Garmin Bell 206, Bell 407 Instruction Manual

G500H Flight Display System

Instructions for Continued Airworthiness

Bell 206A/B Series

Reg. No.____________ S/N_______________

STC SR02295LA

Dwg. Number:

190-01150-11 Rev. 2

Garmin International, Inc.

1200 E. 151st Street

Olathe, Kansas 66062 USA

Record of Revision

Rev. Date Description of Change

1 02/11/10 Initial Release
2 04/12/10 Update to latest installation data revisions; changed VFR placard text;

updated equipment station locations.

1.

INTRODUCTION ................................................................................................................... 3

1.1 Purpose ................................................................................................................. 3

1.2 Scope .................................................................................................................... 3

1.3 Document Control ................................................................................................. 3

1.4 Permission to Use Certain Documents ................................................................. 3

1.5 Definitions ............................................................................................................. 3

2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 4

2.1 Introduction ........................................................................................................... 4

2.2 Description of Alteration ........................................................................................ 5

2.3 Control, Operating Information ............................................................................. 8

2.4 Servicing Information ............................................................................................ 8

2.5 Periodic Maintenance Instructions ........................................................................ 8

2.6 Troubleshooting Information ................................................................................. 9

2.7 Removal and Installation Information ................................................................... 13

2.8 Diagrams ............................................................................................................... 18

2.9 Special Inspection Requirements ......................................................................... 18

2.10 Application of Protective Treatments .................................................................... 18

2.11 Data Relative to Structural Fasteners ................................................................... 18

2.12 Special Tools ........................................................................................................ 18

2.13 Additional Instructions ........................................................................................... 19

2.14 Overhaul Period .................................................................................................... 19

2.15 ICA Revision and Distribution ............................................................................... 19

2.16 Assistance............................................................................................................. 19

2.17 Implementation and Record Keeping ................................................................... 19

3. AIRWORTHINESS LIMITATIONS ........................................................................................ 19

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 2 of 19

1. INTRODUCTION

1.1 Purpose

This document is designed for use by the installing agency of the Garmin G500H PFD/MFD System as
Instructions for Continued Airworthiness in response to Title 14 CFR Part 27.1529, Part 27 Appendix A..
This ICA includes information required by the operator to adequately maintain the Garmin G500H
system installed under STC SR02295LA.

1.2 Scope

This document identifies the Instruction for Continued Airworthiness for the modification of the rotorcraft
for installation of the Garmin G500H PFD/MFD System installed under STC SR02295LA.

1.3 Document Control

This document shall be released, archived, and controlled in accordance with the Garmin document
control system. When this document is revised, refer to Section 2.15 for information on how to gain FAA
acceptance or approval and how to notify customers of changes.

1.4 Permission to Use Certain Documents

Permission is granted to any corporation or person applying for approval of a Garmin G500H system to
use and reference appropriate STC documents to accomplish the Instructions for Continued
Airworthiness and show compliance with STC engineering data. This permission does not con strue
suitability of the documents. It is the responsibility of the applicant to determine the suitability of the
documents for the ICA.

1.5 Definitions

The following terminology is used within this document:

1) ACO: Aircraft Certification Office

2) ADC: Air Data Computer

3) AEG: Aircraft Evaluation Group

4) AHRS: Attitude Heading Reference System

5) CFR: Code of Federal Regulations

6) FAA: Federal Aviation Administration

7) ICA: Instructions for Continued Airworthiness

8) MFD: Multi-Function Display

9) PFD: Primary Flight Display

10) PMI: Principle Maintenance Inspector

11) STC: Supplemental Type Certificate

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 3 of 19

2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

2.1 Introduction

Content, Scope, Purpose and Arrangement: This document identifies the Instructions for

Continued Airworthiness for the modification of the
rotorcraft by installation of the Garmin G500H
PFD/MFD System.

