Garmin | G5 Electronic Flight Instrument for Certificated Aircraft | Garmin G5 Electronic Flight Instrument for Certificated Aircraft AFMS - G5 Electronic Flight Instrument Part 23 AML STC

Garmin G5 Electronic Flight Instrument for Certificated Aircraft AFMS - G5 Electronic Flight Instrument Part 23 AML STC
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Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
AFMS, Garmin G5 AML STC
190-01112-13 Rev. 6
Garmin International, Inc
Log of Revisions
FAA Approved AIRPLANE FLIGHT MANUAL SUPPLEMENT
or
SUPPLEMENTAL AIRPLANE FLIGHT MANUAL
GARMIN G5 ELECTRONIC FLIGHT INSTRUMENT
REV
NO.
PAGE NO(S)
1
ALL
Original Issue
2
ALL
Added information
DG/HSI.
3
ALL
Added interface to 3rd party autopilots.
4
ALL
Added note to General section.
5
ALL
6
ALL
190-01112-13 Rev. 6
DATE OF
APPROVAL
DESCRIPTION
7/22/2016
regarding
G5
Reformatted document.
Updated
system messages interface.
Added
DG/HSI reversion description.
Added interface description to GAD 13.
Added information regarding multiple
NAV source inputs.
4/28/2017
10/18/2017
10/26/17
12/20/17
See Cover
FAA APPROVED
Robert Murray
ODA STC Unit
Administrator
Robert Murray
ODA STC Unit
Administrator
Robert Murray
ODA STC Unit
Administrator
Paul Mast
ODA STC Unit
Administrator
Robert Murray
ODA STC Unit
Administrator
See Cover
AFMS, Garmin G5 AML STC
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190-01112-13 Rev. 6
Table of Contents
Section 1 – General .................................................................................................... 1-1
Abbreviations and Terminology ......................................................................................................... 1-2
Section 2 – Limitations .............................................................................................. 2-1
System Software Requirements ......................................................................................................... 2-1
Use of Secondary Instruments ........................................................................................................... 2-1
Kinds of Operations ............................................................................................................................. 2-1
Section 3 – Emergency Procedures ......................................................................... 3-1
G5 Failure Indications .......................................................................................................................... 3-1
Attitude Failure .................................................................................................................................... 3-1
Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error ............................................. 3-1
GPS Failure ........................................................................................................................................ 3-2
Attitude Aligning ................................................................................................................................... 3-2
Attitude Aligning / Keep Wings Level................................................................................................. 3-2
Loss of Electrical Power to the G5 Display ....................................................................................... 3-2
Loss of Electrical Power to the GAD 29B (If Installed) ..................................................................... 3-3
Loss of Electrical Power to the GAD 13 (If Installed) ........................................................................ 3-3
Section 4 – Normal Procedures ................................................................................ 4-1
G5 Power Button and Knob ................................................................................................................. 4-1
Backlight Intensity Adjustment ........................................................................................................... 4-1
Prior to Flight in Instrument Meteorological Conditions.................................................................. 4-1
Autopilot Operations with the G5 HSI ................................................................................................ 4-2
Course / NAV Selection Coupling to the Autopilot (If Configured) ..................................................... 4-2
Heading Bug Coupling Capability to the Autopilot (If Configured) ...................................................... 4-2
Roll Steering (GPSS) Emulated via HDG Mode (If Configured) ......................................................... 4-2
HSI Source Selection (If Configured) ................................................................................................. 4-3
Section 5 – Performance ........................................................................................... 5-1
Section 6 – Weight and Balance ............................................................................... 6-1
Section 7 – System Description ................................................................................ 7-1
System Messages................................................................................................................................. 7-1
190-01112-13 Rev. 6
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190-01112-13 Rev. 6
SECTION 1 – GENERAL
The G5 Electronic Flight Instrument can display the following information to the pilot depending on the installation
and location of the G5 instrument.
•
•
•
•
•
•
Primary attitude
Primary slip and turn rate information
Primary heading
Secondary airspeed
Secondary altimeter
Secondary ground track
When installed in place of the attitude indicator, the primary function of the G5 is to provide attitude information to
the pilot. When installed in place of the rate of turn indicator, the primary function of the G5 is to provide turn
rate and slip ball information to the pilot. When installed in place of the directional gyro, the primary function of
the G5 is to provide directional information to the pilot.
NOTE:
The pilot is reminded to perform appropriate flight and navigation instrument cross checks for the
type of operation being conducted.
In case of a loss of aircraft electrical power, a backup battery (optional when installed as a DG/HSI) sustains the
G5 Electronic Flight Instrument for up to four hours.
An optional GAD 29B may be installed to provide course and heading datum to an autopilot based on the data
selected for display on the HSI.
