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Garmin G500H Operating instructions

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Instructions for Continued Airworthiness
for the Garmin G500H System in Airbus AS350 and EC130
Garmin Ltd. Or its subsidiaries
c/o Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Dwg. Number:
190-01150-22 Rev. 1
REV.
DATE
DESCRIPTION OF CHANGE
1
02/11/2020
Initial Release
COPYRIGHT © 2020 Garmin Ltd. or its subsidiaries. All rights reserved.
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 2 of 51
TABLE OF CONTENTS
CHAPTER 1 ............................................................................................................................................................... 3
Section 01-00-00 Introduction .................................................................................................................................. 3
CHAPTER 4 ............................................................................................................................................................... 3
Section 04-00-00 Airworthiness Limitations ................................................................................................. 4
CHAPTER 5 ............................................................................................................................................................... 5
Section 05-00-00 Continued Airworthiness Inspections ........................................................................... 5
Section 05-20-10 Continued Airworthiness Scheduled Inspections ..................................................... 7
Section 05-20-20 Continued Airworthiness Special Inspections ........................................................ 12
CHAPTER 6 ............................................................................................................................................................ 13
Section 06-00-00 Dimensions and Access ..................................................................................................... 13
CHAPTER 8 ............................................................................................................................................................ 18
Section 8-00-00 Weight and Balance Information .................................................................................. 18
CHAPTER 12 .......................................................................................................................................................... 19
Section 12-00-00 Servicing Maintenance Practices .................................................................................. 19
Section 12-10-00 Return-to-Service Practices ............................................................................................ 20
Section 12-20-00 Calibration Requirements ............................................................................................... 21
CHAPTER 20 .......................................................................................................................................................... 22
Section 20-00-00 Standard Practices .............................................................................................................. 22
Section 20-10-00 Torques Maintenance Practices .................................................................................... 23
Section 20-30-00 Painting Maintenance Practices .................................................................................... 27
Section 20-40-00 Corrosion Control Maintenance Practices ................................................................ 28
Section 20-50-00 Mechanical Fastener Sealing Methods ....................................................................... 31
Section 20-90-00 Dye Penetrant Inspection Methods ............................................................................. 32
CHAPTER 31 .......................................................................................................................................................... 33
Section 31-00-00 Instruments ........................................................................................................................... 33
Section 98-00-00 Wiring Diagrams and Pitot-Static System Schematics ......................................... 49
Section 98-10-00 Wiring Diagrams.................................................................................................................. 50
Section 98-20-00 Pitot-Static System Schematic ....................................................................................... 51
01-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 3 of 51
CHAPTER 1
Section 01-00-00 Introduction
This document provides the Instructions for Continued Airworthiness for the G500H Flight
Display System as installed in Airbus Helicopters AS 350 B2, AS 350 B3 and EC 130 B4. This
document satisfies the requirement for continued airworthiness as required by 14 CFR 27.1529
and Part 27 Appendix A. Modification of an aircraft by STC SR02295LA obligates the aircraft
operator to include the maintenance information provided by this document in the operator’s
Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program, if
applicable.
The contents of this ICA are limited to the support of equipment installed in accordance with
STC SR02295LA, which includes the GDC 72H Air Data Computer (ADC), GRS 79H Attitude and
Heading Reference System (AHRS), and GSU 75H Air Data, Attitude and Heading Reference
System (ADAHRS), using installation data from 190-01150-07, Installation Manual Addendum
G500H Part 27 AML STC. STC SR02295LA specifies that the G500H Flight Display System must
be installed in accordance with STC SR09575RC or SR09576RC as applicable, prior to installing
these sensors. The instructions contained within this document supplement the existing ICA
and system-level maintenance instructions contained within in the following reference
documents:
• 190-00792-12, Instructions for Continued Airworthiness for the Garmin G500H Installation
in Eurocopter AS350, for G500H system installed per STC SR09575RC
• 190-01527-15, Instructions for Continued Airworthiness for the Garmin G500H Installation
in Eurocopter EC130, for G500H system installed per STC SR09576RC
This document is required for maintaining the continued airworthiness of the aircraft. Garmin
Dealers may obtain the latest revision of this document at the Garmin Dealer Resource Center,
https://dealers.garmin.com. Dealers are notified of manual revision changes by way of a Garmin
Service Bulletin. Owners and operators may obtain the latest revision of this document at
www.flyGarmin.com or by contacting a Garmin dealer. Garmin contact information is available at
www.flyGarmin.com.
