Garmin AS_350B2/B3 Instruction Manual

Instructions for Continued Airworthiness for the Garmin G500H Installation 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

Confidential

This drawing and the specifications contained herein 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 written permission.

Rev. Date

1 2/14/2014 Initial release.

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

Description of Change

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

Instructions for Continued Airworthiness for the Garmin G500H Installation in Eurocopter AS350

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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.

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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 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

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

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OAT- Outside Air Temperature

GTP- Garmin Temperature Probe

ADC- Air Data Computer

STC- Supplemental Type Certificate

AHRS- Attitude Heading Reference System

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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 inspection

.

The special tools necessary for the G500H inspection are listed as follows: a) Milliohm meter (for electrical bonding testing).

Table 5-01 -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

1. Review Airworthiness Directives.

Initial

90 Day Inspection

Requirement

GDC 74H ADC

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

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Initial


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Table 5-02 -1 year (Annual) Inspection


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.




1 year (Annual) Pre-inspection

Requirement


Initial

1 year (Annual) Inspection

Requirement Initial

GDU 620

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

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

3. 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 Practice.

4. Conduct visual inspection of wires, backshells, and connectors looking for signs of wear, deterioration or damage. Replace as required.

5. 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.

GRS 77H AHRS

1. Access GRS 77H (reference Section 6-00-00- Dimensions and Access). Inspect AHRS and 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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GMU 44 Magnetometer Installation

1. Access GMU 44 (reference Section 6-00-00- Dimensions and Access). Inspect GMU 44 and mount for physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.


3. Inspect hardware. Replace the damaged or corroded hardware. Replace any missing hardware. Torque all screws in accordance with Section 20-10-00 Torques Maintenance

Practice.


Shelf Installation

1. Access Shelf Installation (reference Section 6-00-00- 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

Practice.

GDC 74H ADC Installation

1. Access GDC 74H (reference Section 6-00-00- Dimensions and Access). Inspect GDC 74H and mount for physical damage cracks, and corrosion. Treat and repair corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.






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

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

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





Terminal Block Installation

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

Inspect installation 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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Table 5-03 -5 Year Inspection


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.




5 Year Pre-inspection



5 Year Inspection


GRS 77H AHRS

1. The GRS 77 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.

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


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.




10 Year/2000 Flight Hour Pre-inspection



10 Year/2000 Flight Hour Inspection


GRS 77H AHRS

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

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

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 harness connectors.

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


GMU 44

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

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


GTP 59

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

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

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.

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

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 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 (for electrical bonding testing).

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Table 5-05 -Post-Lightning Strike Inspection


Post-Lightning Strike Inspection

• The Post-Lightning Strike Inspection shall be accomplished in the event of a suspected or actual lightning strike to the aircraft.




Post-Lightning Strike Pre-inspection



Post-Lightning Strike Inspection


GTP 59 OAT Probe Installation

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

Access.

2. Inspect the probe and the doubler (P/N: 115-01812-00) for signs of structural damage. If there are visible signs of damage, replace the parts as needed.

Post-Lightning Strike Post- Inspection

Requirement

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

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Initial


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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 a) GMU 44, Magnetometer

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

GMU 44

Figure 6-01

TB

868

REF

TB

1578

REF

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

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)

GDC 74H

Figure 6-02

STA

2325

REF

STA

1790

REF


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.


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c) GRS 77H, AHRS

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)

GRS 77H

STA

2325

REF

STA

1790

REF

Figure 6-03


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







3. Close the Center lower belly access panel and attach screws.


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d) Shelf Installation

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)

Shelf

STA

2325

REF

STA

1790

REF

Figure 6-04


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







3. Close the Center lower belly access panel and attach screws.


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e) Terminal Block Installation

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

Terminal Block

STA

1120

REF

STA

1502

REF

Figure 6-05











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f) GTP 59 OAT Probe Installation

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

2351. (Figure 6-06)

GTP 59

STA

2351

REF

STA

2437

REF

Figure 6-06




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.


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.



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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g) GDU 620 Installation

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).

GDU 620

Figure 6-07


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.


