Garmin G500H Operating instructions

Brand: Garmin

Model: G500H

Type: Operating instructions

Instructions for Continued Airworthiness

for the Garmin G500H System in Airbus AS350 and EC130

Garmin Ltd. Or its subsidiaries

c/o Garmin International, Inc.

1200 E. 151st Street

Olathe, Kansas 66062 USA

Dwg. Number:

190-01150-22 Rev. 1

REV.

DATE

DESCRIPTION OF CHANGE

02/11/2020

Initial Release

Instructions for Continued Airworthiness  190-01150-22 Rev 1 
for the Garmin G500H System in Airbus AS350 and EC130  Page 2 of 51 
TABLE OF CONTENTS 
CHAPTER 1 ............................................................................................................................................................... 3 
Section 01-00-00 Introduction .................................................................................................................................. 3 
CHAPTER 4 ............................................................................................................................................................... 3 
Section 04-00-00  Airworthiness Limitations ................................................................................................. 4 
CHAPTER 5 ............................................................................................................................................................... 5 
Section 05-00-00  Continued Airworthiness Inspections ........................................................................... 5 
Section 05-20-10  Continued Airworthiness Scheduled Inspections ..................................................... 7 
Section 05-20-20  Continued Airworthiness Special Inspections ........................................................ 12 
CHAPTER 6 ............................................................................................................................................................ 13 
Section 06-00-00  Dimensions and Access ..................................................................................................... 13 
CHAPTER 8 ............................................................................................................................................................ 18 
Section 8-00-00  Weight and Balance Information .................................................................................. 18 
CHAPTER 12 .......................................................................................................................................................... 19 
Section 12-00-00  Servicing Maintenance Practices .................................................................................. 19 
Section 12-10-00  Return-to-Service Practices ............................................................................................ 20 
Section 12-20-00  Calibration Requirements ............................................................................................... 21 
CHAPTER 20 .......................................................................................................................................................... 22 
Section 20-00-00  Standard Practices .............................................................................................................. 22 
Section 20-10-00  Torques Maintenance Practices .................................................................................... 23 
Section 20-30-00  Painting Maintenance Practices .................................................................................... 27 
Section 20-40-00  Corrosion Control Maintenance Practices ................................................................ 28 
Section 20-50-00  Mechanical Fastener Sealing Methods ....................................................................... 31 
Section 20-90-00  Dye Penetrant Inspection Methods ............................................................................. 32 
CHAPTER 31 .......................................................................................................................................................... 33 
Section 31-00-00  Instruments ........................................................................................................................... 33 
Section 98-00-00  Wiring Diagrams and Pitot-Static System Schematics ......................................... 49 
Section 98-10-00  Wiring Diagrams.................................................................................................................. 50 
Section 98-20-00  Pitot-Static System Schematic ....................................................................................... 51 

01-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 3 of 51

CHAPTER 1

Section 01-00-00 Introduction

This document provides the Instructions for Continued Airworthiness for the G500H Flight

Display System as installed in Airbus Helicopters AS 350 B2, AS 350 B3 and EC 130 B4. This

document satisfies the requirement for continued airworthiness as required by 14 CFR 27.1529

and Part 27 Appendix A. Modification of an aircraft by STC SR02295LA obligates the aircraft

operator to include the maintenance information provided by this document in the operator’s

Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program, if

applicable.

The contents of this ICA are limited to the support of equipment installed in accordance with

STC SR02295LA, which includes the GDC 72H Air Data Computer (ADC), GRS 79H Attitude and

Heading Reference System (AHRS), and GSU 75H Air Data, Attitude and Heading Reference

System (ADAHRS), using installation data from 190-01150-07, Installation Manual Addendum

G500H Part 27 AML STC. STC SR02295LA specifies that the G500H Flight Display System must

be installed in accordance with STC SR09575RC or SR09576RC as applicable, prior to installing

these sensors. The instructions contained within this document supplement the existing ICA

and system-level maintenance instructions contained within in the following reference

documents:

• 190-00792-12, Instructions for Continued Airworthiness for the Garmin G500H Installation

in Eurocopter AS350, for G500H system installed per STC SR09575RC

• 190-01527-15, Instructions for Continued Airworthiness for the Garmin G500H Installation

in Eurocopter EC130, for G500H system installed per STC SR09576RC

This document is required for maintaining the continued airworthiness of the aircraft. Garmin

Dealers may obtain the latest revision of this document at the Garmin Dealer Resource Center,

https://dealers.garmin.com. Dealers are notified of manual revision changes by way of a Garmin

Service Bulletin. Owners and operators may obtain the latest revision of this document at

www.flyGarmin.com or by contacting a Garmin dealer. Garmin contact information is available at

www.flyGarmin.com.

