G5 Electronic Flight Instrument
Pilot's Guide
for Certified Aircraft
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SYSTEM OVERVIEW
FLIGHT INSTRUMENTS
AFCS
ADDITIONAL FEATURES
INDEX
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© 2017 Garmin Ltd. or its subsidiaries. All rights reserved.
This manual reflects the operation of System Software version 5.00 or later. Some differences
in operation may be observed when comparing the information in this manual to earlier or later
software versions.
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Web Site Address: www.garmin.com
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December, 2017 190-01112-12 Rev. A Printed in the U.S.A.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Warnings, Cautions & Notes
BATTERY WARNINGS:
If these guidelines are not followed, the lithium-ion battery may experience
a shortened life span or may present a risk of damage to the device, fire,
chemical burn, electrolyte leak, and/or injury.
•
Do not leave the battery exposed to a heat source or in a high
temperature environment. To help prevent damage, store the battery
out of direct sunlight.
•
For maximum battery longevity, store within a temperature range of
-4˚F to 68˚F (from -20˚C to 20˚C).
•
Do not use a sharp object to remove the battery.
•
Do not disassemble, puncture, damage, or incinerate the device or
battery.
•
Keep the battery away from children.
•
Only replace the battery with the approved replacement from Garmin.
Using another battery presents a risk of fire or explosion. To purchase
a replacement battery, see you Garmin dealer or the Garmin website.
•
Contact your local waste disposal department to dispose of the device
and battery in accordance with applicable local laws and regulations.
WARNING: To reduce the risk of unsafe operation, carefully review and
understand all aspects of the Pilot's Guide. Thoroughly practice basic operation
prior to actual use. During flight operations, carefully compare indications
from the G5 to all available flight displays. For safety purposes, always resolve
any discrepancies.
WARNING: The altitude calculated by the G5 internal GPS receiver is geo-
metric height above Mean Sea Level and could vary significantly from the
altitude displayed by pressure altimeters. Always use the pressure altitude
display, when available, for determining or selecting aircraft altitude.
WARNING: The United States government operates the Global Positioning
System and is solely responsible for its accuracy and maintenance. The GPS
system is subject to changes which could affect the accuracy and performance
of all GPS equipment.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Warnings, Cautions & Notes
WARNING: For safety reasons, the G5 operational procedures must be learned
on the ground.
WARNING: This product, its packaging, and its components contain chemicals
known to the State of California to cause cancer, birth defects, or reproductive
harm. This Notice is being provided in accordance with California Proposition
65. If you have any questions or would like additional information, please
refer to our website at www.garmin.com/prop65
CAUTION: The display uses a lens with a special coating that may be sensitive
to certain oils, waxes, and abrasive cleaners. CLEANERS CONTAINING
AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important
to clean the lens using a clean, lint-free cloth and a cleaner that is specified
as safe for anti-reflective coatings. Avoid any chemical cleaners or solvents
that can damage plastic components.
CAUTION: The G5 does not contain any user-serviceable parts. Repairs should
only be made by an authorized Garmin service center. Unauthorized repairs
or modifications could result in permanent damage to the equipment and
void both the warranty and the authority to operate this device under FAA,
FCC, and other applicable regulations.
NOTE: The G5 may only be installed in type-certificated aircraft in accordance
with Garmin STC SA01818WI.
NOTE: The term LRU, as used throughout this manual is an abbreviation for
Line Replaceable Unit. LRU is used generically in aviation for a product (such
as a GSA 28 or GMC 507) that can be readily "swapped out" (usually as a
single component) for troubleshooting/repair.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Warnings, Cautions & Notes
NOTE: The G5 has a very high degree of functional integrity. However, the
pilot must recognize that providing monitoring and/or self-test capability for
all conceivable system failures is not practical. Although unlikely, it may be
possible for erroneous operation to occur without a fault indication shown by
the G5. It is thus the responsibility of the pilot to detect such an occurrence
by means of cross-checking with all redundant or correlated information
available in the cockpit.
NOTE: All visual depictions contained within this document, including screen
images of the G5 display, are subject to change and may not reflect the most
current G5 functionality.
NOTE: Use of polarized eyewear may cause the display to appear dim or
blank.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Warnings, Cautions & Notes
DECLARATION OF CONFORMITY
Hereby, Garmin declares that this product is in compliance with the Directive 2014/53/EU. The full
text of the EU declaration of conformity is available at the following internet address www.garmin.
com/compliance.
FCC
This device complies with Part 15 of the FCC Rules. Operation is subject to the following two
conditions: (1) this device may not cause harmful interference, and (2) this device must accept
any interference received, including interference that may cause undesired operation.
This equipment has been tested and found to comply with the limits for a Class B digital
device pursuant to part 15 of the FCC Rules. These limits are designed to provide reasonable
protection against harmful interference in a residential installation. This equipment generates,
uses, and can radiate radio frequency energy and if not installed and used in accordance with
the instructions, may cause harmful interference to radio communications. However, there is
no guarantee that interference will not occur in a particular installation. If this equipment
does cause harmful interference to radio or television reception, which can be determined by
turning the equipment off and on, the user is encouraged to try to correct the interference by
one of the following measures:
• Reorient or relocate the receiving antenna.
• Increase the separation between the equipment and receiver.
• Connect the equipment into an outlet on a circuit different from that to which the
receiver is connected.
• Consult the dealer or an experienced radio/TV technician for help.
LICENSE AGREEMENT AND WARRANTY
ContaCt Garmin
Contact Garmin if you have any questions while using the G5 at www.flygarmin.com.
Software LiCenSe aGreement
BY USING THE DEVICE, COMPONENT OR SYSTEM MANUFACTURED OR SOLD BY GARMIN (“THE
GARMIN PRODUCT”), YOU AGREE TO BE BOUND BY THE TERMS AND CONDITIONS OF THE
FOLLOWING SOFTWARE LICENSE AGREEMENT. PLEASE READ THIS AGREEMENT CAREFULLY.
Garmin Ltd. and its subsidiaries (“Garmin”) grants you a limited license to use the software
embedded in the Garmin Product (the “Software”) in binary executable form in the normal
operation of the Garmin Product. Title, ownership rights, and intellectual property rights in and
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Warnings, Cautions & Notes
to the Software remain with Garmin and/or its third-party providers. You acknowledge that
the Software is the property of Garmin and/or its third-party providers and is protected under
the United States of America copyright laws and international copyright treaties. You further
acknowledge that the structure, organization, and code of the Software are valuable trade secrets
of Garmin and/or its third-party providers and that the Software in source code form remains
a valuable trade secret of Garmin and/or its third-party providers. You agree not to reproduce,
decompile, disassemble, modify, reverse assemble, reverse engineer, or reduce to human readable
form the Software or any part thereof or create any derivative works based on the Software. You
agree not to export or re-export the Software to any country in violation of the export control laws
of the United States of America.
aviation Limited warranty
All Garmin avionics products are warranted to be free from defects in materials or
workmanship for the earlier of: 2 years or 800 flight hours from the date of purchase for
new TSO remote-mount and TSO panel-mount products; 1 year or 400 flight hours from the
date of purchase for new Non-TSO remote-mount* and Non-TSO panel-mount*, portable
products and any purchased newly-overhauled products; 6 months or 200 flight hours for
factory repaired or newly-overhauled products exchanged through a Garmin Authorized
Service Center. Within the applicable period, Garmin will, at its sole option, repair or replace
any components that fail in normal use. Such repairs or replacement will be made at no
charge to the customer for parts or labor, provided that the customer shall be responsible for
any transportation cost. This Limited Warranty does not apply to: (i) cosmetic damage, such
as scratches, nicks and dents; (ii) consumable parts, such as batteries, unless product damage
has occurred due to a defect in materials or workmanship; (iii) damage caused by accident,
abuse, misuse, water, flood, fire, or other acts of nature or external causes; (iv) damage
caused by service performed by anyone who is not an authorized service provider of Garmin;
or (v) damage to a product that has been modified or altered without the written permission
of Garmin. In addition, Garmin reserves the right to refuse warranty claims against products
or services that are obtained and/or used in contravention of the laws of any country.
This Limited Warranty also does not apply to, and Garmin is not responsible for, any
degradation in the performance of any Garmin navigation product resulting from its use
in proximity to any handset or other device that utilizes a terrestrial broadband network
operating on frequencies that are close to the frequencies used by any Global Navigation
Satellite System (GNSS) such as the Global Positioning Service (GPS). Use of such devices
may impair reception of GNSS signals.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Warnings, Cautions & Notes
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF
ALL OTHER WARRANTIES, WHETHER EXPRESS, IMPLIED OR STATUTORY, INCLUDING ANY
LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC
LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.
IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR
CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE OR INABILITY
TO USE THE PRODUCT OR FROM DEFECTS IN THE PRODUCT. SOME STATES DO NOT
ALLOW THE EXCLUSION OF INCIDENTAL OR CONSEQUENTIAL DAMAGES, SO THE ABOVE
LIMITATIONS MAY NOT APPLY TO YOU.
Garmin retains the exclusive right to repair or replace (with a new or newly-overhauled
replacement product) the product or software or offer a full refund of the purchase price at
its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY
BREACH OF WARRANTY.
Online Auction Purchases: Products purchased through online auctions are not eligible for
warranty coverage. Online auction confirmations are not accepted for warranty verification.
To obtain warranty service, an original or copy of the sales receipt from the original retailer is
required. Garmin will not replace missing components from any package purchased through
an online auction.
International Purchases: A separate warranty may be provided by international
distributors for devices purchased outside the U.S. depending on the country. If applicable,
this warranty is provided by the local in-country distributor and this distributor provides
local service for your device. Distributor warranties are only valid in the area of intended
distribution. Devices purchased in the U.S. or Canada must be returned to the Garmin service
center in the U.K., the U.S., Canada, or Taiwan for service.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
Part Number Change Summary
190-01112-12 Initial release.
