Garmin | G500 TXi | Garmin G500 TXi G500(H)/G600/G700 TXi SW v3.00/v3.01 Upgrade Supplement

Garmin G500 TXi G500(H)/G600/G700 TXi SW v3.00/v3.01 Upgrade Supplement
G500(H)/G600/G700 TXI SOFTWARE v3.00/3.01
PILOT’S GUIDE UPGRADE SUPPLEMENT
This supplement contains the pages revised in the G500(H)/G600/G700 TXi Pilot’s Guide,
P/N 190-01717-10, Rev. G and Rev. H, regarding the new features of software v3.00
and 3.01. Change bars are placed adjacent to the revised information corresponding to
the revision summary table.
Current documents are available at flyGarmin.com.
Printed copies may be purchased by contacting Garmin Customer Support.
Feature Descriptions
Features and screen images are dependent upon the installed software version and its
configuration. For more information regarding feature availability, refer to the pilot’s
guide.
G500(H)/G600/G700 TXi Pilot’s Guide Upgrade Supplement
190-01717-20 Rev. A
© 2019
Garmin International, Inc. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated,
downloaded or stored in any storage medium, for any purpose without the express written permission of Garmin.
Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a
hard drive or other electronic storage medium to be viewed for personal use, provided that such electronic or printed
copy of this manual or revision must contain the complete text of this copyright notice and provided further that any
unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.
SkyWatch® and Stormscope® are registered trademarks of L-3 Communications.
© 2019 SiriusXM® Satellite Radio, Sirius, SXM and all related marks and logos are trademarks of SiriusXM Radio
Inc. All other marks and logos are property of their respective owners. All rights reserved.
Garmin®, FliteCharts®, and SafeTaxi® are registered trademarks of Garmin International or its subsidiaries.
Connext™, Garmin Pilot™, G5™, GDU™, GTN™, and Smart Airspace™ are trademarks of Garmin International
or its subsidiaries. These trademarks may not be used without the express permission of Garmin.
The Bluetooth® word mark and logos are registered trademarks owned by Bluetooth SIG, Inc. and any use of such
marks by Garmin is under license. Other trademarks and trade names are those of their respective owners.
© 2019 SD® is a registered trademark of SD-3C, LLC. All rights reserved.
Iridium® is a registered trademark of Iridium Communications, Inc. All rights reserved.
The term Wi-Fi® is a registered trademark of the Wi-Fi Alliance®. For information regarding the Aviation Limited
Warranty, refer to Garmin’s website.
For aviation product support, visit flyGarmin.com.
G500(H)/G600/G700 TXi Pilot’s Guide Upgrade Supplement
190-01717-20 Rev. A
G500(H)/G600/G700 TXi Pilot’s Guide Revision G and H, Change Summary
Section
Page
1
1-2
1.3
1-7
1.5
1.6.1
1.25
1.27.4
1.27.5
1.27.7
1.29
1-9
1-11
1-36
1-47
1-48
1-50
1-58
1.31
1-67
1.31.4
1.31.10
1.31.15
1-70
1-78
1-81
Description
Section 1 – System Description
Updated unit descriptions for GDU 700P and GDU 700L.
Added torque and turbine temperature system functions.
Added table note 5.
Added table note 4.
Added MFD Resize key to“Common Commands” topic.
Added table note 1.
Added “Emergency Descent Mode Advisories“ section.
Added table note 1.
Added TCAS advisory.
Added “Logs“ section.
Added GEA 71 system optional LRUs.
Added TCAS II interface.
Added lighting control information to list of GCU 485 features.
Added turbine engine support.
Added TCAS II function.
Section 2 – Primary Flight Display
2.1
2.3
2-3
2-3
2-4
2-4
2-5
2-11
2.6
2-18
2.6.1
2-19
2.7
2-22
2
Added “Auto EDM” to list of PFD Setup menu options.
Added Logs to GDU 700() PFD system selections.
Added Auto EDM to GDU 1060 PFD selections.
Added table note 4.
“Changed “CDI” selection to “CDI SRC.”
Updated information in “Standard Rate Turn Indicators” topic.
Added EDM information to “Airspeed Controls & Indications“
table.
Added airspeed exeedance information for fixed wing reference
markings.
Added EDM information to Selected Altitude list of functions.
G500(H)/G600/G700 TXi Pilot’s Guide Upgrade Supplement
190-01717-20 Rev. A
Section
2.8
Page
2-28
2-29
2-29
2-30
Description
Updated indicator format information.
Added “TCAS RAS” topic to “VSI“ section.
Updated numeric speed indicator description for arc VSI.
Updated fixed scale range options in “Vertical Speed Range“
topic.
Section 3 – Advanced Features
3.6.1
3.8
3.9
3-23
3-25
3-25
Added “AP Engaged Indication” topic.
Added “Low Bank Mode” section.
Added “Servo Heading Reference” section.
Section 4 – Multi-Function Display
4
4-3
4-4
4.2
4-5
Added “Aircraft Log” and “Exceedances” to “MFD System
Selections“ section.
Added “MFD Resize Option” section.
Added TCAS II feature requirement for Map page. and EIS/MFD
information in “Feature Limitations.”
Added EIS/MFD feature limitations for Map page.
Section 5 – Weather Awareness
5.24
5-30
5.24.1
5-30
Added list of FIS-B weather products.
Updated FIS-B data transmission limitations information for
clarity.
Section 6 – Traffic Awareness
6.5
6-11
Added “TCAS II“ section.
Section 7 – Terrain Awareness
7.9.1
7-28
Added “TAWS-A“ section.
Section 8 – Fuel & Engine Indicating System
8
8-22
8-43
Added “Turbine Engines” section.
Added “Electrical Gauges“ section.
Section 9 – Abnormal Operations
9.1
9.1.2
9.3.1
9.5
9-2
9-8
9-17
9-25
Added “TCAS II RAs“ topic.
Added “Turboprop Gauge Areas“ topic.
Updated AHRS/ADC sensor selection annunciations.
Added “Emergency Descent Mode“ section.
G500(H)/G600/G700 TXi Pilot’s Guide Upgrade Supplement
190-01717-20 Rev. A
System Description
System Overview
The G500(H)/G600/G700 TXi is a display and sensor system available in three display
options.
• GDU 1060 – 10”display
• GDU 700P – 7”portrait display
• GDU 700L – 7”landscape display
Depending on system specifics one or more of the following functions may apply:
• Primary Flight Display (PFD) – provides attitude, heading, air data, and
navigation information to the pilot
• Multi-Function Display (MFD) – provides pilot awareness of factors that may
affect the overall conduct of a flight
• Engine Indicating System (EIS) – provides engine and airframe operating
parameters to the pilot
GDU 1060 PFD/MFD, EIS OPTION
The GDU 1060 is a PFD/MFD display, with an optional EIS function. Each function is
designated to a portion of the display. The MFD can be selectively hidden or shown.
When hidden, the PFD expands into the MFD space. If installed, the EIS function
always shows and occupies either the left or right edge of the display.
GDU 700P PFD, MFD, EIS, MFD/EIS
The GDU 700P provides a single PFD, MFD, EIS, or, in single-engine piston EIS, a
combined MFD/EIS function. In some installations, it provides backup PFD or EIS
information in the event that the primary PFD or EIS display fails or malfunctions.
When configured as an MFD/EIS display, engine instruments are dedicated to 40% of
the screen. The remaining screen portion displays all configured MFD options using a
pilot-selectable menu.
GDU 700L PFD, EIS, OR MFD/EIS
The GDU 700L provides a single PFD, piston EIS, or in single-engine piston EIS,
MFD/EIS combined function. When configured as an MFD/EIS display, engine
instruments are dedicated to 40% of the screen. The remaining screen portion
displays all configured MFD options using a pilot-selectable menu.
1-2
Pilot’s Guide
190-01717-10 Rev. H
System Description
1.3
System Functions
PFD
MFD
EIS [2]
GDU 700( )/1060
GDU 700P/1060 [3]
GDU 700( )/1060 [3]
• Attitude
• Navigation Map
• Fuel Qty (Main, Aux)
• Airspeed
• Traffic [1]
• RPM/Tach
• Altitude
• Terrain
• Propeller Sync Display
• Vertical Speed
• Charts
• Manifold Pressure
• Turn Coordinator
• Flight Plan
• Oil Pressure
• HSI
• Weather [1]
• Oil Temperature
• HSI Map [4]
• Waypoint
Information
• Fuel Flow
• Lateral and Vertical
Deviation Indicators
• Music Services [1]
• Fuel Calculations
• Terrain Avoidance [1]
• Datalink Weather
Display [1]
• Engine Data [1]
• System Advisories
• Cylinder Operating
Temperatures
(CHT, EGT)
• Radar Altimeter [1]
• Video [1]
• TIT
• Clock
• Autopilot
Annunciations [1]
• Fuel Pressure
• Lean Assist Mode
• Carburetor Air
Temperature
• Flight Director [1]
• Synthetic Vision [1]
• Flight Path Marker
[1]
• Intercooler
Temperatures
(IAT, CDT, Difference)
• System Advisories
• Amps/Volts
• Safety Monitors [1]
• User Selectable Fields
• GPS NAV Status
• User Adjustable
Advisories
• Display Backup [1] [4]
• Torque [5]
• Terrain Avoidance [1]
[1]
[2]
[3]
[4]
[5]
• TurbineTemperature[5]
Function availability dependent upon aircraft interfaces or enablement.
Displayed engine operating parameters dependent upon configuration.
GDU 700( ) MFD/EIS provides the same MFD and EIS functionality listed with the exception of
weather radar and multi-engine.
Not available for GDU 700L.
Turboprop only.
190-01717-10 Rev. H
Pilot’s Guide
1-7
System Description
1.5
SD Card Slot
NOTE
Do not remove or insert an SD card while in flight. Always verify the system
is powered off before inserting or removing an SD card.
Determine which card slot is appropriate for the task.
SD CARD SLOT
TASK
GDU 1060
GDU 700P
GDU 700L
Exporting data logs
Top
Top
Left
Saving system
configurations
Top
Top
Left
Transferring crew profiles
Top
Top
Left
Capturing screen images [1]
Top
Top
Left
Upgrading software [4]
Top
Top
Left
Enabling Flight Stream 510
connectivity [2]
Bottom
Bottom
Right
Updating databases [3]
Top or bottom
Top or bottom
Left or right
[1]
[2]
[3]
[4]
Screen images save to the bottom/right card when the top/left card is unavailable.
Install Flight Stream 510 in a GTN, if available.
While either slot may be used, the bottom/left slot has a faster transfer rate and is
recommended for all database-related tasks.
In software v3.00 and later, an installer unlock card must be present in the bottom/right card
slot to perform a software update.