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


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CHAPTER 8

Section 8-00-00 Weight and Balance Information

Installation #

01E06310002-01

01E06310003-01

01E06310003-02

01E06310004-01

01E06310004-02

01E06310005-01

01E06310005-02

01E06310008-01

01E06310009-01

01E06310014-01

01E06310014-02

01E06310014-03

01E06310014-04

Description

GMU 44 Magnetometer

RH Shelf

LH Shelf

GDC 74H

GDC 74H

GRS 77H AHRS

GRS 77H AHRS

Terminal Block

GTP 59 OAT Probe

Instrument Panel

Instrument Panel

Instrument Panel

Instrument Panel

Weight

0.70 lbs

2.20 lbs

2.20 lbs

1.92 lbs

1.92 lbs

3.46 lbs

3.46 lbs

0.47 lbs

0.08 lbs

47.80 lbs

47.80 lbs

47.80 lbs

47.80 lbs

08-00-00

CG Location

TB 1215, WL -2225, BL 0.0

STA 2042, WL -2781, BL 600.7

STA 2042, WL -2781, BL -600.7

STA 2003, WL -2745, BL 662.0

STA 2003, WL -2745, BL -662.0

STA 2019, WL -2748, BL 572.0

STA 2019, WL -2748, BL -572.0

STA 1265, WL -2659, BL -612.2

STA 2386, WL -2910, BL 7.2

STA 1120, WL -2066, BL 0.0

STA 1120, WL -2066, BL 0.0

STA 1120, WL -2066, BL 0.0

STA 1120, WL -2066, BL 0.0


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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.

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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. b) GDC 74H


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


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. c) GRS 77H


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.


31-00-00 Troubleshooting. d) GDU 620


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.

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Section 12-20-00 Calibration Requirements

Condition

Calibrations Required

GRS 77H

Pitch/Roll

Offset

See Section 5 of the G500H STC

Installation Manual

GRS/GMU

Magnetic

Calibration

See Section 5 of the G500H STC

Installation Manual

Engine Run-up

Vibration

Test

See Section 5 of the G500H

STC Installation

Manual

GRS 77H AHRS was removed and/or replaced. The mounting tray was NOT removed and the mounting tray bolts were NOT loosened.

None Required.

GRS 77H AHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts

WERE loosened.

GRS 77H AHRS Configuration Module was replaced.

X

X

X

X

X

X

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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.

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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.

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Figure 20-01

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2. Torque Wrenches

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

Thread Size

Fractional (decimal)

8-36

(0.1640-36)

10-32

(0.1900-32)

¼-28

(0.2500-28)

5/16-24

(0.3125-24)

3/8-24

(0.3750-24)

7/16-20

(0.4375-20)

½-20

(0.5000-20)

9/16-18

(0.5625-18)

5/8-18

(0.6250-18)

¾-16

(0.7500-16)

7/8-14

(0.8750-14)

1-12

(1.0000-12)

1-1/8-12

(1.1250-12)

1-1/4-12

(1.2500-12)

Shear

Recommended in-lb (N m)

7-9

(0.79-1.02)

12-15

(1.36-1.69)

30-40

(3.38-4.51)

60-85

(6.77-9.60)

95-110

(10.73-12.42)

270-300

(30.49-33.88)

290-410

(32.75-46.31)

480-600

(54.22-67.77)

660-780

(74.55-88.10)

1,300-1,500

(146.84-169.44)

1,500-1,800

(169.44-203.32)

2,200-3,300

(248.51-372.76)

3,000-4,200

(338.88-474.43)

5,400-6,600

(609.98-745.53)

9,000

(1016.6)

15,000

(1694.4)

20-10-00

Maximum in-lb (N m)

12

(1.36)

25

(2.82)

60

(6.77)

140

(15.81)

240

(27.11)

500

(56.48)

660

(74.55)

960

(108.44)

1,400

(158.14)

3,000

(338.88)

4,200

(474.43)

6,000

(677.76)

Tension


12-15

(1.36-1.69)

20-25

(2.25-2.82)

50-70

(5.64-7.90)

100-140

(11.29-15.81)

160-190

(18.07-21.46)

450-500

(50.83-56.48)