An optional GAD 13 and OAT probe may be installed to provide measured outside air temperature (OAT) to the
G5 for display of true airspeed (TAS), outside air temperature, winds, and density altitude.
This STC allows the removal of the aircraft’s vacuum system if it is not required to support any other airframe
system.
190-01112-13 Rev. 6
AFMS, Garmin G5 AML STC
Page 1–1
Abbreviations and Terminology
The following glossary is applicable within the airplane flight manual supplement
ADI
AFMS
ATT
CDI
DG
DR
FAA
GPS
GPSS
HDG
HSI
ILS
LOC
LOI
OAT
TAS
VFR
VHF
VOR
Attitude Direction Indicator
Airplane Flight Manual Supplement
Attitude
Course Deviation Indicator
Directional Gyro
Dead Reckoning
Federal Aviation Administration
Global Positioning System
GPS Roll Steering
Heading
Horizontal Situation Indicator
Instrument Landing System
Localizer (no glideslope available)
Loss of Integrity
Outside Air Temperature
True Airspeed
Visual Flight Rules
Very High Frequency
VHF Omni-directional Range
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190-01112-13 Rev. 6
SECTION 2 – LIMITATIONS
System Software Requirements
The G5 must utilize the following or later FAA approved software versions for this AFMS revision to be applicable:
Component
Software Version
G5 Electronic Flight Instrument
6.20
Use of Secondary Instruments
The original type design approved instruments for airspeed, altitude and vertical speed remain the primary
indications for these parameters.
If the G5 Electronic Flight Instrument is installed in place of the rate of turn indicator, the original type design
approved instrument for attitude remains in the primary indication for attitude.
If the G5 Electronic Flight Instrument is installed in place of the directional gyro, the original type design approved
instruments for attitude remains the primary indication for attitude.
NOTE:
For aircraft approved for VFR-only operations, the G5 Electronic Flight Instrument may be
installed as an attitude indicator and rate of turn indicator.
Kinds of Operations
No Change except for the following:
•
When a portable navigation source is selected on the G5, it shall not be used for the primary means
of navigation for IFR operations.
190-01112-13 Rev. 6
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190-01112-13 Rev. 6
SECTION 3 – EMERGENCY PROCEDURES
G5 Failure Indications
If a G5 function fails, a large red ‘X’ is typically displayed over the instrument(s) or data experiencing the failure.
Upon G5 power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should
be operational within one minute of power-up. If any instrument remains flagged and it is not likely an installation
related problem, the G5 should be serviced by a Garmin-authorized repair facility.
Attitude Failure
Attitude failure is indicated by removal of the sky/ground presentation, a red X, and a yellow “ATTITUDE FAIL” on
the display.
Rate-of-turn and slip information will not be available.
1. Use standby instruments.
2. Seek VFR conditions or land as soon as practical.
Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error
A heading failure, loss of magnetometer data, or magnetic field error is indicated by removal of the digital heading
readout, a red X, and a yellow “HDG” on the display.
1. Use standby magnetic compass.
NOTE:
If the G5 DG/HSI has a valid GPS signal the G5 DG/HSI instrument will display the GPS track
information in magenta.
190-01112-13 Rev. 6
AFMS, Garmin G5 AML STC
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GPS Failure
If GPS navigation receivers and/or navigation information are not available or invalid, the G5 will display Dead
Reckoning mode (DR) or Loss of Integrity mode (LOI) on the HSI in the lower left corner.
If Alternate Navigation Sources (ILS, LOC, VOR) Are Available:
1. Use alternate navigation source.
If No Alternate Navigation Sources Are Available:
If DR is Displayed on HSI:
1. Use the amber CDI for course information.
2. Fly toward known visual conditions.
If LOI is Displayed on HSI:
1. Fly toward known visual conditions.
For aircraft equipped with a GAD 29B interfaced to an autopilot, GPSS will be displayed in amber text when GPSS
emulation has been selected from the G5 menu.
1. Deselect GPSS from the G5 menu and select a different autopilot mode.
Attitude Aligning
During system initialization, the G5 displays the message ‘ALIGNING’ over the attitude indicator. The G5 will
typically display valid attitude within the first minute of power-up. The G5 can also align itself while taxiing and
during level flight.
If the “ALIGNING” indication occurs during flight and attitude remains displayed, the attitude display is acceptable
for use for flight in instrument conditions. The message will clear when the attitude solution is within the systems
internal accuracy tolerances. It is recommended to maintain wings level to reduce the time for the system to
align.
Attitude Aligning / Keep Wings Level
If the “ALIGNING KEEP WINGS LEVEL” indication occurs during flight, the G5 has detected an invalid attitude
solution and will not display any attitude information.
1. Use standby instruments to maintain wings level flight.
accuracy tolerances have been met.