INSERT AN SD CARD
When inserting an SD card:
1. Verify unit power if off and the slot is empty.
2. Hold card in the proper orientation.
• GDU 1060/700P: label faces left edge of display screen
• GDU 700L: label faces top edge of display screen
3. Ensure back edge of card is flush with display bezel after insertion.
EJECT AN SD CARD
1. Power off the unit.
2. Release the spring latch by pressing lightly on exposed edge of card.
190-01717-10 Rev. H
Pilot’s Guide
1-9
System Description
1.6.1
Keys
COMMON COMMANDS
Displays Advisories page.
Blinking icon indicates
unread system advisories.
Inputs specified value.
Displays context menus.
Scrolls up.
Returns to previous page.
Scrolls down.
Cancels current function
without inputting data.
Indicates corresponding
item is selected
(e.g., database update)
Allows resizing of the
MFD and PFD screens
[1] [2]
[1]
[2]
GDU 1060 MFD/PFD only.
Software version 3.00 and later.
FUNCTION KEYS
Toggle keys turn a specific function on or
off. The current state of the function is
indicated below the key label.
On
190-01717-10 Rev. H
Off
Pilot’s Guide
1-11
System Description
SYSTEM & DISPLAY PROFILE SETTINGS
DISPLAY
FUNCTION
SETTING
• All
Map
• Motion vector
Traffic
• Altitude filter (ABV/BLW/NRM/UNR)
• View
Terrain
• Layers
• Column data fields
Flight Plan
• Map orientation
Datalink weather
products
(SXM, FIS-B, Connext)
MFD
• Layers
• Legend on/off
• FIS-B on/off
• View
Stormscope
• Mode
• Preset group selection
Music
• Music category selection
• EIS Lean Mode (ROP/LOP/TIT)
• Engine advisories (on/off states,
thresholds)
Engine
• Time format (UTC/local)
• Weather knob shortcut
System
• Outside Air Temperature units
• EIS Lean Mode (ROP/LOP/TIT) [1]
EIS
[1]
1-36
• Engine advisories (on/off states,
thresholds)
Engine
Lean mode is not applicable to turboprop installations.
Pilot’s Guide
190-01717-10 Rev. H
System Description
ADVISORY
CONDITION
CORRECTIVE ACTION
Chart streaming
unavailable. Using
installed chart
database.
Chart streaming is not
available. The GDU
reverted to the currently
installed charts.
Open the System Status page
and check database
synchronization status. If the
problem persists, contact a
Garmin dealer for support.
Database SYNC in
progress. View
System Status page
for more info.
Database
synchronization is in
progress.
Wait for database
synchronization to complete.
Restart the GDU before
attempting to use new
databases.
1.27.4
Emergency Descent Mode Advisories
ADVISORY
CONDITION
Emergency Descent
Mode ACTIVATE
switch inoperative.
EDM switch inoperative.
Emergency Descent
Mode automatic
activation
unavailable. Service
required.
EDM cabin pressurization
is enabled on GDU, but
GMC 605 is not
providing cabin pressure
altitude.
Emergency Descent
Mode unavailable.
Service required.
EDM is enabled on GDU,
but not supported by
GMC 605.
Emergency Descent
Mode automatic
activation is
inhibited.
Auto EDM toggle key in
the PFD Setup menu is
off.
190-01717-10 Rev. H
Pilot’s Guide
CORRECTIVE ACTION
Contact a Garmin dealer for
service.
Enable the Auto EDM
function. On PFD:
Tap Menu > Auto EDM.
1-47
System Description
1.27.5
Engine System Advisories
ADVISORY
CONDITION
<High/Low> <gauge
name> advisory
(e.g., High Oil
Temperature, Low
Battery Voltage).
The indicated engine
parameter exceeds
pilot-specified value.
EGT Difference
advisory. [1]
Pilot-specified EGT Diff is
exceeded by one or more
engines.
CHT Cooling
advisory. [1]
A cylinder’s cooling rate
is faster than
pilot-specified CHT
cooling rate.
Low EST Fuel
Remaining advisory.
Estimated fuel on board
is below pilot-specified
limit.
Low Endurance
advisory.
Remaining flight
endurance is below
pilot-specified limit.
[1]
1-48
CORRECTIVE ACTION
Verify that parameter is within
the operating limitations
defined in the POH.
Piston installations only.
Pilot’s Guide
190-01717-10 Rev. H
System Description
1.27.7
Traffic System Advisories
The following advisories pertain to various traffic system failures.
ADVISORY
CONDITION
CORRECTIVE ACTION
1090ES traffic
receiver fault.
ADS-B LRU reports that
it is unable to receive
1090 Extended Squitter
traffic.
Service required. Contact
dealer for support.
ADS traffic alerting
function
inoperative.
The ADS-B LRU reports a
traffic alerting failure.
Service required. Contact
dealer for support.
ADS traffic function
inoperative.
The ADS-B LRU reports a
failure with the ADS-B
Traffic input.
Service required. Contact
dealer for support.
TAS/TCAS function
inoperative.
TAS/TCAS device reports
a traffic failure.
Communication with the
TAS/TCAS device is lost.
Reset the TCAS device.
Contact dealer for support.
The TAS/TCAS device is
in standby mode for
longer than 60 seconds
while airborne.
If traffic alerts are desired,
enable the operating mode
of the traffic device.
The ADS-B LRU reports a
critical fault and is
inoperative.
Service required. Contact
dealer for support.
Communication with the
ADS-B LRU is lost.
Service required. Contact
dealer for support.
UAT fault.
The UAT LRU reports a
low battery or fan fault.
Service required. Contact
dealer for support.
UAT traffic/data
receiver fault.
The ADS-B LRU reports
that it is unable to
receive UAT traffic and
FIS-B data.
Service required. Contact
dealer for service.
TCAS RA display
unavailable on VSI.
Expand <GDU> to
full screen mode to
restore. [1]
The GDU is operating in
display backup mode,
and the current VSI
format is not able to
display RAs.
Change the VSI type by
expanding the PFD using the
FULL key.
TAS/TCAS system in
standby.
Traffic/FIS-B
functions
inoperative.
[1]
1-50
TCAS II equipped aircraft only.
Pilot’s Guide
190-01717-10 Rev. H
System Description
Logs
1.29 Flight Data Logging
The data logging function is capable of storing approximately
100 hours of flight data in the unit’s internal memory. This
information is available for export to an SD card for later analysis.
FEATURE REQUIREMENTS
• SD card for external data logging
• Flight Stream 510 wireless datacard for data streaming
FEATURE LIMITATIONS
• Engine exceedance logs are available only for turbine aircraft
• External data logging stops when the SD card is full.
Data Logging Function
• Generates log files automatically upon unit power-up
• Records various parameters related to aircraft flight instruments, engine
indications, and configuration
• Streams logged flight and engine data to Garmin Pilot when Flight Stream 510
is present
• Writes logged data to an SD card if one is present in the top/left slot
• Overwrites oldest files when the internal log reaches capacity
• Saves files in the .csv format and stores them in the “data_log” folder
FILE NAMING CONVENTIONS
Log file names provide a useful reference to aid data analysis. They include:
• Log start date and time
• Identifier of the nearest waypoint at the indicated start time
log_YYMMDD_HHMMSS_WPT.csv
Year
Month
Day
Hour
Minute
Second
Nearest Waypoint
Identifier
(at start of log)
Files with the name “log_000101_0000XX_____.csv” do not contain a valid date
and time stamp. These logs may include data recorded during installation.
1-58
Pilot’s Guide
190-01717-10 Rev. H
System Description
Data Logging at a Glance
Flight Stream present
GDU streams data to
Garmin Pilot†
Flight Stream present
GTN streams data to
Garmin Pilot†
To automatically upload
data to flyGarmin:
Install Flight Stream into
GDU or GTN
Upon power up, the GDU...
• Begins logging flight and
engine data automatically
• Stores the data in its internal
memory
• Writes the data to an SD card
(if present in top/left slot)‡
If Flight Stream is present in GTN
• GDU transfers logs to GTN,
which then streams the
data to Garmin Pilot
• GTN is the preferred
location for Flight Stream
installation
† Pilot setup required. ‡ No action required.
What happens if there’s a power interruption?
Data logging stops if power is lost. All data recorded up to that point remains
stored in the internal memory. Data is not recorded for the duration of the outage.
When GDU reboots, logging automatically resumes with a new log file.
190-01717-10 Rev. H
Pilot’s Guide
1-59
System Description
1.29.1
Exporting to SD Card
NOTE
Do not eject the SD card while the export function is in progress. Wait until
the Export Data Log key is available before ejecting the card.
Exportable parameters are dependent on aircraft type.
1. Insert an SD card into top/left slot.
2. Power on GDU.
3. Go to the Logs page.
4. Tap Export Data Log.
During export, the Export Data Log key is
unavailable (gray). It becomes available once
export is complete.
Export in Progress
What if I forget to insert my SD card
before flight?
Internal flight and engine data logging occurs
regardless of whether an SD card is present.
After your flight, you may insert a card and
download log files using the Export Data Log
command.
With the aircraft safely on ground:
1. Power off unit.
2. Insert card.
3. Power on unit.
4. Tap System > Logs > Export Data Log.
Wait for the export to complete before
ejecting the SD card.
1-60
Pilot’s Guide
Once the files are exported
onto SD card, you may
transfer the log files to your
personal logbook on
flyGarmin.com.
Duration varies
depending on the
number of files present.
For lengthy transfers, it
may be necessary to run
the engine or operate
on ground power until
the export is complete.
190-01717-10 Rev. H
System Description
TRANSFER DATA FROM SD CARD TO YOUR ONLINE LOGBOOK
The Logbook tab provides functions for creating and
viewing multiple logbook entries.
To create a logbook and upload data:
1. Sign in to your flyGarmin.com account.
2. Select Logbook > Setup.
3. Select Add Aircraft Type.
4. Provide all necessary aircraft type details, then select Save Aircraft Type.
5. Provide all necessary settings and pilot information, then select Save Settings.
6. Select Import from Spreadsheet.
7. Download the provided spreadsheet templates in the appropriate format. Log
entries and aircraft type data each require a dedicated spreadsheet.
8. Transfer your data from the SD card to the spreadsheets.
9. Save each spreadsheet in the .csv format.
10.Upload each .csv file using the associated Import command.
To upload flight logs to an existing logbook entry:
1. Select Logbook > Entries > Upload Flight Logs.
2. Select and upload the log files according to the onscreen instructions.
190-01717-10 Rev. H
Pilot’s Guide
1-61
System Description
1.29.2
Streaming to Garmin Pilot
The unit automatically streams logged flight data to the
Garmin Pilot app when Flight Stream 510 is present and paired to
a supported tablet or phone.
The data uploads to
flyGarmin.com upon
connecting to Wi-Fi
with Internet.
Logged flight and
engine data streams
to Garmin Pilot.
