Garmin AS-350B2, AS-350B3 Instruction Manual

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Page 1

Rev.

Date

Description of Change

2/14/2014

Initial release.

Confidential

This drawing and the specifications contained herein

written permission.

Instructions for Continued Airworthiness

for the Garmin G500H Installa t ion in Eurocopter AS350

Garmin Ltd. Or its subsidiaries

c/o Garmin International, Inc.

1200 E. 151st Street

Olathe, Kansas 66062 USA

Dwg. Number:

190-00792-12 Rev. 1

Note: Document was RSG P/N 16E06310001 Re v. A

are the property of Garmin Ltd. or its subsidiaries and may not be reproduced or used in whole or in part as the basis for manufacture or sale of products without

Page 2

Table of Contents

Section 01-00-00

Introduction ......................................................................................................... 4

CHAPTER 4 .................................................................................................................................. 5

Section 04-00-00

Airworthiness Limitations .................................................................................. 5

CHAPTER 5 .................................................................................................................................. 6

Section 05-00-00

Continued Airworthiness Inspections ................................................................ 6

Section 05-20-10

Continued Airworthiness Scheduled Inspections .............................................. 9

Section 05-20-20

Continued Airworthiness Special Inspections ................................................... 17

CHAPTER 6 .................................................................................................................................. 19

Section 06-00-00

Dimensions and Access ....................................................................................... 19

CHAPTER 8 .................................................................................................................................. 26

Section 8-00-00

Weight and Balance Information ........................................................................ 26

CHAPTER 12 ................................................................................................................................ 27

Section 12-00-00

Servicing Maintenance Practices ........................................................................ 27

Section 12-10-00

Return-to-Service Practices ................................................................................ 28

Section 12-20-00

Calibration Requirements ................................................................................... 29

CHAPTER 20 ................................................................................................................................ 30

Section 20-00-00

Standard Practices ............................................................................................... 30

Section 20-10-00

Torques Maintenance Practices .......................................................................... 31

Section 20-30-00

Painting Maintenance Practices .......................................................................... 35

Section 20-40-00

Corrosion Control Maintenance Practices .......................................................... 36

Section 20-50-00

Mechanical Fastener Sealing Methods ................................................................ 39

Section 20-90-00

Dye Penetrant Inspection Methods ..................................................................... 40

CHAPTER 31 ................................................................................................................................ 41

Section 31-00-00

Instruments ......................................................................................................... 41

Section 98-00-00

Wiring Diagrams and Pitot-Static System Schematics ....................................... 71

Section 98-10-00

Wiring Diagrams .................................................................................................. 72

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Section 98-20-00

Pitot-Static System Schematic ............................................................................. 80

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CHAPTER 1

Section 01-00-00 Introduction

These are accepted Instructions for Continued Airworthiness for modifications performed in accordance with Eurocopter AS350 Garmin G500H Flight Display System Installation STC. All references to the G500H in this document will refer to the Garmin G500H Flight Display System Installation and other related components specified in these Instructions for Continued Airworthiness (ICA). A STC permission letter and Instructions for Continued Airworthiness (ICA) should be supplied to the owner/operator of the STC at the time of completion. Subsequent accepted changes to the ICA will be distributed to owners and operators of the STC.

This, Instructions for Continued Airworthiness, is intended to supplement the Model AS350 rotorcraft maintenance manuals provided by Eurocopter. The information, procedures, requirements, and limitations contained in this, Instructions for Continued Airworthiness, for this type design change supersedes the information, procedures, requirements, and limitations contained in the rotorcraft’s maintenance manual when the type design change is installed on the Type Certificate Holder’s rotorcraft.

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CHAPTER 4

Section 04-00-00 Airworthiness Limitations

There are no additional Airworthiness Limitations as defined in 14 CFR Part 27, Appendix A. A27.4 that result from this modification. The Airworthiness Limitations section is FAA approved and specifies inspections and other maintenance required under 14 CFR §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.

04-00-00

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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 5-01.

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 5-02.

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 5-03.

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 5-04.

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 5-02.

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The G500H Installation has a Post-Lightning Strike Inspection that must be performed in the

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-

Garmin Reference System

GMU-

Garmin Magnetometer Unit

GDU-

Garmin Display Unit

event of a suspected or actual lightning strike to the aircraft. The Post-Lightning Strike Inspection requirements are specified in Table 5-05.

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

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05-00-00

Page 8

OAT-

Outside Air Temperature

GTP-

Garmin Temperature Probe

ADC-

Air Data Computer

STC-

Supplemental Type Certificate

AHRS-

Attitude Heading Reference System

05-00-00

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Section 05-20-10 Continued Airworthiness Scheduled Inspections

1. General

This section contains requirements for scheduled inspections. Also included is a list of special tools required to perform the scheduled 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 Installation requires scheduled inspections in order 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 required for the G500H Installation.

a) 90 Day Inspection

The 90 day inspection is required to be performed every 90 day period of calendar elapsed time, regardless of hours of operation. Inspection Table 5-01 specifies the requirements of the 90 day inspection.

b) 1 Year (Annual) Inspection

The 1 year (annual) inspection is required to be performed every 1 year period of calendar elapsed time, regardless of hours of operation. Inspection Table 5-02 specifies the requirements of the 1 year (annual) inspection.

c) 5 Year Inspection

The 5 year inspection is required to be performed every 5 year period of calendar elapsed time, regardless of hours of operation. Inspection Table 5-03 specifies the requirements of the 5 year inspection

d) 10 Year / 2000 Flight Hours

The 10 year /2000 Flight Hour inspection is required to be performed at a 10 year period of calendar elapsed time, or at 2000 flight hours of operation, whichever occurs first. Inspection Table 5-04 specifies the requirements of the 10 year/2000 flight hour inspection.

3. Tools and Special Tools for Scheduled Inspection

Although not necessarily considered special tools, the adjustable ball swivel mirror and bright flashlight and / or drop light are standard requirements for doing inspections. These items should be used freely and frequently to enhance inspection quality and help ensure

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

Registration No.

Serial No.

Helicopter Total Hours

90 Day Scheduled Inspection

90 Day Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives.

90 Day Inspection

Requirement

Initial

GDC 74H ADC

1. Access GDC 74H (reference Section 6-00-00- Dimensions and Access). Drain the pitot-

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

3. Reference Section 12-10-00 Return-to-Service Practices for the GDC 74H

inspection

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

a) Milliohm meter (for electrical bonding testing).

• 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.

Table 5-01 -90 Day Inspection

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

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Table 5-02 -1 year (Annual) Inspection

Registration No.

Serial No.

Helicopter Total Hours

1 Year (Annual) Scheduled Inspection

1 year (Annual) Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives. 1 year (Annual) Inspection

Requirement

Initial

1. Locate GDU 620 (reference Section 6-00-00 Access and Dimension). Inspect all knobs

2. Inspect instrument panel for damage, corrosion, and security. If damaged, replace

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

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

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

1. Access GRS 77H (reference Section 6-00-00- Dimensions and Access). Inspect AHRS and

• 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 correction of all findings, make maintenance record entry.

GDU 620

and buttons for legibility.

damaged or cracked Instrument panel. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices. Tighten any loose hardware to values listed in Section 20-10-00.

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

deterioration or damage. Replace as required.

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

GRS 77H AHRS

mount for physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

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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

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

1. Access GMU 44 (reference Section 6-00-00- Dimensions and Access). Inspect GMU 44

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

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

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

1. Access Shelf Installation (reference Section 6-00-00- Dimensions and Access). Inspect for

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

1. Access GDC 74H (reference Section 6-00-00- Dimensions and Access). Inspect GDC 74H

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

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

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

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

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

GMU 44 Magnetometer Installation

and mount for physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

deterioration or damage. Replace as required.

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

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

Shelf Installation

physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 2040-00 Corrosion Control Maintenance Practices

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

GDC 74H ADC Installation

and mount for physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

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

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

Inspection found in Table 5-01.

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GTP 59 OAT Probe Installation

1. Access GTP 59 OAT Probe (reference Section 6-00-00- Dimensions and Access). Inspect and repair

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

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

1. Access Terminal Block Installation (reference Section 6-00-00- Dimensions and Access).

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

GTP 59 OAT and mount for physical damage cracks, and corrosion. Treat corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

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

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

Terminal Block Installation

Inspect installation for physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.

