Garmin 174 GPS Receiver User Manual

GPS 150
INSTALLATION MANUAL
GARMIN INTERNATIONAL, INC.
1200 E. 151st STREET
OLATHE, KANSAS 66062-3426
PART NUMBER: 190-00026-00
REVISION Q, 3 APRIL 1998
Av. Kit Install. Manual
190-00026-00 Rev. Q
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© Copyright 1992-1998
Garmin Corporation
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.
1200 E. 151st Street
Olathe, Kansas 66062-3426
U.S.A.
REVISION RECORD
2264
Rev. E, 25 June 1993 Change Section 3.1 to reflect accessory
configuration.
2316
Rev. F, 23 July 1993
Reverse Pin locations on Fig. 1-1
2351
Rev. G, 18 Aug 1993
Add Altitude Serializer interface details.
2470
Rev. H, 15 Oct 1993
Remove Warning Low from Pin-out; improve
Super Flag description; add rack dimension
3404
Rev. J, 12 Sept 1994
Chg designation to pin 12 on arrival alarm
annunciator
3777
Rev. K,30 Dec 1994
Add additional fuel flow options; remove old
antenna options; add GA56 antennas
5827
Rev. L, 28 June 1996 Chg to barrel type crimp conn
6576
Rev. M, 21 Jan 1997
Correct Database Option Numbers
7708
Rev. N, 10 Dec 1997
Add additional antenna install. instructions
8322
Rev. P, 28 Jan 1998
Chg to/from voltages, install. dwg
8452
Rev. Q, 3 April 1998
Misc chgs.
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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
2.1.5
2.2
2.2.1
2.3
2.4
2.5
2.6
ANTENNA CONSIDERATIONS
SATELLITE VISIBILITY
NOISE SOURCES
ELECTRICAL BONDING
ANTENNA LIMITATIONS
VHF COMM INTERFERENCE
RACK CONSIDERATIONS
ACCESSIBILITY
CABLING AND WIRING
COOLING AIR
ANNUNCIATORS
EXTERNAL ALTITUDE INPUT
SECTION 3
INSTALLATION PROCEDURE
3.1
3.2
3.3
3.4
3.5
3.6
INSTALLATION ACCESSORIES
ANTENNA INSTALLATION
CABLE INSTALLATION
RACK INSTALLATION
GPS 150 INSTALLATION AND REMOVAL
PLACARD
SECTION 4
CHECKOUT PROCEDURE
SECTION 5
CONTINUED AIRWORTHINESS
APPENDIX A
INSTALLATION DETAILS FOR BEECH V35B
APPENDIX B
CONNECTOR CHANGES
APPENDIX C
STC PERMISSION
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LIST OF ILLUSTRATIONS
FIGURE
1-1
1-2
2-1
2-2
3-1
3-2
3-3
3-4
3-5
PINOUT DEFINITION
INTERCONNECT SCHEMATIC
ANTENNA INSTALLATION CONSIDERATIONS
GPS INSTALLATION CONSIDERATIONS
STUD MOUNT GA 56 INSTALLATION
FLANGE MOUNT GA 56 INSTALLATION
COAX CABLE INSTALLATION
AVIATION RACK DIMENSIONS
AVIATION RACK INSTALLATION
A-1
A-2
A-3
A-4
FUNCTIONAL BLOCK DIAGRAM
FUSELAGE STATIONS AND WEIGHT/BALANCE DATA
PANEL LAYOUT AND BREAKER LOCATION
WIRING DIAGRAM
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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 150 Aviation Kit.
After installation of the GPS 150 system, FAA Form 337 must be completed by an
appropriately certificated agency to return the aircraft to service.
1.2
TECHNICAL CHARACTERISTICS
The GPS 150 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 150 Weight:
GA 56 Antenna Weight:
Aviation Rack Weight:
Max Air Speed:
(Structural rating for antenna)
6.25 Inches
2 inches
5.65 inches
2.14 lbs.
4 oz.
14 oz.
Subsonic
1.2.2 OPERATIONAL CHARACTERISTICS
Operating Temperature Range:
Humidity:
Altitude Range:
Power Input:
-20 oC to +55 oC
95% non-condensing
-1,500 to 50,000 ft.
10 to 33 VDC, 5 watts Max.
1 . 2 . 3 INTERFACES
The GPS 150 provides interfaces to various general aviation instruments. Figure 11 defines the function of each pin on the 37 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 5)
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 6)
Capable of driving up to three 200 ohm parallel
loads, +82 millivolts full scale deflection.
Units with Mod Status 1: +190 millivolts full scale
deflection.
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Nav Flag:
(Pins 3 and 4)
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 23)
Output providing bearing to waypoint data for a
Bendix/King RMI (KI 229 or equivalent).