480-690

(54.22-77.94)

800-1,000

(90.36-112.96)

1,100-1,300

(124.25-146.84)

2,300-2,500

(259.80-282.40)

2,500-3,000

(282.40-338-88)

3,700-5,500

(417.95-621.28)

5,000-7,000

(564.80-790.72)

9,000-11,000

(1016.6-1242.6)


20

(2.26)

40

(4.51)

100

(11.29)

225

(25.41)

390

(44.05)

840

(94.88)

1,100

(124.25)

1,600

(180.73)

2,400

(271.10)

5,000

(564.80)

7,000

(790.72)

10,000

(1129.6)

15,000

(1694.4)

25,000

(2824.0)


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

Thread Size

Fractional (decimal) Recommended in-lb (N m)

Shear


Tension



8-32

(0.1640-32)

10-24

(0.1900-24)

7-9

(0.79-1.02 )

12-15

(1.36-1.69)

12

(1.36)

21

(2.37)

12-15

(1.36-1.69)

20-25

(2.25-2.82)

20

(2.26)

35

(3.95)

¼-20

(0.2500-20)

5/16-18

(0.3125-18)

3/8-16

(0.3750-16)

7/16-14

(0.4375-14)

25-30

(2.82-3.38)

48-55

(5.42-6.21)

95-100

(10.73-11.29)

140-155

(15.81-17.50)

45

(5.08)

100

(11.29)

170

(19.20)

280

(31.62)

40-50

(4.51-5.64)

80-90

(9.03-10.16)

160-185

(18.07-20.89)

235-255

(26.54-28.8)

75

(8.47)

160

(18.07)

275

(31.06)

475

(53.65)

½-13

(0.5000-13)

9/16-12

(0.5625-12)

5/8-11

(0.6250-11)

¾-10

(0.7500-10)

7/8-9

(0.8750-9)

1-8

(1.0000-8)

1-1/8-8

(1.1250-8)

1-1/4-8

(1.2500-8)

240-290

(27.11-32.75)

300-420

(33.88-47.44)

420-540

(47.44-60.99)

700-950

(79.07-107.31)

1,300-1,800

(146.84-203.32)

2,200-3,000

(248.51-338.88)

3,300-4,000

(372.76-451.84)

4,000-5,000

(451.84-564.80)

520

(58.73)

650

(73.42)

900

(101.66)

1,500

(169.44)

2,700

(474.43)

4,500

(508.32)

7,200

(813.31)

10,000

(1129.6)

400-480

(45.18-54.22)

500-700

(56.48-79.07)

700-900

(79.07-101.66)

1,150-1,600

(129.90-180.73)

2,200-3,000

(248.51-338-88)

3,700-5,000

(417.95-564.80)

5,500-6,500

(621.28-734.24)

6,500-8,000

(734.24-903.68)

880

(99.40)

1,100

(124.25)

1,500

(169.44)

2,500

(282.40)

4,600

(519.61)

7,600

(858.49)

12,000

(1355.5

16,000

(1807.4 N m)

Thread Size

Fractional (decimal)

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

Recommended in-lb (N m) Maximum in-lb (N m)

8-32 (0.1640-32

10-32 (0.1900-32)

¼-28 (0.2500-28)

12-15 (1.36-1.69)

20-25 (2.25-2.82)

60-70 (6.77-7.90)

23 (2.59)

35 (3.95)

90 (10.16)

5/16-24 (0.3125-24)

3/8-24 (0.3750-24)

7/16-20 (0.4375-20)

½-20 (0.5000-20)

9/16-18 (0.5625-18)

5/8-18 (0.6250-18)

110-125 (12.42-14.12)

150-175 (16.94-19.76)

230-280 (25.98-31.62)

550-650 (62.12-73.42)

750-900 (84.72-101.66)

150 (16.94)

225 (25.41)

450 (50.83)

850 (96.01)

1,200 (135.55)

1,600 (180.73) 1,100-1,300 (124.25-146.84)

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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.

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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

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(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.

(c) Use 320 grit sandpaper.

(d) Glass bead blast.

(e) Use 240 grit abrasive wheel.

