Garmin | G500H | Garmin G500H G500H Flight Display System Instructions for Continued Airworthiness, Bell 206A/B Series

Garmin G500H G500H Flight Display System Instructions for Continued Airworthiness, Bell 206A/B Series
G500H Flight Display System
Instructions for Continued Airworthiness
Bell 206A/B Series
Reg. No.____________
S/N_______________
STC SR02295LA
Dwg. Number:
190-01150-11 Rev. 4
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev.
Date
Description of Change
1
2
02/11/10
04/12/10
3
11/24/15
4
11/25/16
Initial Release
Update to latest installation data revisions; changed VFR placard text;
updated equipment station locations.
Update to latest installation data revisions; added “G500H GDL 88H
Harness Assembly”.
Update to Table 2-2 GDU 620 Alert Troubleshooting Guide; update
reference documents in Section 2.1; remove LRU location diagram in
Section 2.2; add rotorcraft specific LRU location and wire routing diagram
(Section 2.8); move circuit breaker diagram to Section 2.8.
TABLE OF CONTENTS
1. INTRODUCTION................................................................................................................... 1
1.1 Purpose................................................................................................................. 1
1.2 Scope .................................................................................................................... 1
1.3 Document Control ................................................................................................. 1
1.4 Permission to Use Certain Documents ................................................................. 1
1.5 Definitions ............................................................................................................. 1
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 2
2.1 Introduction ........................................................................................................... 2
2.2 Description of Alteration........................................................................................ 2
2.3 Control, Operating Information ............................................................................. 3
2.4 Servicing Information ............................................................................................ 3
2.5 Periodic Maintenance Instructions ........................................................................ 4
2.6 Troubleshooting Information ................................................................................. 5
2.7 Removal and Installation Information ................................................................... 13
2.8 Diagrams............................................................................................................... 18
2.9 Special Inspection Requirements ......................................................................... 22
2.10 Application of Protective Treatments .................................................................... 22
2.11 Data Relative to Structural Fasteners ................................................................... 22
2.12 Special Tools ........................................................................................................ 22
2.13 Additional Instructions........................................................................................... 22
2.14 Overhaul Period .................................................................................................... 23
2.15 ICA Revision and Distribution ............................................................................... 23
2.16 Assistance............................................................................................................. 23
2.17 Implementation and Record Keeping ................................................................... 23
3. AIRWORTHINESS LIMITATIONS ........................................................................................ 23
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page ii
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 provides Instructions for Continued Airworthiness (ICA) for the G500H PFD/MFD system
as 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 construe
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)
2)
3)
4)
5)
6)
7)
8)
9)
10)
11)
ACO: Aircraft Certification Office
ADC: Air Data Computer
AEG: Aircraft Evaluation Group
AHRS: Attitude Heading Reference System
CFR: Code of Federal Regulations
FAA: Federal Aviation Administration
ICA: Instructions for Continued Airworthiness
MFD: Multi-Function Display
PFD: Primary Flight Display
PMI: Principle Maintenance Inspector
STC: Supplemental Type Certificate
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:
Garmin 190-01150-06 Rev. 5 “G500H Rotorcraft
STC Installation Manual” or later FAA Approved
Revisions
Garmin 190-01150-02 Rev. C “G500H PILOT
GUIDE” or later revision
Retention:
2.2
This document, or the information contained within,
will be included in the rotorcraft’s permanent
records.
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.
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 in the diagram in Section 2.8).
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 2 of 23
2.2.1 Weight and Balance Information
Weight and Balance Bell 206 A/B
ITEM PART NUMBER
WEIGHT (LB)
1 011-01264-50 GDU 620 (Unit Only)
6.38
OR
GDU 620 (Installed with rack and
7.04
011-01264-60
connector)
2 011-00882-11 GDC 74H (Unit Only)
1.70
GDC 74H (Installed with connector)
1.92
3 011-00868-20 GRS 77H (Unit Only)
2.80
GRS 77H (Installed with rack and
3.46
connector)
4
011-00870-10
GMU 44 (Unit Only)
GMU 44 (Installed with rack and
connector)
0.35
0.50
MOMENT ARM (IN)
LONGITUDINAL
LATERAL
LOCATION
PRIMARY SECONDARY
38.6
196.3
217.5
0.0
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 (+).
