Garmin Pilatus PC-6 Pilot's Guide
™
Integrated Flight Deck
G950
Pilot’s Guide
Pilatus PC-6
SYSTEM OVERVIEW
FLIGHT INSTRUMENTS
ENGINE INDICATION SYSTEM
AUDIO PANEL & CNS
FLIGHT MANAGEMENT
HAZARD AVOIDANCE
AUTOMATIC FLIGHT CONTROL SYSTEM
ADDITIONAL FEATURES
APPENDICES
INDEX
Copyright © 2009, 2010 Garmin Ltd. or its subsidiaries. All rights reserved.
This manual reflects the operation of System Software version 0935.02 or later. Some differences in operation may be observed when
comparing the information in this manual to earlier or later software versions.
Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A.
Tel: 913/397.8200 Fax: 913/397.8282
Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A.
Tel: 503/391.3411 Fax: 503/364.2138
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Tel: 44/0870.8501241 Fax: 44/0870.8501251
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Tel: 886/02.2642.9199 Fax: 886/02.2642.9099
For after-hours emergency, aircraft on ground (AOG) technical support for Garmin panel mount and integrated avionics systems, please
contact Garmin’s AOG Hotline at 913.397.0836.
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®
Garmin
is a registered trademark of Garmin Ltd. or its subsidiaries, and G950™ and SafeTaxi® are trademarks of Garmin Ltd. or its
subsidiaries. These trademarks may not be used without the express permission of Garmin.
NavData
®
is a registered trademark of Jeppesen, Inc.; .S-TEC® is a registered trademark of S-TEC.
June 2010 Printed in the U.S.A
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B
LIMITED WARRANTY
LIMITED WARRANTY
This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within this
period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made
at no charge to the customer for parts and labor, provided that the customer shall be responsible for any transportation cost. This warranty
does not cover failures due to abuse, misuse, accident, or unauthorized alterations or repairs.
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED
OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR
PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO
STATE.
IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER
RESULTING FROM THE USE, MISUSE, OR INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not
allow the exclusion of incidental or consequential damages, so the above limitations may not apply to you.
Garmin retains the exclusive right to repair or replace the unit or software, or to offer a full refund of the purchase price, at its sole
discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.
Products sold through online auctions are not eligible for rebates or other secial offers from Garmin. Online auction confirmations are not
accepted for warranty verification. To obtain warranty service, an original copy of the sales receipt from the original retailer is required.
Garmin will not replace missing components from any package purchased through an online auction.
To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center, visit the Garmin
website at
Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A.
Toll free: 800/800.1020 Tel: 913/397.8200 Fax: 913/397.8282
Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A.
Toll free: 800/525.6726 Tel: 503/391.3411 Fax: 503/364.2138
Garmin (Europe) Ltd., Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K
Toll free (within U.K.): 0808 238 0000 Tel: 44/0870.8501241 Fax: 44/0870.8501251
www.garmin.com
or contact Garmin Customer Service at one of the numbers listed below:
Refer to the G950 Installation Manual for warranty registration instructions.
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
i
WARNINGS, CAUTIONS, AND NOTES
WARNING:
Navigation and terrain separation must NOT be predicated upon the use of the terrain avoidance
feature. The terrain avoidance feature is NOT intended to be used as a primary reference for terrain avoidance
and does not relieve the pilot from the responsibility of being aware of surroundings during flight. The
terrain avoidance feature is only to be used as an aid for terrain avoidance. Terrain data is obtained from
third party sources. Garmin is not able to independently verify the accuracy of the terrain data.
WARNING:
The displayed minimum safe altitudes (MSAs) are only advisory in nature and should not be
relied upon as the sole source of obstacle and terrain avoidance information. Always refer to current
aeronautical charts for appropriate minimum clearance altitudes.
WARNING:
The altitude calculated by G950 GPS receivers is geometric height above Mean Sea Level and
could vary significantly from the altitude displayed by pressure altimeters, such as the GDC 74A Air Data
Computer, or other altimeters in aircraft. GPS altitude should never be used for vertical navigation. Always
use pressure altitude displayed by the G950 PFD or other pressure altimeters in aircraft.
WARNING:
Do not use outdated database information. Databases used in the G950 system must be updated
regularly in order to ensure that the information remains current. Pilots using any outdated database do so
entirely at their own risk.
WARNING:
Do not use basemap (land and water data) information for primary navigation. Basemap data is
intended only to supplement other approved navigation data sources and should be considered as an aid to
enhance situational awareness.
WARNING:
Traffic information shown on system displays is provided as an aid in visually acquiring traffic.
Pilots must maneuver the aircraft based only upon ATC guidance or positive visual acquisition of conflicting
traffic.
WARNING:
Use of the Stormscope is not intended for hazardous weather penetration (thunderstorm
penetration). Stormscope information, as displayed on the G950 MFD, is to be used only for weather
avoidance, not penetration.
WARNING:
WARNING:
For safety reasons, G950 operational procedures must be learned on the ground.
The Garmin G950, as installed in this aircraft, has a very high degree of functional integrity.
However, the pilot must recognize that providing monitoring and/or self-test capability for all conceivable
system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur
without a fault indication shown by the G950. It is thus the responsibility of the pilot to detect such
an occurrence by means of cross-checking with all redundant or correlated information available in the
cockpit.