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,).

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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)

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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

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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).

2.

3.

4.

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

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

Allow to stand for a minimum of 2 minutes.

Remove excess penetrant with remover (available with dye penetrant kit), or by cleaning with plain water. Allow part to dry.

Apply a light even layer of developer from dye penetrant kit by brushing, spraying, or by dipping. When dipping, avoid excess quantity.

5.

6.

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.

If part is serviceable or repairable, clean part free of penetrant and developer with trichloroethane, MIL-T-81533 cleaning solvent

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CHAPTER 31

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.

Label

PFD

AHRS

ADC

Table 31-01 Circuit Breakers

Unit Controlled

Garmin Display Unit (PFD/MFD), GDU 620

Attitude and Heading Reference System, GRS 77H

Air Data Computer, GDC 74H

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.

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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.

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

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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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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.

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3.

ITEM

NUMBER

1

2

3

4

5

6

7

8

Illustrated Parts List

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

Table 31-01 Parts List for Figure 31-01

QUANTITY PART NUMBER

1

1

6

16

A/R

3

1

1

115-01568-00

DESCRIPTION

BRACKET, MOUNTING, GMU 44,

FAA-PMA, EUROCOPTER AS350

115-01569-00 BRACKET, SUPPORT, GMU 44, FAA-

PMA, EUROCOPTER AS350

MS20426AD5-5 RIVET, SOLID, COUNTERSUNK 100

DEG, PRECISSION HEAD, 5/32 IN

OD, 5/16 IN LONG

MS20470AD4-4

MIL-S-8802

RIVET, SOLID, UNIVERSAL HEAD

SEALING COMPOUND,

TEMPERATURE RESISTANT, HIGH

ADHESION

211-60037-08 SCREW, MACHINE, PAN HEAD,

CROSS-RECESSED, BRASS, 0.1380-

32 UNC-2A

115-00481-10 RACK, INSTALL, MODIFIED, GMU 44

011-00870-10 GMU 44 MAGNETOMETER

MANUFACTURER

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

31-00-00


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Figure 31-01

GMU 44 MAGNETOMETER INSTALLATION, EXPLODED VIEW

(Reference Table 31-01)

31-00-00


190-00792-12 Rev 1

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6

7

4

5

8

9

10

11

12

13

ITEM

NUMBER

1

2

3

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

RH

QTY

LH

QTY

PART NUMBER DESCRIPTION

-

2

1 115-01757-00 BRACKET, SUPPORT, AFT, LH SHELF,


- 115-01755-00 BRACKET, SUPPORT, RH SHELF, FAA-

PMA, EUROCOPTER AS350

-

8

8

-

1

1 115-01756-00 BRACKET, SUPPORT, FWD, LH SHELF,


1

-

115-01758-00

115-01759-00

8

8

AN3-3A

AN3-4A

8 8 MS21042-3

24 24 NAS1149F0332P

8 8 MS21075-3

RH SHELF

LH SHELF

BOLT

BOLT

NUT

WASHER

NUTPLATE

16 16 MS20426AD3-3

- 1 NAS43DD3-24

- 2 MS21266-1

RIVET

SPACER

GROMMET

MANUFACTURER

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

31-00-00


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Page 48 of 80

Figure 31-02

RH SHELF INSTALLATION


31-00-00


190-00792-12 Rev 1

Page 49 of 80

Figure 31-03

LH SHELF INSTALLATION


31-00-00


190-00792-12 Rev 1

Page 50 of 80

ITEM NUMBER

3

4

1

2

5

6

RH

QTY

1

4

-

1

8

4


LH

QTY


1 190-00792-03 LH SHELF INSTALLATION

- 190-00792-03 RH SHELF INSTALLATION

1 011-00882-11

4 MS21075-3

GDC 74H ADC

NUTPLATE

8

4

MS20426AD3-3

AN525-10R8

RIVET

SCREW

MANUFACTURER

GARMIN

GARMIN

GARMIN

Figure 31-04

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

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


31-00-00


190-00792-12 Rev 1

Page 51 of 80

ITEM NUMBER

3

4

1

1

5

6

7


RH

QTY

LH

QTY


1

1

-

1

1

-

1

190-00792-03 LH SHELF INSTALLATION

190-00792-03 RH SHELF INSTALLATION

011-00868-20

5 5 MS21075-3

10 10 MS20426AD3-3

5 5 AN525-10R8

GRS 77H AHRS

1 115-00459-00 GRS 77 MOUNT RACK

NUTPLATE

RIVET

SCREW

MANUFACTURER

GARMIN

GARMIN

GARMIN

GARMIN

Figure 31-05

GRS 77H INSTALLATION LH, EXPLODED VIEW (SHOWN)

