Garmin | G500 TXi | Garmin G500 TXi AFMS G500/G600 TXi Part 23 AML STC

Garmin G500 TXi AFMS G500/G600 TXi Part 23 AML STC
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LOG OF REVISIONS
Description
FAA Approval
Initial issue.
Erik Frisk
ODA STC Unit Administrator
Garmin International, Inc.
ODA-240087-CE
Date : 11/17/2017
5
Added new layout types
6
Added new layout types
11
Updated software version
number
Added section 2.30
discussing portable
electronic devices
Added section 2.31
discussing database updates
JR Brownell
ODA STC Unit Administrator
Garmin International, Inc.
ODA-240087-CE
Date : 08/16/2018
16
16
23
30
38
40
40
Added reference to G5
AFMS
Added section 3.2.9 for
Resetting a G5 standby
instrument.
Added section 4.2.4.5 for
discussing Garmin
Autopilots for selected
altitude
Added section 4.2.5.3
discussing Garmin
Autopilots for vertical
speed mode.
Added section 4.2.6 for
coupling to VNAV.
41
Added section 4.3 for Cold
Weather Compensation
procedures.
43
Included new layouts in
circuit breaker labels
44
Included FS510 for
database update methods.
48
Added FS510 for system
data logging functionality.
49
Included Baro sync
functionality in section 7.15
for interface with a G5 and
GAD 29.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page ii
52
54
55
3
Included requirement for
baro altitude for VNAV
functionality
Included description of
density altitude display in
section 7.15.14
Added checkbox for GFC
500/GFC 600 being
installed in the system.
56
Added description for GFC
500 autopilots not capturing
CDI preview needles.
57
Added reference to G5 and
GFC 500 in 7.16.3.
61
Added description of CDI
selection on G5.
64
Included description of a
selectable CHT gauge in
section 7.19.3.
67
Included description of
Flight Stream 510 LRU.
68
Added section 7.21 for
visual reporting points
68
Added section 7.22 to
describe altitudes provided
by the database.
1
Added GEA 71B references
2
Additional OAT text
3-4
Updated diagrams
5
New abbreviations added
7
Formatting
11
Additional turboprop
information in Section 2.24
14
Turboprop gauge types
added
Updated MFD logic in
Section 2.34
15
See page i
18
Added HDG monitor to
Section 3.1.4
26
Added EDM procedures as
Section 3.2.10
27
Added EDM annunciation
to Section 3.3.1
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page iii
29
Added EDM annunciation
to Section 3.3.2
30
Added EDM annunciation
to Section 3.3.3
New Section 3.4
40
Added GEA 71B references
43
New turboprop modes
shown in Section 7.7
47
Added HDG monitor to
Section 7.15.1
Updated standard rate turn
text in Section 7.15.2
49
51
52
56
57
62-68
68
Note added to Section
7.15.3
Preview needle text added
to Section 7.15.7
Added preview needle to
table 1
Updated FD text in Section
7.16.2
New ARC VSI text for
Section 7.16.5
Additional turboprop gauge
information added to
Section 7.19
New Section 7.23
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page iv
TABLE OF CONTENTS
GENERAL ................................................................................... 1
GDU 1060 ............................................................................................ 1
GDU 700P ............................................................................................ 2
GDU 700L ........................................................................................... 2
AHRS / ADC........................................................................................ 2
OAT PROBES ........................................................................................ 2
STANDBY INSTRUMENTS OR STANDBY PFD ......................................... 2
BACKUP BATTERY ................................................................................ 2
PFD CONTROLLER ................................................................................ 3
BLOCK DIAGRAMS ................................................................................ 3
DEFINITIONS ......................................................................................... 5
LIMITATIONS ........................................................................... 6
MINIMUM SOFTWARE VERSION ............................................................ 6
DATABASES .......................................................................................... 6
AHRS OPERATIONAL AREA ................................................................. 6
MAGNETIC VARIATION OPERATIONAL AREA ....................................... 6
NAVIGATION ANGLE ............................................................................ 6
ADAHRS AND AHRS NORMAL OPERATING MODE............................. 7
AEROBATIC MANEUVERS ..................................................................... 7
ELECTRONIC STANDBY INSTRUMENT POWER ....................................... 7
STANDBY FLIGHT INSTRUMENTS .......................................................... 7
SENSOR SELECTION .............................................................................. 8
SYNTHETIC VISION ............................................................................... 8
MOVING MAPS ..................................................................................... 8
PFD 2 FLIGHT DIRECTOR ..................................................................... 8
AUTOPILOT DISCONNECT ..................................................................... 9
TERRAIN DISPLAY ................................................................................ 9
TERRAIN/TAWS ALERTS ..................................................................... 9
DATALINK PRODUCTS (SIRIUSXM, FIS-B, AND CONNEXT) ................. 9
TRAFFIC DISPLAY ................................................................................. 9
WEATHER RADAR............................................................................... 10
STORMSCOPE® DISPLAY ..................................................................... 10
PFD/EIS DISPLAY BACKUP MODE ..................................................... 10
SURFACE OPERATIONS ....................................................................... 10
TYPE RATINGS .................................................................................... 10
FUEL FLOW......................................................................................... 11
FUEL COMPUTER ................................................................................ 11
GLOVE USAGE .................................................................................... 11
BACKUP GPS ...................................................................................... 11
SERVICE REQUIRED ............................................................................ 11
POWERPLANT GAUGE MARKINGS....................................................... 11
PORTABLE ELECTRONIC DEVICES....................................................... 11
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page v
DATABASE UPDATES .......................................................................... 12
KINDS OF OPERATIONS ....................................................................... 12
PLACARDS .......................................................................................... 15
MFD FLIGHT PLAN DISPLAY .............................................................. 15
EMERGENCY PROCEDURES .............................................. 16
EMERGENCY PROCEDURES ................................................................. 16
ABNORMAL PROCEDURES................................................................... 23
WARNINGS, CAUTIONS, AND ADVISORIES .................................... 27
ENGINE EXCEEDANCES ....................................................................... 30
NORMAL PROCEDURES ...................................................... 31
BEFORE TAKEOFF ............................................................................... 31
AUTOPILOT OPERATION ..................................................................... 32
COLD WEATHER COMPENSATION ....................................................... 36
PERFORMANCE ..................................................................... 38
WEIGHT AND BALANCE ..................................................... 38
SYSTEM DESCRIPTION ....................................................... 39
7.20
CONTROLS OVERVIEW ........................................................................ 39
DISPLAY BRIGHTNESS ........................................................................ 40
SYSTEM POWER SOURCES .................................................................. 40
SYSTEM STATUS ................................................................................. 41
DATABASES ........................................................................................ 41
CREW PROFILES .................................................................................. 42
DISPLAY BACKUP MODES .................................................................. 43
INTEGRATED STANDBY SYSTEM ......................................................... 43
ELECTRIC STANDBY ATTITUDE GYRO ................................................ 44
BACKUP GPS ...................................................................................... 44
AIRCRAFT AUDIO INTERFACE ............................................................. 45
ADVISORY NOTIFICATIONS ................................................................. 45
SYSTEM SETTINGS .............................................................................. 45
SYSTEM DATA LOGGING .................................................................... 45
PRIMARY FLIGHT DISPLAY ................................................................. 46
AUTOPILOT INTERFACES..................................................................... 54
MFD FUNCTIONS................................................................................ 57
TERRAIN AWARENESS AND ALERTING ............................................... 59
ENGINE INDICATING SYSTEM ............................................................. 62
FLIGHT STREAM 510 (OPTIONAL) ....................................................... 68
EUROPEAN VISUAL REPORTING POINTS ............................................. 68
DATABASE PROVIDED ALTITUDES...................................................... 68
CYCLE COUNTER / LANDINGS COUNTER ............................................ 68
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page vi
GENERAL
The G500/G600 TXi system is a display and sensor system which provides one
or more of the following functions:
•
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 the flight
•
Engine Indicating System (EIS) – Provides engine and airframe
operating parameters to the pilot
The G500/G600 TXi system consists of one or more of the following displays:
•
GDU 1060 – 10” PFD/MFD (optional EIS)
•
GDU 700P – 7” Portrait PFD, MFD, EIS, or MFD/EIS (single engine
only)
•
GDU 700L – 7” Landscape PFD, EIS, or MFD/EIS (single engine
only)
PFD functions are supported by interfaced AHRS/ADC (either integrated or
external) and at least one GPS navigator. An optional GAD 43/43e adapter
provides additional functions such as third-party autopilot and analog interfaces.
An optional GCU 485 controller provides additional dedicated controls for PFD
operation. Other PFD interfaces may include VHF navigation radios, radar
altimeter, ADF, and DME.
EIS functions are supported by either a GEA 110 engine/airframe unit, or a GEA
71B Enhanced unit, along with sensors to measure engine parameters.
MFD functions are supported by GPS navigator interfaces and a variety of other
optional interfaces such as datalinks, traffic systems, Stormscope®, and weather
radar.
Although intuitive and user friendly, the system requires a reasonable degree of
familiarity to avoid becoming too engrossed at the expense of basic instrument
flying in IMC and basic see-and-avoid procedures in VMC. Pilot workload will
be higher for pilots with limited familiarity in using the unit in an IFR
environment, particularly without the autopilot engaged. Garmin provides a
detailed Pilot’s Guide and a tablet trainer app. Pilots should take full advantage
of these tools to enhance their familiarity with the system.
GDU 1060
The GDU 1060 is a 10” PFD/MFD display, with an optional EIS function. Each
function is segregated into a portion of the display. The MFD can be selectively
hidden/shown with the PFD expanding into the MFD space when the MFD is
hidden. If installed the EIS function occupies on the left or right edge of the
display and is always shown.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 1 of 68
GDU 700P
The GDU 700P is a 7” portrait display which provides a single PFD, MFD, EIS,
or MFD/EIS function. In some installations, a 700P display may provide
backup PFD or EIS information in the event that the primary PFD or EIS display
fails or malfunctions.
GDU 700L
The GDU 700L is a 7” landscape PFD, MFD/EIS, or EIS display.
AHRS / ADC
The AHRS and ADC sense aircraft attitude and air data to be used for display to
the pilot and for use by other installed systems. The AHRS and ADC can be
either remote-mounted or integrated into the display.
All AHRS units have a magnetometer interface for determining magnetic
heading. The AHRS also requires GPS and airspeed inputs for aiding the
system.
OAT Probes
All ADC units have an OAT probe interface for measuring outside air
temperature. Static and ISA relative temperatures can be displayed on the GDU
in those installations. In EIS-only installations, the OAT can be interfaced with
the system directly and will only display Total Air Temperature on the EIS
display.
Standby Instruments or Standby PFD
Except for installations that are limited to VFR, PFD installations require
standby attitude, altitude, and airspeed instruments. Several types of standby
instruments are acceptable, including individual analog instruments and certain
electronic standby indicators.
An integrated standby system configuration is also available, which consists of
two GDU 700P 7” portrait displays, each with separate AHRS / ADC
functionality. One display serves as the PFD, and the other display can be either
an EIS, MFD, or MFD/EIS display. The EIS/MFD provides standby PFD
functionality which is displayed automatically when faults are detected or upon
manual command. A backup battery provides emergency power to the PFD and
sensors in the event of a failure of aircraft power.
Backup Battery
An optional GBB 54 backup battery can be installed to provide emergency
power to a GDU 700P/L display. The backup battery is mounted remotely and
provides power to the GDU when aircraft power is unavailable. The GDU, in
turn, may be equipped with an integrated ADAHRS and can provide power to
the EIS sensors for one engine. This allows for continued PFD and EIS
functionality when aircraft electrical power is lost.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 2 of 68
PFD Controller
An optional GCU 485 PFD controller may be installed to provide dedicated PFD
controls. Although control of all 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
buttons are also provided for CDI source selection, GPSS emulation mode,
altitude capture arming, and vertical speed mode engagement.
Block Diagrams
The following diagrams illustrate the typical TXi installation and integrated
standby configuration. Due to the large scalability of the TXi system, it is not
practical to represent every possible installation combination.
Figure 1 TXi System Overview
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 3 of 68
Figure 2 Typical Integrated Standby Configuration
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 4 of 68
Definitions
ADAHRS: Air Data and Attitude Heading Reference System
ADC:
Air Data Computer
AHRS:
Attitude & Heading Reference System
CDI:
Course Deviation Indicator
CRS:
Course
EDM:
Emergency Descent Mode
EIS:
Engine Indicating System
FD:
Flight Director
FLTA:
Forward-looking Terrain Alerting
FS510:
Flight Stream 510
GPSS:
GPS Steering
HDG:
Heading
HSI:
Horizontal Situation Indicator
IFR:
Instrument Flight Rules
IMC:
Instrument Meteorological Conditions
LOI:
Loss of Integrity
MFD:
Multifunction Display
PED:
Portable Electronic Device
PFD:
Primary Flight Display
SBAS:
Space-based Augmentation System
SVT:
Synthetic Vision Technology
TAWS:
Terrain Awareness and Warning System (a TSO-C151b function)
TIS-A:
Traffic Information Service (Addressed).
TIS-B:
Traffic Information Service (Broadcast)
VFR:
Visual Flight Rules
VMC:
Visual Meteorological Conditions
VNAV:
Vertical Navigation
VS:
Vertical Speed
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 5 of 68
LIMITATIONS
Minimum Software Version
The following or later software versions must be installed for this AFMS
revision to be applicable to the installation:
Component
Identification
Software Version
GDU
PFD, MFD, and/or EIS
3.01
GEA 71B
Engine Adapter
2.20
NOTE
This section is not intended to be a comprehensive list of
approved software. It is intended to provide a means to
determine if this AFMS revision is applicable to the
software that is installed in the aircraft. Do not use this
AFMS revision if the installation has a software version
less than that shown in the table above.
Databases
Databases identified as intended for helicopters must not be used. These
databases are identified by the word “HELI” or “HELICOPTER” in their title,
as displayed on the database status page.