Your portable device
downloads the data
upon connecting to
Flight Stream 510.
This includes any
previous flights not
already downloaded.
What happens if I forget to bring my tablet on the flight?
No need to worry. During flight, GDU records log data to the internal storage
and SD card (if present). The next time you fly with your tablet, the data will
stream to Garmin Pilot. This includes all previously recorded flights. The device
downloads the data upon connecting to Flight Stream 510.
1-62
Pilot’s Guide
190-01717-10 Rev. H
System Description
1.30 Exceedance Logging
Unlike flight data logging, which records parameters at a specific
rate, exceedance logs record information about a specific gauge
when its value exceeds a threshold.
FEATURE REQUIREMENTS
• Turboprop EIS enablement
OR
• Fixed wing aircraft with variable VNE
FEATURE LIMITATIONS
• Engine exceedances apply to turboprop aircraft only
• Exceedance viewer can acknowledge entries on only one GDU at a time
Not all gauges have exceedance logging. Availability varies depending on airframe
and engine.
Exceedance Recording Function
• Generates an exceedance file after a gauge parameter exceeds its maximum
allowable time at an elevated level
• Engine exceedances record in-depth data about the exceeded gauge, and
contextual details about other parameters during that time
• Advisories notify 30 seconds after the exceedance ends (during flight), and
once the aircraft is on ground
• Entries are available for viewing on the dedicated summary page
Exceedances are installer configured to match the aircraft limitations in the POH.
Pilots are responsible for knowing and respecting all aircraft and engine
limitations.
190-01717-10 Rev. H
Pilot’s Guide
1-63
System Description
Exceedance Gauges
• Torque
• Prop RPM
• NG/N1
• Turbine Engine Temperature
• Oil Temperature
Many engine gauges have a maximum
allowable time limit that the parameter
may operate at an elevated level. This
"grace period" is indicated on the
gauge’s associated countdown timer.
Log entries do not generate until after
this timer expires.
The duration of the exceedance is the
amount of time that the indicated
parameter exceeds the limit, which
includes the grace period time.
• Oil Pressure
• Fuel Pressure
Parameter
Name
Each log entry includes the parameter
name, and the date, time, and
duration of the exceedance.
Date &
Time
Duration
Exceedances Summary Page
1-64
Pilot’s Guide
190-01717-10 Rev. H
System Description
INCOMPLETE ENTRIES
If GDU loses power while recording
an exceedance, the system marks
the duration as “Unknown.”
Incomplete log files contain data recorded up until the time of the interruption.
Some fields are not available due to the GDU not having knowledge of parameters at
the end of the exceedance.
1.30.1
Exceedance Alerts
An advisory informs that an exceedance
alert is available for viewing in the data log.
These alerts occur 30 seconds after the
exceedance ends and upon landing.
Notifications persist until all exceedances
are acknowledged.
ACK Alert
UNACK Alert
Tapping this key acknowledges the
corresponding alert. An alert
symbol indicates acknowledgment
is required.
Tapping this key unacknowledges
the corresponding alert.
Unacknowledged entries rise to the
top of the summary page.
ACKNOWLEDGE AN EXCEEDANCE ALERT
To view and acknowledge the exceedance advisory:
1. Go to the Logs page.
2. Tap Exceedances.
3. Review the list of alert entries.
4. Tap ACK for each unacknowledged entry.
190-01717-10 Rev. H
Pilot’s Guide
1-65
System Description
1.30.2
Exceedance Details
Select an exceedance file to
view gauge details.
Duration and highest value
are useful for determining
whether maintenance
actions are required.
The provided values of
other engine parameters
may be useful when
determining if an
exceedance resulted from
sensor testing or failure.
Exceedance Log Data
• Gauge and exceeded parameter
• Date & time of occurrence
• Duration (total amount of time the
parameter exceeded the limit, which
includes the grace period time)
The GDU uses an internal
circular log to store
exceedances entries for
100 power cycles that have
had an exceedance. The
user should periodically
export the exceedance log
to SD card.
• Highest gauge value
• Power cycle
• Max parameter value during exceedance
period
• Parameter value at end of exceedance
• Value of other engine parameters at
beginning of exceedance
• Any interruptions (e.g., power loss)
• Completeness of data
• Alert state (i.e., acknowledged or
unacknowledged)
1.30.3
If date and time
parameters are not
available (e.g., during
engine start when the
navigator has yet to
acquire a GPS signal),
use the power cycle
parameter value to
narrow down the time
of occurrence.
Exporting to SD Card
Exportable parameters are dependent on aircraft type.
1. Insert an SD card into top/left slot.
2. Power on GDU.
3. Go to the Logs page.
4. Tap Export Data Log.
1-66
Pilot’s Guide
190-01717-10 Rev. H
System Description
Compatible Equipment
1.31 Line Replaceable Units
SYSTEM REQUIRED LRUs (PFD)
ADAHRS or ADC with AHRS
GMU 44/44B
GTP 59
Garmin GPS navigator
The TXi system consists of multiple
LRUs, which are installed behind the
instrument panel or in a separate
avionics bay. Their modular design
aids system maintenance and unit
replacement.
SYSTEM OPTIONAL LRUs
Backup GPS antenna
GAD 43/43e adapter
GBB 54 battery
Optional LRUs may include
compatible equipment from either
Garmin or a third party
manufacturer.
GCU 485 PFD controller
GEA 110 engine airframe interface [1]
GEA 71 engine airframe interface [2]
OPTIONAL INTERFACES
Autopilot/flight director
GDL 69/69A SiriusXM data link
Some LRUs provide features that
require registration and/or
enablement prior to activation.
GDL 88/GTX 345 ADS-B transceiver
GSR 56 satellite data link
Radar altimeter
Stormscope
GTX 330 or
335 mode S transponder (TIS-A)
TAS/TCAS/TCAS II
Airborne weather radar
VHF NAV and glideslope receiver
DME
ADF
[1]
[2]
Piston aircraft only.
Turboprop aircraft only.
190-01717-10 Rev. H
Pilot’s Guide
1-67
System Description
1.31.4
PFD Controller
FUNCTIONAL LIMITATIONS
• Applicable to PFD only
• Selecting a data field does not automatically open control menu
An optional GCU 485 PFD controller provides dedicated PFD controls. Although
control of PFD functions is available using the GDU knobs and touchscreen, the PFD
controller provides dedicated knobs for heading, altitude, vertical speed, airspeed,
and BARO setting. Dedicated keys are provided for CDI source selection, GPSS
emulation mode, altitude capture arming, and vertical speed mode engagement.
If configured, the PFD controller is used to control a Standby PFD.
GCU 485 Features
• Control knobs offer alternative ways to adjust reference bugs and barometric
settings
• Push button configuration depends on the interfacing autopilot: CDI, GPSS,
ARM, and ENG
• Lighting may be controlled by the aircraft lighting or the internal photocell
(dependent upon configuration)
PFD CONTROLLER OPTIONS
CONTROL
1-70
FUNCTION
ALT
Sets the selected altitude bug.
HDG
Sets the selected heading bug.
BARO
Sets the selected barometric pressure value. Pushing
the knob reverts the setting to standard.
IAS
Sets the selected indicated airspeed.
VS
Sets the selected vertical speed.
ARM
Arms the autopilot altitude capture function.
CDI
Changes the NAV source for the CDI.
ENG
Engages the autopilot vertical speed mode.
GPSS
Engages or disengages GPSS mode.
Pilot’s Guide
190-01717-10 Rev. H
System Description
1.31.10 Engine Monitoring
RECIPROCATING ENGINES
LRU
DISPLAY
FUNCTION
• Manifold Pressure
• RPM
• Fuel Flow
• Oil Pressure
GEA 110
Garmin Engine Adapter.
Monitors engine, fuel,
and electrical systems for
piston engine aircraft.
• Oil Temperature
• EGT
EIS
• CHT
• TIT
• IAT
• Fuel Quantity
• Volts
• Amps
• Engine Data
TURBINE ENGINES
LRU
DISPLAY
FUNCTION
• Propeller RPM
• Gas Producer RPM
• Torque
GEA 71B
GEA 71B Enhanced
GEA 71C
Garmin Engine Adapter.
Monitors engine, fuel,
and electrical systems for
turbine aircraft.
• Engine Temperature
• Fuel Flow
EIS
• Fuel Quantity
• Oil Pressure
• Oil Temperature
• Fuel Pressure
• Volts
• Amps
• Engine Data
1-78
Pilot’s Guide
190-01717-10 Rev. H
System Description
1.31.15 Traffic
LRU
GTX 33
GTX 330
GTX 335
GTX 345
DISPLAY
FUNCTION
PFD
TIS-A
MFD
Garmin:
GTS 800
GTS 820
GTS 825
GTS 850
GTS 855
PFD
GTS 8000
PFD/MFD
TAS/TCAS I
TCAS II
Avidyne (Ryan):
TAS 6XX (9900BX)
Honeywell
(Bendix King):
KTA 810
KMH 820
KTA 910
KMH 920
MFD
TAS/TCAS I
L3 Communications
(Goodrich):
SKY497
SKY899
GDL 88
GNX 375
GTX 345
Third-party TCAS II
190-01717-10 Rev. H
PFD
ADS-B
MFD
PFD/MFD
TCAS II
Pilot’s Guide
1-81
Primary Flight Display
PFD Setup
PFD SYSTEM SELECTIONS, GDU 700( )
For GDU 700( ), setup selections are accessible from the System Menu key.
PFD Setup
• Access CDI/VDI Preview, Auto EDM, LOC CDI
Prompting and Wind Field functions
• Access synchronization options (BARO, CDI, and DB)
• Control clock/timer
• Control Outside Air Temp/Density Altitude display
• Set menu display timeout
Except where noted, unit selections synchronize across all
configured GDUs. Certain LRUs may contain unit settings
independent of the TXi system.
Units
• BARO Pressure
• Distance
• NAV Angle
• Temperature
• Wind Speed
Altitude unit settings do not affect the altitude tape.
Audio
• Set click volume
Backlight
• Adjust display brightness
Status
Databases
• View unit and software information
• Check status of all configured LRUs
• View information about active and standby databases
• Perform a manual database update
Flight Stream
• Access Bluetooth Setup and Wi-Fi Setup menus
Logs
• Access data, aircraft, and exceedance logs
190-01717-10 Rev. H
Pilot’s Guide
2-3
Primary Flight Display
PFD SETUP SELECTIONS, GDU 1060
For GDU 1060, setup selections are available on the System page of the MFD.
