Garmin GPS 150, 174 User Manual
GPS 150
INSTALLATION MANUAL
GARMIN INTERNATIONAL, INC. PART NUMBER: 190-00026-00
1200 E. 151st STREET REVISION Q, 3 APRIL 1998
OLATHE, KANSAS 66062-3426
Av. Kit Install. Manual
190-00026-00 Rev. Q
Page 1
© 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.
Av. Kit Install. Manual
190-00026-00 Rev. Q
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TABLE OF CONTENTS
SECTION 1 GENERAL DESCRIPTION
1.1 INTRODUCTION
1.2 TECHNICAL CHARACTERISTICS
1.2.1 PHYSICAL CHARACTERISTICS
1.2.2 OPERATIONAL CHARACTERISTICS
1.2.3 INTERFACES
SECTION 2 INSTALLATION CONSIDERATIONS
2.1 ANTENNA CONSIDERATIONS
2.1.1 SATELLITE VISIBILITY
2.1.2 NOISE SOURCES
2.1.3 ELECTRICAL BONDING
2.1.4 ANTENNA LIMITATIONS
2.1.5 VHF COMM INTERFERENCE
2.2 RACK CONSIDERATIONS
2.2.1 ACCESSIBILITY
2.3 CABLING AND WIRING
2.4 COOLING AIR
2.5 ANNUNCIATORS
2.6 EXTERNAL ALTITUDE INPUT
SECTION 3 INSTALLATION PROCEDURE
3.1 INSTALLATION ACCESSORIES
3.2 ANTENNA INSTALLATION
3.3 CABLE INSTALLATION
3.4 RACK INSTALLATION
3.5 GPS 150 INSTALLATION AND REMOVAL
3.6 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 PINOUT DEFINITION
1-2 INTERCONNECT SCHEMATIC
2-1 ANTENNA INSTALLATION CONSIDERATIONS
2-2 GPS INSTALLATION CONSIDERATIONS
3-1 STUD MOUNT GA 56 INSTALLATION
3-2 FLANGE MOUNT GA 56 INSTALLATION
3-3 COAX CABLE INSTALLATION
3-4 AVIATION RACK DIMENSIONS
3 -5 AVIATION RACK INSTALLATION
A-1 FUNCTIONAL BLOCK DIAGRAM
A-2 FUSELAGE STATIONS AND WEIGHT/BALANCE DATA
A-3 PANEL LAYOUT AND BREAKER LOCATION
A-4 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: 6.25 Inches
Height: 2 inches
Depth: 5.65 inches
GPS 150 Weight: 2.14 lbs.
GA 56 Antenna Weight: 4 oz.
Aviation Rack Weight: 14 oz.
Max Air Speed: Subsonic
(Structural rating for antenna)
1.2.2 OPERATIONAL CHARACTERISTICS
Operating Temperature Range: -20 oC to +55 oC
Humidity: 95% non-condensing
Altitude Range: -1,500 to 50,000 ft.
Power Input: 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: Capable of driving up to three 1000 ohm parallel
(Pins 1 and 5) loads, +150 millivolts full scale deflection with a
maximum output of +300 millivolts.
To/From: Capable of driving up to three 200 ohm parallel
(Pins 2 and 6) loads, +82 millivolts full scale deflection.
Units with Mod Status 1: +190 millivolts full scale
deflection.
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Nav Flag: Capable of driving up to three 1000 ohm parallel
(Pins 3 and 4) loads, 375 millivolts for flag out-of-view, and
+40 millivolts for flag in-view.
OBI data: Output providing bearing to waypoint data for a
(Pins 7, 8, and 23) Bendix/King RMI (KI 229 or equivalent).
Message annunciators: Output capable of driving negative logic message
(Pin 20) annunciators by sinking up to 500mA.
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: Output capable of driving positive logic NAV Super
(Pin 10) Flag by sourcing up to 500mA for flag out of view (NAV
valid).
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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. This reduces the percentage of time
the blade blocks the antenna.
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) 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.
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
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 following hardware is required for installation of
the mounting rack, but is not provided:
#6-32 Flat Head Screw (4 ea.) #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 CARD - AMERICAS DATABASE
010-10038-01 MEMORY CARD - INTERNATIONAL DATABASE
010-10038-02 MEMORY CARD - WORLDWIDE DATABASE
010-10032-03 MEMORY CARD - USER
MISCELLANEOUS OPTIONS
190-00048-00 GPS 150 PILOT'S GUIDE
190-00048-01 GPS 150 QUICK REFERENCE GUIDE
330-00067-00 GPS 1.57542 GHZ NOTCH FILTER
362-00010-00 WALL CHARGER - 110/220VAC
3.2 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
Av. Kit Install. Manual
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