Garmin GPS Receiver 190 00004 00 User Manual

SM  
COMMUNICATION & NAVIGATION  
GPS100  
AVIATION KIT  
INSTALLATION MANUAL  
GARMIN INTERNATIONAL, INC.  
9875 WIDMER ROAD  
PART NUMBER: 190-00004-00  
REVISION G, 15 October 1992  
LENEXA, KANSAS 66215  
Av. Kit Install. Manual  
190-00004-00 Rev. G  
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GPS 100 AVIATION KIT INSTALLATION MANUAL  
TABLE OF CONTENTS  
SECTION 1  
GENERAL DESCRIPTION  
1.1  
INTRODUCTION  
1.2  
TECHNICAL CHARACTERISTICS  
PHYSICAL CHARACTERISTICS  
OPERATIONAL CHARACTERISTICS  
INTERFACES  
1.2.1  
1.2.2  
1.2.3  
SECTION 2  
INSTALLATION CONSIDERATIONS  
2.1  
ANTENNA CONSIDERATIONS  
SATELLITE VISIBILITY  
NOISE SOURCES  
ELECTRICAL BONDING  
ANTENNA LIMITATIONS  
RACK CONSIDERATIONS  
ACCESSIBILITY  
2.1.1  
2.1.2  
2.1.3  
2.1.4  
2.2  
2.2.1  
2.3  
2.4  
CABLING AND WIRING  
ANNUNCIATORS  
SECTION 3  
INSTALLATION PROCEDURE  
3.1  
3.2  
3.3  
3.4  
3.5  
3.6  
3.7  
INSTALLATION KIT CONTENTS  
ANTENNA INSTALLATION  
CABLE INSTALLATION  
RACK INSTALLATION  
AVIATION INTERFACE SET-UP  
GPS 100 INSTALLATION  
PLACARD  
SECTION 4  
CHECKOUT PROCEDURE  
APPENDIX A  
INSTALLATION DETAILS FOR BEECH B60  
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LIST OF ILLUSTRATIONS  
FIGURE  
1-1  
1-2  
2-1  
2-2  
3-1  
3-1A  
3-2  
3-3  
3-4  
AVIATION RACK PINOUT DEFINITION  
INTERCONNECT SCHEMATIC  
ANTENNA INSTALLATION CONSIDERATIONS  
GPS INSTALLATION CONSIDERATIONS  
BLADE ANTENNA INSTALLATION  
LOW PROFILE ANTENNA INSTALLATION  
COAX CABLE INSTALLATION FIGURE  
AVIATION RACK DIMENSIONS  
AVIATION RACK INSTALLATION  
A-1  
A-2  
A-3  
A-4  
A-5  
BLOCK DIAGRAM  
FUSELAGE STATIONS  
PANEL LAYOUT  
WIRING DIAGRAM  
BREAKER LOCATIONS  
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SECTION 1 GENERAL DESCRIPTION  
1.1 INTRODUCTION  
This manual describes the physical, mechanical, and electrical characteristics and  
the installation requirements for the GPS 100 Aviation Kit.  
After installation of the GPS 100 system, FAA Form 337 must be completed by an  
appropriately certificated agency to return the aircraft to service.  
NOTE: TheGPS100musthavesoftwareversion2.09orlatertointerfaceproperlywith  
the aviation rack. If the GPS 100 being installed has an earlier software version,  
contact your nearest GARMIN service center to obtain a software update.  
1.2 TECHNICAL CHARACTERISTICS  
TheGPS100offerstheversatilityoffixedinstallationinapanelmountedaviationrack  
as well as complete portability.  
1.2.1 Physical Characteristics  
Width:  
Height:  
Depth:  
GPS 100 Weight:  
Blade Antenna Weight:  
Low Profile Antenna Weight:  
Aviation Rack Weight:  
Max Air Speed:  
6.25 Inches  
2 inches  
3.95 inches  
28 oz.  
8 oz.  
4 oz.  
11 oz.  