Message
(Pin 20)
Output capable of driving negative logic message
annunciators by sinking up to 500mA.
annunciators:
RS232 chan 1 output data: Output capable of driving ARGUS3000/5000/7000,
(Pin 24)
STORMSCOPE SERIES II with NAVAID moving
map displays, Shadin 91204X[T]/91053X[T],
Electronics International FP-5L fuel flow systems, or
Shadin 962801 Fuel/Airdata Computer. Conforms to
the EIA specification RS-232C.
RS232 chan 2 output data: Output capable of driving real-time plotting interface
(Pin 19)
on GARMIN PC software or NMEA 0183 version 2.0
compatible mapping device. Conforms to the EIA
specification RS-232C.
RS232 chan 1 input data: Input capable of receiving serial altitude data from
(Pin 17)
either an ICARUS Instruments 3000, Shadin Company
(formerly Rosetta MicroAvionics) 8800T, 9000T, or
9200T series altitude serializer/encoder, Shadin
91204XT/91053XT Series Fuel management system,
Arnav FC-10/FT-10 fuel computer/totalizer,
Electronics International FP-5L fuel flow system, or
Shadin 962801 Fuel/Airdata Computer. Conforms to
the EIA specification RS-232C.
Arrival alarm annunciator: Output capable of driving negative logic annunciator
(Pin 12)
by sinking up to 500mA.
ARINC 429 Output A & B: Output capable of interfacing with any device that has
(Pins 15 and 16)
an input conforming to the GAMA ARINC 429
specification.
NAV Super Flag Output:
(Pin 10)
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Output capable of driving positive logic NAV Super
Flag by sourcing up to 500mA for flag out of view (NAV
valid).
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 150.
2.1
ANTENNA CONSIDERATIONS
2 . 1 . 1 SATELLITE VISIBILITY
The GPS 150 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 antenna installation.
For rotorcraft, locate the GA 56 antenna:
1)
As far from the main rotor hub as possible.
the blade blocks the antenna.
This reduces the percentage of time
2) As far below the blade surface as possible if installing the antenna under the blade.
This reduces signal distortion caused by the blades.
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 150
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
GARMIN'S GA 56 Antennas are recommended for installations where the airspeed of
the aircraft will be subsonic.
2 . 1 . 5 VHF COMM INTERFERENCE
On many panel-mounted aircraft the VHF COMM radiates strong harmonics from the
unit and the antenna. If the antenna is found to be the problem, a 1.57542 GHz notch
filter (GPN 330-00067-00) may be installed in the VHF COMM coax, as close to the
COMM as possible. If the box is found to be radiating, the following can be done:
1)
Place the antenna as far from the VHF COMM unit and antenna as
possible.
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2.2
2)
Replace or clean VHF COMM rack connector to assure good coax ground.
3)
Place a grounding brace between the GPS 150, VHF COMM, and ground.
4)
Shield the VHF COMM wiring harness.
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
The recommended antenna cable type is M17/155-0001 (RG-58A/U) per MIL-C-17.
Maximum allowable length for this cable type is 40 feet. Other cable types with 50
ohms nominal impedance and longer lengths can be used, provided the installer
insures that the attenuation does not exceed 10dB 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 and routing near aircraft control cables.
2.4
COOLING AIR
Cooling air is not required for the GPS 150, however as with any electronic equipment,
reduced operating temperature can contribute to increased reliability. Additionally,
location of the GPS 150 in a stack of other power dissipating equipment can produce
unacceptably high ambient air temperatures around the unit. A 5/8 inch diameter
air fitting is provided on the rear of the mounting rack for the purpose of admitting
cooling air under such conditions.
2.5
ANNUNCIATORS
If the installation includes any electrical interface with other flight instruments, an
annunciator may be required. Refer to current FAA directives.
2.6
EXTERNAL ALTITUDE INPUT
Pressure altitude input from an external source may benefit GPS 150 system
performance during times of minimal satellite coverage or poor satellite geometry.
Provisions for RS-232 compatible serial altitude input are described in the Interfaces
section (Section 1.2.3) of this manual.
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SECTION 3 INSTALLATION PROCEDURE
3.1
INSTALLATION ACCESSORIES
The following installation accessories are available:
ANTENNA AND RACK OPTIONS
010-10040-01
GA 56 LOW PROFILE ANTENNA KIT (Stud-mount GA 56 antenna, mounting hardware,
no cable)
010-10040-02
GA 56 FLANGE MOUNT ANTENNA KIT (Flange-mount GA 56 antenna, mounting hardware,
no cable)
011-00059-00
MOUNTING RACK w/CONNECTOR
310-00006-00
RG-58A/U CABLE
320-00003-00
15 FT. LOW-LOSS AVIATION ANTENNA EXTENSION CABLE w/RIGHT ANGLE BNC CONN.
320-00003-02
30 FT. LOW-LOSS AVIATION ANTENNA EXTENSION CABLE w/RIGHT ANGLE BNC CONN.
325-00014-00
GPS 100 to GPS 150 WIRING HARNESS ADAPTER
330-00087-00
CONNECTOR, BNC, MALE, CLAMP
011-00313-01
CONNECTOR (J1 only)KIT
The mounting rack is required for approved installations.
the mounting rack, but is not provided:
#6-32 Flat Head Screw (4 ea.)
