in feet
<CR> CARRIAGE RETURN (0D HEX)
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D.4
SHADIN FUEL FLOW SENTENCE
The GARMIN 400 Series units shall be capable of receiving the following 55-byte message from the
Shadin Fuel Flow Indicator:
<STX>K0543.2<sp>0100.0<sp>0040.0<sp>0060.0<sp>0123.4<sp>0045.4<sp>0078.0<sp>123<ETX>
Where:
<STX> start-transmit character (0x02)
K
units designation (i.e., Gallons, Liters, Kilograms, B[pounds])
0543.2 total fuel remaining (i.e., ASCII-coded decimal format: 0x30, 0x35, 0x34, 0x33, 0x2e, 0x32)
<sp>
space (0x20)
0100.0 fuel flow rate, total (formatted as for total fuel remaining)
0040.0 fuel flow rate, engine one (or asterisks["∗∗∗∗∗∗"], in the case of single engine aircraft)
0060.0 fuel flow rate, engine two (asterisks, in the case of single engine aircraft)
0123.4 fuel used, total
0045.4 fuel used, engine one (asterisks, in the case of single engine aircraft)
0078.0 fuel used, engine two (asterisks, in the case of single engine aircraft)
123
checksum (of bytes 2 through 51)
<ETX> end-transmit character (0x03)
Note: Checksum is calculated by adding each byte in the message (2 through 51), such that carries are
discarded to give a one byte result. The ASCII-coded decimal representation of that byte is given, ranging
from 0 (0x30, 0x30, 0x30) to 255 (0x32, 0x35, 0x35).
D.5
ARNAV / EI FUEL FLOW SENTENCE
The GARMIN GNC 400 shall be capable of receiving the following 13-byte message from the ARNAV or
Electronics International (“EI”) Fuel Flow Indicators:
<STX>G0245100550<ETX>
Where:
<STX> start-transmit character (0x02 hex)
G
units designation (i.e., Gallons, Imperial gallons, Liters, Kilograms, B[pounds])
0245
total fuel remaining in reverse order (i.e., ASCII-coded decimal format: 0x30, 0x32, 0x34,
0x35)
1
fuel remaining checksum (modulo 10 sum of four "total fuel remaining" digits)
0055
total fuel flow rate in reverse order
0
fuel flow checksum
<ETX> end-transmit character (0x03)
NOTE: Fuel remaining and fuel flow are [∗ 10] when units designation is gallons or imperial gallons. For
example, 0245 gallons indicates 542 gallons; 0245 liters indicates 5420 liters.
Checksum is the modulo 10 sum of the four fuel flow decimal digits, converted to an ASCII
numerical character (e.g., checksum for "5678" would be ASCII "6").
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
D.6
SHADIN FUEL/AIRDATA COMPUTER SENTENCE
The GARMIN 400 Series units shall be capable of receiving the following message strings from the Shadin
Fuel/Airdata or Airdata Computer:
<STX>
ZA012<CR><LF>
"ZA" (ASCII characters); "012" represents indicated Air Speed (knots)
ZB345<CR><LF>
"ZB" (ASCII characters); "345" represents true Air Speed (knots)
ZC678<CR><LF>
"ZC" (ASCII characters); "678" represents Mach Speed (thousandths)
ZD<+/->9012<CR><LF>
"ZD" (ASCII characters); sign; "9012" represents pressure altitude (tens of feet)
ZE<+/->3456<CR><LF>
"ZE" (ASCII characters); sign; "3456" represents density altitude (tens of feet)
ZF<+/->78<CR><LF>
"ZF" (ASCII characters); sign; "78" represents outside air temperature (Celsius)
ZG<+/->90<CR><LF>
"ZG" (ASCII characters); sign; "90" represents true air temperature (Celsius)
ZH123<CR><LF>
"ZH" (ASCII characters); "123" represents wind direction (degrees from north)
ZI456<CR><LF>
"ZI" (ASCII characters); "456" represents wind speed (knots)
ZJ<+/->78<CR><LF>
"ZJ" (ASCII characters); sign; "78" represents rate of turn (degrees per second)
ZK<+/->901<CR><LF>