Applicability: Applies to Bell models 206A, 206A-1 and 206B

rotorcraft altered by installation of the Garmin

G500H PFD/MFD System.
Definition of Abbreviations: See Section 1.5
Precautions: None
Units of measurement: None
Referenced publications:

Additional Maintenance Data: Garmin 190-01150-41 Rev. 2 “INSTALLATION,

Garmin 190-01150-06 Rev. 1 “G500H Rotorcraft

STC Installation Manual” or later FAA Approved

Revisions

Garmin 190-01150-40 Rev. 1 “GENERAL

ARRANGEMENT, G500H SYSTEM, BELL 206 A/B

ROTORCRAFT” or later FAA Approved Revisions

G500H SYSTEM, BELL 206A/B ROTORCRAFT” or

later FAA Approved Revisions

Garmin 005-W0222-00 Rev. 3 “G500H MAIN

WIRE HARNESS ASSEMBLY” or later FAA

Approved Revisions

Garmin 005-W0222-01 Rev. 1 “G500H NAV 1

HARNESS ASSEMBLY” or later FAA Approved

Revisions

Garmin 005-W0222-02 Rev. 1 “G500H GPS 2

HARNESS ASSEMBLY” or later FAA Approved

Revisions

Garmin 005-W0222-03 Rev. 1 “G500H NAV 2

HARNESS ASSEMBLY” or later FAA Approved

Revisions

Garmin 005-W0222-04 Rev. 1 “G500H WX

DATALINK HARNESS ASSEMBLY” or later FAA

Approved Revisions

Garmin 005-W0222-05 Rev. 1 “G500H IRIDIUM

DATALINK HARNESS ASSEMBLY” or later FAA

Approved Revisions

Garmin 005-W0222-06 Rev. 1 “G500H VIDEO

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 4 of 19

HARNESS ASSEMBLY” or later FAA Approved

Revisions

Garmin 005-W0222-07 Rev. 2 “G500H SERIAL

ALTITUDE HARNESS ASSEMBLY” or later FAA

Approved Revisions

Garmin 005-W0222-08 Rev. 1 “G500H TRAFFIC

HARNESS ASSEMBLY” or later FAA Approved

Revisions
Retention: This document, or the information contained within,

will be included in the rotorcraft’s permanent

records.

2.2 Description of Alteration

This STC upgrades existing avionics for the Bell 206A/B rotorcraft as summarized below.
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.

Rotorcraft modified under this G500H STC are restricted to VFR only, including rotorcraft that may not
have previously been restricted to VFR. To clarify this operation limitation, a placard with the text,
“APPROVED FOR DAY/NIGHT VFR” is required to be in the pilot’s view.

All installed G500H equipment is connected to a power bus that receives power as soon as the battery
master switch is turned on.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 5 of 19

Separate circuit breakers have been installed in the overhead circuit breaker panel for each for the GDU
620 (PFD), GRS 77H + GMU 44 (AHRS), and GDC 74H (ADC) as circled belo w:

COPILOT

HEADSET

PILOT

HEADSET

FLOATS

XPNDR COMNAV

TURNCABLEHOIST

INDCUTPOWER

OFF

PWR

ADCAHRSPFD

MKR

HAND

AUDIO/

MIKE

CARGO HTR HTR

HOOK CONT PWR

LDG INST PIT

LT LT LT

FUELBOOST

COCK

FUEL

SAS

SAS

CONT

INVTR

CAUTIONLTTOT

IND

ENG

FUEL

XMSN

AFT FWD

HYD GOV IGN

BOOST CONT ENG

OFF

POS LT

HTR

START

DIR

GYRO PITOT DEFOG

& ATT HEAT BLOWER

IND

QTY

INST LT

OFF BRT

HEAT

VENT

GEN

OFF

FIELD

OFF

BATOGEN

VALVE

START

ENG

TEMP

INDPRESS

ENG

HEAT

OFF

ANTI

COLL LT

GEN

RESET

OFF

F
F

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 6 of 19

The installed G500H equipment can be accessed as described below:

1

2

6

5

3

4

1. GDU 620: FS38.6, WL 43.3 Access or remove by removing the six screws in the bezel of the
GDU 620.

2. GDC 74H: FS32.8, WL 37.6 Access or remove by lowering instrument console at its hinge
point and removing the top instrument console cowling.

3. GRS 77H: FS60.4, WL20.0 (Secondary location) Access or remove by removing the cushion
from the co-pilots seat and the panel on top of the seat pedestal.

4. GRS 77H: FS151.4, WL54.7 (Primary location) Access or remove by opening the baggage
compartment and removing the access panel located on the ceiling of the baggage
compartment.

5. GMU 44: FS196.3, WL59.5 (Primary location) Access or remove by opening the baggage
compartment, removing the screws on the aft wall of the baggage compartment which hold
in place the plastic baggage compartment extension, then remove the baggage
compartment extension.

6. GMU 44: FS217.5, WL64.8 (Secondary location) Access or remove by removing the bolts
from the access panel on the pilots side of the aircraft at the juncture of the tail boom and
fuselage.