Rev Date Description
1 July, 2017 Production Release.
2 April, 2017 Added G5 HSI.
3 October, 2017 Added autopilot interface
A December, 2017 Added GMC 507/GFC 500 interface
Updated AFCS Status Display throughout
Added Electronic Stability & Protection (ESP)
Added 'Unable to Charge Battery' indication
Added ability to configure Sky Pointer or Ground Pointer
Other miscellaneous updates for current Software Version
5.00
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A i
Table of Contents
Section 1 System Overview .................................................................................................. 3
1.1 Bezel Overview .................................................................................................................. 3
1.2 micro-SD
™
Cards .................................................................................................................. 4
1.3 System Power-up .............................................................................................................. 5
1.4 Operation ............................................................................................................................ 5
1.4.1 G5 Annunciations ....................................................................................................... 5
1.4.2 Backlight Intensity ...................................................................................................... 8
1.5 Accessing Functionality ................................................................................................... 9
1.5.1 Pages ......................................................................................................................... 9
1.5.2 Menu ....................................................................................................................... 10
1.6 Messages ........................................................................................................................... 10
1.6.1 System Messages ..................................................................................................... 11
Section 2 Flight Instruments .............................................................................................. 13
2.1 PFD Page ........................................................................................................................... 13
2.1.1 Airspeed Indicator .................................................................................................... 14
2.1.2 Attitude Indicator ..................................................................................................... 15
2.1.3 Altimeter .................................................................................................................. 17
2.1.4 Turn Rate Indicator ................................................................................................... 20
2.1.5 Heading/Ground Track (PFD Page)............................................................................. 20
2.1.6 Vertical Speed Indicator (VSI) .................................................................................... 22
2.1.7 Battery Status Indicator ............................................................................................ 23
2.2 HSI Page ............................................................................................................................ 24
2.2.1 Horizontal Situation Indicator (HSI) ........................................................................... 25
2.2.2 Heading/Ground Track (HSI Page) ............................................................................. 27
2.3 Navigation ........................................................................................................................ 28
2.3.1 Course Deviation Indicator (CDI) ............................................................................... 28
2.3.2 Course Selection (optional) ....................................................................................... 31
Section 3 Automatic Flight Control System (Optional) ....................................... 33
3.1 AFCS System Architecture ............................................................................................. 33
3.1.1 Autopilot and Yaw Damper Operation ....................................................................... 33
3.1.2 Flight Control ........................................................................................................... 34
3.1.3 Pitch Axis and Trim ................................................................................................... 34
3.1.4 Roll Axis ................................................................................................................... 34
3.1.5 Yaw Axis .................................................................................................................. 34
3.1.6 G5 AFCS Status Box ................................................................................................. 35
3.2 GFC 500 AFCS Configuration ......................................................................................... 36
3.2.1 GMC 507 Mode Controller ....................................................................................... 37
3.2.2 GSA 28 Servo ........................................................................................................... 37
3.2.3 GFC 500 Messages and Annunciations ..................................................................... 38
3.3 AFCS Operation ................................................................................................................ 39
3.3.1 GMC 507 Controls ................................................................................................... 40
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
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Table of Contents
3.3.2 Flight Director Operation .......................................................................................... 43
3.3.3 Vertical Modes ......................................................................................................... 46
3.3.4 Lateral Modes .......................................................................................................... 54
3.4 GFC 500 AFCS Alerts ........................................................................................................ 64
3.4.1 Trim Alerts ................................................................................................................ 64
3.4.2 Speed Alerts ............................................................................................................. 65
3.5 Electronic Stability & Protection (ESP) (GFC 500) .................................................... 66
3.5.1 Roll Engagement ...................................................................................................... 68
3.5.2 Pitch Engagement .................................................................................................... 69
3.5.3 Airspeed Protection (GFC 500 Only) .......................................................................... 70
Section 4 Additional Features ........................................................................................... 71
4.1 GPS Steering (GPSS) ...................................................................................................... 71
4.1.1 GAD 29B (Optional) ................................................................................................. 71
Section 5 Index ....................................................................................................................Index-1
Index ...................................................................................................................................Index-1
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A 3
System Overview
System Overview Flight Instruments AFCS Additional Features Index
SECTION 1 SYSTEM OVERVIEW
The G5 Electronic Flight Instrument is installed as an attitude display indicator (ADI)
and/or horizontal situation indicator (HSI). The G5 contains integrated attitude/air data
sensors that provide display of attitude and secondary display of air data information.
The G5 can also be interfaced to an external sensor to provide heading information.
The G5 features a bright, sunlight readable, 3.5-inch color display. In the case of
aircraft power loss, the G5 battery sustains the G5 flight display with up to 4 hours of
power.
1.1 BEZEL OVERVIEW
Power/
Backlight
KnobAmbient
Light
Sensor
microSD
™
Card Slot
Figure 1-1 G5 Bezel Overview
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
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System Overview
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
Control Action Description
Power Button Press
Press to turn unit ON. Press and hold for 5
seconds to turn unit OFF. Once on, press to
adjust the backlight.
microSD
™
Card
Slot
Insert microSD card to update software and
log data.
Knob
Press
Press to access the Menu.
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.
Turn
From the Main Menu, turn the Knob to move
the cursor to the desired menu item.
From the PFD Page, rotate to adjust the
barometric setting.
From the HSI Page, rotate to adjust the
heading or track bug.
Turn to select the desired value when editing
numeric data or selecting from a list.
Table 1-1 G5 Controls
1.2 micro-SD
™
CARDS
The G5 data card slot uses micro Secure Digital (SD) cards. The microSD
™
card can
be used for software updates and data logging. The maximum supported card size is
32GB.
Installing an microSD
™
Card:
1)
Insert the microSD
™
card in the microSD
™
card slot with the card contacts
facing down (the card should be flush with the face of the bezel).
2)
To eject the card, gently press on the microSD
™
card to release the spring
latch.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A 5
System Overview
System Overview Flight Instruments AFCS Additional Features Index
1.3 SYSTEM POWER-UP
During system initialization, the G5 displays the message ‘ALIGNING’ over the
attitude indicator. The G5 should display valid attitude typically within the first minute
of power-up. The G5 can align itself both while taxiing and during level flight.
1.4 OPERATION
1.4.1 G5 ANNUNCIATIONS
When a G5 function fails, a 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 .
Figure 1-2 G5 PFD Page Failure Annunciations
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
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System Overview
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
Figure 1-3 G5 HSI Page Failure Annunciations
1.4.1.1 G5 ATTITUDE
The G5 calculates aircraft attitude using information from its built-in inertial sensors.
The G5 also uses GPS and airspeed data to provide the most accurate attitude
information. The G5 should display valid attitude within the first minute of power-up.
If the G5 senses that the attitude solution is valid, but not yet within the internal
accuracy limits, "ALIGNING" is displayed. The displayed attitude information is still
accurate and usable while this indication is shown. The G5 can align itself both while
taxiing and during level flight.
Figure 1-4 Attitude Aligning Indication
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A 7
System Overview
System Overview Flight Instruments AFCS Additional Features Index
If the G5 senses that the attitude solution is invalid, “ALIGNING KEEP WINGS LEVEL”
is displayed. No attitude information is displayed while this indication is shown. The
G5 can align itself both while taxiing and during level flight.
Figure 1-5 Attitude Aligning Keep Wings Level Indication
If the G5 inertial sensors fail, “ATTITUDE FAIL” is displayed in addition to a red-X
flag. No attitude information is displayed while this indication is shown.
Figure 1-6 Attitude Failure Indication
1.4.1.2 G5 HEADING
The G5 can display magnetic heading information received from the GMU 11
magnetometer. If magnetic heading input data is not available, the G5 will display
GPS-derived ground track and the heading field will have a red-X displayed.
Figure 1-7 Heading Fail (PFD Page) Figure 1-8 Heading Fail (HSI Page)
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
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System Overview
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
If both magnetic heading and GPS are unavailable, the heading field will have a
red-X displayed and the compass card will be removed from the HSI.
Figure 1-9 Heading/Track Fail (PFD Page) Figure 1-10 Heading/Track Fail (HSI Page)
The G5 corrects for shifts and variations in the Earth’s magnetic field by applying the
Magnetic Field Variation Database. The Magnetic Field Variation Database is derived
from the International Geomagnetic Reference Field (IGRF). The IGRF is a mathematical
model that describes the Earth’s main magnetic field and its annual rate of change.
The database is updated approximately every 5 years via a software update. Failure to
update this database could lead to erroneous heading information being displayed to
the pilot.
If the G5 senses that the magnetic heading measurement is valid but possibly
outside of the internal accuracy limits, the numeric heading is displayed in yellow.
If the GAD 29B fails, VFR will be displayed in amber text and GPSS will be displayed
in amber text, if GPSS mode is selected.
Figure 1-11 GAD 29B Fail (Amber VFR) Figure 1-12 GAD 29B Fail (Amber GPSS)
1.4.2 BACKLIGHT INTENSITY
When set to Auto, the backlight is automatically adjusted according to ambient
light conditions. When set to Manual, the backlight level is set by the pilot.
Adjusting backlight intensity:
1)
While the unit is turned on, press the Power Button.
2)
Turn the Knob to adjust the backlight intensity.
3)
Press the Knob to close the backlight page.
Setting the backlight intensity to automatic:
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.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A 9
System Overview
System Overview Flight Instruments AFCS Additional Features Index
1.5 ACCESSING FUNCTIONALITY
1.5.1 PAGES
NOTE: The G5 will automatically return to the PFD Page when the aircraft
enters an unusual attitude (if enabled in the system configuration). Refer to
the Installation Manual for more information.
The G5 has two main pages, the HSI Page and the PFD Page. The HSI Page can be
accessed from the PFD Page (unless it has been disabled in configuration).
Figure 1-13 PFD Page Figure 1-14 HSI Page
Displaying the HSI page from the PFD page:
1)
From the PFD Page press the Knob to display the Menu.
2)
Use the Knob to select HSI.
NOTE: The G5 can be configured to power-up on either the PFD or HSI page
(if allowed by the current system configuration). Refer to the Installation
Manual for more information.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A
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System Overview
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
1.5.2 MENU
Press the Knob to access the G5 Menu. Navigate the menu by rotating the Knob
and make selections by pressing the Knob.
Figure 1-15 PFD Page Menu Figure 1-16 HSI Page Menu
1.6 MESSAGES
A message [!] indicator appears in the left corner of PFD and MFD Page to alert the
pilot of any status messages. The message [!] indicator blinks when there is a new
message that has not been viewed.
Figure 1-17 Message [!] Indicator (PFD Page)
Message [!] Indicator
Viewing messages on the PFD and MFD Page:
1)
Press the Knob to display the Menu. The Message Menu Option will
appear.
2)
If necessary, turn the Knob to highlight the Message Menu Option.
3)
Press the Knob to select Message. A list of messages is displayed.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
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System Overview
System Overview Flight Instruments AFCS Additional Features Index
Figure 1-18 Message [!]
Menu Option (PFD Page)
Figure 1-19 Messages [!]
Displayed (PFD Page)
Message [!] Indication
Menu Option
1.6.1 SYSTEM MESSAGES
The following table describes G5 system messages that may appear. System
messages are displayed in white text.
Table 1-2 System Messages
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
Unit is too hot or too cold.
Network address conflict
Another G5 with the same address is detected on
the network (most commonly a wiring error on one
of the units).
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
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System Overview
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
Table 1-2 System Messages
Message Meaning
Communication error
General communication error (most commonly
appears in conjunction with Network Address
Conflict message).
Factory calibration data
invalid
Unit calibration data not valid – unit needs service.
Magnetic field model
database out of date
Internal magnetic field database is out of date -
software update required.
Magnetometer Hardware
fault
The magnetometer has detected a fault – unit
needs service. Heading data may not be available.
Using external GPS data
GPS data from another network LRU is being used.
The unit's internal GPS receiver is enabled, but
unable to establish a GPS fix.
Not receiving RS-232 data
The G5 is not receiving RS-232 data from the GPS
navigator – system needs service.
Not receiving ARINC 429 data
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
The G5 ARINC 429 port is receiving information
from an incorrect source – system needs service.
Software version mismatch
The G5 attitude indicator and the G5 HSI units have
different software. Cross fill of baro, heading and
altitude bugs is disabled.
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
190-01112-12 Rev. A 13
Flight Instruments
System Overview Flight Instruments AFCS Additional Features Index
SECTION 2 FLIGHT INSTRUMENTS
2.1 PFD PAGE
The G5 PFD Page displays a horizon, airspeed, attitude, altitude, vertical speed,
heading, and course deviation information. The following flight instruments and
supplemental flight data are displayed on the PFD Page.
Figure 2-1 G5 PFD Flight Instruments
12
15
16
9
11
13
14
10
1
4
3
8
5
7
6
2
18 172021 1922
1
Airspeed Indicator
2
Attitude Indicator
3
Pitch Scale
4
Current Airspeed
5
Aircraft Symbol
6
Course Deviation Indicator
7
Slip/Skid Indicator
8
Ground Speed (GS)
9
Turn Rate Indicator
10
Altimeter Barometric
Setting
11
Selected Altitude Bug
12
Vertical Speed Indicator
13
Current Altitude
14
VNAV Indicator or Vertical
Deviation Indicator
15
Altimeter
16
Selected Altitude
17
Navigation Course
18
Current Heading or
Ground Track
19
Ground Track
20
Heading or Ground Track
21
Vspeed Reference
22
Battery Status Indicator
G5 Electronic Flight Instrument Pilot's Guide for Certified Aircraft
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Flight Instruments
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
2.1.1 AIRSPEED INDICATOR
NOTE: The G5 Vspeed Reference values depend upon the aircraft’s specific
system configuration and may vary from the examples discussed in this sec-
tion.