AHRS Operational Area
IFR Operations are prohibited north of 72°N and south of 70°S latitudes. In
addition, IFR operations are prohibited in the following four regions:
1) North of 65° North latitude between longitude 75° W and 120° W
2) North of 70° North latitude between longitude 70° W and 128° W
3) North of 70° North latitude between longitude 85° E and 114° E
4) South of 55° South latitude between longitude 120° E and 165° E
Loss of attitude and heading may occur near the poles.
Magnetic Variation Operational Area
IFR operations are prohibited in areas where the magnetic variation is greater
than 99.9 degrees East or West.
Navigation Angle
The Magnetic/True Navigation Angle (as selected on the System Units page)
must match the navigation angle selected on all interfaced GPS/SBAS
navigators.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 6 of 68
ADAHRS and AHRS Normal Operating Mode
The Attitude and Heading Reference System integrity monitoring function
requires external GPS and Air Data to be provided to the AHRS. An ADAHRS
receives Air Data internally and therefore only requires external GPS.
NOTE
Attitude will remain valid if either GPS or Air Data is lost.
Flight in IMC is not authorized unless the ADAHRS or
AHRS is receiving valid GPS and valid Air Data. The
G500/G600 TXi system monitors these integrity systems
automatically and will advise the pilot when the ADAHRS
or AHRS is not receiving GPS or Air Data.
NOTE
In dual GPS installations, only one GPS needs to be
available to the ADAHRS or AHRS for IFR flight.
Aerobatic Maneuvers
Do not conduct aerobatic maneuvers if uninterrupted attitude information is
required on the PFD.
Electronic Standby Instrument Power
The independent power source for electronic standby instrument(s) must be
verified to be operational before flight, or the electronic standby(s) must be
considered inoperative. For the verification procedure, refer to the approved
Airplane Flight Manual and/or Instructions for Continued Airworthiness for the
independent power source.
Standby Flight Instruments
 This installation uses separate standby instruments (other than a GDU) or
does not require standby instruments (aircraft limited to VFR).
 This installation uses the Integrated Standby System with dual GDU 700P
displays for the primary and standby flight instruments. IFR flight must
not be initiated unless the system check in Section 4.1.1 is completed
successfully to verify the following:
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 7 of 68
•
The backup battery is operational and sufficiently charged (no amber or
red battery icons on the pilot’s PFD)
•
Attitude, heading, altitude, and airspeed from AHRS/ADC 1 are
operational on the pilot’s PFD with no warnings, cautions, or advisories
present
•
Selecting the display backup switch to ON causes the standby PFD to
display attitude, heading, altitude, and airspeed with no warnings,
cautions, or advisories present
WARNING
Failure to observe to these limitations may result in the loss
of all attitude or air data or both, resulting in loss of aircraft
control.
Sensor Selection
Do not select or operate on cross-side AHRS or ADC sensors (e.g. PFD 1 using
AHRS/ADC 2), unless directed to do so as part of an emergency or abnormal
procedure in this AFMS.
CAUTION
Changing the AHRS/ADC sensor source when a white
ATTITUDE/IAS/ALT annunciation is displayed on the
PFD will result in the selection of an inoperative sensor
source and subsequent loss of information. Operating both
PFDs on the same sensor source will inhibit the
AHRS/ADC comparison monitor.
Synthetic Vision
The synthetic vision presentation must not be used as the sole reference for
aircraft control (without reference to the primary flight instruments).
The synthetic vision presentation must not be used as the sole reference for
navigation or obstacle/terrain/traffic avoidance.
If the installed TAWS or Terrain Alerting system is inoperative, the synthetic
vision display on the PFD must be selected off.
Moving Maps
Moving map displays (ownship position relative to map features) must not be
used as the primary or sole means of navigation or course guidance.
PFD 2 Flight Director
The flight director on PFD 2 (if installed) is a duplicate of the flight director
shown on PFD 1 (i.e. the flight director is based on the mode references
displayed on PFD 1). When utilizing the flight director on PFD 2, the heading,
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 8 of 68
CDI source, altitude, or other information affecting the flight director must be
cross-checked and verified between the two PFDs.
Autopilot Disconnect
The “AP DISC” button in the PFD Test Menu (if present for the installation)
must disconnect the autopilot when pressed. If the button does not disconnect
the autopilot when pressed, then the autopilot must not be used.
Terrain Display
Maneuvers and navigation must not be based solely on the display of terrain,
obstacles, or wires on the moving map terrain displays.
Terrain/TAWS Alerts
Terrain/TAWS alerts must be inhibited when landing at an airport that is not in
the airport database.
Datalink Products (SiriusXM, FIS-B, and Connext)
Do not use datalink weather information for maneuvering in, near, or around
areas of hazardous weather. Information provided by datalink weather products
may not accurately depict current weather conditions.
Do not use the indicated datalink weather product age to determine the age of
the weather information shown by the datalink weather product. Due to time
delays inherent in gathering and processing weather data for datalink
transmission, the weather information shown by the datalink weather product
may be significantly older than the indicated weather product age.
Do not rely solely upon datalink services to provide Temporary Flight
Restriction (TFR) or Notice to Airmen (NOTAM) information. Not all TFRs
and NOTAMS may be depicted.
Traffic Display
The display of traffic is intended as an aid to visual acquisition and must not be
used as the sole basis for aircraft maneuvering.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 9 of 68
Weather Radar
Do not operate in the vicinity of refueling operations.
Do not operate while personnel are in the vicinity (approximately 20 feet) of the
radar sweep area.
WARNING
An operating radar generates microwave radiation and
improper use, or exposure, may cause serious bodily
injury. DO NOT OPERATE THE RADAR EQUIPMENT
UNTIL YOU HAVE READ AND CAREFULLY
FOLLOWED THE SAFETY PRECAUTIONS AND
INSTRUCTIONS IN THE RADAR USER MANUAL.
Stormscope® Display
Stormscope® lightning information displayed is limited to supplemental use
only. The use of the Stormscope® lightning data on the display for hazardous
weather (thunderstorm) penetration is prohibited. Stormscope® lightning data on
the display is intended only as an aid to enhance situational awareness of
hazardous weather, not penetration. It is the flight crew’s responsibility to avoid
hazardous weather using official weather data sources.
PFD/EIS Display Backup Mode
When a 7” display is operating in PFD/EIS display backup mode, the fuel
selector must be positioned to use fuel from a tank for which fuel quantity is
indicated unless it is deemed operationally necessary by the pilot to select a tank
for which quantity is not indicated.
NOTE
In some installations, auxiliary or tip fuel quantity gauges
may not be available in PFD/EIS composite display backup
mode.
Surface Operations
SafeTaxi or Chartview functions shall not be used as the sole basis for ground
maneuvering. SafeTaxi and Chartview functions do not comply with the
requirements of AC 20-159 and are not qualified to be used as an airport moving
map display (AMMD). SafeTaxi and Chartview use is limited to airport surface
orientation to improve flight crew situational awareness during ground
operations.
Type Ratings
Unless otherwise authorized by this section, operations are prohibited in aircraft
that require a type rating.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 10 of 68
Fuel Flow
In some turboprop installations, fuel flow values may be erratic or erroneous
before fuel is introduced into the system during engine starts. Once fuel is
present in the system, the fuel flow values are accurate. The pilot should
disregard fuel flow indications during engine start before fuel is introduced in
these aircraft.
Fuel flow values may be in error by as much as 15% if the K factor calibration is
improperly set. Do not depend solely on the fuel flow indication to determine
fuel used, fuel remaining, or fuel reserves.
Fuel Computer
The fuel computer functions must not be used as the primary means of
determining the quantity of fuel in the tanks. The aircraft fuel quantity gauge(s)
are the primary means of determining fuel quantity.
Glove Usage
No device may be used to cover fingers used to operate the TXi display unless
the Glove Qualification Procedure located in the Pilot’s Guide has been
successfully completed. The Glove Qualification Procedure must be
successfully completed for each combination of pilot, glove, and GDU
1060/700P/700L that is intended to be used.
Backup GPS
The Backup GPS is an emergency positional awareness function and must not
be used as a normal means of navigation.
Service Required
It is prohibited to initiate flight when a “Service Required” advisory is present
on the PFD, MFD, or EIS display.
Powerplant Gauge Markings
Aircraft that were previously equipped with a fuel flow gauge which measured
metered fuel pressure may have this gauge replaced by a gauge which measures
fuel flow directly. When these gauges are replaced in accordance with this STC,
the fuel pressure and fuel flow markings on such gauges are replaced by
equivalent fuel flow markings.
Portable Electronic Devices
This STC does not relieve the operator from complying with the requirements of
91.21 or any other operational regulation regarding portable electronic devices.
The Flight Stream interface and data provided to a portable electronic device is
not approved to replace any aircraft display equipment, including navigation or
traffic/weather display equipment.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 11 of 68
Database Updates
Database updates via MMC / SD card or Flight Stream wireless transfers must
be done while the aircraft is on the ground and stationary. In-flight database
transfers or updates are prohibited in flight unless part of the Database SYNC
function that occurs in the background to move databases from one LRU to
another.
Kinds of Operations
Unless placarded as limited to VFR only operations, equipment installed in a
certified aircraft is approved for Day and Night / VFR and IFR operations in
accordance with 14 Code of Federal Regulations Part 91, Part 121, and Part 135
when appropriately maintained.
The tables below list the minimum fully functional equipment required for
flight.
The following note applies where indicated:
For VFR operations under 14 CFR Part 91, the aircraft
must have at least one source of altitude and airspeed
information. This may be from either the PFD or the
standby instruments. (i.e. all “1a” items or all “1b” items
from the tables above)
Primary Flight Display (Non-Integrated Standby):
OR
Equipment
Number
installed
VFR
IFR
Primary Flight Display
1 or 2
1
1
Garmin GPS/SBAS Navigator (interfaced to a
PFD)
1 or 2
-
1
Air data and Attitude / Heading Unit (ADAHRS)
1 or 2
1a*
1
Attitude / Heading Unit (AHRS)
1 or 2
-
1
Air data computer (ADC)
1 or 2
1a*
1
Magnetometer (GMU)
1 or 2
-
1
Standby Attitude Indicator
1
-
1
Standby Airspeed Indicator
1
1b
1
Standby Altimeter
1
1b
1
Non-stabilized Magnetic Compass
1
1
1
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 12 of 68
Primary Flight Display (Integrated Standby):
Equipment
Number
installed
VFR
IFR
1 or 2
1a*
1
Pilot MFD or EIS Display providing backup PFD
functions
1
1b
1
Garmin GPS/SBAS Navigator (interfaced to a
PFD)
1 or 2
-
1
Air data and Attitude / Heading Unit (ADAHRS)
2
1a*
2
Attitude / Heading Unit (AHRS)
2
-
2
Air data computer (ADC)
2
1a*
2
Magnetometer (GMU)
2
-
2
Non-stabilized Magnetic Compass
1
1
1
PFD Backup Battery
1
1
Display Backup Switch
1
1
OR
Pilot Primary Flight Display
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 13 of 68
Engine Indicating System (if installed):
Equipment
EIS Display
Engine Adaptor Unit (GEA 110 or 71B)
Number
installed
Req’d
1
1
1 or 2 *
All
* GEA 71B is used for turboprop installations and is limited to a single adapter
For piston engine aircraft, the following engine indications must be functional
on the EIS display (if these gauges are present on the EIS display as installed):
•
•
•
•
•
•
•
Tachometer
Manifold Pressure
Propeller RPM
Oil Pressure
Oil Temperature
Fuel Quantity
Any additional engine instruments required by the aircraft Kinds Of
Equipment list as listed in the Aircraft Flight Manual.
For turboprop powered aircraft, the following engine indications must be
functional on the EIS display (if these gauges are present on the EIS display as
installed):
•
•
•
•
•
•
•
•
Torque
Propeller RPM
Gas Generator RPM
Engine Temperature
Fuel Flow
Oil Pressure
Oil Temperature
Any additional engine instruments required by the aircraft Kinds Of
Equipment list as listed in the Aircraft Flight Manual.
 This installation has the EIS display within the primary field of view and
does not require a remote EIS annunciator.
 This installation does not have the EIS display within the primary field of
view and the following limitations apply:
OR
Equipment
Number
installed
Req’d
EIS Annunciator
0 or 1
All
PFD with EIS Annunciator
0 or 1
All
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 14 of 68
Placards
2.33.1 (Removed)
2.33.2 KFC 275/325 Altitude Preselect
When the altitude preselect option is installed with KFC 275/325 autopilots,
SOFT RIDE (SR) mode must be disengaged when altitude capture mode is
engaged (green ALTC). The following placard must be installed near the
autopilot mode controller or above PFD 1:
“DISENGAGE SOFT RIDE DURING ALTITUDE CAPTURE (ALTC)”
2.33.3 Installations Limited to VFR
 This installation is not limited to VFR.
 This installation is limited to VFR and the following placard is required:
“AIRCRAFT LIMITED TO VFR”
MFD Flight Plan Display
When an MFD is associated with a specific PFD (e.g.- The co-pilot’s side has a
700P PFD and a 700P MFD), the flight plan displayed on the MFD is from the
navigation source selected on the PFD CDI. If the MFD is not associated with a
specific pilot position (e.g.- The MFD is a stand-alone center MFD) the flight
plan displayed is from the navigation source selected on the pilot’s PFD CDI.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 15 of 68
EMERGENCY PROCEDURES
Emergency Procedures
3.1.1 PFD Failure
PFD failure is indicated by the loss of displayed information on the PFD,
including a blank, frozen, or unresponsive display.
1.
Use standby flight instruments for attitude, airspeed, altitude, and
heading reference.
2.
Refer directly to the navigation source for navigation information (such
as GPS).
3.
Seek VFR conditions or land as soon as practical.
If autopilot is engaged:
4.
Verify autopilot mode and cross check against standby flight and
navigation data.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 16 of 68
3.1.2 AHRS Failure
AHRS failure is indicated by the removal of the attitude/heading information and
a red X on the PFD. Rate-of-turn information (heading trend vector) will not be
available. A heading failure will also occur as described in Section 3.2.1.