2.2.1 Weight and Balance Information

Weight and Balance Bell 206 A/B MOMENT ARM (IN) LOCATION
ITEM PART NUMBER WEIGHT (LB) LONGITUDINAL LATERAL PRIMARY SECONDARY

1

011-01264-501

2 011-00882-11 GDC 74 H (Unit Only) 1.70
3 011-00868-20 GRS 77H (Unit Only) 2.80

4 011-00870-10 GMU 44 (Unit Only) 0.35 196.3 0.0

[1] A rotorcraft weight and balance is required after installation of the G500H system. Refer to STC

installation manual P/N 190-01150-06 for additional information, including overall size and center of

gravity location of all LRUs.
[2] The longitudinal arm is measured in terms of the fuselage station (FS) number.
[3] The lateral arm is measured in terms of the butt line (BL). The centerline of the helicopter is BL0.00.

The moment arms to the left side (looking forward) are negative (-) and the moment arms to the right

side are positive (+).

1

Either 011-01264-50 or 011-01264-60 units are acceptable

GDU 620 (Unit Only) 6.38
GDU 620 (Installed with rack and

connector)
GDC 74H (Installed with connector) 1.92
GRS 77H (Installed with rack and

connector)

GMU 44 (Installed with rack and

connector)

7.04

3.46

0.50 217.5 0.0

38.6

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 7 of 19

2.3 Control, Operating Information

See the G500H Pilot’s Guide or the G500H STC Installation Manual, listed under the reference
documentation in paragraph 2.1 of this document, for system operation and self-test information.

2.4 Servicing Information

None. In the event of system failure, troubleshoot the G500H system in accordance with Section 2.6
Troubleshooting Information.

2.5 Periodic Maintenance Instructions

Maintenance of the components installed by this STC is on condition, except as noted in the following
table.

Item Interval Description/Procedure

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

GRS 77H AHRS 5 years

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.

GDC 74H ADC On condition

GDU 620, GRS 77H,
GDC 74H, GMU 44, GTP
59

12 Calendar
Months

Per Part 43 Appendix E, paragraph (b)(2), the GDC 74H must be
checked using a test procedure equivalent to Part 43 Appendix E,
paragraph (b)(1) with the following exception:

The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric
Scale Error) are not applicable because the digital outputs of the
GDC 74H are not susceptible to these types of errors.

Conduct a visual inspection (look for signs of wear, deterioration,
or damage to wires, backshells, or connectors) on units and their
wire harnesses to ensure installation integrity:

1. Gain access to LRU (see General Arrangement Drawing
for LRU locations)

2. Inspect each unit for security of attachment.

3. Inspect all knobs and buttons for legibility.

4. Inspect condition of wiring, routing and
attachment/clamping.

5. Inspect integrity of shield terminations.

6. Inspect for signs of corrosion on equipment and their rack
installations.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 8 of 19

Item Interval Description/Procedure

Perform an electrical bonding test for each listed LRU:

1. Gain access to the LRU (see General Arrangement
Drawing for LRU location)

2. Disconnect all harness connectors from the LRU

3. Measure the resistance between the LRU and a nearby
exposed portion of aircraft metallic structure

a. For the GDU 620, verify the resistance is less than

or equal to 40 milliohms

b. For the remaining LRUs, verify the resistance is

less than or equal to 20 milliohms

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

Repeat for each listed LRU.

GDU 620, GRS 77H,
GDC 74H, GMU 44, GTP
59

Every 2000
flight hours or
ten (10)
years,
whichever is
first

2.6 Troubleshooting Information

If error indications are displayed on the GDU 620 display unit, consult the Troubleshooting section
contained below:

2.6.1 G500H Troubleshooting

Table 2-1. GDU 620 Troubleshooting Guide

Problem Cause Solution

Unit does not power up –
blank screen.

All expected configuration
pages are not displayed.

The GDC OAT probe type
shows up as UNKNOWN

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.

Improper wiring; circuit breaker
open.

Unit intensity turned down.

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

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.

The software loader card contains
no information.

The configuration module has not
been updated.

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

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.

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.

Repeat the process for making the
software loader card.

Update the configuration module.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 9 of 19

Problem Cause Solution

Vertical GPS deviation is not
displayed on the GDU 620.

Unable to control the GPS
course when in OBS mode.

Data is not being received
from an ARINC 429 device.

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

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

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

ARINC 429 bus hi and low are
swapped.