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


31-00-00


190-00792-12 Rev 1

Page 52 of 80

ITEM

NUMBER

3

4

5

1

2

Table 31-05 Part List for Figure 31-06


1

REF

2

2

2

M81714/67-18

M81714/60-22-05

AN525-10R7

NAS1149F0332P

MS21042-3

DESCRIPTION

MOUNTING TRACK

TERMINAL BLOCK

SCREW

WASHER

NUT

MANUFACTURER

Figure 31-06

TERMINAL BLOCK INSTALLATION, EXPLODED VIEW


31-00-00


190-00792-12 Rev 1

Page 53 of 80

ITEM

NUMBER

3

4

1

2



1

1

8

A/R

011-00978-00

115-01567-00

CR3213-4-03

MIL-S-8802

DESCRIPTION

GTP 59 OAT PROBE

DOUBLER

RIVET

SEALING COMPOUND

MANUFACTURER

GARMIN

GARMIN

CHERRYMAX

Figure 31-07

GTP 59 OAT PROBE INSTALLATON, EXPLODED VIEW


31-00-00


190-00792-12 Rev 1

Page 54 of 80

8

9

10

5

6

7

11

12

13

22

23

24

25

19

20

21

26

27

14

15

16

17

18

ITEM

NUMBER

1*

2*

3*

4*

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

QUANTITY

-01 -02 -03 -04

1 - - -

PART NUMBER

011-02764-01

DESCRIPTION

-

-

-

1

1

-

-

1

-

1

-

1

-

-

1

1

011-02764-02

011-02764-03

011-02764-04

011-01264-60

INSTRUMENT PANEL ASSEMBLY,

OPTION 1


OPTION 2


OPTION 3


OPTION 4

GDU 620 PFD/MFD

REF REF REF REF 5956-28-01 REV. A

1 1 1 1 B3500BA01

DIMMING CONTROL OVERLAY

V.E.M.D.