The Airspeed Indicator displays airspeed on a rolling number gauge using a moving
tape. The numeric labels and major tick marks on the moving tape are marked at
intervals of 10 knots. Speed indication starts at 30 knots, with 60 knots of airspeed
viewable at any time. The actual airspeed is displayed inside the black pointer. The
pointer remains black until reaching never-exceed speed (V
NE
), at which point it turns
red.
A color-coded (red, white, green, yellow, and red/white “barber pole”) speed range
strip is located on the moving tape. The colors denote flaps operating range, normal
operating range, caution range, and never-exceed speed (V
NE
). A red range is also
present for low speed awareness.
The Airspeed Trend Vector is a vertical, magenta line, extending up or down on the
airspeed scale, shown to the right of the color-coded speed range strip. The end of
the trend vector corresponds to the predicted airspeed in 6 seconds if the current rate
of acceleration is maintained. If the trend vector crosses V
NE
, the text of the actual
airspeed readout changes to yellow. The trend vector is absent if the speed remains
constant or if any data needed to calculate airspeed is not available due to a system
failure.
Figure 2-2 Airspeed Indicator
Ground Speed
Actual Airspeed
Airspeed Trend Vector
Airspeed Color Ranges
Vspeed References
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2.1.1.1 VSPEED REFERENCE
When airspeed is present, the configured Vspeeds are displayed at their respective
locations to the right of the airspeed scale, otherwise the Vspeeds are displayed at the
bottom of the airspeed indicator.
Figure 2-3 Vspeed References
Vspeed References
2.1.2 ATTITUDE INDICATOR
Attitude information is displayed over a virtual blue sky and brown ground with a
white horizon line. The Attitude Indicator displays the pitch (indicated by the yellow
symbolic aircraft on the pitch scale), roll, and slip/skid information.
The horizon line is part of the pitch scale. Pitch markings occur at 2.5˚ intervals
through all pitch ranges. Refer to the Installation Manual to configure the pitch scale.
The inverted white triangle indicates zero on the roll scale. Major tick marks at 30˚
and 60˚ and minor tick marks at 10˚, 20˚, and 45˚ are shown to the left and right of the
zero. Angle of bank is indicated by the position of the pointer on the roll scale.
Slip/skid is indicated by the location of the ball.
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1
Roll Pointer
2
Roll Scale
3
Horizon Line
4
Aircraft Symbol
5
Slip/Skid Indicator
6
Land Representation
7
Pitch Scale
8
Sky Representation
9
Roll Scale Zero
Figure 2-4 Attitude Indicator
5
6
8
7
2
4
3
9
1
Figure 2-5 Attitude Indicator with
Flight Director (Single Cue)
Flight Director
Figure 2-6 Attitude Indicator with
Flight Director (Dual Cue)
2.1.2.1 ATTITUDE CONFIGURATION
The roll (bank angle) indication may be configured to be a Ground Pointer (default)
or a Sky Pointer. Refer to the G5 Installation Manual for configuration information.
The Ground Pointer configuration displays both the roll arc and the pitch ladder
anchored to the horizon and the roll pointer beneath the roll arc pointing to the
present roll angle.
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Figure 2-7 Ground Pointer Configuration
The Sky Pointer configuration displays the pitch ladder moving with the horizon, but
the roll arc remains fixed and centered in the display. The roll pointer beneath the roll
arc moves with the horizon and in the opposite direction of aircraft roll.
Figure 2-8 Sky Pointer Configuration
2.1.3 ALTIMETER
The Altimeter displays 400 feet of barometric altitude values at a time on a rolling
number gauge using a moving tape. Numeric labels and major tick marks are shown
at intervals of 100 feet. Minor tick marks are at intervals of 20 feet. The current
altitude is displayed in the black pointer.
The Selected Altitude is displayed above the Altimeter in the box indicated by a
selection bug symbol. A bug corresponding to this altitude is shown on the tape; if
the Selected Altitude exceeds the range shown on the tape, the bug appears at the
corresponding edge of the tape.
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Setting the selected altitude:
Rotate the ALT SEL Knob on the GMC 507.
Or
1)
Press the Knob to display the Menu.
2)
Select Altitude and use the Knob to change the Selected Altitude.
Syncing to the current altitude:
Press the ALT SEL Knob on the GMC 507.
Or
1)
Press the Knob to display the Menu.
2)
Select Altitude and press and hold the Knob to sync the Selected Altitude
to the current altitude
Figure 2-9 Altimeter
Selected
Altitude
Selected
Altitude Bug
Barometric
Setting
2.1.3.1 BAROMETRIC PRESSURE
The barometric pressure setting is displayed below the Altimeter in inches of mercury
(Hg), hectopascals (hPa), or milibars (mb) when metric units are selected.
Selecting the altimeter barometric pressure setting:
Turn the Knob to set the barometric pressure.
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2.1.3.2 ALTITUDE ALERTING
The Altitude Alerting function provides the pilot with a visual alert and tone when
approaching the Selected Altitude. Whenever the Selected Altitude is changed, the
Altitude Alerter is reset. The following will occur when approaching the Selected
Altitude:
•Passing within 1,000 feet of the Selected Altitude, the Selected Altitude (shown
above the Altimeter) flashes for 5 seconds.
•When the aircraft passes within 200 feet of the Selected Altitude, the Selected
Altitude flashes for 5 seconds to indicate that the aircraft is approaching the
selected altitude.
•After reaching the Selected Altitude, if the pilot flies outside the deviation band
(±200 Feet of the Selected Altitude), the Selected Altitude changes to yellow text
on a black background, flashes for 5 seconds.
Figure 2-10 Altitude Alerting Visual Annunciation
Deviation of ±200 feet
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2.1.4 TURN RATE INDICATOR
The Turn Rate Indicator is located at the bottom of the PFD Page. Tick marks to
the left and right of the displayed heading denote standard turn rates (3 deg/sec).
A magenta Turn Rate Trend Vector shows the current turn rate. A standard-rate turn
is shown on the indicator by the trend vector stopping at the standard turn rate tick
mark.
Figure 2-11 Turn Rate Indicator
Turn Rate Indicator
(Standard Rate Tick Marks)
Turn Rate
Trend Vector
2.1.5 HEADING/GROUND TRACK (PFD PAGE)
NOTE: Heading is displayed if magnetometer data is available from a mag-
netometer via the CAN network. Otherwise, Ground Track is displayed.
A Heading/Ground Track Tape is displayed at the top of the PFD Page and displays
numeric labels every 10°. Major tick marks are at 5° intervals and minor tick marks
at 1° intervals. The current track is represented by a magenta triangle. The Heading/
Ground Track Tape also displays the navigation course.
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When displaying the Selected Heading, a light blue bug on the tape corresponds to
the Selected Heading. When displaying Ground Track, a magenta bug is displayed on
the tape. The heading bug turns hollow when GPSS is selected.
Adjusting the selected heading or ground track:
Use the HDG Knob on the GMC 507.
O
r
1)
Press the Knob to display the Menu.
2)
Select Heading or Track and use the Knob to change the Selected
Heading or Track.
Syncing to the current heading or ground track:
Press the HDG Knob on the GMC 507.
O
r
1)
Press the Knob to display the Menu.
2)
Select Heading or Track and press and hold the Knob to sync the selected
heading or ground track to the current heading or ground track.
Figure 2-12 PFD Page - Selected Heading
Current
Heading
Ground
Track
Selected
Heading
Bug
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Figure 2-13 PFD Page - Selected Ground Track
Current
Ground
Track
Selected
Ground
Track Bug
2.1.6 VERTICAL SPEED INDICATOR (VSI)
The Vertical Speed Indicator displays the aircraft vertical speed using a non-moving
tape with minor tick marks every 100 feet. The current vertical speed is displayed using
a white arrow along the tape.
Figure 2-14 Vertical Speed Indicator
Current Vertical Speed
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2.1.7 BATTERY STATUS INDICATOR
When the G5 is powered by the aircraft electrical bus, the battery status indicator
can be displayed by pressing the G5 power button. When the G5 is powered by the
battery, the battery status indicator is displayed automatically. This indicator shows the
estimated percent charge of the battery. After about one minute on battery power, the
indicator shows the estimated time (in hours and minutes) until the battery is empty.
The current charge level of the battery is indicated by the filled-in portion of the battery
icon. The battery icon turns yellow or red to indicate a low-battery condition
3:15
41%-100%
1:31
21%-40%
0:38
0%-20%
The battery is required for the G5 unit installed as an attitude display indicator (ADI)
and is optional for the G5 unit installed as a horizontal situation indicator (HSI)
When the G5 is connected to external power and the battery is being charged, a
lightning bolt symbol appears over the battery icon.
92%
Charging
Other battery indications:
Battery charger hardware fault, or temperature too high/low to
safely charge the battery. The system is running on external power
but cannot charge the battery.
BATT
Battery fault.
NO BATT
Battery is not present (appears only when the battery status field
has been configured to always appear).
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2.2 HSI PAGE
NOTE: The HSI Page can be configured as disabled in configuration mode.
The G5 HSI Page displays a rotating compass card in a heading-up orientation.
Letters indicate the cardinal points and numeric labels occur every 30˚. Major tick
marks are at 10˚ intervals and minor tick marks at 5˚ intervals. The current ground track
is represented on the HSI by magenta triangle and a dashed line. The HSI also presents
course deviation, bearing, and navigation source information. The following items are
displayed on the HSI Page:
Figure 2-15 Horizontal Situation Indicator (HSI)
8
7
2
4
5
3
1
GPS Steering Indicator
2
Battery Status Indicator
3
Navigation Source
4
Aircraft Symbol
5
Navigator Messages
6
Rotating Compass Rose
7
Ground Speed
8
Selected Heading
9
OBS Annunciator
10
Course Deviation Indica-
tor (CDI)
11
GPS CDI Scale
12
Bearing Pointer
13
Heading Bug
14
Distance To Waypoint
15
Current Heading
16
Current Ground Track
Indicator
6
9
15
12
11
10
1
16
13
14
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Table 2-1 Annunciations
3
Nav Source Annunciations
11
GPS CDI Scale Annunciations
GPS/
GPS1/
GPS2
VLOC/
VLOC1/
VLOC2
VOR/
VOR1/
VOR2
LOC/
LOC1/
LOC2
LP LPV LNAV
LNAV/VNAV LNAV+V APR
TERM ENR OCN
VFR (0.25nm, 1.25nm, 5.00nm)
5
Navigator Messages Annunciations
LOI Loss of GPS Integrity MSG Pending Nav Message
DR GPS Dead-Reckoning Mode WPT Waypoint Arrival
NOTE: The VFR CDI Scale is displayed when the G5 is connected to a GPS
navigator via RS-232 only, or if ARINC 429 GPS navigation data is unavailable.
2.2.1 HORIZONTAL SITUATION INDICATOR (HSI)
The Horizontal Situation Indicator (HSI) on the HSI Page displays a rotating compass
card in a heading-up orientation. Letters indicate the cardinal points and numeric
labels occur every 30˚. Major tick marks are at 10˚ intervals and minor tick marks at
5˚ intervals. The current track is represented on the HSI by magenta triangle and a
dashed line. The HSI also presents course deviation, bearing, and navigation source
information.
Displaying the HSI page from the PFD page:
1)
From the PFD Page press the Knob to display the Menu.
2)
Select HSI.
2.2.1.1 BEARING POINTERS
One or two bearing pointers can be displayed on the HSI for NAV (VOR) and GPS
sources. The bearing pointers are light blue. The bearing pointers never override the
CDI and are visually separated from the CDI by a white ring (shown when the bearing
pointers are selected but not necessarily visible due to data unavailability). If there are
two navigation inputs configured, two bearing pointers will be displayed.
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Figure 2-16 GPS Source Bearing Pointer Figure 2-17 VOR Source Bearing Pointer
Bearing Pointer
Bearing Pointer
Enabling/disabling the bearing pointer(s):
1)
From the HSI Page, press the Knob to display the Menu.