Wrong device is connected to port
on GDU 620.

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

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

Verify wiring.

Use correct ports (refer to interconnect
details).

Data is not being received
from an ARINC 429 device.

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

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

Heading red ‘X’ during air
data ground testing

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

Wiring is not correct.

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.

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

Set the ARINC 429 transmitter speed to
correct speed.

Check for continuity/shorts and correct as
required.

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

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

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 10 of 19

2.6.2 G500H Alerts

The G500H will display a number of alerts on the GDU 620 MFD. These are listed in the following table.

Table 2-2. GDU 620 Alert Troubleshooting Guide

Alert Text Cause Solution

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 no­GPS mode.

AHRS1 GPS – AHRS 1 not
receiving backup GPS
information.

AHRS1 SRVC

AHRS1 TAS

AHRS is using the backup GPS
information

AHRS is not receiving any GPS
information.

AHRS is not receiving any GPS
information.

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.

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.
ARINC 429 connection from GDC 74H to

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

CAL LOST

CNFG MODULE

DATA LOST

FAN 1 FAIL

G500H Flight Display System 190-01150-11 Rev. 2

Registry reports that it has lost
calibration data.

The configuration module is
inoperative.

Pilot stored data was lost. Recheck
data and settings.

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

Contact Garmin Technical Support.

Verify wiring to configuration module
Replace configuration module

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

Instructions for Continued Airworthiness Bell 206A/B Series Page 11 of 19

Alert Text Cause Solution

FAN 2 FAIL

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.
Contact Garmin Technical Support.

GDL69 CONFIG

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

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

GDU CONFIG

This error appears whenever the
GDU is replaced with a GDU that
was configured for a different
installation.

Error in the configuration of the
GDU 620.

GDU (1/2) COOLING

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

GDU (1/2) DB ERR

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

GDU (1/2) VOLTAGE

GDU supply voltage is below 12
VDC.

GEO LIMITS

Location is too far north/south for
GRS 77H magnetic compass.

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

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.

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

Ensure fans on indicated GDU are
functioning

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.

Ensure GPS (1/2) is turned on
Verify RS-232 wiring from the GPS to the

GDU 620.

GPS(1/2) PPS Failure

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

Ensure GPS (1/2) is turned on
Verify 1PPS wiring from the GPS to the

GDU 620.

side will be specified in the error.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 12 of 19

Alert Text Cause Solution

GPS2 FPL USED

HDG FAULT

HDG LOST

<LRU> SERVICE

The GPS1 has failed and GPS2 is
configured and operating.

AHRS magnetometer fault has
occurred.

Heading from the GRS77/ GMU 44
is not valid.

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

GRS 77H not receiving information from
GMU 44. Verify wiring to GMU 44.

Caused by a local magnetic anomaly. No
action required.

Return indicated LRU to Garmin for
service.

MANIFEST

NAV1 FAIL No navigation receiver 1 data.
NAV2 FAIL No navigation receiver 2 data.
SIMULATOR The simulator mode is active.
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.

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.

GPS1 TRK lost. HSI defaulted to
GPS2 TRK.

Heading Lost. Traffic is now based
on track.

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.

See HDG errors.

2.7 Removal and Installation Information

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

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 13 of 19

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.

2.7.1 GDU™ 620 Unit

2.7.1.1 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.

2.7.1.2 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.

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 m odule
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.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 14 of 19

2.7.1.3 Return to Service
After removing and reinstalling the GDU 620 per the instructions above, a simple return-to-service check

should be performed.

1. Power up the GDU 620 and all interfaced systems in normal mode.

2. Verify that there are no red-Xs and that no alerts are present. If red Xs or alerts are present,
troubleshoot using Section 2.6 of this ICA.

2.7.2 GRS 77H Unit

2.7.2.1 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)

2.7.2.2 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.

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 Table 2-3 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 Table 2-3 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
Table 2-3.

2.7.2.3 Return to Service
After removing and reinstalling the GRS 77H, 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 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

2.6 of this ICA.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 15 of 19

Table 2-3. GRS 77H Calibration Criteria

Condition

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.

GRS 77H

Pitch/Roll

Offset

Calibrations Required

GRS/GMU

Magnetic

Calibration

See Section 5

of the G500H STC
Installation Manual

None Required.

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
removed and/or mounting tray bolts
WERE loosened.

GRS 77H AHRS Configuration Module
was replaced.