REF REF REF REF

REF REF - -

REF REF - -

704A47723068

EXISTING

C4E0118-01

ANNUNCIATOR PANEL

3-IN NR TACHOMETER

3-IN EYEBROW LIGHT

- REF - REF

- REF - REF

EXISTING

EXISTING

3-IN AIRSPEED INDICATOR

3-IN ALTIMETER INDICATOR

REF - REF - 3A43.22.35F.28.1.FU 2-IN ALTIMETER COUNTER DRUM

POINTER

REF - REF - MD25-200 2-IN AIRSPEED INDICATOR

-

-

- REF REF EXISTING

- REF REF 350A67-0159-20

- REF - REF

13 6 15 8

71450B23

MS35214-29

2-IN NR TACHOMETER

2-IN EYEBROW LIGHT

LED POST LIGHT

SCREW

2

2

6

5

2

-

-

3

-

6 6 6

2

6

2 2 2

6 6 6

15 11 13 9

7 - 7 -

MS35214-31

MS35214-33

MS35214-44

NAS1149DN632P

NAS1149DN832P

NAS620-6L

MS33737-14C

2 7 2 5 MS33737-16C

REF REF REF REF LED-40-17-HE-E0G3T

SCREW

SCREW

SCREW

WASHER

WASHER

WASHER

NUT

NUT

VIVISUN LED SWITCH

MANUFACTURER

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

AERO DYNAMIX

EUROCOPTER

EUROCOPTER

THOMMEN

MID-CONTINENT

EUROCOPTER

EUROCOPTER

AEROSPACE

OPTICS

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

31-00-00


190-00792-12 Rev 1

Page 55 of 80

Figure 31-08

INSTRUMENT PANEL INSTALLATION


31-00-00


190-00792-12 Rev 1

Page 56 of 80

Figure 31-09

ITEM 1, INSTRUMENT PANEL INSTALLATION


31-00-00


190-00792-12 Rev 1

Page 57 of 80

Figure 31-10



31-00-00


190-00792-12 Rev 1

Page 58 of 80

Figure 31-11



31-00-00


190-00792-12 Rev 1

Page 59 of 80

Figure 31-12



31-00-00


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Page 60 of 80

ITEM

NUMBER

1

2

3

4

5

6

7

QUANTITY

1

1

4

6

6

2

36


PART NUMBER

115-01760-01

161-02779-01

MS21061L08

MS21069-08

MS21071-06

MS21075-08

MS20426AD3-4

DESCRIPTION

OPTION 1 INSTRUMENT PANEL

FAA-PMA LABEL

NUTPLATE

NUTPLATE

NUTPLATE

NUTPLATE

RIVET

MANUFACTURER

GARMIN

GARMIN

Figure 31-13

OPTION 1, INSTRUMENT PANEL ASSEMBLY


31-00-00


190-00792-12 Rev 1

Page 61 of 80

ITEM

NUMBER

1

2

3

4

5

6

7

QUANTITY

4

6

6

1

1

2

36


PART NUMBER

115-01760-02

161-02779-02

MS21061L08

MS21069-08

MS21071-06

MS21075-08

MS20426AD3-4

DESCRIPTION


FAA-PMA LABEL

NUTPLATE

NUTPLATE

NUTPLATE

NUTPLATE

RIVET

MANUFACTURER

GARMIN

GARMIN

Figure 31-14



31-00-00


190-00792-12 Rev 1

Page 62 of 80

ITEM

NUMBER

1

2

3

4

5

6

7

QUANTITY

4

6

6

1

1

2

36


PART NUMBER

115-01760-03

161-02779-03

MS21061L08

MS21069-08

MS21071-06

MS21075-08

MS20426AD3-4

DESCRIPTION


FAA-PMA LABEL

NUTPLATE

NUTPLATE

NUTPLATE

NUTPLATE

RIVET

MANUFACTURER

GARMIN

GARMIN

Figure 31-15



31-00-00


190-00792-12 Rev 1

Page 63 of 80

ITEM

NUMBER

1

2

3

4

5

6

7

QUANTITY

4

6

6

1

1

2

36


PART NUMBER

115-01760-04

161-02779-04

MS21061L08

MS21069-08

MS21071-06

MS21075-08

MS20426AD3-4

DESCRIPTION


FAA-PMA LABEL

NUTPLATE

NUTPLATE

NUTPLATE

NUTPLATE

RIVET

MANUFACTURER

GARMIN

GARMIN

Figure 31-16



31-00-00


190-00792-12 Rev 1

Page 64 of 80

Table 31-12 List of Consumable Materials

DESCRIPTION

THREAD LOCK

ADHESIVE

Cleaning cloth, Low-Lint

Mineral Spirits, Cleaning Solvent

Alodine

Alodine

Paint Stripper

Polyamide Paint Primer

Dye Penetrant Kit

Acetone

Isopropyl Alcohol

Trichloroethane

Nylon Scouring Pad

240 Grit Sandpaper

320 Grit Sandpaper

240 Grit Aluminum Oxide Abrasive

Cloth

Sealant

Adhesive transfer tape 950 (2")

P/N

242

1300L

--

--

Alodine 1200

Iridite 14-2

Turco 5873

--

--

--

--

--

(3M) Scotchbrite 63

--

--

--

--

--

70-0060-3057-4

VENDOR/SPECIFICATION

LOCTITE

3M

Commercial

MIL-PRF-680, TYP II

OR ASTM-D235

--

--

--

--

--

ASTM-D329

TT-I-735

MIL-T-81533

3M

Commercial

Commercial

Commercial

Commercial

MIL-S-8802

3M

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Page 65 of 80

4. Troubleshooting guide

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.

Problem

Unit does not power up – blank screen.

