Garmin 190-00004-00 GPS Receiver User Manual

SM
COMMUNICATION & NAVIGATION
GPS100
AVIATION KIT
INSTALLATION MANUAL
GARMIN INTERNATIONAL, INC.
9875 WIDMER ROAD
LENEXA, KANSAS 66215
PART NUMBER: 190-00004-00
REVISION G, 15 October 1992
Av. Kit Install. Manual
190-00004-00 Rev. G
Page 1
© Copyright 1992
Garmin International, Inc.
All Rights Reserved
This publication is the proprietary property of Garmin International Inc. It may not
be reproduced or transmitted in any form whether printed or electronic, without the
expressed written consent of Garmin International.
Garmin International, Inc.
9875 Widmer Road
Lenexa, KS 66215
U.S.A.
REVISION RECORD
Initial
Rev. 0, 1 Mar 1991
Initial release and STC approval
1224
Rev. 1, 1 May 1991
Minor Change. Added this revision record page.
Changed company name from PRONAV to GARMIN.
1254
Rev. B, 8 Aug 1991
Minor Change. Revised Photos to show GARMIN
company name. Changed Rev sequencing to use
alphabetic rev instead of numeric. Clarify antenna
sealing requirements in 3.2.C
1385
Rev. C, 18 Nov 1991 Minor Change. Replace photographs with drawings
for better reproducibility. Add page numbering. Add
compass safe distance to Fig. 2-2. Revise text.
1506
Rev. D, 26 Feb 1992 Minor Change. Change coax cable type.
1549
Rev. E, 30 Mar 1992 Add Low Profile Antenna and Appendix A.
1608
Rev. F, 4 May 1992
1839
Rev. G, 15 May 1992 Change company address and add eco #'s to record
page.
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Minor Change. Revise installation details in Appendix
A.
GPS 100 AVIATION KIT INSTALLATION MANUAL
TABLE OF CONTENTS
SECTION 1
GENERAL DESCRIPTION
1.1
1.2
1.2.1
1.2.2
1.2.3
INTRODUCTION
TECHNICAL CHARACTERISTICS
PHYSICAL CHARACTERISTICS
OPERATIONAL CHARACTERISTICS
INTERFACES
SECTION 2
INSTALLATION CONSIDERATIONS
2.1
2.1.1
2.1.2
2.1.3
2.1.4
2.2
2.2.1
2.3
2.4
ANTENNA CONSIDERATIONS
SATELLITE VISIBILITY
NOISE SOURCES
ELECTRICAL BONDING
ANTENNA LIMITATIONS
RACK CONSIDERATIONS
ACCESSIBILITY
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: The GPS 100 must have software version 2.09 or later to interface properly with
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
The GPS 100 offers the versatility of fixed installation in a panel mounted aviation rack
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:
(Structural rating for antenna)
6.25 Inches
2 inches
3.95 inches
28 oz.
8 oz.
4 oz.
11 oz.
Subsonic
1.2.2 Operational Characteristics
Temperature Range:
Humidity:
Altitude Range:
Power Input:
-15 oC to +70 oC
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
should not be routed near components or cabling which are sources of electrical noise.
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
One of the following two installation kits is required for aircraft installation, depending
on the type of antenna used.
The GPS 100 Aviation Installation Kit (010-10002-00) consists of the following parts:
P/N
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
DESCRIPTION
QTY
BLADE ANTENNA SUBASSEMBLY
1
RACK SUBASSEMBLY
1
BACKING PLATE
1
EJECTOR PIN
4
PLACARD, INSTRUMENT PANEL
1
INSTALLATION MANUAL (THIS MANUAL) 1
#8-32 SS, PH, FLAT HEAD SCREW
4
ANTENNA GASKET
1
CABLE ASSY, COAX
1
CONNECTOR, BNC, MALE, CLAMP
1
CONNECTOR, 15 PIN DSUB, FEMALE
1
The GPS 100 Low Profile Aviation Installation Kit (010-10008-00) consists of the
following parts:
P/N
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
DESCRIPTION
QTY
LOW PROFILE ANTENNA SUBASSEMBLY 1
RACK SUBASSEMBLY
1
BACKING PLATE
1
EJECTOR PIN
4
PLACARD, INSTRUMENT PANEL
1
INSTALLATION MANUAL (THIS MANUAL) 1
NUT, SELF-LOCKING, #8-32
4
ANTENNA GASKET
1
CABLE ASSY, COAX
1
CONNECTOR, BNC, MALE, CLAMP
1
CONNECTOR, 15 PIN DSUB, FEMALE
1
The following equipment is required for installation but is not included in the
installation kit:
#6-32 Flat Head Screw (4 ea.)
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#6-32 Self-locking Nut (4 ea.)
3.2 ANTENNA INSTALLATION
The Blade Antenna outline and footprint dimensions are shown in Figure 3-1. The Low
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 considering 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 recommendations 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
installing the rack into the instrument panel. The rack is designed to facilitate removal
of the GPS 100 for portable use. Deformation of the rack may make it difficult to install
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 setup 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
After completing the installation, a placard stating “GPS limited to VFR use only” must
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
In order to verify the installation, the aircraft must be outside the hanger and well away
from any buildings or aircraft that might block satellite signals. To perform the
checkout procedure it is necessary to be familiar with operating the GPS 100 or to have
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 setup per the instructions in Section 3.5 before performing the checkout procedure. Prior
to approving the Initialization page verify the following interfaces as appropriate:
CDI
Ensure the CDI is deflected half scale left (2.5 dots).
TO/FROM
Ensure the TO/FROM flag is in a TO condition.
NAV FLAG
Ensure the NAV FLAG is out of view.
MESSAGE ANNUNCIATOR
Ensure the message annunciators are illuminated.
RMI
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
minutes to obtain navigation information (15 minutes or less when searching the sky).
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.
ARGUS 3000/5000/7000 or STORMSCOPE SERIES II with NAVAID or SHADIN FUEL
MANAGEMENT SYSTEM
Once GPS position information is available, use the AutoStoreTM function to store a
waypoint at your current position (see Chapter 8 of the GPS 100 Owner’s Manual for
information on the AutoStoreTM function). After storing your location, GOTO the stored
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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Antenna masked by vertical fin,
T tail, or dorsal fin
OK
Antenna must be on
top of aircraft.
f:\antplace.cdr
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 location 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
GARMIN GPS 100 navigation system in the Beech Duke Model B60 in accordance with
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 190-0000400. 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
at fuselage station 138.0. Figure A-2 illustrates the proper antenna positioning. 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,
assuring that the front is not twisted out of square. Match drill the flanges on the radio
rack to the installation holes on the GPS 100 aviation rack. Using 4 each #6-32 screws
and self locking nuts, attach the aviation rack to the aircraft panel. For additional
information, refer to the Installation Manual.
2.3
WIRING
Fabricate an appropriate cable to connect the GPS 100 aviation rack to 28VDC power,
a message annunciator, a remote switch (for selecting between GPS and standard
navigation equipment), a transfer switch with integral white, illuminated annunciators 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
instrument panel in the location shown in Figure A-3 which states “GPS limited to VFR
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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