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: [phone] Fax: [phone]

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A.
Tel: [phone] Fax: [phone]

Garmin (Europe) Ltd., Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K
Tel: [phone] Fax: [phone]

Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan
Tel: [phone] Fax: [phone]

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.

Website Address: www.garmin.com

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored
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and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

®

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: [phone] Fax: [phone]

Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A.
Toll free: 800/525.6726 Tel: [phone] Fax: [phone]

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: [phone] Fax: [phone]

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

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

SD Card Slots

Figure 1-3 Display Bezel SD Card Slots

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

7

SYSTEM OVERVIEW

1.3 SYSTEM POWER-UP

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

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

EIS

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.

& CNS

AUDIO PANEL

•Systemversion

•Copyright

•Landdatabasenameandversion

FLIGHT

MANAGEMENT

•SafeTaxidatabaseinformation(seeAdditionalFeatures)

•Terrain,AirportTerrain,Obstacle,andAviationdatabasename,version,andeffectivedates

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:

HAZARD

AVOIDANCE

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

AFCS

FEATURES

ADDITIONAL

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.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

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.

190-00870-00 Rev. B

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

9

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

If the system fails to detect a display problem, reversionary mode may be manually activated by pressing the

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

display backup button installed in the cockpit. Pressing this button again deactivates reversionary mode.

NAV1 and COM1 (provided by the

failed PFD) Flagged Invalid

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AFCS

ADDITIONAL

GIA 63W Integrated

AVOIDANCE

GIA 63W Integrated

FEATURES

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

APPENDICESINDEX

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

190-00870-00 Rev. B10

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,

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

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.

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00870-00 Rev. B

Figure 1-9 Example System Status Page

Garmin G950 Pilot’s Guide for the Pilatus PC-6

11

ADDITIONAL

FEATURES

APPENDICES INDEX

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.

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

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.

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B12

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.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

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.

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

Figure 1-10 AHRS Operation

13

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

GPS RECEIVER OPERATION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

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.

•SBASSelection(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.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

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

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

15

SYSTEM OVERVIEW

RAIM PREDICTION

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

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 specied waypoint, time, and date

• ‘RAIM NOT AVAILABLE’—RAIM is predicted to be unavailable for the specied waypoint, time, and date

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B16

Predicting RAIM availability at present position

1) Select the GPS Status Page.

SYSTEM OVERVIEW

OVERVIEW

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 specied waypoint, time, and date

• ‘RAIM NOT AVAILABLE’—RAIM is predicted to be unavailable for the specied 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:

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

- 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:

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

17

ADDITIONAL

FEATURES

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

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

•HorizontalandVerticalFiguresofMerit(HFOMandVFOM)—Measuresofhorizontalandverticalposition

uncertainty; the current 95% confidence horizontal and vertical accuracy values reported by the GPS
receiver

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B18

SYSTEM OVERVIEW

1.5 G950 CONTROLS

The G950 controls have been designed to simplify operation of the system and minimize workload and the time

required to access sophisticated functionality. Controls are located on the PFD and MFD bezels, MFD Control
Unit, and Audio Panel. PFD and MFD controls and softkeys are discussed in this section. Audio Panel controls
are described in the Audio Panel and CNS section; see the Audio Panel and CNS Section for more information
about NAV/COM controls.

PFD/MFD CONTROLS

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

2

31 9

4

5

1718

6

7

8

10

11

12

16

13

14

15

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

1

NAV VOL/ID Knob

2

NAV Frequency
Transfer Key

3

NAV Knob

4

Heading Knob

190-00870-00 Rev. B

Figure 1-13 PFD/MFD Controls

Turn to control NAV audio volume (shown in the NAV Frequency Box as a

percentage)

Press to toggle Morse code identifier audio ON/OFF

Transfers the standby and active NAV frequencies

Turn to tune NAV receiver standby frequencies (large knob for MHz; small for kHz)
Press to toggle light blue tuning box between NAV1 and NAV2

Turn to manually select a heading
Press to display a digital heading momentarily to the left of the HSI and synchronize

the Selected Heading to the and current heading

Garmin G950 Pilot’s Guide for the Pilatus PC-6

19

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

5

Joystick

6

CRS/BARO Knob

7

COM Knob

8

COM Frequency
Transfer Key
(EMERG)

9

COM VOL/SQ Knob

10

Direct-to Key ( )

11

FPL Key

Turn to change map range
Press to activate Map Pointer for map panning

Turn large knob for altimeter barometric pressure setting
Turn small knob to adjust course (only when HSI is in VOR or OBS Mode)
Press to re-center the CDI and return course pointer directly TO bearing of active

waypoint/station

Turn to tune COM transceiver standby frequencies (large knob for MHz; small for

kHz)
Press to toggle light blue tuning box between COM1 and COM2
The selected COM (green) is controlled with the COM MIC Key (Audio Panel).

Transfers the standby and active COM frequencies
Press and hold 2 seconds to tune the emergency frequency (121.5 MHz) automatically

into the active frequency field

Turn to control COM audio volume level (shown as a percentage in the COM

Frequency Box)
Press to turn the COM automatic squelch ON/OFF

Activates the direct-to function and allows the user to enter a destination waypoint

and establish a direct course to the selected destination (specified by identifier,

chosen from the active route)

Displays flight plan information

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

12

CLR Key
(DFLT MAP)

13

MENU Key

14

PROC Key

15

ENT Key

16

FMS Knob

(Flight Management
System Knob)

17

Softkey Selection
Keys

18

ALT Knob

Erases information, cancels entries, or removes menus
Press and hold to display the MFD Navigation Map Page (MFD only).

Displays a context-sensitive list of options for accessing additional features or making

setting changes

Gives access to IFR departure procedures (DPs), arrival procedures (STARs), and

approach procedures (IAPs) for a flight plan or selected airport

Validates/confirms menu selection or data entry

Press to turn the selection cursor ON/OFF.
Data Entry: With cursor ON, turn to enter data in the highlighted field (large

knob moves cursor location; small knob selects character for highlighted cursor

location)
Scrolling: When a list of information is too long for the window/box, a scroll bar

appears, indicating more items to view. With cursor ON, turn large knob to scroll

through the list.
Page Selection: Turn knob on MFD to select the page to view (large knob selects a

page group; small knob selects a specific page from the group)

Press to select softkey shown above the bezel key on the PFD/MFD display

Sets the Selected Altitude, shown above the Altimeter (the large knob selects the

thousands, the small knob selects the hundreds)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B20

SYSTEM OVERVIEW

OVERVIEW

The NAV, CRS/BARO, COM, FMS, and ALT knobs are concentric dual knobs, each having small (inner)

and large (outer) control portion. When a portion of the knob is not specified in the text, either may be used.

INSTRUMENTS

Large (Outer) Knob

Small (Inner) Knob

SYSTEM

FLIGHT

Figure 1-14 Dual Concentric Knob

SOFTKEY FUNCTION

The softkeys are located along the bottoms of the displays. The softkeys shown depend on the softkey level
or page being displayed. The bezel keys below the softkeys can be used to select the appropriate softkey. When
a softkey is selected, its color changes to black text on gray background and remains this way until it is turned
off, at which time it reverts to white text on black background. When a softkey function is disabled, the softkey
label is subdued (dimmed).

Softkeys revert to the previous level after 45 seconds of inactivity.

Softkey

On

Softkey Names

Bezel-Mounted
Softkeys (Press)

Figure 1-15 Softkeys (Third-Level PFD Configuration)

(Displayed)

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

21

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

PFD SOFTKEYS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

The

CDI, IDENT, TMR/REF, NRST,

and

ALERTS

softkeys undergo a momentary change to black text on

gray background and automatically switch back to white text on black background when selected.

The PFD softkeys provide control over flight management functions, including GPS, NAV, terrain, traffic,

and lightning (optional). Each softkey sublevel has a BACK Softkey which can be selected to return to the
previous level. The ALERTS Softkey is visible at all softkey levels (label changes if messages are issued).

INSET
OFF
DCLTR (3)

Displays Inset Map in PFD lower left corner
Removes Inset Map
Selects desired amount of map detail; cycles through declutter levels:

DCLTR (No Declutter): All map features visible
DCLTR-1: Declutters land data
DCLTR-2: Declutters land and SUA data
DCLTR-3: Removes everything except for the active flight plan

TRAFFIC

Displays traffic information on Inset Map
TRAFFIC: No Traffic displayed on Inset Map
TRFC-1: Traffic displayed on Inset Map
TRFC-2: Traffic Only display shown

TOPO

Displays topographical data (e.g., coastlines, terrain, rivers, lakes) and elevation
scale on Inset Map

TERRAIN
STRMSCP
PFD
DFLTS
WIND
OPTN 1
OPTN 2
OPTN 3

Displays terrain information on Inset Map
Displays Stormscope information on Inset Map (optional)
Displays second-level softkeys for additional PFD configurations
Resets PFD to default settings, including changing units to standard
Displays softkeys to select wind data parameters
Displays headwind/tailwind and crosswind arrows with numeric speed components
Displays wind direction arrow with numeric speed
Displays wind direction arrow with numeric headwind/tailwind and cross-wind

speed components

OFF
BRG1

Information not displayed
Cycles the Bearing 1 Information Window through NAV1 or GPS waypoint identifier

and GPS-derived distance information, and ADF/frequency.

HSI FRMT

Displays the softkeys for selecting the two HSI formats

APPENDICESINDEX

360 HSI
ARC HSI
BRG2

ALT UNIT

METERS

Displays HSI as a 360° compass rose
Displays HSI as a 140° viewable arc
Cycles the Bearing 2 Information Window through NAV2 or GPS waypoint identifier

and GPS-derived distance information, and ADF/frequency.
Displays softkeys for setting the altimeter and BARO settings to metric units

When enabled, displays altimeter in meters

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B22

IN

INSET XPDR IDENT TMR/REF NRST ALERTSOBSPFD CDI

Press the CDI Softkey to cycle through
navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

DME

(optional)

Press to display the BARO setting as inches of mercury

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

HPA

STD BARO

OBS

CDI

DME

XPDR

STBY

ON

A LT

GND

VFR

CODE

0 — 7

BKSP

IDENT

TMR/REF

NRST

ALERTS

Press to display the BARO setting as hectopacals

Sets barometric pressure to 29.92 in Hg (1013 hPa if metric units are selected)
Selects OBS mode on the CDI when navigating by GPS (only available with active

leg)
Cycles through GPS, VOR1, and VOR2 navigation modes on the CDI
Displays the DME Tuning Window, allowing tuning and selection of the DME

(optional)
Displays transponder mode selection softkeys
Selects standby mode (transponder does not reply to any interrogations)
Selects Mode A (transponder replies to interrogations)
Selects Mode C – altitude reporting mode (transponder replies to identification and

altitude interrogations)
Manually selects Ground Mode, the transponder does not allow Mode A and

Mode C replies, but it does permit acquisition squitter and replies to discretely
addressed Mode S interrogations

Automatically enters the VFR code (1200 in the U.S.A. only)
Displays transponder code selection softkeys 0-7
Use numbers to enter code
Removes numbers entered, one at a time
Activates the Special Position Identification (SPI) pulse for 18 seconds, identifying

the transponder return on the ATC screen
Displays Timer/References Window
Displays Nearest Airports Window
Displays Alerts Window

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00870-00 Rev. B

Figure 1-16 Top Level PFD Softkeys

Garmin G950 Pilot’s Guide for the Pilatus PC-6

23

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

INSET XPDR IDENT TMR/REF NRST ALERTSOBSPFD CDI

Press the CDI Softkey to cycle through
navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

BACK

Select the BACK Softkey to return
to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

TERRAIN

OFF

INSET

DME

(optional)

TRFC-1

TRFC-2

STRMSCP

INSET XPDR IDENT TMR/REF NRST ALERTSOBSPFD CDI

Press the CDI Softkey to cycle through
navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

BACK

Select the BACK Softkey to return
to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

TERRAIN

OFF

INSET

STD BARO

BACK

ALERTS

WIND

HSI FMT

PFD

BRG

1

BRG

2

Select the BACK Softkey to return
to the top-level softkeys.

ALT UNIT

DFLTS

Select the BRG1/BRG2
softkeys to display/remove
the Bearing Information
windows and cycle through
bearing sources:

- NAV1/NAV2

- GPS

DME

(optional)

HPA BACK

ALERTS

METERS IN

BACK

ALERTS

OPTN1OPTN2 OPTN3 OFF

BACK

ALERTS

360 HSI

ARC HSI

TRFC-1

TRFC-2

STRMSCP

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

Figure 1-17 INSET Softkeys

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

Figure 1-18 PFD Configuration Softkeys

190-00870-00 Rev. B24

Press the CDI Softkey to cycle through
navigation sources:

- GPS

- NAV1 (VOR/LOC)

- NAV2 (VOR/LOC)

Select the BACK Softkey to return
to the top-level softkeys.

Select the BACK Softkey to return

to the top-level softkeys.

XPDR

STBY ON ALT VFR IDENT BACK ALERTSCODE

IDENT BACK

ALERTS

0 1 2 3 4 5 6 7 BKSP

BACK

Select the BACK Softkey to return
to the top-level softkeys.

DCLTR

DCLTR-2

DCLTR-3

DCLTR-1

TOPO

ALERTS

TERRAIN

OFF

INSET

STD BARO

BACK

ALERTS

WIND

HSI FMT

PFD

BRG

1

BRG

2

Select the BACK Softkey to return
to the top-level softkeys.