All expected configuration pages are not displayed.

The GDC OAT probe type shows up as UNKNOWN

When loading software, the

LRU software is not being displayed on the SOFTWARE

UPLOAD page.

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

Vertical GPS deviation is not displayed on the GDU 620.

Unable to control the GPS course when in OBS mode.

Table 31-13 GDU 620 Troubleshooting Guide

Cause Solution

Improper wiring; circuit breaker open.

Ensure power is properly wired to the

GDU 620 and the circuit breaker is closed.

Unit intensity turned down.

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

Ensure that unit is not in manual intensity control mode with the intensity turned down.

Insert the Installer Unlock Card

P/N 010-00769-60 into the bottom slot of the GDU 620 and cycle power.

The RS-232 connection to the

GDC 74H is not working.

The software loader card is installed in the bottom slot of the

GDU 620.

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

Insert the loader card in the top slot and cycle power to the GDU.

The software loader card contains no information.

Repeat the process for making the software loader card.

The configuration module has not been updated.

Update the configuration module.

For 400W/500W Series units, the

ARINC 429 vertical deviation labels are not being transmitted.

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

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

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

GPS2.

Data is not being received from an ARINC 429 device.

ARINC 429 bus hi and low are swapped.

Verify wiring.

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Problem

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

MONITORING page)

Cause

Wrong device is connected to port on GDU 620.

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)

On the transmitting LRU, the

ARINC 429 transmitter speed is not set correctly.

Wiring is not correct.

Use correct ports (refer to interconnect details).

Solution

Set the ARINC 429 transmitter speed to correct speed.

Check for continuity/shorts and correct as required.

Attitude and heading on

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

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.

Heading red ‘X’ during air data ground testing

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.

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

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

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Alert Text

Table 31-14 GDU 620 Alert Troubleshooting Guide

Cause

AHRS1 GPS – AHRS 1 using backup GPS source.

AHRS1 GPS - AHRS is not receiving any GPS information

AHRS1 GPS – AHRS 1 operating in exclusively in no-

GPS mode.

AHRS is using the backup GPS information

AHRS is not receiving any GPS information.

AHRS is not receiving any GPS information.

AHRS1 GPS – AHRS 1 not receiving backup GPS information.

AHRS1 SRVC

AHRS1 TAS

AHRS is not receiving GPS information from GPS2.

AHRS magnetic field model should be updated. Appears on ground only.

AHRS is not receiving true airspeed from ADC.

Solution

Verify GPS1 power and check the wiring

Verify GPS power and check the wiring

Ensure that at least one GPS has acquired a valid position.

If GDU 620 does not have a valid position, verify wiring between GDU and

GPS receiver, and configuration of GDU

620 and GPS receiver.

If GDU has a valid GPS position, verify wiring between GDU and GRS. Also verify time mark wiring.

Verify GPS2 power and check the wiring

Update GRS 77H IGRF model (current model is with aviation database).

GDC not powered up. Close ADC C/B.

GDC not receiving input from GTP 59

OAT probe. Verify wiring is correct.

CAL LOST

CNFG MODULE

DATA LOST

FAN 1 FAIL

FAN 2 FAIL

Registry reports that it has lost calibration data.

The configuration module is inoperative.

Pilot stored data was lost. Recheck data and settings.

ARINC 429 connection from GDC 74H to

GRS 77H is not working. Verify wiring is correct.

Contact Garmin Technical Support.

Verify wiring to configuration module

Replace configuration module

Fan 1 has reported 0 RPM when it was powered with a PWM duty cycle higher than or equal to 10%

Fan 2 has reported 0 RPM when it was powered with a PWM duty cycle higher than or equal to 10%

Inspect the GDU fan for an obstruction.


Inspect the GDU fan for an obstruction.


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Page 68 of 80

Alert Text

GDL69 CONFIG

GDU CONFIG

GDU (1/2) COOLING

GDU (1/2) DB ERR

GDU (1/2) VOLTAGE

GEO LIMITS

GPS(1/2) FAIL

GPS(1/2) PPS Failure

GPS2 FPL USED

HDG FAULT

Cause

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

Solution

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

620 into the GDL 69.