05-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 5 of 51
CHAPTER 5
Section 05-00-00 Continued Airworthiness Inspections
1. General
This chapter contains time limit intervals for the Component Overhaul Schedule and Scheduled
Inspections for the G500H Installation. This chapter is to be added to the approved scheduled
inspection for the rotorcraft.
2. Component Overhaul Schedule
The system does not require overhaul at a specific time period. Power on self-test and
continuous BIT will monitor the health of the G500H system. If any LRU indicates an internal
failure, the unit may be removed and replaced.
3. Scheduled Inspections Overview
The G500H Installation requires a 90 Day Inspection that must be performed 90 days after
installation and then afterwards within 90 days of the last G500H Installation 90 day inspection.
The 90 Day Inspection requirements are specified in Table 5-1.
The G500H Installation requires an Annual Inspection that must be performed within 1 year (12
months) of initial installation and then afterwards within 1 year (12 months) of the last G500H
Installation annual inspection. The annual inspection requirements are specified in Table 5-2.
The G500H Installation requires a 5 Year Inspection that must be performed within 60 months
of initial installation and then afterwards within 60 months of the last G500H Installation
inspection. The 5 Year Inspection requirements are specified in Table 5-3.
The G500H Installation requires a 10 Year/2000 Flight Hours Inspection that must be performed
within 120 months or 2000 flight hours, whichever occurs first, of initial installation and then
afterwards within 120 months or 2000 flight hours, whichever occurs first, of the last G500H
Installation 10 year/2000 flight inspections. The 10 Year/2000 Flight Hour Inspection
requirements are specified in Table 5-4.
4. Special Inspection Practices
Conditions may arise from incidents or accidents that may warrant additional inspection requirements.
A Special Inspection is required if the aircraft is involved in a hard landing or is subjected to total
immersion in water. If either of these conditions occurs, the G500H Installation must be inspected using
the same procedures called out in the Annual Inspection Procedures in Table 5-2.
05-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 6 of 51
5. Definitions and Acronyms
The following is short descriptions of words and terms used in the procedures for the required
scheduled inspections.
• Examine – Look carefully to find the condition of the component. Find how that condition
is related to a specific standard.
• Condition – The state of an item or component compared to a known standard.
• Standard – A specified rule or measure that is used to find the condition of a component.
• Damage – Physical deterioration of a component.
• Inspection – A procedure that includes checking, inspecting, and examining a system or
component.
• Scheduled Inspection – An inspection procedure that must occur at a specified calendar
interval or at specified operational time intervals. Scheduled Inspections are required to
help ensure the rotorcraft stays airworthy.
• Maintenance – The servicing and / or repair of a rotorcraft, a system, or a component that
keeps it serviceable.
• Security – Term used for inspection of hardware and components to make sure they are
properly attached and tightened.
Acronyms
FOV-
Field of View
ICA-
Instructions for Continued Airworthiness
PFD-
Primary Flight Display
MFD-
Multifunction Display
VOM-
Volt Ohm Meter
GDC-
Garmin Data Computer
GRS-
GSU-
Garmin Reference System
Garmin Sensing Unit
GMU-
Garmin Magnetometer Unit
GDU-
Garmin Display Unit
OAT-
Outside Air Temperature
GTP-
Garmin Temperature Probe
ADC-
Air Data Computer
STC-
Supplemental Type Certificate
AHRS-
Attitude Heading Reference System
ADAHRS
Air Data and Attitude Heading Reference System
05-20-10
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 7 of 51
Section 05-20-10 Continued Airworthiness Scheduled Inspections
1. General
This section contains requirements for scheduled inspections and a list of special tools required
to perform these inspections. If any part of the installation appears to be functioning
improperly, consult the troubleshooting guide. If a major component is damaged or continues
to malfunction, the component in question should be returned to the manufacturer for
replacement.