The following hardware is required for installation of
#6-32 Self-locking Nut (4 ea.)
Cable and two BNC connectors are required to make the antenna cable, or it can be fabricated by the installer
from materials meeting the requirements of paragraph 2.3.
DATA BASE OPTIONS
010-10038-00
MEMORY
010-10038-01
MEMORY
010-10038-02
MEMORY
010-10032-03
MEMORY
MISCELLANEOUS
190-00048-00
190-00048-01
330-00067-00
362-00010-00
3.2
CARD
CARD
CARD
CARD
-
AMERICAS DATABASE
INTERNATIONAL DATABASE
WORLDWIDE DATABASE
USER
OPTIONS
GPS 150 PILOT'S GUIDE
GPS 150 QUICK REFERENCE GUIDE
GPS 1.57542 GHZ NOTCH FILTER
WALL CHARGER - 110/220VAC
ANTENNA INSTALLATION
The GA 56 Antenna outline and footprint dimensions are shown in Figures 3-1 and
3-2.
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 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.
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
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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 to the rack location keeping in mind the recommendations
of Section 2. Secure the cable in accordance with good aviation practice.
B. Trim the coaxial cable to the desired length and install the BNC connector (33000087-00) per the cabling instructions on Figure 3-3. If the connector is provided
by the installer, follow the connector manufacturer's instructions for cable
preparation.
C . Contacts for the 37-pin connector must be crimped into the individual wires of the
aircraft wiring harness. The following table lists recommended crimp tools:
Non- GARMIN part numbers shown are not maintained by GARMIN and consequently
are subject to change without notice.
See Appendix B for information regarding obsolete stamped type contacts.
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3.4
RACK INSTALLATION
A. Figure 3-4 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 150 for portable use. Deformation of the rack may make it
difficult to install and remove the GPS 150.
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 3-5).
3.5
GPS 150 INSTALLATION AND REMOVAL
The GPS 150 is installed in the rack by sliding it straight in until about 1 inch short
of the final position. A 3/32 inch 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 counter-clockwise until the unit is forced out about 3/4 inch 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.
3.6
PLACARD
After completing the installation, a placard stating that the GPS 150 is limited to VFR
use 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 unit, or a suitable equivalent.
SECTION 4 CHECKOUT PROCEDURE
The GPS 150 ground test procedure incorporates a series of four (4) display pages to
test CDI/flag, OBI, annunciator, and power functions of the unit. These pages can
be selected by ensuring the flashing cursor is off and rotating the outer knob either
direction. To change data on the displayed test page, depress the CRSR key and the
cursor will begin flashing on the first selectable field on the page. The inner knob will
change data on the selected field. The ENT key or the outer knob will advance to the
next field on the page. Pressing the CRSR key again will stop the current field from
flashing, allowing the outer knob to select the next test page (see Chapter 2 of the GPS
150 Pilot's Guide for more information on page and data selection).
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With power applied to the aviation rack and the GPS 150 unit off, continuously
depress the ENT key and turn the unit on (release the ENT key when the display
activates). Rotate the outer knob, and the CDI Test Page will be displayed. Using the
controls on the GPS 150 front panel, make the selections indicated below and verify
the interfaces as appropriate:
CDI
Full scale
Full scale
Centered
Maximum
Maximum
left
right
scale left
scale right
Ensure
Ensure
Ensure
Ensure
Ensure
the CDI is deflected full scale left (5 dots)
the CDI is deflected full scale right (5 dots)
the CDI is centered
the CDI is deflected beyond full scale left
the CDI is deflected beyond full scale right
TO/FROM/FLAG
TO
FROM
FLAG
Ensure TO flag is visible
Ensure FROM flag is visible
Ensure TO and FROM are NOT visible
CDI FLAG
IN VIEW
OUT OF VIEW
Ensure CDI flag is in view
Ensure CDI flag is out of view
SUPERFLAG
IN VIEW
OUT OF VIEW
Ensure superflag is in view
Ensure superflag is out of view
Select the OBI Test Page by removing the cursor from the CDI Test Page and turning
the outer knob one detent to the right. Using the controls on the GPS 150 front panel,
make the selections indicated below and verify the interfaces as appropriate:
OBI Data
VALID
INVALID
OBI Value
Ensure that the OBI indicates the proper value
Ensure the OBI is invalid
Ensure that the OBI displays the value entered when
the VALID option is selected
Select the Annunciator Test Page by removing the cursor from the OBI Test Page and
turning the outer knob one detent to the right. Using the controls on the GPS 150 front
panel, make the selections indicated below and verify the interfaces as appropriate:
Panel
OFF
ON
Ensure no panel annunciators are illuminated
Ensure all panel annunciators are illuminated
OFF
ON
Ensure the Message Annunciator is OFF
Ensure the Message Annunciator is ON
Msg
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Arrival
OFF
ON
Ensure the Arrival Annunciator is OFF
Ensure the Arrival Annunciator is ON
Select the Power Test Page by removing the cursor from the Annunciator Test Page and
turning the outer knob one detent to the right. Verify the following status is displayed:
Using EXTERNAL POWER
Memory Batt OK
Intrnl Batt OK
Note: Depending on the power source for the unit (aircraft, wall charger, or internal
battery) and the status of battery charging, the top line may read: “Battery
power”, “charger power”, “external power”.