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

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Table 5-03 -5 Year Inspection

Registration No.

Serial No.

Helicopter Total Hours

5 Year Scheduled Inspection

5 Year Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives.

5 Year Inspection

Requirement

Initial

GRS 77H AHRS

1. The GRS 77 utilizes an Earth magnetic field model which is updated once every five years

• 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.

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.

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Table 5-04 -10 Year/2000 Flight Hour Inspection

Registration No.

Serial No.

Helicopter Total Hours

10 Year/ 2000 Flight Hour Scheduled Inspection

10 Year/2000 Flight Hour Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives. 10 Year/2000 Flight Hour Inspection

Requirement

Initial

GRS 77H AHRS

1. Access GRS 77H, (Reference Section 6-00-00 Dimensions and Access) and disconnect all

2. Measure the resistance between the GRS 77H and a nearby exposed portion of aircraft

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

GDU 620

4. Access GDU 620, (Reference Section 6-00-00 Dimensions and Access) and disconnect all

5. Measure the resistance between the GDU 620 and a nearby exposed portion of aircraft

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

• 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.

harness connectors.

metallic structure. Verify that the resistance is less than or equal to 20 milliohms. If greater must be restored to the value specified in the G500H STC Installation Manual.

harness connectors.

metallic structure. Verify that the resistance is less than or equal to 40 milliohms. If greater must be restored to the value specified in the G500H STC Installation Manual.

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GDC 74H ADC

7. Access GDC 74H, (Reference Section 6-00-00 Dimensions and Access) and disconnect all

harness connectors.

8. Measure the resistance between the GDC 74H and a nearby exposed portion of aircraft

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

GMU 44

10. Access GMU 44, (Reference Section 6-00-00 Dimensions and Access) and disconnect all

11. Measure the resistance between the GMU 44 and a nearby exposed portion of aircraft

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

GTP 59

13. Access GTP 59, (Reference Section 6-00-00 Dimensions and Access) and disconnect all

14. Measure the resistance between the GTP 59 and a nearby exposed portion of aircraft

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

metallic structure. Verify that the resistance is less than or equal to 20 milliohms. If greater must be restored to the value specified in the G500H STC Installation Manual.

harness connectors.

metallic structure. Verify that the resistance is less than or equal to 20 milliohms. If greater must be restored to the value specified in the G500H STC Installation Manual.

harness connectors.

metallic structure. Verify that the resistance is less than or equal to 5 milliohms. If greater must be restored to the value specified in the G500H STC Installation Manual.

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 12-00-00 Return-to-Service Practices) should be accomplished in preparation for returning the rotorcraft to service

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Section 05-20-20 Continued Airworthiness Special Inspections

1. General

This section contains requirements for special inspections. Also included is a list of special tools

required to perform the scheduled 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

The G500H Installation has a Post-Lightning Strike Inspection that must be performed in the event of a suspected or actual lightning strike to the aircraft. The Post-Lightning Strike Inspection requirements are specified in Table 5-05.

3. Tools and Special Tools for Special Inspections

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

a) Milliohm meter (for electrical bonding testing).

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Table 5-05 -Post-Lightning Strike Inspection

Registration No.

Serial No.

Helicopter Total Hours

Post-Lightning Strike Inspection

Post-Lightning Strike Pre-inspection

Requirement

Initial

1. Review Airworthiness Directives. Post-Lightning Strike Inspection

Requirement

Initial

GTP 59 OAT Probe Installation

1. Access the GTP 59 OAT Probe Installation. Reference Section 6-00-00 Dimensions and

2. Inspect the probe and the doubler (P/N: 115-01812-00) for signs of structural damage. If

Post-Lightning Strike Post- Inspection

Requirement

Initial

1. Verify that the OAT is displayed on the GDU 620 PFD normally.

• The Post-Lightning Strike Inspection shall be accomplished in the event of a suspected or actual

lightning strike to the aircraft.

• 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.

Access.

there are visible signs of damage, replace the parts as needed.

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CHAPTER 6

Figure 6-01

REF

GMU 44

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

a) GMU 44, Magnetometer

Magnetometer is located in the tail boom between TB 868 and 1578. (Figure 6-01)

868

1578

Access Removal and Installation Methods

i. Removal

1. Un-latch and open the baggage compartment door on the left side of the aircraft.

2. Remove the tail boom closeout panel by loosening the ¼ turn fasteners that hold it

in place.

3. If an air conditioner is installed it may be necessary to remove the air conditioner

unit to gain access to the magnetometer. Consult the manufacturers Installation and removal instructions for proper removal of unit.

ii. Installation

1. Re-install air conditioner if removed to gain access to the magnetometer. Consult

the manufacturers Installation and Removal instructions for proper installation of unit.

2. Re-install tail boom closeout panel by tightening the ¼ turn fasteners that hold it in

place.

3. Close the baggage compartment door and latch it.

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.

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b) GDC 74H, Air Data Computer

Figure 6-02

GDC 74H

STA

REF

STA

REF

GDC 74H 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 6-02)

2325

1790

Access Removal and Installation Methods

i. Removal

1. Un-latch 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 latch it.

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.

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c) GRS 77H, AHRS

Figure 6-03

GRS 77H

STA

GRS 77H 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 6-03)

2325

REF

1790

REF

Access Removal and Installation Methods

i. Removal

1. Un-screw 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 attach screws.

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.

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d) Shelf Installation

Figure 6-04

Shelf

STA

The shelf installation 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 6-04)

Access Removal and Installation Methods

i. Removal

1. Un-screw 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 attach screws.

2325

1790

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.

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e) Terminal Block Installation

Figure 6-05

Terminal Block

STA

Terminal Block is located underneath the cabin floor between station 1120 and 1502 on the left side of the aircraft. (Figure 6-05)

1120

REF

1502

REF

Access Removal and Installation Methods

i. Removal

1. Un-latch 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 latch it.

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.

06-00-00

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f) GTP 59 OAT Probe Installation

Figure 6-06

GTP 59

STA

REF

STA

REF

The GTP 59 OAT Probe is located on the existing belly panel between station 2437 and

2351. (Figure 6-06)

2351

2437

Access Removal and Installation Methods

i. Removal

1. Un-latch the Center lower belly access panel.

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

3. If other 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 any other 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 latch it.

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

06-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 24 of 80

Page 25

g) GDU 620 Installation

Figure 6-07

GDU 620

The GDU 620 is located in the right hand side of the instrument panel (Reference Section 31-00-00 Instruments, Figures 31-08 through 31-11 for specific location based on installation configuration).

Access Removal and Installation Methods

i. Removal

1. Un-screw the screws on the front of the instrument panel.

2. For items that are attached to the instrument panel it may be necessary to remove

or disconnect them in order to remove the instrument panel. Consult the manufacturers Installation and Removal instructions for proper removal of items.

ii. Installation

1. Re-install items if removed or disconnected to remove the instrument panel.

Consult the manufacturers Installation and Removal instructions for proper installation of items.

2. Re-install screw on front of instrument panel.

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.

06-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 25 of 80

Page 26

CHAPTER 8

Installation #

Description

Weight

CG Location

01E06310002-01

GMU 44 Magnetometer

0.70 lbs

TB 1215, WL -2225, BL 0.0

01E06310003-01

RH Shelf

2.20 lbs

STA 2042, WL -2781, BL 600.7

01E06310003-02

LH Shelf

2.20 lbs

STA 2042, WL -2781, BL -600.7

01E06310004-01

GDC 74H

1.92 lbs

STA 2003, WL -2745, BL 662.0

01E06310004-02

GDC 74H

1.92 lbs

STA 2003, WL -2745, BL -662.0

01E06310005-01

GRS 77H AHRS

3.46 lbs

STA 2019, WL -2748, BL 572.0

01E06310005-02

GRS 77H AHRS

3.46 lbs

STA 2019, WL -2748, BL -572.0

01E06310008-01

Terminal Block

0.47 lbs

STA 1265, WL -2659, BL -612.2

01E06310009-01

GTP 59 OAT Probe

0.08 lbs

STA 2386, WL -2910, BL 7.2

01E06310014-01

Instrument Panel

47.80 lbs

STA 1120, WL -2066, BL 0.0

01E06310014-02

Instrument Panel

47.80 lbs

STA 1120, WL -2066, BL 0.0

01E06310014-03

Instrument Panel

47.80 lbs

STA 1120, WL -2066, BL 0.0

01E06310014-04

Instrument Panel

47.80 lbs

STA 1120, WL -2066, BL 0.0

Section 8-00-00 Weight and Balance Information

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 26 of 80

08-00-00

Page 27

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 Installation.