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.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 3 of 23
2.5
Periodic Maintenance Instructions
Maintenance of the components installed by this STC is on condition, except as noted in the following
table.
Item
GRS 77H AHRS
Interval
Description/Procedure
5 years
The GRS 77 utilizes an Earth magnetic field model which is
updated once every five years as part of the Aviation Database
maintained by the owner/operator. If the magnetic model is not
current, the unit will issue an alert upon startup indicating the
model has expired. The model can be updated by inserting an
aviation database card with an updated IGRF model and
powering on the system. A prompt will direct the user to press
ENT to update the model.
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:
GDC 74H ADC
On condition
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:
GDU 620, GRS 77H,
GDC 74H, GMU 44, GTP
59
12 Calendar
Months
1.
2.
3.
4.
Gain access to LRU (see Section 2.8 for LRU locations)
Inspect each unit for security of attachment.
Inspect all knobs and buttons for legibility.
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.
Perform an electrical bonding test 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
1. Gain access to the LRU (see Section 2.8 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.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 4 of 23
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
Unit does not power up –
blank screen.
Cause
Improper wiring; circuit breaker
open.
Unit intensity turned down.
All expected configuration
pages are not displayed.
An Installer Unlock Card is not
inserted into the GDU 620.
The GDC OAT probe type
shows up as UNKNOWN
The RS-232 connection to the
GDC 74H is not working.
When loading software, the
LRU software is not being
displayed on the
SOFTWARE UPLOAD page.
The software loader card is
installed in the bottom slot of the
GDU 620.
The software loader card contains Repeat the process for making the
no information.
software loader card.
The configuration module has not Update the configuration module.
been updated.
Configuration errors are
displayed on power-up,
before the GDU enters
normal mode.
Vertical GPS deviation is not
displayed on the GDU 620.
Unable to control the GPS
course when in OBS mode.
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)
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)
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.
Solution
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.
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.
Wrong device is connected to port Use correct ports (refer to interconnect
on GDU 620.
details in Appendix D of the installation
manual).
On the transmitting LRU, the
ARINC 429 transmitter speed is
not set correctly.
Wiring is not correct.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Set the ARINC 429 transmitter speed to
correct speed.
Check for continuity/shorts and correct as
required.
190-01150-11 Rev. 4
Page 5 of 23
Problem
Attitude and heading on
GDU 620 red ‘X’ / GRS 77H
resets during air data ground
testing.
Heading red ‘X’ during air
data ground testing
Cause
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.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Solution
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.
190-01150-11 Rev. 4
Page 6 of 23
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
<LRU> CAL
Cause
Error in the calibration of a
specific LRU, where “<LRU>”
denotes a specific LRU.
<LRU> CONFIG
Error in the configuration of a
specific LRU.
<LRU> database error exists,
where “<LRU> database”
denotes a specific unit
database.
The indicated LRU key is stuck.
<LRU> DB ERR
<LRU> KEYSTK
<LRU> SERVICE
<LRU> VOLTAGE
AHRS (1/2) GPS – AHRS (1/2)
using backup GPS source.
The indicated LRU requires
service.
<LRU> has low voltage.
Reducing power usage by
dimming display, where <LRU>
denotes the specific LRU
experiencing the power
reduction.
AHRS 1 or AHRS 2 is using the
backup GPS information.
AHRS (1/2) GPS - AHRS (1/2)
is not receiving any GPS
information
AHRS 1 or AHRS 2 is not
receiving any GPS information.
AHRS (1/2) GPS – AHRS (1/2)
operating exclusively in no-GPS
mode.
AHRS 1 or AHRS 2 is not
receiving any GPS information.
AHRS1 GPS – AHRS 1 not
receiving backup GPS
information.
AHRS is not receiving GPS
information from GPS2.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Solution
Calibration service required.
Contact repair facility. Return
indicated LRU to Garmin for
service, if necessary.
Configuration service required.
Contact repair facility.
Replace or update database.