Subsonic  
(Structural rating for antenna)  
1.2.2 Operational Characteristics  
Temperature Range:  
Humidity:  
Altitude Range:  
Power Input:  
-15 oC to +70oC  
95% non-condensing  
-1,500 to 50,000 ft.  
11 to 33 VDC at 500mA MAX  
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1.2.3 Interfaces  
The aviation rack contains an electronic module which provides interfaces to various  
general aviation instruments. Figure 1-1 defines the function of each pin on the 15  
pin DSUB connector located at the back of the rack. Figure 1-2 depicts the  
interconnects between the rack and other instruments. The following interfaces are  
provided.  
CDI:  
(Pins 1 and 4)  
Capable of driving up to three 1000 ohm parallel  
loads, +150 millivolts full scale deflection with a  
maximum output of +300 millivolts.  
To/From:  
(Pins 2 and 5)  
Capable of driving up to three 200 ohm parallel  
loads, +82 millivolts full scale deflection.  
Nav Flag:  
(Pins 3 and 6)  
Capable of driving up to three 1000 ohm parallel  
loads, 375 millivolts for flag out-of-view, and  
+40 millivolts for flag in-view.  
OBI data:  
(Pins 7, 8, and 12)  
Output providing bearing to waypoint data for a  
Bendix/King RMI (KI 229 or equivalent).  
Message annunciators: Output capable of driving negative or positive logic  
(Pins 9 and 11):  
annunciators.  
Message audio:  
(Pin 10)  
Output capable of producing 10 milliwatts into 500  
ohms at a frequency of 2 KHz.  
RS232 data:  
(Pin 13)  
Output capable of driving ARGUS3000/5000/7000  
and STORMSCOPE SERIES II with NAVAID moving  
map displays and Shadin fuel management system.  
Conforms to the EIA specification RS-232C.  
SECTION 2 INSTALLATION CONSIDERATIONS  
Careful planning and consideration of the suggestions in this section are required to  
achieve the desired performance and reliability from the GPS 100.  
2.1 ANTENNA CONSIDERATIONS  
2.1.1  
SATELLITE VISIBILITY  
The GPS 100 Blade or Low Profile Antenna must be mounted on top of the aircraft in  
the upright position. 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  
blade antenna installation. Recommended installation locations for the Low Profile  
Antenna are the same.  
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2.1.2  
NOISE SOURCES  
The antenna should be located at least 3 ft from transmitting antennas such as VHF  
Comm, HF transmitter, DME, Transponder, and Radar. Cabling for the GPS 100  
shouldnotberoutednearcomponentsorcablingwhicharesourcesofelectricalnoise.  
2.1.3  
ELECTRICAL BONDING  
No special precautions need to be taken to provide a bonding path between the  
antenna and the aircraft structure.  
2.1.4  
ANTENNA LIMITATIONS  
The GPS 100 Blade and Low Profile Antennas are recommended for installations  
where the airspeed of the aircraft will be subsonic. For aerodynamic considerations,  
the Low Profile Antenna is recommended for operation above 200 kts.  
2.2 RACK CONSIDERATIONS  
2.2.1  
ACCESSIBILITY  
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. 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. Figure 2-2 illustrates a typical  
aviation rack installation.  
2.3 CABLING AND WIRING  
Use only the antenna cable supplied in the installation kit. Other cabling may lead  
to degraded performance. Check that there is ample space for the cabling and mating  
connectors. Avoid sharp bends in cabling and routing near aircraft control cables.  
2.4 ANNUNCIATORS  
If the installation includes any electrical interface with other flight instruments, an  
annunciator may be required. Refer to current FAA directives.  
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SECTION 3 INSTALLATION PROCEDURE  
3.1 INSTALLATION KIT CONTENTS  
Oneofthefollowingtwoinstallationkitsisrequiredforaircraftinstallation,depending  
on the type of antenna used.  