2)
Turn the Knob to highlight Setup.
3)
Press the Knob and turn to highlight the Bearing Pointer 1 setting.
Figure 2-18 Setup Menu
Figure 2-19 Bearing Pointer Setting
4)
Press the Knob and turn to select bearing pointer source (None, GPS,
VLOC).
5)
Repeat steps 1-4 to enable/disable the Bearing Pointer 2 setting.
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Figure 2-20 Bearing Pointer Source Options
2.2.2 HEADING/GROUND TRACK (HSI PAGE)
The Selected Heading or Ground Track is shown to the right of the HSI. The light blue
bug (heading) or magenta bug (ground track) on the compass rose corresponds to the
Selected Heading or Ground Track.
NOTE: Heading is displayed if magnetometer data is available from a mag-
netometer via the CAN network. Otherwise, Ground Track is displayed.
Adj
usting the selected heading or ground track from the HSI page:
Use the HDG Knob on the GMC 507.
O
r
From the HSI Page, turn the Knob to adjust the selected heading or ground
track.
Syn
cing to the current heading or ground track from the HSI page:
Press the HDG Knob on the GMC 507.
O
r
From the HSI Page, press and hold the Knob to sync to the current heading
or ground track.
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2.3 NAVIGATION
The G5 will only display data from the #1 navigation source. If the navigation source
is a GNS/GTN unit, both GPS and VLOC data can be displayed
2.3.1 COURSE DEVIATION INDICATOR (CDI)
The PFD Page displays the Course Deviation Indicator (CDI) below the slip/skid
indicator. The HSI Page displays the CDI on the Horizontal Situation Indicator.
The Course Deviation Indicator (CDI) move left or right along a lateral deviation
scale to display the aircraft position relative to the course. If the course deviation data
is not valid, the CDI is not displayed.
The CDI is capable of displaying multiple sources of navigation (GPS, VLOC, or both)
depending on the external navigator(s) configured (refer to the G5 Installation Manual
for more information). Color indicates the current navigation source: magenta (for
GPS) or green (for VOR and LOC). The full-scale limits for the CDI are defined by a
GPS-derived distance when coupled to GPS. When coupled to a VOR or localizer (LOC),
the CDI has the same angular limits as a mechanical CDI.
Figure 2-21 Course Deviation Indicator (PFD Page)
Course
Deviation
Indicator
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Figure 2-22 Course Deviation Indicator (HSI Page)
Course
Deviation
Indicator
Changing the navigation source (GPS, VOR, LOC, or VLOC):
Use the #1 external navigator to toggle between GPS and VOR/LOC source
types.
2.3.1.1 VERTICAL DEVIATION (GLIDESLOPE) INDICATOR - ILS
SOURCE
The Vertical Deviation (Glideslope) Indicator (VDI) appears to the left of the altimeter
(PFD page) and to the right of the compass rose (HSI page) whenever an ILS frequency
is tuned in the active NAV field of an external navigator. A green diamond acts as the
VDI, like a glideslope needle on a conventional indicator. If a localizer frequency is
tuned and there is no glideslope signal, “NO GS” is annunciated.
Figure 2-23 Vertical Deviation Indicator
(Glideslope ILS Source) (PFD Page)
Vertical
Deviation
Indicator
Figure 2-24 Vertical Deviation Indicator
(Glideslope ILS Source) (HSI Page)
Vertical
Deviation
Indicator
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2.3.1.2 VERTICAL DEVIATION (GLIDEPATH) INDICATOR - GPS
SOURCE
The Vertical Deviation (Glidepath) Indicator (VDI) also appears to the left of the
altimeter (PFD page) and to the right of the compass rose (HSI page) during a GPS
approach. The glidepath is analogous to the glideslope for GPS approaches supporting
WAAS vertical guidance (LNAV+V, L/VNAV, LPV). The Glidepath Indicator appears
on the G5 as a magenta diamond. If the approach type downgrades past the final
approach fix (FAF), “NO GP” is annunciated.
Figure 2-25 Vertical Deviation Indicator
(Glidepath GPS Source) (PFD Page)
Vertical
Deviation
Source
Figure 2-26 Vertical Deviation
Indicator Position (HSI Page)
Vertical
Deviation
Indicator
Vertical
Deviation
Indicator
Vertical
Deviation
Source
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2.3.2 COURSE SELECTION (OPTIONAL)
When the G5 is receiving VOR or LOC data, a Course menu option is displayed.
Setting the course for a VOR or localizer:
1)
From the HSI Page, press the Knob to display the Menu.
2)
Select Course and use the Knob to adjust the course.
Figure 2-27 Course on HSI Page
When OBS is activated on the navigator, an OBS menu option is displayed.
Setting the OBS:
1)
From the HSI Page, press the Knob to display the Menu.
2)
Select OBS and use the Knob to adjust the course.
Figure 2-28 OBS on HSI Page
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SECTION 3 AUTOMATIC FLIGHT CONTROL
SYSTEM (OPTIONAL)
NOTE: The approved Pilot’s Operating Handbook (POH) always supersedes
the information in this Pilot’s Guide.
NOTE: Refer to the approved Pilot’s Operating Handbook (POH) for emergency
procedures.
NOTE: A GMC 507 controller is required for GFC 500 AFCS functionality.
3.1 AFCS SYSTEM ARCHITECTURE
An Automatic Flight Control System (AFCS) is typically comprised of two major
components: A Flight Director (FD) and Autopilot servos. The Flight Director provides
pitch and roll commands to the autopilot servos. These pitch and roll commands are
displayed on the PFD Page as Command Bars. When the Flight Director is active the
pitch and roll commands can be hand-flown by the pilot or when coupled with the
autopilot, the autopilot servos drive the flight controls to follow the commands issued
by the Flight Director. The Flight Director operates independently of the autopilot
servos, but in most cases the autopilot servos can not operate independent of the
Flight Director.
3.1.1 AUTOPILOT AND YAW DAMPER OPERATION
The autopilot and optional yaw damper operate the flight control surface servos
to provide automatic flight control. The autopilot controls the aircraft pitch and roll
attitudes following commands received from the flight director. Pitch, Roll, and Yaw
(if installed) autotrim provides trim commands to each servo to relieve any sustained
effort required by the servo(s). Autopilot operation is independent of the optional yaw
damper.
The optional yaw damper reduces Dutch roll tendencies, coordinates turns, and
provides a steady force to maintain directional trim. It can operate independently
of the autopilot and may be used during normal hand-flight maneuvers. Yaw rate
commands are limited to 6 deg/sec by the yaw damper.
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3.1.2 FLIGHT CONTROL
Pitch and roll commands are provided to the servos based on the active flight
director modes. Yaw commands are provided by the yaw servo. Servo motor control
limits the maximum servo speed and torque. This allows the servos to be overridden
in case of an emergency.
3.1.3 PITCH AXIS AND TRIM
The autopilot pitch axis uses pitch rate to stabilize the aircraft pitch attitude during
flight director maneuvers. Flight director pitch commands are rate and attitude-limited,
combined with pitch damper control, and sent to the pitch servo motor. The pitch servo
measures the output effort (torque) and optionally provides this signal to the pitch trim
motor. The pitch servo commands the pitch trim motor to reduce the average pitch
servo effort.
3.1.4 ROLL AXIS
The autopilot roll axis uses roll rate to stabilize aircraft roll attitude during flight
director maneuvers. The flight director roll commands are rate- and attitude-limited,
combined with roll damper control, and sent to the roll servo motor.
3.1.5 YAW AXIS
The yaw damper uses yaw rate and roll attitude to dampen the aircraft’s natural
Dutch roll response. It also uses lateral acceleration to coordinate turns and reduce
or eliminate the need for the pilot to use rudder pedal force to maintain coordinated
flight during climbs and descents.
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3.1.6 G5 AFCS STATUS BOX
The AFCS status box displays Autopilot (AP) and Flight Director (FD) mode
annunciations on the PFD Page.
Autopilot (AP) status is displayed middle of the G5 Autopilot Status Box. Lateral
modes are displayed on the left, and vertical modes are displayed on the right. Armed
modes are displayed in white and active in green.
Figure 3-1 Autopilot Status Box
Autopilot
Status
Active Armed
Active
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3.2 GFC 500 AFCS CONFIGURATION
The following figure provides an overview of the GFC 500 system:
Figure 3-2 Core GFC 500 System
GMC 507 Autopilot Mode
Controller
G5
Control Yoke
GSA 28 Servos
In addition to the core autopilot functions, the GFC 500 incorporates an independent
monitor that uses independent inertial sensors to determine what is happening to the
aircraft. By monitoring aircraft attitude, attitude rate and accelerations using these
independent sensors, the monitor can shut down the autopilot if it determines the
aircraft has exceeded predetermined limits.
The minimum configuration for the G500 system is a G5 configured as an Attitude
Indicator and two GSA 28 servos (in the pitch and roll positions). This will provide
Pitch, Roll, Track, and Air Data modes only.
If navigation modes are desired, a G5 connected to a compatible navigation source
(e.g., a GTN 6XX/7XX) is an option.
The basic GFC 500 system is comprised of the following equipment:
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3.2.1 GMC 507 MODE CONTROLLER
The panel-mounted GMC 507 serves as the primary user interface for the GFC 500.
The GMC 507 provides autopilot and Flight Director mode selection buttons and a
wheel for convenient adjustment of the pitch, airspeed, and vertical speed references.
The G5 PFD Page displays active and armed modes and reference values.
Figure 3-3 GMC 507
3.2.2 GSA 28 SERVO
The GSA 28 servos provide control surface actuation as part of the autopilot, yaw
damper, electric trim, and ESP functions. The GSA 28 is a ‘smart’ servo which performs
most of the autopilot processing functions and offers many inherent safety features.
The brushless motor and electronic torque and speed sensing capabilities provide
smooth, reliable operation. The GSA 28 design incorporates an internal engagement
solenoid and a gear train that allows the motor to be backdriven by the pilot in case
the solenoid fails to disengage. This eliminates the need for a mechanical slip clutch
along with the associated performance limitations and maintenance requirements.
Figure 3-4 GSA 28
NOTE: Refer to the G5 Installation Manual for information on installing and
configuring the G5 Integrated Autopilot Interface.
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3.2.3 GFC 500 MESSAGES AND ANNUNCIATIONS
Table 3-1 GFC 500 Messages and Annunciations
Autopilot Messages
AFCS Controller Key
Stuck
The system has sensed a key input on the GMC 507 for 30
seconds or longer.
AFCS Controller Audio
Database Missing
The audio database is missing from the GMC 507. The aural
voice alerts will not be heard.
Servo Clutch Fault
One or more autopilot servos has a stuck clutch. The servo
needs service.
Servo Trim Input Fault
The inputs to the trim system are invalid. The trim system
needs service.
Autopilot Annunciations
Autopilot has failed. Autopilot and trim are inoperative and
flight director is not available.
Autopilot normal disconnect.
Autopilot abnormal disconnect.
Autopilot has failed. The autopilot is inoperative. FD modes
may still be available.
Autopilot Overspeed Protection mode is active. Autopilot
will raise the nose to limit the aircraft’s speed.
Autopilot Underspeed Protection mode is active. Autopilot
will lower the nose to prevent the aircraft’s speed from
decreasing.
Autopilot preflight test is in progress.
Pitch Trim Fail – Manual Electric Pitch Trim is inoperative.
Elevator Trim Down – Autopilot is holding elevator nose
down force. The pitch trim needs to be adjusted nose down.
Elevator Trim Up – Autopilot is holding elevator nose up
force. The pitch trim needs to be adjusted nose up.