12-00-00

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Page 28

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

1. General

a) GMU 44 Magnetometer

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

2. Verify that the GDU displays valid heading 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.

GDC 74H

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 5-01 90 Day Inspection)

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

speed for proper operation.

GRS 77H

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.

d) GDU 620

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

2. Verify that there are no red-Xs and that no alerts are present. If red Xs or alerts are present,

troubleshoot using Section 31-00-00 Troubleshooting.

12-10-00

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Page 29

Calibrations Required

Engine Run-up

Manual

GRS 77H AHRS was removed and/or

GRS 77H AHRS Configuration Module

Section 12-20-00 Calibration Requirements

Condition

replaced. The mounting tray was NOT removed and the mounting tray bolts were NOT loosened.

replaced. The mounting tray WAS removed and/or mounting tray bolts WERE loosened.

was replaced.

GRS 77H

Pitch/Roll

Offset

See Section 5 of the G500H STC Installation Manual

X X X

GRS/GMU

Magnetic

Calibration

See Section 5

of the G500H STC

Installation Manual

None Required.

Vibration

Test

See Section 5

of the G500H

STC Installation

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 29 of 80

12-20-00

Page 30

CHAPTER 20

Section 20-00-00 Standard Practices

This chapter contains maintenance information and procedures that are common standard practices used on the G500H installation. Information contained in this chapter is standard torque charts and application procedures, corrosion prevention, painting, mechanical fastener sealing, and dye penetrant inspection techniques.

20-00-00

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Page 31

Section 20-10-00 Torques Maintenance Practices

1. Torque Wrenches

a) Torque Wrench Accuracy

Torque wrenches must be of good quality and calibrated at least once a year. Any torque wrench that has been dropped or abused should be calibrated to ensure continued accuracy.

b) Application of Torque Wrench Loads

(1) Be sure the bolt and nut and the surface they bear on are clean and dry, unless otherwise

specified by the manufacturer.

(2) Run the nut down to near contact with the washer or bearing surface and check the friction

drag torque required to turn the nut. Add the friction drag torque to the desired torque to arrive at the “final torque” to be registered on the torque wrench indicator.

(3) Whenever possible, apply the torque to the nut instead of the bolt. This will reduce

rotation of the bolt in the hole and reduce wear.

(4) Apply a smooth even pull when applying torque pressure. (5) If special adapters are used which will change the effective length of the torque wrench,

the final torque indication or wrench setting must be adjusted accordingly. To determine the torque wrench setting or indication with adapter installed reference Figure 20-01.

20-10-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 31 of 80

Page 32

Figure 20-01

20-10-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 32 of 80

Page 33

2. Torque Wrenches

Thread Size

Shear

Tension

Recommended

in-lb (N m)

Maximum

in-lb (N m)

Recommended

in-lb (N m)

Maximum

in-lb (N m)

8-36

7-9

12-15

10-32

12-15

20-25

¼-28

30-40

50-70

100

5/16-24

60-85

140

100-140

225

3/8-24

(0.3750-24)

95-110

(10.73-12.42)

240

(27.11)

160-190

(18.07-21.46)

390

(44.05)

7/16-20

270-300

500

450-500

840

½-20

290-410

660

480-690

1,100

9/16-18

480-600

960

800-1,000

1,600

5/8-18

660-780

1,400

1,100-1,300

2,400

¾-16

1,300-1,500

3,000

2,300-2,500

5,000

7/8-14

(0.8750-14)

1,500-1,800

(169.44-203.32)

4,200

(474.43)

2,500-3,000

(282.40-338-88)

7,000

(790.72)

1-12

(1.0000-12)

2,200-3,300

(248.51-372.76)

6,000

(677.76)

3,700-5,500

(417.95-621.28)

10,000

(1129.6)

1-1/8-12

3,000-4,200

9,000

5,000-7,000

15,000

1-1/4-12

5,400-6,600

15,000

9,000-11,000

25,000

Warning: Do not exceed maximum allowable torque value. Overstressing of fastener may result.

Standard hardware torque values are given in the following tables 20-01 through table 20-03. Table 20-01 gives recommended torque values for fine thread fasteners, shear and tension applications. Table 20-02 gives recommended torque values for coarse thread fasteners, shear and tension applications. Table 20-03 gives recommended torque values for phillips head

screws.

Table 20-01- Recommended Torque Values for Fine Thread Fasteners

Fractional (decimal)

(0.1640-36)

(0.1900-32)

(0.2500-28)

(0.3125-24)

(0.4375-20)

(0.5000-20)

(0.5625-18)

(0.6250-18)

(0.7500-16)

(0.79-1.02)

(1.36-1.69)

(3.38-4.51)

(6.77-9.60)

(30.49-33.88)

(32.75-46.31)

(54.22-67.77)

(74.55-88.10)

(146.84-169.44)

(1.36)

(2.82)

(6.77)

(15.81)

(56.48)

(74.55)

(108.44)

(158.14)

(338.88)

(1.36-1.69)

(2.25-2.82)

(5.64-7.90)

(11.29-15.81)

(50.83-56.48)

(54.22-77.94)

(90.36-112.96)

(124.25-146.84)

(259.80-282.40)

(2.26)

(4.51)

(11.29)

(25.41)

(94.88)

(124.25)

(180.73)

(271.10)

(564.80)

(1.1250-12)

(1.2500-12)

(338.88-474.43)

(609.98-745.53)

(1016.6)

(1694.4)

(564.80-790.72)

(1016.6-1242.6)

(1694.4)

(2824.0)

20-10-00

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Page 34

Thread Size

Fractional (decimal)

Shear

Tension

Recommended

Maximum

Recommended

Maximum

8-32

7-9

12-15

10-24

12-15

20-25

¼-20

25-30

40-50

5/16-18

48-55

100

80-90

160

3/8-16

95-100

170

160-185

275

7/16-14

140-155

280

235-255

475

½-13

240-290

520

400-480

880

9/16-12

300-420

650

500-700

1,100

5/8-11

420-540

900

700-900

1,500

¾-10

700-950

1,500

1,150-1,600

2,500

7/8-9

1,300-1,800

2,700

2,200-3,000

4,600

1-8

(1.0000-8)

2,200-3,000

(248.51-338.88)

4,500

(508.32)

3,700-5,000

(417.95-564.80)

7,600

(858.49)

1-1/8-8

3,300-4,000

7,200

5,500-6,500

12,000

1-1/4-8

4,000-5,000

10,000

6,500-8,000

16,000

Thread Size

Recommended in-lb (N m)

Maximum in-lb (N m)

8-32 (0.1640-32

12-15 (1.36-1.69)

23 (2.59)

10-32 (0.1900-32)

20-25 (2.25-2.82)

35 (3.95)

¼-28 (0.2500-28)

60-70 (6.77-7.90)

90 (10.16)

5/16-24 (0.3125-24)

110-125 (12.42-14.12)

150 (16.94)

3/8-24 (0.3750-24)

150-175 (16.94-19.76)

225 (25.41)

7/16-20 (0.4375-20)

230-280 (25.98-31.62)

450 (50.83)

½-20 (0.5000-20)

550-650 (62.12-73.42)

850 (96.01)

9/16-18 (0.5625-18)

750-900 (84.72-101.66)

1,200 (135.55)

5/8-18 (0.6250-18)

1,100-1,300 (124.25-146.84)

1,600 (180.73)

Table 20-02. Recommended Torque Values for Coarse Thread Fasteners

in-lb (N m)

(0.1640-32)

(0.1900-24)

(0.2500-20)

(0.3125-18)

(0.3750-16)

(0.4375-14)

(0.5000-13)

(0.5625-12)

(0.6250-11)

(0.7500-10)