The GPS 100 Aviation Installation Kit (010-10002-00) consists of the following parts:  
P/N  
DESCRIPTION  
QTY  
1
011-00013-00  
011-00014-00  
115-00015-00  
117-00001-00  
161-00024-00  
190-00004-00  
211-20001-00  
253-00002-00  
320-00003-00  
330-00017-00  
330-00024-00  
BLADE ANTENNA SUBASSEMBLY  
RACK SUBASSEMBLY  
BACKING PLATE  
EJECTOR PIN  
PLACARD, INSTRUMENT PANEL  
INSTALLATION MANUAL (THIS MANUAL) 1  
#8-32 SS, PH, FLAT HEAD SCREW  
ANTENNA GASKET  
CABLE ASSY, COAX  
CONNECTOR, BNC, MALE, CLAMP  
CONNECTOR, 15 PIN DSUB, FEMALE  
1
1
4
1
4
1
1
1
1
The GPS 100 Low Profile Aviation Installation Kit (010-10008-00) consists of the  
following parts:  
P/N  
DESCRIPTION  
QTY  
011-00042-00  
011-00014-00  
115-00031-00  
117-00001-00  
161-00024-00  
190-00004-00  
210-10004-09  
253-00002-00  
320-00003-00  
330-00017-00  
330-00024-00  
LOW PROFILE ANTENNA SUBASSEMBLY 1  
RACK SUBASSEMBLY  
BACKING PLATE  
EJECTOR PIN  
1
1
4
1
PLACARD, INSTRUMENT PANEL  
INSTALLATION MANUAL (THIS MANUAL) 1  
NUT, SELF-LOCKING, #8-32  
ANTENNA GASKET  
CABLE ASSY, COAX  
CONNECTOR, BNC, MALE, CLAMP  
CONNECTOR, 15 PIN DSUB, FEMALE  
4
1
1
1
1
The following equipment is required for installation but is not included in the  
installation kit:  
#6-32 Flat Head Screw (4 ea.)  
#6-32 Self-locking Nut (4 ea.)  
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3.2 ANTENNA INSTALLATION  
TheBladeAntennaoutlineandfootprintdimensionsareshowninFigure3-1. TheLow  
Profile Antenna outline and footprint dimensions are shown in Figure 3-1A. Both  
antennas require the same Installation procedure.  
A. Using the backing plate as a template, mark the location of the mounting holes and  
the through hole for coax cable. Drill or punch the holes.  
B. The antenna installation must provide adequate support for the antenna consid-  
ering a maximum drag load of 14 lbs (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.  
C. 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.  
3.3 CABLE INSTALLATION  
A. Route the coax cable supplied to the rack location keeping in mind the recommen-  
dations of Section 2. Secure the cable in accordance with good aviation practice.  
B. Trim the supplied RG-59/U cable to the desired length and install the BNC  
connector (330-00017-00) per the cabling instructions on Figure 3-2.  
3.4 RACK INSTALLATION  
A. Figure 3-3 shows outline dimensions for the aviation rack. Install the rack in a  
rectangular 6.320" x 2.000" hole in the instrument panel. Exercise caution when  
installingtherackintotheinstrumentpanel. Therackisdesignedtofacilitateremoval  
oftheGPS100forportableuse. Deformationoftherackmaymakeitdifficulttoinstall  
and remove the GPS 100.  
B. Install the rack in the aircraft panel using four #6-32 countersunk screws and  
four self-locking nuts. The screws are inserted from the inside through the holes  
in the sides of the rack (see Figure 3-4).  
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3.5 AVIATION INTERFACE SET-UP  
Before installing the GPS 100 into the aviation rack, several operating parameters  
need to be set-up so that the GPS 100 can interface properly with the aviation rack  
and other avionics. Press the ON button. The Initialization page will appear. See  
Chapter 3 in the GPS 100 Owner’s Manual for information on initialization. Approve  
the initialization page.  