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3.3 AFCS OPERATION
The AFCS provides the following main operating functions:
•Flight Director (FD) — The Flight Director function provides pitch and roll
commands needed to guide the aircraft toward the active reference selected by
the pilot. These pitch and rolls commands are displayed on the G5 PFD Page as
Command Bars. When the Flight Director is active the pitch and roll commands
can be hand-flown by the pilot. When the Autopilot is engaged the autopilot
servos drive the flight controls to follow the commands issued by the Flight
Director.
•Autopilot (AP) — The Autopilot function is provided by servo actuators which
move the flight control surfaces in response to Flight Director steering commands,
aircraft attitude, and airspeed. The optional pitch auto-trim function serves to
relieve any sustained effort required by the pitch servo to keep the aircraft in trim.
•Yaw Damper (YD) — The optional Yaw Damper function provides Dutch Roll
damping, assists in turn coordination, and provides a steady force to help maintain
directional trim. If installed the YD comes on when the autopilot is engaged. It
can be turned on/off independent of the autopilot and may be used during normal
hand-flying maneuvers.
•Manual Electric Trim (MET) — The optional Manual Electric Trim uses the same
servo as the auto-trim function and allows the pilot to command trim via a trim
switch when the autopilot is not engaged. The MET function does not preclude
the use of the aircraft’s basic mechanical trim system.
•Electronic Stability & Protection (ESP) (GFC 500) — The ESP function
provides a soft barrier to keep the aircraft within the desired operating envelope
when the autopilot is not engaged. When the AFCS senses that the aircraft is near
the defined operating limit in pitch attitude, roll attitude, high airspeed, or low
airspeed, the ESP function will automatically engage one or more servos to nudge
it back to the nominal operating envelope. While ESP utilizes the same sensors,
processors, and actuators as the AFCS autopilot it is a separate mutually exclusive
function. ESP can be easily overpowered by the pilot and can be disabled using
the AP DISC / TRIM INT button.
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3.3.1 GMC 507 CONTROLS
Table 3-2 AFCS Controls
1
HDG Key Selects/deselects Heading Select Mode. (Used for TRK
Mode in installations without a magnetometer)
2
NAV Key Selects/deselects Navigation Mode. Cancels GS Mode if
LOC Mode is either active or armed. Cancels GP Mode if
GPS Mode is either active or armed. Cancels LOC Mode if
GPS Mode is active and LOC Mode is armed.
3
AP Key Engages/disengages the autopilot
4
LVL (Level) Key Engages the autopilot (if the autopilot is disengaged) in
level vertical and lateral modes
5
NOSE UP/DN
Wheel
Adjusts the vertical mode reference in Pitch Hold, Vertical
Speed, Indicated Airspeed, and Altitude Hold modes
6
IAS Key Selects/deselects Indicated Airspeed Mode
7
ALT Key Selects/deselects Altitude Hold Mode
8
VNAV Key Selects/deselects Vertical Path Tracking Mode for Vertical
Navigation flight control
9
VS Key Selects/deselects Vertical Speed Mode
10
YD Key Engages/disengages the yaw damper
11
FD Key Activates/deactivates the flight director only
Pressing once turns on the director in the default vertical
and lateral modes. Pressing again deactivates the
flight director and removes the Command Bars. If the
autopilot is engaged, the key is disabled.
12
APR Key Selects/deselects Approach Mode (GP or GS mode only)
13
HDG/TRK Knob Selects the desired Heading/Track
14
ALT SEL Knob Selects the desired Altitude setting
15
TRK Key Selects/deselects Track (TRK) Mode.
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Figure 3-5 GMC 507 AFCS Control Unit
13
12 3 4 5 14
710 91 11
6
8
2
15
The following AFCS controls are located separately from the G5 and GMC 507 AFCS
Control Unit:
Table 3-3 Other AFCS Controls
Control Action
AP DISC / TRIM INT
(Autopilot
Disconnect)
An AP DISC / TRIM INT Button is located on the pilot’s control
stick.
Press and release the AP DISC / TRIM INT Button to
disengage the autopilot.
Go Around Button
(Takeoff/Go
Around)
Selects flight director Takeoff or Go Around Mode.
MET Switch
(Optional)
(Manual Electric
Trim)
Used to command manual electric pitch trim.
3.3.1.1 ENGAGING THE AUTOPILOT
E
nGaGinG the autopiLot (GmC 507)
:
An initial press of the AP Key on the GMC 507 will activate the Flight
Director and engage the autopilot in the default PIT and ROL modes.
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3.3.1.2 DISENGAGING THE AUTOPILOT
The Autopilot is manually disengaged by pressing the autopilot disconnect button
on the control stick or yoke or by pressing the AP Key on the GMC 507. Manual
disengagement is indicated by a five-second flashing yellow ‘AP’ annunciation. Cancel
the aural alert by pressing and releasing the AP Button again.
In addition, the optional MET trim switch will disengage the autopilot.
Automatic disengagement is indicated by a flashing red ‘AP’ annunciation. Automatic
disengagement occurs due to:
•System failure
•Invalid sensor data
•Inability to compute default autopilot modes
•Autopilot internal monitoring detects abnormal behavior
3.3.1.3 OVERPOWERING AUTOPILOT SERVOS
In the context of this discussion, “overpowering” refers to any pressure or force
applied to the pitch controls when the autopilot is engaged. A small amount of
pressure or force on the pitch controls can cause the autopilot automatic trim to run to
an out-of-trim condition. Therefore, any application of pressure or force to the controls
should be avoided when the autopilot is engaged.
Overpowering the autopilot during flight will cause the autopilot’s automatic trim to
run, resulting in an out-of-trim condition or cause the trim to hit the stop if the action
is prolonged. In this case, larger than anticipated control forces may be required after
the autopilot is disengaged.
The following steps should be added to the preflight check:
1)
Check for proper autopilot operation and ensure the autopilot can be
overpowered.
2)
Note the forces required to overpower the autopilot servo clutches.
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3.3.2 FLIGHT DIRECTOR OPERATION
NOTE: Refer to the Installation Manual for AFCS setup information.
The flight director function provides pitch and roll commands to the pilot and
autopilot, which are displayed on the PFD Page. With the flight director active, the
aircraft can be hand-flown to follow the path shown by the Command Bars. The Flight
Director has the following maximum commands: pitch (-15°, +20°) and roll (30°)
angles.
3.3.2.1 ACTIVATING THE FLIGHT DIRECTOR
An initial press of a key listed in the table below (when the flight director is not
active) activates the flight director in the listed modes. The flight director may be
turned off and the Command Bars removed from the display by pressing the FD Key
again. The FD Key is disabled when the autopilot is engaged.
Table 3-4 Flight Director Activation (GMC 507)
Control Pressed
Modes Selected
Lateral Vertical
FD Key Roll Hold (default) ROL Pitch Hold (default) PIT
AP Key Roll Hold (default) ROL Pitch Hold (default) PIT
GA Button
Takeoff (on-ground)
Go Around (in-air)
TO
GA
Takeoff (on-ground)
Go Around (in-air)
TO
GA
ALT Key Roll Hold (default) ROL Altitude Hold ALT
VS Key Roll Hold (default) ROL Vertical Speed VS
VNAV Key Roll Hold (default) ROL
Vertical
Navigation*
VNAV
IAS Key Roll Hold (default) ROL Indicated Airspeed IAS
APR Key Approach**
GPS/VOR/
LOC/ILS
Pitch Hold (default) PIT
NAV Key Navigation**
GPS/VOR/
LOC
Pitch Hold (default) PIT
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Table 3-4 Flight Director Activation (GMC 507)
Control Pressed
Modes Selected
Lateral Vertical
HDG Key Heading Select HDG Pitch Hold (default) PIT
TRK Key Track Select TRK Pitch Hold (default) PIT
LVL Key Level Hold LVL Level Hold LVL
*Must be receiving VNAV data from a GPS navigator.
**The selected navigation receiver must have an active GPS course before
NAV
or
APR
Key press
activates flight director.
3.3.2.2 FLIGHT DIRECTOR MODES
Flight director modes are normally selected independently for the pitch and roll axes.
Unless otherwise specified, all mode keys are alternate action (i.e., press on, press off).
In the absence of specific mode selection, the flight director reverts to the default pitch
and/or roll modes.
Armed modes are annunciated in white and active in green in the AFCS Status Box.
Under normal operation, when the control for the active flight director mode is pressed,
the flight director reverts to the default mode(s) for the axis(es). Automatic transition
from armed to active mode is indicated by the white armed mode annunciation moving
to the green active mode field and flashing for 10 seconds.
If the information required to compute a flight director mode becomes invalid or
unavailable, the flight director automatically reverts to the default mode for that axis.
A flashing yellow mode annunciation and annunciator light indicate loss of sensor or
navigation data required to compute commands. When such a loss occurs, the system
automatically begins to roll the wings level (enters Roll Hold Mode) or maintain the
pitch angle (enters Pitch Hold Mode), depending on the affected axis. The flashing
annunciation stops when the affected mode key is pressed or another mode for the
axis is selected. If after 10 seconds no action is taken, the flashing annunciation stops.
The flight director is automatically disabled if the attitude information required to
compute the default flight director modes becomes invalid or unavailable.
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3.3.2.3 COMMAND BARS
Upon activation of the flight director, Command Bars are displayed in magenta on
the PFD Page. If the aircraft is being flown by hand, the command bars are displayed
hollow. The Command Bars do not override the Aircraft Symbol. The Command Bars
move together vertically to indicate pitch commands and bank left or right to indicate
roll commands.
Hollow Command Bars (Pilot Hand Flying Aircraft, FD Only)
Figure 3-6 Command Bars (Single Cue Flight Director)
Aircraft Symbol
Solid Command Bars (Autopilot Engaged)
Figure 3-7 Flight Director (Dual Cue)
Flight
Director
If the attitude information being sent to the flight director becomes invalid or
unavailable, the Command Bars are removed from the display.
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3.3.3 VERTICAL MODES
The table lists the vertical modes with their corresponding controls and annunciations.
The mode reference is displayed next to the active mode annunciation for Altitude
Hold, Vertical Speed, and Indicated Airspeed modes. The NOSE UP/DN Wheel can be
used to change the vertical mode reference while operating under Pitch Hold, Vertical
Speed, Indicated Airspeed, or Altitude Hold modes. Increments of change of values for
each of these references using the NOSE UP/DN Wheel, are also listed in the table.
Table 3-5 Flight Director Vertical Modes
Vertical
Mode
Description Control Annunciation
Reference
Change
Increment
Pitch Hold
Holds the current aircraft pitch
attitude; may be used to climb/
descend to the Selected Altitude
(default) PIT 0.5°
Selected
Altitude
Capture
Captures the Selected Altitude * ALTS
10 ft
Altitude
Hold
Holds the current Altitude ALT Key ALT
Vertical
Speed
Maintains the current aircraft
vertical speed; may be used to
climb/descend to the Selected
Altitude
VS Key VS 100 fpm
Indicated
Airspeed
(IAS)
Maintains the current aircraft
airspeed in IAS while the aircraft
is climbing/descending to the
Selected Altitude
IAS Key IAS 1 kt
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Table 3-5 Flight Director Vertical Modes
Vertical
Mode
Description Control Annunciation
Reference
Change
Increment
Vertical
Navigation
Captures and tracks descent legs
of an active vertical profile
VNAV Key VNAV
Glidepath
Captures and tracks the GPS
WAAS glidepath on approach
APR Key
GP
Glideslope
Captures and tracks the ILS
glideslope on approach
GS
Takeoff
Commands a constant pitch
angle and wings level on-ground
in preparation for takeoff
GA Button
TO
Go Around
Commands a constant pitch
angle and wings level in the air
GA
* ALTS armed automatically when PIT, VS, IAS, TO, or GA active, and under VNAV when Selected
Altitude is to be captured instead of VNAV Target Altitude
PITCH HOLD MODE (PIT)
When the flight director is activated (FD key pressed) or when the Autopilot is
activated, Pitch Hold Mode is selected by default. Pitch Hold Mode is indicated as the
active vertical mode by the green ‘PIT’ annunciation. This mode may be used for climb
or descent to the Selected Altitude (shown above the Altimeter), since Selected Altitude
Capture Mode is automatically armed when Pitch Hold Mode is activated.