(0.8750-9)

(0.79-1.02 )

(1.36-1.69)

(2.82-3.38)

(5.42-6.21)

(10.73-11.29)

(15.81-17.50)

(27.11-32.75)

(33.88-47.44)

(47.44-60.99)

(79.07-107.31)

(146.84-203.32)

(1.36)

(2.37)

(5.08)

(11.29)

(19.20)

(31.62)

(58.73)

(73.42)

(101.66)

(169.44)

(474.43)

(1.36-1.69)

(2.25-2.82)

(4.51-5.64)

(9.03-10.16)

(18.07-20.89)

(26.54-28.8)

(45.18-54.22)

(56.48-79.07)

(79.07-101.66)

(129.90-180.73)

(248.51-338-88)

(2.26)

(3.95)

(8.47)

(18.07)

(31.06)

(53.65)

(99.40)

(124.25)

(169.44)

(282.40)

(519.61)

(1.1250-8)

(1.2500-8)

Fractional (decimal)

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 34 of 80

(372.76-451.84)

(451.84-564.80)

Table 20-03. Recommended Torque Values for Phillips Head Fasteners

(813.31)

(1129.6)

(621.28-734.24)

(734.24-903.68)

20-10-00

(1355.5

(1807.4 N m)

Page 35

Section 20-30-00 Painting Maintenance Practices

The following procedures should be used to touch-up paint flaking, scratches, nicks, and gouges.

Warning: Cleaning solvents and epoxy primer are flammable. Cleaning solvents, epoxy primer, and alodine can cause burns and irritation when skin is contacted. Vapors are harmful and caustic to eyes; Goggles must be worn for eye protection. Cleaning solvents and alodine are poisonous. Vapors are harmful to life or health; work should be performed with proper ventilation and / or respirators should be worn while working with Cleaning solvents, epoxy primer and alodine.

1. Paint Touch-Up of Small Areas

Use the following procedures to touch-up paint of small sanded areas and Nicks, Scratches, Gouges, Etc., that do not go through paint and primer to bare metal.

a. Wipe surface clean with trichloroethane, MIL-T-81533, or equivalent cleaning

solvent, and wipe dry immediately.

b. Apply coat of epoxy polymide primer, MIL-P-23377F or equivalent, to match

original. Feather primer coating onto surrounding color coat. Allow primer to air dry for 30 minutes.

c. Apply topcoat to match original finish.

20-30-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 35 of 80

Page 36

Section 20-40-00 Corrosion Control Maintenance Practices

1. Corrosion Control

The G500H mounting components are fabricated primarily of aluminum. All components should be inspected regularly for any signs of corrosion. The following procedures should be used for removing corrosion and treating affected areas.

2. Corrosion Removal

Remove corrosion by either chemical or mechanical means.

a) Paint Removal, Chemical

Caution: Do not use chemical paint stripper on composite materials. Chemical paint strippers can cause composite components to debond and / or loose adhesion of the epoxy matrix.

(1) Mask all non-metallic surfaces in area to be stripped as well as areas where

solution may get entrapped.

Warning: Paint stripper can cause burns and irritation when it contacts skin; proper gloves should be worn. Vapors are harmful and caustic to eyes; Goggles must be worn for eye protection. Paint stripper is poisonous. Vapors are harmful to life or health; work should be performed with proper ventilation and / or respirators should be worn while working with paint stripper.

(2) Using a fiber brush, apply sufficient paint stripper, (Turco 5873), to cover area of

removal.

Note: If paint stripper evaporates quickly or works slowly, cover area with plastic sheet.

(3) Allow paint remover to remain on surface for a time sufficient to cause wrinkling

and lifting of paint (about 10-30 minutes).

(4) Using non-metallic scraper or abrasive pads, (3M scotchbrite 63), scrub area to

further loosen paint.

(5) Re-apply paint stripper, (Turco 5873), as necessary in areas where paint remains

tightly adherent.

(6) Wash and scrub surface with demineralized water and alkaline cleaner to

neutralize paint stripper.

(7) Remove masking materials and any residual paint or stripper

20-40-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 36 of 80

Page 37

(8) Rinse with demineralized water.

b) Paint Removal, Mechanical

Caution: Do not sand into or expose composite fibers. Do not remove more material than necessary. Do not use aluminum oxide abrasive materials on epoxy/graphite materials.

Use abrasive flap wheel, abrasive disk, abrasive paper, or plastic media blast to remove paint.

c) Corrosion Removal

Note: Aircraft shall be electrically grounded during corrosion removal operations. When removing exterior corrosion from electronic boxes, the unit case shall be electrically grounded during the complete operation.

(1) Corrosion shall be removed by the mildest method possible.

(a) Hand scrub with dry non-metallic brush/pad. (3M scotchbrite 63

cellulose/nylon scouring pad).

(b) Use abrasive cloth. (Aluminum oxide 240 grit). Caution: Do not use on

epoxy/graphite materials.

Note: On high strength steel, do not use power tools other than a flap brush or mandrel with abrasive mat; overheating and notching may occur.

(2) Ensure all active corrosion and corrosion products have been removed. (3) Using 320 grit sandpaper blend edges of paint (if applicable) surrounding repair

area to create a smooth transition. Vacuum area thoroughly to remove all contaminates.

(4) Apply aluminum surface treatment if applicable. (Ref. Item 4. Below). (5) Touch-up primer and paint to match original

3. Mechanical Defects (Nicks, Scratches, Gouges, Etc.)

a) Determine if damage is through the paint. If not touch-up the paint (Ref. Section 20-30-

00,).

20-40-00

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Page 38

b) If damage is through the paint surface prepare area for paint touch-up using following

methods.

Note: On high strength steel, do not use power tools other than a flap brush or mandrel with abrasive mat; overheating and notching may occur.

(1) Remove defect using flap wheel, abrasive disk, abrasive paper, or plastic media

blast.

(2) Using 320 grit sandpaper, blend edges of paint surrounding repair area to create a

smooth transition.

(3) Apply aluminum surface treatment if applicable. (Ref. Item 4. Below). (4) Touch-up primer and paint to match original.

4. Aluminum Alloy Surface Touch-Up Treatment

Note: If there is any question of whether or not the protective coating is removed,

surface treatment shall be applied.

Warning: Alodine and solvents can cause burns and irritation when it contacts skin; proper gloves should be worn. Vapors are harmful and caustic to eyes; Goggles must be worn for eye protection. Alodine is poisonous. Vapors are harmful to life or health; work should be performed with proper ventilation and / or respirators should be worn while working with Solvents and alodine. Solvent cleaners are flammable.

a) Scuff surface using 3M scotchbrite 63 cellulose/nylon scouring pad. b) Wipe exposed surface with isopropyl alcohol or aliphatic naphtha. Allow area to air dry

for 10 minutes. Do not touch or otherwise contaminate surface after solvent wipe.

c) Apply Alodine 1200 or equivalent with cotton swap, non-metallic brush, or by dipping.

Maintain moist surface for 1-3 minutes with repeated application. Surface will become amber or brown in color.

d) Irrigate surface with demineralized or distilled water, to remove surface treatment

chemical. Allow to air dry for approximately 1 hour.

e) If there are any surface without color change, repeat procedure. f) Apply paint touch-up as required. (Ref Section 20-30-00)

20-40-00

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Page 39

Section 20-50-00 Mechanical Fastener Sealing Methods

Seal mechanical fasteners as shown using the following:

1. MTC-20-01-01-310 Use of Sealing Compounds, and

2. MCT 20-05-01 Sealing

Figure 20-02. Mechanical Fastener Sealing

20-50-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 39 of 80

Page 40

Section 20-90-00 Dye Penetrant Inspection Methods

Warning: solvents can cause burns and irritation when it contacts skin; proper gloves should be worn. Vapors are harmful and caustic to eyes; Goggles must be worn for eye protection. Vapors are harmful to life or health; work should be performed with proper ventilation and / or respirators should be worn while working with Solvents. Solvent cleaners are flammable.

Use the following steps to perform dye penetrant inspection:

1. Using cleaning solvent trichloroethane, MIL-T-81533, clean area to be inspected.

Note: Parts to be inspected must be dry and heated to at least 70° F (21.1° C), but not over

130° F (54.4° C).