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. Bii
WARNINGS, CAUTIONS, AND NOTES
WARNING:
The United States government operates the Global Positioning System and is solely responsible
for its accuracy and maintenance. The GPS system is subject to changes which could affect the accuracy
and performance of all GPS equipment. Portions of the Garmin G950 utilize GPS as a precision electronic
NAVigation AID (NAVAID). Therefore, as with all NAVAIDs, information presented by the G950 can be
misused or misinterpreted and, therefore, become unsafe.
WARNING:
To reduce the risk of unsafe operation, carefully review and understand all aspects of the G950
Pilot’s Guide documentation and the G950 Integrated Avionics System in the Pilatus PC-6 Pilot’s Operating
Handbook (POH). Thoroughly practice basic operation prior to actual use. During flight operations, carefully
compare indications from the G950 to all available navigation sources, including the information from
other NAVAIDs, visual sightings, charts, etc. For safety purposes, always resolve any discrepancies before
continuing navigation.
WARNING
:
The illustrations in this guide are only examples. Never use the G950 to attempt to penetrate
a thunderstorm. Both the FAA Advisory Circular, Subject: Thunderstorms, and the Aeronautical Information
Manual (AIM) recommend avoiding “by at least 20 miles any thunderstorm identified as severe or giving an
intense radar echo.”
WARNING:
Lamp(s) inside this product may contain mercury (HG) and must be recycled or disposed of
according to local, state, or federal laws. For more information, refer to our website at www.garmin.com/
aboutGarmin/environment/disposal.jsp.
WARNING:
Because of variation in the earth’s magnetic field, operating the G950 within the following areas
could result in loss of reliable attitude and heading indications. North of 72° North latitude at all longitudes;
South of 70° South latitude at all longitudes; North of 65° North latitude between longitude 75° W and
120° W. (Northern Canada); North of 70° North latitude between longitude 70° W and 128° W. (Northern
Canada); North of 70° North latitude between longitude 85° E and 114° E. (Northern Russia); South of 55°
South latitude between longitude 120° E and 165° E. (Region south of Australia and New Zealand)
WARNING:
Do not use GPS to navigate to any active waypoint identified as a ‘NON WGS84 WPT’ by a
system message. ‘NON WGS84 WPT’ waypoints are derived from an unknown map reference datum that
may be incompatible with the map reference datum used by GPS (known as WGS84) and may be positioned
in error as displayed.
CAUTION:
The GDU 1040 PFD and GDU 1040 MFD displays use a lens coated with a special anti-reflective
coating that is very sensitive to skin oils, waxes, and abrasive cleaners. CLEANERS CONTAINING AMMONIA
WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free
cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective coatings.
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
iii
WARNINGS, CAUTIONS, AND NOTES
CAUTION:
The Garmin G950 does not contain any user-serviceable parts. Repairs should only be made by
an authorized Garmin service center. Unauthorized repairs or modifications could void both the warranty
and the pilot’s authority to operate this device under FAA/FCC regulations.
NOTE:
All visual depictions contained within this document, including screen images of the G950 panel and
displays, are subject to change and may not reflect the most current G950 system. Depictions of equipment
may differ slightly from the actual equipment.
NOTE
:
This device complies with part 15 of the FCC Rules. Operation is subject to the following two conditions:
(1) this device may not cause harmful interference, and (2) this device must accept any interference received,
including interference that may cause undesired operation.
NOTE
:
Interference from GPS repeaters operating inside nearby hangars can cause an intermittent loss of
attitude and heading displays while the aircraft is on the ground. Moving the aircraft more than 100 yards
away from the source of the interference should alleviate the condition.
NOTE
:
Use of polarized eyewear may cause the flight displays to appear dim or blank.
NOTE
:
This product, its packaging, and its components contain chemicals known to the State of California
to cause cancer, birth defects, or reproductive harm. This notice is being provided in accordance with
California’s Proposition 65. If you have any questions or would like additional information, please refer to
our web site at www.garmin.com/prop65.
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. Biv
REVISION INFORMATION
Record of Revisions
Part Number Revision Date Page Range Description
190-00870-00 A 12/1/09 i – I-6 Initial release for 9.15 software.