ALT UNIT

DFLTS

Select the BRG1/BRG2
softkeys to display/remove
the Bearing Information
windows and cycle through
bearing sources:

- NAV1/NAV2

- GPS

GND

HPA BACK

ALERTS

METERS IN

BACK

ALERTS

OPTN1OPTN2 OPTN3 OFF

BACK

ALERTS

360 HSI

ARC HSI

TRFC-1

TRFC-2

STRMSCP

DCLTR

ENGINE

DCLTR-2

DCLTR-3

DCLTR-1

SYSTEM FUEL

ENGINE

MAP

BACKENGINE

BACK

BACK

TOPO

TRAFFIC

TERRAIN

Select the BACK softkey to
return to the top-level softkeys.

AIRWY LO

AIRWY HI

AIRWY ON

AIRWAYS

SYSTEM FUEL

DEC FUEL INC FUEL RST FUEL

STRMSCP

SYSTEM OVERVIEW

Figure 1-19 XPDR Softkeys

MFD SOFTKEYS

MFD softkeys vary depending on the page selected. EIS and Navigation Map Page (default MFD page)

softkeys are described here.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

190-00870-00 Rev. B

Figure 1-20 MFD Softkeys (EIS, Navigation Map Page, and Checklist)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

25

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

ENGINE

ENGINE

SYSTEM

FUEL

DEC FUEL

INC FUEL

RST FUEL

BACK

MAP

TRAFFIC

TOPO

TERRAIN

AIRWAYS

STRMSCP

BACK

DCLTR (3)

Displays second-level engine softkeys
Displays engine data in EIS Strip (see the Engine Instruments section)
Displays system data in EIS Strip (see the Engine Instruments section)

Displays fuel data in EIS Strip and displays fuel system softkeys (see the

Engine Instruments section)
Decreases displayed fuel remaining in 1-gal increments
Increases displayed fuel remaining in 1-gal increments
Resets displayed fuel remaining to maximum fuel capacity for aircraft and

fuel used to zero
Returns to top-level softkeys
Enables second-level Navigation Map Page softkeys
Displays/removes traffic information on Navigation Map Page
Displays/removes topographical data (e.g., coastlines, terrain, rivers,

lakes) on Navigation Map Page
Displays/removes terrain information on Navigation Map Page
Selects the desired display of Airways; cycles through:
AIRWY ON: All Airways displayed
AIRWY LO: Low Altitude (Victor) Airways displayed
AIRWY HI: High Altitude Airways (Jetways) displayed
AIRWAYS: Airways are not displayed
Displays Stormscope information on Navigation Map (optional)
Returns to top-level softkeys
Selects desired amount of map detail; cycles through declutter levels:
DCLTR (No Declutter): All map features visible
DCLTR-1: Removes land data
DCLTR-2: Removes land and SUA data
DCLTR-3: Removes everything except the active flight plan

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B26

1.6 ACCESSING G950 FUNCTIONALITY

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

MENUS

The G950 has a dedicated MENU Key that when pressed displays a context-sensitive list of options. This
options list allows the user to access additional features or make settings changes which specifically relate to
the currently displayed window/page. There is no all-encompassing menu. Some menus provide access to
additional submenus that are used to view, edit, select, and review options. Menus display ‘NO OPTIONS’
when there are no options for the window/page selected. The main controls used in association with all
window/page group operations are described in Section 1.5, G950 Controls.

Navigating a menu:

1) Press the MENU Key to display the menu.

2) Turn the FMS Knob to scroll through a list of available options (a scroll bar always appears to the right of the

window/box when the option list is longer than the window/box).

3) Press the ENT Key to select the desired option.

4) Press the CLR Key or the FMS Knob to remove the menu and cancel the operation.

No Options for

NRST Window

Options for FPL Window

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Figure 1-21 Page Menu Examples

DATA ENTRY

The method for directly entering alphanumeric data (e.g., Flight ID, waypoint identifiers, barometric minimum
descent altitude) into the G950 is by using the FMS Knob corresponding to the display (PFD, MFD).

In some instances, such as when entering an identifier, the G950 tries to predict the desired identifier based
on the characters being entered. In this case, if the desired identifier appears, use the ENT Key to confirm the
entry without entering the rest of the identifier manually. This can save the pilot from entering all the characters
of the identifier.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

27

SYSTEM OVERVIEW

Besides character-by-character data entry, the system also provides a shortcut for entering waypoint identifiers.

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

When the cursor is on a field awaiting entry of a waypoint identifier, turning the small FMS Knob counter­clockwise accesses five different lists of waypoint identifiers for quick selection: flight plan (FPL), nearest (NRST),
recently-entered (RECENT), user-defined (USER), and airway (AIRWAY)(AIRWAY available when active leg is
part of an airway). The G950 automatically fills in the identifier, facility, and city fields with the information
for the selected waypoint.

Using the FMS Knob to enter data:

1) If needed, press the FMS Knob to activate the cursor.

2) Use the large FMS Knob to highlight the desired field.

3) Begin entering data.

a) To quickly enter a waypoint identifier, turn the small FMS Knob counter-clockwise to display a list of waypoints

in the active flight plan (list is titled FPL). If desired, turn the small FMS Knob clockwise to scroll through lists
of other waypoints (NRST, USER, AIRWAY, RECENT).

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

b) Turn the large FMS Knob to highlight the desired waypoint from the list and press the ENT Key.

Or:

a) Turn the small FMS Knob to select a character for the first placeholder.

Turning the knob clockwise scrolls through the alphabet (where appropriate) toward the letter Z, starting at

K, and the digits zero through nine. Afterwards, turning the knob counter-clockwise scrolls in the opposite
direction.

b) Use the large FMS Knob to move the cursor to the next placeholder in the field.

c) Repeat, using the small FMS Knob to select a character and the large FMS Knob to move the cursor, until the

field is complete.

d) Press the ENT Key to confirm entry.

7) Press the FMS Knob or CLR Key to cancel data entry (the field reverts back to its previous information).

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B28

PAGE GROUPS

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

NOTE:

Refer to other supporting sections in this Pilot’s Guide for details on specific pages.

Information on the MFD is presented on pages which are grouped according to function. The page group and
active page title are displayed in the upper center of the screen, below the Navigation Status Box. In the bottom
right corner of the screen, the page group tabs are displayed along the bottom Number of pages available in the
group are displayed in a list above the page groups. The current page group and current page within the group
are shown in cyan. For some of these pages (Airport/Procedures/Weather Information, Procedure Loading), the
active title of the page changes while the page name in the list remains the same.

Page Group

MFD

Pages in

Current

Group

Active Page Title

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

Page Groups

Figure 1-22 Page Title and Page Groups

The main page groups are navigated using the FMS Knob; specific pages within each group can vary depending
on the configuration of optional equipment.

Selecting a page using the FMS Knob:

1) Turn the

large FMS

Knob to display the list of page groups; continue turning the large FMS Knob until the

desired page group is selected

2)

Turn

the

small FMS

Knob to display the desired page within a specific page group.

There are also several pages (Airport/Procedures/Weather Information pages) which are selected first from
within a main page group with the FMS Knob, then with the appropriate softkey at the bottom of the page. In
this case, the page remains set to the selected page until a different page softkey is selected, even if a different
page group is selected.

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

29

SYSTEM OVERVIEW

•Map Page Group (MAP)

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

Navigation Map

Traffic Map

Weather Radar (optional)

Stormscope (optional)

Terrain Map

Figure 1-23 Map Pages

•Waypoint Page Group (WPT)

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Airport/Procedures/Weather Information Pages

- Airport Information
(INFO Softkey)

- Departure Information
(DP Softkey)

- Arrival Information
(STAR Softkey)

- Approach Information
(APR Softkey)

Intersection Information

NDB Information

VOR Information

User Waypoint Information

Figure 1-24 Waypoint Pages

Airport/Procedures/
Weather Information
Pages

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B30

•Auxiliary Page Group (AUX)

Trip Planning

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

Utility

GPS Status

System Setup

System Status

•Nearest Page Group (NRST)

Nearest Airports

Nearest Intersections

Figure 1-25 Auxiliary Pages

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Nearest NDB

Nearest VOR

Nearest User Waypoints

Nearest Frequencies

Nearest Airspaces

Figure 1-26 Nearest Pages

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

31

SYSTEM OVERVIEW

In addition to the main page groups accessed exclusively using the FMS Knob, there are pages for flight

SYSTEM

OVERVIEW

planning (FPL) and loading procedures (PROC) which are accessed by key. In some instances, softkeys may be
used to access the Procedure Loading pages.

The Flight Plan pages are accessed using the FPL Key on the MFD. Main pages within this group are selected

by turning the small FMS Knob.

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

•Flight Plan Page Group (FPL)

Active Flight Plan

Flight Plan Catalog

- Stored Flight Plan
(NEW Softkey)

Figure 1-27 Flight Plan Pages

The Procedure Loading pages may be accessed at any time on the MFD by pressing the PROC Key. A menu
is initialized, and when a departure, approach, or arrival is selected, the appropriate Procedure Loading page is
opened. These pages can also be accessed from the Stored Flight Plan page using the LD softkeys. Turning the
FMS Knob does not scroll through the Procedure Loading pages.

•Procedure Loading Page Group (PROC)

Departure Loading

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Arrival Loading

Approach Loading

Figure 1-28 Procedure Loading Pages

Information on optional electronic checklist pages is offered later in this section. Checklist pages may be
accessed from any page on the MFD using the CHKLIST Softkey.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B32

SYSTEM SETTINGS

The System Setup Page allows management of the following system parameters:

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

•Timeformat(local12-or24-hr,orUTC)

•Displayedmeasurementunits

•Baro transition alert (see Flight Instruments

Section)

•Airspacealerts

•Arrivalalerts

•Audioalertvoice

•MFDDataBar(NavigationStatusBox)elds

•GPSCourseDeviationIndicator(CDI)range

•COMtransceiverchannelspacing

•Displayednearestairports

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Restoring system setup defaults:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the DFLTS Softkey.

Or:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the MENU Key.

3) Highlight ‘Restore Defaults’ and press the ENT Key.

190-00870-00 Rev. B

Figure 1-29 System Setup Page

Garmin G950 Pilot’s Guide for the Pilatus PC-6

33

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

PILOT PROFILES

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

System settings may be saved under a pilot profile. When the system is powered on, the last selected
pilot profile is shown on the MFD Power-up Screen (Figure 1-5). The G950 can store up to 25 profiles;
the currently active profile, the amount of memory used, and the amount of memory available are shown at
the top of the System Setup Page in the box labeled ‘Pilot Profile’. From here, pilot profiles may be created,
selected, renamed, or deleted.

Creating a profile:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight ‘CREATE’ in the Pilot Profile Box.

4) Press the ENT Key. A ‘Create Profile’ window is displayed.

5) Use the FMS Knob to enter a profile name up to 16 characters long and press the ENT Key. Pilot profile names

cannot begin with a blank as the first letter.

6) In the next field, use the small FMS Knob to select the desired settings upon which to base the new profile.

Profiles can be created based on Garmin factory defaults, default profile settings (initially based on Garmin
factory defaults unless edited by the pilot), or current system settings.

7) Press the ENT Key.

8) With ‘CREATE’ highlighted, press the ENT Key to create the profile

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Or:

Use the large FMS Knob to select ‘CREATE and ACTIVATE’ and press the ENT Key to activate the new profile.

9) To cancel the process, select ‘CANCEL’ with the large FMS Knob and press the ENT Key.

Selecting an active profile:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the active profile field in the Pilot Profile Box.

4) Turn the small FMS Knob to display the pilot profile list and highlight the desired profile.

5) Press the ENT Key. The G950 loads and displays the system settings for the selected profile.

Renaming a profile:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight ‘RENAME’ in the Pilot Profile Box.

4) Press the ENT Key.

5) In the ‘Rename Profile’ window, turn the FMS Knob to select the profile to rename.

6) Press the ENT Key.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B34

SYSTEM OVERVIEW

7) Use the FMS Knob to enter a new profile name up to 16 characters long and press the ENT Key.

8) With ‘RENAME’ highlighted, press the ENT Key.

OVERVIEW

SYSTEM

9) To cancel the process, use the large FMS Knob to select ‘CANCEL’ and press the ENT Key.

Deleting a profile:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight ‘DELETE’ in the Pilot Profile Box.

4) Press the ENT Key.

5) In the ‘Delete Profile’ window, turn the FMS Knob to select the profile to delete.

6) Press the ENT Key.

7) With ‘DELETE’ highlighted, press the ENT Key.

8) To cancel the process, use the large FMS Knob to select ‘CANCEL’ and press the ENT Key.

DATE/TIME

The system time is displayed in the lower right corner of the PFD. Time and date format (local 12-hr,
local 24-hr, or UTC) are modified on the System Setup Page. Universal Coordinated Time (UTC; also called
Greenwich Mean Time (GMT) or Zulu) date and time are calculated directly from the GPS satellites signals
and cannot be changed. An offset is provided to add or subtract the desired amount of time (hours:minutes)
from UTC to define current local time.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Configuring the system time:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob to activate the cursor.

3) Turn the large FMS Knob to highlight the ‘Time Format’ field.

4) Turn the small FMS Knob to select the desired format and press the ENT Key to confirm selection. The ‘Time

Offset’ field is highlighted (for local time formats).