In Pitch Hold Mode, the flight director maintains a constant pitch attitude. The pitch
reference is set to the aircraft pitch attitude at the moment of mode selection. If the
aircraft pitch attitude exceeds the flight director pitch command limitations, the flight
director commands a pitch angle equal to the nose-up/down limit.
Changing the pitch reference:
When operating in Pitch Hold Mode, the pitch reference can be adjusted by
using the
NOSE UP/DN
Wheel.
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Figure 3-8 Pitch Hold & Selected Altitude Capture Modes
Pitch Hold
Mode Active
Selected
Altitude
Selected Altitude
Capture Mode
Armed
3.3.3.1 SELECTED ALTITUDE CAPTURE MODE (ALTS)
Selected Altitude Capture Mode is automatically armed with activation of the
following modes:
•PitchHold
•VerticalSpeed
•IndicatedAirspeed
•TO/GoAround
•VerticalPathTracking
The white ‘ALTS’ annunciation indicates Selected Altitude Capture Mode is armed.
Figure 3-9 Selected Altitude Capture Mode (Armed)
As the aircraft nears the Selected Altitude, the flight director automatically transitions
to Selected Altitude Capture Mode with Altitude Hold Mode armed. This automatic
transition is indicated by the green ‘ALTS’ annunciation flashing for up to 10 seconds
and the appearance of the white ‘ALTS’ annunciation.
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At 50 feet from the Selected Altitude, the flight director automatically transitions
from Selected Altitude Capture to Altitude Hold Mode and holds the reference altitude.
As Altitude Hold Mode becomes active, the white ‘ALTS’ annunciation moves to the
active vertical mode field and flashes green for 10 seconds to indicate the automatic
transition.
Setting the selected altitude:
Use the ALT SEL Knob on the GMC 507 to adjust the selected altitude.
O
r
1)
Press the Knob to display the Menu.
2)
Select Altitude and use the Knob to change the Selected Altitude.
Syncing to the current altitude:
Press the Knob on the GMC 507.
O
r
1)
Press the Knob to display the Menu.
2)
Select Altitude and press and hold the Knob to sync the Selected Altitude
to the current altitude
Changing the Selected Altitude while Selected Altitude Capture Mode is active
causes the autopilot to revert to Pitch Hold Mode with Selected Altitude Capture Mode
armed for the new Selected Altitude.
3.3.3.2 ALTITUDE HOLD MODE (ALT)
Altitude Hold Mode can be activated by pressing the
ALT
Key; the AFCS maintains
the current aircraft altitude (to the nearest 10 feet) as the Altitude Reference. Altitude
Hold Mode active is indicated by a green ‘ALT’ annunciation in the G5 Autopilot Status
Box.
Altitude Hold Mode is automatically armed when in Selected Altitude Capture Mode.
Selected Altitude Capture Mode automatically transitions to Altitude Hold Mode when
within 50 feet of the Selected Altitude. In this case, the Selected Altitude becomes the
Altitude Reference.
3.3.3.2.1 ChanGinG the aLtitude referenCe
When operating in Altitude Hold Mode, the Altitude Reference can be adjusted in
the following ways:
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•The Altitude Reference can be adjusted up or down in 10-foot increments
by rolling the NOSE UP/DN Wheel. Using this method, up to 200 feet of
altitude change can be commanded. To change the Altitude Reference by
more the 200 feet, use another vertical mode (PIT, VS) to capture the desired
Selected Altitude.
Figure 3-10 Altitude Hold Mode
Altitude Hold
Mode Active
3.3.3.3 VERTICAL SPEED MODE (VS)
In Vertical Speed Mode, the flight director acquires and maintains a Vertical Speed
Reference. Current aircraft vertical speed (to the nearest 100 fpm) becomes the Vertical
Speed Reference at the moment of Vertical Speed Mode activation. This mode may be
used for climb or descent to the Selected Altitude (shown above the Altimeter) since
Selected Altitude Capture Mode is automatically armed when Vertical Speed Mode is
selected.
When Vertical Speed Mode is activated by pressing the
VS
Key, ‘VS’ is annunciated
in green in the Autopilot Status Box. The Vertical Speed Reference is also displayed
below the Vertical Speed Indicator. A Vertical Speed Reference Bug corresponding to
the Vertical Speed Reference is shown on the indicator.
Figure 3-11 Vertical Speed Reference on PFD Page
Vertical Speed
Reference Bug
Vertical Speed
Reference
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3.3.3.3.1 ChanGinG the vertiCaL Speed referenCe
Use the
NOSE UP/DN
Wheel to adjust the Vertical Speed Reference in increments
of 100 fpm.
Figure 3-12 Vertical Speed Mode
Vertical
Speed
Mode
Active
3.3.3.4 INDICATED AIRSPEED MODE (IAS)
Indicated Airspeed
Mode is selected by pressing the
IAS
Key on the GMC.
This mode acquires and maintains the Airspeed Reference (IAS) while climbing or
descending. When Indicated Airspeed Mode is active, the flight director continuously
monitors Selected Altitude, airspeed and altitude.
The Airspeed Reference is set to the current airspeed upon mode activation.
Indicated Airspeed Mode is indicated by a green ‘IAS’ annunciation in the Autopilot
Status Box. The Airspeed Reference is also displayed as a light blue bug corresponding
to the Airspeed Reference along the airspeed tape.
Engine power must be adjusted to allow the autopilot to fly the aircraft at a pitch
attitude corresponding to the desired flight profile (climb or descent) while maintaining
the Airspeed Reference.
3.3.3.4.1 ChanGinG the airSpeed referenCe
The Airspeed Reference (shown in both the Autopilot Status Box and above the
Airspeed Indicator) may be adjusted by using the
NOSE UP/DN
Wheel.
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Figure 3-13 Indicated Airspeed Reference on PFD Page
Indicated
Airspeed
Reference Bug
Indicated
Airspeed
Reference
3.3.3.5 VERTICAL NAVIGATION MODE (VNAV)
Vertical Navigator Mode (VNAV) is not available for the certified instrument.
3.3.3.6 GLIDEPATH MODE (GP) (WITH EXTERNAL WAAS
ENABLED IFR NAVIGATOR ONLY)
Glidepath Mode is used to track a WAAS or other satellite-based augmentation
system WAAS generated glidepath. When Glidepath Mode is armed, ‘GP’ is
annunciated in white in the Autopilot Status Box.
Selecting glidepath mode:
1)
EXTERNAL NAVIGATOR: Ensure a GPS approach with vertical guidance
(LPV, LNAV/VNAV, LNAV +V) is loaded into the active flight plan. The active
waypoint must be part of the flight plan (cannot be a direct-to a waypoint
not in the flight plan).
2)
Ensure that GPS is the selected navigation source.
3)
Press the APR Key on the GMC.
NOTE: Some RNAV (GPS) approaches provide a vertical descent angle as an
aid in flying a stabilized approach. These approaches are NOT considered
Approaches with Vertical Guidance (APV). Approaches that are annunciated
on the HSI as LNAV or LNAV+V are considered Non-precision Approaches
(NPA) and are flown to an MDA even though vertical glidepath (GP) informa-
tion may be provided.
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WARNING: When flying an LNAV approach (with vertical descent angle)
with the autopilot coupled, the aircraft will not level off at the MDA even if
the MDA is set in the altitude preselect.
Upon reaching the glidepath, the flight director transitions to Glidepath Mode and
begins to capture and track the glidepath.
Once the following conditions have been met, the glidepath can be captured:
•Theactivewaypointisatorafterthenalapproachx(FAF).
•Verticaldeviationisvalid.
•TheCDIisatlessthanfull-scaledeviation.
•Automaticsequencingofwaypointshasnotbeensuspended.
Figure 3-14 Glidepath Mode
Glidepath
Mode Active
3.3.3.7 GLIDESLOPE MODE (GS)
Glideslope Mode is available for LOC/ILS approaches to capture and track the
glideslope. When Glideslope Mode is armed (annunciated as ‘GS’ in white), LOC
Approach Mode is armed as the lateral flight director mode.
NOTE: Glideslope Mode requires a valid GPS position.
Selecting Glideslope Mode:
1)
EXTERNAL NAVIGATOR: Tune and activate the desired localizer frequency.
2)
EXTERNAL NAVIGATOR: Ensure that LOC is the selected navigation source.
3)
Press the APR Key on the GMC.
Or
:
1)
EXTERNAL NAVIGATOR: Tune and activate the desired localizer frequency.
2)
EXTERNAL NAVIGATOR: Load the approach (LOC, ILS, LDA, SDF, etc) into
the flight plan.
3)
Press the APR Key on the GMC.
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Once LOC is the navigation source, the localizer and glideslope can be captured.
Upon reaching the glideslope, the flight director transitions to Glideslope Mode and
begins to capture and track the glideslope.
Figure 3-15 Glideslope Mode
Glideslope
Mode Active
3.3.3.8 GO AROUND (GA) AND TAKEOFF (TO) MODES
Go Around and Takeoff modes are coupled pitch and roll modes and are annunciated
as both the vertical and lateral modes when active. In these modes, the flight director
commands a constant set pitch attitude and keeps the wings level. The GA Switch
is used to activate both modes. The mode entered by the flight director depends on
whether the aircraft is on the ground or in the air.
Takeoff Mode provides an attitude reference during rotation and takeoff. This mode
can be selected only while on the ground by pushing the Go Around Button. The flight
director Command Bars assume a wings-level, pitch-up attitude.
Pressing the Go Around Button while in the air activates the flight director in a
wings-level, pitch-up attitude, allowing the execution of a missed approach or a go
around. Go Around Mode arms Selected Altitude Capture Mode automatically when
the altitude preselect bug is set at least 100 ft above the current altitude, and attempts
to modify the aircraft attitude (i.e., with the
NOSE UP/DN
Wheel) will result in reversion
to Pitch and Roll Hold modes.
3.3.4 LATERAL MODES
The following table lists the lateral modes and respective control(s) and annunciation.
Refer to the vertical modes section for information regarding Takeoff and Go Around
Modes.
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Table 3-6 Flight Director Lateral Modes
Lateral Mode Description Control Annunciation
Roll Hold
Holds the current aircraft roll
attitude or rolls the wings level,
depending on the commanded
bank angle
(default) ROL
Heading
Captures and tracks the
Selected Heading
HDG Key HDG
Track
Captures and tracks the
Selected Ground Track
TRK Key TRK
Navigation, GPS
Captures and tracks the
selected navigation source (GPS,
VOR, LOC)
NAV Key
GPS
Navigation, VOR
Enroute Capture/
Track
VOR
Navigation, LOC
Capture/Track (No
Glideslope)
LOC
Approach, GPS
Captures and tracks the
selected navigation source (GPS,
VOR, LOC, BC)
NAV Key
GPS
Approach, VOR
Capture/Track
Approach, LOC
Capture/Track
(Glideslope Mode
automatically armed)
LOC
Approach, BC
Capture/Track
BC
Takeoff
Commands a constant pitch
angle and wings level on-
ground in preparation for
takeoff
Go
Around
Button
TO
Go Around
Commands a constant pitch
angle and wings level in the air
GA
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3.3.4.1 ROLL HOLD MODE (ROL)
NOTE: If Roll Hold Mode is activated as a result of a mode reversion, the
flight director rolls the wings level.
When the flight director is activated or switched, Roll Hold Mode is selected by
default. This mode is annunciated as ‘ROL’ in the Autopilot Status Box. The current
aircraft bank angle is held, subject to the bank angle condition.