X

X X X

X

X

2.7.3 GMU 44 Unit

2.7.3.1 Removal

1. Gain access to the GMU 44 magnetometer.

2. Unscrew the three screws that hold the GMU 4 4 to its mounting rack.

3. Carefully lift the GMU 44 from the rack.

4. Disconnect the wiring harness.

2.7.3.2 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 includ e
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 th e 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).

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 16 of 19

Return to Service

After removing and reinstalling the GMU 44, 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 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

2.6 of this ICA.

2.7.4 GDC 74H Unit

2.7.4.1 Removal

1. Disconnect the pitot/static plumbing from the rear of the unit. Disconnect the single connector.

2. Remove the two (2) screws on the mounting plate near the pitot/st atic ports. Loosen the other two
(2) screws.

3. Carefully remove the unit from its mounting location.

2.7.4.2 Installation

1. Place the unit in the mounting tray.

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

3. Connect the pitot/static plumbing.

4. Inspect the connector and pins for damage. Repair an y damage.

5. 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

2.7.4.3 Return to Service
After removing and reinstalling the GDC 74H, the following return-to-service checks must be performed.

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

2.6 of this ICA.

4. Perform a leak check of the pitot-static system and observe the airspeed, altitude, and vertical
speed for proper operation.

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 17 of 19

2.8 Diagrams

Rotorcraft specific LRU locations and wire routing diagrams are contained in the Garmin Reference
Publications listed in Section 2.1 of this document. Point to point wiring diagrams are in Appendix D of
the G500H STC Installation Manual. Refer to the G500H Post-Installation Checkout Log retained in the
rotorcraft permanent records for a list of the interfaced equipment and port configurations.

2.9 Special Inspection Requirements

2.9.1

Post-Lightning Strike Inspection

In the event of a suspected or actual lightning strike to the aircraft, the GTP 59
OAT Probe and its associated installation shall be inspected.

The probe and the surrounding installation shall be inspected to ensure that there is no stru ctural
damage around the areas where lightning may have attached. If there is visible sign of damage to the
probe then it must be replaced.

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

2.10 Application of Protective Treatments

None, N/A.

2.11 Data Relative to Structural Fasteners

Refer to the following table for data on the location, type, and torque values for structural fasteners.

Location

(seeGeneralArrangement

Drawing)

6‐32Screw

12‐15inch‐pounds

FASTENERTYPEANDTORQUE

8‐32Screw

12‐15inch‐pounds

10‐32Screw

22‐25inch‐pounds

NUT,5/16",HEX,SKIRT

100±20inch‐pounds

InstrumentPanel,
Instruments

X X 

GDU620 X  

GRS77H XX

GDC74H  X X

GMU44 X X 

GTP59 X

2.12 Special Tools

For electrical bonding testing, a milliohm meter is required.
G500H Flight Display System 190-01150-11 Rev. 2

Instructions for Continued Airworthiness Bell 206A/B Series Page 18 of 19

2.13 Additional Instructions

None

2.14 Overhaul Period

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. See the troubleshooting section contained in the G500H STC Installation
Manual, listed under reference documentation in paragraph 2.1 of this document.

2.15 ICA Revision and Distribution

To revise this ICA, a letter must be submitted to the ACO along with the revised ICA. The ACO will
obtain AEG acceptance, and approve any revision to the Airworthiness Limitations in Section 3. After
FAA acceptance/approval, Garmin will release the revised ICA for customer use, and provide any
required notification of the revision.

The latest revision of this document will be available through any Garmin dealer or from Garmin
customer assistance. A Garmin Service Bulletin, describing ICA revision, will be sent to dealers if
revision is determined to be significant.

2.16 Assistance

FAA Flight Standards Inspectors or the certificate holder’s PMI have the required resources to respond
to questions regarding this ICA. In addition, the customer may refer questions regarding this equipment
and its installation to the manufacturer, Garmin. Garmin customer assistance may be contacted during
normal business hours via telephone [phone] or email from the Garmin web site at
www.garmin.com.

2.17 Implementation and Record Keeping

Modification of an rotorcraft by this Supplemental Type Certificate obligates the rotorcraft operator to
include the maintenance information provided by this document in the operator’s rotorcraft maintenance
manual and/or the operator’s rotorcraft scheduled maintenance program.

3. AIRWORTHINESS LIMITATIONS

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

G500H Flight Display System 190-01150-11 Rev. 2
Instructions for Continued Airworthiness Bell 206A/B Series Page 19 of 19