Clock/Timer
TEMP/DALT
• Control Outside Air Temp/Density Altitude display
• Specify air temperature units and reference type
Wind Field
• Control wind field function
Menu Timeout
• Set menu display timeout
CDI/VDI
Preview
• Enable preview indicators for VDI Glidepath/Glideslope
deviation, and VOR/LOC course and deviation [1]
Auto EDM
• Enable automatic EDM [4]
LOC CDI
Prompting
• Allow prompts for switching the CDI source from GPS
to LOC [2] [3]
SYNC Control
• Access synchronization options (BARO, CDI)
Database SYNC
[1]
[2]
[3]
[4]
2-4
• Control clock/timer
• View information about active and standby databases
• Perform a manual database update
Available only when a configured GTN is present.
Available only when a configured GPS/NAV navigator (GTN 650/750 or GNS 430/530) is
present.
For installations with a GFC 600, LOC CDI prompting is suppressed when the autopilot is
armed to capture the localizer. The TXi CDI source automatically switches from GPS to LOC
once the autopilot couples to the localizer.
Available only with GFC 600 installation and cabin altitude threshold configured.
Pilot’s Guide
190-01717-10 Rev. H
Primary Flight Display
2.1
Synchronization Options
FEATURE LIMITATIONS
• Multi-PFD systems only
• SYNC Control availability dependent upon configuration
Selecting SYNC Control opens a pop-up menu. Selected
functions synchronize across all TXi PFDs.
GDU 1060: The database synchronization option resides on the MFD System Status
page.
SELECTION
FUNCTION
BARO
• Synchronizes the current barometric pressure value [1]
CDI SRC
• Synchronizes the selected CDI source [1]
• Initiates the database synchronization function
DB
[1]
• GDU 700( ) only
Selection not available if synchronization function is configured as
always on.
190-01717-10 Rev. H
Pilot’s Guide
2-5
Primary Flight Display
2.3
Attitude Indicator
The attitude indicator provides a virtual representation of the ground and sky.
Roll Scale
Standard Rate Turn
Indicator
Roll Scale Zero
Roll Pointer
Slip/Skid Indicator
Sky
Pitch Scale
Horizon Line
Ground
ROLL POINTER
The roll pointer indicates angle of bank at
varying degrees on the roll scale.
Fixed Pointer
Pointer type is configured at installation as
either fixed or sky.
• Major tick marks: 30º and 60º
• Minor tick marks: 10º, 20º, and 45º
Sky Pointer
STANDARD RATE TURN INDICATORS
Standard Rate Turn Indicators
• Show the required bank angle needed
to maintain a standard rate turn
• Dynamically change position based on
True Airspeed
• Remain at 30º when TAS is at or above
210 kts
Standard rate turn indicators are removed when:
• TAS is invalid
• TAS is less than 60 kts
• Aircraft is on the ground
190-01717-10 Rev. H
Pilot’s Guide
2-11
Primary Flight Display
AIRSPEED CONTROLS & INDICATIONS
• Sets airspeed bug on tape if configured
Selected
Airspeed
• Both the bug and its digital value display in cyan
• Automatically synchronizes across all connected TXi PFDs
• Not selectable during EDM selected data lockout
(both field and bug turn gray)
• Magenta trend vector at the right of the airspeed tape
Airspeed
Trend Vector
Speed Range
Strip
• 6 second prediction of airspeed based on current
acceleration
• Removed if airspeed remains constant or if any data
necessary to calculate airspeed is not available due to a
system failure
• Multi-colored strip at the right of the moving tape
• Actual colors and patterns vary according to aircraft type
• Set using the selected airspeed control
• Present on the right, inboard side of the tape if configured
Selected
Airspeed Bug
• Parks at the top or bottom of the tape when selected
airspeed is outside the visible range
• Changes from cyan to gray during EDM selected data
lockout
2-18
Pilot’s Guide
190-01717-10 Rev. H
Primary Flight Display
2.6.1
Reference Markings
FIXED WING
The VNE, VMO, or MMO barber pole is
configurable as a fixed VNE value, or a variable
VNE/VMO/MMO value that changes with altitude.
VNE/VMO/MMO
For configurations with multiple variable
VNE/VMO/MMO values, the barber pole and
alerting parameters extend to the lowest
airspeed based on VNE/VMO/MMO calculations.
VNO
For fixed wing installations, exceeding a variable
VNE/VMO/MMO value creates an airspeed
exceedance entry.
VFE
A white triangle reference marking is configured
for airframes that are placarded with approach
flap speed limitations.
VSO
Approach Flap Speed
VLE
Low Speed
Awareness Band
VYSE
VMCA
ROTORCRAFT
VNO
VNE (Power Off)
Two types of markings are available for
denoting maximum auto rotation speed
(VNE power off). This option is
configured during installation.
Variable VNE is based on values in the
airspeed limitations placard.
Glide
VY
190-01717-10 Rev. H
Pilot’s Guide
2-19
Primary Flight Display
ALTIMETER CONTROLS & INDICATIONS
• Sets altitude bug on altimeter when configured
• Bug automatically synchronizes across PFDs
• If barometric minimums is set, selected altitude may be set
to same value as barometric minimums
Selected
Altitude
• Determines visual and aural alerts for approaching and
deviating from selected altitude.
• Not selectable during EDM selected data lockout
(both field and bug turn gray)
• Provides source data for the range to altitude arc display on
MFD map (GDU 1060 only)
• Controls altitude preselect mode for various autopilots
• Bug is removed upon system startup or by rotating control
knob to a value <-1,000 ft
• Magenta trend vector at the left of the altitude tape
Altitude Trend
Vector
• 6 second prediction of altitude based on current vertical
speed
• Absent if aircraft altitude remains constant or if data
needed for rate calculation is not available due to a system
failure
• Displays in cyan digits at the bottom of altimeter tape
Barometric
Correction
Control
• Pilot can select units to display in inches of mercury
(in Hg), Hectopascals (hPa), or Millibars (Mb)
• Digits display in yellow when pilot and co-pilot TXi PFD
settings differ by more than 0.03 in Hg
• Barometric Pressure Setting to 29.92 in. / 1013 Mb setting
when STD BARO is selected
• Displays as a colored bracket for selected MDA/DH
minimums set on the altimeter tape
• Bug is parked to the top or bottom of altimeter tape when
value is outside current visible range
Minimums
Bug
• Cyan bracket denotes BARO or RAD ALT minimums altitude
• Magenta bracket denotes TEMP COMP minimums altitude
• White bracket denotes close proximity above minimums
altitude
• Yellow bracket denotes below minimums
• Triggers “Minimums, Minimums” aural alert at MDA/DHs
2-22
Pilot’s Guide
190-01717-10 Rev. H
Primary Flight Display
2.8
VSI
Vertical speed data displays on either a standard or arc style indicator. Format is
dependent on unit type (portrait or landscape) and installer configuration.
Arc VSI
Standard VSI
Fixed Scale
Fixed Scale
Trend Indicator
Vertical Speed
Rate Needle
VS Bug
Numeric Speed
Indication
Vertical Speed
Control
Moving needle indicates current
vertical speed on a fixed scale.
Vertical Speed
Control
Trend indicator replaces needle,
pointer, or indications.
AUTOMATIC FORMAT CHANGES
The arc format changes to standard when alternating between full and split views
(arc during full PFD, standard during split). This occurs in the following display
configurations.
GDU 1060 MFD/PFD/EIS or MFD/PFD (60%/40%)
GDU 700L PFD/menu open
2-28
Pilot’s Guide
190-01717-10 Rev. H
Primary Flight Display
TCAS II RAS
The TCAS II uses transponder replies to determine relative altitude, range, and
bearing of any air traffic control radar beacon system (ATCRBS) or Mode S equipped
aircraft with altitude reporting. Based on the information TCAS II determines the
level of advisory. The TCAS II will not issue RAs for ATCRBS aircraft that reply with
only Mode A information.
Requirements:
• Installed GTS 8000 or compatible ARINC 429 TCAS II unit
• GDU 1060 with 60% PFD or 700L PFD
• Standard style VSI
When the TCAS II LRU issues an RA, the
VSI displays red no-fly bands to indicate
areas to avoid. The green band indicates
the desired climb/descent rate.
NUMERIC SPEED INDICATION
GDU 1060/700L: A numeric field displaying current vertical speed is available on
both standard and arc VSIs. The type of field depends on indicator format and, in the
case of arc VSI, aircraft type.
Standard VSI: This field replaces the trend indicator and
moves up or down as the vertical speed changes. It displays
only in expanded layouts.
GDU 1060: full screen PFD, split MFD/PFD, and split PFD/EIS
GDU 700L: full screen PFD
Arc VSI: Field behavior is dependent upon aircraft type:
For rotorcraft, a stationary field appears when vertical speed
exceeds +/- 300 fpm (1.5 mps).
For fixed wing aircraft, the digital value is always present.
190-01717-10 Rev. H
Pilot’s Guide
2-29
Primary Flight Display
VERTICAL SPEED RANGE
Vertical speed range is dependent upon
aircraft performance. Both range and
units are configured at installation.
Available range types include:
+/- 2,000 FPM
+/- 3,000 FPM
+/- 4,000 FPM
+/- 6,000 FPM
Metric:
+/- 15 MPS
+/- 9 MPS
Fixed Scale Range Options
+/- 21 MPS
+/- 30 MPS
REQUIRED VERTICAL SPEED INDICATION
When receiving VNAV data from the
navigator, a magenta chevron indicates
the rate of descent needed to reach
target altitude.
2.8.1
Selected Vertical Speed
Controls for setting the vertical speed bug reside in the
VS control menu. Selected VS bug limits are determined
by the visible tape range.
SELECTION
FUNCTION
VS SYNC
• Synchronizes selected VS bug to current vertical speed
VS
• Allows entry of a numeric vertical speed
2-30
Pilot’s Guide
190-01717-10 Rev. H
Advanced Features
CONDITION
COMMAND INDICATION
Commanded pitch is greater than
GDU maximum allowable limit.
Command bars display at maximum
allowable limit.
Aircraft pitch exceeds -20º/+30º.
Command bars and annunciations
declutter.
Aircraft roll exceeds ±65º.
Attitude information becomes invalid
or unavailable.
Command bars do not display.
AP ENGAGED INDICATION
For some autopilots, single cue command bars alternate between hollow and solid to
show autopilot status.
AP Engaged
Command bars are solid.
190-01717-10 Rev. H
AP Not Engaged
Command bars are hollow.
Pilot’s Guide
3-23
Advanced Features
3.8
Low Bank Mode
FEATURE REQUIREMENTS
• PFD
• GFC 600 with low bank mode support
This feature is intended for aircraft that operate at high altitude or would otherwise
need low bank autopilot support (e.g., multi-engine aircraft experiencing engine
failure during takeoff).
Roll Limits
When crossing the altitude
threshold, enable low bank mode
by activating the associated
switch. A green arc appears on the
roll scale to indicate the roll limits.
Actual roll limits are determined by
the autopilot and based on
airframe type.