The system will display attitude when internal
2. If attitude does not return, seek VFR conditions or land as soon as practical.
Loss of Electrical Power to the G5 Display
In the event of a loss of aircraft electrical power to the G5 attitude display, the indicator will continue to function on
its internal battery. If an internal battery is installed on the optional G5 HSI, the indicator will continue to function
on the internal battery if aircraft power is lost. Internal battery endurance is indicated on the G5 display in hours
and minutes. The charging symbol will be removed and the internal battery will not be charged.
In the event the G5 attitude display powers down, the optional G5 HSI will automatically revert to displaying
attitude information. It will not revert back to the DG/HSI format if the G5 attitude unit regains power. The
DG/HSI presentation may be selected from the G5 menu on the G5 DG/HSI unit after reversion to the attitude
display.
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190-01112-13 Rev. 6
Loss of Electrical Power to the GAD 29B (If Installed)
In the event of a loss of aircraft electrical power to the optional GAD 29B, the heading and course datum will be
unavailable to the autopilot and the autopilot may deviate from the intended path or may disconnect. GPS flight
plan course information may be displayed on the HSI and VFR will be displayed in amber text on the HSI. GPSS
will be displayed in amber text, if GPSS mode is selected.
1. Deselect GPSS from the G5 menu and select a different autopilot mode.
2. Lateral GPS course guidance may only be used in VFR conditions.
Loss of Electrical Power to the GAD 13 (If Installed)
In the event of a loss of aircraft electrical power to the optional GAD 13, the OAT and TAS indications will be
replaced with a red X. The Density Altitude indication will be removed, and “No Wind Data” will be displayed in
the wind field.
1. Use an alternate source of outside air temperature to calculate true airspeed, density altitude, and winds.
190-01112-13 Rev. 6
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190-01112-13 Rev. 6
SECTION 4 – NORMAL PROCEDURES
G5 Power Button and Knob
The G5 display will power on with the application of aircraft power. The G5 power button is used to turn the
display on and off. Press and hold the power button to turn the display off.
The knob performs the following functions:
Press to access the Menu.
Press
From the Menu, press to select the desired menu item.
Press to accept the displayed value when editing numeric data or selecting from a list.
Press to sync the heading or track bug for the HSI.
From the Menu, turn the Knob to move the cursor to the desired menu item.
Turn
For the ADI, rotate to adjust the baro setting on the secondary altitude display.
For the HSI, rotate to adjust the heading or track bug.
Turn to select the desired value when editing numeric data or selecting from a list.
Backlight Intensity Adjustment
The power up state of the G5 backlight is in Auto adjustment mode.
To adjust the backlighting:
To select Manual mode from Auto mode:
1. While the unit is turned on, press the Power button.
2. Turn the knob to manually adjust the backlight intensity.
3. Press the knob to close the backlight page.
To select Auto mode from Manual mode:
1. While the unit is turned on, press the Power button.
2. Press the Power button again to select Auto.
3. Press the knob to close the backlight page.
Prior to Flight in Instrument Meteorological Conditions
1. Press the Power button on the G5 attitude indicator.
2. Verify the battery status indicator is green on the G5 attitude indicator.
190-01112-13 Rev. 6
AFMS, Garmin G5 AML STC
Page 4–1
Autopilot Operations with the G5 HSI
The G5 and optional GAD 29B offer various integration capabilities dependent upon the type of autopilot installed
in a particular aircraft.
The G5 Electronic Flight Instrument installation in this aircraft provides the following autopilot functions
(appropriate boxes will be checked):
 This installation does not interface with the autopilot (basic wing leveling autopilot or no autopilot is
installed in the aircraft).
 A GAD 29B Adapter is installed in this aircraft.
 Course / NAV Selection coupling to the autopilot.
 Heading Bug coupling capability to the autopilot.
 Roll Steering (GPSS) emulated via heading mode.
OR
 Roll Steering capable autopilot (GPSS menu function for emulation not applicable).
Course / NAV Selection Coupling to the Autopilot (If Configured)
When operating the autopilot in NAV mode, the deviation information from the installed navigation sources (i.e.
GPS or NAV) is switched via the navigation source. The NAV source displayed on the HSI is the NAV source
the autopilot is following. Many autopilots also use the course datum to determine the best intercept angles
when operating in NAV mode.
Heading Bug Coupling Capability to the Autopilot (If Configured)
When operating the autopilot in HDG mode, the difference between the HDG bug location on the HSI and the
actual aircraft heading creates an error signal which the autopilot will minimize by turning in the direction of the
bug. If the bug is turned more than 180 degrees, the autopilot may turn the airplane in the opposite direction of
the desired turn.