Note: Manufacturers instructions on Dye Penetrant Kit take precedence over the following

instructions.

2. Apply penetrant from dye penetrant kit, MIL-25135, by brushing, spraying, or by dipping.

Allow to stand for a minimum of 2 minutes.

3. Remove excess penetrant with remover (available with dye penetrant kit), or by cleaning

with plain water. Allow part to dry.

4. Apply a light even layer of developer from dye penetrant kit by brushing, spraying, or by

dipping. When dipping, avoid excess quantity.

5. Penetrant, which has penetrated into cracks (or other openings) in the surface of the part

will be drawn out by the developer resulting in a bright red indication.

6. If part is serviceable or repairable, clean part free of penetrant and developer with

trichloroethane, MIL-T-81533 cleaning solvent

20-90-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 40 of 80

Page 41

CHAPTER 31

Table 31-01 Circuit Breakers

Label

Unit Controlled

PFD

Garmin Display Unit (PFD/MFD), GDU 620

AHRS

Attitude and Heading Reference System, GRS 77H

ADC

Air Data Computer, GDC 74H

Section 31-00-00 Instruments

1. Description and Operation

The Garmin G500H Flight Display System consists of an instrument panel mounted GDU 620 display and remote mounted LRUs which provide data to the display. The GDU 620 provides controls for the G500H system and a PFD and MFD in the pilot’s primary field of view. The remote mounted LRUs include one GRS 77H AHRS, one GMU 44 Magnetometer, one GDC 74H ADC, and one GTP 59 OAT probe.

The G500H system depends on electrical power to function. The Garmin Display Unit (GDU), Attitude and Heading Reference System (AHRS), and Air Data Computer (ADC) are connected to the aircraft main bus.

The major components of the G500H are circuit breaker protected with push-pull type circuit breakers available to the pilot. These breakers are located in the pedestal (30 α) circuit breaker panel and are labeled as shown in Table 31-01.

2. Removal and Installation

If any G500H LRUs are removed and reinstalled or a new unit is installed, verify that the LRU unit power-up self-test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display.

If any work has been done on the rotorcraft that could affect the system wiring or any interconnected equipment, verify the G500H system unit power-up self-test sequence is successfully completed and no failure messages are annunciated on the GDU 620 display.

Whenever removing or installing units, remove power from the LRU by removing aircraft power or opening the LRU circuit breaker.

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 41 of 80

31-00-00

Page 42

a) GMU 44, Magnetometer Removal and Installation

i Removal

1. Access the GMU 44 magnetometer (reference Section 6-00-00 Dimensions and

Access).

2. Unscrew the three screws that hold the GMU 44 to its mounting rack.

3. Carefully lift the GMU 44 from the rack.

4. Disconnect the wiring harness.

ii Installation

1. Visually inspect the connectors to ensure there are no bent or damaged pins.

Repair any damage.

2. Connect the wiring harness to the GMU 44.

3. Lower the GMU 44 into the rack and secure the plate with the three Phillips

screws.

Original GMU 44 is Reinstalled

If the original GMU 44 was reinstalled, then software loading is not required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Recalibration is required only if the mount for the magnetometer was changed. If the magnetometer mount was changed, refer to Section 5.6.2 of the G500H STC Installation Manual for the GRS 77H/GMU 44 Magnetic Calibration

New, Repaired or Exchange GMU 44 is Installed

If a new, repaired, or exchange GMU 44 unit is installed, then software must be loaded and the GRS 77H/GMU 44 Magnetic Calibration must be performed. Refer to Section 5 of the G500H STC Installation Manual for instructions on software loading (5.4.3) and Magnetic Calibration (5.6.2).

iii Return to Service

After removing and reinstalling the GMU 44, the following return-to-service checks should be performed (reference Section 12-00-10 Return to Service Checks).

b) GDC 74H, Air Data Computer

i Removal

1. Access the GDC 74H, (reference Section 6-00-00, Dimensions and Access)

2. Disconnect the pitot/static plumbing from the rear of the unit. Disconnect the

single connector.

3. Remove the two (2) screws on the mounting plate near the pitot/static ports.

Loosen the other two (2) screws.

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 42 of 80

Page 43

4. Carefully remove the unit from its mounting location.

ii Installation

1. Position the unit and fasten using the four (4) screws.

2. Connect the pitot/static plumbing.

3. Inspect the connector and pins for damage. Repair any damage.

4. Connect the connector to the unit, ensuring that each jackscrew is secured.

Original GDC 74H is Reinstalled

If the original GDC 74H is re-installed, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process.

New, Repaired or Exchange GDC 74H is Installed

If a new, repaired, or exchange GDC 74H unit is installed, then software must be loaded to the unit. Refer to Section 5.4.4 of the G500H STC Installation Manual for more information.

GDC 74H Configuration Module is Replaced

If the GDC 74H Configuration Module is replaced, the GDC 74H must be configured. Refer to Section 5.5.8 of the G500H STC Installation Manual

iii Return to Service

After removing and reinstalling the GDC 74H, the return-to-service checks must be performed (reference Section 12-00-00 Return-to-Service Check).

C) GRS 77H

i Removal

1. Disconnect the GRS 77H connector.

2. Loosen the four Phillips thumbscrews with a screwdriver.

3. Gently lift the GRS 77H from the mounting plate (if the supports for the

ii Installation

1. Place the GRS 77H on the mounting plate, ensuring the orientation is correct.

2. Fasten the unit to the plate using the Phillips thumbscrews. Recommended torque

is 22-25 inch pounds.

mounting plate are removed, the GRS 77H must be recalibrated)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 43 of 80

Page 44

3. Visually inspect the connectors to ensure there are no bent or damaged pins.

Repair any damage.

4. Connect the connector to the GRS 77H, ensuring that each slidelock is secured on

both sides.

Original GRS 77H is Reinstalled

If the original GRS 77H is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Reference Section 12-20-00 Calibration Requirements to determine whether recalibration is required.

New, Repaired, or Exchange GRS 77H is Installed

If a new, repaired, or exchange GRS 77H unit is installed then software must be loaded per Section 5.4.2 of the G500H STC Installation Manual. Reference Section 12-20-00 Calibration Requirements to determine whether re-calibration is required.

GRS 77H Configuration Module is Replaced

If the GRS 77H Configuration Module is replaced, the GRS 77H must be re-calibrated. Reference Section 12-10-20 Calibration Requirements.

iii Return to Service

After removing and reinstalling the GRS 77H, the return-to-service check should be performed. (Reference Section 12-00-10)

d) GDU 620 MFD

i Removal

1. Remove the six mounting screws from the bezel of the GDU 620.

2. Pull the GDU 620 far enough out from the instrument panel to access the three

rear connectors.

3. Disconnect the rear connectors.

4. Remove the GDU 620.

ii Installation

1. Visually inspect the connectors to ensure that there are no bent or damaged pins.

Repair any damage.

2. Connect the rear connectors, ensuring that each slidelock is secured on both sides.

3. Set the GDU 620 into place.

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Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 44 of 80

Page 45

4. Install the six mounting screws into the bezel of the GDU 620.

NOTE: The installation configuration settings are stored in the

configuration module and will be retained when the GDU 620 is replaced with a new unit. User settings, such as map orientation preferences, are stored internally and will be lost when the GDU 620 is replaced with a new unit.

Original GDU 620 is Reinstalled

If the original GDU 620 is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair process. No configuration is required.

New, Repaired or Exchange GDU 620 is Installed

If a new, repaired, or exchange GDU 620 unit is installed, then software must be loaded. No configuration is required

NOTE: Upon first power-up after installing a new GDU 620, it is normal

to see a series of “LOADING…” messages appear on the screen. These messages indicate that the GDU 620 is updating its configuration settings from the configuration module.

Refer to Section 5 of the G500H STC Installation Manual for the GDU 620 Software Loading procedure (5.4.1), followed by the Manifest Configuration (5.5.5) and the Configuration Module Update (5.5.12).

GDU 620 Configuration Module is Replaced

If the GDU 620 Configuration Module is replaced, the GDU 620 will update the configuration module from its internally-stored settings when the UPDT CFG soft key is pressed. If the GDU 620 is replaced at the same time as the Configuration Module, then the System Setup will need to be performed per Section 5.5 of the G500H STC Installation Manual.