Figure 3-16 Roll Hold Mode Annunciation
Table 3-7 Roll Hold Mode Responses
Bank Angle Flight Director Response
< 6° Rolls wings level
6 to 20° Maintains current aircraft roll attitude
> 20° Limits bank to 20°
3.3.4.2 HEADING SELECT MODE (HDG)
NOTE: A magnetometer is required for Heading Select Mode (HDG).
Heading Select Mode is activated by pressing the
HDG Key
. Heading Select Mode
acquires and maintains the Selected Heading. The Selected Heading is shown by a
light blue bug on the HSI and in the box on the bottom right of the HSI.
Changing the selected heading:
1)
Press the Knob to display the Menu.
2)
Select Heading and use the Knob to change the Selected Heading.
Or
Rotate the HDG/TRK Knob.
Activating heading mode:
Press the HDG Key on the GMC.
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Turns are commanded in the same direction as Selected Heading Bug movement,
even if the bug is turned more than 180˚ from the present heading (e.g., a 270˚ turn
to the right). However, Selected Heading changes of more than 330˚ at a time result
in turn reversals.
Figure 3-17 Heading Mode Annunciation
3.3.4.3 TRACK MODE (TRK)
Track Mode is activated by pressing the
HDG Key or TRK Key on the GMC
. Track
Mode acquires and maintains the Selected Ground Track. The Selected Ground Track is
displayed as a magenta bug on the HSI and in the box on the bottom right of the HSI.
Changing the selected ground track:
1)
Press the Knob to display the Menu.
2)
Select Track and use the Knob to change the Selected Ground Track.
Or
Rotate the HDG/TRK Knob.
Activating track mode:
Press the TRK Key on the GMC.
Turns are commanded in the same direction as Selected Ground Track Bug movement,
even if the bug is turned more than 180˚ from the present heading (e.g., a 270˚ turn
to the right). However, Selected Ground Track changes of more than 330˚ at a time
result in turn reversals.
Figure 3-18 Track Mode Annunciation
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Figure 3-19 Track Mode Annunciation
3.3.4.4 NAVIGATION MODE (GPS, VOR, LOC)
NOTE: The G5 must have a valid GPS position for VOR and LOC Modes.
NOTE: When intercepting a flight plan leg, the flight director gives com-
mands to capture the active leg at approximately a 45° angle to the track
between the waypoints defining the active leg. The flight director does not
give commands fly to the starting waypoint of the active leg.
Pressing the NAV Key selects Navigation Mode. Navigation Mode acquires and
tracks the navigation source. The flight director follows GPS roll steering commands
when GPS is the navigation source. Navigation Mode can also be used to fly non-
precision GPS, VOR, and LOC approaches where vertical guidance is not required.
If the Course Deviation Indicator (CDI) shows greater than one dot when the NAV
Key is pressed, the selected mode is armed. If the CDI is less than one dot, Navigation
Mode is automatically captured when the NAV Key is pressed. The armed annunciation
appears in white to the left of the active roll mode.
Figure 3-20 Navigation Mode Annunciation
If Navigation Mode is active and either of the following occur, the AFCS reverts to
Roll Hold Mode (wings rolled level):
• Active navigation source manually switched
•Navigation input is lost
•GPS reception is lost
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3.3.4.5 APPROACHES WITHOUT VERTICAL GUIDANCE
NOTE: The selected navigation receiver must have an active GPS course for
the flight director to enter Approach Mode.
Press the NAV Key to arm/activate GPS (LNAV only) lateral mode. The lateral
mode acquires and tracks the selected navigation source, depending on the loaded
approach. Press
NAV
when the CDI is greater than one dot to arm the selected mode
(annunciated in white). Press
NAV
when the CDI deviation is less than one dot to
activate, capture and track the selected navigation source.
Table 3-8 Approach without Vertical Guidance
Example Control Lateral Mode Annunciation Description
LNAV
NAV Key
Approach, GPS GPS
Captures and tracks
the selected navigation
source (GPS, VOR, LOC,
BC)
VOR
VOR Approach
Capture/Track
VOR
LOC
LOC Approach
Capture/Track
LOC
BC
BC Approach
Capture/Track
BC
3.3.4.5.1 GpS approaCh without vertiCaL GuidanCe
A GPS approach without vertical guidance (LNAV) is flown using GPS NAV Mode.
Selecting a GPS Approach without vertical guidance:
1)
EXTERNAL NAVIGATOR: Ensure a GPS approach without vertical guidance
(LNAV) is loaded into the active flight plan.
2)
EXTERNAL NAVIGATOR: Ensure the ‘GPS’ indication is showing in the
lower-left corner
. If not, press the CDI Key on the navigator.
3)
EXTERNAL NAVIGATOR: Select and activate the GPS approach using the
PROC Key.
4)
Press the NAV Key.
5)
Adjust the aircraft’s pitch axis as required.
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3.3.4.5.2 vor approaCh
A VOR approach is flown using VOR Mode.
Selecting a VOR Approach:
1)
EXTERNAL NAVIGATOR: Tune and activate the desired VOR frequency.
2)
EXTERNAL NAVIGATOR: Ensure the ‘VLOC’ indication is showing in the
lower-left corner
. If not, press the CDI Key on the navigator.
3)
Ensure that VOR1 or VOR2 is the selected navigation source on the HSI
Page. It should say ‘VOR1’ or ‘VOR2’ on the HSI and the needle should be
green.
4)
From the HSI Page, press the Knob to display the Menu.
5)
Set the inbound approach course. Select Course and use the Knob to
adjust the course.
6)
Press or the NAV Key on the GMC.
If there is less than half-scale deviation when the NAV Key is pressed, VOR
Mode will activate (green text), intercept, and track the selected radial. If
there is more than half-scale deviation when the NAV Key is pressed, VOR
Mode will arm (white text) first, then activate when closer to the radial.
7)
Adjust the aircraft’s pitch axis as required.
3.3.4.5.3 LoCaLizer approaCh (no GS)
LOC Mode is used to fly a localizer only approach (no glideslope).
Selecting LOC Mode for a localizer only approach:
1)
EXTERNAL NAVIGATOR: Tune and activate the desired LOC frequency,
2)
Ensure the ‘LOC1’ indication is showing in the lower-left corner
. If not,
press the CDI Key on the navigator.
The HSI should automatically slew the
needle to the correct course.
3)
Press or the NAV Key on the GMC.
If the localizer deviation is less than half-scale when the NAV Key is
pressed, the autopilot will activate LOC Mode and track the localizer,
otherwise LOC Mode is armed and the pilot is responsible for intercepting
the localizer. In some cases it may be necessary to use HDG Mode with
LOC Mode armed to follow a vector to the localizer.
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3.3.4.6 GPS APPROACHES WITH LATERAL + VERTICAL
GUIDANCE
Press the APR Key to arm/activate both lateral and vertical modes for approach.
When Glidepath (GP) Mode is armed for a GPS approach with vertical guidance, GPS
Mode is automatically armed. Press the APR Key when the CDI is greater than one
dot to arm the selected modes (annunciated in white). Press the APR Key when the
CDI deviation is less than one dot to activate, capture and track the selected navigation
source.
Table 3-9 Lateral + Vertical Approaches
Example Control Modes Annunciation Description
LPV,
LNAV/
VNAV,
LNAV+V
APR Key
Lateral:
GPS
GPS
Captures and tracks the
lateral portion of a GPS
approach
Vertical:
Glidepath
GP
Captures and tracks a
WAAS approach glidepath
LOC, ILS APR Key
Lateral:
Localizer
LOC
Captures and track the
localizer
Vertical:
Glideslope
GS
Captures and tracks the
glideslope
3.3.4.7 GPS APPROACH WITH VERTICAL GUIDANCE
NOTE: To cancel Glidepath (GP) Mode without cancelling GPS Mode, NAV
once. Pressing it a second time cancels GPS Mode.
When Glidepath (GP) Mode is armed for a GPS approach with vertical guidance, GPS
Mode is automatically armed.
Selecting a GPS approach with vertical guidance:
1)
EXTERNAL NAVIGATOR: Ensure a GPS approach with vertical guidance
(LPV, LNAV/VNAV, LNAV+V) is loaded into the active flight plan.
2)
EXTERNAL NAVIGATOR: Ensure the ‘GPS’ indication is showing in the
lower-left corner
. If not, press the CDI Key.
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3)
EXTERNAL NAVIGATOR: Select and activate the GPS approach using the
PROC Key.
4)
Press the
APR Key.
3.3.4.8 LOCALIZER WITH GLIDESLOPE
LOC Mode (lateral) and GS Mode (vertical) are both armed by pressing the APR
Key on the GMC. LOC/ILS approach captures are inhibited if the difference between
aircraft heading and localizer course exceeds 105
˚
.
NOTE: To cancel Glideslope (GS) Mode without cancelling LOC Mode, press
NAV once. Pressing it a second time cancels LOC Mode.
Selecting LOC Mode with GS Mode:
1)
EXTERNAL NAVIGATOR: Tune and activate the desired LOC frequency.
2)
EXTERNAL NAVIGATOR: Ensure the ‘LOC1’ indication is showing in the
lower-left corner
. If not, press the CDI Key.
The HSI should automatically
slew the needle to the correct course.
3)
Press the
APR Key on the GMC
.
This simultaneously selects LOC Mode and GS (Glideslope) Mode. If the localizer
deviation is less than half-scale when the APR Key is pressed, the autopilot will activate
LOC Mode and track the localizer, otherwise LOC Mode is armed and the pilot is
responsible for intercepting the localizer.
If the following occurs, the autopilot reverts to Roll Hold Mode (wings rolled level):
•
Approach Mode is active and the Navigation source is manually
switched
•
The localizer signal is lost
If the Glideslope signal is lost , GS Mode will revert to Pitch Hold Mode and hold the
last pitch attitude.
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3.3.4.9 BACKCOURSE APPROACH
NOTE: When making a backcourse approach, set the Selected Course to the
localizer front course.
Backcourse Mode captures and tracks a localizer signal in the backcourse direction.
Backcourse is indicated by ‘BC’ in the autopilot status box.
If GS and LOC Mode are armed, the autopilot can only capture the localizer front
course, indicated by ‘LOC’ in the autopilot status box. If only LOC Mode is armed (not
GS Mode), the autopilot will capture either the front course or the backcourse based
on the angle at which the aircraft intercepts the localizer.
Selecting BC Mode:
1)
EXTERNAL NAVIGATOR: Tune and activate the desired LOC frequency.
2)
EXTERNAL NAVIGATOR: Ensure the ‘LOC1’ indication is showing in the
lower-left corner
. If not, press the CDI Key.
3)
EXTERNAL NAVIGATOR: Select the front course on the CDI.
4)
Press the NAV Key on the GMC.
If the aircraft heading is within 75˚ of the localizer backcourse then BC
Mode will be armed. If the aircraft heading is within 105˚ of the localizer
front course, LOC Mode will be armed.
3.3.4.10 LEVEL MODE
Level Mode is coupled in pitch and roll modes and is annunciated as both the vertical
and lateral modes when active. Pressing the LVL Key engages the autopilot in Level
vertical and lateral modes. Level Mode does not track altitude or heading. When the
LVL Key is pressed all armed and active modes are cancelled and the autopilot and
flight director revert to LVL mode for pitch and roll. While in level mode, all other
modes are available by pressing the corresponding button.
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3.4 GFC 500 AFCS ALERTS
3.4.1 TRIM ALERTS
If the commanded operation cannot be achieved due to the limitations configured,
the following messages can be displayed over the pitch ladder. The annunciation is
removed once the condition is resolved.
Figure 3-21 TRIM UP Alert Figure 3-22 TRIM DOWN Alert
Alert Condition Annunciation Description
Up-elevator Trim Required TRIM UP
The autopilot does not have the
required elevator authority to
reach the desired flight condition.