5) Use the FMS Knob to enter the desired time offset (±HH:MM) and press the ENT Key to confirm selection.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

35

SYSTEM OVERVIEW

DISPLAY UNITS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Units in which various quantities are displayed on the G950 screens can be changed on the System Setup

Page.

Changing a display units setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

Knob to highlight the desired field in the ‘Display Units’ box.

4) Turn the small FMS Knob to select from a list of measurement units and press the ENT Key when the desired

unit is highlighted.

Category Settings Affected Quantities Exceptions

Navigation Angle Magnetic*

True

Heading
Course
Bearing
Track
Desired Track
Wind direction (Trip Planning Page)

Distance and
Speed**

Metric
Nautical*

Crosstrack error (HSI)
Bearing distances (information windows)
DME distance (information window)
Flight plan distances
Map ranges
DIS, GS, TAS, XTK fields (Navigation Status Box)
All distances on MFD

Airspeed Indicator
True Airspeed (PFD)
Wind speed vector
Map range (Traffic Page, Terrain

Page)
CDI scaling (System Setup)
Fuel range calculation (EIS)

Altitude buffer distance (System Setup)
Arrival Alert trigger distance (System Setup)
All speeds on MFD

Altitude and
Vertical Speed

Feet*
Meters

All altitudes on MFD
All elevations on MFD

Altimeter
Vertical Speed Indicator
VNV altitudes (Active Flight Plan)

Temperature Celsius

Fahrenheit*

Fuel and

Gallons* Fuel parameters (Trip Planning Page) Engine Indication System (EIS)

All temperatures on PFD
Total Air Temperature (Trip Planning Page)

Engine Indication System (EIS)

Fuel Flow**
Weight Pounds*

N/A N/A

Kilograms

Position HDDD°MM.MM’*

All positions N/A

HDDD°MM’SS.S”

* Default setting
** Contact a Garmin-authorized service center to change this setting

Table 1-1 Display Units Settings (System Status Page)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B36

SYSTEM OVERVIEW

AIRSPACE ALERTS

The Airspace Alert feature provides a message alert when the aircraft is approaching or near a controlled or
special-use airspace. The altitude buffer setting increases the range above or below an airspace for which an
alert is generated; the default value is 200 feet. Alerts for the following airspaces can be turned on/off from
the System Setup Page:

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

•ClassB/TMA

•ClassC/TCA

•ClassD

•Restricted

•MOA(Military)

•Otherairspaces

Turning Airspace Alerts off does not affect the alerts listed on the Nearest Airspaces Page or the airspace
boundaries depicted on the Navigation Map Page.

Turning an airspace alert on or off:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the desired field in the ‘Airspace Alerts’ Box.

4) Turn the small FMS Knob clockwise to turn the airspace alert ON or counterclockwise to turn the alert OFF.

Changing the altitude buffer distance setting:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the altitude buffer field in the ‘Airspace Alerts’ Box.

4) Enter an altitude buffer value and press the ENT Key.

ARRIVAL ALERTS

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The Arrival Alert Box on the System Setup Page allows the Alerts Window arrival alerts to be turned
ON/OFF, and the alert trigger distance (up to 99.9 units) set for alerts in the Alerts Window and the PFD
Navigation Status Box. An arrival alert can be set to notify the pilot with a message upon reaching a user­specified distance from the final destination (the direct-to waypoint or the last waypoint in a flight plan).
When Arrival Alerts is set to ON, and the set distance is reached, an “Arrival at waypoint” message is displayed
in the PFD Navigation Status Box, and a “WPT ARRIVAL - Arriving at waypoint - [xxxx]” is displayed in the
Alerts Window. When Arrival Alerts is set to OFF, only the PFD Navigation Status Box message “Arriving
at waypoint” is displayed, and it is displayed when the time to the final destination is approximately ten
seconds.

Figure 1-30 Arrival Alert Settings (System Setup Page)

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FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

37

SYSTEM OVERVIEW

Enabling/disabling the Alerts Window arrival alert:

SYSTEM

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MANAGEMENT

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to select the ON/OFF field in the Arrival Alert Box.

4) Turn the small FMS Knob clockwise to turn the airspace alert ON or counterclockwise to turn the alert OFF.

Changing the arrival alert trigger distance:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the distance field in the Arrival Alert Box.

4) Use the FMS Knob to enter a trigger distance and press the ENT Key.

AUDIO ALERTS

The gender of the voice used to announce audio alerts may be set to male or female on the System Setup

Page. See the Appendices for voice alerts.

Changing the audio alert voice:

1) Use the FMS Knob to select the AUX - System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

HAZARD

AVOIDANCE

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ADDITIONAL

APPENDICESINDEX

3) Turn the large FMS Knob to highlight the voice in the Audio Alert Box.

4) Turn the small FMS Knob to display and highlight the desired voice and press the ENT Key.

MFD DATA BAR FIELDS

By default, the Navigation Status Box on the MFD is set to display ground speed (GS), distance to next
waypoint (DIS), estimated time enroute (ETE), and enroute safe altitude (ESA). These four data fields can be
changed to display the following information:

•Bearing(BRG)

•Distance(DIS)

•DesiredTrack(DTK)

•Endurance(END)

•EnrouteSafeAltitude(ESA)

•EstimatedTimeofArrival(ETA)

•EstimatedTimeEnroute(ETE)

•FuelonBoard(FOB)

•FueloverDestination(FOD)

•GroundSpeed(GS)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B38

•MinimumSafeAltitude(MSA)

•TrueAirSpeed(TAS)

SYSTEM OVERVIEW

OVERVIEW

SYSTEM

•TrackAngleError(TKE)

•Track(TRK)

•VerticalSpeedRequired(VSR)

•CrosstrackError(XTK)

The Navigation Status Box on the PFD is not affected by these changes; flight plan, distance, and bearing

information are displayed at all times.

Changing the information shown in the MFD Navigation Status Box:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the desired field number in the MFD Data Bar Fields Box.

4) Turn the small FMS Knob to highlight the desired selection from the data options list and press the ENT Key.

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GPS CDI

The GPS CDI Box on the System Setup Page allows the pilot to define the scale for the Course Deviation
Indicator (CDI) when GPS is the selected navigation source and also displays the current system value for the
CDI scale. The range values represent full scale deflection for the CDI to either side. The default setting is
‘Auto’ (refer to the CDI description in the Flight Instruments Section for information on CDI scaling).

If a lower CDI scale setting is selected (i.e., 1.0 or 0.3 nm), the higher scale settings are not selected during
any phase of flight. Note that the Receiver Autonomous Integrity Monitoring (RAIM) protection limits follow
the selected CDI scale and corresponding flight phase.

190-00870-00 Rev. B

Figure 1-31 Navigation Status Box (MFD)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

39

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APPENDICES INDEX

SYSTEM OVERVIEW

Changing the selected GPS CDI setting:

SYSTEM

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AVOIDANCE

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

Knob to highlight ‘Selected’ in the ‘GPS CDI’ box.

4) Turn the small FMS Knob to highlight the desired setting (2 nm, 1 nm, 0.3 nm, Auto) and press the ENT Key.

COM CONFIGURATION

The COM Configuration Box on the System Setup Page allows the pilot to select 8.33 kHz or 25.0 kHz

COM frequency channel spacing.

Changing COM channel spacing:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the channel spacing field in the COM Configuration Box.

4) Turn the small FMS Knob to select the desired spacing and press the ENT Key.

NEAREST AIRPORTS

The Nearest Airports Box on the System Setup Page defines the minimum runway length and surface type
used when determining the nine nearest airports to display on the MFD Nearest Airports Page. A minimum
runway length and/or surface type can be entered to prevent airports with small runways or runways that are
not of appropriate surface from being displayed. Default settings are 0 feet (or meters) for runway length and
“any” for runway surface type.

Selecting nearest airport surface matching criteria (any, hard only, hard/soft, water):

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ADDITIONAL

APPENDICESINDEX

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the runway surface field in the Nearest Airports Box.

4) Turn the small FMS Knob to select the desired runway option (any, hard only, hard/soft, water) and press the
ENT Key.

Selecting nearest airport minimum runway length matching criteria:

1) Use the FMS Knob to select the System Setup Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the minimum length field in the Nearest Airport Box.

4) Enter the minimum runway length (zero to 99,999 feet) and press the ENT Key.

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190-00870-00 Rev. B40

SYSTEM OVERVIEW

SYSTEM UTILITIES

For flight planning purposes, timers, trip statistics, and a scheduler feature are provided on the AUX - Utility
Page. The timers available include a stopwatch-like generic timer, a total time in flight timer, and a record of the
time of departure. Trip statistics—odometer, trip odometer, and average trip and maximum groundspeeds—are
displayed from the time of the last reset. A scheduler feature is also provided so the pilot can enter reminder
messages to be displayed at specified intervals in the Alerts Window on the PFD (see Figure 1-33).

OVERVIEW

SYSTEM

INSTRUMENTS

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Figure 1-32 Utility Page

TIMERS

The generic timer can be set to count up or down from a specified time (HH:MM:SS). When the countdown
on the timer reaches zero the digits begin to count up from zero. If the timer is reset before reaching zero
on a countdown, the digits are reset to the initial value. If the timer is counting up when reset, the digits are
zeroed.

Setting the generic timer:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

AVOIDANCE

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APPENDICES INDEX

3) Turn the small FMS Knob to select the timer counting direction (UP/DN) and press the ENT Key.

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

41

SYSTEM OVERVIEW

4) If a desired starting time is desired:

SYSTEM

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a) Use the large FMS Knob to highlight the HH:MM:SS field.

b) Use the FMS Knob to enter the desired time and press the

5) Turn the

large FMS

Knob to highlight ‘START?’ and press the

ENT

Key.

ENT

Key to start the timer. The field changes to

‘STOP?’.

6) To stop the timer, press the ENT Key with ‘STOP?’ highlighted. The field changes to ‘RESET?’.

7) To reset the timer, press the ENT Key with ‘RESET?’ highlighted. The field changes back to ‘START?’ and the

digits are reset.

The flight timer can be set to count up from zero starting at system power-up or from the time that the

aircraft lifts off; the timer can also be reset to zero at any time.

Setting the flight timer starting criterion:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the field next to the flight timer.

4) Turn the

small FMS

Knob to select the starting criterion (PWR-ON or IN-AIR) and press the

ENT

Key.

Resetting the flight timer:

1) Use the FMS Knob to select the AUX - Utility Page.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

2) Press the

3) With ‘Reset Flight Timer’ highlighted, press the

MENU

Key.

ENT

Key.

The G950 records the time at which departure occurs, measured from system power-up or aircraft lift off.
The displayed departure time can also be reset to display the current time at the point of reset. The format in
which the time is displayed is controlled from the System Setup Page.

Setting the departure timer starting criterion:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the field next to the departure time.

4) Turn the

small FMS

Knob to select the starting criterion (PWR-ON or IN-AIR) and press the

ENT

Key.

Resetting the departure time:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the

3) Use the FMS Knob to highlight ‘Reset Departure Time’ and press the

MENU

Key.

ENT

Key.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B42

SYSTEM OVERVIEW

TRIP STATISTICS

The odometer and trip odometer record the total mileage traveled from the last reset; these odometers can
be reset independently. Resetting the trip odometer also resets the average trip groundspeed. Maximum
groundspeed for the period of time since the last reset is also displayed.

Resetting trip statistics readouts:

1) Use the FMS Knob to select the AUX - Utility Page.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

2) Press the

MENU

Key. The following reset options for trip statistics are displayed:

• Reset Trip ODOM/AVG GS—Resets trip average ground speed readout and odometer

• Reset Odometer—Resets odometer readout only

• Reset Maximum Speed—Resets maximum speed readout only

• Reset All—Resets ight timer, departure timer, odometers, and groundspeed readouts

3) Use the FMS Knob to highlight the desired reset option and press the

ENT

Key. The selected parameters are reset

to zero and begin to display data from the point of reset.

SCHEDULER

The scheduler feature can be used to enter and display reminder messages (e.g., “Change oil”, “Switch
fuel tanks”, “Overhaul”). Messages can be set to display based on a specific date and time (event), once the
message timer reaches zero (one-time; default setting), or recurrently whenever the message timer reaches
zero (periodic). Message timers set to periodic alerting automatically reset to the original timer value once
the message is displayed. When power is cycled, messages are retained until deleted, and message timer
countdown is restarted.

Entering a scheduler message:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

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3) Turn the large FMS Knob to highlight the first empty scheduler message naming field.

4) Use the FMS Knob to enter the message text to be displayed in the Alerts Window and press the

5) Press the ENT Key again or use the large FMS Knob to move the cursor to the field next to ‘Type’.

6) Turn the small FMS Knob to select set the message alert type:

7) Press the ENT Key again or use the large FMS Knob to move the cursor to the next field.

8) For periodic and one-time message, use the FMS Knob to enter the timer value (HHH:MM:SS) from which to

190-00870-00 Rev. B

• Event—Message issued at the specied date/time

• One-time—Message issued when the message timer reaches zero (default setting)

• Periodic—Message issued each time the message timer reaches zero

countdown and press the ENT Key.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

ENT

Key.

43

ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

9) For event-based messages:

SYSTEM

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a) Use the FMS Knob to enter the desired date (DD-MMM-YYY) and press the ENT Key.

b) Press the ENT Key again or use the large FMS Knob to move the cursor to the next field.

c) Use the FMS Knob to enter the desired time (HH:MM) and press the ENT Key.