2. Scheduled Inspection Program
The G500H system requires scheduled inspections to maintain continued airworthiness. Every
effort should be made to perform the inspections with the aircraft placed in a clean, well-lit
environment. There are four different scheduled inspections of the G500H system.
a) 90 Day Inspection
The 90 day inspection is performed every 90-day period of calendar elapsed time, regardless
of hours of operation. The requirements of the 90-day inspection are specified in Table 5-1.
b) 1 Year (Annual) Inspection
The 1 year (annual) inspection is performed every 1 year period of calendar elapsed time,
regardless of hours of operation. The requirements of the 1 year (annual) inspection are
specified in Table 5-2.
c) 5 Year Inspection
The 5 year inspection is performed every 5 year period of calendar elapsed time, regardless
of hours of operation. The requirements of the 5 year inspection are specified in Table 5-3.
d) 10 Year / 2000 Flight Hours
The 10 year /2000 Flight Hour inspection is performed at a 10 year period of calendar elapsed
time, or at 2000 flight hours of operation, whichever occurs first. The requirements of the 10
year/2000 flight hour inspection are specified in Table 5-4.
05-20-10
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 8 of 51
3. Tools and Special Tools for Scheduled Inspection
Adjustable ball swivel mirror and bright flashlight and / or drop light are standard requirements
for doing inspections, although they are not necessarily considered special tools. These items
should be used freely and frequently to enhance inspection quality and help ensure
discrepancies are not missed. It is important to have adequate lighting for all phases of the
inspection.
The special tools necessary for the G500H inspection are listed as follows:
a) Milliohm meter with an accuracy of ± 0.1 milliohms or better (for electrical bonding
testing).
Table 5-1. 90-Day Inspection
Registration No.
Serial No.
Helicopter Total Hours
Requirement
Initial
1. Review Airworthiness Directives.
Requirement
Initial
1. Access the GDC 72H / GSU 75H (reference Section 06-00-00 Dimensions and Access).
Drain the pitot-static system by removing the safety wire, nut and plug.
2. Re-install the plug, nut and safety wire.
3. Reference Section 12-10-00 Return-to-Service Practices for the air data unit.
05-20-10
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 9 of 51
Table 5-2. 1 year (Annual) Inspection
Registration No.
Serial No.
Helicopter Total Hours
1 Year (Annual) Scheduled Inspection
• The 1 Year inspection shall be accomplished at least at an interval of once every year of elapsed
calendar time.
• Initial each item after accomplishing the inspection.
• Record all findings and attach a copy of findings to this inspection form.
• After all findings are corrected, make maintenance record entry.
1 year (Annual) Pre-inspection
Requirement
Initial
1. Review Airworthiness Directives.
1 year (Annual) Inspection
Requirement
Initial
GRS 79H AHRS, or GSU 75H ADAHRS
1. Access the GRS 79H / GSU 75H (reference Section 06-00-00 Dimensions and Access).
Inspect unit and mount for physical damage cracks, and corrosion. Treat and repair
corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.
2. Conduct visual inspection of wires, backshells, and connectors looking for signs of wear,
deterioration or damage. Replace as required.
3. Inspect harness connections in back of unit. Secure any loose connections and support
unsecure wiring harness with additional clamping and / or tie rap supports if required.
4. Inspect unit for security of attachment. Replace the damaged or corroded hardware.
Replace any missing hardware. Torque all screws in accordance with Section 20-10-00
Torques Maintenance Practices.
Shelf Installation
1. Access Shelf Installation (reference Section 06-00-00 Dimensions and Access). Inspect
for physical damage cracks, and corrosion. Treat and repair corrosion as required in
Section 20-40-00 Corrosion Control Maintenance Practices.
2. Inspect hardware. Replace the damaged or corroded hardware. Replace any missing
hardware. Torque all screws in accordance with Section 20-10-00 Torques Maintenance
Practices.
GDC 72H ADC, or GSU 75H ADAHRS Installation
1. Access the GDC 72H / GSU 75H (reference Section 06-00-00 Dimensions and Access).
Inspect unit and mount for physical damage cracks, and corrosion. Treat and repair
corrosion as required in Section 20-40-00 Corrosion Control Maintenance Practices.