05-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 5 of 51

CHAPTER 5

Section 05-00-00 Continued Airworthiness Inspections

1. General

This chapter contains time limit intervals for the Component Overhaul Schedule and Scheduled

Inspections for the G500H Installation. This chapter is to be added to the approved scheduled

inspection for the rotorcraft.

2. Component Overhaul Schedule

The system does not require overhaul at a specific time period. Power on self-test and

continuous BIT will monitor the health of the G500H system. If any LRU indicates an internal

failure, the unit may be removed and replaced.

3. Scheduled Inspections Overview

The G500H Installation requires a 90 Day Inspection that must be performed 90 days after

installation and then afterwards within 90 days of the last G500H Installation 90 day inspection.

The 90 Day Inspection requirements are specified in Table 5-1.

The G500H Installation requires an Annual Inspection that must be performed within 1 year (12

months) of initial installation and then afterwards within 1 year (12 months) of the last G500H

Installation annual inspection. The annual inspection requirements are specified in Table 5-2.

The G500H Installation requires a 5 Year Inspection that must be performed within 60 months

of initial installation and then afterwards within 60 months of the last G500H Installation

inspection. The 5 Year Inspection requirements are specified in Table 5-3.

The G500H Installation requires a 10 Year/2000 Flight Hours Inspection that must be performed

within 120 months or 2000 flight hours, whichever occurs first, of initial installation and then

afterwards within 120 months or 2000 flight hours, whichever occurs first, of the last G500H

Installation 10 year/2000 flight inspections. The 10 Year/2000 Flight Hour Inspection

requirements are specified in Table 5-4.

4. Special Inspection Practices

Conditions may arise from incidents or accidents that may warrant additional inspection requirements.

A Special Inspection is required if the aircraft is involved in a hard landing or is subjected to total

immersion in water. If either of these conditions occurs, the G500H Installation must be inspected using

the same procedures called out in the Annual Inspection Procedures in Table 5-2.

05-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 6 of 51

5. Definitions and Acronyms

The following is short descriptions of words and terms used in the procedures for the required

scheduled inspections.

• Examine – Look carefully to find the condition of the component. Find how that condition

is related to a specific standard.

• Condition – The state of an item or component compared to a known standard.

• Standard – A specified rule or measure that is used to find the condition of a component.

• Damage – Physical deterioration of a component.

• Inspection – A procedure that includes checking, inspecting, and examining a system or

component.

• Scheduled Inspection – An inspection procedure that must occur at a specified calendar

interval or at specified operational time intervals. Scheduled Inspections are required to

help ensure the rotorcraft stays airworthy.

• Maintenance – The servicing and / or repair of a rotorcraft, a system, or a component that

keeps it serviceable.

• Security – Term used for inspection of hardware and components to make sure they are

properly attached and tightened.

Acronyms

FOV-

Field of View

ICA-

Instructions for Continued Airworthiness

PFD-

Primary Flight Display

MFD-

Multifunction Display

VOM-

Volt Ohm Meter

GDC-

Garmin Data Computer

GRS-

GSU-

Garmin Reference System

Garmin Sensing Unit

GMU-

Garmin Magnetometer Unit

GDU-

Garmin Display Unit

OAT-

Outside Air Temperature

GTP-

Garmin Temperature Probe

ADC-

Air Data Computer

STC-

Supplemental Type Certificate

AHRS-

Attitude Heading Reference System

ADAHRS

Air Data and Attitude Heading Reference System

05-20-10

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 7 of 51

Section 05-20-10 Continued Airworthiness Scheduled Inspections

1. General

This section contains requirements for scheduled inspections and a list of special tools required

to perform these inspections. If any part of the installation appears to be functioning

improperly, consult the troubleshooting guide. If a major component is damaged or continues

to malfunction, the component in question should be returned to the manufacturer for

replacement.