3.9
Servo Heading Reference
FEATURE REQUIREMENTS
• PFD
• GFC 600
FEATURE LIMITATIONS
• Rotorcraft only
For rotorcraft, the option to beep heading using the yaw beep switch is available
while hovering. This displays as the servo heading reference bug on the HSI and as a
numeric value in a field adjacent to the HSI.
Servo Heading
Reference Bug
190-01717-10 Rev. H
Servo Heading
Reference
Pilot’s Guide
3-25
Multi-Function Display
MFD Setup
MFD SYSTEM SELECTIONS
SELECTION
FUNCTION
• View unit, software, and database information
System Status
External LRUs
Setup
Units
• Check standby database availability
• Access Database SYNC, Chart Streaming, and manual
database update functions
• Check status of all configured LRUs
• Set the clock and click volume
• Create Weather page shortcut
Specify units of measure for displayed data. Selections
synchronize across all configured GDUs. Certain LRUs may
contain unit settings independent of the TXi system.
• Distance
• Temperature
• Altitude
• NAV Angle
Backlight
• Adjust display brightness
Crew Profile
• Access crew profile management function
Flight Stream
• Access Bluetooth Setup and Wi-Fi Setup menus
Aircraft Log
• View engine and airframe cycle counters
Exceedances
Export Data Log
190-01717-10 Rev. H
• View and acknowledge exceedance advisories
• Availability dependent upon unit configuration
• Save logged data to SD card
Pilot’s Guide
4-3
Multi-Function Display
4.1
Nearest Airport Criteria
Filtering criteria includes settings for minimum runway length and hard or soft
runway surface options. Selections determine which airports are available when
using the nearest airport search feature.
RUNWAY SURFACE
Aircraft runway surface selection:
• Any
• Hard/Soft
• Hard Only
• Water
4.2
MINIMUM RUNWAY LENGTH
Specify the shortest distance
required for takeoff and landing.
In the AFM/POH, this is typically
the distance given for sea level and
the coldest air temperature.
MFD Resize Option
FEATURE LIMITATIONS
• GDU 1060 PFD/MFD units with software v3.00 and later
• Availability dependent upon configuration
• Accessible from the MFD Home page only
The Resize key allows you to change the size of the MFD screen.
This key resides on the MFD Home page.
Tapping the key once expands the MFD from the default 40%
screen area to 60%. Tapping it again returns the screen to
40% area.
4-4
Pilot’s Guide
190-01717-10 Rev. H
Multi-Function Display
Map
To increase situational awareness, the Map page depicts the
aircraft’s current position relative to land, aeronautical, weather,
and traffic information.
FEATURE REQUIREMENTS
• Active GPS source (aircraft position symbol)
• FIS-B, Iridium transceiver, or SiriusXM receiver (weather data)
• GDL 69, GDL 88, GTX 345, or GSR 56, with appropriate weather service
subscription (NEXRAD overlay)
• Active weather subscription (Connext and SiriusXM only)
• Valid charts database (ChartView, FliteCharts) with effective database cycle,
and aircraft to be airborne
• GWX 68, GWX 70, or GWX 75 (airborne weather radar overlay)
• WX-series Stormscope receiver (lightning data)
• GTS 8000 or feature enablement (TCAS II traffic data)
FEATURE LIMITATIONS
• Onboard weather radar not available for GDU 700( ) EIS/MFD configuration
Map
Orientation
Basemap
True North
Indicator
NAV Range
Ring
Map Range
Indicator
Actual Aircraft
Location
Aircraft Symbol
Map Overlay
Icons
Advisory
Key
Menu Key
Default Map Elements
190-01717-10 Rev. H
Pilot’s Guide
4-5
Weather Awareness
5.24 FIS-B Weather
No pilot action is required to receive FIS-B weather information.
FIS-B weather products include:
• METARS
• TAFs
• PIREPs
• AIRMETs
• SIGMETs
• NOTAMs
• Winds Aloft
• Temperatures Aloft
• Cloud Tops
• TFRs
• Lightning
• Turbulence
• CWA
• NEXRAD (Regional and
CONUS combined
FEATURE REQUIREMENTS
• UAT receiver (GDL 88, GTX 345)
The FAA provides FIS-B as a Surveillance and Broadcast Service operating on the UAT
(978 MHz) frequency band. FIS-B uses a network of FAA-operated ground-based
transceivers to transmit weather datalink information to the aircraft’s receiver on a
scheduled continuous basis.
The Flight Information Service-Broadcast (FIS-B) Weather service is freely available for
aircraft equipped with a capable datalink universal access transceiver (UAT). Ground
stations provide uninterrupted services for the majority of the contiguous U.S.,
Hawaii, Guam, Puerto Rico, and parts of Alaska. No weather subscription service is
required. For the latest FAA ground station coverage information, visit:
www.faa.gov/nextgen/programs/adsb/
FIS-B weather product update and transmission intervals are published in the SBS
Description Document associated with TSO-C157b. This information is available
electronically at the FAA’s Regulatory and Guidance Library: https://rgl.faa.gov/
5.24.1
FIS-B Data Transmission Limitations
FIS-B broadcasts provide weather data in a repeating cycle which may take several
minutes to completely transmit all available weather data. Therefore, not all weather
data may be immediately present upon initial FIS-B signal acquisition.
LINE OF SIGHT RECEPTION
To receive FIS-B weather information, the aircraft’s datalink receiver must be within
range and line-of-sight of an operating ground-based transceiver. Reception may be
affected by altitude, terrain, and other factors. Per the FAA, much of the United
States has FIS-B In airborne coverage at and above 3,000 feet AGL. Terminal
coverage is available at altitudes below 3,000 feet AGL and is available when flying
near approximately 235 major U.S. airports. Surface coverage allows FIS-B ground
reception at approximately 36 major U.S. airports.
5-30
Pilot’s Guide
190-01717-10 Rev. H
Traffic Awareness
6.5
TCAS II
WARNING
TRAFFIC INFORMATION SHOWN ON SYSTEM DISPLAYS IS PROVIDED AS
AN AID IN VISUALLY ACQUIRING TRAFFIC. TRAFFIC AVOIDANCE
MANEUVERS ARE BASED UPON TCAS II RESOLUTION ADVISORIES, ATC
GUIDANCE, OR POSITIVE VISUAL ACQUISITION OF CONFLICTING
TRAFFIC.
NOTE
If the installed TCAS II traffic system is not a GTS 8000, refer to the
applicable documentation for system-specific information.
FEATURE REQUIREMENTS
• GDU software v3.00 and later
• GTS 8000 or third-party TCAS II system
TCAS II Features
• Monitors nearby airspace for aircraft flying with operating transponders
• Issues TAs to assist in visual identification of traffic
• Issues RAs to provide recommended vertical guidance maneuvers to resolve
traffic conflicts
6.5.1
TCAS II Status Indications
TRAFFIC PAGE
ANNUNCIATIONS
SELECTION
TCAS II Self-Test Initiated (TEST)
Test
Traffic and Resolution Advisory (TA/RA)
TA/RA
Traffic Advisory Only
TA Only
TCAS II Standby
STBY
TCAS II Failed
Fail
190-01717-10 Rev. H
Pilot’s Guide
6-11
Traffic Awareness
6.5.2
TCAS II Alerts
When the TCAS II unit issues a TA or RA,”TRAFFIC” appears in the annunciator bar
of the GDU, flashes for 5 seconds and remains until no TAs or RAs are detected.
• RA ‘TRAFFIC’ annunciations are white text with red backgrounds
• TA ‘TRAFFIC’ annunciations are black text with yellow backgrounds
• If a TA and RA occur simultaneously, only the red and white RA “TRAFFIC”
annunciation displays
If the GDU is not displaying the Traffic page, the system displays a traffic alert
pop-up.
• During a TA event, the system issues a single “Traffic, Traffic” voice alert each
time the system detects a new TA threat
• During an RA event, voice alert(s) provide vertical guidance to resolve the
traffic conflict
• The VSI displays a range of vertical speeds to fly to or avoid as applicable
• Additional voice alerts occur if the RA status changes and when the
aircraft is clear of the conflict
6-12
Pilot’s Guide
190-01717-10 Rev. H
Traffic Awareness
TRAFFIC ALERT BANNER
If the traffic system cannot determine the bearing of a traffic or RA, the alert displays
as a traffic alert banner.
Warning Banner
RA X.X ± XX <UP> OR <DN>
• Displays when the system is
unable to determine the
bearing of an RA and
extreme pilot vigilance is
required
• Banner indicates distance in
nm and altitude separation
in hundreds of feet
• If altitude trend is available,
the banner indicates
altitude trend up <UP> for
climbing and down <DN>
for descending traffic
Caution Banner
• Displays when the system is
unable to determine the
bearing of a TA and pilot
vigilance is required
TA X.X ± XX <UP> OR <DN>
• Banner indicates distance in
nm and altitude separation
in hundreds of feet
• If altitude trend is available,
the banner indicates
altitude trend up <UP> for
climbing and down <DN>
for descending traffic
190-01717-10 Rev. H
Pilot’s Guide
6-13
Traffic Awareness
6.5.3
TCAS II Traffic Symbols
Traffic information is for advisory use only. The pilot is responsible for identifying and
avoiding traffic conflict. The TCAS II system categorizes detected traffic into four
groups of increasing collision threat potential. Lowest threat is OT and the highest is
RA.
OT
Other non-threatening traffic.
PA
Traffic is not currently a threat, but is within 6 nm and
±1,200 feet of the own-aircraft altitude.
TA
Indicates traffic is within 20-48 seconds of a potential collision
area.
Off-scale TA
Traffic is beyond the selected map range and the system
displays a half-TA symbol at the edge of the map at the
approximate relative bearing of the TA traffic. If TA traffic
subsequently meets the criteria for an RA, the system issues
an RA.
RA
Indicates traffic is within 15-35 seconds of a potential collision
area.
Off-scale RA
If RA traffic is beyond the selected map range, the system
displays a half-RA symbol at the edge of the map positioned
at the approximate relative bearing to the RA traffic.
6.5.4
TCAS II with ADS-B
NOTE
Aircraft that are surveilled by ADS-B In only will not trigger a TCAS
resolution advisory.
TCAS II interrogates Mode-S transponder data while automatically receiving ADS-B
position and velocity information directly from a comparably equipped aircraft target.
For preciseness, the system correlates between two data sources and the system
displays the traffic information for the source determined to be the most accurate.
Traffic that is not correlated (i.e., only detected by one system but not the other) is
also displays for the flight crew. This may occur, for example, if another aircraft is
beyond the surveillance range of the TCAS II, but it is still receiving position and
velocity information from other ADS-B equipped aircraft. The traffic correlation
feature improves the accuracy of the traffic displayed, while reducing the occurrence
of displaying a single target twice.