2. Inspect unit for security of attachment. Replace the damaged or corroded hardware.
Replace any missing hardware. Torque all screws in accordance with Section 20-10-00
Torques Maintenance Practices.
05-20-10
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 10 of 51
3. Conduct visual inspection of wires, backshells, and connectors looking for signs of wear,
deterioration or damage. Replace as required.
4. Inspect harness connections in back of unit. Secure any loose connections and support
unsecure wiring harness with additional clamping and / or tie rap supports if required.
5. Inspect Pitot-Static System for damage. Replace parts as needed. Complete the 90 Day
Inspection found in Table 5-1.
Table 5-3. -5 Year Inspection
Registration No.
Serial No.
Helicopter Total Hours
Requirement
Initial
1. Review Airworthiness Directives.
Requirement
Initial
1. The AHRS / ADAHRS unit utilizes an Earth magnetic field model which is updated once
every five years as part of the Aviation Database maintained by the owner/operator. If the
magnetic model is not current, the unit will issue an alert upon startup indicating the model
has expired. The model can be updated by inserting an aviation database card with an
updated IGRF model and powering on the system. A prompt will direct the user to press
ENT to update the model.
05-20-10
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 11 of 51
Table 5-4. 10 Year/2000 Flight Hour Inspection
Registration No.
Serial No.
Helicopter Total Hours
Requirement
Initial
1. Review Airworthiness Directives.
Requirement
Initial
GRS 79H AHRS, or GSU 75H ADAHRS
1. Access GRS 79H / GSU 75H, (Reference Section 06-00-00 Dimensions and Access) and
disconnect all harness connectors.
2. Measure the resistance between the GRS 79H / GSU 75H and a nearby exposed portion
of aircraft main metallic structure like a keel beam (not to other installed equipment or
shelves). Verify that the resistance is less than or equal to 5 milliohms for GRS 79H or GSU
75H. If greater must be restored to the value specified in the G500H Installation Manual
Addendum for GRS 79H or GSU 75H.
3. Reconnect all disconnected harness connectors and ensure they are secure.
GDC 72H ADC, or GSU 75H ADAHRS
1. Access GDC 72H / GSU 75H, (Reference Section 06-00-00 Dimensions and Access) and
disconnect all harness connectors.
2. Measure the resistance between the GDC 72H / GSU 75H and a nearby exposed portion
of aircraft main metallic structure like a keel beam (not to other installed equipment or
shelves). Verify that the resistance is less than or equal to 5 milliohms. If greater must be
restored to the value specified in the G500H Installation Manual Addendum for GDC 72H or
GSU 75H.
3. Reconnect all disconnected harness connectors and ensure they are secure
4. Post Inspection Maintenance Practices
After completion of the 1 Year (Annual) Inspection, 5 Year Inspection and 10 Year/2000 Flight
Hour Inspection and all discrepancies found have been corrected, the Return-to-Service
Practices (Reference Section 12-10-00 Return-to-Service Practices) should be accomplished in
preparation for returning the rotorcraft to service
05-20-20
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 12 of 51
Section 05-20-20 Continued Airworthiness Special Inspections
1. General
This section contains requirements for special inspections and includes the list of special tools
required to perform these inspections. If any part of the installation appears to be functioning
improperly, consult the troubleshooting guide. If a major component is damaged or continues
to malfunction, the component in question should be returned to the manufacturer for
replacement.
2. Special Inspection Program
Conditions may arise from incidents or accidents that may warrant additional inspection requirements.
A Special Inspection is required if the aircraft is involved in a hard landing or is subjected to total
immersion in water. If either of these conditions occurs, the G500H system must be inspected following
the Annual Inspection Procedures detailed in Table 5-2.
3. Tools and Special Tools for Special Inspections
Adjustable ball swivel mirror and bright flashlight and / or drop light are standard requirements
for doing inspections, although these may not necessarily be considered special tools. These
items should be used freely and frequently to enhance inspection quality and help ensure
discrepancies are not missed. It is important to have adequate lighting for all phases of the
inspection.