2. Scheduled Inspection Program

The G500H system requires scheduled inspections to maintain continued airworthiness. Every

effort should be made to perform the inspections with the aircraft placed in a clean, well-lit

environment. There are four different scheduled inspections of the G500H system.

a) 90 Day Inspection

The 90 day inspection is performed every 90-day period of calendar elapsed time, regardless

of hours of operation. The requirements of the 90-day inspection are specified in Table 5-1.

b) 1 Year (Annual) Inspection

The 1 year (annual) inspection is performed every 1 year period of calendar elapsed time,

regardless of hours of operation. The requirements of the 1 year (annual) inspection are

specified in Table 5-2.

c) 5 Year Inspection

The 5 year inspection is performed every 5 year period of calendar elapsed time, regardless

of hours of operation. The requirements of the 5 year inspection are specified in Table 5-3.

d) 10 Year / 2000 Flight Hours

The 10 year /2000 Flight Hour inspection is performed at a 10 year period of calendar elapsed

time, or at 2000 flight hours of operation, whichever occurs first. The requirements of the 10

year/2000 flight hour inspection are specified in Table 5-4.

05-20-10

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 8 of 51

3. Tools and Special Tools for Scheduled Inspection

Adjustable ball swivel mirror and bright flashlight and / or drop light are standard requirements

for doing inspections, although they are not necessarily considered special tools. These items

should be used freely and frequently to enhance inspection quality and help ensure

discrepancies are not missed. It is important to have adequate lighting for all phases of the

inspection.

The special tools necessary for the G500H inspection are listed as follows:

a) Milliohm meter with an accuracy of ± 0.1 milliohms or better (for electrical bonding

testing).

Table 5-1. 90-Day Inspection

Registration No.

Serial No.

Helicopter Total Hours

90 Day Scheduled Inspection

• The 90 Day Inspection shall be accomplished at least at an interval of once every 90 days of

elapsed calendar time.

• Initial each item after accomplishing the inspection.

• Record all findings and attach a copy of findings to this inspection form.

• After correction of all findings, make maintenance record entry.

90 Day Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives.

90 Day Inspection

Requirement

Initial

GDC 72H ADC, or GSU 75H ADAHRS

1. Access the GDC 72H / GSU 75H (reference Section 06-00-00 Dimensions and Access).

Drain the pitot-static system by removing the safety wire, nut and plug.

2. Re-install the plug, nut and safety wire.

3. Reference Section 12-10-00 Return-to-Service Practices for the air data unit.

05-20-10

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 9 of 51

Table 5-2. 1 year (Annual) Inspection

Registration No.

Serial No.

Helicopter Total Hours

1 Year (Annual) Scheduled Inspection

• The 1 Year inspection shall be accomplished at least at an interval of once every year of elapsed

calendar time.

• Initial each item after accomplishing the inspection.

• Record all findings and attach a copy of findings to this inspection form.

• After all findings are corrected, make maintenance record entry.

1 year (Annual) Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives.

1 year (Annual) Inspection

Requirement

Initial

GRS 79H AHRS, or GSU 75H ADAHRS

1. Access the GRS 79H / GSU 75H (reference Section 06-00-00 Dimensions and Access).

Inspect unit and mount for physical damage cracks, and corrosion. Treat and repair

corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

2. Conduct visual inspection of wires, backshells, and connectors looking for signs of wear,

deterioration or damage. Replace as required.

3. Inspect harness connections in back of unit. Secure any loose connections and support

unsecure wiring harness with additional clamping and / or tie rap supports if required.

4. Inspect unit for security of attachment. Replace the damaged or corroded hardware.

Replace any missing hardware. Torque all screws in accordance with Section 20-10-00

Torques Maintenance Practices.

Shelf Installation

1. Access Shelf Installation (reference Section 06-00-00 Dimensions and Access). Inspect

for physical damage cracks, and corrosion. Treat and repair corrosion as required in

Section 20-40-00 Corrosion Control Maintenance Practices.

2. Inspect hardware. Replace the damaged or corroded hardware. Replace any missing

hardware. Torque all screws in accordance with Section 20-10-00 Torques Maintenance

Practices.

GDC 72H ADC, or GSU 75H ADAHRS Installation

1. Access the GDC 72H / GSU 75H (reference Section 06-00-00 Dimensions and Access).

Inspect unit and mount for physical damage cracks, and corrosion. Treat and repair

corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

2. Inspect unit for security of attachment. Replace the damaged or corroded hardware.

Replace any missing hardware. Torque all screws in accordance with Section 20-10-00

Torques Maintenance Practices.