10) Press the ENT Key again or use the large FMS Knob to move the cursor to enter the next message.

Deleting a scheduler message:

1) Use the FMS Knob to select the AUX - Utility Page.

2) Press the FMS Knob momentarily to activate the flashing cursor.

3) Turn the large FMS Knob to highlight the name field of the scheduler message to be deleted.

4) Press the CLR Key to clear the message text. If the CLR Key is pressed again, the message is restored.

5) Press the ENT Key to confirm message deletion.

Scheduler messages appear in the Alerts Window on the PFD and cause the ALERTS Softkey label to
change to ‘ADVISORY’. Selecting the ADVISORY Softkey opens the Alerts Window and acknowledges
the scheduler message. The softkey reverts to the ‘ALERTS’ label and when pressed, the Alerts Window is
removed from the display and the scheduler message is deleted from the message list.

HAZARD

AVOIDANCE

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ADDITIONAL

APPENDICESINDEX

PFD

Figure 1-33 PFD Alerts Window

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B44

SYSTEM OVERVIEW

1.7 DISPLAY BACKLIGHTING

Backlighting of the PFD and MFD, and Audio Panel keys can be adjusted automatically or manually. The
automatic setting (default) uses photocells to adjust for ambient lighting conditions. Photocell calibration curves
are pre-configured to optimize display appearance through a broad range of cockpit lighting conditions. In
normal display mode, backlighting can only be adjusted from the PFD. In Reversionary Mode, it can be adjusted
from the remaining display(s).

Adjusting display backlighting manually:

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

1) Press the PFD MENU Key to display the PFD Setup Menu. ‘AUTO’ is now highlighted next to ‘PFD DSPL’. No

other window can be displayed on the PFD while the PFD Setup Menu is displayed. Pressing the MENU Key
while any other PFD window is displayed does not display the PFD Setup Menu.

2) Turn the

3) Use the FMS Knob to enter the desired backlighting then press the

4) Turn the

5) To remove the menu, press the

small FMS

large FMS

Knob to select ‘MANUAL’ and press the

ENT

Key. The intensity value is now highlighted.

ENT

Key.

Knob to highlight ‘AUTO’ next to ‘MFD DSPL’ and repeat steps 2-4.

CLR

or

MENU

Key.

Adjusting key backlighting manually:

1) Press the PFD

2) Turn the

3) Turn the

4) Turn the

5) Turn the

6) Use the FMS Knob to enter the desired backlighting and press the

7) Turn the

MENU

large FMS

small FMS

large FMS

small FMS

large FMS

Key to display the PFD Setup Menu. ‘AUTO’ is now highlighted next to ‘PFD DSPL’.

Knob to highlight ‘PFD DSPL’.

Knob in the direction of the green arrowhead to display ‘PFD KEY’.

Knob to highlight ‘AUTO’.

Knob to select ‘MANUAL’ and press the

ENT

Key. The intensity value is now highlighted.

ENT

Key.

Knob to highlight ‘MFD DSPL’.

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8) Turn the

9) To remove the menu, press the

190-00870-00 Rev. B

small FMS

PFD

Knob in the direction of the green arrowhead to display ‘MFD KEY’ and repeat steps 4-7.

CLR

or

MENU

Key.

Figure 1-34 PFD Setup Menu

Garmin G950 Pilot’s Guide for the Pilatus PC-6

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ADDITIONAL

FEATURES

APPENDICES INDEX

SYSTEM OVERVIEW

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APPENDICESINDEX

Bl a n k Pa g e

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B46

SECTION 2 FLIGHT INSTRUMENTS

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

WARNING:

In the event that the airspeed, attitude, altitude, or heading indications become unusable, refer

to the backup instruments.

Increased situational awareness is provided by replacing the traditional instruments on the panel with an easy­to-scan Primary Flight Display (PFD) that features a large horizon, airspeed, attitude, altitude, vertical speed, and
course deviation information. In addition to the flight instruments, navigation, communication, terrain, traffic,
and weather information are also presented on the PFD and explained in other sections of this Pilot’s Guide.

The following flight instruments and supplemental flight data are displayed on the PFD:

•AirspeedIndicator,showing

– True airspeed

– Airspeed awareness ranges

– Trend vector

– Reference flags

•AttitudeIndicatorwithslip/skid

indication

•Altimeter,showing

– Trend vector

•VerticalDeviation,Glideslope,

and Glidepath Indicators

•VerticalSpeedIndicator(VSI)

•HorizontalSituationIndicator,

showing

– Heading and course indications

– Turn Rate Indicator

– Navigation source

– Course Deviation Indicator

(CDI)

•Timer/ReferencesWindow,

showing

– Generic timer

– Vspeed values and flags

– Barometric minimum descent

altitude (MDA; or decision
height, DH)

•Systemtime

•Winddata

•VerticalNavigationindications

– Barometric setting

– Bearing pointers and

– Selected Altitude

information windows

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•OutsideAirTemperature(OAT)

The PFD also displays various alerts and annunciations.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

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Garmin G950 Pilot’s Guide for the Pilatus PC-6

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FLIGHT INSTRUMENTS

SYSTEM

OVERVIEW

1920

18

FLIGHT

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AVOIDANCE

1

2

3

4

5

6

7

1

NAV Frequency Box

2

Airspeed Indicator

3

True Airspeed

11

Turn Rate Indicator

12

Altimeter Barometric Setting

13

Selected Altitude Bug

17

16

15

14

13

12

11

10

9

8

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ADDITIONAL

APPENDICESINDEX

4

Current Heading

5

Selected Heading Bug

6

Outside Air Temperature (OAT)

7

Softkeys

8

System Time

9

Transponder Data Box

10

Horizontal Situation Indicator ( HSI)

Figure 2-1 Primary Flight Display (Default)

14

Vertical Speed Indicator (VSI)

15

Altimeter

16

Selected Altitude

17

COM Frequency Box

18

Navigation Status Box

19

Slip/Skid Indicator

20

Attitude Indicator

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190-00870-00 Rev. B48

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

14

1

2

3

4

5

6

7

13

12

11

10

9

8

INSTRUMENTS

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1

Traffic Annunciation

2

Selected Heading

3

Wind Data

4

Inset Map

5

DME Information Window

6

Bearing Information Windows

7

Minimum Descent Altitude/Decision
Height

Figure 2-2 Primary Flight Display (Additional Information)

8

Flight Plan Window

9

Annunciation Window

10

Selected Course

11

Vertical Speed Required

12

Vertical Deviation Indicator (VDI)

13

Current VNV Target Altitude

14

TAWS-B Annunciation

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FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

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FLIGHT INSTRUMENTS

2.1 FLIGHT INSTRUMENTS

SYSTEM

OVERVIEW

AIRSPEED INDICATOR

FLIGHT

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AVOIDANCE

NOTE:

Refer to the Pilot’s Operating Handbook (POH) for airspeed criteria and Vspeed values.

The Airspeed Indicator displays airspeed on a rolling number gauge using a moving tape. The true airspeed

(TAS) is displayed in knots below the Airspeed Indicator. The numeric labels and major tick marks on the
moving tape are marked at intervals of 10 knots, while minor tick marks on the moving tape are indicated at
intervals of 5 knots. Speed indication starts at 20 knots, with 60 knots of airspeed viewable at any time. The
actual airspeed is displayed inside the black pointer. The pointer remains black until reaching never-exceed
speed (VNE), at which point it turns red.

Airspeed

Actual
Airspeed

Color-coded
Speed
Ranges

Figure 2-3 Airspeed Indicator

Trend
Vector

Vspeed
Reference

Figure 2-4 Red Pointer

Showing Overspeed

True
Airspeed

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

A color-coded (red, white, green, yellow, and red/white ‘barber pole”) speed range strip is located on the

moving tape. The colors denote flaps operating range, normal operating range, caution range, and never-exceed
speed (VNE). A red range is also present for low speed awareness.

The Airspeed Trend Vector is a vertical, magenta line that appears to the right of the color-coded speed

range strip when airspeed is either accelerating or decelerating. One end of the magenta line is anchored to
the tip of the airspeed pointer while the other end moves continuously up or down corresponding to the rate
of acceleration or deceleration. For any constant rate of acceleration or deceleration, the moving end of the
line shows approximately what the indicated airspeed value will be in six seconds. If the trend vector crosses
VNE, the text of the actual airspeed readout changes to yellow. The trend vector is absent if the speed remains
constant or if any data needed to calculate airspeed is not available due to a system failure.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B50

FLIGHT INSTRUMENTS

Vspeeds (Glide, VX, and VY,) can be changed and their flags turned on/off from the Timer/References
Window (Figure 2-5). When active (on), the Vspeeds are displayed at their respective locations to the right
of the airspeed scale. By default, all Vspeed values are reset and all flags turned off when power is cycled.

OVERVIEW

SYSTEM

Changing Vspeeds and turning flags on/off:

1) Select the

2) Turn the

TMR/REF

large FMS

Softkey.

Knob to highlight the desired Vspeed.

3) Use the small FMS Knob to change the Vspeed in 1-kt increments (when a speed has been changed from a

default value, an asterisk appears next to the speed).

4) Press the

5) Turn the

6) To remove the window, press the

Figure 2-5 Timer/References Window

ENT

Key or turn the large FMS Knob to highlight the ON/OFF field

small FMS

Knob clockwise to ON or counterclockwise to OFF.

CLR

Key or select the

TMR/REF

Softkey.

Figure 2-6 Timer/References Menu

INSTRUMENTS

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HAZARD

Turning all Vspeed flags ON/OFF:

1) Select the

2) Press the

3) To view all Vspeed flags, highlight ‘All References On’ and press the

4) To remove all Vspeed flags, turn the FMS Knob to highlight ‘All References Off’ and press the

TMR/REF

MENU

Key.

Softkey.

ENT

Key (Figure 2-6).

ENT

Restoring all Vspeed defaults:

1) Select the

2) Press the

3) Turn the

TMR/REF

MENU

FMS

Softkey.

Key.

Knob to highlight ‘Restore Defaults’ and press the

ENT

Key.

Key.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

51

FLIGHT INSTRUMENTS

ATTITUDE INDICATOR

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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AVOIDANCE

AFCS

Attitude information is displayed over a virtual blue sky and brown ground with a white horizon line. The
Attitude Indicator displays the pitch (indicated by the yellow symbolic aircraft on the pitch scale), roll, and
slip/skid information.

9

1

1

2

3

4

8

7

6

5

Roll Pointer

2

Roll Scale

3

Horizon Line

4

Aircraft Symbol

5

Land Representation

6

Pitch Scale

7

Slip/Skid Indicator

8

Sky Representation

9

Roll Scale Zero

Figure 2-7 Attitude Indicator

The horizon line is part of the pitch scale. Above and below the horizon line, major pitch marks and numeric
labels are shown for every 10˚, up to 80˚. Minor pitch marks are shown for intervening 5˚ increments, up to
25˚ below and 45˚ above the horizon line. Between 20˚ below to 20˚ above the horizon line, minor pitch marks
occur every 2.5˚. If the optional Synthetic Vision System (SVS) is activated, the pitch scale is reduced to 10˚ up
and 7.5˚ down; refer to the Additional Features section for more information about SVS.

The inverted white triangle indicates zero on the roll scale. Major tick marks at 30˚ and 60˚ and minor tick
marks at 10˚, 20˚, and 45˚ are shown to the left and right of the zero. Angle of bank is indicated by the position
of the pointer on the roll scale.

The Slip/Skid Indicator is the bar beneath the roll pointer. The indicator moves with the roll pointer and
moves laterally away from the pointer to indicate lateral acceleration Slip/skid is indicated by the location of
the bar relative to the pointer. One bar displacement is equal to one ball displacement on a traditional Slip/Skid
Indicator.

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-8 Slip/Skid Indication

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B52

FLIGHT INSTRUMENTS

ALTIMETER

The Altimeter displays 600 feet of barometric altitude values at a time on a rolling number gauge using a
moving tape. Numeric labels and major tick marks are shown at intervals of 100 feet. Minor tick marks are at
intervals of 20 feet. The indicated altitude is displayed in the black pointer.

The Selected Altitude is displayed above the Altimeter in the box indicated by a selection bug symbol. A bug
corresponding to this altitude is shown on the tape; if the Selected Altitude exceeds the range shown on the
tape, the bug appears at the corresponding edge of the tape. The metric value, when selected, is displayed in a
separate box above the Selected Altitude.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

A magenta Altitude Trend Vector extends up or down the left of the altitude tape, the end resting at the
approximate altitude to be reached in 6 seconds at the current vertical speed. The trend vector is not shown if
altitude remains constant or if data needed for calculation is not available due to a system failure.

Setting the Selected Altitude:

Turn the

ALT

Knob to set the Selected Altitude (large knob for 1000-ft increments, small knob for 100-ft
increments, (increments reduce to 10 feet for approach). If set to Metric mode, the large knob adjusts the Selected
Altitude in 500-meter increments; the small knob adjusts the Selected Altitude in 50-meter increments.

If set, the Minimum Descent Altitude/Decision Height (MDA/DH) value is also available for the Selected Altitude.