Update the GDL 69 configuration using the GDU 620.

The GDL 69 configuration was updated using another LRU

(e.g. the GMX 200 or 400W/500W).

This error appears whenever the

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

Cycle power to the GDU. This error automatically clears on the second power up with a different configuration module.

Error in the configuration of the

GDU 620.

Specific GDU has poor cooling, and power usage is being reduced.

Ensure fans on indicated GDU are functioning

Error in specific database, where

GDU (1/2) DB denotes specific database.

GDU supply voltage is below 12

VDC.

Location is too far north/south for

GRS 77H magnetic compass.

Ensure fans on indicated GDU are not obstructed

Verify the correct card is installed, reload the DB on the card.

Increase the voltage above 12VDC.

No GPS1 or GPS2 data is available.

Ensure GPS (1/2) is turned on

Verify RS-232 wiring from the GPS to the

GDU 620.

This alert will be set if the PPS 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.

Ensure GPS (1/2) is turned on

Verify 1PPS wiring from the GPS to the

GDU 620.

The GPS1 has failed and GPS2 is configured and operating.

AHRS magnetometer fault has occurred.

GRS 77H not receiving information from

GMU 44. Verify wiring to GMU 44.

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Page 69 of 80

HDG LOST

Alert Text

<LRU> SERVICE

Cause

Heading from the GRS77/ GMU 44 is not valid.

Specific LRU should be serviced, where <LRU> denotes specific LRU.

Solution

Caused by a local magnetic anomaly. No action required.

Return indicated LRU to Garmin for service.

MANIFEST

NAV1 FAIL

NAV2 FAIL

SIMULATOR

SVT DISABLED - Out of available terrain region.

SVT DISABLED - Terrain DB resolution too low.

SW MISMATCH

TRAFFIC FAIL

TRK LOST

TRK TRAFFIC

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 match the values being reported by that LRU.

No navigation receiver 1 data.

No navigation receiver 2 data.

The simulator mode is active.

Location is beyond region covered by terrain database.

A 30 arc-second terrain database is being used.

GDU software version strings do not match.

The traffic information system has failed.

Ensure the manifest is properly configured.

Update the LRU software to match the manifest

Update the manifest to match the LRU software

Ensure P6202-36 is not grounded.

Update the Supplemental Data card with the 9 arc-second terrain database.

Verify the correct SW is loaded

The GDU 620 is not receiving traffic information from the traffic sensor. Verify wiring between GDU 620 and traffic sensor.

The GDU 620 is receiving information from the traffic sensor, but the information is indicating that the traffic sensor has failed. Troubleshoot traffic system.

GPS1 TRK lost. HSI defaulted to

GPS2 TRK.

Heading Lost. Traffic is now based on track.

See HDG errors.

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Page 70 of 80

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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Section 98-10-00 Wiring Diagrams

G500H EFIS System Wiring

98-10-00


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98-10-00


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98-10-00


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Section 98-20-00 Pitot-Static System Schematic

98-20-00


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Page 80 of 80

Garmin AS_350B2/B3 Instruction Manual

Instructions for Continued Airworthiness for the Garmin G500H Installation 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

Rev. Date

Description of Change

Table of Contents

CHAPTER 1

Section 01-00-00 Introduction

CHAPTER 4

Section 04-00-00 Airworthiness Limitations

CHAPTER 5

Section 05-00-00 Continued Airworthiness Inspections

Section 05-20-10 Continued Airworthiness Scheduled Inspections

Section 05-20-20 Continued Airworthiness Special Inspections

CHAPTER 6

Section 06-00-00 Dimensions and Access

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

Section 12-20-00 Calibration Requirements

CHAPTER 20

Section 20-00-00 Standard Practices

Section 20-10-00 Torques Maintenance Practices

Section 20-30-00 Painting Maintenance Practices

Section 20-40-00 Corrosion Control Maintenance Practices

Section 20-50-00 Mechanical Fastener Sealing Methods

Section 20-90-00 Dye Penetrant Inspection Methods

CHAPTER 31

Section 31-00-00 Instruments

CHAPTER 98

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

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Garmin

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