190-00870-00 B 6/11/10 i – I-6 Revised to add the following optional functionality:
• TAWS-B
• KTA 870
• WX 500
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
v
TABLE OF CONTENTS
SECTION 1 SYSTEM OVERVIEW
1.1 Line Replaceable Units ........................................... 2
1.2 Secure Digital (SD) Cards ....................................... 7
1.3 System Power-up ..................................................... 8
.4 System Operation .................................................... 9
1
Display Operation ......................................................... 9
G950 System Annunciations ........................................ 10
System Status ............................................................. 11
AHRS Operation .........................................................13
GPS Receiver Operation ..............................................14
1.5 G950 Controls ........................................................19
PFD/MFD Controls ...................................................... 19
Softkey Function ......................................................... 21
1.6 Accessing G950 Functionality .............................. 27
Menus ....................................................................... 27
Data Entry.................................................................. 27
Page Groups .............................................................. 29
System Settings .......................................................... 33
System Utilities ........................................................... 41
1
.7 Display Backlighting ............................................. 45
SECTION 2 FLIGHT INSTRUMENTS
2.1 Flight Instruments ................................................. 50
Airspeed Indicator ......................................................50
Attitude Indicator ....................................................... 52
Altimeter ................................................................... 53
Vertical Speed Indicator (VSI) ....................................... 56
Vertical Deviation ....................................................... 56
Horizontal Situation Indicator (HSI) ..............................57
Course Deviation Indicator (CDI) .................................. 62
2.2 Supplemental Flight Data ....................................69
Outside Air Temperature ..............................................69
Wind Data .................................................................70
Vertical Navigation (VNV) Indications ...........................71
2.3 PFD Annunciations and Alerting Functions ........ 72
System Alerting .......................................................... 72
Marker Beacon Annunciations...................................... 73
Traffic Annunciation .................................................... 73
TAWS Annunciations ................................................... 74
Altitude Alerting .........................................................74
Low Altitude Annunciation .......................................... 75
Minimum Descent Altitude/Decision Height Alerting ...... 75
2.4 Abnormal Operations ...........................................77
Abnormal GPS Conditions ...........................................77
Unusual Attitudes .......................................................78
SECTION 3 ENGINE INDICATION SYSTEM
3.1 Engine Display ....................................................... 80
3.2 System Display ......................................................82
3.3 Fuel Display ............................................................ 84
3.4 EIS Display in Reversionary Mode ....................... 86
EIS Softkeys ...............................................................87
SECTION 4 AUDIO PANEL AND CNS
4.1 Overview ................................................................ 89
PFD Controls and Frequency Display ............................. 90
GMA 347 Audio Panel Controls .................................... 92
4.2 COM Operation ...................................................... 94
COM Transceiver Selection and Activation ..................... 94
COM Transceiver Manual Tuning .................................. 95
Quick-tuning and Activating 121.500 MHz .................... 96
Auto-tuning the COM Frequency ..................................97
Auto-tuning from the MFD .......................................... 98
Frequency Spacing ....................................................101
Automatic Squelch .................................................... 102
Volume .................................................................... 102
4.3 NAV Operation .....................................................103
NAV Radio Selection and Activation ........................... 103
NAV Receiver Manual Tuning .....................................104
Auto-tuning a NAV Frequency from the MFD ............... 106
Auto-tuning NAV Frequencies on Approach Activation . 110
Marker Beacon Receiver ............................................ 111
4.4 GTX 33 Mode S Transponder .............................. 112
Transponder Controls ................................................ 112
Transponder Mode Selection ...................................... 113
Entering a Transponder Code ..................................... 115
IDENT Function ........................................................116
Flight ID Reporting.................................................... 117
4.5 Additional Audio Panel Functions ..................... 118
Power-Up ................................................................. 118
Mono/Stereo Headsets .............................................. 118
Speaker ................................................................... 118
Intercom .................................................................. 119
Passenger Address (PA) System .................................. 121
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. Bvi
TABLE OF CONTENTS
Clearance Recorder and Player ................................... 121
Split COM Operation ................................................. 122
Entertainment Inputs ................................................ 123
Multifunction Controls .............................................. 124
4.6 Audio Panel Preflight Procedure ....................... 125
4.7 Abnormal Operation ........................................... 126
Stuck Microphone ..................................................... 126
COM Tuning Failure ...................................................126
Audio Panel Fail-safe Operation .................................126
PFD Failure (Reversionary Mode) ............................... 126
SECTION 5 FLIGHT MANAGEMENT
5.1 Introduction ......................................................... 127
Navigation Status Box ............................................... 129
5.2 Using Map Displays ............................................. 130
Map Orientation .......................................................130
Map Range .............................................................. 132
Map Panning ............................................................134
Measuring Bearing and Distance ................................ 139
Topography ..............................................................140
Map Symbols ........................................................... 143
Airways ................................................................... 149
Track Vector .............................................................151
Wind Vector ............................................................. 152
Nav Range Ring........................................................ 153
Fuel Range Ring ....................................................... 154
5.3 Waypoints .............................................................155
Airports ................................................................... 156
Intersections ............................................................162
NDBs .......................................................................164
VORs ....................................................................... 166
User Waypoints ........................................................ 168
5.4 Airspaces .............................................................. 174
5.5 Direct-to-Navigation .......................................... 178
5.6 Flight Planning ..................................................... 185
Flight Plan Creation .................................................. 186
Adding Waypoints to an Existing Flight Plan ................191
Adding Airways to a Flight Plan .................................193