05-20-10

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 10 of 51

3. Conduct visual inspection of wires, backshells, and connectors looking for signs of wear,

deterioration or damage. Replace as required.

4. Inspect harness connections in back of unit. Secure any loose connections and support

unsecure wiring harness with additional clamping and / or tie rap supports if required.

5. Inspect Pitot-Static System for damage. Replace parts as needed. Complete the 90 Day

Inspection found in Table 5-1.

Table 5-3. -5 Year Inspection

Registration No.

Serial No.

Helicopter Total Hours

5 Year Scheduled Inspection

• The 5 Year Inspection shall be accomplished at least at an interval of once every 5 years of

elapsed calendar time.

• Initial each item after accomplishing the inspection.

• Record all findings and attach a copy of findings to this inspection form.

• After correction of all findings, make maintenance record entry.

5 Year Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives.

5 Year Inspection

Requirement

Initial

GRS 79H AHRS, or GSU 75H ADAHRS

1. The AHRS / ADAHRS unit utilizes an Earth magnetic field model which is updated once

every five years as part of the Aviation Database maintained by the owner/operator. If the

magnetic model is not current, the unit will issue an alert upon startup indicating the model

has expired. The model can be updated by inserting an aviation database card with an

updated IGRF model and powering on the system. A prompt will direct the user to press

ENT to update the model.

05-20-10

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 11 of 51

Table 5-4. 10 Year/2000 Flight Hour Inspection

Registration No.

Serial No.

Helicopter Total Hours

10 Year/ 2000 Flight Hour Scheduled Inspection

• The 10 Year/ 2000 Flight Hour Inspection shall be accomplished at least at an interval of once

every 10 years of elapsed calendar time or 2000 Flight Hours, whichever occurs first.

• Initial each item after accomplishing the inspection.

• Record all findings and attach a copy of findings to this inspection form.

• After correction of all findings, make maintenance record entry.

10 Year/2000 Flight Hour Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives.

10 Year/2000 Flight Hour Inspection

Requirement

Initial

GRS 79H AHRS, or GSU 75H ADAHRS

1. Access GRS 79H / GSU 75H, (Reference Section 06-00-00 Dimensions and Access) and

disconnect all harness connectors.

2. Measure the resistance between the GRS 79H / GSU 75H and a nearby exposed portion

of aircraft main metallic structure like a keel beam (not to other installed equipment or

shelves). Verify that the resistance is less than or equal to 5 milliohms for GRS 79H or GSU

75H. If greater must be restored to the value specified in the G500H Installation Manual

Addendum for GRS 79H or GSU 75H.

3. Reconnect all disconnected harness connectors and ensure they are secure.

GDC 72H ADC, or GSU 75H ADAHRS

1. Access GDC 72H / GSU 75H, (Reference Section 06-00-00 Dimensions and Access) and

disconnect all harness connectors.

2. Measure the resistance between the GDC 72H / GSU 75H and a nearby exposed portion

of aircraft main metallic structure like a keel beam (not to other installed equipment or

shelves). Verify that the resistance is less than or equal to 5 milliohms. If greater must be

restored to the value specified in the G500H Installation Manual Addendum for GDC 72H or

GSU 75H.

3. Reconnect all disconnected harness connectors and ensure they are secure

4. Post Inspection Maintenance Practices

After completion of the 1 Year (Annual) Inspection, 5 Year Inspection and 10 Year/2000 Flight

Hour Inspection and all discrepancies found have been corrected, the Return-to-Service

Practices (Reference Section 12-10-00 Return-to-Service Practices) should be accomplished in

preparation for returning the rotorcraft to service

05-20-20

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 12 of 51

Section 05-20-20 Continued Airworthiness Special Inspections

1. General

This section contains requirements for special inspections and includes the list of special tools

required to perform these inspections. If any part of the installation appears to be functioning

improperly, consult the troubleshooting guide. If a major component is damaged or continues

to malfunction, the component in question should be returned to the manufacturer for

replacement.

2. Special Inspection Program

Conditions may arise from incidents or accidents that may warrant additional inspection requirements.

A Special Inspection is required if the aircraft is involved in a hard landing or is subjected to total

immersion in water. If either of these conditions occurs, the G500H system must be inspected following

the Annual Inspection Procedures detailed in Table 5-2.