Press the key again to cycle its
operation. If the problem
persists, contact Garmin
Technical Support.
Return indicated LRU to Garmin
for service.
Increase the supply voltage.
This is common for 14V aircraft
running on battery only. This
alert should clear once the
aircraft is running and loads are
on the alternator/generator.
Verify GPS1 power and inspect
wiring. If the problem persists,
contact Garmin Technical
Support.
Verify GPS1 power and inspect
the wiring. If the problem
persists, contact Garmin
Technical Support.
Ensure that at least one GPS
has acquired a valid position.
If GDU 620 does not have a
valid position, inspect all wiring
between the GDU and the GPS
receiver. Verify the
configuration of the GDU 620
and the GPS receiver.
If the GDU has a valid GPS
position, inspect all wiring
between the GDU and the GRS.
Verify time mark wiring.
Verify GPS2 power and inspect
wiring. If problem persists,
contact Garmin Technical
Support
190-01150-11 Rev. 4
Page 7 of 23
Alert Text
AHRS MAG DB
Cause
AHRS / GDU magnetic model
database version mismatch.
AHRS (1/2) SRVC
AHRS 1 or AHRS 2 magnetic
field model requires update.
(This alert appears on the
ground only.)
AHRS1 TAS – AHRS
AHRS 1 or
AHRS 2 is not
receiving true
airspeed from
the ADC.
Solution
Update AHRS and/or GDU
magnetic field model database.
(current model is with aviation
database). If the problem
persists, contact Garmin
Technical Support.
Update the GRS 77H IGRF
model (current model is with
aviation database). If the
problem persists, contact
Garmin Technical Support.
Close ADC C/B.
ALT KEY INOP
GDC not
powered up.
GDC not
receiving input
from GTP 59
OAT probe.
ARINC 429
connection
from GDC 74H
to GRS 77H is
not
functioning.
The ALT key is disabled.
ARINC 708 CONFIG
ARINC 708 configuration error.
ARINC 429 CONFIG
ARINC 429 configuration error.
Inspect wiring. Contact Garmin
Technical Support.
AUD NOT AVAIL
Audio system not available.
AUD SYS FAIL
Audio system failure
CAL LOST
Registry reports that it has lost
calibration data.
GDU in normal mode has
received updated crossfill tags
for configuration registry entries.
(Applicable only to dual GDU
installations.)
The configuration module is
inoperative.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Restart both GDUs in
configuration mode to
automatically synchronize
settings.
CNFG MISMATCH –
GDU 1-2 airframe
configurations disagree.
CNFG MODULE
DATALINK
DATALINK
GDL 88 ADS-B Failure. Unable
to transmit ADS-B messages.
GDL 88 ADS-B fault.
DATALINK
ADS-B fault: UAT receiver.
DATALINK
ADS-B fault: 1090 receiver.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Inspect all wiring from the GDC
to the probe.
Inspect all wiring between the
GDC and the GRS. If problem
persists, contact Garmin
Technical Support.
Contact Garmin Technical
Support.
Inspect wiring. Contact Garmin
Technical Support.
Inspect all wiring to
configuration module
Replace configuration module
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
190-01150-11 Rev. 4
Page 8 of 23
Alert Text
DATALINK
Cause
GDL 88 needs service.
DATALINK
GDL 88 ADS-B is not
transmitting position.
DATALINK
GDL 88 control panel input fault.
DATALINK
GDL 88 ADS-B fault. Pressure
altitude source inoperative.
GDL 88 external traffic system
inoperative or connection lost.
GDL 88 configuration module
needs service.
GDL 88 is inoperative or
connection to GDU is lost.
GDL 88 CSA Failure.
DATALINK
DATALINK
DATALINK
DATALINK
DATALINK
DATALINK
DATALINK
GDL 88 external traffic system
has a low battery.
GDL 88 ADS-B traffic has failed.
DATA LOST
GDL 88 external traffic system in
standby for more than 60
seconds.
Pilot stored data was lost.
DB ERR
Database found on top card.
DB SYNC COMPLETE
Database sync complete.
DB SYNC DISABLED
No database card found to
receive databases
Not enough space to receive
one or more databases.