"ZK" (ASCII characters); sign; "901" represents vertical speed (tens of ft/minute)
ZL234<CR><LF>
"ZL" (ASCII characters); "234" represents heading (degrees from north)
ZM5678<CR><LF>*
"ZM" (ASCII characters); "5678" represents fuel flow, right (tenths gallons/hour)
ZN90123<CR><LF>*
"ZN" (ASCII characters); "90123" represents fuel used, right (tenths gallons)
ZO4567<CR><LF>*
"ZO" (ASCII characters); "4567" represents fuel flow, left (tenths gallons/hour)
ZP89012<CR><LF>*
"ZP" (ASCII characters); "89012" represents fuel used, left (tenths gallons)
ZQ345<CR><LF>
"ZQ" (ASCII characters); "345" represents error log/reason indicator
ZR678<CR><LF>
"ZR" (ASCII characters); "678" represents checksum
<ETX>
Where:
<STX> start-transmit character (0x02)
<CR>
carriage-return character (0x0d)
<LF>
line-feed character (0x0a)
<+/->
sign indicator (0x2b["+"] or 0x2d["-"])
<ETX> end-transmit character (0x03)
*Not available from Airdata Computer
Note: Checksum is calculated by adding each byte in the message (including all characters from <STX>
up to and including the error log/reason indicator), such that carries are discarded to give a one byte result.
The ASCII-coded decimal representation of that byte is given, ranging from 0 (0x30, 0x30, 0x30) to 255
(0x32, 0x35, 0x35).
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
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400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Appendix E. 400 Series LRU Interface Overview
The following tables provide a quick overview of some of the equipment that can be interfaced with the
GARMIN 400 Series units. This is not a complete listing however; it only represents those units listed in
Section 4 of this manual. When installing equipment on the aircraft always refer to the manufacturers’
documentation for complete pinout and interconnect information
E.1
GARMIN 420/430 LRU INTERFACE
Function
Audio Panel
E.2
Bendix/King
KMA 24
KMA 24H
-70/-71
Garmin
GMA 340
PS Engineering
PMA 6000
GARMIN 400/420/430 LRU INTERFACE
Function
Air Data Computer
Bendix/King
KDC 281
KDC 481
B&D
2600
2601
2800
90004-003
Function
Shadin
Icarus
Instruments
ARNAV
Altitude Serializer or
Fuel/Air Data
8800T
9000T
9200T
3000
FC-10
FT-10
Function
Altitude Serializer or
Fuel/Air Data
Function
Autopilot
Flight Control
Function
Encoding Altimeter
Or Blind Encoder
Shadin
Digiflo-L
91053XP
91053XT-D
Bendix/King
KFC 150
KFC 200
KFC 400
KCP 420
Shadin
Digidata
91802-()
JP
Instrument
s
EDM-700
Shadin
F/ADC-200
F/ADC-2000
Shadin Miniflo-L
91204XT(38)D
Electronics
International
FP-5L
S-Tec
System 55
Bendix/King
KEA-130A
KEA-346
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02
Terra
AT-3000
Shadin
Miniflo-L
Digiflo-L
Digidata
Page E-1
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Function
EFIS
Displays
Bendix/King
EFIS 40/50
SG 465
Function
EHSI
Sandel
SN 3308
Function
IRU/AHRS
Function
Nav
Indicator
Bendix/King
KI 202A
KI 203
KI 204
KI 206
KI 208/A
KI 209/A
KI 525A
KPI 522/B
KPI 553/A/B
Function
Weather, Traffic
and Terrain
Page E-2
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Bendix/King
KAU 461
Collins
EFIS-84
DPU-84
Collins
AHC 85E
Garmin
GI 102/A
GI 106/A
Bendix/King
KTA 870
KMH 880
Honeywell
Laseref
HG 1075 AB
HG 1095 AB
Century
NSD 360A
NSD 1000
Litef
LTR 81
Collins
331A-6P
331A-6G
BF Goodrich
SKY497 (Skywatch)
SKY899 (Skywatch HP)
WX-500
Litton
LTN 90-100
LTN-91
LTN-92
Sperry
RD 550A
RD 650
S-Tec
ST 180
Ryan
9900B/BX
400 SERIES INSTALLATION MANUAL
P/N 190-00140-02