There are several set-up pages which can be viewed by pressing the SET key. Press  
the SET key until the CDI SETTINGS page is displayed. Move the cursor to highlight  
the setting for STEER TO. Press the clear key until “D-BAR” appears. Move the cursor  
to highlight the “OK” and press ENT. Press the SET key to continue through the set-  
up pages and set-up the following parameters:  
STEER TO> D-BAR  
OUTPUT> AVIATION  
Ensure that the following parameters are set-up properly for your application. The  
following are typical settings for an aviation environment. See Chapter 10 in the GPS  
100 Owner’s Manual for more information on customizing the GPS 100 settings:  
CDI SCALE>+ 5.00  
>AUTO MAG  
NAV> nm kt  
ALT> ft FPM  
DATUM> WGS 84 or as indicated on navigation charts for the area.  
3.6 GPS 100 INSTALLATION  
To install or remove the GPS 100 from the aviation rack, see the addendum to the GPS  
100 Owner’s Manual included in the installation kit. This addendum should be given  
to the end user.  
3.7 PLACARD  
Aftercompletingtheinstallation,aplacardstatingGPSlimitedtoVFRuseonlymust  
be installed on the panel in clear view of the pilot. The placard may be Garmin p/n  
161-00024-00 as supplied with the installation kit, or a suitable equivalent.  
SECTION 4 CHECKOUT PROCEDURE  
Inordertoverifytheinstallation,theaircraftmustbeoutsidethehangerandwellaway  
from any buildings or aircraft that might block satellite signals. To perform the  
checkoutprocedureitisnecessarytobefamiliarwithoperatingtheGPS100ortohave  
the GPS 100 Owner’s Manual available for reference.  
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With power applied to the aviation rack turn the GPS 100 on. The Self-Test Page will  
be displayed followed by the Initialization Page. The GPS 100 must be properly set-  
uppertheinstructionsinSection3.5beforeperformingthecheckoutprocedure. Prior  
to approving the Initialization page verify the following interfaces as appropriate:  
CDI  
Ensure the CDI is deflected half scale left (2.5 dots).  
Ensure the TO/FROM flag is in a TO condition.  
Ensure the NAV FLAG is out of view.  
TO/FROM  
NAV FLAG  
MESSAGE ANNUNCIATOR  
RMI  
Ensure the message annunciators are illuminated.  
Ensure the RMI indicates 315o.  
Approve the Initialization page, select the GPS Status page from Navigation Menu 1  
(see Chapter 9 for more information on the GPS Status page). The process of satellite  
acquisition is fully automatic and under normal circumstances will require 2-3  
minutestoobtainnavigationinformation(15minutesorlesswhensearchingthesky).  
If unable to acquire satellites, relocate the aircraft away from obstructions which  
might be shading reception. If the situation does not improve, check the antenna  
installation.  
AUDIO  
Select the Event Timer 1 page from Navigation Menu 2 (see Chapter 10 of the GPS 100  
Owner’s Manual for more information on event timers). Set the count down timer to  
go off in 1 minute. Prior to viewing the message indicating “TIMER 1 EXPIRED” (while  
the "M" character is flashing in the upper right hand corner of the display), ensure the  
audio interface is operating properly.  
ARGUS3000/5000/7000orSTORMSCOPESERIESIIwithNAVAIDorSHADINFUEL  
MANAGEMENT SYSTEM  
TM  
Once GPS position information is available, use the AutoStore function to store a  
waypoint at your current position (see Chapter 8 of the GPS 100 Owner’s Manual for  
TM  
informationontheAutoStore function). Afterstoringyourlocation,GOTOthestored  
waypoint (see Chapter 6 of the GPS 100 Owner’s Manual for information on the GOTO  
function). Ensure the ARGUS or STORMSCOPE or SHADIN fuel management system  
are receiving data from the GPS 100 and are functioning properly.  
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FIGURE 1-1 AV. RACK PINOUT DEFINITION  
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FIGURE 1-2 INTERCONNECT SCHEMATIC  
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Ante nna m a ske d b y ve rtic a l fin,  
T ta il, o r d o rsa l fin  
OK  
Ante nna m ust b e o n  
to p o f a irc ra ft.  