System is in diagnostic mode.
DB SYNC ERROR
DIAG MODE
DSCRT CONFIG – Discrete
output configuration error.
A discrete output required by an
interfaced system has not been
configured.
EXTERNAL TAWS FAIL
External TAWS device has
failed.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Solution
Contact Garmin Technical
Support.
Check GPS devices. If the
problem persists, contact
Garmin Technical Support.
Check transponder mode. If the
problem persists, contact
Garmin Technical Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Verify data was lost, recheck
data and settings. Reconfigure
all personal settings.
Remove database or move to
bottom slot. Contact Garmin
Technical Support.
Restart required to use new
databases
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Use the DISCRETE
CONFIGURATION page in the
SYS page group to configure
the discrete outputs to match
the installation.
Verify wiring to the discrete
Verify all wiring between the
TAWS device and the GDU.
Contact Garmin Technical
Support.
190-01150-11 Rev. 4
Page 9 of 23
Alert Text
FAN (1/2) FAIL
GDC CONFIG
Cause
Fan 1 or Fan 2 has reported 0
RPM when it was powered with
a PWM duty cycle higher than or
equal to 10%.
The GDC configuration
information stored in the GDC
and the GDU 620 configuration
module do not match.
GDL69
GDL 69H has failed.
GDL69 CONFIG
The GDL 69H configuration
information stored in the GDL
69H and the GDU 620
configuration module do not
match.
GDU CONFIG
The GDL 69H configuration was
updated using another LRU
(e.g. the GMX 200 or
400W/500W).
This alert appears whenever the
GDU is replaced with a GDU not
configured for this 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 the indicated database.
GDU KEYSTK
The indicated GDU key is stuck
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Solution
Inspect the GDU fan for an
obstruction. If the problem
persists, contact Garmin
Technical Support.
With the GDU 620 in
configuration mode, go to the
GDC 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 GDC.
Verify wiring between the GDU
and the GDL 69H.
Check power and ground wires
on GDL 69H. If the problem
persists, contact Garmin
Technical Support.
Ensure that the GDU 620 is in
configuration mode. Go to the
GDL 69 page of the GDL page
group. Verify that the SET and
ACTIVE configuration settings
are the same. If they are not
the same, touch the SET>ACTV
soft key. The configuration
settings are copied from the
GDU 620 to the GDL 69H.
Update the GDL 69H
configuration using the GDU
620.
Cycle power to the GDU. This
error automatically clears on the
second power up with a
different configuration module.
Check GDU 620 configuration
in accordance with the section 5
of the installation manual.
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.
Press the key again to cycle its
operation. If the problem
persists contact Garmin
Technical Support.
190-01150-11 Rev. 4
Page 10 of 23
Alert Text
GDU (1/2) VOLTAGE
Cause
GDU supply voltage is below 12
VDC.
GPS (1/2) FAIL
Communication with GPS1 or
GPS2 lost. No GPS1 or GPS2
data is available.
GPS2 FPL USED
The GPS1 has failed and GPS2
is configured and operating.
GPS (1/2) PPS Failure
Timing data from GPS 1 or GPS
2 is lost. PPS signal is not
received before 5 second timer
expires.
GSR FAIL
GSR has failed.
HDG FAULT
AHRS magnetometer fault has
occurred. GRS 77H not
receiving information from the
GMU 44.
Heading from the GRS77/
GMU 44 is not valid. This
problem is caused by a local
magnetic anomaly.
HDG LOST
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Solution
Increase the supply voltage
above 12VDC.
This alert is normal in 14V
aircraft that are running on the
battery only and should clear
once the aircraft engine is
started and the
alternator/generator is carrying
the load.
Ensure that the indicated GPS
is turned on.
Verify RS-232 wiring from the
GPS to the GDU 620.
Verify GPS 1 power and inspect
wiring. Check configuration
settings and formats. Go to the
Diagnostics page and verify that
data is being received by the
configured port.
Ensure that the indicated GPS
is turned on.
Verify PPS wiring from the
indicated GPS to the GDU 620.
Check if GSR power discrete is
on and GSR status discrete is
off at the same time.