Selected

Altitude

(Meters)

Altitude

Trend

Vector

Selected
Altitude

Indicated
Altitude

Indicated

Altitude
(Meters)

EIS

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AFCS

Altitude Bug

190-00870-00 Rev. B

Selected

Barometric

Setting

Figure 2-9 Altimeter

Garmin G950 Pilot’s Guide for the Pilatus PC-6

Minimum Descent
Altitude/Decision
Height Bug

Barometric
Setting
(Hectopascals)

Figure 2-10 Altimeter (Metric Units)

53

ADDITIONAL

FEATURES

APPENDICES INDEX

FLIGHT INSTRUMENTS

Selected and current altitudes can also be displayed in meters (readouts displayed above the normal readouts

SYSTEM

OVERVIEW

in feet; Figure 2-10). Note that the altitude tape does not change scale.

Displaying altitude in meters:

1) Select the PFD Softkey to display the second-level softkeys.

FLIGHT

INSTRUMENTS

EIS

& CNS

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FLIGHT

MANAGEMENT

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AVOIDANCE

2) Select the ALT UNIT Softkey.

3) Select the METERS Softkey to turn on metric altitude readouts.

4) Select the

BACK

Softkey to return to the top-level softkeys.

The barometric pressure setting is displayed below the Altimeter in inches of mercury (in Hg) or hectopascals
(hPa) when metric units are selected. Adjusting the altimeter barometric setting creates discontinuities in VNV
vertical deviation, moving the descent path. For large adjustments, it may take several minutes for the aircraft
to re-establish on the descent path. If the change is made while nearing a waypoint with a VNV Target Altitude,
the aircraft may not re-establish on the descent path in time to meet the vertical constraint.

Selecting the altimeter barometric pressure setting:

Turn the BARO Knob to select the desired setting.

Selecting standard barometric pressure (29.92 in Hg):

1) Select the PFD Softkey to display the second-level softkeys.

2) Select the STD BARO Softkey; STD BARO is displayed in barometric setting box.

Figure 2-11 Standard Barometric Altimeter Setting

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Changing altimeter barometric pressure setting units:

1) Select the PFD Softkey to display the second-level softkeys.

2) Select the ALT UNIT Softkey.

3) Select the IN Softkey to display the barometric pressure setting in inches of mercury (in Hg).

Or, select the HPA Softkey to display the barometric pressure setting in hectopascals (hPa; see Figure 2-10).

4) Select the

BACK

Softkey to return to the top-level softkeys.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B54

FLIGHT INSTRUMENTS

A Baro Transition Alert is provided to notify the pilot to change the barometric pressure setting when crossing
the baro transition altitude. If the aircraft is at least 500 feet below the transition altitude and then climbs
through this altitude and the STD BARO Softkey has not been pressed, the barometric pressure setting flashes
in light blue until the pressure setting is changed. If the aircraft is at least 500 feet above the transition altitude
and then descends through this altitude and the barometric pressure setting has not been changed from STD
BARO, the setting flashes in light blue until it is changed (Figure 2-12).

Setting the Baro Transition Alert:

1) Use the FMS Knob to select the AUX - System Setup Page.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

2) Press the FMS Knob to activate the cursor.

3) Turn the large FMS Knob to highlight ‘OFF or ON’ in the ‘BARO TRANSITION ALERT’ box.

4) Turn the small FMS Knob to turn the alert OFF or ON and press the ENT Key.

5) With the altitude field highlighted, turn the small FMS Knob to select the desired altitude and press the ENT

Key.

6) To cancel the selection, press the FMS Knob.

Pressure setting flashes during climb above
transition altitude if the STD BARO Softkey

has not been pressed.

Pressure setting flashes during descent below

transition altitude to indicate setting has not

been changed from STD BARO.

EIS

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FLIGHT

AVOIDANCE

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AFCS

190-00870-00 Rev. B

Figure 2-12 Baro Transition Alert

(AUX - System Setup Page)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

55

ADDITIONAL

FEATURES

APPENDICES INDEX

FLIGHT INSTRUMENTS

VERTICAL SPEED INDICATOR (VSI)

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

The Vertical Speed Indicator (VSI, Figure 2-13) displays the aircraft vertical speed using a non-moving tape
labeled at 1000 and 2000 fpm with minor tick marks every 500 fpm. The current vertical speed is displayed
in the pointer along the tape. Digits appear in the pointer when the climb or descent rate is greater than 100
fpm. If the rate of ascent/descent exceeds 2000 fpm, the pointer appears at the corresponding edge of the tape
and the rate appears inside the pointer.

A magenta chevron bug is displayed as the Required Vertical Speed Indication (RVSI; Figure 2-13) for reaching
a VNV Target Altitude once the “TOD [Top of Descent] within 1 minute” alert has been generated. Refer to
Section 2.2, Supplemental Flight Data, for more information about VNV indications on the PFD.

VERTICAL DEVIATION

NOTE:

WAAS is available.

The Vertical Deviation Indicator (VDI; Figure 2-13) is a magenta chevron indicating the baro-VNV vertical
deviation when Vertical Navigation (VNV) is being used. The VDI appears in conjunction with the “TOD within
1 minute” alert. The VDI is removed from the display if vertical deviation becomes invalid. See the Flight
Management Section for details on VNV features, and refer to Section 2.2, Supplemental Flight Data, for more
information about VNV indications on the PFD.

The Glideslope Indicator (Figure 2-14) appears to the left of the Altimeter whenever an ILS frequency is
tuned in the active NAV field. A green diamond acts as the Glideslope Indicator, like a glideslope needle on
a conventional indicator. If a localizer frequency is tuned and there is no glideslope, “NO GS” is displayed in
place of the diamond.

The glidepath is analogous to the glideslope for GPS approaches supporting WAAS vertical guidance (LNAV+V,
L/VNAV, LPV). When an approach of this type is loaded into the flight plan and GPS is the selected navigation
source, the Glidepath Indicator (Figure 2-15) appears as a magenta diamond during the approach. If the
approach type downgrades past the final approach fix (FAF), “NO GP” is displayed in place of the diamond.

Full-scale deflection (two dots) is 1000 feet.

Vertical

Deviation

Indicator

The Glidepath Indicator is only shown for aircraft with GIA 63W Integrated Avionics Units when

VNV Target
Altitude

Vertical
Speed
Indicator

Glideslope

Indicator
Vertical
Speed
Pointer

Required
Vertical
Speed

Marker
Beacon
Annunciation

Glidepath

Indicator

Figure 2-13 Vertical Speed and

Deviation Indicators (VSI and VDI)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

Figure 2-14 Glideslope Indicator

Figure 2-15 Glidepath Indicator

190-00870-00 Rev. B56

FLIGHT INSTRUMENTS

HORIZONTAL SITUATION INDICATOR (HSI)

The Horizontal Situation Indicator (HSI) displays a rotating compass card in a heading-up orientation. Letters
indicate the cardinal points and numeric labels occur every 30˚. Major tick marks are at 10˚ intervals and minor
tick marks at 5˚ intervals. A digital reading of the current heading appears on top of the HSI, and the current
track is represented on the HSI by a magenta diamond. The HSI also presents turn rate, course deviation,
bearing, and navigation source information and is available in two formats (360˚ compass rose and 140˚ arc).

Changing the HSI display format:

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

1) Select the

PFD

Softkey.

2) Select the HSI FRMT Softkey.

3) Select the

360 HSI

or

ARC HSI

Softkey.

The 360˚ HSI contains a Course Deviation Indicator (CDI), with a Course Pointer, To/From Indicator, and a
sliding deviation bar and scale. The course pointer is a single line arrow (GPS, VOR1, and LOC1) or a double
line arrow (VOR2 and LOC2) which points in the direction of the set course. The To/From arrow rotates with
the course pointer and is displayed when the active NAVAID is received.

1415 13

1

2

3

4

5

6

7

12

11

10

9

8

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AVOIDANCE

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AFCS

190-00870-00 Rev. B

1

Turn Rate Indicator

2

Current Track Indicator

3

Lateral Deviation Scale

4

Navigation Source

5

Aircraft Symbol

6

Course Deviation Indicator
(CDI)

7

Rotating Compass Rose

8

OBS Mode Active

9

To/From Indicator

10

Course Pointer

11

Selected Heading Bug

12

Flight Phase

13

Turn Rate/Heading
Trend Vector

14

Current Heading

15

Lubber Line

Figure 2-16 Horizontal Situation Indicator (HSI)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

57

ADDITIONAL

FEATURES

APPENDICES INDEX

FLIGHT INSTRUMENTS

The Arc HSI is a 140˚ expanded section of the compass rose. The Arc HSI contains a Course Pointer,

SYSTEM

OVERVIEW

To/From Indicator, a sliding deviation indicator (the To/From and deviation indicators are combined), and a
deviation scale. Upon station passage, the To/From Indicator flips and points to the tail of the aircraft, just like
a conventional To/From flag. Depending on the navigation source, the CDI on the Arc HSI can appear in two
different ways: an arrowhead (GPS, VOR, OBS) or a diamond (LOC).

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

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AVOIDANCE

Course Pointer

Navigation

Source

Lateral

Deviation

Scale

Figure 2-17 Arc HSI

Flight Phase
Annunciation

Course Deviation and
To/From Indicator

The Selected Heading is shown to the upper left of the HSI for 3 seconds after being adjusted The light blue
bug on the compass rose corresponds to the Selected Heading. While the HSI is displayed as an arc, if the
Selected Heading Bug is adjusted off the shown portion of the compass rose, the digital reading displayed.

Adjusting the Selected Heading:

Turn the

HDG

Knob to set the Selected Heading.

Press the HDG Knob to synchronize the bug to the current heading.

The Selected Course is shown to the upper right of the HSI for 3 seconds after being adjusted. While the
HSI is displayed as an arc, the Selected Course is displayed whenever the Course Pointer is not within the 140˚
currently shown.

Adjusting the Selected Course:

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Turn the

CRS

Knob to set the Selected Course.

Press the CRS Knob to re-center the CDI and return the course pointer to the bearing of the active waypoint or

navigation station (see OBS Mode for adjusting a GPS course).

Current HeadingCurrent Track Indicator

Selected

Selected
Heading

Figure 2-18 Heading and Course Indications

Course

Selected
Heading
Bug

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B58

FLIGHT INSTRUMENTS

Navigation angles (track, heading, course, bearing) are corrected to the computed magnetic variation (‘Mag
Var’) or referenced to true north (denoted ‘T’), set on the AUX - System Setup Page. When an approach
referenced to true north has been loaded into the flight plan, the system generates a message to change the
navigation angle setting to ‘True’ at the appropriate time.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

Figure 2-19 Heading and Course Indications (True)

Changing the navigation angle setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

Knob to highlight ‘Nav Angle’ in the ‘Display Units’ box.

4) Turn the small FMS Knob to highlight the desired setting and press the ENT Key.

 •TRUE - References angles to true north (denoted with ‘T’)

 •MAGNETIC - Angles corrected to the computed magnetic variation (‘Mag Var’)

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

190-00870-00 Rev. B

Figure 2-20 Navigation Angle Settings

(AUX - System Setup Page)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

59

ADDITIONAL

FEATURES

APPENDICES INDEX

FLIGHT INSTRUMENTS

TURN RATE INDICATOR

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

The Turn Rate Indicator is located directly above the rotating compass card. Tick marks to the left and right

of the lubber line denote half-standard and standard turn rates. A magenta Turn Rate Trend Vector shows the
current turn rate. The end of the trend vector gives the heading predicted in 6 seconds, based on the present
turn rate. A standard-rate turn is shown on the indicator by the trend vector stopping at the standard turn
rate tick mark, corresponding to a predicted heading of 18˚ from the current heading. At rates greater than 4
deg/sec, an arrowhead appears at the end of the magenta trend vector and the prediction is no longer valid.

Half-standard

Turn Rate

Standard

Turn Rate

Figure 2-21 Turn Rate Indicator and Trend Vector

Arrow Shown

for Turn Rate

> 4 deg/sec

BEARING INFORMATION

NOTE:

The pointers are light blue and are single- (BRG1) or double-lined (BRG2); an icon is shown in the respective
information window to indicate the pointer type. The bearing pointers never override the CDI and are
visually separated from the CDI by a white ring (shown when bearing pointers are selected but not necessarily
visible due to data unavailability).

When the Arc HSI is displayed, the Bearing Information windows and pointers are disabled.

Two bearing pointers and associated information can be displayed on the HSI for NAV, GPS and sources.

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Tuning Mode

Frequency

Distance

DME Information Window

(optional)

Distance to

Bearing Source

Bearing

Source

Bearing 1 Information Window

Pointer

Station

Identifier

Icon

Bearing 2

Pointer

Figure 2-22 HSI with Bearing and DME Information

Bearing 1

Pointer

Station

Identifier

Bearing 2 Information Window

Distance to

Bearing Source

Pointer

Icon

Bearing

Source

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B60

FLIGHT INSTRUMENTS

When a bearing pointer is displayed, its associated information window is also displayed. The Bearing

Information windows (Figure 2-22) are displayed to the lower sides of the HSI and show:

OVERVIEW

SYSTEM

•Bearingsource(NAV,GPS,ADF)

• Pointericon(BRG1=singleline,BRG2=doubleline)

•Station/waypointidentier(NAV,GPS)

• GPS-derivedgreatcircledistancetobearingsource

•Frequency(NAV,ADF)

If the NAV radio is the bearing source and is tuned to an ILS frequency (refer to the Audio Panel and CNS
Section for information on tuning the radios), the bearing pointer is removed from the HSI and the frequency
is replaced with “ILS”. When NAV1 or NAV2 is the selected bearing source, the frequency is replaced by the
station identifier when the station is within range. If GPS is the bearing source, the active waypoint identifier
is displayed in lieu of a frequency.