Turn the GPS 150 off in preparation for a signal acquisition test.
The following tests assume that the aircraft is outside the hangar facility and well away
from buildings or other obstructions that might interfere with satellite signal
reception. With power applied to the aviation rack, turn the GPS 150 on. The Self Test
Page will be displayed followed by the Data Base Page. Upon approval of the Data Base
Page, the Satellite Status Page will be displayed. 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.
Once GPS position information is available, use the DIRECT key to activate the
navigation function to a nearby NAVAID, intersection, or airport. Ensure the ARGUS,
STORMSCOPE, EFIS, fuel management system or other mapping device is receiving
data from the GPS 150 and is functioning properly (see Chapter 5 of the GPS 150 Pilot's
Guide for more information on the Direct function).
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FIGURE 1-1 PINOUT DEFINITION
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FIGURE 1-2 INTERCONNECT SCHEMATIC
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Antenna masked by vertical
T tail, or dorsal fin
fin,
OK
Antenna must be
top of aircraft.
on
FIG 2-1
ANTENNA INSTALLATION CONSIDERATIONS
Maintain 6"(16 cm)
compass safe distance
FIG 2-2
GPS INSTALLATION CONSIDERATIONS
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FIG 3-1
STUD MOUNT GA 56 ANTENNA INSTALLATION
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FIGURE 3-2
FLANGE MOUNT GA 56 ANTENNA INSTALLATION
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FIGURE 3-3 COAX CABLE INSTALLATION
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FIGURE 3-4 AVIATION RACK DIMENSIONS
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FIGURE 3-5 AVIATION RACK INSTALLATION
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APPENDIX A INSTALLATION DETAILS FOR BEECH V35B
1.0
INTRODUCTION
This appendix provides airframe specific information which is necessary to install the
GARMIN GPS 150 navigation system in the Beech Bonanza Model V35B in accordance
with STC SA00066WI. See Appendix C for copy of STC. When so installed, the GPS
150 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 150 Aviation Kit Installation Manual, P/N 190-0002600. Within this appendix, the base document will be referred to as the "Installation
Manual".
2.0
INSTALLATION INSTRUCTIONS
2.1
ANTENNA
The GPS 150 antenna is to be installed on top of the cabin on the aircraft centerline
at fuselage station 130. 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 150 aviation rack is to be installed in the instrument panel radio rack as
shown in figure A-3. The controls and display of the GPS 150 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 150 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 150 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-3. 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 150 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 150
components. The aircraft should then be returned to service by completion of FAA
form 337 by an appropriately certificated person.
5.0
CONTINUED AIRWORTHINESS
Maintenance of the GPS 150 is on condition only.
150 is not required.
Periodic maintenance of the GPS
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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 AND BREAKER LOCATION
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FIG A-4
WIRING DIAGRAM
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APPENDIX B CONNECTOR CHANGES
STAMPED CONTACT CONNECTOR USAGE
Garmin panel mount GPS radios have previously been shipped with stamped crimp type
contacts. All products are now being shipped with machined mil-spec contacts with
color-coded barrels. The following figures can be used to identify which type contact you
have:
When working with the stamped crimp type contacts, the following tools should be used:
Tools
Supplier
Amp
ITT Cannon
Cinch
37 position connectors
Crimp Tool
Extraction Tool
58448-2
91067-22
995-2000-000
980-0008-124
HTD-544
CIET-20-HDB
Part numbers shown are not maintained by Garmin and consequently are subject to
change without notice.
$Y.LW,QVWDOO0DQXDO
5HY4
3DJH
APPENDIX C STC PERMISSION
Consistent with N8110.69 or Order 8110.4, Aviation Authority approved installers
are hereby granted permission to use STC# SA00066WI data to modify aircraft.
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