3. Tools and Special Tools for Special Inspections

Adjustable ball swivel mirror and bright flashlight and / or drop light are standard requirements

for doing inspections, although these may not necessarily be considered special tools. These

items should be used freely and frequently to enhance inspection quality and help ensure

discrepancies are not missed. It is important to have adequate lighting for all phases of the

inspection.

The special tools necessary for the G500H inspection are listed as follows:

a) Milliohm meter with an accuracy of ± 0.1 milliohms or better (for electrical bonding

testing).

06-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 13 of 51

CHAPTER 6

Section 06-00-00 Dimensions and Access

1. Access Methods

For removal and installation of specific components, reference Section 31-00-00 Instruments,

Removal and Replacement.

Caution: Use of power tools during removal or installation of

panels and attaching hardware may damage nut plates or

deform holes in composite doors, covers, panels, and fairings.

a) GDC 72H Air Data Computer

GDC 72H is located underneath the cabin floor between station 1790 and 2325 on the left or

right side of the aircraft depending on aircraft configuration. (Figure 6-1)

Refer to Figure 6-3 for location of GDC 72H if installed on a 115-01761-00 Remote LRU Shelf

(applicable to AS 350 B2, B3 models only).

Figure 6-1

Access Removal and Installation Methods

i. Removal

1. Remove the Center lower belly access panel.

2. Disconnect the retaining straps that prevent the panel from falling to the floor.

3. If aftermarket items are attached to the Center lower belly panel it may be

necessary to remove or disconnect them in order to remove the lower belly panel.

Consult the manufacturers Installation and Removal instructions for proper

removal of items.

ii. Installation

1. Re-install aftermarket items if removed to gain access to the air data computer.

Consult the manufacturers Installation and Removal instructions for proper

installation of items.

2. Connect the retaining strap that was disconnected to gain access to the air data

computer.

GDC 72H

STA

2325

REF

STA

1790

REF

06-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 14 of 51

3. Close the Center lower belly access panel and secure it.

b) GRS 79H AHRS

GRS 79H is located underneath the cabin floor between station 1790 and 2325 on the left or

right side of the aircraft depending on aircraft configuration. (Figure 6-2)

Refer to Figure 6-3 for location of GRS 79H if installed on a 115-01761-00 Remote LRU Shelf

(applicable to AS 350 B2, B3 models only).

Figure 6-2

Access Removal and Installation Methods

i. Removal

1. Remove the Center lower belly access panel.

2. Disconnect the retaining straps that prevent the panel from falling to the floor.

3. If aftermarket items are attached to the Center lower belly panel it may be

necessary to remove or disconnect them in order to remove the lower belly panel.

Consult the manufacturers Installation and Removal instructions for proper

removal of items.

ii. Installation

1. Re-install aftermarket items if removed to gain access to the air data computer.

Consult the manufacturers Installation and Removal instructions for proper

installation of items.

2. Connect the retaining strap that was disconnected to gain access to the air data

computer.

3. Close the Center lower belly access panel and secure it.

GRS 79H

STA

2325

REF

STA

1790

REF

06-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 15 of 51

Figure 6-3

06-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 16 of 51

c) GSU 75H ADAHRS

GSU 75H is located underneath the cabin floor between station 1790 and 2325 on the left side

of the aircraft. (Figure 6-4) Installation on 115-01761-00 Remote LRU Shelf is applicable to AS

350 B2, B3 models only.

Figure 6-4

Access Removal and Installation Methods

i. Removal

1. Remove the Center lower belly access panel.

2. Disconnect the retaining straps that prevent the panel from falling to the floor.

3. If aftermarket items are attached to the Center lower belly panel it may be

necessary to remove or disconnect them in order to remove the lower belly panel.

Consult the manufacturers Installation and Removal instructions for proper

removal of items.

ii. Installation

1. Re-install aftermarket items if removed to gain access to the ADAHRS computer.

Consult the manufacturers Installation and Removal instructions for proper

installation of items.

2. Connect the retaining strap that was disconnected to gain access to the air data

computer.

06-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 17 of 51

3. Close the Center lower belly access panel and secure it.

d) Shelf Installations

The shelf is located underneath the cabin floor between station 1790 and 2325 on the left

or right side of the aircraft depending on aircraft configuration. (Figure 6-5) GDC 72H / GRS

79H / GSU 75H are installed on the shelf.