The bearing pointer is removed from the HSI and “NO DATA” is displayed in the information window if:

•TheNAVradioisnotreceivingthetunedVOR

station

•GPSisthebearingsourceandanactivewaypoint

is not selected

Selecting bearing display and changing sources:

1) Select the PFD Softkey.

2) Select a BRG Softkey to display the desired bearing pointer and information window with a NAV source.

3) Select the BRG Softkey again to change the bearing source to GPS.

4) Press the BRG Softkey a third time to change the bearing source to ADF (note: ADF radio installation is

optional).

5) To remove the bearing pointer and information window, select the BRG Softkey again.

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

DME INFORMATION WINDOW

NOTE:

the DME label, tuning mode (NAV1, NAV2, or HOLD), frequency, and distance. When a signal is invalid,
the distance is replaced by “–.– – NM”. Refer to the Audio Panel and CNS Section for information on tuning
the radios.

DME radio installation is optional.

The DME Information Window (Figure 2-22) is displayed above the BRG1 Information Window and shows

Displaying the DME Information Window:

1) Press the PFD Softkey.

2) Press the DME Softkey to display the DME Information Window above the BRG1 Information Window.

3) To remove the DME Information Window, press the DME Softkey again.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

61

FLIGHT INSTRUMENTS

COURSE DEVIATION INDICATOR (CDI)

SYSTEM

OVERVIEW

NOTE

:

If a heading change of greater than 105˚ with respect to the course is made, the CDI on the Arc HSI

switches to the opposite side of the deviation scale and displays reverse sensing.

The Course Deviation Indicator (CDI) moves left or right from the course pointer along a lateral deviation

FLIGHT

INSTRUMENTS

scale to display aircraft position relative to the course. If the course deviation data is not valid, the CDI is not
displayed.

360º HSI

EIS

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MANAGEMENT

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AVOIDANCE

AFCS

Navigation

Source

CDI

Flight
Phase

Navigation

Source

Scale

Crosstrack

Error

Figure 2-23 Course Deviation Indicator

Crosstrack

Error

CDI Scale

Arc HSI

Flight

Phase

CDI

The CDI can display two sources of navigation: GPS or NAV (VOR, localizer). Color indicates the current
navigation source: magenta (for GPS) or green (for VOR and LOC). The full scale limits for the CDI are defined
by a GPS-derived distance when coupled to GPS. When coupled to a VOR or localizer (LOC), the CDI has the
same angular limits as a mechanical CDI. If the CDI exceeds the maximum deviation on the scale (two dots)
while coupled to GPS, the crosstrack error (XTK) is displayed below the white aircraft symbol.

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-24 Navigation Sources

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B62

FLIGHT INSTRUMENTS

Changing navigation sources:

1) Select the CDI Softkey to change from GPS to VOR1 or LOC1. This places the light blue tuning box over the

NAV1 standby frequency in the upper left corner of the PFD.

2) Select the CDI Softkey again to change from VOR1 or LOC1 to VOR2 or LOC2. This places the light blue tuning

box over the NAV2 standby frequency.

3) Select the CDI Softkey a third time to return to GPS.

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

GPS

Selected

CDI

Softkey

Cycles Through

Navigation Sources

NAV1 Selected for Tuning

LOC1

Selected

Figure 2-25 Selecting a Navigation Source

LOC2

Selected

NAV2 Selected for Tuning

The system automatically switches from GPS to LOC navigation source and changes the CDI scaling accordingly

when all of the following occur:

•AlocalizerorILSapproachhasbeenloadedintotheactiveightplan

•Thenalapproachx(FAF)istheactiveleg,theFAFislessthan15nmaway,andtheaircraftismoving

toward the FAF

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

•Avalidlocalizerfrequencyhasbeentuned

•TheGPSCDIdeviationislessthan1.2timesfull-scaledeection

GPS steering guidance is still provided after the CDI automatically switches to LOC until LOC capture, up
to the Final Approach Fix (FAF) for an ILS approach, or until GPS information becomes invalid. Activating
a Vector-to-Final (VTF; see the Flight Management Section) also causes the CDI to switch to LOC navigation
source; GPS steering guidance is not provided after this switch.

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

63

ADDITIONAL

FEATURES

APPENDICES INDEX

FLIGHT INSTRUMENTS

GPS CDI SCALING

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

When GPS is the selected navigation source, the flight plan legs are sequenced automatically and

annunciations appear on the HSI for the flight phase. Flight phase annunciations are normally shown in
magenta, but when cautionary conditions exist the color changes to yellow. If the current leg in the flight plan
is a heading leg, ‘HDG LEG’ is annunciated in magenta beneath the aircraft symbol.

The current GPS CDI scale setting is displayed as ‘System CDI’ on the AUX - System Setup Page and the full-

scale deflection setting may also be changed (2.0 nm, 1.0 nm, 0.3 nm, or Auto) from this page. If the selected
scaling is smaller than the automatic setting for enroute and terminal phases, the CDI is scaled accordingly
and the selected setting is be displayed rather than the flight phase annunciation.

Changing the selected GPS CDI setting:

1) Use the FMS Knob to select the AUX - System Setup Page on the MFD.

2) Press the FMS Knob to activate the cursor.

3) Turn the

large FMS

Knob to highlight the ‘SELECTED’ field in the ‘GPS CDI’ box.

4) Turn the small FMS Knob to highlight the desired setting and press the ENT Key.

5) To cancel the selection, press the FMS Knob or the CLR Key.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-26 GPS CDI Settings

(AUX - System Setup Page)

When set to ‘Auto’ (default), the GPS CDI scale automatically adjusts to the desired limits based upon the

current phase of flight (Figure 2-27, Table 2-1).

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B64

FLIGHT INSTRUMENTS

2.0 nm

Enroute

(Oceanic if >200 nm
from nearest airport)

0.3 nm

Missed

Approach

1.0 nm

Approach

1.0 nm

Te rminal

1.0 nm

Te rminal

0.3 nm

Departure

CDI Full-scale Deflection

Refer to accompanying

approach CDI scaling figures

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

Figure 2-27 Automatic CDI Scaling

•Whenadepartureprocedureisactive,theCDIisscaledfordeparture (0.3 nm).

•Thesystemswitchesfromdeparturetoterminal CDI scaling (1.0 nm) under the following conditions:

- The next leg in the procedure is not aligned with the departure runway

-

The next leg in the departure procedure is not CA, CD, CF, CI, CR, DF, FA, FC, FD, FM, IF, or TF (see
Glossary for leg type definitions)

- After any leg in the departure procedure that is not CA or FA

•At30nmfromthedepartureairport,theenroute phase of flight is automatically entered and CDI scaling
changes to 2.0 nm over a distance of 1.0 nm, except under the following conditions:

- When navigating with an active departure procedure, the flight phase and CDI scale will not change until

the aircraft arrives at the last departure waypoint (if more than 30 nm from the departure airport) or the
leg after the last departure waypoint has been activated or a direct-to waypoint is activated.

•Ifaftercompletingthedepartureprocedurethenearestairportismorethan200nmawayfromtheaircraft

and the approach procedure has not yet commenced, the CDI is scaled for oceanic flight (2.0 nm).

•Within31nmofthedestinationairport(terminal area), the CDI scale gradually ramps down from 2.0 nm
to 1.0 nm over a distance of 1.0 nm; except under the following conditions:

- When navigating with an active arrival route, the flight phase and CDI scale will not change until the

aircraft arrives at the first waypoint in the arrival route (if within 31 nm from the destination airport).

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

190-00870-00 Rev. B

•Duringapproach, the CDI scale ramps down even further (see Figures 2-28 and 2-29). This transition
normally occurs within 2.0 nm of the final approach fix (FAF). The CDI switches to approach scaling
automatically once the approach procedure is activated or if Vector-to-Final (VTF) is selected.

- If the active waypoint is the FAF, the ground track and the bearing to the FAF must be within 45° of the

final approach segment course.

- If the active waypoint is part of the missed approach procedure, the active leg and preceding missed

approach legs must be aligned with the final approach segment course and the aircraft must not have
passed the turn initiation point.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

APPENDICES INDEX

65

FLIGHT INSTRUMENTS

1.0 nm

2 nm

350 ft

angle set
by system

0.3 nm

FA F

CDI Full-scale Deflection

CDI scale is set to the smaller of 0.3 nm

or an angle set by the system

CDI scale varies if VTF is activated

1.0 nm

2 nm

FA F

0.3 nm

course width

Landing

Threshold

CDI Full-scale Deflection

angle based
on database
information

CDI scale varies if VTF is activated

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

Figure 2-28 Typical LNAV and LNAV+V Approach CDI Scaling

Figure 2-29 Typical LNAV/VNAV and LPV Approach CDI Scaling

•Whenamissed approach is activated, the CDI scale changes to 0.3 nm.

•Thesystemautomaticallyswitchesbacktoterminal scaling under the following conditions:

- The next leg in the missed approach procedure is not aligned with the final approach path

-

The next leg in the missed approach procedure is not CA, CD, CF, CI, CR, DF, FA, FC, FD, FM, IF, or TF

- After any leg in the missed approach procedure that is not CA or FA

Flight Phase Annunciation Automatic CDI Full-scale Deflection

Departure DPRT 0.3 nm
Terminal TERM 1.0 nm
Enroute ENR 2.0 nm
Oceanic OCN 2.0 nm

Approach
(Non-precision)

Approach
(Non-precision with

LNAV

1.0 nm decreasing to 350 feet depending on
variables (see Figure 2-29)

LNAV + V

Vertical Guidance)
Approach

(LNAV/VNAV)
Approach

(LPV)

L/VNAV

LPV

1.0 nm decreasing to a specified course width, then

0.3 nm, depending on variables (see Figure 2-30)

Missed Approach MAPR 0.3 nm

APPENDICESINDEX

Table 2-1 Automatic GPS CDI Scaling

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B66

OBS MODE

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

NOTE:

VNV is inhibited while automatic waypoint sequencing has been suspended.

Enabling Omni-bearing Selector (OBS) Mode suspends the automatic sequencing of waypoints in a GPS
flight plan (GPS must be the selected navigation source), but retains the current “active-to” waypoint as the
navigation reference even after passing the waypoint. ‘OBS’ is annunciated to the lower right of the aircraft
symbol when OBS Mode is selected.

While OBS Mode is enabled, a course line is drawn through the “active-to” waypoint on the moving map.
If desired, the course to/from the waypoint can now be adjusted. When OBS Mode is disabled, the GPS flight
plan returns to normal operation with automatic sequencing of waypoints, following the course set in OBS
Mode. The flight path on the moving map retains the modified course line.

GPS

Selected

OBS Mode

OBS

Enabled

Selecting the

Softkey Again

Returns to Normal

Operation

OBS

Extended

Course

Line

Selecting the
Softkey Suspends

Waypoint Sequencing

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Figure 2-30 Omni-bearing Selector (OBS) Mode

Enabling/disabling OBS Mode while navigating a GPS flight plan:

1) Select the OBS Softkey to select OBS Mode.

2) Turn the CRS Knob to select the desired course to/from the waypoint. Press the CRS Knob to synchronize the

Selected Course with the bearing to the next waypoint.

3) Select the OBS Softkey again to return to automatic waypoint sequencing.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

67

FLIGHT INSTRUMENTS

As the aircraft crosses the missed approach point (MAP), automatic approach waypoint sequencing is

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

suspended. ‘SUSP’ appears on the HSI at the lower right of the aircraft symbol. The
changes to indicate the suspension is active as shown in Figure 2-31. Pressing the SUSP Softkey, deactivates
the suspension and resumes automatic sequencing of approach waypoints.

Annunciation

SUSP

Softkey Suspends

Waypoint Sequencing

SUSP

OBS

Softkey label

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

Figure 2-31 Suspending Automatic Waypoint Sequencing

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B68

2.2 SUPPLEMENTAL FLIGHT DATA

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

NOTE:

Selecting the DFLTS Softkey (a second-level PFD softkey) turns off metric Altimeter display, the Inset

Map, and wind data display.

In addition to the flight instruments, the PFD also displays various supplemental information, including the

Outside Air Temperature (OAT), wind data, and Vertical Navigation (VNV) indications.

OUTSIDE AIR TEMPERATURE

The Outside Air Temperature (OAT) is displayed in degrees Celsius (°C) in the lower left of the PFD under

normal display conditions. During reversionary display conditions the OAT is displayed to the right of the flap
indicator.

Normal Display

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Reversionary Mode with EIS

Figure 2-32 Outside Air Temperature

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

69

FLIGHT INSTRUMENTS

WIND DATA

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

Wind direction and speed (relative to the aircraft) in knots can be displayed in a window to the upper left of
the HSI. When the window is selected for display, but wind information is invalid or unavailable, the window
shows “NO WIND DATA”. Wind data can be displayed in three different ways:

Option 1

Option 3

Figure 2-33 Wind Data

Option 2

No Data

Displaying wind data:

1) Select the PFD Softkey.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

2) Select the WIND Softkey to display wind option Softkeys.

3) Select one of the OPTN softkeys to change how wind data is displayed:

 •OPTN 1: Head and crosswind components

 •OPTN 2: Total wind direction and speed

 •OPTN 3: Total wind direction with head and crosswind speed components

4) To remove the window, select the OFF Softkey.

