Garmin GPS 165 Manuel utilisateur

Av. Kit Install. Manual

190-00066-02 Rev. J

Page 1

GPS 165

INSTALLATION MANUAL

GARMIN INTERNATIONAL, INC. PART NUMBER: 190-00066-02

1200 E. 151st STREET REVISION J, 27 MARCH 1998

OLATHE, KANSAS 66062-3426

Av. Kit Install. Manual

190-00066-02 Rev. J

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GARMIN Corporation

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, KS 66062

U.S.A.

Initial Rev. A, 18 Mar 1994 Initial release

3160 Rev. B, 01 Jun 1994 Add Crimp/Extract Tools & Access. List, Misc.

3405 Rev. C, 12 Sept 1994 Add Electronics International fuel flow interface

selection, update output unit list, Fig. 1-3,

installation requirements and wiring diagram

4841 Rev. D, 09 Nov 1995 Add Mid-Continent as option

5219 Rev. E, 29 Jan 1996 Add MCI options, JST connector details, misc

5827 Rev. F, 28 June 1996 Chg to barrel type crimp connectors

7708 Rev. G, 10 Dec 1997 Add additional antenna install. instructions

8322 Rev. H, 28 Jan 1998 Update install. dwg.

8383 Rev. J, 27 Mar 1998 Add to/from voltage & mod status/misc chgs.

REVISION RECORD

ECO # Rev. Date of Rev. Description FAA Approval

Av. Kit Install. Manual

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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

1.2.3.1 37 PIN CONNECTOR (J101)

1.2.3.2 26 PIN CONNECTOR (J102)

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 VHF COMM INTERFERENCE

2.2 UNIT ACCESSIBILITY

2.3 CABLING AND WIRING

2.4 COOLING AIR

2.5 EXTERNAL ALTITUDE INPUT

2.6 MINIMUM INSTALLATION REQUIREMENTS

SECTION 3 INSTALLATION PROCEDURE

3.1 INSTALLATION ACCESSORIES

3.2 ANTENNA INSTALLATION

3.3 CABLE INSTALLATION

3.4 GPS 165 INSTALLATION AND REMOVAL

SECTION 4 POST INSTALLATION CONFIGURATION AND CHECKOUT

PROCEDURE

4.1 TEST MODE OPERATIONS

4.2 INSTALLATION CONFIGURATION

4.2.1 SELECTED COURSE CALIBRATION

4.2.2 I/O CHANNEL 1

4.2.3 RS-422 CHANNEL

4.2.4 ARINC 429 CHANNEL

4.2.5 CONFIGURATION

4.2.6 I/O CHANNEL 2

4.3 GROUND TEST

4.3.1 CDI AND FLAG TEST

4.3.2 OBI TEST

4.3.3 COMMUNICATIONS LOOPBACK TEST

4.3.4 ANNUNCIATOR TEST

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4.3.5 EXTERNAL SWITCH TEST

4.3.6 ALTITUDE INPUT TEST

4.3.7 POWER TEST

4.3.8 SIGNAL ACQUISITION TEST

4.3.9 VHF COMM INTERFERENCE CHECK

SECTION 5 CERTIFICATION

SECTION 6 CONTINUED AIRWORTHINESS

APPENDIX A CERTIFICATION DOCUMENTS

APPENDIX B CONNECTOR CHANGES

APPENDIX C REFERENCE DISCRETE SWITCH/ANNUNCIATOR INSTALLATION

APPENDIX D STC PERMISSION

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LIST OF ILLUSTRATIONS

FIGURE

1-1 PINOUT DEFINITION, 37 PIN DSUB

1-2 PINOUT DEFINITION, 26 PIN HD-DSUB

1-3 INTERCONNECT SCHEMATIC

2-1 ANTENNA INSTALLATION CONSIDERATIONS

2-2 GPS INSTALLATION CONSIDERATIONS

3-1 REMOTE BATTERY PACK ASSEMBLY

3-2 GA 56 ANTENNA INSTALLATION

3-3 FLANGE MOUNT GA 56 ANTENNA INSTALLATION

3-4 COAX CABLE INSTALLATION

3-5 GPS 165 FACE DIMENSIONS

3-6 AVIATION RACK INSTALLATION

Av. Kit Install. Manual

190-00066-02 Rev. J

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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 165 Aviation Kit.

After installation of the GPS 165 system, FAA Form 337 must be completed by an

appropriately certificated agency to return the aircraft to service.

1.2 TECHNICAL CHARACTERISTICS

The GPS 165 is a full-featured GPS navigator intended for fixed installation in a

Dzusrail mounted aviation rack.

For TSO Compliance, see Appendix A.

The conditions and tests required for TSO approval of this article 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.

1.2.1 PHYSICAL CHARACTERISTICS

Width: 5.75 inches

Height: 2.25 inches

Depth: 5.00 inches

GPS 165 Weight: 2.0 lbs.

Low Profile Antenna Weight: 4 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: 0 to 50,000 ft.

Power Input: 10 to 33 VDC, 5 watts Max.

1.2.3 INTERFACES

The GPS 165 provides interfaces to various general aviation instruments. Figure 1-

1 defines the function of each pin on the 37 pin DSUB connector (J101) located at the

back of the unit. Figure 1-2 depicts the function of each pin in 26 pin HD-DSUB

connector (J102) located above the 37 pin connector at the back of the unit. Figure

1-3 depicts the interconnects between the unit and other instruments. Appendix

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C depicts the interconnect between the rack and other instruments using discrete

switch annunciators. The following interfaces are provided.