FIG 2-1  
ANTENNA INSTALLATION CONSIDERATIONS  
Maintain 6"(16 cm)  
compass safe distance  
Unit to be mounted in aircraft radio  
rack as high as possible. If the loca-  
tion chosen is very low, or to the left  
of the pilot, it should be evaluated  
for display visibility.  
FIG 2-2  
GPS INSTALLATION CONSIDERATIONS  
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FIGURE 3-1 BLADE ANTENNA INSTALLATION  
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FIGURE 3-1A LOW PROFILE ANTENNA INSTALLATION  
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FIGURE 3-2 COAX CABLE INSTALLATION  
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FIGURE 3-3 AVIATION RACK DIMENSIONS  
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FIGURE 3-4 AVIATION RACK INSTALLATION  
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APPENDIX A INSTALLATION DETAILS FOR BEECH B60  
1.0 INTRODUCTION:  
This appendix provides airframe specific information which is necessary to install the  
GARMINGPS100navigationsystemintheBeechDukeModelB60inaccordancewith  
STC (tbd). When so installed, the GPS 100 system is approved for use as a  
supplementary navigation system under Visual Flight Rules (VFR) only. A functional  
block diagram of the system is shown in Figure A-1.  
The information provided herein is to be considered supplemental to the information  
contained in the GARMIN GPS 100 Aviation Kit Installation Manual, P/N 190-00004-  
00. Within this appendix, the base document will be referred to as the "Installation  
Manual".  
2.0 INSTALLATION INSTRUCTIONS  
2.1 ANTENNA  
The GPS 100 antenna is to be installed on top of the cabin on the aircraft centerline  
atfuselagestation138.0. FigureA-2illustratestheproperantennapositioning. Refer  
to section 2.1 of the Installation Manual for general antenna mounting requirements.  
2.2 AVIATION RACK INSTALLATION  
The GPS 100 aviation rack is to be installed on the right side of the instrument panel  
radio rack as shown in figure A-3. The controls and display of the GPS 100 must be  
readily visible to the pilot when seated at the controls.  
To install the aviation rack, position it in the instrument panel in the desired position,  
assuringthatthefrontisnottwistedoutofsquare. Matchdrilltheflangesontheradio  
racktotheinstallationholesontheGPS100aviationrack. Using4each#6-32screws  
and self locking nuts, attach the aviation rack to the aircraft panel. For additional  
information, refer to the Installation Manual.  
2.3 WIRING  
FabricateanappropriatecabletoconnecttheGPS100aviationrackto28VDCpower,  
a message annunciator, a remote switch (for selecting between GPS and standard  
navigation equipment), a transfer switch with integral white, illuminated annuncia-  
tors with black markings (to control and indicate the status of the remote switch).  
Wiring connections are to be made in accordance with Figure A-4. Breaker locations  
are to be as shown in Figure A-5. Route and connect the wiring in accordance with  
Advisory Circular AC-43.13-2A. After the wiring installation is complete, carefully  
check the operation of all flight controls throughout their range to assure that no  
operational interference exists.  
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2.4 PLACARDS  
After completion of the GPS 100 system installation, affix a durable placard on the  
instrumentpanelinthelocationshowninFigureA-3whichstatesGPSlimitedtoVFR  
use only". GARMIN placard p/n 161-00024-00 or an appropriate equivalent should  
be used for this purpose.  
3.0 OPERATIONAL CHECKOUT  
When the installation is complete, conduct a post installation checkout as specified  
in section 4 of the Installation Manual, being sure to check the proper operation of all  
connected instruments.  
4.0 RETURN TO SERVICE  
After installation, a new weight and balance must be computed to show the GPS 100  
components. The aircraft should then be returned to service by completion of FAA  
form 337 by an appropriately certificated person.  
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FIG A-1  
FUNCTIONAL BLOCK DIAGRAM  
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FIG A-2  
FUSELAGE STATIONS AND WEIGHT AND BALANCE DATA  
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FIG A-3  
PANEL LAYOUT  
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FIG A-4  
WIRING DIAGRAM  
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FIG A-5  
BREAKER LOCATIONS  
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