Garmin G500 PFD Airplane Flight Manual Supplement

Rev.

Date

Description of Change

06/30/09

Initial Release

11/30/09

Add replacement instructions for OAT bond strap

02/08/11

Update referenced publications. Clarified periodic maintenance instructions. Foil check annual. Added new special inspection requirements and periodic bonding test.

08/15/11

Remove “FAA Approved” language. Update IM rev. Add additional instructions for Mid-Continent standby attitude indicator installations.

12/11/12

Added information regarding GAD 43e. Added additional Control,

Operating Information and deleted Pilot’s Guide reference. Incorporated

GDC 74 testing procedural information from Installation Manual. Revised lightning strike inspection.

G500 PFD/MFD System

Instructions for Continued Airworthiness

as installed in

_____________________________

(Make and Model Airplane)

Reg. No.____________ S/N_______________

Dwg. Number:

190-01102-00 Rev. 5

Garmin International, Inc.

1200 E. 151st Street

Olathe, Kansas 66062 USA

Record of Revision

1. INTRODUCTION ................................................................................................................... 3

1.1 Purpose ................................................................................................................. 3

1.2 Scope .................................................................................................................... 3

1.3 Document Control ................................................................................................. 3

1.4 Airworthiness Limitations Section ......................................................................... 3

1.5 Permission to Use Certain Documents ................................................................. 3

1.6 Definitions ............................................................................................................. 3

2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 4

2.1 Introduction ........................................................................................................... 4

2.2 Description of Alteration ........................................................................................ 4

2.3 Control, Operating Information ............................................................................. 4

2.4 Servicing Information ............................................................................................ 5

2.5 Periodic Maintenance Instructions ........................................................................ 6

2.6 Troubleshooting Information ................................................................................. 8

2.7 Removal and Replacement Information ............................................................... 8

2.8 Diagrams............................................................................................................... 9

2.9 Special Inspection Requirements ......................................................................... 9

2.10 Application of Protective Treatments .................................................................... 9

2.11 Data Relative to Structural Fasteners ................................................................... 9

2.12 Special Tools ........................................................................................................ 9

2.13 Additional Instructions ........................................................................................... 10

2.14 Overhaul Period .................................................................................................... 10

2.15 ICA Revision and Distribution ............................................................................... 10

2.16 Assistance............................................................................................................. 10

2.17 Implementation and Record Keeping ................................................................... 10

3. APPENDIX A ......................................................................................................................... 11

3.1 LRU Locations ...................................................................................................... 11

3.2 Wire Routing – Single-Engine .............................................................................. 12

3.3 Wire Routing – Twin-Engine ................................................................................. 13

G500 PFD/MFD System 190-01102-00 Rev. 5 Instructions for Continued Airworthiness Page 2 of 13

1. INTRODUCTION

1.1 Purpose

This document is designed for use by the installing agency of the Garmin G500 PFD/MFD System as Instructions for Continued Airworthiness in response to Federal Aviation regulation (FAR) Part 23.1529, and Part 23 Appendix G. This ICA includes information required by the operator to adequately maintain the Garmin G500 system installed under Approved Model List (AML) STC.

1.2 Scope

This document identifies the Instruction for Continued Airworthiness for the modification of the aircraft for installation of the Garmin G500 PFD/MFD System installed under Approved Model List (AML) STC.

1.3 Document Control

This document shall be released, archived, and controlled in accordance with the Garmin document control system. When this document is revised, refer to Section 2.15 for information on how to gain FAA acceptance or approval and how to notify customers of changes.

1.4 Airworthiness Limitations Section

There are no additional Airworthiness Limitations as defined in 14 CFR § 23, Appendix G. G23.4 that result from this modification. The Airworthiness Limitations section is FAA approved and specifies maintenance required under §§43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.

1.5 Permission to Use Certain Documents

Permission is granted to any corporation or person applying for approval of a Garmin G500 system to use and reference appropriate STC documents to accomplish the Instructions for Continued Airworthiness and show compliance with STC engineering data. This permission does not construe suitability of the documents. It is the responsibility of the applicant to determine the suitability of the documents for the ICA.

1.6 Definitions

The following terminology is used within this document:

1) AC: Advisory Circular

2) ACO: Aircraft Certification Office

3) ADC: Air Data Computer

4) AEG: Aircraft Evaluation Group

5) AHRS: Attitude Heading Reference System

6) CFR: Code of Federal Regulations

7) FAA: Federal Aviation Administration

8) ICA: Instructions for Continued Airworthiness

9) MFD: Multi-Function Display

10) PFD: Primary Flight Display

11) PMI: Primary Manufacturing Inspector

12) STC: Supplemental Type Certificate

13) TSO: Technical Standard Order

14) TVS: Transient Voltage Suppressor

G500 PFD/MFD System 190-01102-00 Rev. 5 Instructions for Continued Airworthiness Page 3 of 13

Content, Scope, Purpose and Arrangement:

This document identifies the Instructions for Continued Airworthiness for the modification of the aircraft by installation of the Garmin G500 PFD/MFD System.

Applicability:

Applies to aircraft altered by installation of the Garmin G500 PFD/MFD System.

Definition of Abbreviations:

See Section 1.6

Precautions:

None

Units of measurement:

None

Referenced publications:

Garmin 190-01102-06 Rev. 7 “G500 AML STC Installation Manual” or later revisions

Retention:

This document, or the information contained within, will be included in the aircraft’s permanent records.

2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

2.1 Introduction

2.2 Description of Alteration

The Garmin G500 PFD/MFD System is a combination of Garmin LRUs designed to provide both a PFD and MFD in the primary field of view. The system consists of a GDU 620 display, GRS 77 AHRS, GDC 74( ) ADC, GMU 44 magnetometer, and GTP 59 outside air temperature probe. This modification may also include a Garmin GAD 43 Adapter and/or Mid Continent Instruments attitude indicator (models 4300-4( ), or 4200-( ) with MD420). Installation of the Garmin G500 system, specific for the aircraft installation, is documented in the G500 AML STC Installation Manual.

2.3 Control, Operating Information

The GDU 620, GRS 77, GMU 44, and GDC 74( ) are powered by an electrical bus which is normally energized with battery, generator, or external power applied to the aircraft. The GAD 43/43e is typically powered by an avionics bus which is normally controlled by the avionics bus power switch. The LRUs do not have individual power switches and are powered when the bus is energized and the circuit breakers are closed. The following circuit breakers provide power to the individual LRUs:

• PFD: GDU 620

• AHRS: GRS 77 #1 and GMU 44 #1

• ADC: GDC 74( )

• GAD: GAD 43/43e

In a dual G600 installation, the PFD, AHRS, and ADC circuit breakers are suffixed with the numbers 1 and 2 (i.e. AHRS 1 and AHRS 2). If an LRU is optionally powered from multiple circuit breakers, then the circuit breakers will be suffixed with the letters A and B (i.e AHRS 1A and AHRS 1B).

The GDU 620 has a PFD and MFD display and front panel controls for performing all normal and configuration operations. Knobs at the lower left and right corners are used for selecting and entering

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