Adding Procedures to a Stored Flight Plan ..................196
Flight Plan Storage ...................................................203
Flight Plan Editing ....................................................205
Along Track Offsets ................................................... 208
Parallel Track ............................................................210
Activating a Flight Plan Leg ....................................... 213
Inverting a Flight Plan ............................................... 214
Flight Plan Views ...................................................... 215
Closest Point of FPL .................................................. 217
5.7 Vertical Navigation ............................................. 218
Altitude Constraints ..................................................220
5.8 Procedures ...........................................................224
Departures ............................................................... 224
Arrivals ...................................................................227
Approaches .............................................................229
5.9 Trip Planning ........................................................ 235
Trip Planning ............................................................ 235
5.10 RAIM Prediction................................................... 239
5.11 Navigating a Flight Plan .....................................243
5.12 Abnormal Operation ........................................... 271
SECTION 6 HAZARD AVOIDANCE
6.1 Airborne Color Weather Radar ..........................273
System Description ................................................... 273
Principles of Pulsed Airborne Weather Radar ............... 274
Safe Operating Distance ............................................278
Basic Antenna Tilt Setup ............................................ 278
Weather Mapping and Interpretation .........................280
Ground Mapping and Interpretation ...........................292
6.2 WX-500 Stormscope ...........................................293
Setting Up Stormscope on the Navigation Map ...........293
Selecting the Stormscope Page .................................. 298
6.3 Terrain Proximity ................................................. 299
Displaying Terrain Proximity Data ............................... 300
Terrain Proximity Page ...............................................302
6.4 TAWS-B .................................................................304
Displaying TAWS-B Data ............................................305
TAWS-B Page ........................................................... 308
TAWS-B Alerts .......................................................... 310
System Status ........................................................... 316
6.5 Traffic Information Service (TIS) ........................ 318
Displaying TRAFFIC Data ........................................... 319
Traffic Map Page .......................................................322
TIS Alerts ................................................................. 323
System Status ........................................................... 324
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
vii
TABLE OF CONTENTS
6.6 Traffic Advisory System (TAS)............................. 327
TAS Symbology ......................................................... 327
Operation ................................................................ 328
Altitude Display ........................................................331
Traffic Map Page Display Range ................................. 331
TAS Alerts ................................................................ 333
System Status ........................................................... 333
SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM
7.1 S-TEC Fifty Five X Autopilot (Optional) ............ 335
Flight Director Mode Annunciation ............................. 335
Altitude Preselect .....................................................335
SECTION 8 ADDITIONAL FEATURES
8.1 SafeTaxi ................................................................ 337
SafeTaxi Database Cycle Number and Revision ............ 340
8.2 Scheduler .............................................................. 343
APPENDICES
Annunciations and Alerts ............................................. 345
G950 System Message Advisories .............................. 351
Flight Plan Import/Export Messages ...........................359
TAWS ALERTS ...........................................................360
SD Card Use and Databases
Jeppesen Databases .................................................. 363
......................................... 363
Glossary .......................................................................... 367
Frequently Asked Questions ........................................ 375
General TIS Information ............................................... 379
Map Symbols ................................................................. 381
INDEX
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. Bviii
SYSTEM OVERVIEW
SECTION 1 SYSTEM OVERVIEW
The G950 Integrated Flight Deck System presents flight instrumentation, position, navigation, communication,
and identification information to the pilot using flat-panel color displays. The system is distributed across the
following Line Replaceable Units (LRUs):
•
GDU 1040
•
GDU 1040
Primary Flight Display (PFD)
Multi Function Display (MFD)
GDC 74A
•
•
GTX 33
Air Data Computer (ADC)
Mode S Transponder
OVERVIEW
SYSTEM
INSTRUMENTS
FLIGHT
•
GMA 347
Receiver
•
GIA 63W
Audio Panel with Integrated Marker Beacon
Integrated Avionics Units (IAU)
•
GRS 77
(AHRS)
•
GMU 44
Attitude and Heading Reference System
Magnetometer
Figure 1-1 shows interactions between the LRUs. Additional/optional equipment are shown in Figure 1-2. The
G950 is capable of interfacing with the following optional equipment:
GWX 68
•
Weather Radar
•S-TEC 55X Autopilot
•
KTA 870
•
WX 500
Traffic System
Lightning Detection System
EIS
AUDIO PANEL
& CNS
MANAGEMENT
FLIGHT
AVOIDANCE
HAZARD
AFCS
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
1
ADDITIONAL
FEATURES
APPENDICES INDEX
SYSTEM OVERVIEW
1.1 LINE REPLACEABLE UNITS
SYSTEM
OVERVIEW
FLIGHT
INSTRUMENTS
EIS
& CNS
AUDIO PANEL
•GDU 1040 (2) – The left-hand GDU is configured as a Primary Flight Display (PFD) and the right-hand GDU
as a Multi Function Display (MFD). Both feature 10.4-inch LCD screens with 1024 x 768 resolution. The
displays communicate with each other through a High-Speed Data Bus (HSDB) Ethernet connection. Each
display is also paired with an Ethernet connection to an IAU.
•
GMA 347
(1) – The Audio Panel integrates navigation/communication radio (NAV/COM) digital audio, intercom,
and marker beacon controls, and is installed between the displays. This unit communicates with both IAUs
using an RS-232 digital interface.
FLIGHT
MANAGEMENT
HAZARD
AVOIDANCE
•GIA 63W (2) – The Integrated Avionics Units (IAU) function as the main communication hubs, linking all
AFCS
FEATURES
ADDITIONAL
APPENDICESINDEX
LRUs with the on-side display. Each IAU contains a GPS WAAS receiver, VHF COM/NAV/GS receivers, and
system integration microprocessors, and is paired with the on-side display via HSDB connection. The IAUs are
not paired together and do not communicate with each other directly.
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B2
SYSTEM OVERVIEW
•
GDC 74A (1)
temperature (OAT) sensor. The ADC provides pressure altitude, airspeed, vertical speed, and OAT information
to the G950 System, and it communicates with the primary IAU, displays, and AHRS using an ARINC 429
digital interface.
•
GEA 71
sensors. This unit communicates with both IAUs using an RS-485 digital interface.
– The Air Data Computer (ADC) processes data from the pitot/static system and outside air
(1) – (optional) The Engine Airframe Unit receives and processes signals from the engine and airframe
OVERVIEW
SYSTEM
INSTRUMENTS
FLIGHT
EIS
AUDIO PANEL
& CNS
MANAGEMENT
FLIGHT
•
GTX 33 (1)
– The solid-state Transponder provides Modes A, C, and S capability and communicates with both
IAUs through an RS-232 digital interface.
•
GRS 77 (1)
– The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading
information via ARINC 429 to both PFDs and the primary IAU. The AHRS contains advanced sensors (including
accelerometers and rate sensors) and interfaces with the Magnetometer to obtain magnetic field information,
with the ADC to obtain air data, and with both IAUs to obtain GPS information. AHRS operation is discussed
in Section 1.4, System Operation.
