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

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

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 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 2 of 80

Section 98-20-00

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

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 3 of 80

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.

01-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 4 of 80

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.

05-00-00

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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

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 7 of 80

05-00-00

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

05-20-10

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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.

05-20-10

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

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.

05-20-10

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 13 of 80

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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Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 15 of 80

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).

05-20-20

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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.

06-00-00

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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.

06-00-00

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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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Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 21 of 80

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.

06-00-00

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 22 of 80

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

Instructions for Continued Airworthiness 190-00792-12 Rev 1 for the Garmin G500H Installation in Eurocopter AS350 Page 23 of 80

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

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