6-14
Pilot’s Guide
190-01717-10 Rev. H
Terrain Awareness
7.9.1
TAWS-A
FUNCTIONAL REQUIREMENTS
• Valid 3-D GPS position
• GTN with TAWS-A feature enablement
• Valid flap and landing gear status inputs into the GTN
• Valid radar altimeter
• External annunciator for displaying alert information (non-PFD GDUs only)
TAWS-A Features
• Optional TSO C151c Class A terrain alerting system
• All Terrain-FLTA functions plus: premature descent, excessive descent rate,
negative climb rate, excessive glideslope/glidepath deviation, flap override,
flight into terrain, and altitude voice callout (500 ft) alerts
• Terrain depictions and display overlays
• Textual annunciations on PFD
• Pop-up alerts on MFD
On PFD: Changes in CDI source selection have no effect on TAWS alerting functions.
For more information, refer to the applicable GTN series pilot’s guide.
7-28
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
Turbine Engines
8.8
EIS Display
The EIS displays engine, electrical, and fuel information using
parameter specific indicator types (e.g., analog indicators, digital data
fields, dynamic markings, horizontal and vertical bar indicators).
FEATURE REQUIREMENTS
• GDU 700P configured for turboprop EIS only
• GDU 1060 with turboprop EIS display
These instruments replace traditional analog
gauges used for starting the engine and
monitoring performance. For limitations,
consult the AFM or POH.
Layout varies according to display type and
the number and type of installed sensors.
GDU 700P presents engine instrumentation
on a full-screen dedicated display when
configured for EIS.
GDU 700P
8-22
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
GDU 1060 presents two
views of engine
instrumentation: a pilot
selectable Engine page on
the MFD, and a vertical
gauge strip which is
always present.
Engine Page
Engine Page
Gauge Strip
• Expanded information for configured secondary engine
gauges
• Pilot selectable user fields
• Menu access key
• Unobstructed compact view of primary engine information
Gauge Strip
• Resides at the left or right edge of the display [1]
• No selectable features
[1]
Location dependent upon configuration.
190-01717-10 Rev. H
Pilot’s Guide
8-23
Fuel & Engine Indicating System
8.9
EIS Setup
The Menu key provides access
to the fuel computer, engine
and flight hours, and engine
advisories. On GDU 700P,
controls for customizing system
settings also reside here.
GDU 700P setup functions are
accessible from the System
menu. On GDU 1060, they
reside on the MFD System page.
Specify units of measure for fuel computer and pilot selectable
gauges. Selections synchronize across all configured GDUs. [1]
Units
• Distance
• Temperature
• Fuel Computer
• View unit and software information
Status
• Check status of all configured LRUs
Backlight
• Adjust display brightness
Aircraft Log
• View engine and airframe cycle counters
Exceedances
• View and acknowledge exceedance advisories
Export Data
Log
• Save logged data to SD card
[1]
8-24
Engine gauge units are not adjustable.
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
8.10 EIS Functions
Graphical Indicator
Horizontal Bar
Indicators
Electrical Gauge
Fuel Used
Indicator
Text Lamp
Selectable
User Field
Single
Horizontal
Bar Indicator
Dual Digital Data
Fields (Selectable)
EST Fuel
Remaining
Indicator
Common EIS Display Elements
Graphical
Indicators
Display a graphical presentation and digital readout of the
specified value. If configured, these gauges may be
accompanied by a text lamp. [1]
Digital Data
Fields
Display a digital readout from the associated sensor. [1]
Includes single or dual input values depending on system
configuration.
Fuel Quantity
Gauges
Display fuel amounts for the specified fuel tanks. [2]
Horizontal
and Vertical
Bar Indicators
Display instrument information on a single horizontal or vertical
bar. Includes single or dual pointers depending on engine type.
May include digital readout fields depending on display layout.
Selectable
User Field
Opens a menu of the selectable data fields available for display.
The type of parameters available for selection is determined
during installation. A gray border differentiates selectable user
fields from non-selectable digital data fields.
[1]
[2]
Limits are configured according to system design or the AFM/POH. They are not pilot
selectable.
Fuel gauges are configured and calibrated during installation.
190-01717-10 Rev. H
Pilot’s Guide
8-25
Fuel & Engine Indicating System
8.11 Gauges
8.11.1
Gauge Types
Gauge labels are customizable to match aircraft configuration. Labeling presented in
the following table may differ from actual labeling on the unit.
LABEL [1]
UNITS
FUNCTION
NG
%, RPM
• Engine gas producer speed
NP
%, RPM
• Propeller RPM
TRQ
%, psi, ft-lb • Engine torque
Engine TEMP
ºC, ºF
Fuel or Fuel
Pressure
psi, bar
gph, lt/hr,
PPH,
kg/hr
• Fuel flow
FF
Oil or Oil
Pressure
psi, HPa,
bar
• Oil pressure
Oil or Oil
Temperature
ºC, ºF
Fuel or
Main Fuel
lb, lt, gal,
kg
• Current fuel quantity in main tanks
EST Fuel RMNG
lb, lt, gal,
kg
• Estimated fuel based on pilot entered value
and fuel flow
Tip Fuel
lb, lt, gal,
kg
• Current fuel quantity in tip tanks
Aux Fuel
lb, lt, gal,
kg
• Current fuel quantity in auxiliary tanks
Bus Volts
V
• Bus voltage
Bat Volts
V
• Battery voltage
ALT/Gen AMPS
or ALT/Gen %
A, %
BAT Amps
A
• Turbine engine temperature
[1]
8-26
• Typically inter turbine temp (ITT) or exhaust gas
temp
• Fuel pressure
• Oil temperature
• Alternator/generator load
• Battery load
Actual gauge labels are dependent upon installer setup.
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
CABIN ALTITUDE/RATE
FEATURE REQUIREMENTS
• GFC 600 autopilot configured to provide cabin altitude
• Displays cabin altitude from the GFC 600 autopilot
• GDU calculates cabin rate based on received altitude
• Units (FT, FT/Min or MT/Min) are determined by the
System Units
• Beneficial for TXi installs in pressurized aircraft
• Available as a user-selectable field on MFD Engine page
DIGITAL FUEL TOTALIZER
This gauge displays the fuel totalizer calculation from the fuel computer (estimated
fuel remaining). It is available in two formats:
• a user-selectable field on MFD Engine page
• a non-selectable gauge on the EIS gauge strip
Selectable User Field
Non-selectable Gauge
MFD Engine Page
GDU 1060/700( )
EIS Gauge Strip
GDU 1060 only
The estimation of fuel remaining is based on the pilot input of fuel onboard
along with the measurement of fuel flow.
190-01717-10 Rev. H
Pilot’s Guide
8-27
Fuel & Engine Indicating System
SUNRISE TURBINE GAUGES
These truncated round gauges have fewer graduations, allowing room for more
gauges on the display. Labels may vary based on configuration.
Gas Generator Turbine Speed
(N1, NG)
• RPM or % RPM values
Torque
Engine Temperature
• Units are °F or ºC
Propeller RPM
• Units are %, ft-lb, or psi
• RPM or % RPM values
• Displays up to four
whole numbers
Propeller RPM Minimum Threshold
Depending on aircraft, sensor type, and configuration, this gauge may be
configured with a minimum threshold value. During start and shutdown, RPM
values below this threshold display as a series of dashes (---). Values above the
threshold display as normal.
8-28
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
NON-SAFE RANGE INDICATIONS & ALERTING
Alert Suppression
To avoid nuisance alerts while the
parameters are in typical ranges
for the engine state, flashing is
suppressed for fuel pressure, oil
pressure, and oil temp when the
engine is off or starting.
To attract attention, engine gauge
display markings (bands, radials,
limitations) change appearance when a
parameter is within a caution or
warning alert band. These non-safe
range indications remain active while
the gauge is within the alerted range.
Warning
Caution
Pointer Color
Change
Solid
Highlight
Pointer Color
Change
Solid
Highlight
Dynamic Gauge
Solid
Highlight
Pointer Color
Change
Solid
Highlight
Pointer Color
Change
Horizontal Bar Indicator
190-01717-10 Rev. H
Pilot’s Guide
8-29
Fuel & Engine Indicating System
TEXT LAMPS
Text lamps are available for the
following sunrise gauges:
• Torque
• ITT
• NG
If configured, sunrise gauges may be
accompanied by a text lamp. These
windows display a single abbreviated
message when the related system is in
operation.
These fields appear at the top left of the
gauge.
• NP
• Fuel Flow
• Oil Temperature
• Oil Pressure
Text color and behavior (i.e., solid or flashing)
are dependent upon configuration.
Starter lamps may display a timer.
When the system is inactive, the window
is empty.
TEXT
MEANING
Text color and behavior
(i.e., solid or flashing) are
dependent upon configuration.
START
Starter on
IGN
Ignition on
BETA
Reverse thrust
When the starter lamp is configured, GDU uses the photocell for display
brightness during engine start. This is to ensure EIS visibility as power is drawn to
start the engine.
8-30
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
8.11.2
Timers
FEATURE LIMITATIONS
• Timer type, quantity, and availability are dependent upon configuration
• Maximum allowable exceedance time (or grace period) dependent upon
configuration
Timers are available for the
following gauges:
• Torque
• Prop RPM
• NG/N1
• Turbine Engine Temperature
• Oil Temperature
Timers indicate the amount of time
remaining in the allowable grace period
for operation above a limit.
If configured, timers appear at the
bottom right of the gauge, adjacent to
the parameter field.
Timer exceedances are viewable in the
System Logs.
• Oil Pressure
• Fuel Pressure
A single gauge may contain multiple timers running simultaneously.
Timer fields always display the parameter with the shortest time remaining. The
other timers continue to count down. If a timer expires, the system generates an
exceedance log entry for the parameter.
Timers:
• Exceedance
• Engine start/cooldown
190-01717-10 Rev. H
Pilot’s Guide
8-31
Fuel & Engine Indicating System
EXCEEDANCE TIMERS
Exceedance timers indicate the maximum allowable
time that the parameter can operate at an elevated
level. This grace period is configured by the installer
during initial setup. Depending on the parameter
type, the time limit may be based on aircraft or
engine manufacturer specifications.
Exceedance Timer Behaviors
• Timer begins counting once the indicated parameter exceeds its threshold
• Timers reset/disappear if the parameter falls below the threshold prior to
expiration
• Exceedance recording begins when the timer expires (i.e., once grace period
ends)
• Exceedances without a grace period cause the system to record a log entry
upon going above the threshold and does not display a timer
Exceedance timers are very useful for recording temperature exceedances during
engine starts. For more information about exceedance logging, refer to
section 1.30.
8-32
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
Within Range
Timer does not display during
normal operating conditions
Above Threshold
Timer displays once the
parameter exceeds threshold.
Automatic countdown begins.
Approaching Time Limit
Timer begins to flash during
the last 5 seconds of the
configured grace period.