1.
Use Standby Attitude Indicator.
2.
Seek VFR conditions or land as soon as practical.
If multiple AHRS sources are installed:
3.
Select operative AHRS using the PFD Sensors menu
NOTE
If the AHRS is restarting in flight without an operative
GPS navigator, attempt to minimize maneuvering and
turbulence during and after the restart process. Without an
operative GPS navigator, excessive maneuvering or
turbulence may prevent the AHRS from completing
alignment properly. Continue to minimize maneuvering
and seek smooth air for the first 5 minutes after the attitude
becomes valid following the in-air alignment restart. If
maneuvering or turbulence cannot be avoided, carefully
cross-check the AHRS for correctness against other flight
instruments.
3.1.3 ADC Failure
ADC failure is indicated by:
•
•
•
Red X over the airspeed and altitude tapes
Yellow X over the vertical speed tape
Dashed out TAS and OAT fields
Wind calculations will also be unavailable. If valid GPS data is available, the
PFD will automatically revert to display GPS calculated altitude relative to
mean sea level. GPS altitude is displayed at the top of the altitude tape.
1.
Use Standby Airspeed Indicator and Altimeter
2.
Seek VFR conditions or land as soon as practical
If multiple ADC sources are installed:
3.
Select operative ADC using the PFD Sensors menu
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 17 of 68
3.1.4 ATTITUDE, ALT, HDG, or IAS monitor CAUTION
If an ATTITUDE, ALT, HDG, or IAS monitor CAUTION is displayed in amber
on the attitude display or airspeed/altitude tape:
Figure 3- Miscompare Flags
1.
Cross check flight instruments against all available information to
determine which indications are correct
2.
Seek VFR conditions or land as soon as practical
NOTE
White ATTITUDE/ALT/HDG/IAS annunciations indicate
that the other AHRS/ADC source is not available.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 18 of 68
3.1.5 Aircraft Electrical System Failure
In the event of a total loss of aircraft electrical power, the G500/G600 TXi
system will cease to operate, except for displays which are equipped with an
optional backup battery. Refer to procedures for failure of affected equipment
and operation on backup battery. For power loss effects on the G5 standby, see
the AFMS for the G5, 190-01112-13.
3.1.6 Operation on Backup Battery (if installed)
Displays equipped with a backup battery will continue to operate after a loss of
aircraft electrical power. Twin engine aircraft equipped with EIS will lose right
engine gauges, fuel quantity from the right tank(s), and amps and volts from the
right side. Operation on battery power is indicated by the presence of a battery
icon on the affected display and a system advisory. A minimum of 30 minutes
of operation on the backup battery is provided.
1.
Seek VFR conditions or land as soon as possible.
3.1.7 Display Backup Malfunction
Display backup malfunction is indicated by repeated changes to the display
layout (e.g. display changes back and forth between normal and backup mode).
1.
Select Display Backup switch to ON to force all displays into backup
mode.
3.1.8 Backup Battery Malfunction
A malfunction of the backup battery is indicated by the following indication:
.
1.
Seek VFR conditions or land as soon as practical.
3.1.9 EIS Failure
EIS failure is indicated by the loss of displayed information on the EIS,
including a blank, frozen, or unresponsive display of EIS parameters.
1.
Position engine controls to ensure operation within engine limitations.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 19 of 68
3.1.10 Loss of Electrical Power to 3-inch Electric Standby Attitude
Indicator (flashing amber STBY PWR light) (MidContinent 4300 Series)
When a 3-inch electric standby attitude indicator is installed, loss of primary
electrical power to the attitude indicator is annunciated by a flashing amber light
on the indicator. The attitude indicator is operating on backup battery power,
and pilot action is required for the gyro to continue operating.
1.
Press STBY PWR button on the indicator one time.
2.
Verify that the flashing amber light extinguishes.
3.
Verify that the red gyro warning flag is not displayed.
4.
Seek visual meteorological conditions (VMC) or land as soon as
practical (operation of standby attitude indicator is limited by battery
life).
WARNING
Do not press the STBY PWR button a second time after
the flashing amber light extinguishes. This will turn off the
backup battery and the red gyro warning flag will be
displayed. If the STBY PWR button is inadvertently
pressed and the red gyro warning flag is displayed, press
the STBY PWR button again to return to battery power
operation (red gyro warning flag should not be displayed).
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 20 of 68
3.1.11 Loss of Electrical Power to 2-inch Electric Standby Attitude
Indicator (flashing or steady amber STBY text) (MidContinent 4200 Series)
When a 2-inch electric standby attitude indicator is installed, loss of primary
electrical power to the attitude indicator is annunciated by amber STBY text on
the Annunciation Control Unit. The attitude indicator is operating on backup
battery power, and pilot action may be required for the gyro to continue
operating.
If the amber STBY text is flashing (manual operation):
1.
Press the STBY PWR button one time.
2.
Verify that the amber STBY text is steadily illuminated.
3.
Verify that the red gyro warning flag is not displayed.
4.
Seek visual meteorological conditions (VMC) or land as soon
as practical (operation of standby attitude indicator is limited
by battery life).
If the amber STBY text is steadily illuminated (automatic operation):
1.
Verify that the red gyro warning flag is not displayed.
2.
Seek visual meteorological conditions (VMC) or land as soon
as practical (operation of standby attitude indicator is limited
by battery life).
WARNING
Do not press the STBY PWR button when the amber
STBY text is steadily illuminated. This will turn off the
backup battery and the red gyro warning flag will be
displayed. If the STBY PWR button is inadvertently
pressed and the red gyro warning flag is displayed, press
the STBY PWR button again to return to battery power
operation (red gyro warning flag should not be displayed).
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 21 of 68
3.1.12 TAWS/Terrain Alerts
Aural Alert
Visual Alert
Action
Disconnect autopilot and initiate
maximum performance climb
(maximum takeoff power and
best angle of climb airspeed)
“Terrain, Terrain
Pull up, Pull up”
-OR“Obstacle, Obstacle
Pull up, Pull up”
-OR“Wire, Wire
-OR-
Pull up, Pull up”
-OR“Warning, Terrain,
Terrain”
-OR-
NOTE: Only the climb maneuver
is recommended, unless
operating in VMC or it is
determined, based on all
available information, that
turning in addition climbing is
the safest course of action.
-OR-
-OR“Warning, Obstacle,
Obstacle”
-OR“Warning, Wire, Wire”
-OR“Pull up”
“CAUTION, Terrain”
-OR-
-OR-
“CAUTION, Obstacle”
-OR-
-OR-
“CAUTION, Wire”
“Too low, Terrain”
Take corrective action until the
alert ceases. Using all available
information to determine the
appropriate action, alter the flight
path away from the threat by
stopping descent, climbing,
and/or turning.
Establish climb to the minimum
altitude for present
position/procedure
“Sink Rate”
Decrease rate of descent
“Don’t sink”
Establish a positive rate of climb
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 22 of 68
Abnormal Procedures
3.2.1 Heading Failure
Heading failure is indicated by removal of the digital magnetic heading display
on the HSI and a red
annunciation.
If GPS ground track is available, it will automatically be displayed in place of
heading. The heading bug and course pointer will continue to function normally,
using GPS ground track as a reference instead of magnetic heading.
If GPS track is not available:
1.
Use standby compass for heading reference.
NOTE
Without magnetic heading or GPS track, the CDI provides
no directional information. Only course deviation
information is presented, and the orientation of the CDI is
based on the selected course, regardless of aircraft heading.
Course deviation indications will behave like a traditional
CDI. VOR deviations will be relative to the selected course
with a TO/FROM indication. Localizer deviations will not
be affected by the selected course, and reverse sensing will
occur when tracking inbound on a localizer back course.
3.2.2 Display Fan Failure
Display fan failure is indicated by an amber
annunciation on the
affected display. Without fan cooling, the affected display will overheat and
shutdown.
1.
Prepare for loss of the affected display.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 23 of 68
3.2.3 GPS Data Failure
GPS data failure may be indicated by any or all of the following:
•
•
•
•
•
Loss of GPS course deviation information on HSI
Amber “LOI” text on the PFD
Amber “DG” text on the PFD
Amber “NO GPS POSITION” text on the moving map
Loss of waypoint bearing/distance information
1.
Select alternate GPS source, if available, by pressing “CDI” button on
PFD.
If alternate GPS source is not available:
2.
Select alternate navigation source (VOR, LOC, or ADF, if
available) or refer directly to external navigation data.
3.2.4 Navigation Data Failure (VOR/LOC/GS/ADF)
Navigation data failure may be indicated by any or all of the following:
•
•
•
Loss of course deviation information on PFD
Loss of glideslope/glidepath information on PFD
Loss of bearing pointer on HSI
1.
Select alternate navigation source or refer directly to external
navigation data.
3.2.5 Synthetic Vision Malfunction
If the synthetic vision depiction is known or suspected to be inaccurate or
malfunctioning:
1.
Turn off synthetic terrain using the PFD Terrain/SVT menu.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 24 of 68
3.2.6 Electrical Load Shedding
The following equipment is considered non-essential. If it becomes necessary to
reduce electrical load (for example, during loss of generators or alternators),
power to these units may be removed in the order listed.
1.
PFD ADAPTER circuit breaker(s) [if installed] – PULL
NOTE
When the PFD ADAPTER is shed, this may result in the
loss of autopilot function and/or loss of some navigation
data on the PFD (VOR/LOC, ADF, DME, radar altimeter).
2.
PFD CTLR circuit breaker(s) [if installed] – PULL
NOTE
Any non-required displays on the co-pilot side may also be
powered off.
3.2.7 AHRS ALIGN
If an “AHRS ALIGN / Keep Wings Level” annunciation is displayed on the
attitude indicator in flight, limit aircraft operation to:
•
•
•
±10º bank
±5º pitch
200 KTAS or less
CAUTION
Exceeding these values may delay or prevent AHRS
alignment.
3.2.8 EIS Display Parameter Failure
Indicated by individual parameters having a red or yellow X drawn through the
gauge and data removed (see EIS failure procedure for loss of entire EIS
function).
1.
Monitor remaining parameters and set engine controls to operate within
limitations.
3.2.9 G5 Standby Reset
If a G5 is used as a standby for the TXi, and for any reason does not respond to
the power button to turn on or off the G5, a hard reset needs to be performed on
the G5. To perform a hard reset, use the following procedure.
1. Press and hold the power button on the G5 for 15 seconds.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 25 of 68
3.2.10 Emergency Descent Mode (EDM)
If the aircraft if equipped with a GFC 600 autopilot capable of Emergency
Descent Mode, the pilot’s PFD will host menu buttons and alerting for EDM in
the event of activation/deactivation or system malfunctions.
 This aircraft is equipped with a GFC 600 capable of Emergency Descent
Mode.
 This aircraft is equipped with a manual Emergency Descent Mode
activation switch.
If the aircraft if equipped with a GFC 600 autopilot capable of Emergency
Descent Mode, the following procedures apply:
3.2.10.1 Emergency Descent Mode Automatic Activation
If the aircraft is above the activation altitude with the autopilot engaged, and the
cabin altitude climbs above the configured threshold, automatic activation of
EDM will commence. Refer to the Airplane Flight Manual Supplement for the
GFC 600 for specific EDM altitude triggers and EDM behaviors.
To Temporarily Inhibit Automatic EDM Activation
1.
Select the “Inhibit EDM” button on the EDM popup when
presented on the PFD. This will inhibit automatic EDM for 5
minutes.
To Inhibit Automatic EDM Activation (for the duration of the flight)
1.
Deselect the “Auto EDM” button on the PFD->System menu.
-
or -
2.
Override EDM when it is activated by pressing the A/P DISC
button on the control yoke, or the “AP” button on the GFC 600.
To Re-enable Automatic EDM Activation
1.
Select the “Auto EDM” button on the PFD->System menu.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 26 of 68
WARNINGs, CAUTIONs, and Advisories
The following tables show the color and significance of the warning, caution, and
advisory messages which may appear on the G500/G600 displays.
3.3.1 WARNING Annunciations – Red
Annunciation Pilot Action
Cause
HDG FAIL
Use Standby
Display system is not receiving valid
Magnetic
heading input from the ADAHRS or
Compass or GPS AHRS; accompanied by a red X through
track information the digital heading display.
Red X
Reference the
A red X through any display field,
data source or
indicates that display field is not
alternate
receiving data or is corrupted.
equipment.
ENGINE
Observe the
One or more engine parameters have
warning
exceeded a warning threshold.
indication on the
EIS display and
take appropriate
action.
Red Engine
Take appropriate The engine parameter has exceeded the
Parameter
action to correct
warning threshold.
condition causing
engine parameter
exceedance
EDM
Take all
The autopilot has initiated an emergency
appropriate
descent.
corrective actions
to correct the
condition that
triggered the
emergency
descent
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 27 of 68
3.3.2 CAUTION Annunciations – Yellow
Annunciation
Pilot Action
Cause
FAN FAIL
Prepare for loss of
display. Display
may overheat and
shut down.
Cooling fan for the display has
failed.
AHRS
ALIGN –
Keep Wings
Level
Limit aircraft
attitude to ±10º bank
and ±5º pitch as
AHRS Aligns - OK
to taxi.
Attitude and Heading Reference
System is aligning. AHRS may not
align with excessive pitch/bank
angles.
AHRS NOT
READY – Do
Not Takeoff
Remain stationary
and allow AHRS to
finish initialization
and allow
navigators to
acquire sufficient
GPS position.
AHRS sensors are not ready for
flight. Additionally, the interfaced
navigator does not have sufficient
GPS position.
No GPS
Position
Use alternate
information for
positional and
situational
awareness
GPS data is unavailable.
BACKUP
GPS
Observe limitations
regarding use of
emergency backup
GPS
No external GPS data is available,
and system is using emergency
backup GPS.
Yellow X
Reference the data
source or alternate
equipment.
A yellow X through any display
field, indicates that display field is
not receiving data or is corrupted.