Down-elevator Trim Required TRIM DOWN
Table 3-10 Status Alerts
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3.4.2 SPEED ALERTS
If the remote autopilot unit supports speed alerts and the airspeed limitations
configured have been reached, the following messages can be displayed the airspeed
tape. The annunciation is removed once the condition is resolved.
Figure 3-23 MAXSPD Alert
Figure 3-24 MINSPD Alert
Alert Condition Annunciation Description
High speed
Protection
MAXSPD
Autopilot unit will raise the nose to limit the
aircraft’s speed.
Low speed
Protection
MINSPD
Autopilot unit will lower the nose to prevent
the aircraft’s speed from decreasing.
Table 3-11 Speed Alerts
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3.5 ELECTRONIC STABILITY & PROTECTION (ESP)
(GFC 500)
WARNING: Do not assume ESP will provide stability protection in all circum-
stances. There are in-flight situations that can exceed the capabilities of ESP
technology.
WARNING: A GPS navigator that can provide AGL height data is required
for low-airspeed protection.
WARNING: The autopilot (or ESP) will disengage if the roll attitude exceeds
75° or the pitch attitude exceeds 50°.
Electronic Stability and Protection (ESP) is a feature that is intended to monitor the
aircraft and provide control input feedback when necessary to discourage operating
the aircraft at potentially unsafe attitudes and/or airspeeds. If enabled, this feature
will automatically arm when the aircraft is above 500 feet AGL and the autopilot is
not engaged, and disarm when below 200 feet AGL (if AGL height data is unavailable,
ESP can be armed on the ground, but low-airspeed protection will not be available).
When selected, ESP engages automatically when the aircraft approaches or exceeds
one or more predetermined airspeed or attitude limitations. Stability protection
for each flight axis is provided by the autopilot servos, which apply force to the
appropriate control surface(s) to discourage pilot control inputs that would cause the
aircraft to exceed the normal or "protected" flight envelope. This is perceived by the
pilot as resistance to control movement in the undesired direction when the aircraft
approaches a steep attitude, and/or the airspeed is below the minimum or above the
maximum configured airspeed.
As the aircraft deviates further from the normal attitude and/or airspeed, the
force increases proportionally (up to an established maximum) to encourage control
movement in the direction necessary to return to the normal attitude and/or airspeed
range.
When ESP has been engaged for more than 10 seconds (cumulative; not necessarily
consecutive seconds) of a 20-second interval, the autopilot can be configured to
engage with the flight director in Level Mode, bringing the aircraft into level flight. An
aural “Engaging Autopilot” alert is played and the flight director mode annunciation
will indicate ‘LVL’ for vertical and lateral modes.
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Level mode as activated by ESP is limited by altitude. ESP will not be able to activate
Level mode until the aircraft climbs above 2000 feet AGL. ESP will be locked out of
automatically activating Level mode after the aircraft descends below 1500 feet AGL
as well. Also note that Level mode as activated by ESP is different than manually
selected Level mode. Manually selected Level mode is not limited by altitude at all.
NOTE: If AGL height data is unavailable automatic engagement of Level mode
is not supported.
ESP is enabled or disabled from the PFD Page Menu.
Enabling/Disabling ESP using the G5 Menu:
1)
From the PFD Page, press the Knob to display the Menu.
2)
Turn the Knob to highlight ESP.
3)
Press the Knob to enable or disable ESP.
Figure 3-25 AFCS (ESP Enabled)
ESP Roll Engage-
ment Indication
(ESP NOT Engaged)
Select To
Enable/
Disable ESP
PDF Page
Menu
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3.5.1 ROLL ENGAGEMENT
Roll Limit Indicators displayed on the roll scale are configurable between 45º and
60º right and left, indicating where ESP will engage. As roll attitude exceeds the
configured limit, ESP will engage and the Roll Limit Indicators will move to 15º less
than the configured ESP bank limit. The Roll Limit Indicator now indicates where ESP
will disengage as roll attitude decreases.
Figure 3-26 ESP Roll Engagement Indication
(ESP Enabled but NOT Engaged)
Roll Limit Indicator
ESP Engage (45º)
(Configurable)
ESP Engage (45º)(Configurable)
Aircraft Roll Attitude = 35º
Figure 3-27 Roll Increasing to ESP Engagement
ESP Disengage (30º)
(15º < Configured Bank Limit)
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Once engaged, the torque applied by ESP is at its maximum when bank angle is
15º more than the configured bank limit, and tapers to the minimum applied torque
when the bank angle is 15º less than the configured bank limit. The force increases
as roll attitude increases and decreases as roll attitude decreases. The applied force is
intended to encourage pilot input to return the airplane to a more normal roll attitude.
When beyond 15º of the configured bank limit, the maximum torque is held until the
aircraft returns inside the protected envelope.
Figure 3-28 ESP Roll Operating Range When Engaged
(Force Increases as Roll Increases & Decreases as Roll Decreases)
0º
10º
10º
20º
20º
30º
30º
45º
45º
60º
60º
75º
75º
90º
90º
Configured
Bank Limit
(45
º)
Minimum
ESP Torque
(30
º)
Maximum
ESP Torque
(60
º)
Maximum
ESP Torque
(60
º)
Minimum
ESP Torque
(30
º)
Configured
Bank Limit
(45
º)
3.5.2 PITCH ENGAGEMENT
ESP pitch engagement is configurable between 10º and 25º nose-up and between
5º and 25º nose-down. Once engaged, the torque applied by ESP is at its maximum
when pitch is 5º more than the configured nose-up and nose-down pitch limits, and
tapers to the minimum applied torque when pitch is 5º less than the configured nose-
up and nose-down pitch limits. When beyond 5º of the configured pitch limit, the
maximum torque is held until the aircraft returns inside the protected envelope.
The opposing force increases or decreases depending on the pitch angle and the
direction of pitch travel. This force is intended to encourage movement in the pitch axis
in the direction of the normal pitch attitude range for the aircraft.
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Figure 3-29 ESP Pitch Operating Range When Engaged
(Force Increases as Pitch Increases & Decreases as Pitch Decreases)
30˚
25˚
20˚
15˚
10˚
5˚
0˚
5˚
10˚
15˚
20˚
25˚
30˚
30˚
25˚
20˚
15˚
10˚
5˚
0˚
5˚
10˚
15˚
20˚
25˚
30˚
35˚
40˚
45˚
50˚
35˚
40˚
45˚
50˚
50˚
45˚
40˚
35˚
50˚
45˚
40˚
35˚
ESPESP
3.5.3 AIRSPEED PROTECTION (GFC 500 ONLY)
NOTE: If AGL height data is unavailable low-airspeed protection is not sup-
ported.
An airspeed below the minimum configured airspeed or above maximum configured
airspeed will result in ESP applying force to raise or lower the nose of the aircraft.
When the high or low airspeed condition is remedied, ESP force is no longer applied.
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SECTION 4 ADDITIONAL FEATURES
4.1 GPS STEERING (GPSS)
NOTE: This section is only applicable to non-Garmin autopilots.
When installed with the appropriate interfaces, the G5 can interface to some third-
party autopilot systems.
4.1.1 GAD 29B (OPTIONAL)
The GAD 29B (optional) is an adapter that converts digital heading and course
data into analog signals used by analog autopilot systems. The GAD 29B is installed
remotely between the G5 and an existing autopilot. The analog signals from the GAD
29B mimic those of spinning-mass heading gyros that provide data to the autopilot
and allow the gyro to be replaced by the G5 and GAD 29B combination. The GAD 29B
is also used to interface certain Garmin IFR navigators with the G5.
The GAD 29B sends analog information about the G5’s heading bug to a third-party
analog autopilot, allowing it to operate in HDG mode and follow the G5 heading bug.
The navigation course selected on the G5 is also sent to the analog autopilot, enabling
proper operation of the autopilot’s NAV mode.
NOTE: If multiple navigators are configured, course data is sent by the GAD
29B for navigator #1 only.
Figure 4-1 GAD 29B (Optional)
GPS Steering (GPSS) provides roll command signals calculated by the GPS navigator
to the autopilot in order to allow the aircraft to anticipate turns, make smooth
transitions when passing waypoints, and fly leg types such as procedure turns and
holding patterns.
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Some autopilots have built-in support for GPS Steering (GPSS) commands from
a GPS navigator. These autopilots receive digital GPSS commands directly from the
navigator. Refer to the Airplane Flight Manual and autopilot system documentation for
instructions on how to use the autopilot's GPSS function.
For older autopilots that do not have built-in support for digital GPSS signals, GPSS
functionality may be emulated using the analog heading bug output of the G5 and
GAD 29B, by operating the autopilot in HDG mode and selecting GPSS from the G5
menu.
NOTE: If multiple navigators are configured, GPSS emulation is supported
for navigator #1 only.
NOTE: GPSS commands are not sent to the autopilot when a VLOC source
is displayed on the HSI.
Wpt 1
Wpt 2
Wpt 3
Aircraft
Present
Position
Flight Plan Leg 1
Flight Plan Leg 2
Turn Anticipation
Curve
Figure 4-2 GPSS Turn Anticipation
Enabling/Disabling GPSS Mode:
1)
Press the Knob to display the Menu.
2)
Turn the Knob to select GPSS.
3)
Press the Knob to enable/disable GPSS Mode.
When GPSS is selected on the G5, the heading bug will change to a hollow outline,
and a crossed-out heading bug symbol appears on the G5 indicating that the autopilot
is not coupled to the heading bug. The heading bug is still controllable and may still
be used for reference.
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When the G5 and GAD 29B are providing analog GPSS emulation, GPSS turn
commands from the navigator 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 navigator. If the GPSS data is invalid (for example, if there is
not active GPS leg) or the selected HSI source on the G5 is not GPS, the annunciated
"GPSS" text will turn amber and a zero turn command will be sent to the autopilot.
Figure 4-3 GPSS Enabled (PFD Page)
GPSS Enabled
GPSS Menu
Option
GPSS Menu
Option
GPSS Enabled
Figure 4-4 GPSS Enabled (HSI Page)
Hollow Heading Bug
Hollow Heading Bug
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Index
Index-1
System Overview Flight Instruments AFCS Additional Features Index
A
AFCS Operation 39
Airspeed Indicator 14
Altimeter 17–19
Altitude Alerting 19
Altitude Hold Mode (ALT) 49
Approach Mode 59
Attitude and Heading Reference System
(AHRS) 6, 7
Attitude Indicator 15
Autopilot 39
Autopilot Disconnect 41
B
Barometric setting, Altimeter 13,
16–17, 18–19
Bearing Pointers 25
C
Command Bars 45
D
Display
Overview 3
E
Electronic Stability & Protection 39
F
Flight Director 39
Flight Level Change Mode 51
G
GFC 500 36
Glidepath Mode (GP) 52
GMC 507 37
GSA 28 37
H
Heading 13
Heading Select Mode 56, 57
Heading Strip 20
Horizontal Situation Indicator (HSI) 27
I
Integrated Autopilot
Disengaging 42
Engaging 41
M
Manual Electric Trim 39
MENU Key 4
Menus 9, 10, 11
Messages
Miscellaneous 10, 11, 38, 64
N
Navigation Mode 58–59
NRST Key 4
P
Pitch Hold Mode 47
Power-up 5
R
Roll Hold Mode 56
S
Secure Digital (SD) Cards 4
Installing 4
SECTION 5 INDEX
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Index-2
System OverviewFlight InstrumentsAFCSAdditional FeaturesIndex
Selected Altitude 47, 48, 50
Selected Altitude Capture Mode 47, 48,
50, 54
Selected Heading 27, 56, 57
System
Annunciations 5
Functionality 9
Initialization 5
Power-up 5
T
Takeoff Mode 54
Transponder
Status Box 13
True Airspeed (TAS) 13
V
Vertical Deviation Indicator (VDI) 29
Vertical Speed Indicator (VSI) 22, 28
Vertical Speed Mode 50
Y
Yaw Damper 39
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Contact Garmin Product Support at
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