AVOIDANCE
HAZARD
AFCS
ADDITIONAL
FEATURES
APPENDICES INDEX
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
3
SYSTEM OVERVIEW
•
GMU 44 (1)
SYSTEM
OVERVIEW
FLIGHT
INSTRUMENTS
EIS
& CNS
AUDIO PANEL
determine aircraft magnetic heading. This unit receives power directly from the AHRS and communicates with
it via an RS-485 digital interface.
•
GWX 68
(1) – (optional) Provides airborne weather and ground mapped radar data to the MFD, through the
GDL 69A, via HSDB connection.
– The Magnetometer measures local magnetic field and sends data to the AHRS for processing to
FLIGHT
MANAGEMENT
HAZARD
AVOIDANCE
AFCS
FEATURES
ADDITIONAL
APPENDICESINDEX
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B4
SYSTEM OVERVIEW
GTX 33
Tr ansponder
GEA 71
Engine/Airframe
Unit
GDC 74A
Air Data
Computer
OAT
Airspeed
Altitude
Ve rtical Speed
GMU 44
Magnetometer
Heading
GMA 347
Audio Panel
G
C
V
e
r
d
No. 2 GIA 63W
Integrated Avionics Unit
System Integration Processors
I/O Processors
VHF COM
VHF NAV/LOC
GPS
Glideslope
GPS Output
No. 1 GIA 63W
Integrated Avionics Unit
System Inegration Processors
I/O Processors
VHF COM
VHF NAV/LOC
GPS
Glideslope
GPS Output
GRS 77
AHRS
Attitude
Rate of Tu rn
Slip/Skid
GDU 1040
Primary Flight Display
GDU 1040
Multi Function Display
Display Backup
Button
OVERVIEW
SYSTEM
INSTRUMENTS
FLIGHT
EIS
AUDIO PANEL
& CNS
MANAGEMENT
FLIGHT
Figure 1-1 Basic G950 Block Diagram
AVOIDANCE
HAZARD
AFCS
ADDITIONAL
FEATURES
APPENDICES INDEX
190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
5
SYSTEM OVERVIEW
KN 63
DME
(optional)
KR 87
ADF
(optional)
WX 500
Stormscope
(optional)
KTA 870
TA S
(optional)
No. 1 GIA 63W
Integrated Avionics Unit
System Integration Processors
I/O Processors
VHF COM
VHF NAV/LOC
GPS
Glideslope
No. 2 GIA 63W
Integrated Avionics Unit
System Integration Processors
I/O Processors
VHF COM
VHF NAV/LOC
GPS
Glideslope
GWX 68
Weather Radar
(optional)
SYSTEM
OVERVIEW
FLIGHT
INSTRUMENTS
EIS
& CNS
AUDIO PANEL
FLIGHT
MANAGEMENT
HAZARD
AVOIDANCE
AFCS
FEATURES
ADDITIONAL
APPENDICESINDEX
Figure 1-2 G950 With Optional/Additional Equipment
NOTE:
For information on non-Garmin optional/additional equipment shown in Figure 1-2, consult the
applicable optional interface user’s guide. This document assumes that the reader is already familiar with
the operation of this additional equipment.
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B6
SYSTEM OVERVIEW
1.2 SECURE DIGITAL (SD) CARDS
NOTE:
Ensure the G950 System is powered off before inserting an SD card.
NOTE:
Refer to Appendix B for instructions on updating the aviation database.
The PFD and MFD data card slots use Secure Digital (SD) cards and are located on the upper right side of the
display bezels. Each display bezel is equipped with two SD card slots. SD cards are used for aviation database
and system software updates as well as terrain database storage.
Installing an SD card:
1) Insert the SD card in the SD card slot (the front of the card should be flush with the face of the display bezel).
2) To eject the card, gently press on the SD card to release the spring latch.
OVERVIEW
SYSTEM
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SD Card Slots
Figure 1-3 Display Bezel SD Card Slots
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Garmin G950 Pilot’s Guide for the Pilatus PC-6
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SYSTEM OVERVIEW
1.3 SYSTEM POWER-UP
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busses. The PFD, MFD, and supporting sub-systems include both power-on and continuous built-in test features
that exercise the processor, RAM, ROM, external inputs, and outputs to provide safe operation.
should disappear typically within the first minute of power-up. Upon power-up, key annunciator lights also
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become momentarily illuminated on the Audio Panel, the MFD Control Unit, and the display bezels.
display valid attitude and heading fields typically within the first minute of power-up. The AHRS can align itself
both while taxiing and during level flight.
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AUDIO PANEL
•Systemversion
•Copyright
•Landdatabasenameandversion
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•SafeTaxidatabaseinformation(seeAdditionalFeatures)
•Terrain,AirportTerrain,Obstacle,andAviationdatabasename,version,andeffectivedates
NOTE:
Refer to Appendix A for system-specific annunciations and alerts.
The G950 System is integrated with the aircraft electrical system and receives power directly from electrical
During system initialization, test annunciations are displayed, as shown in Figure 1-4. All system annunciations
On the PFD, the AHRS begins to initialize and displays “AHRS ALIGN: Keep Wings Level”. The AHRS should
When the MFD powers up, the Power-up screen (Figure 1-5) displays the following information:
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information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to
continue.
displayed upon pressing the key a second time. When the system has acquired a sufficient number of satellites to
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APPENDICESINDEX
determine a position, the aircraft’s current position is shown on the Navigation Map Page.