ATTITUDE
Fly aircraft
manually and
crosscheck attitude
indication with
standby attitude
indicator and other
sources of attitude
information
(airspeed, heading,
altitude, etc.)
The PFD attitude monitors have
detected an AHRS malfunction or an
error between AHRS sources (if two
sources installed). Autopilot will
disconnect if AHRS is being used to
drive the autopilot.
(Autopilot
may
automatically
disconnect)
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 28 of 68
ALT, HDG,
or IAS
Cross-check the
flagged information
against other
sources to identify
erroneous
information.
Difference detected between
displayed airspeed, heading, or
altitude (dual ADC installations
only).
ON AHRS
1/2
Confirm intended
AHRS source
selection
The PFD is using the cross-side
AHRS (dual PFD and AHRS
installations only).
ON ADC 1/2
Confirm intended
ADC source
selection
The PFD is using the cross-side
ADC (dual PFD and ADC
installations only).
NO AP
DATA
Verify autopilot
mode of operation
using alternate
means.
Autopilot mode of operation is not
available.
ENGINE
Observe the caution
indication on the
EIS display and take
appropriate action.
One or more engine parameters have
exceeded a caution threshold.
Yellow EIS
Parameter
Take appropriate
action to correct
condition causing
engine parameter
exceedance.
The engine parameter has exceeded
the caution threshold.
TRAFFIC
Visually acquire the
traffic to see and
avoid.
The interfaced traffic system has
determined that nearby traffic may
be a threat to the aircraft.
TAWS N/A,
TAWS FAIL
Use vigilance,
terrain depiction and
TAWS alerting is no
longer provided.
Database errors or lack of required
GPS position.
EDM
Understand that
emergency descent
mode on the
autopilot is not
functional.
EDM mode is not functional. Refer
to the system advisory message for
details.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 29 of 68
3.3.3 Advisories – White
Annunciation
Pilot Action
ATTITUDE, ALT,
Be aware that the
HDG, or IAS
other (unselected)
(text on PFD)
AHRS/ADC source is
not available
ON AHRS 1/2
Confirm intended
AHRS source
selection
Cause
The other (unselected)
AHRS/ADC source is
unavailable.
The PFD is using the
secondary AHRS (singlePFD installation only).
ON ADC 1/2
Confirm intended
ADC source selection
The PFD is using the
secondary ADC (single PFD
installation only).
Various Alert
Messages may
appear in the Alerts
list, accessed by
pressing the Alert
key.
View and understand
all advisory
messages. Refer to
the TXi Pilot Guide
for appropriate pilot
or service action.
Typically, they indicate
communication issues within
the TXi System.
EDM
Be aware that
automatic EDM
activation will not
occur.
Automatic EDM engagement
has been inhibited by the
pilot.
Engine Exceedances
When the TXi system includes EIS, engine exceedance and some basic airframe
exceedances can be logged in the system. Should an exceedance occur, the pilot
is notified 30 seconds after the exceedance has ended via a system advisory. The
pilot will be reminded of the exceedance when on the ground with a system
advisory until the exceedance is acknowledged on the System  Logs 
Exceedances page. Additional details regarding the exceedance are available on
the exceedance log page. All exceedance thresholds are configured by the
installer and will vary from aircraft to aircraft. Refer to the EIS Appendix of this
document for aircraft specific details.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 30 of 68
NORMAL PROCEDURES
Before Takeoff
1.
Review displays for any abnormal warning, caution, or advisory
indications.
2.
If equipped with a TAWS/Terrain warning system, ensure that the
terrain alert audio test can be heard clearly (a system test audio clip is
played during the startup self-test).
4.1.1 Integrated Standby System Check
1.
Verify that no amber or red battery icon is displayed on the PFD.
2.
Verify that attitude, heading, altitude, and airspeed are displayed
normally on the PFD (no warnings, cautions, or advisories related to
these functions).
3.
Select the “Display Backup” switch to the ON position
4.
a.
Verify that the standby PFD information is displayed on the
backup display (MFD becomes a PFD display, or both
displays become PFD/EIS composite displays)
b.
Ensure that attitude, heading, altitude, and airspeed are
displayed normally on the standby PFD (no warnings,
cautions, or advisories related to these functions)
Select the “Display Backup” switch to the AUTO position and verify
that both displays return to their normal PFD, MFD, or EIS state.
4.1.2 Electric Standby Attitude Gyro (Mid Continent 4200 and 4300
Series)
When an electric standby attitude gyro is installed, test the backup battery before
takeoff.
1.
Apply power to electric standby attitude gyro and allow the gyro to
reach operating speed (approximately 5 minutes).
2.
Verify that the red gyro flag is not in view.
3.
Press and hold the STBY PWR button until the amber annunciator
begins to flash.
4.
Verify that the green annunciator is displayed continuously, and the red
annunciator is not displayed for the duration of the test (approximately
1 minute).
CAUTION
The standby attitude gyro must be considered inoperative if
the red annunciator is displayed during the test.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 31 of 68
Autopilot Operation
4.2.1 Autopilot Disconnect Test
In some installations, the autopilot may receive attitude from an installed PFD
Adapter. This adapter converts digital AHRS attitude into analog attitude for
use by the autopilot. If this is installed, an “AP DISC” button will be present in
the PFD Test Menu, and this function must be tested using the following
procedure.
1.
While on the ground, engage the autopilot.
2.
In the PFD Test Menu, press the AP DISC button and verify that the
autopilot disconnects.
CAUTION
Do not use the autopilot if the AP DISC button fails to
disengage the autopilot normally.
4.2.2 Autopilot NAV / APR mode coupling
To couple the autopilot NAV / APR mode:
1.
Select the desired navigation source on the Pilot’s PFD with the CDI
button.
2.
Select the desired NAV / APR mode on the autopilot.
NOTE
The autopilot will use the navigation source that is
displayed on the Pilot’s PFD.
4.2.3
GPSS Emulation
To use emulated GPSS roll steering commands with autopilots that do not
support GPSS roll steering in NAV / APR modes:
1.
Select the desired GPS navigation source on the Pilot’s PFD.
2.
Enable GPSS emulation on the PFD using one of the following
methods:
3.
a.
Use the AP HDG REF button in the heading context menu
b.
Use the GPSS button on the PFD controller (if installed)
c.
Select GPSS on the external HDG/GPSS switch (if installed)
Engage the autopilot in HDG mode.
AFMS, G500/G600 TXi P23 AML STC
FAA APPROVED
190-01717-B2 Rev. 3
Page 32 of 68
NOTE
When GPSS emulation is enabled, the heading bug will be
hollowed out, and the PFD heading button will display
“GPSS” text along with a crossed-out heading bug. The
“GPSS” text will be white when GPSS commands are
available, and it will be amber when there is no GPSS
command available.
NOTE
GPSS can be enabled from PFD 2, but GPSS is not
annunciated on PFD 2. The GPSS commands to the
autopilot are based on the GPS source displayed on PFD 1.
4.2.4 Altitude Preselect
Certain autopilots may use the PFD selected altitude bug for altitude preselect
and capture. Except as described in this section, refer to the autopilot AFMS
and/or Pilot’s Guide for autopilot system operation.
4.2.4.1 S-Tec Autopilots
To preselect and capture a selected altitude:
1.
Select the desired altitude with the PFD selected altitude bug.
2.
On the autopilot programmer computer press/hold VS then press ALT
to arm altitude hold mode.
4.2.4.2 Collins Autopilots
To preselect and capture a selected altitude:
1.
Select the desired altitude with the PFD selected altitude bug.
2.
On the autopilot flight control panel select ALT SEL mode.
CAUTION
Changing the selected altitude bug while ALT SEL mode
is selected may result in autopilot mode changes. Verify
the autopilot mode after changing the selected altitude.
4.2.4.3 Bendix/King Autopilots
To preselect and capture a selected altitude:
1.
Select the desired altitude with the PFD selected altitude bug.
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2.
Press the ALT CAP button in the ALT context menu or the ARM
button on the PFD controller to arm or disarm the selected altitude.
CAUTION
Changing the selected altitude bug while ALTC mode is
active will result in cancellation of ALTC mode. Verify the
autopilot mode after changing the selected altitude.
NOTE
When the selected altitude is armed for capture, ALTC is
displayed in white text in the upper right corner of the
PFD. When altitude capture mode is active, ALTC is
displayed in green text in the upper right corner of the
PFD. When a KA 315 annunciator panel is installed, the
“ALT ARM” annunciator on this panel will not be
operative.
NOTE
KFC 200/250 autopilots will inhibit glideslope (GS) mode
if altitude capture (ALTC) mode is engaged during
glideslope intercept.
4.2.4.4 Cessna Autopilots
To preselect and capture a selected altitude:
1.
Select the desired altitude with the PFD selected altitude bug.
2.
Press the ALT CAP button in the ALT context menu or the ARM
button on the PFD controller to arm or disarm the selected altitude.
NOTE
When the selected altitude is armed for capture, ARMED
is displayed in white text above the selected altitude.
4.2.4.5 Garmin Autopilots
To preselect and capture a selected altitude:
1.
Select the desired altitude with the PFD selected altitude bug.
2.
Press the ALT button on the autopilot mode controller.
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4.2.5 Vertical Speed Bug Coupling
Certain autopilots may be coupled to the PFD vertical speed bug for maintaining
a selected vertical speed. Except as described in this section, refer to the
autopilot AFMS and/or Pilot’s Guide for autopilot system operation.
4.2.5.1 S-Tec Autopilots
To select and maintain a vertical speed:
1.
Select the desired vertical speed with the PFD vertical speed bug.
2.
On the autopilot programmer computer press VS to engage vertical
speed mode.
NOTE
The selected vertical speed will automatically be reduced
towards zero when approaching the selected altitude bug.
AUTO will be displayed in the vertical speed context menu
button when vertical speed is being reduced automatically.
Manually changing the selected vertical speed while
AUTO is displayed will cancel automatic vertical speed
reduction.
4.2.5.2 Bendix/King Autopilots
To select and maintain a vertical speed:
1.
Press the VS ENG button in the VS context menu or the ENG button
on the PFD controller to sync the VS to current vertical speed and
engage vertical speed mode.
2.
Select the desired vertical speed with the PFD vertical speed bug.
NOTE
When engaging VS mode, the VS bug will be synced to the
current vertical speed. VS is displayed in green text in the
upper right corner of the PFD to indicate that VS mode is
engaged.
While VS mode is engaged, the vertical speed bug may be changed by:
•
Adjust the vertical speed bug with the PFD knob, or
•
Press and hold the vertical trim rocker switch on the autopilot in the
desired direction, or
•
Press the CWS button on the control wheel to synchronize the vertical
speed bug to the current vertical speed.
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4.2.5.3 Garmin Autopilots
To select and maintain a vertical speed:
1.
Press the VS button on the mode controller.
2.
Select the desired vertical speed with the PFD vertical speed bug.
NOTE
When engaging the VS mode, the VS bug will be synced to
the current vertical speed. VS displayed in green text in the
upper right corner of the PFD to indicate that VS mode is
engaged.
4.2.6 Coupling the Autopilot for Enhanced Descent-Only VNAV
The TXi allows for the display of Enhanced Descent Only (EDO) Vertical
Navigation (VNAV) deviations when interfaced with a Garmin GTN. In order to
provide autopilot coupling to the EDO VNAV guidance, the interface must also
include either a Garmin GFC 500 or GFC 600 with VNAV capability. If EDO
VNAV is enabled on the GTN and TXi in these installations, EDO VNAV
guidance may be coupled to the autopilot using the VNAV function of the GFC.
 This installation is equipped and configured to provide EDO VNAV
display and autopilot coupling.
 This installation is equipped and configured to provide EDO VNAV
display only.
 This installation does not support EDO VNAV display or coupling.
Cold Weather Compensation
The TXi can provide compensated minimums for cold weather compensation for
the IFR approaches. If the instrument approach chart requires temperature
compensation, the pilot must enter the destination airport temperature into the
TXi. If interfaced to a GTN that also has temperature compensation enabled,
approach altitudes provided on the map and flight plan are adjusted based on the
pilot entered temperature and the altitudes on the flight plan page are appended
with a snowflake icon.
Pilots must coordinate with ATC when flying temperature compensated
approaches.
Garmin G500/600/700TXi systems can provide compensated minimum values
when interfaced with a GTN and when temperature compensated minimums are
selected.
 This installation supports cold weather compensated approach and
minimums altitudes.
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 This installation supports cold weather compensated minimums only. No
GTN is installed in the system.
 This installation does not support cold weather compensation.
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PERFORMANCE
No change.
WEIGHT AND BALANCE
See current weight and balance data.
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SYSTEM DESCRIPTION
A detailed G500/G600 TXi Pilot’s Guide is available, as well as trainer software
applications.
A power button is provided at the top right corner of the bezel on each display
(lower left on GDU 700L). When the display is ON, pressing the power button
results in an onscreen menu with controls prompting action to close the menu,
power the display OFF, or enter display backup mode (if applicable).
Two SD card slots are provided for loading software and databases and for
logging flight data. An optional Flight Stream 510 can also be inserted into the
top-most SD card slot to add wireless capabilities to the TXi.
The following colors are used consistently within the TXi system:
Color
Red
Yellow
Functions
Warning conditions
Operating Limits
Cautionary conditions
Conditional operating ranges
Safe operating conditions
Green
Normal operating ranges
VOR/Localizer Data
Engaged Modes
Scales and Markings
White
Current data and values
Armed Modes
Magenta
Cyan
GPS Data
Active flight plan legs
Pilot selectable references
Controls Overview
Dual concentric knobs and a capacitive touchscreen provide control of functions
for the units. The touchscreen controls accept single touch, two finger pinch,
and single finger swiping actions. Virtual “buttons” which can be touched to
provide control functions are depicted using white outlines, round corners, and
shading. Display range can be controlled using two finger pinching. Map
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panning can be accomplished using single finger swiping. The enhanced HSI
map display range can be controlled using two finger pinch or single finger
swipe.