The special tools necessary for the G500H inspection are listed as follows:
a) Milliohm meter with an accuracy of ± 0.1 milliohms or better (for electrical bonding
testing).
06-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 13 of 51
CHAPTER 6
Section 06-00-00 Dimensions and Access
1. Access Methods
For removal and installation of specific components, reference Section 31-00-00 Instruments,
Removal and Replacement.
Caution: Use of power tools during removal or installation of
panels and attaching hardware may damage nut plates or
deform holes in composite doors, covers, panels, and fairings.
a) GDC 72H Air Data Computer
GDC 72H is located underneath the cabin floor between station 1790 and 2325 on the left or
right side of the aircraft depending on aircraft configuration. (Figure 6-1)
Refer to Figure 6-3 for location of GDC 72H if installed on a 115-01761-00 Remote LRU Shelf
(applicable to AS 350 B2, B3 models only).
Figure 6-1
Access Removal and Installation Methods
i. Removal
1. Remove the Center lower belly access panel.
2. Disconnect the retaining straps that prevent the panel from falling to the floor.
3. If aftermarket items are attached to the Center lower belly panel it may be
necessary to remove or disconnect them in order to remove the lower belly panel.
Consult the manufacturers Installation and Removal instructions for proper
removal of items.
ii. Installation
1. Re-install aftermarket items if removed to gain access to the air data computer.
Consult the manufacturers Installation and Removal instructions for proper
installation of items.
2. Connect the retaining strap that was disconnected to gain access to the air data
computer.
GDC 72H
STA
2325
REF
STA
1790
REF
06-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 14 of 51
3. Close the Center lower belly access panel and secure it.
b) GRS 79H AHRS
GRS 79H is located underneath the cabin floor between station 1790 and 2325 on the left or
right side of the aircraft depending on aircraft configuration. (Figure 6-2)
Refer to Figure 6-3 for location of GRS 79H if installed on a 115-01761-00 Remote LRU Shelf
(applicable to AS 350 B2, B3 models only).
Figure 6-2
Access Removal and Installation Methods
i. Removal
1. Remove the Center lower belly access panel.
2. Disconnect the retaining straps that prevent the panel from falling to the floor.
3. If aftermarket items are attached to the Center lower belly panel it may be
necessary to remove or disconnect them in order to remove the lower belly panel.
Consult the manufacturers Installation and Removal instructions for proper
removal of items.
ii. Installation
1. Re-install aftermarket items if removed to gain access to the air data computer.
Consult the manufacturers Installation and Removal instructions for proper
installation of items.
2. Connect the retaining strap that was disconnected to gain access to the air data
computer.
3. Close the Center lower belly access panel and secure it.
GRS 79H
STA
2325
REF
STA
1790
REF
06-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 15 of 51
Figure 6-3
06-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 16 of 51
c) GSU 75H ADAHRS
GSU 75H is located underneath the cabin floor between station 1790 and 2325 on the left side
of the aircraft. (Figure 6-4) Installation on 115-01761-00 Remote LRU Shelf is applicable to AS
350 B2, B3 models only.
Figure 6-4
Access Removal and Installation Methods
i. Removal
1. Remove the Center lower belly access panel.
2. Disconnect the retaining straps that prevent the panel from falling to the floor.
3. If aftermarket items are attached to the Center lower belly panel it may be
necessary to remove or disconnect them in order to remove the lower belly panel.
Consult the manufacturers Installation and Removal instructions for proper
removal of items.
ii. Installation
1. Re-install aftermarket items if removed to gain access to the ADAHRS computer.
Consult the manufacturers Installation and Removal instructions for proper
installation of items.
2. Connect the retaining strap that was disconnected to gain access to the air data
computer.
06-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 17 of 51
3. Close the Center lower belly access panel and secure it.
d) Shelf Installations
The shelf is located underneath the cabin floor between station 1790 and 2325 on the left
or right side of the aircraft depending on aircraft configuration. (Figure 6-5) GDC 72H / GRS
79H / GSU 75H are installed on the shelf.