Current database information includes valid operating dates, cycle number, and database type. When this
Pressing the ENT Key (or right-most softkey) acknowledges this information, and the Navigation Map Page is
Figure 1-4 PFD Initialization Figure 1-5 Example MFD Power-up Screen
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B8
1.4 SYSTEM OPERATION
SYSTEM OVERVIEW
OVERVIEW
SYSTEM
NOTE:
The G950 system alerts the pilot when backup paths are utilized by the LRUs. Refer to the Appendices
for further information regarding system-specific alerts.
The displays are connected together via a single Ethernet bus for high-speed communication. As shown in
Figure 1-1, each IAU is connected to the on-side display. This section discusses normal and reversionary G950
display operation, AHRS modes, GPS receiver operation, and G950 System Annunciations.
DISPLAY OPERATION
NOTE:
In normal operating mode, backlighting can only be adjusted from the PFD (see Section 1.7). In
reversionary mode, it can be adjusted from the remaining display(s).
In normal operating mode, the PFD presents graphical flight instrumentation (attitude, heading, airspeed,
altitude, vertical speed), replacing the traditional flight instrument cluster (see the Flight Instruments Section
for more information). The MFD normally displays a full-color moving map with navigation information (see
the Flight Management Section), while the left portion of the MFD is dedicated to the Engine Indication System
(see the EIS Section). Both displays offer control for COM and NAV frequency selection.
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In the event of a display failure, the G950 System automatically switches to reversionary (backup) mode. In
reversionary mode, all important flight information is presented on the remaining display(s) in the same format
as in normal operating mode.
•
PFD failure
MFD failure
•
If a display fails, the appropriate IAU-display Ethernet interface is cut off. Thus, the IAU can no longer
communicate with the remaining display (refer to Figure 1-1), and the NAV and COM functions provided to
the failed display by the IAU are flagged as invalid on the remaining display. The system reverts to backup
paths for the AHRS, ADC, Engine/Airframe Unit, and Transponder, as required. The change to backup paths is
completely automated for all LRUs and no pilot action is required.
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Figure 1-6 G950 System Normal Operation
– MFD enters reversionary mode.
– PFD enters reversionary mode.
Garmin G950 Pilot’s Guide for the Pilatus PC-6
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SYSTEM OVERVIEW
If the system fails to detect a display problem, reversionary mode may be manually activated by pressing the
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display backup button installed in the cockpit. Pressing this button again deactivates reversionary mode.
NAV1 and COM1 (provided by the
failed PFD) Flagged Invalid
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GIA 63W Integrated
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Figure 1-7 G950 Reversionary Mode (Failed PFD)
G950 SYSTEM ANNUNCIATIONS
When an LRU or an LRU function fails, a large red ‘X’ is typically displayed over the instrument experiencing
failed data (Figure 1-8 displays all possible flags and responsible LRUs). Upon G950 power-up, certain
instruments remain invalid as equipment begins to initialize. All instruments should be operational within one
minute of power-up. If any instrument remains flagged, the G950 should be serviced by a Garmin-authorized
repair facility.
GIA 63W Integrated
Avionics Units
GEA 71 Engine
Airframe Unit
OR
Avionics Unit
Avionics Units
GDC 74A Air
Data Computer
GRS 77 AHRS
OR
GMU 44
Magnetometer
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GDC 74A Air
Data Computer
Figure 1-8 G900X System Failure Annunciations
Garmin G950 Pilot’s Guide for the Pilatus PC-6
GIA 63W Integrated
Avionics Units
GTX 33 Transponder
OR
GIA 63W Integrated
Avionics Units
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SYSTEM OVERVIEW
SYSTEM STATUS
The System Status Page displays the statuses, serial numbers, and software version numbers for all detected
system LRUs. Active LRUs are indicated by green check marks; failed, by red ‘X’s. Failed LRUs should be noted
and a service center or Garmin-authorized dealer informed.
Viewing LRU information:
1) Use the FMS Knob to select the AUX - System Status Page.
2) To place the cursor in the ‘LRU Info’ Box,
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a) Press the LRU Softkey.
Or:
a) Press the MENU Key.
b) With ‘Select LRU Window’ highlighted, press the ENT Key.
3) Use the FMS Knob to scroll through the box to view LRU status information.
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Figure 1-9 Example System Status Page
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SYSTEM OVERVIEW
Pertinent information on all system databases is also displayed on this page. Refer to the Appendices and
SYSTEM
OVERVIEW
Additional Features sections for more information about databases.
Viewing database information:
1) Use the FMS Knob to select the AUX - System Status Page.
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2) To place the cursor in the ‘Database’ Box,
a) Press the DBASE Softkey.
Or:
a) Press the MENU Key.
b) Highlight ‘Select Dbase Window’ and press the ENT Key.
3) Use the FMS Knob to scroll through the box to view database status information.
The G950 uses aural tones to convey the priority of airframe-specific alerts. The alerting system’s annunciation
tone may be tested from the System Status Page. Refer to the Appendices for airframe-specific alerts.
Testing the system annunciation tone:
1) Use the FMS Knob to select the AUX - System Status Page.
2) Press the ANN TEST Softkey.
Or:
a) Press the MENU Key.
b) Highlight ‘Enable Annunciator Test Mode’ and press the ENT Key.
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AHRS OPERATION
Attitude/Heading Invalid
AHRS
no-GPS
Mode
AHRS Normal
Operation
AHRS no-
Mag Mode
AHRS no-Mag/
no-Air Mode
Heading Invalid
available
available
unavailable
unavailable
available
unavailable
unavailable
available
Air Data
Magnetometer Data
unavailable
available
GPS Data
Magnetometer Data
Air Data
SYSTEM OVERVIEW
OVERVIEW
SYSTEM
NOTE:
Aggressive maneuvering while AHRS is not operating normally may degrade AHRS accuracy.