Display Brightness
Display brightness is controlled automatically based on input to a bezel mounted
photocell. The brightness level can be manually adjusted using controls in the
System  Backlight selection. Optionally, brightness can be controlled using
cockpit lighting dimmer switches.
System Power Sources
The G500/G600 TXi system depends on electrical power to function. The
Garmin Display Unit (GDU) and Air Data Attitude and Heading Reference
System (ADAHRS) (or separate AHRS and ADC) are directly connected to the
aircraft’s main or essential bus and energized when the aircraft master switch is
turned on. Other systems, like the navigation equipment, weather datalink,
autopilot and Adapter (GAD) are typically located on the avionics bus and may
not be functional when this bus is powered off.
The major components of the G500/G600 TXi system are circuit breaker
protected with resettable type breakers available to the pilot. These breakers are
labeled as follows:
Circuit
Breaker Label
Equipment
PFD
GDU 1060 (PFD/MFD), GDU 700P (PFD), GDU
700L (PFD)
EIS
GDU 700P (EIS or MFD/EIS) or GDU 700L (EIS or
MFD/EIS)
MFD
ADAHRS
GDU 700P (MFD)
Air Data and Attitude Heading Reference System
AHRS
Attitude and Heading Reference System
ADC
Air Data Computer
PFD
ADAPTER
GAD 43/43e interface adapter
ENG SNSR
GEA 110 or GEA 71B Engine/Airframe Unit
PFD CTLR
GCU 485 PFD Controller
STBY ATT
Electric Standby Attitude Indicator (Mid-Continent
4200/4300 gyros)
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In dual installations, the pilot side equipment is suffixed with the number 1 and
the copilot side equipment is suffixed with the number 2. For example: PFD 1
and PFD 2.
Equipment that receives power from two different circuit breakers will be
suffixed with the letters A and B. For example: PFD 1A and PFD 1B, or
PFD 2A and PFD 2B.
System Status
The G500/G600 TXi system status can be viewed via the status page; this
includes the GDU serial number and system ID of the unit, the software version
loaded on the unit, and the AHRS and ADC software if the integral ADAHRS is
installed.
An External LRUs list displays information and status of various units that are
interfaced to the TXi system. This list only includes LRUs that can report status
information, which is typically limited to other Garmin LRUs. Software
versions, serial numbers, and LRU status is typically provided. A green
checkmark indicates normal online status, and a red X indicates offline or failed
status. Some LRUs, like the GDL 69, GSR 56, and GTX 345, provide a button
to see more detailed information about the status of that unit. These LRUspecific status pages provide additional controls, like the ability to register the
unit, as applicable.
Databases
The G500/G600 TXi system utilizes databases to provide some system
functions.
Database status information is available to the pilot at system startup on the
MFD splash screen and during normal operations on the MFD system status
page for units with an MFD, or PFD Menu for PFD only units. Controls are
provided for enabling database sync and chart streaming and for manually
initiating a database update. EIS-only units do not support database functions.
System time (as received from an interfaced GPS navigator or the internal
backup GPS) is used to determine if a database is within its effective period. On
the splash screen, databases are displayed in amber if they are expired, not yet
effective, or if the current date/time is unknown. Databases are displayed in
white if they are within their effective date range. All database status
information is depicted in white on the System Status page.
The GDU utilizes two sets of databases – those which are active, and standby
databases which are databases whose valid period has not yet begun. Upon
reaching the effective date of a standby database the pilot is prompted to update
the database in use.
Internal database validation prevents incorrect data from being displayed.
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Databases can be updated using an SD card, by Syncing with other compatible
units, or using database concierge through a FS510 and PED. Databases are
stored internally on the GDU.
The terrain and basemap databases are updated periodically and have no
expiration date.
The Garmin or Jeppesen navigation database contains data associated with
navigation including airports, navigation aids, airways, airspaces, and other data.
The obstacle database contains data for obstacles and wires that pose a potential
hazard to aircraft. Obstacles 200 feet and higher are included in the obstacle
database. Wires which have been identified as a hazard to fixed wing aircraft are
included in the database. Coverage of the obstacle database includes the United
States and Europe. Wire coverage is limited to the United States. This database
is updated on a 56-day cycle.
CAUTION
Not all obstacles or wires are included in the databases.
The Garmin SafeTaxi database contains airport diagrams for selected airports.
This database is updated on a 56-day cycle.
The Garmin FliteCharts or Jeppesen ChartView electronic charts database
contains procedure charts for the coverage area purchased. An own-ship position
icon will be displayed on these charts when the aircraft icon on the chart page is
not X’d. This database is updated on a 28-day cycle. If not updated within 180
days of the expiration date, FliteCharts or ChartView will no longer function.
The airport directory database contains information on landing facilities, such as
operating hours, services available, and transportation/lodging resources. Airport
directory information may be available from multiple sources and coverage
areas. This database is updated on a 56-day cycle.
The magnetic variation model contains data about variations in the earth’s
magnetic field based on location. This database is loaded using the GDU and is
stored on the AHRS. This database is included with the navigation database and
is updated on a five-year cycle.
Crew Profiles
The crew profile function is provided for units which have an MFD to allow the
management of pilot-controlled settings. If the aircraft is operated by multiple
pilots, each pilot can recall their individual settings for use. These profiles
include settings from all displays in the system.
Upon power up, the MFD splash screen provides the option for the pilot to
select a crew profile. If no selection is made the unit will default to the crew
profile used on the last power cycle. Profiles can be managed via the System –
Setup page. Only one profile may be selected as active at a time. New profiles
are created with the settings currently in use.
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Display Backup Modes
Display backup modes are provided to replace the functionality of a failed PFD
or EIS display by providing the same function on another display. Display
backup capability is enabled based on the configuration of the GDUs installed in
the aircraft.
Integrated Standby System
For Class I and II aircraft, standby instruments (attitude, altitude, airspeed) may
be provided by a second GDU 700P display. The integrated standby system
consists of two GDU 700P displays installed adjacent to each other, with one
display configured as the PFD and the second display configured as either an
EIS or an MFD.
One display has an integrated ADAHRS and the other will be interfaced to a
GSU 75. A “display backup” switch is installed which will force both displays
into their display backup mode of operation when activated.
A GBB 54 backup battery will provide power to the PFD and sensors (GEA
110, GMU 44, GTP 59) in the event of primary aircraft power failure. This
configuration will provide the following functionality:
•
If the PFD fails or communication with the PFD is lost, the MFD/EIS
will automatically display its backup primary flight information
(attitude, altitude, airspeed) with the MFD or EIS behaving as follows:
o An MFD will transition to a full-screen PFD display
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•
o An EIS will transition to a split-screen PFD/EIS display
The two displays monitor and compare the independent attitude,
altitude, and airspeed data. If either display detects a difference
between any of the parameters (attitude, altitude, or airspeed), the
MFD/EIS display will automatically display its backup primary flight
information and amber annunciations will appear next to the data
generating the miscompare.
Electric Standby Attitude Gyro
If an electric standby attitude gyro is installed, the gyro operates from the
aircraft electrical system with a dedicated emergency battery specific to the
electric gyro. The electric attitude gyro battery capacity may vary considerably
depending on temperature, charge status, and battery life condition. Low
temperatures below 32°F will temporarily degrade battery capacity. Internal
chemistry will slowly degrade battery capacity over several years of operation
even when correctly maintained. A poorly maintained battery will suffer
accelerated degradation. Extended storage in a discharged state and overcharging will permanently damage the battery. Complete charging is required to
bring the battery up to full capacity if it has been unused for more than four
months or has been partially discharged.
Backup GPS
Each Garmin TXi GDU is equipped with a backup GPS receiver. When the
optional backup GPS antenna is connected, the TXi system will provide 2D GPS
position information from the backup GPS if all the certified GPS sources are
lost. There is no pilot action required to enable use of backup GPS data.
Backup GPS data is only used to provide non-safety critical functions after the
failure of all certified GPS position sources. Backup GPS data will only be
provided if a valid GPS position has been received from a certified GPS source
since becoming airborne and is subsequently lost.
Backup GPS data is utilized to provide the following functions: ownship
position on the moving map, GPS track display, waypoint bearing/distance
information, ground speed, and wind calculations. When backup GPS data is in
use, a yellow “BACKUP GPS” annunciation is displayed on all georeferenced
maps. Navigation using backup GPS is not provided. Overlays of
Stormscope®, traffic, terrain, and obstacles on the moving map is disabled when
backup GPS is in use. Traffic information from TIS-A and TCAS sources is
still available on the traffic page. Other functions which are inhibited include
bearing pointer on waypoint info page, chart geo-referencing, Synthetic Vision,
GPS altitude displays, GPS navigation status field, and terrain page display.
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Aircraft Audio Interface
The Pilot PFD is interfaced to the aircraft audio system to provide aural alerts
(altitude alerter, minimums, terrain). If multiple PFDs are installed, only the
Pilot PFD is interfaced to the audio system (to prevent duplicated aural alerts).
GDU 700P MFD displays may be interfaced to audio system for terrain alerts or
touch clicks, but only if there is no Pilot PFD installed.
GDU 700P/700L EIS displays are not interfaced to the audio system.
Advisory Notifications
An Advisory notification system is available on all installed GDUs. This system
notifies the pilot when a new advisory is available and displays a queue of active
advisories.
When a new advisory occurs, an “Advisory” button appears and flashes at the
bottom of each GDU.
Pressing the advisory button opens a popup window with a list of the active
advisories. Advisories are scrollable and are separated by a horizontal line
between entries.
Advisories are common to all GDUs, meaning that the same list of advisories is
displayed on all GDUs.
System Settings
The Setup page provides pilot controls for click volume, time format, and local
time offset. Controls are provided to set the nearest airport criteria so that
airports not usable by the aircraft type do not appear in waypoint searches. A
control is provided that allows the pilot to select which weather receiver is used
for the weather shortcut accessed by turning the outer dual concentric knob.
Crew profiles are managed from this page. Settings on this page are crossfilled
to all other GDUs in the system.
Units of Measure for temperature, barometric pressure, nav angle, altitude, fuel,
distance, and wind speed are pilot controllable via the System  Units page.
These units are propagated throughout the system with the exception of Air
Temperature Reference and Fuel Computer units which only affect the display
being used to make the selection.
The units and markings on the PFD are not user configurable. They match the
units as specified in the aircraft’s FAA approved Airplane Flight Manual and
standby instruments.
System Data Logging
The TXi system incorporates a data logging feature that can record parameters
related to the aircraft’s primary flight instruments, engine indications, and
aircraft configuration. Recorded data is stored in internal memory and can be
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exported to an SD Card by the pilot. Data logs can be sent via the Flight Stream
510 to a PED in the cockpit.
Primary Flight Display
PFD functions are controlled by the dual concentric knob located adjacent to the
PFD and using touchscreen controls. The outer knob assigns the function of the
inner knob and is annunciated at the bottom of the display adjacent to the knob.
The PFD knobs control Selected Heading Bug, Course Pointer, Selected
Altitude Bug, Vertical Speed Bug, Airspeed Bug, and Barometric Correction. In
addition, the inner knob provides for numeric entry. The knob function defaults
to HDG if it is not rotated for a period of 10 seconds.
When interfaced to a G5 via GAD 29, the TXi will send its BARO setting to the
G5 but the G5 cannot send its BARO setting to the TXi. It is recommended that
BARO SYNC be enabled when using VNAV functionality as the GTN will only
use the pilot-side BARO unless there is a failure.
The PFD can also be controlled using the touchscreen controls. Touching any of
the buttons on the screen will display a context sensitive menu. The inner knob
may be used to directly change the displayed value or buttons within the menu
may be used to access additional control or utilize the touchscreen to enter data.
The PFD can optionally be controlled using a remotely mounted controller
which provides dedicated knobs and buttons for Selected Heading Bug, Course
Pointer, Selected Altitude Bug, Vertical Speed Bug, Airspeed Bug, Barometric
Correction, and GPSS as well as optional controls for interfaced autopilot
functions.
A Menu button on the PFD provides access to additional controls and settings.
7.15.1 Primary Flight Data
The PFD displays attitude, heading, airspeed, barometric altitude, and vertical
speed data. Airspeed and altitude displays include a six second trend indicator.
Pilot selectable bugs may be provided for airspeed, altitude, vertical speed, and
heading.
The G500/G600 TXi requires at least one Garmin GPS/SBAS navigation unit to
ensure the integrity of the Attitude and Heading Reference System. The
ADAHRS or AHRS will continue to operate in a reversionary mode if the GPS
fails, and the attitude display on the PFD will still be presented.
When dual ADC or AHRS sensors are installed and configured, the pilot is
provided with AHRS/ADC source selection controls via the PFD Menu 
Sensors menu.
The default ADC or AHRS source on power up is ADC 1 and AHRS 1 for the
pilot side PFD and ADC 2 and AHRS 2 for the co-pilot side PFD.
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For single PFD installations, selection of ADC 2 or AHRS 2 as the sensor
source will cause a “ON ADC 2” or “ON AHRS 2”, respectively, to be
displayed with black text on a white background, to the right of the HSI.
For installations with two (2) PFDs, the pilot’s PFD will display “ON ADC 2”
or “ON AHRS 2” with black text on yellow background if the sensor source is
changed from the default. The co-pilot’s PFD will display “ON ADC 1” or “ON
AHRS 1” with black text on yellow background if the sensor source is changed
from the default.
When dual ADC or AHRS sensors are installed and configured, software
monitors provide detection of sensor miscompares. If a monitor detects a
difference between sources exceeding the allowable limit, a visual attitude,
altitude, or airspeed miscompare annunciation will be shown on the PFD.
Miscompares are annunciated using black text on a yellow background as
follows: airspeed miscompare is “IAS” shown below the airspeed pointer,
barometric altitude miscompare is “ALT” below the barometric altitude pointer,
heading miscompare is “HDG” in the bottom of the digital heading display
window, and attitude miscompare is “ATTITUDE” on the attitude indicator.