Verify wiring between the GDU
and the GSR.
Check power and ground wires
on GSR 56. If the problem
persists, contact Garmin
Technical Support.
Inspect all wiring to GMU 44.
No action required.
190-01150-11 Rev. 4
Page 11 of 23
Alert Text
HTAWS
Cause
External HTAWS not available.
Internal TERRAIN-HSVT
alerting enabled.
External TAWS Configuration
mismatch
MANIFEST
GDU has received product data
for an LRU that should have a
manifest entry, but is not in the
manifest.
The LRU software P/N and
version number in the manifest
does not match the values being
reported by that LRU.
NAV(1/2)
REGISTER GFDS
Communication with NAV1 or
NAV 2 is lost. No data from the
indicated navigation receiver.
Data services are inoperative.
RS-485 CONFIG
RS-485 configuration error.
RS-232 CONFIG
RS-232 configuration error.
SIMULATOR
The simulator mode is active.
SVT DISABLED - Out of
available terrain region.
SVT DISABLED - Terrain DB
resolution too low.
Location is beyond region
covered by terrain database.
A 30 arc-second terrain
database is being used.
SW MISMATCH
GDU software version strings do
not match.
Terrain, Airport Terrain, or
Obstacle database error.
TERRAIN DSP
TRAFFIC CONFIG
ADS-B traffic data does not
match configuration.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
Solution
Ensure TAWS unit is wired as
GPS 1 source. Verify the
required software versions
(refer to section 5.8.7 in the
installation manual). If the
problem persists, contact
Garmin Technical Support.
Verify all configuration settings.
For more information refer to
table 2-7 in the installation
manual. If the problem persists,
contact Garmin Technical
Support.
Ensure the manifest is properly
configured. For additional
information refer to section
5.5.5 in the installation manual.
Update the LRU software to
match the manifest
Update the manifest to match
the LRU software
Verify NAV RCVR (1/2) is
configured and operating
correctly. Inspect all wiring.
Register the GSR 56 with
Garmin Flight Data Services
(GFDS) to receive weather data.
Contact Garmin Technical
Support.
Contact Garmin Technical
Support.
Ensure P6202-36 is not
grounded.
Ensure the terrain database
includes the region of operation.
Update the Supplemental Data
card with the 9 arc-second
terrain database.
Verify the correct SW is loaded.
Update or reload database. If
the problem persists, contact
Garmin Technical Support.
Verify configuration settings. If
the problem persists, contact
Garmin Technical Support.
190-01150-11 Rev. 4
Page 12 of 23
Alert Text
TRAFFIC FAIL
TRAFFIC STDBY
TRK LOST
TRK TRAFFIC
2.7
Cause
The traffic
information
system has
failed.
The GDU 620
is not receiving
traffic
information
from the traffic
sensor.
The GDU 620
is receiving
information
from the traffic
sensor, but the
information is
indicating that
the traffic
sensor has
failed.
The traffic information system is
in Standby mode while the
aircraft is In-Air.
GPS1 TRK lost. HSI defaulted
to GPS2 TRK.
Heading Lost. Traffic is now
based on track.
Solution
Verify wiring between GDU 620
and traffic sensor.
Troubleshoot traffic system.
Check traffic system controls on
MFD traffic page or traffic
system. If the problem persists,
contact Garmin Technical
Support.
Ensure the GPS has a valid
position.
See HDG FAULT and HDG
LOST alerts. If the problem
persists, contact Garmin
Technical Support.
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.
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
2.7.1.1
1.
2.
3.
4.
2.7.1.2
GDU™ 620 Unit
Removal
Remove the six mounting screws from the bezel of the GDU 620.
Pull the GDU 620 far enough out from the instrument panel to access the three rear connectors.
Disconnect the rear connectors.
Remove the GDU 620.
Installation
1. Visually inspect the connectors to ensure that there are no bent or damaged pins. Repair any
damage.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 13 of 23
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 module
from its internally-stored settings when the UPDT CFG soft key is pressed If the GDU 620 is
replaced at the same time as the Configuration Module, then the System Setup will need to be
performed per Section 5.5 of the G500H STC Installation Manual.