The Attitude and Heading Reference System (AHRS) performs attitude, heading, and vertical acceleration
calculations for the G950 System, utilizing GPS, magnetometer, and air data in addition to information from its
internal sensors. Attitude and heading information are updated on the PFD while the AHRS receives appropriate
combinations of information from the external sensor inputs.
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Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts. Any
failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red
‘X’ flags over the corresponding flight instruments).
Two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses
the remaining GPS input and an alert message is issued to inform the pilot. If both GPS inputs fail, the AHRS
can continue to provide attitude and heading information to the PFD as long as magnetometer and airspeed
data are available and valid.
If the magnetometer input fails, the AHRS continues to output valid attitude information; however, the
heading output on the PFD is flagged as invalid with a red ‘X’.
Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information.
Invalid/unavailable airspeed data in addition to GPS failure results in loss of all attitude and heading
information.
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Garmin G950 Pilot’s Guide for the Pilatus PC-6
Figure 1-10 AHRS Operation
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SYSTEM OVERVIEW
GPS RECEIVER OPERATION
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Each Integrated Avionics Unit (IAU) contains a GPS receiver. Internal system checking is performed to
ensure both GPS receivers are providing accurate data to the PFD. When both GPS receivers are providing
accurate data, the GPS receiver producing the better solution is used by the system. Information collected by
the specified receiver (GPS1 for the #1 IAU or GPS2 for the #2 IAU) may be viewed on the AUX - GPS Status
Page.
Viewing GPS receiver status information:
1) Use the large FMS Knob on the MFD to select the Auxiliary Page Group (see Section 1.6 for information on
navigating MFD page groups).
2) Use the small FMS Knob to select GPS Status Page (third page in the AUX Page Group).
3) To change the selected GPS receiver:
Press the desired
GPS
Softkey.
Or:
a) Press the MENU Key.
b) Use the FMS Knob to highlight the receiver which is not selected and press the ENT Key.
Satellite Constellation
Diagram
Satellite Signal
Information
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GPS
Receiver
Status
RAIM
Availability
Prediction
Satellite
Signal
Strength
Bars
Figure 1-11 GPS Status Page
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B14
SYSTEM OVERVIEW
GPS sensor annunciations are most often seen after system power-up when one GPS receiver has acquired
satellites before the other or one of the GPS receivers has not yet acquired an SBAS signal. While the aircraft
is on the ground, the SBAS signal may be blocked by obstructions causing one GPS receiver to have difficulty
acquiring a good signal. Also, while airborne, turning the aircraft may result in one of the GPS receivers
temporarily losing the SBAS signal. If no failure message exists, check the GPS Status Page and compare the
information for GPS1 and GPS2. Discrepancies may indicate a problem.
GPS RECEIVER STATUS
The GPS solution type (ACQUIRING, 2D NAV, 2D DIFF NAV, 3D NAV, 3D DIFF NAV) for the active
GPS receiver (GPS1 or GPS2) is shown in the upper right of the GPS Status Page. When the receiver is
in the process of acquiring enough satellite signals for navigation, the receiver uses satellite orbital data
(collected continuously from the satellites) and last known position to determine the satellites that should be
in view. ACQUIRING is indicated as the solution until a sufficient number of satellites have been acquired
for computing a solution.
When the receiver is in the process of acquiring a 3D differential GPS solution, 3D NAV is indicated as the
solution until the 3D differential fix has finished acquisition. Satellite-Based Augmentation System (SBAS)
status should be indicated as INACTIVE at this point. When acquisition is complete, the solution status
changes to 3D DIFF NAV and SBAS becomes active.
•SBASSelection(SBAS Softkey is pressed)
In certain situations, such as when the aircraft is outside or on the fringe of the SBAS coverage area, it may
be desirable to disable WAAS or MSAS (although it is not recommended). When disabled, the SBAS field in
the GPS Status box indicates DISABLED. There may be a small delay for the GPS Status box to be updated
upon WAAS and MSAS enabling/disabling.
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Disabling WAAS or MSAS
1) Select the GPS Status Page.
2) If necessary, press the SBAS Softkey.
3) Press the
FMS
Knob
, and turn the large FMS Knob to hightlight ‘MSAS’ or ‘WAAS’.
4) Press the ENT Key to uncheck the box.
5) Press the FMS Knob to remove the cursor
Figure 1-12 Enable/Disable SBAS
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190-00870-00 Rev. B
Garmin G950 Pilot’s Guide for the Pilatus PC-6
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SYSTEM OVERVIEW
RAIM PREDICTION
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Receiver Autonomous Integrity Monitoring (RAIM) is a GPS receiver function that performs a consistency
check on all tracked satellites. RAIM ensures that the available satellite geometry allows the receiver to
calculate a position within a specified RAIM protection limit (2.0 nautical miles for oceanic and enroute, 1.0
nm for terminal, and 0.3 nm for non-precision approaches). During oceanic, enroute, and terminal phases of
flight, RAIM is available nearly 100% of the time.
The RAIM prediction function also indicates whether RAIM is available at a specified date and time. RAIM
computations predict satellite coverage within ±15 min of the specified arrival date and time. In most cases
performing RAIM prediction is not necessary. However, in some cases, the selected approach may be outside
the WAAS coverage area and it may be necessary to perform a RAIM prediction for the intended approach.