The PFD inhibits the “HDG”, “IAS”, “ALT”, and “ATTITUDE” annunciations
in dual TXi PFD installations when both PFDs are displaying the same sensor
source.
A no compare monitor is used to determine when data to the second ADC or
AHRS source is not able to be used for comparison. No compares are
annunciated using black text on a white background in the same location and
same text as miscompare annunciations.
Figure 4- Miscompare Flags on SVT
Figure 5- No Compare Flags no SVT
7.15.2 Attitude
The attitude display is a blue over brown presentation and optionally can display
synthetic vision data (SVT).
Standard rate turn marks are provided on the roll scale for bank angles up to 30°.
When a standard rate turn would be higher than 30° of bank, the indicator will
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be displayed at 30°. A turn rate indicator is displayed across the top of the HSI
compass dial. Tick marks are shown for half-standard and standard rate turns.
If pitch exceeds 20° nose down or 30° nose up, or bank angle exceeds ±65°, the
attitude display will automatically declutter removing non-essential data to
facilitate recognition and recovery from extreme attitudes. Red chevrons which
indicate the direction to level pitch are displayed when pitch attitudes exceed
30° nose down or 50° nose up.
Slip/skid information is shown using a white trapezoid below the sky pointer.
7.15.3 Synthetic Vision Technology
SVT may optionally be provided to assist the pilot in maintaining situational
awareness with regard to the terrain, obstacles, and traffic surrounding the
aircraft.
SVT controls are provided via Menu  Terrain/SVT. Synthetic terrain, horizon
headings, and airport signs can be toggled on and off from this menu.
SVT provides additional information on the PFD:
•
Synthetic Terrain: an artificial, database derived, three-dimensional
view of the terrain ahead of the aircraft within a field of view of
approximately 25 degrees left and 25 degrees right of the aircraft
heading.
•
Obstacles: obstacles such as towers, including buildings over 200 AGL
that are within the depicted synthetic terrain field of view. Powerlines
are not depicted in synthetic vision.
•
Flight Path Marker (FPM): an indication of the current lateral and
vertical path of the aircraft. The FPM is always displayed when
synthetic terrain is selected for display.
•
Traffic: a display on the PFD indicating the position of other aircraft
detected by a traffic system interfaced to the G500/G600 system.
•
Horizon Line: a white line indicating the true horizon is always
displayed on the SVT display.
•
Horizon Headings: a pilot selectable display of heading marks
displayed just above the horizon line on the PFD.
•
Airport Signs: pilot selectable “signposts” displayed on the synthetic
terrain display indicating the position of nearby airports that are in the
G500/G600 database.
•
Runway Highlight: a highlighted presentation of the location and
orientation of the runway(s) at the destination airport.
The synthetic terrain display is intended to aid the pilot awareness of the terrain
and obstacles in front of the airplane. It may not provide either the accuracy or
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fidelity, or both, on which to solely base decisions and plan maneuvers to avoid
terrain or obstacles. The synthetic vision elements are not intended to be used for
primary aircraft control in place of the primary flight instruments.
Note
In aircraft with nose high or nose low pitch attitudes during
normal maneuvers, the sky awareness, or ground
awareness bands may appear over the SVT display. It is
recommended that if this is discreating, that SVT be turned
off for those maneuvers.
7.15.4 Airspeed
The airspeed tape on the left side of the PFD displays red/white striping to
indicate the maximum allowable airspeed (VNE/VMO/MMO). This maximum
allowable airspeed display is configured to indicate the appropriate maximum
allowable airspeed for the airplane, including variations for altitude or Mach
number.
The airspeed tape displays a red low-speed awareness band at the lower range of
the airspeed tape. This low-speed awareness band is configured to a fixed value.
It does not indicate an actual or calculated stall speed and does not adjust with
variations in aircraft weight or other factors.
All other airspeed tape indications are configured to indicate the type design
limitations. The airspeed tape does not adjust these additional markings
(including VNO, landing gear, or flap speed limitations) for variations with
aircraft weight, altitude, or other factors.
Airspeed reference bugs are provided on the airspeed tape on are pilot
configurable via Menu  Airspeeds.
True airspeed and groundspeed are displayed below the airspeed tape and are
always in knots.
7.15.5 Barometric Altitude and Vertical Speed
Barometric Altitude and Vertical Speed are displayed on tapes on the right side
of the display. Barometric correction can be set using dual rotary knobs or
touchscreen. Selected altitude and vertical speed bugs may be provided and
when set are synchronized across all PFDs. The selected altitude bug may be
removed by selecting a value of -1,000ft.
Barometric altitude is required for Vertical Navigation (VNAV) calculations on
interfaced GTN. Baro sync should be enabled on TXi units. VNAV uses the
pilot-side baro setting unless that unit fails, in which case the co-pilot side baro
setting will be used.
7.15.6 Navigation
Navigation information is presented on the PFD through a combination of
horizontal situation indicator (HSI), a lateral deviation indicator (LDI) above the
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heading display, vertical deviation indicator (VDI), and GPS navigation status
information. Optional bearing pointers, distance measuring equipment (DME)
display, and marker beacon annunciations may be displayed.
Navigation information can be cycled through up to four independent sources by
pressing the “CDI” touchscreen button at the bottom center of the display. The
selected navigation source is shown on the left side of the HSI or LDI. CDI
source selection can be synchronized across multiple TXi PFDs if enabled by
the pilot.
Automation of CDI source selection and course selection is provided in the
following situations:
•
•
•
Localizer CDI Switch Prompting – the CDI button on the PFD will
flash when established on the final approach course of a LOC-based
approach, if the CDI source is GPS. This serves as a reminder to
change the CDI source to LOC.
Localizer Course Auto-Slewing – the appropriate LOC course will be
automatically preset when a LOC-based approach is loaded in the
navigator and the CDI source is not already selected to LOC.
Missed Approach Point Auto-Switching from VLOC to GPS – When
the missed approach segment of an approach is begun (navigator
unsuspended after the missed approach point), the CDI source will
automatically switch from VOR/LOC back to GPS. NOTE: this
functionality is not available with GNS 480 (CNX 80) navigators, as
they do not suspend at the missed approach point.
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7.15.7 HSI
The course pointer and deviation indicator are shown as a single, solid line for
GPS 1 and VLOC 1, and as an outline with no fill for GPS 2 and VLOC 2. GPS
and VLOC sources are further differentiated with color.
Optional CDI preview is available for ILS and GPS approaches when interfaced
with a GTN navigator. If enabled, grey CDI/VDI needles will indicate the
loaded approach deviations while still navigating on a GPS course.
The selected course is displayed above and to the right of the HSI. The selected
course is set via touchscreen keyboard entry or dual-concentric knob.
In addition, the HSI can display two simultaneous bearing pointers sourced from
GPS, VHF NAV, or ADF. DME distances can be displayed adjacent to the HSI.
The bearing pointer display and navigation source are pilot controlled under the
PFD Menu  HSI Setup  Bearing Pointers sub menu.
An enhanced HSI may be selected by the pilot under the PFD Menu  HSI
Options sub menu. The enhanced HSI includes an integral moving map within
the HSI depiction. HSI map data is a subset of the data on the MFD map page.
Traffic, terrain, obstacle, topographic, and weather overlays are also available
for the HSI map. Flight plan, runways, TAWS FLTAs, and TFRs are always
displayed. Overlays are controlled on the HSI Map Overlays menu.
7.15.8 Lateral Deviation Indicator (LDI)
A Lateral Deviation Indicator (LDI) is always displayed on the PFD above the
heading display. This LDI shows course deviation, navigation source, and
VLOC station identifier or GPS phase of flight. The LDI uses the same color
convention as the HSI .
The LDI incorporates automatic reverse sensing correction into the deviation
display. When the difference between the heading and the selected course is
greater than 107°, the LDI will enable reverse sensing correction. Reverse
sensing correction inverts the course deviation needle and to/from indicator so
that they correctly indicate the direction of the course and waypoint. The course
deviation needle will be deflected in the direction of the desired course, and the
to/from indicator will point in the direction of the waypoint (similar to how the
HSI depiction inverts with heading changes).
Message, waypoint, OBS, SUSP, phase of flight, LOI, and DR annunciations
from a GTN or GNS interfaced to the TXi are annunciated on the upper CDI.
7.15.9 Vertical Deviation Indication (VDI)
Vertical guidance is shown by a vertical deviation indicator (VDI) inboard of the
barometric altitude tape. The VDI can display up to two sources of vertical
deviation depending on the interfaced navigator. The following table describes
the available vertical deviation indications.
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Magenta Diamond
GPS Approach Vertical Guidance
Magenta “V”
Barometric VNAV Guidance
Green Diamond
VHF Glideslope Approach Guidance
Open Gray Diamond
Preview approach guidance when
actively using Barometric VNAV as
the vertical path
Table 1- Vertical Deviation Indication Description
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7.15.10 DME Display
Pressing on the DME field opens a DME popup menu. The DME popup menu
allows selection of a DME tuning source when two navigation sources are
connected and, if supported by the DME, a hold option.
7.15.11 Marker Beacon Display
The PFDs can show marker beacon annunciations from an interfaced marker
beacon receiver. The marker beacon annunciations are shown to the left of the
selected altitude.
7.15.12 Radar Altimeter Display
If interfaced to a radar altimeter the radar altitude will be displayed on the PFD
adjacent to the altitude tape. Additionally, when the radar altitude AGL value is
within the viewable range of the barometric altitude tape, a ground awareness
band is displayed.
If the installed radar altimeter includes self-test capability the Test controls are
provided in the “Test” sub-menu under the PFD Menu. Refer to the Radar
Altimeter user documentation for information about values displayed during
Test.
NOTE
For KRA 405 Radar Altimeters the displayed Test value
will be between 25 and 50ft.
7.15.13 Minimum Altitude Display and Alerting
When enabled by the pilot, an altitude minimums bug will be displayed in cyan
on the barometric altitude tape. If a radar altimeter is installed, the pilot can
select between barometric or radar-altitude minimums.
Altitude minimums are accessed under the PFD Menu  Minimums sub menu
and can be set by touchscreen keypad or dual-concentric knob.
Both visual and aural altitude minimums alerts are provided. During a descent
to minimums, the minimums bug will change from cyan to white when the
aircraft descends to within 100 ft of minimums. An aural “Minimums,
Minimums” alert will be triggered when the aircraft’s altitude descends through
minimums and the minimums bug will change to yellow. As the aircraft altitude
climbs back above minimums, the minimums bug will change to white 50 ft
above minimums and cyan 150 ft above minimums. Alerting is rearmed once
the aircraft is 150 ft or more above the minimums altitude.
7.15.14 Outside Air Temperature/Density Altitude
The PFD provides a pilot configurable display of outside air temperature or
density altitude information below the airspeed tape. The pilot can choose to
show Static Air Temperature (SAT), Total Air Temperature (TAT), or
temperature delta from the International Standard Atmosphere (ISA). Density
Altitude can also be configured to be displayed instead of the temperature.
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NOTE
When operating with ice accumulation on the temperature
probe, the displayed air temperature may be in error by as
much as 4°C.
Autopilot Interfaces
The G500/G600 TXI System provides various autopilot integration capabilities
dependent upon the type of autopilot installed in a particular aircraft.
The G500/G600 TXi installation in this aircraft provides the following autopilot
functions (appropriate boxes will be checked):
 This installation does not interface with the autopilot (basic wing
leveling autopilot, or no autopilot is installed in the aircraft).
 Course / NAV Selection coupling to the autopilot.
 Heading Bug coupling capability to the autopilot.
 Roll Steering emulated via heading mode.
 Roll Steering capable autopilot.
 Altitude Pre-Selector integrated with the autopilot.
 Vertical speed bug integrated with the autopilot
 Flight Director display driven from external autopilot or FD computer.
 A GAD 43 Adapter is installed in this aircraft
 GAD 43 provides attitude to the autopilot
 GAD 43 provides yaw rate to the yaw damper
 GAD 43 provides baro correction to the altitude preselector
 GAD 43 provides altitude preselect and/or vertical speed
 G500/G600 TXi provides attitude / air data to autopilot
 Autopilot Modes annunciated on PFD
 GFC 500 or GFC 600 is installed in this aircraft and the TXi provides a
means for mode annunciation, altitude selection, vertical speed
selection, heading bug selection, and navigation source selection.
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7.16.1 Navigation Data for Autopilots
The G500/G600 TXi system can provide course and heading data to the
autopilot based on the data selected for display on the HSI. For aircraft equipped
with multiple GPS/NAV systems, the PFD acts as a selection hub for the
autopilot’s NAV mode, and the G500/G600 TXi may also provide GPS Steering
(GPSS) data.
Not all autopilot systems are approved for coupling to vertical guidance on GPS
based approaches; consult the AFMS for the autopilot and/or GPS system.
If the installation has dual PFDs installed, control of navigation course, heading,
or altitude data affecting the autopilot from the co-pilot side can only be made if
the systems are synchronized with each other. Synchronization controls are
provided under the PFD Menu.
If the autopilot is capable of receiving GPSS Roll Steering information, the data
is transmitted via a digital communications bus from the G500/G600 TXi to the
autopilot. The PFD receives this data from the GPS. In dual GPS installations,
the PFD sends Roll Steering information for the currently-selected GPS source.
For autopilots which are not GPSS Roll Steering capable, the G500/G600 TXi
can convert GPSS turn commands into a heading error signal for the autopilot.
When the autopilot is operated in HDG mode and GPSS is selected on the PFD,
the autopilot will fly the turn commands from the GPS navigator selected on
PFD 1. If an autopilot is interfaced to the GDU which supports GPS steering
(GPSS), an additional touchscreen button is provided on the selected heading
popup window for toggling the autopilot heading reference between GPSS and
selected heading. When GPSS is selected, the heading bug display will change
to a cyan outline with no fill and the selected heading display will annunciate
“GPSS” with an icon of a crossed out heading bug. The heading bug may still
be adjusted by the pilot as a visual reference without affecting GPSS to the
autopilot.