Roll Steering (GPSS) Emulated via HDG Mode (If Configured)
For autopilots that do not support digital GPSS signals, GPSS functionality may be emulated by operating the
autopilot in HDG mode and selecting GPSS from the G5 menu. If the autopilot is already designed to receive roll
steering information, the data is transmitted digitally from the navigator to the autopilot.
When GPSS is selected on the G5 menu, the heading bug on the HSI changes to a hollow outline and a crossedout heading bug appears on the G5 HSI display indicating that the autopilot is not coupled to the heading bug.
The bug is still controllable and may still be used for reference.
When GPSS is selected on the G5, GPSS turn commands are converted into a heading error signal to the
autopilot. When the autopilot is operated in HDG mode, the autopilot will fly the turn commands from the GPS
AFMS, Garmin G5 AML STC
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190-01112-13 Rev. 6
navigator. If the GPSS data is invalid (for example, if there is no active GPS leg) or the selected HSI source on
the G5 HSI is not GPS, the annunciated GPSS text will be yellow and a zero turn command will be sent to the
autopilot.
HSI Source Selection (If Configured)
For aircraft configured with two navigation inputs to the G5, the desired source may be selected using the G5
knob and menu selection. Press the G5 knob to cycle between the NAV1 and NAV2 input.
HSI Portable Navigation Device GPS VFR Annunciation (If Configured)
For aircraft configured for a portable navigation device input to the G5, a GPS VFR indicated in magenta will be
displayed on the HSI. When the G5 with a portable navigation device is interfaced there is not enough
guidance data for IFR use.
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190-01112-13 Rev. 6
SECTION 5 – PERFORMANCE
No change.
190-01112-13 Rev. 6
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190-01112-13 Rev. 6
SECTION 6 – WEIGHT AND BALANCE
See current weight and balance data.
190-01112-13 Rev. 6
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190-01112-13 Rev. 6
SECTION 7 – SYSTEM DESCRIPTION
Refer to Garmin G5 Electronic Flight Instrument Pilot’s Guide for Certified Aircraft, part number 190-01112-12
Rev A (or later approved revisions), for a description of the G5 electronic flight instrument. This reference
material is not required to be on board the aircraft but does contain a more in depth description of all the functions
and capabilities of the G5.
The ATT circuit breaker supplies power to the G5 instrument for normal power operation and to charge the
internal battery.
The DG circuit breaker supplies power to the G5 instrument for normal power operation when configured as a
DG, and to charge the internal battery (if installed).
The HSI circuit breaker supplies power to the G5 instrument for normal power operation when configured as an
HSI, and to charge the internal battery (if installed).
The GAD circuit breaker supplies power to the optional GAD 29 adapter and optional GAD 13 adapter for normal
power operation.
System Messages
The G5 has the capability to display system messages to the crew along the bottom of the display.
message is indicated through a white
indication on the G5.
A system
Messages can be displayed by pressing the G5 knob, and selecting the Message menu item.
(For Reference Only)
190-01112-13 Rev. 6
AFMS, Garmin G5 AML STC
Page 7–1
The following table shows the meaning of each message.
System messages are displayed in white text.
Message
Meaning
External Power Lost
Aircraft power has been removed from the G5.
Critical battery fault!
Powering off
Battery has critical fault condition and the unit is about to power off to avoid
damage to the battery.
Battery fault
Battery has a fault condition – unit needs service.
Battery charger fault
Battery charger has a fault condition – unit needs service.
Low battery
Battery charge level is low.
Hardware fault
Unit has a hardware fault – unit needs service.
Power supply fault
Unit power supply fault detected – unit needs service.
Unit temperature limit
exceeded
Network address
conflict
Communication error
Factory calibration
data invalid
Magnetic field model
database out of date
Magnetometer
Hardware fault
Using external GPS
data
Not receiving RS-232
data
Not receiving ARINC
429 data
Unit is too hot or too cold.
Another G5 with the same address is detected on the network (most commonly
a wiring error on one of the units).
General communication error (most commonly appears in conjunction with
Network Address Conflict message).
Unit calibration data not valid – unit needs service.
Internal magnetic field database is out of date - software update required.
The magnetometer has detected a fault – unit needs service. Heading data
may not be available.
GPS data from another network LRU is being used. The unit's internal GPS
receiver is enabled, but unable to establish a GPS fix.
The G5 is not receiving RS-232 data from the GPS navigator – system needs
service.
The G5 is not receiving ARINC 429 data from the navigation source – system
needs service.
GPS receiver fault
The G5 on-board GPS receiver has a fault.
ARINC 429 interface
configuration error
Software version
mismatch
The G5 ARINC 429 port is receiving information from an incorrect source –
system needs service.
The G5 attitude indicator and the G5 HSI units have different software. Cross
fill of baro, heading and altitude bugs is disabled.
These messages remain while the condition persists.
AFMS, Garmin G5 AML STC
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190-01112-13 Rev. 6
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