1.2.3.1 37 PIN CONNECTOR (J101)

CDI: Capable of driving up to three 1000 ohm parallel

(Pins 1 and 5) CDI loads.

To/From: Capable of driving up to three 200 ohm parallel to/

(Pins 2 and 6) from loads. Units without Mod Status 1: +82 millivolts

full scale deflection. Units with Mod Status 1: +190

millivolts full scale deflection.

Nav Flag: Capable of driving up to three 1000 ohm parallel flag

(Pins 3 and 4) loads.

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. Indicates an

unread message is available for viewing.

RS232 chan 1 output data: Output capable of driving devices as listed in Section

(Pin 24) 4. Conforms to the EIA specification EIA-232C.

RS232 chan 2 output data: Output capable of driving devices as listed in Section

(Pin 19) 4. Conforms to the EIA specification EIA-232C.

RS232 chan 1 input data: Input capable of receiving data from devices as listed

(Pin 17) in Section 4. Conforms to the EIA specification EIA-

232C.

GPS arrival alarm: Output capable of driving negative logic annunciator

(Pin 12) by sinking up to 500mA. Indicates arrival at a

prescribed GPS waypoint

GPS approach annunciator: Output capable of driving negative logic annunciator

(Pin 13) by sinking up to 500mA. See GPS 165 Pilot's Guide,

(GPN 190-00065-00), for more information.

ARINC 429 Output A & B: Output capable of driving ARINC 429 devices as listed

(Pins 15 and 16) in Section 4.

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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RS422 input: Input capable of receiving serial OBS data from

(Pins 11 and 27) Collins Pro Line 2 EFIS DSP unit.

GPS approach select switch: Input, when grounded, arms approach mode.

(Pin 9)

GPS OBS: Capable of interfacing with a standard OBS

(Pins 14, 35, and 37) resolver.

ARINC 429 Input A & B: Input capable of receiving data from ARINC 429

(Pins 32 and 33) devices as listed in Section 4.

1.2.3.2 26 PIN CONNECTOR (J102)

Altimeter input: Capable of receiving encoded output data from any

(Pins 14-24) parallel altimeter device. (Gillham/Greycode).

GPS Sequence Switch: Input, when grounded, activates HOLD mode. See

(Pin 13) the GPS 165 Pilot's Guide, (GPN 190-00065-00), for

more information.

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 165.

2.1 ANTENNA CONSIDERATIONS

2.1.1 SATELLITE VISIBILITY

The GARMIN GA 56 Low Profile GPS 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 165

should not be routed near components or cabling which are sources of electrical noise.

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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 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.

2) Replace or clean VHF Comm rack connector to assure good coax ground.

3) Place a grounding brace between the GPS 165, VHF COMM and ground.

4) Shield the VHF COMM wiring harness.

2.2 UNIT 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 unit and connectors in the instrument panel. A location away

from heating vents or other sources of heat generation is optimal. In order to minimize

accumulation of dirt and residues on the face of the unit, it is best to mount the unit

with its face vertically positioned. 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 165, however as with any electronic equipment,

reduced operating temperature can contribute to increased reliability. Additionally,

location of the GPS 165 in a stack of other power dissipating equipment can produce

unacceptably high ambient air temperatures around the unit.

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2.5 EXTERNAL ALTITUDE INPUT

Pressure altitude input from an external source may be derived from a RS-232

compatible serial altitude input or Parallel Greycode/Gillham Altitude as described

in Section 4 of this manual. Gillham Altitude is not required when serial altitude is

used.

2.6 MINIMUM INSTALLATION REQUIREMENTS

Below is a list of required devices for A1 and A2 certification. Figure 1-3 shows various

equipment that can be used. For a specific list of equipment used in the initial STC,

see GPN 190-00065-07. Deviations from this equipment should be approved by the

FAA or the governing organization.

Pressure Altitude Device

This device delivers pressure altitude data to the GPS 165. This data can come

from an encoder or serializer.

Manual Course Device

This device delivers the manual course selected to the GPS 165. Course

information can come from an analog resolver, or from an EFIS via the ARINC

429 bus or RS 422 bus.

HSI/CDI Device

This device displays Nav Flag, Left/Right and To/From. This can be displayed

on an EFIS or HSI.

External Annunciators and Switches

NAV/GPS Switch/Annunciator

GPS Sequence Switch/Annunciator

Approach Switch/Annunciator (not required for A2)

Message Annunciator

Arrival Annunciator

The installer is advised to ensure that the switches and annunciators are the

functional equivalent to and perform at least as well as the GARMIN devices

used in the initial STC. The GARMIN switches and annunciators are sunlight

readable and in the primary view of the pilot. See Appendix C for what GARMIN

used in the initial STC installation. For other information concerning

switches/annunciators see the Generic Airplane Flight Manual Supplement

(190-00066-04) as well as current FAA directives.

Qualified GPS Antenna

This antenna must be one of those listed in the accessories list.

Remote Battery Pack (010-10041-00)

This device provides power to the GPS 165 during momentary power interrup-

tions.

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