Figure 6-5
Access Removal and Installation Methods
i. Removal
1. Remove the Center lower belly access panel.
2. Disconnect the retaining straps that prevent the panel from falling to the floor.
3. If aftermarket items are attached to the Center lower belly panel it may be
necessary to remove or disconnect them in order to remove the lower belly panel.
Consult the manufacturers Installation and Removal instructions for proper
removal of items.
ii. Installation
1. Re-install aftermarket items if removed to gain access to the air data computer.
Consult the manufacturers Installation and Removal instructions for proper
installation of items.
2. Connect the retaining strap that was disconnected to gain access to the air data
computer.
3. Close the Center lower belly access panel and secure it.
Shelf
Installatio
n
STA
2325
REF
STA
1790
REF
08-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 18 of 51
CHAPTER 8
Section 8-00-00 Weight and Balance Information
Drawing/Part No.
Description
Weight
CG Location (1)
115-01761-00
Shelf, Remote LRU (2)
0.55 lbs
(1)
190-01150-07
GDC 72H ADC
1.71 lbs
(1)
190-01150-07
GRS 79H AHRS
1.45 lbs
(1)
190-01150-07
GSU 75H ADAHRS
1.72 lbs
(1)
Note 1: Location of the GDC 72H, GRS 79H and GSU 75H can vary as described in the
190-01150-07 G500H STC Installation Manual Addendum.
Note 2: 115-01761-00 Remote LRU Shelf is applicable to AS 350 B2, B3 models only
12-00-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 19 of 51
CHAPTER 12
Section 12-00-00 Servicing Maintenance Practices
This chapter includes Return-to-Service Practices and Calibration Practices to be used with the G500H
Flight Display System.
a) GDU 620 cooling fan replacement
Over time, the GDU cooling fans may degrade in performance and need to be replaced in order
to continue adequately cooling the display system.
To replace the cooling fans, follow the replacement procedure below.
NOTE
The GDU cooling fan replacement kit (P/N K00-00683-10) must be obtained
from an authorized Garmin dealer. In order for the GDU warranty to remain
valid, this procedure must be accomplished by an authorized Garmin dealer.
1. Removal
a. Place the GDU 620 on a flat surface with the fan cover plate assembly facing up
b. Remove and discard the six Torx
®
screws with a T10 driver.
c. Lift fan cover assembly and disconnect fan connectors. Set aside.
2. Installation
a. Place replacement fan cover assembly over unit.
b. Connect both fan connectors, noting plate orientation to match recess in unit. Ensure
connectors are fully engaged.
c. Lower fan cover assembly into place while being careful to not pinch fan wires.
d. Secure fan cover assembly with six provided Torx® screws. Torque each screw to 8 in-lbs,
+/- 1 in-lb.
3. Return to Service
a. After removing and reinstalling the GDU 620 cooling fans, the return-to-service checks
must be performed (reference Section 12-10-00 Return-to-Service Practices).
12-10-00
Instructions for Continued Airworthiness 190-01150-22 Rev 1
for the Garmin G500H System in Airbus AS350 and EC130 Page 20 of 51
Section 12-10-00 Return-to-Service Practices
a) GDC 72H, or GSU 75H
1. Power up the G500H system with the GDU 620 in normal mode.
2. Verify that the GDU displays valid air data within approximately one minute.
3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Section
31-00-00 Troubleshooting .
4. Drain pitot-static system (reference Table 5-1 90 Day Inspection)
5. Perform a leak check of the pitot-static system and observe the airspeed, altitude, and vertical
speed for proper operation.
b) GRS 79H, or GSU 75H
1. Power up the G500H system with the GDU 620 in normal mode.
2. Verify that the GDU displays valid heading and attitude within approximately one minute. Note
that heading can remain invalid if the magnetometer is near a large metal structure such as a
hangar wall or if the magnetometer is close to a large ground power cart.
3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Section
31-00-00 Troubleshooting .
c) GDU 620 Cooling Fans
After removing and reinstalling the GDU cooling fans, the following return-to-service checks should
be performed.
1. Power up the G500H system with the GDU 620 in normal mode.
2. Verify that the newly-installed cooling fans are operating correctly.
3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Section
31-00-00 Troubleshooting .
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