Warning/Expired
Timer changes color once it
reaches zero. It flashes in unison
with the alerted gauge pointer,
value, and label, indicating a
warning condition. Exceedance
recording begins.
While the timer counts down, attempt to remedy the exceeding parameter by
managing aircraft systems or reducing engine power.
The exceedance timer feature is useful for managing engine and aircraft systems
within safe operating limits. The feature relies on the installer to configure specific
aircraft/engine data and it is possible not all operating limitations are entered into the
EIS system. The pilot in command is responsible to know and abide by all published
limitations and operating ranges in the POH/AFM.
190-01717-10 Rev. H
Pilot’s Guide
8-33
Fuel & Engine Indicating System
ENGINE START/COOLDOWN TIMERS
• Availability dependent upon
configuration
• Start timer counts up from zero
when the starter engages
• Starter cooldown timer changes to
blue and counts down from zero if
the starter engages then
disengages without a successful
engine start
• May display as a text lamp with a
sunrise gauge or as a
user-selectable field on the MFD
Engine page (depending on
configuration)
On MFD: The start timer is available as a user select gauge on the Engine page.
When the starter is active:
• Label changes to show that the starter is “Engaged”
• Timer begins counting up from zero to indicate the
amount of time that the starter has been active
When the starter is inactive, the gauge displays underscores.
When the starter switches from active to inactive, but the
engine is OFF:
• Timer text turns blue and the label changes to show the
starter is in “Cooldown”
• Timer counts down from zero (negative value) to indicate
the time since the starter was turned off
When the starter goes from active to inactive, and the engine is
in the RUNNING or STARTING state, the annunciation changes
to “Ready.”
8-34
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
8.11.3
Counters
NOTE
Do not reboot the GDU during flight unless operational procedures dictate.
Doing so may register an additional engine or airframe cycle. Contact a
Garmin dealer to adjust counters to match other tracking records.
Counter Types
• Engine and flight hours
• Takeoffs and Landings
• Starts and Shutdowns
(based on engine data)
Counters record various cycle data
(e.g., takeoffs/landings, engine and
flight hours). These fields always display
the counter type with the higher value
(e.g., if the number of starts is higher
than the number of shutdowns, the
number of starts displays).
Counter values are viewable in the
System Logs.
ENGINE & AIRFRAME CYCLE COUNTERS
Types include: Takeoffs and Landings; Starts and Shutdowns (based on engine data)
Turbine engine components are
life limited by hours of operation
and the number of cycles. In the
past, aircraft operators would
typically record the number of
flight hours and operations in a
paper logbook. GDU records this
information automatically.
• Takeoffs/landings increment based
on GPS, air data, or the weight on
wheels discrete
• System records parameters
separately on individual counters
• Higher counter value always displays
(e.g., if the number of starts is higher
than the number of shutdowns, the
field displays the number of starts)
GDU stores and displays the information in the aircraft log.
Home > System > Logs > Aircraft Logs
ENGINE AND FLIGHT HOURS
The system records engine and flight hours. These parameters
may display as a user-selectable field. They are also viewable in
the aircraft log.
For convenience, engine and flight hours
also display on the startup screen.
190-01717-10 Rev. H
Pilot’s Guide
8-35
Fuel & Engine Indicating System
8.11.4
Dynamic Markings and Indications
NOTE
It is the responsibility of the pilot in command to know and abide by all
published limitations and operating ranges in the POH/AFM.
FEATURE LIMITATIONS
The dynamic gauge feature relies on the installer to configure specific aircraft/engine
data. It is possible that not all operating limitations are entered into the EIS system.
Dynamic Gauge Markings
Knowing what you need to know
The EIS system is useful for
managing engine and aircraft
systems within safe operating
limits. Dynamic gauges further
assist the pilot by presenting only
the gauge limits and markings
appropriate for the current aircraft
conditions. This allows for easier
gauge interpretation as well as
increased safety and efficiency.
Dynamic gauge range markings change
to accommodate non-safe range and
alerting parameters. For example, torque
gauge markings change based on
propeller RPM, while temperature
markings change based on engine
operating conditions.
COLOR INDICATIONS
Colors are in accordance with their specified operating limits. Units of measure,
limits, and gauge colors are configured during installation.
• Amber radial line or arc denotes a caution range
• Red minimum/maximum line or arc denotes a limitation
8-36
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
MARKING SETS
Dynamic markings modify the standard gauge by showing only the pertinent
information during a particular flight situation.
The system uses four types of marking sets.
Standard
Configured by the installer to
match the existing ITT gauge
in the aircraft.
If for any reason the system
cannot determine the correct
markings to show, the gauge
defaults to the standard set.
Starting
Once the system determines
that the engine is starting, the
gauge changes to show the
starting temperature limits.
In this example, the absolute
maximum temperature is absent
and the highest red line limit
indicates starting maximum
temperature.
Running
Alerted
Once the system determines
that the engine is running,
the gauge changes to show
the cruise red line limit.
Alerting behavior changes
based on the active marking
set.
Starting limit indications are
absent.
Unlike analog gauges, which require you to memorize limitations or interpret
multiple markings, dynamic gauges present only the limitations applicable to
specific situations or flight conditions.
190-01717-10 Rev. H
Pilot’s Guide
8-37
Fuel & Engine Indicating System
GAUGE PREVIEW
You may generate a report detailing the different dynamic marking states for each
individual gauge. This information is unique to the aircraft and its configuration.
Gauge Report
Use this report to familiarize yourself with the different marking states that are
possible with each gauge. To obtain a report, contact your dealer for assistance.
8-38
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
8.11.5
Gauge Interactions
SELECTABLE USER FIELDS
These fields allows selection of engine and fuel parameters for display on the EIS.
Available user fields and selectable parameters are determined during installation.
Tapping any user field opens a list of available engine parameters and their current
values. Selecting a parameter displays its value on the EIS and closes the menu.
• Fields may be modified to display alternate data at any time
• Several parameter units are pilot adjustable
KEY
EST Fuel
Remaining
DISPLAYS
• Estimated amount of total fuel remaining [1] [3]
Fuel Used
• Total fuel used since last update to estimated fuel remaining
quantity [1] [3]
Range
• Total range based on remaining fuel and current ground
speed [1] [3]
Endurance
(HH+MM)
• Fuel endurance time in hours+minutes [1]
Fuel at
Destination
• Estimated fuel amount at current flight plan destination
[1] [2] [3]
Endurance
at DEST
• Remaining fuel endurance time (hours+minutes) at
destination [1] [2]
Flight/Engine
Hours
• Total flight and engine hours [5]
Efficiency
• Fuel efficiency [3]
Outside Air
TEMP (ISA)
• Degrees deviation from the International Standard
Atmosphere model [4]
Outside Air
TEMP (SAT)
• Outside static air temperature [4]
Outside Air
TEMP (TAT)
• Outside total air temperature [4]
Cabin
Altitude/Rate
• Cabin altitude and calculated cabin rate [6] [7]
[1]
[2]
[3]
[4]
[5]
[6]
[7]
Values are based on fuel computer calculations.
Requires an active flight plan from the navigator.
Parameter units are pilot selectable.
Units are independent of PFD units.
Engine hours accumulate when an engine is running. Flight hours accumulate when the
aircraft is in air.
Units are dependent upon configuration.
Requires cabin altitude data from GFC 600. Rate calculations performed by GDU.
190-01717-10 Rev. H
Pilot’s Guide
8-39
Fuel & Engine Indicating System
8.12 EIS Operations
PHASE
OF FLIGHT
OPERATION
Customize system settings
Initial Setup
Set fuel full and tab capacity levels
Set engine advisories
Calibrate fuel flow
8.12.1
Preflight
Add fuel
En Route
Monitor gauges
Post Flight
Record aircraft log and exceedance data
Initial Setup
Initial setup operations include:
• Customizing system settings
• Setting fuel tabs
• Setting engine advisories
• Calibrating fuel flow
CUSTOMIZE SYSTEM SETTINGS
Specify all necessary EIS settings. Customization options reside in either the System
page (GDU 1060) or the System menu (GDU 700( )).
SET FUEL FULL AND TAB CAPACITY
Specify estimated fuel full and tab values using the controls in the fuel computer.
SET ENGINE ADVISORIES
Specify engine advisory parameters and limit values.
8-40
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
CALIBRATE FUEL FLOW
NOTE
If the calculated adjustment factor exceeds the 10 percent fuel flow
calibration limit, contact your dealer for support.
Calibrate fuel flow using the controls provided in the fuel computer. Re-calibration is
recommended following the first flight or any time there is a significant difference
between the estimated remaining fuel quantity and the actual amount of fuel in the
tanks.
1. Fuel aircraft to a known level (i.e., the bottom of the tabs inside each fuel
filler port).
2. Tap EST Fuel Remaining and enter the amount of fuel on board.
NOTE: This value must be at least 5 liters (2 gallons) greater than the previous
estimated fuel on board amount.
3. Burn no less than 10 percent of usable fuel. Burning more than 10 percent will
yield a more accurate calibration.
4. Refuel to the previously entered level.
5. Tap EST Fuel Remaining and enter the amount of fuel on board.
6. Tap Calibrate FFlow.
7. Enter the amount of actual fuel used. Note the adjustment value.
8. Tap Update Calibration.
9. Confirm the request.
10.Acknowledge the pop-up message.
8.12.2
Preflight
ADD FUEL
Update the remaining fuel quantity whenever fuel is added to the aircraft.
1. Fuel the aircraft.
2. Enter the appropriate fuel amount using the fuel computer.
190-01717-10 Rev. H
Pilot’s Guide
8-41
Fuel & Engine Indicating System
8.12.3
En Route
MONITOR GAUGES
Monitor all dynamic gauges as limitations may change based on flight conditions.
MONITOR FOR ENGINE EXCEEDANCE ADVISORIES
Acknowledge any exceedance advisories occurring in flight and upon landing.
Always operate the aircraft in accordance with the POH.
8.12.4
Post Flight
RECORD AIRCRAFT LOG DATA
Document total engine and flight time. If configured, record the number of engine
and flight cycles. This information is necessary for logging and maintenance
purposes.
EXPORT DATA LOGS
Export flight data and engine exceedance logs to an SD card for later analysis.
8.13 Engine Advisories
Specify values at which the system will advise of certain engine parameters. The
system issues an advisory message when an engine gauge exceeds its specified value.
These messages are acknowledged in the same manner as system advisories.
Available selections are based on aircraft configuration.
• High/Low Battery Voltage
• Low Endurance [1]
• High/Low Bus Voltage
• Low Estimate Fuel Remaining [1]
• High/Low Oil Temperature
[1]
8-42
Actual amounts are based on fuel computer calculations and an active flight plan.