If the GPSS data is invalid (for example, if there is no active GPS leg) or the
selected HSI source on PFD 1 is not GPS, the annunciated GPSS text will be
yellow and a zero turn (wings level) command will be sent to the autopilot.
GPSS commands are not available when the CDI is selected to a VOR/LOC
source.
For GFC 500 only: Even if LOC is the armed mode the autopilot will not
capture localizer CDI preview when CDI is on GPS. Change CDI to LOC when
capturing if auto CDI sequence is not enabled.
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7.16.2 Flight Director Display
If autopilot flight director commands are interfaced to the G500/G600 TXi, they
will be presented as a single cue flight director on the PFD. Control of the flight
director is accomplished via the autopilot/flight director controller; there are no
pilot controls or adjustments for the flight director on the G500/G600 TXi.
The GDU limits the distance the flight director pitch commands may deviate
from the aircraft attitude icon. If the pitch command provided by the autopilot
flight director is greater than the distance allowed by the GDU, the command
bars will be displayed at the maximum distance allowed by the GDU. As the
aircraft pitch changes to satisfy the command bars, the bars will continue to be
displayed at the maximum distance from the aircraft attitude icon until the
aircraft pitch deviation is within the command display limit.
In supported installations, the flight director will show hollow bars when the
autopilot is not engaged, and solid colored bars when the autopilot is engaged.
Figure 6- Flight Director Bars (Autopilot Not Engaged)
7.16.3 Attitude and Rate Data Sources for Autopilots
Attitude-based autopilots may be driven by the standby gyro, a remote mounted
gyro, the GDU, a G5 when driving a GFC 500, or the GAD 43 adapter. If the
TXi system is providing attitude to the autopilot, it will be indicated in Section
7.15.9 above. Otherwise, the autopilot is receiving attitude or rate information
from the standby or a remote gyro and the autopilot attitude input is independent
of the attitude displayed on the PFD.
The pilot must understand the autopilot system inputs to detect faults and
capabilities with inoperative equipment. Refer to the autopilot flight manual for
operational information.
7.16.4 Altitude Pre-Select and VS Engagement
Optionally, G500/G600 TXi system can provide altitude preselect functions
such that the autopilot can capture the pre-selected altitude or couple to the
selected vertical speed if these capabilities are supported by the autopilot
equipment installed. Refer to the autopilot operator’s manual or autopilot
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Airplane Flight Manual Supplement for the proper operation of the autopilot
system.
Controls for altitude preselect functions are provided using the selected altitude
context menu, and vertical speed controls are provided using the vertical speed
context menu. Altitude preselect, and VS mode annunciations are displayed
adjacent to the altitude preselect display above the altitude tape.
7.16.5 ARC Style VSI
When an ARC style VSI is configured on the PFD, it is replaced with a standard
vertical VSI when the PFD screen is reduced below a 60% PFD on the 10” TXi
display. ARC VSI’s are not available in 7” PFD’s or in aircraft where TCAS II
is interfaced with the TXi PFD.
MFD Functions
The MFD functions are controlled using the dual concentric knob located
adjacent to the MFD or using touchscreen controls. The outer knob can be used
to select various MFD pages and is annunciated at the bottom of the display
adjacent to the knob. The inner knob can be used to control the display range.
Various MFD functions can be controlled using the touchscreen.
On all MFD pages, the nose of the ownship symbol represents the actual
location of your aircraft.
7.17.1 Map Page
A 2D moving map function is provided on the MFD. The appearance and
determination of data displayed on the moving map is controlled by pilot
selections made via a Menu button. The map menu provides on/off controls for
map overlays, a map detail selector, and a map setup button which accesses
additional map controls.
The map range can be altered using the touchscreen or rotary knob to allow for
display of data pertinent to the operation being conducted. The current zoom
scale or range of the map is continuously indicated by a range ring centered
around the ownship with a range indication at the 11 o’clock position on the
ring. In addition to zooming, a panning function is provided to allow the
position of the map to be centered on a location other than the ownship.
Panning mode is entered by dragging a single finger on the display. The map
orientation can be changed to North Up by pressing the North Up arrow in the
top left corner.
If an active flight plan is present in the interfaced navigator, it will be depicted
on the map. Traffic, Terrain, Weather, Land, and Aviation data can be selected
for overlay on the map.
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7.17.2 Traffic Display
The MFD can display traffic data from interfaced traffic systems. Sources of
traffic data include TIS-A, TAS/TCAS, and ADS-B traffic. The information
from these systems is displayed on and controlled using the MFD.
Traffic system operating controls and system status are provided on the
dedicated traffic page via touchscreen control in the lower left corner and/or the
Menu button, depending on the interfaced traffic system type. A display altitude
filter is provided in the lower right corner. Filtering of targets based on altitude
is accomplished by the display and affects the traffic page and map page. When
interfaced to a TIS traffic system, altitude filtering is not available.
The center of the traffic target icon serves as the reported location for the target
aircraft.
Additional functions are provided on the dedicated traffic page when an ADS-B
traffic system is interfaced including the depiction of motion vectors.
Absolute motion vectors are colored white and depict the reported track of the
traffic target referenced to the ground. An absolute motion vector pointed
towards your ownship symbol does not necessarily mean the traffic target is
getting closer to your aircraft.
Relative motion vectors are colored green and depict the motion of the traffic
target relative to your ownship symbol. The direction the traffic target is pointed
may vary greatly from the motion vector and a target may be getting closer to
your aircraft independent of the direction the target is pointed. A green relative
motion vector pointed towards your ownship indicates that the traffic target is
converging on your aircraft.
For ADS-B traffic systems - if while on ground without valid magnetic heading
and the aircraft stops the traffic page orientation will change from TRACK UP
to LATCHED. In this mode the display remains oriented to the last valid track
until a new valid track is obtained.
Traffic can be displayed on the moving map as an overlay. Additional filtering
based on traffic type (all, advisories, alerts) can be selected using the Menu
Traffic selection. For TIS-A traffic selection of the advisories and alerts will
result in display of alerted targets only.
Traffic page units are always in nautical miles and feet. If systems units for
altitude are selected to meters, then an annunciation is provided on the traffic
page indicating that traffic altitudes are depicted in feet and the traffic overlay
icon for the map includes a “FT” indication.
If a traffic alert occurs and the MFD is not selected to the dedicated traffic page,
then a traffic “popup window” is provided which depicts the traffic and provides
controls to either go to the dedicated traffic page or close the popup window.
On a GDU 1060, if a traffic alert occurs and display is showing a full screen
PFD, then a button is provided which will return to split screen mode and
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display the dedicated traffic page. On systems with a PFD installed, a yellow
TRAFFIC annunciator is provided adjacent to the HSI.
Terrain Awareness and Alerting
The following terrain awareness and alerting functions may be provided by the
TXi system: Terrain Proximity, Terrain FLTA, or TAWS-B. If the TXi system
is interfaced to a GNS or GTN navigator equipped with TAWS-B, then the TXi
will display TAWS-B parameters provided by the GNS or GTN. The Terrain or
TAWS function provided by the TXi system is indicated by a text box in the
lower left corner of the Terrain Page.
Terrain Proximity function is a 2D depiction of terrain, obstacle, and powerlines
with no alerting. A dedicated terrain page is provided on the MFD on which the
relative height of terrain, obstacles, and powerlines are depicted using color to
convey the height of the obstruction relative to aircraft altitude based on
database data. An obstacle and/or wire overlay icon will be shown near the
bottom of the display when the obstacle or wire depiction is being provided as
determined by the zoom scale. The Terrain Proximity function is present on the
system regardless of other higher-level terrain functions that may be selected.
If SVT is enabled in the TXi system, then the Terrain - FLTA function is
provided. Forward Looking Terrain Alerts and Reduced Terrain Clearance
Alerts are provided for terrain, obstacles, and wires.
If TAWS-B is enabled in the TXi system, then the same alerts as the Terrain –
FLTA configuration are provided plus additional alerts necessary for TSOC151c compliance.
If the TXi is interfaced to a GNS or GTN with TAWS-B enabled, then TAWS
alerts are only displayed from the GPS/TAWS navigator interfaced as GPS 1
and are displayed regardless of the CDI 1-2 setting.
Visual indications are provided for terrain, obstacle, and wire alerts as follows:
•
For all TXi configurations which provide alerts and all configurations
where the TXi is interfaced to GNS or GTN with TAWS-B enabled:
o An annunciator located on the PFD adjacent to the HSI
provides text annunciations of system status, self-test, and
alert conditions using yellow, red, or white as appropriate to
the condition.
•
For all TXi configurations which provide alerts and all configurations
where the TXi is interfaced to a GTN with TAWS-B enabled:
o If a terrain alert occurs and the MFD is not selected to the
dedicated terrain page, then a terrain “popup window” is
provided, which depicts the obstruction generating the alert
with controls provided to either go to the dedicated terrain
page or close the popup window. On a GDU 1060, if a terrain
alert occurs and the display is showing a full screen PFD, a
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o
o
o
button is provided which will return to split screen mode and
display the dedicated terrain page.
The terrain page and map page will depict the area or
obstruction causing the alert as an area of color corresponding
to the alert severity and encircling the obstruction.
If Synthetic Vision depiction is turned on, an area
corresponding to the alert area on the map/terrain page is
shaded in the corresponding color for terrain alerts. Obstacle
alerts will cause the relevant obstacle to be depicted in the
alert color in SVT. Powerline alerts do not have a
corresponding indication in SVT.
In Dual PFD installations, TXi generated alert audio is only
provided by the Pilot side GDU. If the Pilot side GDU
becomes inoperative, the Co-Pilot side GDU visual
annunciations may still function, but the aural alerts will not be
heard.
Controls are provided for terrain, obstacle, and wire alerts as follows:
•
For all TXi configurations in which the TXi system provides alerts:
o Controls are provided in the menu on the Terrain Page. A
“Terrain Inhibit” button inhibits terrain, obstacle, and
powerline alerts when pressed. Annunciations are provided on
the PFD and Terrain Page to indicate that alerts are inhibited.
A “Terrain Test” button initiates a self-test sequence which
results in aural and visual self-test annunciations.
7.18.1 Charts
The MFD can provide depiction of aeronautical charts on a dedicated charts
page as well as the map page. Charts are geo-referenced on both the map and
charts pages. The map page will always depict the chart that is currently
selected on the charts page; this chart is overlaid on top of the terrain, TOPO,
and Basemap layers but below the traffic and ownship layers. The overlaid
chart is oriented appropriately for the current orientation of the map considering
the selected map orientation and position/direction of the ownship. The charts
page will include a depiction of the ownship, colored magenta, if the selected
chart supports geo-referencing and the ownship is located within a georeferenced portion of the selected chart. If geo-referencing is not available on
the charts page an icon is presented that indicates the ownship is not being
depicted.
7.18.2 Flight Plan Page
The MFD includes a Flight Plan page which displays the active flight plan from
the selected GPS navigator. The flight plan page is only a display of the active
flight plan from the navigator (flight plans in the navigator catalog cannot be
displayed). The active flight plan cannot be edited using the MFD. Flight plan
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waypoints for which addition information is available appear as buttons.
Touching a button will jump to the Waypoint Info page for that waypoint.
On a GDU 1060, the active flight plan is shown for the GPS source that
corresponds to the PFD CDI selection (e.g. GPS 1 when the CDI source is GPS
1 or VOR/LOC 1, GPS 2 when the CDI source is GPS 2 or VOR/LOC 2). This
is the same GPS source shown on the PFD NAV Status field. If a G5 is installed
as part of the GFC 500 system, the navigation source matches the TXi and there
is no side (1 or 2) indications on the G5.
On a GDU 700P MFD, the active flight plan for the associated PFD is displayed
(e.g.- if the co-pilot has a PFD and MFD in the co-pilot panel, the co-pilot PFD
CDI selection will change the flight plan data on the associated PFD). If the
MFD is a center located stand-alone MFD, the flight plan shown will be from
the pilot’s PFD source selection.
7.18.3 Weather Data
The MFD can display weather data from interfaced datalink systems. Sources of
weather data include the Garmin “GDL 69(A)” and “GDL 69(A) SXM” Sirius
XM receivers, Garmin GSR 56 Iridium Transceiver, and Garmin ADS-B
transceivers. If one of these optional weather datalink receivers is installed, the
pilot will be able to access graphical and text weather products using the MFD.
Datalink weather products use color and/or timestamps to indicate the recency
with which the data was received.
Selected weather products from each receiver can be overlaid on the map page
as well as the enhanced HSI map while all received products can be displayed
on the dedicated weather pages. The products available on the map page and
HSI are different for each weather receiver. The map page and HSI provide
controls to select the desired weather receiver; only one weather receiver can be
selected at a time.
Text and graphical datalink weather associated with a facility can only be
viewed when a database which includes that facility is installed.
The G500/G600 TXi system can optionally control various airborne weather
radars and display their data. Weather radar data is depicted on the dedicated
weather radar page and can be overlaid on the map page. The weather radar
page contains controls for operating modes, gain, bearing, tilt, stabilization,
horizontal and vertical scan sectors, and scan directions, as applicable. Controls
for Garmin radars may include advanced functions such as altitude
compensating tilt, turbulence detection, weather advisories, and ground clutter
suppression, and a 15-color scale. The TXi will automatically command the
radar into standby mode upon landing.
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NOTE
Weather radar may be shown on multiple cockpit displays,
and some other displays may use a 3-color scale for
weather returns (instead of a 4-color scale). The 4-color
scale used in the TXi is displayed on the radar page, and
the 4-color scale provides additional distinction between
heavy (red) and extreme (magenta) returns.
The GWX 70/75/80 Weather Radar can optionally provide a turbulence
detection function. The turbulence detection function can only detect turbulence
between 2.5 nautical miles and 40 nautical miles ahead of the aircraft. The
display of turbulence is only provided when the radar range is set to 160 nautical
miles or less.
NOTE
Turbulence detection does not detect all turbulence
especially that which is occurring in clear air. The display
of turbulence indicates the possibility of Severe or greater
turbulence, as defined in the Aeronautical Information
Manual.