Figure 6-5

Access Removal and Installation Methods

i. Removal

1. Remove the Center lower belly access panel.

2. Disconnect the retaining straps that prevent the panel from falling to the floor.

3. If aftermarket items are attached to the Center lower belly panel it may be

necessary to remove or disconnect them in order to remove the lower belly panel.

Consult the manufacturers Installation and Removal instructions for proper

removal of items.

ii. Installation

1. Re-install aftermarket items if removed to gain access to the air data computer.

Consult the manufacturers Installation and Removal instructions for proper

installation of items.

2. Connect the retaining strap that was disconnected to gain access to the air data

computer.

3. Close the Center lower belly access panel and secure it.

Shelf

Installatio

STA

2325

REF

STA

1790

REF

08-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 18 of 51

CHAPTER 8

Section 8-00-00 Weight and Balance Information

Drawing/Part No.

Description

Weight

CG Location (1)

115-01761-00

Shelf, Remote LRU (2)

0.55 lbs

(1)

190-01150-07

GDC 72H ADC

1.71 lbs

(1)

190-01150-07

GRS 79H AHRS

1.45 lbs

(1)

190-01150-07

GSU 75H ADAHRS

1.72 lbs

(1)

Note 1: Location of the GDC 72H, GRS 79H and GSU 75H can vary as described in the

190-01150-07 G500H STC Installation Manual Addendum.

Note 2: 115-01761-00 Remote LRU Shelf is applicable to AS 350 B2, B3 models only

12-00-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 19 of 51

CHAPTER 12

Section 12-00-00 Servicing Maintenance Practices

This chapter includes Return-to-Service Practices and Calibration Practices to be used with the G500H

Flight Display System.

a) GDU 620 cooling fan replacement

Over time, the GDU cooling fans may degrade in performance and need to be replaced in order

to continue adequately cooling the display system.

To replace the cooling fans, follow the replacement procedure below.

NOTE

The GDU cooling fan replacement kit (P/N K00-00683-10) must be obtained

from an authorized Garmin dealer. In order for the GDU warranty to remain

valid, this procedure must be accomplished by an authorized Garmin dealer.

1. Removal

a. Place the GDU 620 on a flat surface with the fan cover plate assembly facing up

b. Remove and discard the six Torx

screws with a T10 driver.

c. Lift fan cover assembly and disconnect fan connectors. Set aside.

2. Installation

a. Place replacement fan cover assembly over unit.

b. Connect both fan connectors, noting plate orientation to match recess in unit. Ensure

connectors are fully engaged.

c. Lower fan cover assembly into place while being careful to not pinch fan wires.

d. Secure fan cover assembly with six provided Torx® screws. Torque each screw to 8 in-lbs,

+/- 1 in-lb.

3. Return to Service

a. After removing and reinstalling the GDU 620 cooling fans, the return-to-service checks

must be performed (reference Section 12-10-00 Return-to-Service Practices).

12-10-00

Instructions for Continued Airworthiness 190-01150-22 Rev 1

for the Garmin G500H System in Airbus AS350 and EC130 Page 20 of 51

Section 12-10-00 Return-to-Service Practices

a) GDC 72H, or GSU 75H

1. Power up the G500H system with the GDU 620 in normal mode.

2. Verify that the GDU displays valid air data within approximately one minute.

3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Section

31-00-00 Troubleshooting .

4. Drain pitot-static system (reference Table 5-1 90 Day Inspection)

5. Perform a leak check of the pitot-static system and observe the airspeed, altitude, and vertical

speed for proper operation.

b) GRS 79H, or GSU 75H

1. Power up the G500H system with the GDU 620 in normal mode.

2. Verify that the GDU displays valid heading and attitude within approximately one minute. Note

that heading can remain invalid if the magnetometer is near a large metal structure such as a

hangar wall or if the magnetometer is close to a large ground power cart.

3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Section

31-00-00 Troubleshooting .

c) GDU 620 Cooling Fans

After removing and reinstalling the GDU cooling fans, the following return-to-service checks should

be performed.

1. Power up the G500H system with the GDU 620 in normal mode.

2. Verify that the newly-installed cooling fans are operating correctly.

3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Section

31-00-00 Troubleshooting .

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Garmin G500H Operating instructions

Garmin G500H Operating instructions

Garmin G500H Operating instructions

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