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 45 of 80

Page 46

3. Illustrated Parts List

Table 31-01 Parts List for Figure 31-01

115-01568-00

BRACKET, MOUNTING, GMU 44,

GARMIN

115-01569-00

BRACKET, SUPPORT, GMU 44, FAA-

GARMIN

MS20426AD5-5

RIVET, SOLID, COUNTERSUNK 100

MS20470AD4-4

RIVET, SOLID, UNIVERSAL HEAD

A/R

MIL-S-8802

SEALING COMPOUND,

211-60037-08

SCREW, MACHINE, PAN HEAD,

GARMIN

115-00481-10

RACK, INSTALL, MODIFIED, GMU 44

GARMIN

011-00870-10

GMU 44 MAGNETOMETER

GARMIN

This section contains information on parts for the G500H Flight Display System, for use in ordering replacements if necessary.

ITEM

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

FAA-PMA, EUROCOPTER AS350

PMA, EUROCOPTER AS350

DEG, PRECISSION HEAD, 5/32 IN

OD, 5/16 IN LONG

TEMPERATURE RESISTANT, HIGH

ADHESION

CROSS-RECESSED, BRASS, 0.1380-

32 UNC-2A

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 46 of 80

31-00-00

Page 47

Figure 31-01

GMU 44 MAGNETOMETER INSTALLATION, EXPLODED VIEW

(Reference Table 31-01)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 47 of 80

Page 48

Table 31-02 Part Lists for Figures 31-02 and 31-03

ITEM

- 1 115-01757-00

BRACKET, SUPPORT, AFT, LH SHELF,

GARMIN

2 - 115-01755-00

BRACKET, SUPPORT, RH SHELF, FAA-

GARMIN

- 1 115-01756-00

BRACKET, SUPPORT, FWD, LH SHELF,

GARMIN

- 1 115-01758-00

RH SHELF

GARMIN

1 - 115-01759-00

LH SHELF

GARMIN

8 8 AN3-3A

BOLT

8 8 AN3-4A

BOLT

8 8 MS21042-3

NUT

NAS1149F0332P

WASHER

8 8 MS21075-3

NUTPLATE

MS20426AD3-3

RIVET

- 1 NAS43DD3-24

SPACER

- 2 MS21266-1

GROMMET

NUMBER

QTY

PART NUMBER DESCRIPTION MANUFACTURER

FAA-PMA, EUROCOPTER AS350

PMA, EUROCOPTER AS350

FAA-PMA, EUROCOPTER AS350

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 48 of 80

31-00-00

Page 49

Figure 31-02

RH SHELF INSTALLATION (Reference Table 31-02)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 49 of 80

Page 50

Figure 31-03

LH SHELF INSTALLATION (Reference Table 31-02)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 50 of 80

Page 51

Table 31-03 Parts List for Figure 31-04

ITEM NUMBER

- 1 190-00792-03

LH SHELF INSTALLATION

GARMIN

1 - 190-00792-03

RH SHELF INSTALLATION

GARMIN

1 1 011-00882-11

GDC 74H ADC

GARMIN

4 4 MS21075-3

NUTPLATE

8 8 MS20426AD3-3

RIVET

4 4 AN525-10R8

SCREW

QTY

PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 51 of 80

Figure 31-04

GDC 74H INSTALLATION LH, EXPLODED VIEW (SHOWN);

GDC 74H INSTALLATION RH, EXPLODED VIEW (OPPOSITE – NOT SHOWN)

(Reference Table 31-03)

31-00-00

Page 52

Table 31-04 Parts List for Figure 31-05

ITEM NUMBER

- 1 190-00792-03

LH SHELF INSTALLATION

GARMIN

1 - 190-00792-03

RH SHELF INSTALLATION

GARMIN

1 1 011-00868-20

GRS 77H AHRS

GARMIN

1 1 115-00459-00

GRS 77 MOUNT RACK

GARMIN

5 5 MS21075-3

NUTPLATE

MS20426AD3-3

RIVET

5 5 AN525-10R8

SCREW

QTY

PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 52 of 80

Figure 31-05

GRS 77H INSTALLATION LH, EXPLODED VIEW (SHOWN)

GRS 77H INSTALLATION RH, EXPLODED VIEW (OPPOSITE – NOT SHOWN)

(Reference Table 31-04)

31-00-00

Page 53

Table 31-05 Part List for Figure 31-06

ITEM

M81714/67-18

MOUNTING TRACK

REF

M81714/60-22-05

TERMINAL BLOCK

3 2 AN525-10R7

SCREW

NAS1149F0332P

WASHER

5 2 MS21042-3

NUT

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 53 of 80

Figure 31-06

TERMINAL BLOCK INSTALLATION, EXPLODED VIEW

(Reference Table 31-05)

31-00-00

Page 54

Table 31-06 Parts List for Figure 31-07

ITEM

011-00978-00

GTP 59 OAT PROBE

GARMIN

115-01567-00

DOUBLER

GARMIN

3 8 CR3213-4-03

RIVET

CHERRYMAX

A/R

MIL-S-8802

SEALING COMPOUND

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 54 of 80

Figure 31-07

GTP 59 OAT PROBE INSTALLATON, EXPLODED VIEW

(Reference Table 31-06)

31-00-00

Page 55

Table 31-07 Parts List for Figures 31-08 through 31-12

ITEM

NUMBER

QUANTITY

-01

-02

-03

-04

1 - - - 011-02764-01

INSTRUMENT PANEL ASSEMBLY,

GARMIN

- 1 - - 011-02764-02

INSTRUMENT PANEL ASSEMBLY,

GARMIN

- - 1 - 011-02764-03

INSTRUMENT PANEL ASSEMBLY,

GARMIN

- - - 1 011-02764-04

INSTRUMENT PANEL ASSEMBLY,

GARMIN 5

1 1 1 1 011-01264-60

GDU 620 PFD/MFD

GARMIN

REF

5956-28-01 REV. A

DIMMING CONTROL OVERLAY

AERO DYNAMIX

1 1 1 1 B3500BA01

V.E.M.D.

REF

704A47723068

ANNUNCIATOR PANEL

EUROCOPTER

REF

REF - -

EXISTING

3-IN NR TACHOMETER

REF

REF - -

C4E0118-01

3-IN EYEBROW LIGHT

EUROCOPTER

REF - REF

EXISTING

3-IN AIRSPEED INDICATOR

REF - REF

EXISTING

3-IN ALTIMETER INDICATOR

REF

REF - 3A43.22.35F.28.1.FU

2-IN ALTIMETER COUNTER DRUM

THOMMEN

REF

REF - MD25-200

2-IN AIRSPEED INDICATOR

MID-CONTINENT

- - REF

REF

EXISTING

2-IN NR TACHOMETER

- - REF

REF

350A67-0159-20

2-IN EYEBROW LIGHT

EUROCOPTER

REF - REF

71450B23

LED POST LIGHT

EUROCOPTER

13 6 15 8 MS35214-29

SCREW

2 5 - 3 MS35214-31

SCREW

2 2 - - MS35214-33

SCREW

6 6 6 6 MS35214-44

SCREW

2 2 2 2 NAS1149DN632P

WASHER

6 6 6 6 NAS1149DN832P

WASHER

13 9 NAS620-6L

WASHER

7 - 7 - MS33737-14C

NUT

2 7 2 5 MS33737-16C

NUT

REF

LED-40-17-HE-E0G3T

VIVISUN LED SWITCH

AEROSPACE

PART NUMBER DESCRIPTION MANUFACTURER

OPTION 1

OPTION 2

OPTION 3

OPTION 4

POINTER

*Reference Table 31-08 through 31-11 and Figures 31-13 through 31-16

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 55 of 80

OPTICS

31-00-00

Page 56

Figure 31-08

INSTRUMENT PANEL INSTALLATION

(Reference Table 31-07)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 56 of 80

Page 57

Figure 31-09

ITEM 1, INSTRUMENT PANEL INSTALLATION

(Reference Table 31-07)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 57 of 80

Page 58

Figure 31-10

ITEM 2, INSTRUMENT PANEL INSTALLATION

(Reference Table 31-07)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 58 of 80