The MFD can optionally display data from Stormscope® lightning detection
systems. Stormscope data can be depicted on the map page, dedicated
Stormscope page, and HSI map. For detailed information about the capabilities
and limitations of the Stormscope system, refer to the documentation provided
with that system.
7.18.4 Waypoint Information
The MFD provides pages that display information about the different waypoint
types. These pages can be accessed by touching one of the supported waypoint
types on the map and then pressing the provided Waypoint Info button, or by
navigating to the Waypoint Info page group from the home page
Engine Indicating System
Engine Indicating functions are optionally provided for single and twin-engine
aircraft with four and six-cylinder reciprocating engines, and some single-engine
turboprop aircraft powered by Pratt & Whitney PT6A derivative engines.
The following indications are provided in all EIS installations:
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Piston Powered Aircraft
Tachometer
Manifold Pressure (If required)
Fuel Flow
Oil Pressure
Oil Temperature
Cylinder Head Temperature (CHT)
Exhaust Gas Temperature (EGT)
Turboprop Powered Aircraft
Torque
Propeller RPM
Gas Generator RPM
Engine Temperature (ITT)
Fuel Flow
Oil Pressure
Oil Temperature
Other engine indications in the aircraft may be provided by either the EIS
display or previously installed indicators in their original locations. The
following indications may be provided on the G500/G600 TXi EIS display:
•
•
•
•
•
•
•
•
Fuel Pressure
Electrical gauges (Amps / Volts)
Main and Auxiliary Fuel Quantity
Carburetor Air Temperature (CAT)
Turbine Inlet Temperature (TIT)
Inlet Air Temperature (IAT)
Compressor Discharge Temperature (CDT)
IAT/CDT Differential
Pilot-selectable data fields may be present on GDU 700P/L displays, or on the
MFD Engine page. Additional functions provided by the EIS system include a
fuel computer, hour meters, and pilot-selectable engine advisories.
The layout of EIS gauges is dependent on the G500/G600 TXi display type and
number of engines. The determination of which data is presented in which slot
is set by the installer in configuration mode based on data in the STC which
specifies the data located in each position. The markings on the EIS gauges are
the same as those markings provided by the previously installed gauges and
depict the operating ranges and limitations provided in the Airplane Flight
Manual and Type Certificate Datasheet.
For installations in which the EIS display is not within the primary field of view,
an EIS annunciator is required to be installed within the primary field of view
which will draw the pilot’s attention to the EIS display when certain parameters
are outside normal operating ranges. This annunciation may be provided on a
G500/G600 TXi PFD or by a separate red/yellow “ENGINE” annunciator lamp.
Some previously installed aircraft gauges included non-required markings such
as advisory marks for certain altitude and power combinations. EIS gauges will
include all markings required to comply with operating limitations associated
with that gauge. Markings not required by regulation and which do not convey
limitations or operating ranges are provided to the pilot by means of a placard.
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190-01717-B2 Rev. 3
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EIS gauges include display characteristics to attract the pilot’s attention when
outside normal operating ranges. Gauge behavior in caution or warning ranges
is dependent on gauge type and is suppressed when the engine is OFF and the
aircraft is on the ground.
The primary engine gauges (see Table 2) change the color of the digital readout,
gauge title, and pointer to yellow or red when in non-normal ranges. Other
gauges will flash when entering a non-safe range and cause the ENGINE
annunciator (if installed) to illuminate and flash.
Piston Powered Aircraft
Engine Tachometer
Manifold Pressure
Fuel Flow
Turboprop Powered Aircraft
Torque
Propeller RPM
Gas Generator RPM
Engine Temperature (ITT)
Fuel Flow
Table 2: Primary Engine Gauges
On the GDU 700, flashing will continue indefinitely until the pilot manually
acknowledges the alert by pressing the “ACK” button at the bottom on the
screen. The color of the “ACK” button is dependent on the type of alert being
issued. On the GDU 1060 a parameter will flash for 10 seconds with no option
for pilot acknowledgment. After 10 seconds, the flashing will stop.
7.19.1 Dynamic Gauge Ranges (Turboprop Only)
In turboprop aircraft, the gauge markings may be dynamically updated based on
certain conditions. For example, ITT gauge markings may change based on the
state of the engine (e.g.- different marking while the engine is starting). This
allows the pilot to easily interpret several different limitations for the engine that
may be based on operating conditions such as temperature, air/ground logic, or
engine parameters. The installer will configure those dynamic gauges based on
the individual aircraft parameters listed in the aircraft Pilot’s Operation
Handbook.
 This installation includes EIS with dynamic gauges. Gauge indications
could be different depending on the aircraft engine status. See the
attached gauge diagrams for specific gauge markings.
 This installation does not include EIS with dynamic gauge markings.
7.19.2 Engine Tachometer (Piston Aircraft Only)
For aircraft in which a starting vibrator is installed the RPM indication is not
accurate during engine cranking.
For aircraft equipped with P lead sensors to measure engine RPM, the RPM
indication may momentarily fluctuate when selecting operation on a single
magneto.
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190-01717-B2 Rev. 3
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7.19.3 Carburetor Air Temperature (Piston Aircraft Only)
The Carburetor Air Temperature gauge (if installed) is marked with a blue arc
from -15 to 5 ⁰C which indicates a range of temperatures where carburetor icing
is likely to occur. Operation in this temperature range should be avoided in
conditions where carburetor icing is possible (humid air or visible moisture).
7.19.4 CHT (Piston Aircraft Only)
A CHT cooling rate monitor is provided on the CHT graph gauge. A single blue
down arrow is presented on the graph gauge when cylinder head temperature is
decreasing at a rate of approximately 30 degrees Fahrenheit per minute. A
double blue down arrow is displayed when the cylinder head cooling rate is
approximately 60 degrees Fahrenheit per minute or greater.
The cylinders can be cycled through by touching the CHT gauge. Each cylinder
will numerically display it’s respective CHT, and after 10 seconds will revert to
displaying the hottest CHT.
7.19.5 EGT (Piston Aircraft Only)
An exhaust gas temperature gauge is provided on the EIS display for all
configurations. The EIS display can provide indications of EGT for each
cylinder and additionally can indicate a primary EGT which is a measurement of
the EGT in the exhaust manifold. On the GDU 1060, EGT information is
presented on the EIS strip and the MFD engine page. The EIS strip gauge
presents the primary EGT (if installed) or hottest EGT of the individual EGTs.
The EGT presentation on the GDU 700P/L and GDU 1060 MFD EIS pages
shows all cylinders plus primary EGT at the same time on a graphical gauge.
Primary EGT is labeled as E, while individual cylinders are labeled by number.
The digital EGT readout displays the hottest EGT or the EGT for the cylinder
selected by the pilot by touching the EGT graph to cycle through the cylinders.
Cylinder specific EGT displayed on the EGT graph gauge does not provide
configurable operating ranges (yellow, red) and will not provide any alerting or
non-safe range indications to the pilot. Primary EGT displayed on the EGT
graph gauge and bar gauge can be configured with blue arcs, green arcs, yellow
arcs and red maximum lines.
7.19.6 Mixture Leaning (Piston Aircraft Only)
G500/G600 TXi EIS provides four different leaning modes depending on the
installed configuration: rich of peak, lean of peak, primary EGT, and TIT
leaning. The system lean mode can be set from the Engine Menu.
Lean mode is entered by pressing the Lean Button. When in lean mode peak,
EGT/TIT is indicated by the appropriate temperature bar turning white on the
graph gauge. A white line is also drawn at the recorded maximum EGT/TIT
value. The system will display “PEAK” at the top of the CHT/EGT graph gauge
for three seconds when a peak is detected. The top of the CHT/EGT will then
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190-01717-B2 Rev. 3
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display the EGT/TIT value for the appropriate cylinder/turbo and the
temperature differential from the maximum recorded EGT/TIT value.
Rich of peak leaning detects and indicates the first engine cylinder to peak
during the leaning process. Once the first peak in EGT is detected, the
temperature differential from the recorded maximum EGT of the first cylinder to
peak is displayed.
Lean of peak leaning detects and indicates the last engine cylinder to peak
during the leaning process. Once the last peak EGT is detected for each engine
cylinder, the system will display the temperature differential from the recorded
maximum EGT of the last cylinder to peak.
EGT leaning is available when the system is configured to display an EGT other
than the EGTs for each cylinder (such as an EGT probe installed in the exhaust
manifold). EGT leaning looks for a peak in primary EGT during the leaning
process. Once a peak in EGT is detected, the system will display the temperature
differential from the maximum primary EGT value.
TIT leaning is available when the aircraft is configured to measure a single TIT.
TIT leaning looks for a peak in TIT during the leaning process. Once a peak in
TIT is detected, the system will display the temperature differential from the
maximum recorded TIT value.
The system supports dual TIT measurements for single engine aircraft. In this
configuration, a leaning mode is available for the first TIT sensor to peak, TIT –
First Peak, or for the second TIT sensor to peak, TIT – Second Peak. TIT – First
Peak functions similar to rich of peak leaning mode. TIT – Second Peak
functions similar to lean of peak leaning mode
7.19.7 Fuel Quantity
Usable fuel may be displayed on the EIS display. Main fuel quantities are
grouped together, and aux/tip fuel quantities are grouped together.
Previously installed aircraft low fuel quantity annunciators will be deactivated as
part of the fuel quantity installation in some aircraft. In this case, the low fuel
annunciators will be placarded as deactivated, and a red or yellow arc must be
added to the fuel quantity gauge to indicate the fuel level that corresponds to the
low fuel annunciation.
7.19.8 Fuel Computer
A Fuel Computer/Totalizer is provided on the GDU 1060 MFD engine page and
on the GDU 700 EIS display. The Fuel Computer/Totalizer is accessed through
the Menu. The fuel computer function provides computation and display of
estimated fuel remaining, range, endurance, endurance at destination, fuel at
destination, efficiency, and fuel used. The fuel computer calculates these values
using the engine fuel flow sensor, ground speed, flight plan, and estimated fuel
remaining. Estimated fuel remaining is independent of the measured fuel
quantity shown on the fuel quantity gauges.
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190-01717-B2 Rev. 3
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CAUTION
The fuel computer calculates the remaining fuel based on
the initial fuel value entered by the pilot. The estimated
fuel remaining is derived by the fuel computer by
subtracting the measured fuel flow from the initial fuel
entry. Fuel quantity indications shown on the fuel gauges
may not provide the accuracy required for determination of
estimated fuel remaining values. “TAB” and “FULL”
buttons are available to aid the pilot in entering the initial
estimated fuel. It is the responsibility of the pilot to ensure
that the estimated fuel quantity value is accurate.
User calibration of the fuel flow measurements used for the fuel computer is
provided. The fuel flow calibration function compares the estimated fuel used
determined by the fuel computer with the actual fuel used determined by the
pilot when refueling. Using these inputs, the system develops a fuel flow
correction factor which will be applied to future fuel flow calculations.
Calibration offset is limited to ±15% of the K-Factor.
7.19.9 Engine Advisories
Engine advisories can be configured by the pilot from the Engine Menu to
provide notifications to the pilot via an Advisory notification when the pilot
configured threshold has been exceeded. These thresholds are determined solely
by the pilot are have no effect on the display of EIS operating range indications
or gauge alerting and are not shown on the EIS page in any way.
The following parameters may be configured by the pilot to provide advisories:
Piston Powered Aircraft
High CHT
Low Oil TEMP
High Oil TEMP
CHT Cooling Rate
EGT DIFF
Low Endurance
Low EST Fuel Remaining
Low Bus Voltage
High Bus Voltage
Low Battery Voltage
High Battery Voltage
High TIT
Turboprop Powered Aircraft
Low Oil TEMP
High Oil TEMP
Low Endurance
Low EST Fuel Remaining
Low Bus Voltage
High Bus Voltage
Low Battery Voltage
High Battery Voltage
Table 7-2: Available Engine Advisories
7.19.10 Flight and Engine Hour Meter
The Flight/Engine Hour Meter can be accessed from the Engine Menu. The
flight hour meter will increment in tenth of an hour resolution when the aircraft
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is in the air and the engine hour meter will increment in tenth of an hour
resolution when any engine is running. On multi-engine aircraft, the engine hour
meter will start incrementing when either engine is running.
Flight Stream 510 (Optional)
The Flight Stream product line uses a wireless transceiver to provide data to and
from a GTN to personal electronic devices (PEDs). The Flight Stream 510 is
mounted in the GTN SD card slot and includes a Bluetooth and Wi-Fi
transceiver.
Data such as traffic, datalink weather, entertainment audio information, and
attitude information is sent from the Flight Stream to the PED. The PED is
capable of sending databases to the Flight Stream which will then be available
on the GTN. Limitations regarding database operations are found in Section
2.31.
Garmin provides a list of tested and compatible devices that can be used with the
Flight Stream. Connection to the Flight Stream may be possible with devices
other than those on the supported device list, but Bluetooth® and/or Wi-Fi
stability and wireless data integrity cannot be guaranteed.
For details about the Garmin supported devices and apps for use with the Flight
Stream product line, please visit: http://garmin.com/connext/supported_devices
European Visual Reporting Points
If the TXi is interfaced to a GTN, and a flight plan contains a visual reporting
point (VRP), the TXi must have a database that contains the VRP in order to
appropriately display the VRP. If the database on the TXi does not contain the
VRP, the VRP will display on the MFD map as an intersection.
Database Provided Altitudes
When the TXi displays altitude data for waypoints included in IFR procedures,
the altitudes provided are those shown on the procedure chart for “Turbojet” or
“Jet” aircraft. If altitudes for other aircraft such as “Turboprop” or “Prop” are
required, the crew must manually edit the waypoint altitude on the GTN
navigator.
Cycle Counter / Landings Counter
The TXi can count takeoff and landing cycles along with engine cycles when
EIS is included in the TXi system. The cycle information is based on the system
detection of takeoffs, landings, and engine starts. The cycle counter is available
in the System menu of the TXi.
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