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B70

FLIGHT INSTRUMENTS

VERTICAL NAVIGATION (VNV) INDICATIONS

When a VNV flight plan has been activated, VNV indications (VNV Target Altitude, RVSI, VDI) appear on the
PFD in conjunction with the “TOD within 1 minute” message and “Vertical track” voice alert. See the Flight
Management Section for details on VNV features. VNV indications are removed from the PFD according to the
criteria listed in Table 2-2.

Top of Descent Message

VNV Target

Altitude

Vertical

Deviation

Indicator

Required

Vertical

Speed Bug

GPS is

Selected

Navigation

Source

Terminal
Phase of

Flight

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

Figure 2-34 Vertical Navigation Indications (PFD)

VNV Indication Removed

Criteria

Required Vertical

Speed (RVSI)

Vertical

Deviation (VDI)

VNV Target

Altitude

Aircraft > 1 min before the next TOD due to flight plan change X X X
VNV cancelled (CNCL VNV Softkey selected on MFD) X X X
Distance to active waypoint cannot be computed due to

unsupported flight plan leg type (see Flight Management

X X X

Section)
Aircraft > 250 feet below active VNV Target Altitude X X X
Current crosstrack or track angle error has exceeded limit X X X
Active altitude-constrained waypoint can not be reached within

maximum allowed flight path angle and vertical speed

Table 2-2 VNV Indication Removal Criteria

X X

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

71

FLIGHT INSTRUMENTS

2.3 PFD ANNUNCIATIONS AND ALERTING FUNCTIONS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

The following annunciations and alerting functions are displayed on the PFD. Refer to Appendix A for more

information on alerts and annunciations.

SYSTEM ALERTING

Messages appear in the Alerts Window (in the lower right corner of the PFD; Figure 2-35) when a warning,
caution, advisory alert, or G950 message advisory occurs. System alert messages are provided for aware of
G950 system problems or status and may not require pilot action. The Alerts Window allows system alerts to be
displayed simultaneously. The FMS Knob can be used to scroll through the alert messages. The Alerts Window
is enabled/disabled by selecting the
generated, selecting the ALERTS Softkey to acknowledge the message causes it to turn gray.

The ALERTS Softkey label changes to display the appropriate annunciation when an alert is issued. The
annunciation flashes and the appropriate aural alert sounds until acknowledged by pressing the softkey. The
softkey then reverts to the ALERTS Softkey label, and when selected again opens the Alerts Window to display
a descriptive message of the alert.

The Annunciation Window appears to the right of the Vertical Speed Indicator and displays abbreviated
annunciation text for aircraft alerts. Text color is based on alert level: warnings appear in red, cautions in
yellow, advisory alerts in white. New alerts, regardless of priority, are displayed at the top of the Annunciation
Window, separated by a white line from acknowledged alerts. Once acknowledged, they are sequenced based
on priority.

ALERTS

Softkey. If the window is already open when a new message is

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Annunciation
Window

Alerts

Window

Softkey
Annunciation

Figure 2-35 G950 Alerting System

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B72

FLIGHT INSTRUMENTS

MARKER BEACON ANNUNCIATIONS

Marker Beacon Annunciations are displayed on the PFD to the left of the Selected Altitude. Outer marker
reception is indicated in blue, middle in yellow, and inner in white. Refer to the Audio Panel and CNS Section
for more information on Marker Beacon Annunciations.

Inner MarkerMiddle MarkerOuter Marker

Altimeter

Figure 2-36 Marker Beacon Annunciations

OVERVIEW

SYSTEM

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

TRAFFIC ANNUNCIATION

The G950 System displays traffic symbolically on the PFD Inset Map, the Navigation Map Page (MFD), and
various other MFD page maps. Refer to the Hazard Avoidance Section and Appendix E for more details about
the Traffic Information Service (TIS). When a traffic advisory (TA) is detected, the following automatically
occur:

•ThePFDInsetMapisenabledanddisplaystrafc

•A ashing black-on-yellow ‘TRAFFIC’ annunciation (Figure 2-37) appears to the top left of the Attitude

Indicator for five seconds and remains displayed until no TAs are detected in the area

•Asingle“Traffic” aural alert is generated, unless an optional Traffic Advisory System (TAS) is installed (refer

to the applicable TAS documentation for alerts generated by TAS equipment)

If additional TAs appear, new aural and visual alerts are generated.

Traffic
Symbols

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Figure 2-37 Traffic Annunciation and Inset Map with Traffic Displayed

Garmin G950 Pilot’s Guide for the Pilatus PC-6

73

FLIGHT INSTRUMENTS

TAWS ANNUNCIATIONS

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

Terrain Awareness and Warning System (TAWS) annunciations appear on the PFD at the top left of the Altimeter.

Refer to the Hazard Avoidance Section and Appendix A for information on TAWS alerts and annunciations.

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Figure 2-38 Traffic and TAWS Annunciations

ALTITUDE ALERTING

The Altitude Alerting function provides visual and aural alerts when the aircraft is approaching the Selected
Altitude. Whenever the Selected Altitude is changed, the Altitude Alerter is reset. The Altitude Alerter is
independent of the installed AFCS. The following occur when approaching the Selected Altitude:

•Uponpassingthrough1000feetoftheSelectedAltitude,theSelectedAltitude(shownabovetheAltimeter)

changes to black text on a light blue background, flashes for 5 seconds, and an aural tone is generated.

•Whentheaircraftpasseswithin200ftoftheSelectedAltitude,theSelectedAltitudechangestolightbluetext

on a black background and flashes for 5 seconds, and an aural tone is generated.

•AfterreachingtheSelectedAltitude,iftheaircraftiesoutsidethedeviationband(±200feetoftheSelected

Altitude), the Selected Altitude changes to yellow text on a black background, flashes for 5 seconds, and an

aural tone is generated.

Within 1000 feet Within 200 feet Deviation of ±200 feet

Figure 2-39 Altitude Alerting Visual Annunciations

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B74

LOW ALTITUDE ANNUNCIATION

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

NOTE:

The Low Altitude Annunciation is only available when WAAS is available and TAWS-B alerting has

been inhibited.

When the Final Approach Fix (FAF) is the active waypoint in a RNAV GPS approach using vertical guidance,
a Low Altitude Annunciation may appear if the current aircraft altitude is at least 164 feet below the prescribed
altitude at the FAF. A black-on-yellow ‘LOW ALT’ annunciation appears to the top right of the Altimeter,
flashing for several seconds then remaining displayed until the condition is resolved.

Altimeter

Figure 2-40 Low Altitude on RNAV GPS Approach with Vertical Guidance

MINIMUM DESCENT ALTITUDE/DECISION HEIGHT ALERTING

For altitude awareness, a barometric Minimum Descent Altitude (MDA) or Decision Height (DH) can be set
in the Timer/References Window and is reset when the power is cycled. When active, the altitude setting is
displayed to the lower left of the Altimeter and with a bug at the corresponding altitude along the Altimeter
(once the altitude is within the range of the tape).

The following visual annunciations occur when approaching the MDA/DH:

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

•Whentheaircraftaltitudedescendstowithin2500feetoftheMDA/DHsetting,the‘BAROMIN’boxappears

with the altitude in light blue text. The bug appears on the altitude tape in light blue once in range.

•Whentheaircraftpassesthrough100feetoftheMDA/DH,thebugandtextturnwhite.

•Once the aircraft reaches the MDA/DH, the bug and text turn yellow and the aural alert, “Minimums

Minimums”, is generated.

Alerting is inhibited while the aircraft is on the ground and until the aircraft reaches 150 feet above the setting
for the alert. If the aircraft proceeds to climb after having reached the MDA/DH, once it reaches 50 feet above
the MDA/DH, alerting is disabled.

Within 2500 feet

MDA/DH

Bug

MDA/DH

Setting

Figure 2-41 Minimum Descent Altitude/Decision Height Alerting Visual Annunciations

Altitude ReachedWithin 100 feet

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

75

FLIGHT INSTRUMENTS

Alerting is inhibited while the aircraft is on the ground and until the aircraft reaches 150 feet above the setting

SYSTEM

OVERVIEW

for the alert. If the aircraft proceeds to climb after having reached the MDA/DH, once it reaches 50 feet above
the MDA/DH, alerting is disabled.

The MDA/DH may be set from the PFD. It is synchronized on both PFDs in a 3 Display System. The function

is reset when the power is cycled.

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

HAZARD

AVOIDANCE

Setting the barometric minimum descent altitude/decision height and bug:

1) Select the

TMR/REF

Softkey.

2) Turn the large FMS Knob to highlight the ‘Minimums’ field (Figure 2-42).

3) Turn the small FMS Knob to select ‘BARO’. ‘OFF’ is selected by default. Press the ENT Key or turn the large

FMS Knob to highlight the next field.

4) Use the small FMS Knob to enter the desired altitude (from zero to 16,000 feet).

5) To remove the window, press the

CLR

Key or press the

Figure 2-42 MDA/DH Setting

(Timer/References Window)

TMR/REF

Softkey.

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B76

2.4 ABNORMAL OPERATIONS

FLIGHT INSTRUMENTS

OVERVIEW

SYSTEM

ABNORMAL GPS CONDITIONS

The annunciations listed in Table 2-3 can appear on the HSI when abnormal GPS conditions occur; see Figure
2-43 for examples. Refer to the Flight Management Section for more information on Dead Reckoning Mode.

Annunciation Location Description

LOI

INTEG OK

DR

Lower left of

aircraft symbol

Lower left of

aircraft symbol

Upper right of

aircraft symbol

Table 2-3 Abnormal GPS Conditions Annunciated on HSI

Loss of Integrity Monitoring–GPS integrity is insufficient for the current
phase of flight

Integrity OK–GPS integrity has been restored to within normal limits
(annunciation displayed for 5 seconds)

Dead Reckoning–System is using projected position rather than GPS position
to compute navigation data and sequence active flight plan waypoints

INSTRUMENTS

FLIGHT

EIS

AUDIO PANEL

& CNS

MANAGEMENT

FLIGHT

AVOIDANCE

HAZARD

Figure 2-43 Example HSI Annunciations

Dead Reckoning Mode causes the CDI to be removed from the display (when GPS is the selected navigation
source) and the following items on the PFD to be shown in yellow:

•CurrentTrackIndicator

•WindData

•GroundSpeed

•DistancesintheBearingInformationwindows

•GPSbearingpointers

These items should be verified when operating in Dead Reckoning Mode as they become increasingly
inaccurate over time.

AFCS

ADDITIONAL

FEATURES

APPENDICES INDEX

190-00870-00 Rev. B

Garmin G950 Pilot’s Guide for the Pilatus PC-6

77

FLIGHT INSTRUMENTS

UNUSUAL ATTITUDES

SYSTEM

OVERVIEW

FLIGHT

INSTRUMENTS

EIS

& CNS

AUDIO PANEL

FLIGHT

MANAGEMENT

When the aircraft enters an unusual pitch attitude, red extreme pitch warning chevrons pointing toward the

horizon are displayed on the Attitude Indicator, starting at 50˚ above and 30˚ below the horizon line.

Nose High

Figure 2-44 Pitch Attitude Warnings

Nose Low

If pitch exceeds +30˚/-20˚ or bank exceeds 65˚, some information displayed on the PFD is removed. The
Altimeter and Airspeed, Attitude, Vertical Speed, and Horizontal Situation indicators remain on the display
and the Bearing Information, Alerts, and Annunciation windows can be displayed during such situations. The
following information is removed from the PFD (and corresponding softkeys are disabled) when the aircraft
experiences unusual attitudes:

HAZARD

AVOIDANCE

AFCS

FEATURES

ADDITIONAL

APPENDICESINDEX

•TrafcAnnunciations

•AFCSAnnunciations

•FlightdirectorCommandBars

•InsetMap

•Outsideairtemperature(OAT)

•DMEInformationWindow

•Winddata

•SelectedHeadingreadout

•SelectedCoursereadout

•TransponderStatusBox

•SystemTime

•PFDSetupMenu

•Windowsdisplayedinthelower

right corner of the PFD:

– Timer/References

– Nearest Airports

– Flight Plan

– Messages

– Procedures

– ADF/DME Tuning

•Minimum Descent Altitude/

Decision Height readout

•Vertical Deviation, Glideslope,

and Glidepath Indicators

•AltimeterBarometricSetting

•SelectedAltitude

•VNVTargetAltitude

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B78

ENGINE INDICATION SYSTEM

SECTION 3 ENGINE INDICATION SYSTEM

The G950 Engine Indication System (EIS) displays critical engine, electrical, fuel, and other system parameters

on the left side of the MFD during normal operations (Figure 3-1).

EIS Display

OVERVIEW

OVERVIEW

SYSTEM

SYSTEM

INSTRUMENTS

INSTRUMENTS

FLIGHT

FLIGHT

EIS

EIS

AUDIO PANEL

AUDIO PANEL

& CNS

& CNS

MANAGEMENT

MANAGEMENT

FLIGHT

FLIGHT

Figure 3-1 MFD

Green bands on the instruments indicate normal ranges of operation; yellow and red bands indicate caution
and warning, respectively. White or uncolored bands indicate areas outside of normal operation not yet in the
caution or warning ranges. When unsafe operating conditions occur, the corresponding readouts flash to indicate
cautions and warnings. If sensory data to an instrument becomes invalid or unavailable, a red “X” is displayed
across the instrument.