Page 59

Figure 31-11

ITEM 3, INSTRUMENT PANEL INSTALLATION

(Reference Table 31-07)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 59 of 80

Page 60

Figure 31-12

ITEM 4, INSTRUMENT PANEL INSTALLATION

(Reference Table 31-07)

31-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 60 of 80

Page 61

Table 31-08 Parts List for Figure 31-13

1 1 115-01760-01

OPTION 1 INSTRUMENT PANEL

GARMIN

2 1 161-02779-01

FAA-PMA LABEL

GARMIN

3 4 MS21061L08

NUTPLATE

4 6

MS21069-08

NUTPLATE

5 6

MS21071-06

NUTPLATE

6 2

MS21075-08

NUTPLATE

7 36

MS20426AD3-4

RIVET

ITEM

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 61 of 80

Figure 31-13

OPTION 1, INSTRUMENT PANEL ASSEMBLY

(Reference Table 31-08)

31-00-00

Page 62

Table 31-09 Parts List for Figure 31-14

ITEM

1 1 115-01760-02

OPTION 2 INSTRUMENT PANEL

GARMIN

2 1 161-02779-02

FAA-PMA LABEL

GARMIN

3 4 MS21061L08

NUTPLATE

4 6

MS21069-08

NUTPLATE

5 6

MS21071-06

NUTPLATE

6 2

MS21075-08

NUTPLATE

7 36

MS20426AD3-4

RIVET

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 62 of 80

Figure 31-14

OPTION 2, INSTRUMENT PANEL ASSEMBLY

(Reference Table 31-09)

31-00-00

Page 63

Table 31-10 Parts List for Figure 31-15

ITEM

1 1 115-01760-03

OPTION 3 INSTRUMENT PANEL

GARMIN

2 1 161-02779-03

FAA-PMA LABEL

GARMIN

3 4 MS21061L08

NUTPLATE

4 6

MS21069-08

NUTPLATE

5 6

MS21071-06

NUTPLATE

6 2

MS21075-08

NUTPLATE

7 36

MS20426AD3-4

RIVET

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 63 of 80

Figure 31-15

OPTION 3, INSTRUMENT PANEL ASSEMBLY

(Reference Table 31-10)

31-00-00

Page 64

Table 31-11 Parts List for Figure 31-16

ITEM

1 1 115-01760-04

OPTION 4 INSTRUMENT PANEL

GARMIN

2 1 161-02779-04

FAA-PMA LABEL

GARMIN

3 4 MS21061L08

NUTPLATE

4 6

MS21069-08

NUTPLATE

5 6

MS21071-06

NUTPLATE

6 2

MS21075-08

NUTPLATE

7 36

MS20426AD3-4

RIVET

NUMBER

QUANTITY PART NUMBER DESCRIPTION MANUFACTURER

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 64 of 80

Figure 31-16

OPTION 4, INSTRUMENT PANEL ASSEMBLY

(Reference Table 31-11)

31-00-00

Page 65

Table 31-12 List of Consumable Materials

DESCRIPTION

P/N

VENDOR/SPECIFICATION

THREAD LOCK

242

LOCTITE

ADHESIVE

1300L

Cleaning cloth, Low-Lint

Commercial

Mineral Spirits, Cleaning Solvent

MIL-PRF-680, TYP II

Alodine

Alodine 1200

Alodine

Iridite 14-2

Paint Stripper

Turco 5873

Polyamide Paint Primer

Dye Penetrant Kit

Acetone

ASTM-D329

Isopropyl Alcohol

TT-I-735

Trichloroethane

MIL-T-81533

Nylon Scouring Pad

(3M) Scotchbrite 63

240 Grit Sandpaper

Commercial

320 Grit Sandpaper

Commercial

240 Grit Aluminum Oxide Abrasive

Commercial

Cloth

Commercial

Sealant

MIL-S-8802

Adhesive transfer tape 950 (2")

70-0060-3057-4

-OR ASTM-D235

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 65 of 80

31-00-00

Page 66

4. Troubleshooting guide

60 into the bottom slot of

When loading software, the

The software loader card is

Insert the loader card in the top slot and The software loader card contains

Repeat the process for making the

If error indications are displayed on the GDU 620 display unit, consult the Troubleshooting section contained in Table 31-11.

The G500H will display a number of alerts on the GDU 620 MFD. These are listed in the Table 31-12.

Table 31-13 GDU 620 Troubleshooting Guide

Problem Cause Solution

Unit does not power up – blank screen.

All expected configuration pages are not displayed.

The GDC OAT probe type shows up as UNKNOWN

LRU software is not being displayed on the SOFTWARE UPLOAD page.

Configuration errors are displayed on power-up, before the GDU enters normal mode.

Improper wiring; circuit breaker open.

Ensure power is properly wired to the GDU 620 and the circuit breaker is closed.

Unit intensity turned down. Ensure that unit is not in manual intensity

control mode with the intensity turned down.

An Installer Unlock Card is not inserted into the GDU 620.

Insert the Installer Unlock Card P/N 010-00769the GDU 620 and cycle power.

The RS-232 connection to the GDC 74H is not working.

Ensure that the GDC 74H RS-232 connection to the GDU is properly wired, and ensure that the GDC 74H circuit breaker is closed.

installed in the bottom slot of the

cycle power to the GDU.

GDU 620.

no information.

The configuration module has not

software loader card.

Update the configuration module.

been updated.

Vertical GPS deviation is not displayed on the GDU 620.

Unable to control the GPS course when in OBS mode.

Data is not being received from an ARINC 429 device.

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 66 of 80

For 400W/500W Series units, the ARINC 429 vertical deviation labels are not being transmitted.

The GPS navigator is not correctly configures as LNAV1/2 or SYS1/2.

ARINC 429 bus hi and low are swapped.

31-00-00

Enable Labels on the 400W/500W Series unit ARINC 429 configuration page.

Configure the ARINC 429 inputs/outputs for LNAV1 (SYS1) or LNAV2 (SYS2) based upon whether the navigator is GPS1 or GPS2.

Verify wiring.

Page 67

Problem Cause Solution

Wiring is not correct.

Check for continuity/shorts and correct as

(valid data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page)

Wrong device is connected to port on GDU 620.

Use correct ports (refer to interconnect details).

Data is not being received from an ARINC 429 device.

(no data is being received on the 429 input port as shown on the GDU 620 PORT MONITORING page)

Attitude and heading on GDU 620 red ‘X’ / GRS 77H resets during air data ground testing.

On the transmitting LRU, the ARINC 429 transmitter speed is not set correctly.

Attitude and heading errors/resets are possible if the air data tests are conducted indoors without a good GPS signal. With marginal or no GPS signals present, sudden changes in airspeed caused by using a pressure tester may result in attitude and heading errors and possibly cause the GRS 77H to reset. This occurs because the artificial changes in airspeed cause disagreement with the other sensor measurements internal to the GRS 77H. This sensor disagreement will not occur in the normal conditions of flight.

Set the ARINC 429 transmitter speed to correct speed.

required.

This is expected behavior and no troubleshooting is required if this occurs. To reduce the chances of inducing attitude and heading errors/resets while conducting the air data tests, ensure that the G500H is receiving good GPS signals.

Heading red ‘X’ during air data ground testing

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 67 of 80

Invalidation of heading is possible if the air data tests are conducted indoors, due to typical magnetic anomalies, even with a good GPS signal.

31-00-00

This is expected behavior and no troubleshooting is required if this occurs.

Page 68

Alert Text Cause Solution

AHRS is using the backup GPS

Verify GPS1 power and check the wiring

Verify GPS power and check the wiring acquired a valid position.

620 and GPS receiver.

If GDU has a valid GPS position, verify verify time mark wiring.

Verify GPS2 power and check the wiring

Update GRS 77H IGRF model (current

GDC not powered up. Close ADC C/B.

GDC not receiving input from GTP 59

ARINC 429 connection from GDC 74H to correct.

calibration data.

Verify wiring to configuration module

Replace configuration module

cycle higher than or equal to 10%

Fan 2 has reported 0 RPM when it

Inspect the GDU fan for an obstruction.

AHRS1 GPS – AHRS 1 using backup GPS source.