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.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 14 of 23
2.7.2
2.7.2.1
GRS 77H Unit
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 recalibration 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
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 15 of 23
Table 2-3. GRS 77H Calibration Criteria
Calibrations Required
Condition
GRS 77H
Pitch/Roll
Offset
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 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.
2.7.3
2.7.3.1
GRS/GMU
Magnetic
Calibration
See Section 5
of the G500H STC
Installation Manual
Engine Run-up
Vibration
Test
See Section 5
of the G500H
STC Installation
Manual
None Required.
X
X
X
X
X
X
GMU 44 Unit
Removal
1. Gain access to the GMU 44 magnetometer.
2. Unscrew the three screws that hold the GMU 44 to its mounting rack.
3. Carefully lift the GMU 44 from the rack.
4. Disconnect the wiring harness.
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 include
units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Recalibration is required only if the mount for the magnetometer was
changed. If the magnetometer mount was changed, refer to Section 5.6.2 of the G500H STC
Installation Manual for the GRS 77H/GMU 44 Magnetic Calibration.
New, Repaired or Exchange GMU 44 is Installed
If a new, repaired, or exchange GMU 44 unit is installed, then software must be loaded and the GRS
77H/GMU 44 Magnetic Calibration must be performed. Refer to Section 5 of the G500H STC
Installation Manual for instructions on software loading (5.4.2) and Magnetic Calibration (5.6.2).
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 16 of 23
2.7.3.3
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
2.7.4.1
GDC 74H Unit
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/static 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 any 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 5.4.2 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
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 17 of 23
2.8
Diagrams
A rotorcraft specific LRU location and wire routing diagram is included below. A circuit breaker diagram
is also included below (circuit breakers added as part of the G500H system are circled). Point to point
wiring diagrams are in Appendix D of the G500H STC Installation Manual. Refer to the G500H PostInstallation Checkout Log retained in the rotorcraft permanent records for a list of the interfaced
equipment and port configurations.
Top View:
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 18 of 23
Side View:
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 19 of 23
The installed G500H equipment can be accessed as described below:
1.
2.
3.
4.
5.
6.
GDU 620: FS38.6, WL 43.3 Access or remove by removing the six screws in the bezel of the
GDU 620.
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.
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.
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.
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.
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.
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 20 of 23
COPILOT
HEADSET
PILOT
HEADSET
HOIST CABLE TURN
POWER CUT
AUDIO/ HAND
MIKE
MKR
IND
FLOATS
XPNDR
OFF
NAV
COM
SAS
SAS
PWR
PFD
AHRS
ADC
CARGO HTR
HTR
HOOK CONT
PWR
LDG
INST
LT
LT
FUELBOOST
CONT INVTR
COCK
PIT CAUTION TOT
LT
LT
IND
FUEL
FUEL
ENG
XMSN
AFT
FWD
HYD
GOV
IGN
START
ENG
BOOST CONT
ENG
ENG
HEAT
INST LT
OFF
POS LT
HTR
QTY VALVE TEMP
PRESS
IND
OFF
OFF
BRT
GEN
HEAT
ANTI
COLL LT
GEN
OFF
START
FIELD RESET
VENT
DIR
OFF
GYRO PITOT DEFOG OFF
O
F
F
& ATT
IND
HEAT BLOWER BAT
GEN
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 21 of 23
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 structural
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.
FASTENER TYPE AND TORQUE
Location
(see Section 2.8)
6-32 Screw
8-32 Screw
10-32 Screw
12-15 inch-pounds
12-15 inch-pounds
22-25 inch-pounds
100±20 inch-pounds
Instrument Panel,
Instruments
X
GDU 620
X
GRS 77H
X
X
X
X
GDC 74H
GMU 44
NUT, 5/16", HEX,
SKIRT
X
X
X
GTP 59
X
2.12 Special Tools
For electrical bonding testing, a milliohm meter is required.
2.13 Additional Instructions
None
G500H Flight Display System
Instructions for Continued Airworthiness Bell 206A/B Series
190-01150-11 Rev. 4
Page 22 of 23
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