Because of the tighter protection limit on approaches, there may be times when RAIM is not available. The
G950 automatically monitors RAIM and warns with an alert message when it is not available. If RAIM is not
predicted to be available for the final approach course, the approach does not become active, as indicated by
the messages “Approach is not active”. If RAIM is not available when crossing the FAF, the missed approach
procedure must be flown.
Predicting RAIM availability:
1) Select the GPS Status Page.
2) Press the RAIM Softkey.
3) Press the
FMS
Knob
. The ‘WAYPOINT’ field is highlighted.
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4) Turn the small FMS Knob to display the Waypoint Information Window.
5) Enter the desired waypoint:
a) Use the FMS Knob to enter the desired waypoint by identifier, facility, or city name and press the ENT Key. Refer
to Section 1.7 for instructions on entering alphanumeric data into the G950.
Or:
a) Turn the small FMS Knob counter-clockwise to display a list of flight plan waypoints (the FPL list is populated
only when navigating a flight plan).
b) Turn the small FMS Knob clockwise to display the NRST, RECENT, or AIRWAY waypoints, if required.
c) Turn the large FMS Knob clockwise to select the desired waypoint. The G950 automatically fills in the identifier,
facility, and city fields with the information for the selected waypoint.
d) Press the ENT Key to accept the waypoint entry.
6) Enter an arrival time and press the ENT Key.
7) Enter an arrival date and press the ENT Key.
8) With the cursor highlighting ‘COMPUTE RAIM?’, press the ENT Key. Once RAIM availability is computed, one
of the following is displayed:
• ‘COMPUTE RAIM?’—RAIM has not been computed for the current waypoint, time, and date combination
• ‘COMPUTING AVAILABILITY’—RAIM calculation in progress
• ‘RAIM AVAILABLE’—RAIM is predicted to be available for the specied waypoint, time, and date
• ‘RAIM NOT AVAILABLE’—RAIM is predicted to be unavailable for the specied waypoint, time, and date
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Predicting RAIM availability at present position
1) Select the GPS Status Page.
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SYSTEM
2) If necessary, press the RAIM Softkey.
3) Press the
FMS
Knob
. The ‘WAYPOINT’ field is highlighted.
4) Press the MENU Key.
5) With ‘Set WPT to Present Position’ highlighted, press the ENT Key.
6) Press the ENT Key to accept the waypoint entry.
7) Use the FMS Knob to enter an arrival time and press the ENT Key.
8) Use the FMS Knob to enter an arrival date and press the ENT Key.
9) With the cursor highlighting ‘COMPUTE RAIM?’, press the ENT Key. Once RAIM availability is computed, one
of the following is displayed:
• ‘COMPUTE RAIM?’—RAIM has not been computed for the current waypoint, time, and date combination
• ‘COMPUTING AVAILABILITY’—RAIM calculation in progress
• ‘RAIM AVAILABLE’—RAIM is predicted to be available for the specied waypoint, time, and date
• ‘RAIM NOT AVAILABLE’—RAIM is predicted to be unavailable for the specied waypoint, time, and date
SATELLITE INFORMATION
Satellites currently in view are shown at their respective positions on a satellite constellation diagram.
This sky view is always oriented north-up, with the outer circle representing the horizon, the inner circle
representing 45° above the horizon, and the center point showing the position directly overhead. Each satellite
is represented by an oval containing the Pseudo-random noise (PRN) number (i.e., satellite identification
number). Satellites whose signals are currently being used are represented by solid ovals.
The GPS Status Page can be helpful in troubleshooting weak (or missing) signal levels due to poor satellite
coverage or installation problems. As the GPS receiver locks onto satellites, a signal strength bar is displayed
for each satellite in view, with the appropriate satellite PRN number (01-32 or 120-138 for WAAS) below each
bar. The progress of satellite acquisition is shown in three stages, as indicated by signal bar appearance:
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- No bar—Receiver is looking for the indicated satellite
- Hollow bar—Receiver has found the satellite and is collecting data
- Light blue bar—Receiver has collected the necessary data and the satellite signal can be used
- Green bar—Satellite is being used for the GPS solution
- Checkered bar—Receiver has excluded the satellite (Fault Detection and Exclusion)
- “D” indication—Denotes the satellite is being used as part of the differential computations
Each satellite has a 30-second data transmission that must be collected (signal strength bar is hollow) before
the satellite may be used for navigation (signal strength bar becomes solid).
Using the current satellite signal information, they system calculates the aircraft’s GPS position, time,
altitude, ground speed, and track for the aircraft (displayed below the satellite signal accuracy measurements
for reference). The following quantities denote the accuracy of the aircraft’s GPS fix:
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APPENDICES INDEX
SYSTEM OVERVIEW
•Estimated Position Uncertainty (EPU)—A statistical error indication; the radius of a circle centered on an
SYSTEM
OVERVIEW
estimated horizontal position in which actual position has 95% probability of lying
•Horizontal Dilution of Precision (HDOP)—Measures satellite geometry quality (i.e., number of satellites
received and where they are relative to each other) on a range from 0.0 to 9.9, with lower numbers denoting
better accuracy
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•HorizontalandVerticalFiguresofMerit(HFOMandVFOM)—Measuresofhorizontalandverticalposition
uncertainty; the current 95% confidence horizontal and vertical accuracy values reported by the GPS
receiver
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APPENDICESINDEX
Garmin G950 Pilot’s Guide for the Pilatus PC-6
190-00870-00 Rev. B18
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