Pilot’s Guide
190-01717-10 Rev. H
Fuel & Engine Indicating System
Electrical
APPLICABLE TO PISTON &
TURBINE AIRCRAFT
8.14 Electrical Gauges
To accommodate more complex electrical
systems, electrical gauges allow up to six
parameters to display on three dedicated rows.
These may include: • main generator • standby
alternator • multiple buses • batteries
Markings and gauge titles are dependent upon
configuration.
190-01717-10 Rev. H
Pilot’s Guide
8-43
Fuel & Engine Indicating System
Points About Estimated Fuel Remaining Data
• Based on estimated fuel remaining value entered by the pilot
• Initial value automatically reduced based on current fuel flow
• Not limited to the capacity of the aircraft fuel system
• Preset keys for “full” and “tabs” aid in fuel data entry
Fuel range rings are a pilot-selectable map overlay indicating an estimate of
remaining flight distance based on fuel onboard, fuel consumption rates, and
current ground speed.
The map depicts two separate rings: an outer yellow ring displaying total
endurance range, and an inner dashed green ring displaying range to reserve
fuel. These rings offer the pilot additional situational awareness regarding fuel
remaining and endurance.
8.15.1
Preset Fuel Quantities
The fuel computer stores preset fuel amounts for estimated full and tab amounts. For
the operating limitations of a specific aircraft, consult the POH.
SELECTION
FUNCTION
Full
Sets the fuel remaining value to the specified full amount.
Tab
Sets the fuel remaining value to the specified tab amount.
Set Full/Tabs
Opens the Set Fuel Tabs menu. Select the appropriate data
entry key and enter the estimated fuel amounts. These values
vary according to aircraft type.
Fuel Full Capacity: Specify the tank full amount.
Fuel Tab Capacity: Specify a tank tab amount.
190-01717-10 Rev. H
Pilot’s Guide
8-45
Abnormal Operations
Backup Instruments
9.1
Display Backup
FUNCTIONAL LIMITATIONS
• Applicable to pilot side units only
• Only pilot or center units trigger backup mode when offline
• Not available in single TXi display installations
• Display backup mode supports a limited set of EIS gauges
Display backup mode
occurs under these
three conditions
• Loss of communication with
a GDU that displays EIS or
PFD data
When transitioning, priority is given to
primary gauges first. All menu items
and lean controls are disabled in this
mode. An optional external toggle
switch allows manual activation of
backup mode.
• Pilot activation through
on-screen selection or toggle
switch
• AHRS or ADC fault caused by
miscompare or missing data
(this only triggers backup
mode when the unit is
configured as a standby PFD)
TCAS II RAs
When a GDU 1060 is in display backup mode and providing PFD/MFD/EIS functions,
the format of the PFD narrows and the VSI is too small to depict RA bands.
To view TCAS II RAs, tap Full on the PFD to expand it to 80%.
9-2
Pilot’s Guide
190-01717-10 Rev. H
Abnormal Operations
TURBOPROP GAUGE AREAS
A
B
A
C
B
B
GDU 700P Gauges
9-8
GDU 1060
Gauge Strip
A
Gauges display with little or no change.
B
Gauges transfer depending on priority and open gauge slots.
C
Does not transfer to display backup.
Pilot’s Guide
190-01717-10 Rev. H
Abnormal Operations
AHRS/ADC SENSOR SELECTION ANNUNCIATIONS
ANNUNCIATION
DISPLAY
DESCRIPTION
SINGLE TXI PFD
“ON ADC 2” or
“ON AHRS 2”
(black text on white)
Pilot selected ADC 2 or
AHRS 2 as the sensor
source.
Pilot’s PFD
TWO TXI PFDS
“ON ADC 1” or
“ON AHRS 1”
(black text on yellow)
Standby PFD (pilot side)
Co-pilot’s PFD
“ON ADC 2” or
“ON AHRS 2”
(black text on yellow)
Pilot’s PFD
“ON ADC 2” or
“ON AHRS 2”
(black text on white)
Standby PFD (pilot side)
9.3.2
GDU is in display backup
mode.
Pilot changed sensor
source from the default
setting.
Sensor source is the
default setting (sensor 2).
AHRS Operating In Reversionary Mode
A failure of the air data input has no effect on AHRS output, while AHRS is operating
in normal mode. If the air data input fails, while the AHRS is operating in backup
No-GPS mode, PFD attitude and heading data are invalid.
9.3.3
GPS Failure
Two GPS inputs may be provided to the AHRS. If GPS information from one of the
inputs fails, the AHRS uses the remaining GPS input, and an advisory message
informs the pilot. If both GPS inputs fail, the AHRS continues to provide attitude and
heading information to the PFD as long as true airspeed data is available and valid.
190-01717-10 Rev. H
Pilot’s Guide
9-17
Abnormal Operations
9.5
Emergency Descent Mode
FEATURE REQUIREMENTS
• GDU 700( )/1060 PFD
• GFC 600 autopilot configured for EDM
FEATURE LIMITATIONS
• Availability dependent upon configuration
While EDM can assist in workload
reduction, it is the responsibility of
the pilot in command to know
and follow all published POH/AFM
normal and emergency
procedures.
9.5.1
GDU offers an Emergency Descent Mode
(EDM) that assists pilots of pressurized
aircraft in the event of cabin
depressurization.
EDM Activation
FEATURE REQUIREMENTS
• EDM must be armed in order for activation to occur
FEATURE LIMITATIONS
The manner in which activation occurs (manual or automatic) is dependent upon
configuration. For manual activation, GDU must be configured with an emergency
descent switch.
The system begins monitoring cabin pressure once EDM is armed.
EDM is considered armed when:
• Autopilot is active
• Aircraft is above 15,000 ft MSL
Once armed, activation may occur manually or automatically.
• Manual activation. Pilot triggers EDM by enabling the dedicated switch
(if configured).
• Automatic activation. If the aircraft experiences decompression and cabin
altitude increases beyond the threshold configured for the aircraft, the
system automatically triggers EDM.
190-01717-10 Rev. H
Pilot’s Guide
9-25
Abnormal Operations
Once triggered, a pop-up warning
displaying a timer appears on the PFD.
Emergency descent occurs once the
timer expires. This delay may range from
10 to 60 seconds. If manually activated,
you may skip the delay and active EDM
immediately by pressing the emergency
descent switch a second time.
During emergency descent:
• Autopilot enters HDG lateral mode
• Aural alert “Emergency Descent,
Emergency Descent” repeats every
20 seconds
• HDG bug on PFD sets to 90° to left
HDG = 90º left turn
• Simultaneously:
• Autopilot enters IAS mode
• PFD sets airspeed bug at VMO and
altitude preselect bug to 15,000 ft
IAS = VMO
15,000 ft
• Aircraft descends at VMO
• Autopilot captures altitude hold
mode at 15,000 ft
If available, the pilot may reduce power and deploy speed brakes to increase the
rate of descent and reduce the time needed to reach a lower altitude. Ensure
that all actions are in accordance with the POH.
9-26
Pilot’s Guide
190-01717-10 Rev. H
Abnormal Operations
EDM ACTIVE INDICATIONS
ANNUNCIATION
STATE
During EDM, airspeed and altitude
bugs are locked and unchangeable.
The active state annunciates in the
upper left corner of the PFD.
Active
Override or
Inhibit Mode
Selected Airspeed
Locked
EDM Active
Annunciation
Selected Altitude
Locked
Airspeed
Bug
Locked
Altitude
Bug
Locked
EDM Selected Data Lockout
9.5.2
EDM Inhibit
Tapping Inhibit EDM prevents automatic activation once the delay timer expires.
During inhibit mode:
• Automatic activation remains inhibited for a duration of 5 minutes
• An advisory message with timer counts down the remaining
minutes/seconds
• Inhibit state annunciation appears beneath the autopilot banner
Inhibit Advisory
190-01717-10 Rev. H
Inhibit Annunciation
Pilot’s Guide
9-27
Abnormal Operations
Once the 5 minute inhibit timer expires,
the same pop-up warning appears
regardless of whether EDM was
triggered automatically or by the pilot.
IF
THEN
Pilot triggers EDM and then chooses to
inhibit.
Automatic activation remains enabled.
EDM is triggered automatically and the
pilot chooses to inhibit.
Manual activation remains available for
as long as the aircraft is above 15,000 ft
and the autopilot is engaged. [1]
The 5 minute inhibit timer expires and
activation conditions are still present.
EDM automatically triggers again.
Pilot loses consciousness after enabling
the inhibit function.
Once the 5 minute inhibit timer expires,
EDM automatically activates in order to
bring the aircraft to a safer altitude.
[1]
9-28
Dependent upon configuration.
Pilot’s Guide
190-01717-10 Rev. H
Abnormal Operations
9.5.3
EDM Override
To deactivate EDM, disengage the autopilot. You may do this multiple ways:
On PFD: Tap Menu > Test > AP Disconnect.
On GMC 605: Push the AP bezel key.
On the yoke: Push the AP DISC button.
Activating autopilot will override EDM and return the autopilot to normal operation.
In this state:
• EDM does not automatically reactivate until arming conditions are cleared
• An advisory message alerts you to re-pressurize the cabin and reset the
autopilot
• Override state annunciation appears beneath the autopilot banner
Override Advisory
Override Annunciation
AUTO EDM
This key allows you to manually enable or disable automatic
activation. During system power up, this function is active by
default.
When the function is off, manual activation of EDM is still
available.
To reset EDM automatic activation following an override:
1. Descend below 15,000 ft.
2. Disengage and then re-engage the autopilot.
OR
1. Open the PFD Setup menu.
2. Toggle Auto EDM off and on.
Disabling the Auto EDM function may be desired if current cabin conditions are
causing erroneous activation of EDM. This can occur when:
• Cabin altitude is above the configured threshold
• GDU reports incorrect cabin altitude
190-01717-10 Rev. H
Pilot’s Guide
9-29
Abnormal Operations
9.5.4
EDM Active Discrete Output
Active Discrete Output &
Engine Torque Control
On the Socata TBM 850, the
discrete output may be connected
to the engine torque limiter. In
such case, turning on EDM would
energize the torque limiter circuit,
resulting in overtorque protection
while the aircraft is in emergency
descent mode.
PFD provides a discrete output that
allows synchronization of EDM with
other systems in the aircraft.
• When EDM is on, the discrete
output is active.
• When EDM is off, the output is
inactive.
Use of the active discrete output is
airframe and installation specific.
This capability is dependent upon
installation and should not be
relied upon to maintain the
engine within torque limits.
It is the full responsibility of the
pilot-in-command to operate the
aircraft and engine within the
limitations defined in the
POH/AFM.
9-30
Pilot’s Guide
190-01717-10 Rev. H
Was this manual useful for you? yes no
Thank you for your participation!

* Your assessment is very important for improving the work of artificial intelligence, which forms the content of this project

Download PDF

advertising