Table 31-14 GDU 620 Alert Troubleshooting Guide

information

AHRS1 GPS - AHRS is not receiving any GPS information

AHRS1 GPS – AHRS 1 operating in exclusively in no-

AHRS is not receiving any GPS information.

GPS mode.

AHRS1 GPS – AHRS 1 not receiving backup GPS

AHRS is not receiving GPS information from GPS2.

information.

AHRS1 SRVC AHRS magnetic field model should

be updated. Appears on ground only.

AHRS1 TAS AHRS is not receiving true airspeed

from ADC.

Ensure that at least one GPS has

If GDU 620 does not have a valid position, verify wiring between GDU and GPS receiver, and configuration of GDU

wiring between GDU and GRS. Also

model is with aviation database).

OAT probe. Verify wiring is correct.

CAL LOST

Registry reports that it has lost

CNFG MODULE The configuration module is

inoperative.

DATA LOST Pilot stored data was lost. Recheck

data and settings.

FAN 1 FAIL

Fan 1 has reported 0 RPM when it was powered with a PWM duty

FAN 2 FAIL

was powered with a PWM duty cycle higher than or equal to 10%

31-00-00

GRS 77H is not working. Verify wiring is

Contact Garmin Technical Support.

Inspect the GDU fan for an obstruction. Contact Garmin Technical Support.

Contact Garmin Technical Support.

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 68 of 80

Page 69

Alert Text

Cause

Solution

620 into the GDL 69.

GDU CONFIG

This error appears whenever the

Cycle power to the GDU. This error

Ensure fans on indicated GDU are obstructed

Verify the correct card is installed, reload

Ensure GPS (1/2) is turned on

GDU 620.

GRS 77H not receiving information from

GDL69 CONFIG The GDL 69 configuration

information stored in the GDL 69 and the GDU 620 configuration module do not match.

The GDL 69 configuration was updated using another LRU (e.g. the GMX 200 or 400W/500W).

GDU is replaced with a GDU that was configured for a different installation.

Error in the configuration of the GDU 620.

GDU (1/2) COOLING Specific GDU has poor cooling, and

power usage is being reduced.

GDU (1/2) DB ERR Error in specific database, where

GDU (1/2) DB denotes specific database.

GDU (1/2) VOLTAGE GDU supply voltage is below 12

VDC.

With the GDU 620 in configuration mode, go to the GDL 69 page in the GDL page group. Verify that the SET and ACTIVE configuration settings are the same. If not, use the SET>ACTV soft key to copy the configuration settings from the GDU

Update the GDL 69 configuration using the GDU 620.

automatically clears on the second power up with a different configuration module.

functioning Ensure fans on indicated GDU are not

the DB on the card.

Increase the voltage above 12VDC.

GEO LIMITS Location is too far north/south for

GPS(1/2) FAIL No GPS1 or GPS2 data is available.

GPS(1/2) PPS Failure This alert will be set if the PPS

GPS2 FPL USED The GPS1 has failed and GPS2 is

HDG FAULT AHRS magnetometer fault has

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 69 of 80

GRS 77H magnetic compass.

signal has not been received in more than 5 sec. If the unit is configured for dual GPSs then the side will be specified in the error.

configured and operating.

occurred.

31-00-00

Verify RS-232 wiring from the GPS to the

Ensure GPS (1/2) is turned on

Verify 1PPS wiring from the GPS to the GDU 620.

GMU 44. Verify wiring to GMU 44.

Page 70

Alert Text

Cause

Solution

HDG LOST Heading from the GRS77/ GMU 44

Caused by a local magnetic anomaly. No

match the values being reported by

manifest

Update the manifest to match the LRU

NAV2 FAIL

No navigation receiver 2 data.

SIMULATOR

The simulator mode is active.

Ensure P6202-36 is not grounded.

SVT DISABLED - Out of

Location is beyond region covered

Update the Supplemental Data card with

The GDU 620 is not receiving traffic

sensor.

failed. Troubleshoot traffic system.

is not valid.

<LRU> SERVICE Specific LRU should be serviced,

where <LRU> denotes specific LRU.

action required.

Return indicated LRU to Garmin for service.

MANIFEST GDU has received product data for

an LRU that should have a manifest entry, but is not in the manifest.

The LRU software P/N and version number in the manifest does not

that LRU.

NAV1 FAIL No navigation receiver 1 data.

available terrain region.

SVT DISABLED - Terrain DB resolution too low.

by terrain database.

A 30 arc-second terrain database is being used.

SW MISMATCH GDU software version strings do

not match.

TRAFFIC FAIL The traffic information system has

failed.

Ensure the manifest is properly configured.

Update the LRU software to match the

software

the 9 arc-second terrain database.

Verify the correct SW is loaded

information from the traffic sensor. Verify wiring between GDU 620 and traffic

TRK LOST GPS1 TRK lost. HSI defaulted to

TRK TRAFFIC Heading Lost. Traffic is now based

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 70 of 80

The GDU 620 is receiving information from the traffic sensor, but the information is indicating that the traffic sensor has

GPS2 TRK.

See HDG errors.

on track.

31-00-00

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CHAPTER 98

Section 98-00-00 Wiring Diagrams and Pitot-Static System Schematics

This chapter includes the Wiring Diagrams and Pitot-Static System Schematics for the G500H Flight Display System.

98-00-00

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Page 72

Section 98-10-00 Wiring Diagrams

G500H EFIS System Wiring

98-10-00

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Page 80

Section 98-20-00 Pitot-Static System Schematic

98-20-00

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Garmin AS-350B2, AS-350B3 Instruction Manual

Specifications and Main Features

Frequently Asked Questions

User Manual

Section 01-00-00 Introduction

CHAPTER 4

Section 04-00-00 Airworthiness Limitations

CHAPTER 5

Section 05-00-00 Continued Airworthiness Inspections

1. General

2. Component Overhaul Schedule

3. Scheduled Inspections Overview

4. Special Inspection Practices

5. Definitions and Acronyms

Section 05-20-10 Continued Airworthiness Scheduled Inspections

1. General

2. Scheduled Inspection Program

3. Tools and Special Tools for Scheduled Inspection

4. Post Inspection Maintenance Practices

Section 05-20-20 Continued Airworthiness Special Inspections

1. General

2. Special Inspection Program

3. Tools and Special Tools for Special Inspections

CHAPTER 6

Section 06-00-00 Dimensions and Access

1. Access Methods

CHAPTER 8

Section 8-00-00 Weight and Balance Information

CHAPTER 12

Section 12-00-00 Servicing Maintenance Practices

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

1. General

Section 12-20-00 Calibration Requirements

CHAPTER 20

Section 20-00-00 Standard Practices

Section 20-10-00 Torques Maintenance Practices

1. Torque Wrenches

2. Torque Wrenches

Section 20-30-00 Painting Maintenance Practices

1. Paint Touch-Up of Small Areas

Section 20-40-00 Corrosion Control Maintenance Practices

1. Corrosion Control

2. Corrosion Removal

Note: If paint stripper evaporates quickly or works slowly, cover area with plastic sheet.

(8) Rinse with demineralized water.

Note: Aircraft shall be electrically grounded during corrosion removal operations. When removing exterior corrosion from electronic boxes, the unit case shall be electrically grounded during the complete operation.

(1) Corrosion shall be removed by the mildest method possible.

Note: On high strength steel, do not use power tools other than a flap brush or mandrel with abrasive mat; overheating and notching may occur.

3. Mechanical Defects (Nicks, Scratches, Gouges, Etc.)

Note: On high strength steel, do not use power tools other than a flap brush or mandrel with abrasive mat; overheating and notching may occur.

4. Aluminum Alloy Surface Touch-Up Treatment

Section 20-50-00 Mechanical Fastener Sealing Methods

Section 20-90-00 Dye Penetrant Inspection Methods

CHAPTER 31

Section 31-00-00 Instruments

1. Description and Operation

2. Removal and Installation

3. Illustrated Parts List

4. Troubleshooting guide

Table 31-13 GDU 620 Troubleshooting Guide

Table 31-14 GDU 620 Alert Troubleshooting Guide

Section 98-00-00 Wiring Diagrams and Pitot-Static System Schematics

Section 98-10-00 Wiring Diagrams

Section 98-20-00 Pitot-Static System Schematic