AVOIDANCE

AVOIDANCE

HAZARD

HAZARD

AFCS

AFCS

ADDITIONAL

ADDITIONAL

FEATURES

FEATURES

APPENDICES INDEX

APPENDICES INDEX

190-00870-00 Rev. B 79

Garmin G950 Pilot’s Guide for the Pilatus PC-6

ENGINE INDICATION SYSTEM

SYSTEM

SYSTEM

OVERVIEW

OVERVIEW

FLIGHT

FLIGHT

INSTRUMENTS

INSTRUMENTS

3.1 ENGINE DISPLAY

The Engine Display is shown by default. If another EIS display is currently shown, the Engine Display may be
selected by pressing the ENGINE or BACK Softkey. At the top of all three EIS displays, the Torque, Interstage
Turbine Temperature (ITT), Propeller Speed, and Gas Generator Speed gauges are present. Trim and flap
indications are also shown on all EIS displays.

NOTE

:

Refer to the Pilot’s Operating Handbook (POH) for engine operating limitations.

EIS

EIS

& CNS

& CNS

AUDIO PANEL

AUDIO PANEL

FLIGHT

FLIGHT

MANAGEMENT

MANAGEMENT

HAZARD

HAZARD

AVOIDANCE

AVOIDANCE

AFCS

AFCS

FEATURES

FEATURES

ADDITIONAL

ADDITIONAL

APPENDICESINDEX

APPENDICESINDEX

1

Torque Gauge

(TRQ FT-LB)

2

Interstage Turbine

Temperature Gauge
(ITT °C)

3

Propeller Speed Gauge

(NP RPM)

4

Gas Generator Speed

Gauge (NG %)

5

Fuel Flow

(FFLOW GPH)

6

Oil Pressure Indicator

(OIL PSI)

7

Oil Temperature Indicator

(OIL °C)

8

Ammeter

(AMPS)

9

Voltmeter

(VOLTS)

10

Fuel Quantity Indicator

(FUEL QTY)

11

Aileron and Rudder Trim

Bars (AIL, RUD)

12

Flap Position Indicator

(FLAPS)

13

Elevator Trim Bar

(ELEV)

Displays engine torque in foot-pounds (ft-lb)

Displays Interstage Turbine Temperature (ITT) in degrees Celsius (°C)

When the engine is not running, ‘OFF’ is annunciated above the ITT readout;

this changes to ‘STRT’ upon engine start. No annunciation is shown when
the engine is running normally (see Figure 3-3).

Displays propeller speed in revolutions per minute (rpm)

Displays gas generator speed as a percentage

Displays current fuel flow in gallons per hour (gph)

Displays engine oil pressure in pounds per square inch (psi)

Displays engine oil temperature in °C

Displays DC current in amperes (amps) for the generator (G); Alternate Power

(A) is not used

Displays DC bus voltages for bus 1 and bus 2.

Displays quantities of fuel in gallons in the main left (L) and right (R) tanks

Aileron and rudder trim are indicated with pointers along slide bars; the

green bars indicate takeoff trim positions

Flap deflection is indicated with a pointer along a slide bar; takeoff flap

position is indicated with a green bar

Elevator trim is indicated with a pointer along a slide bar; takeoff trim position

is indicated with a green bar and T/O label

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B80

ENGINE INDICATION SYSTEM

OVERVIEW

OVERVIEW

SYSTEM

SYSTEM

1

INSTRUMENTS

INSTRUMENTS

FLIGHT

2

FLIGHT

3

EIS

EIS

4

AUDIO PANEL

AUDIO PANEL

5

& CNS

& CNS

6

10

11

7

MANAGEMENT

MANAGEMENT

FLIGHT

FLIGHT

8

9

12

13

Figure 3-2 Engine Display

NormalEngine Start

Engine Off

AVOIDANCE

AVOIDANCE

HAZARD

HAZARD

AFCS

AFCS

ADDITIONAL

ADDITIONAL

FEATURES

FEATURES

APPENDICES INDEX

APPENDICES INDEX

Figure 3-3 Interstage Turbine Temperature Gauge Status Annunciations

190-00870-00 Rev. B 81

Garmin G950 Pilot’s Guide for the Pilatus PC-6

ENGINE INDICATION SYSTEM

SYSTEM

SYSTEM

OVERVIEW

OVERVIEW

FLIGHT

FLIGHT

INSTRUMENTS

INSTRUMENTS

3.2 SYSTEM DISPLAY

NOTE:

Refer to the Pilot’s Operating Handbook (POH) for limitations.

The System Display (Figure 3-4) is accessed by pressing the SYSTEM Softkey. The instruments presented here,
in addition to the gauges and trim slide bars, are presented into two categories: Oil (pressure and temperature)
and Electrical (currents and voltages).

Accessing the EIS System Display:

EIS

EIS

& CNS

& CNS

AUDIO PANEL

AUDIO PANEL

FLIGHT

FLIGHT

MANAGEMENT

MANAGEMENT

HAZARD

HAZARD

AVOIDANCE

AVOIDANCE

AFCS

AFCS

FEATURES

FEATURES

ADDITIONAL

ADDITIONAL

APPENDICESINDEX

APPENDICESINDEX

1) Press the ENGINE Softkey.

2) Press the SYSTEM Softkey.

3) To return to the default Engine Display, press the ENGINE or BACK Softkey.

1

Torque Gauge

(TRQ FT-LB)

2

Interstage Turbine

Temperature Gauge
(ITT °C)

3

Propeller Speed Gauge

(NP RPM)

4

Generator Speed Gauge

(NG %)

5

Oil Pressure

(PRES PSI)

6

Oil Temperature

(TEMP °C)

7

Ammeter

(GEN A, ALT A)

8

Voltmeter

(BUS 1 V, BUS 2 V)

9

Aileron and Rudder Trim

Bars (AIL, RUD)

10

Flap Position Indicator

(FLAPS)

11

Elevator Trim Bar

(ELEV)

Displays engine torque in foot-pounds (ft-lb)

Displays Interstage Turbine Temperature (ITT) in degrees Celsius (°C) When

the engine is not running, ‘OFF’ is annunciated above the ITT readout; this
changes to ‘STRT’ upon engine start. No annunciation is shown when the
engine is running normally

Displays propeller speed in revolutions per minute (rpm)

Displays gas generator speed as a percentage

Displays engine oil pressure in pounds per square inch (psi)

Displays engine oil temperature in °C

Displays DC current in amperes (A) for the generator (GEN); Alternate Power

(ALT) is not used

Displays DC bus voltages

Aileron and rudder trim are indicated with pointers along slide bars; the

green bars indicate takeoff trim positions

Flap deflection is indicated with a pointer along a slide bar; takeoff flap

position is indicated with a green bar

Elevator trim is indicated with a pointer along a slide bar; takeoff trim position

is indicated with a green bar and T/O label

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B82

ENGINE INDICATION SYSTEM

OVERVIEW

OVERVIEW

SYSTEM

SYSTEM

INSTRUMENTS

INSTRUMENTS

FLIGHT

FLIGHT

1

2

3

EIS

EIS

AUDIO PANEL

AUDIO PANEL

& CNS

& CNS

4

MANAGEMENT

MANAGEMENT

FLIGHT

FLIGHT

5

6

AVOIDANCE

AVOIDANCE

HAZARD

HAZARD

AFCS

10

AFCS

7

8

11

9

Figure 3-4 System Display

190-00870-00 Rev. B 83

Garmin G950 Pilot’s Guide for the Pilatus PC-6

ADDITIONAL

ADDITIONAL

FEATURES

FEATURES

APPENDICES INDEX

APPENDICES INDEX

ENGINE INDICATION SYSTEM

SYSTEM

SYSTEM

OVERVIEW

OVERVIEW

FLIGHT

FLIGHT

INSTRUMENTS

INSTRUMENTS

EIS

EIS

3.3 FUEL DISPLAY

NOTE:

The Fuel Display (Figure 3-5) is accessed by pressing the FUEL Softkey. Besides the gauges and trim slide bars,
all indications on this display are digital readouts, separated into three categories: Oil (pressure and temperature),
Fuel (flow, pressure, and quantities), and Fuel Calculations (fuel remaining and used, endurance, and range).

Fuel calculations do not use the aircraft fuel quantity indicators and are calculated from the last time

the fuel was reset.

NOTE:

Refer to the Pilot’s Operating Handbook (POH) for limitations.

Accessing the EIS Fuel Display:

1) Press the ENGINE Softkey.

2) Press the FUEL Softkey.

& CNS

& CNS

AUDIO PANEL

AUDIO PANEL

the pilot using the following softkeys:

•DEC FUEL – Decreases totalizer-based fuel remaining in 1-gal increments

FLIGHT

FLIGHT

MANAGEMENT

MANAGEMENT

HAZARD

HAZARD

AVOIDANCE

AVOIDANCE

AFCS

AFCS

FEATURES

FEATURES

ADDITIONAL

ADDITIONAL

APPENDICESINDEX

APPENDICESINDEX

•INC FUEL – Increases totalizer-based fuel remaining in 1-gal increments

•RST FUEL – Resets totalizer-based fuel remaining to 170-gal and the displayed fuel used (GAL USED) to zero

3) To return to the default Engine Display, press the ENGINE or BACK Softkey.

Fuel calculations are based on the fuel flow totalizer and the displayed fuel remaining (GAL REM), adjusted by

1

Torque Gauge

Displays engine torque in foot-pounds (ft-lb)

(TRQ FT-LB)

2

Interstage Turbine

Temperature Gauge
(ITT °C)

Displays Interstage Turbine Temperature (ITT) in degrees Celsius (°C) When

the engine is not running, ‘OFF’ is annunciated above the ITT readout; this
changes to ‘STRT’ upon engine start. No annunciation is shown when the
engine is running normally.

3

Propeller Speed Gauge

Displays propeller speed in revolutions per minute (rpm)

(NP RPM)

4

Generator Speed Gauge

Displays gas generator speed as a percentage

(NG %)

5

Oil Pressure

Displays engine oil pressure in pounds per square inch (psi)

(PRES PSI)

6

Oil Temperature

Displays engine oil temperature in °C

(TEMP °C)

7

Fuel Flow

Displays current fuel flow in gallons per hour (gph)

(FFLOW GPH)

8

Fuel Pressure

Displays current fuel pressure in psi

(PRES PSI)

9

Fuel Quantities

Displays quantities of fuel in gallons in the left (L) and right (R) tanks

(QTY L/R GAL)

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B84

ENGINE INDICATION SYSTEM

10

Set Fuel Remaining

(GAL REM)

11

Calculated Fuel Used

(GAL USED)

12

Calculated Endurance

(ENDUR)

13

Calculated Range

(RANGE NM)

14

Aileron and Rudder Trim

Bars (AIL, RUD)

15

Flap Position Indicator

(FLAPS)

16

Elevator Trim Bar

(ELEV)

Displays current fuel remaining in gallons as set by the pilot and adjusted for

fuel burn since last set

Displays quantity of fuel used in gallons based on fuel flow since last reset

Displays flight time remaining in hours:minutes (HH:MM) based on the

calculated fuel remaining

Displays aircraft range in nautical miles (nm) based on the calculated fuel

remaining, the aircraft’s heading, and the wind direction and speed

Aileron and rudder trim are indicated with pointers along slide bars; the green

bars indicate takeoff trim positions

Flap deflection is indicated with a pointer along a slide bar; takeoff flap

position is indicated with a green bar

Elevator trim is indicated with a pointer along a slide bar; takeoff trim position

is indicated with a green bar and T/O label

OVERVIEW

OVERVIEW

SYSTEM

SYSTEM

INSTRUMENTS

INSTRUMENTS

FLIGHT

FLIGHT

EIS

EIS

AUDIO PANEL

AUDIO PANEL

& CNS

& CNS

10

1

2

3

4

5

6

7

8

9

15

MANAGEMENT

MANAGEMENT

FLIGHT

FLIGHT

AVOIDANCE

AVOIDANCE

HAZARD

HAZARD

AFCS

AFCS

ADDITIONAL

ADDITIONAL

FEATURES

FEATURES

APPENDICES INDEX

APPENDICES INDEX

11

12

13

16

14

Figure 3-5 Fuel Display

190-00870-00 Rev. B 85

Garmin G950 Pilot’s Guide for the Pilatus PC-6

ENGINE INDICATION SYSTEM

SYSTEM

SYSTEM

OVERVIEW

OVERVIEW

FLIGHT

FLIGHT

INSTRUMENTS

INSTRUMENTS

EIS

EIS

& CNS

& CNS

AUDIO PANEL

AUDIO PANEL

FLIGHT

FLIGHT

MANAGEMENT

MANAGEMENT

3.4 EIS DISPLAY IN REVERSIONARY MODE

In reversionary mode, the remaining display is re-configured to present PFD symbology together with the
EIS Display (refer to the System Overview for information about display Reversionary Mode). When the G950
displays enter reversionary mode, the EIS is separated into Engine, System, and Fuel displays. The displays are
identical to the displays in normal mode.

EIS Display

HAZARD

HAZARD

AVOIDANCE

AVOIDANCE

AFCS

AFCS

FEATURES

FEATURES

ADDITIONAL

ADDITIONAL

APPENDICESINDEX

APPENDICESINDEX

Figure 3-6 Reversionary Mode

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B86

ENGINE INDICATION SYSTEM

EIS SOFTKEYS

ENGINE

Select the ENGINE Softkey to
return to the top-level softkeys.

INC FUEL RST FUEL DCLTR ASSIST DEC FUEL

ENGINE

CO RST

(optional)

Select the BACK Softkey to
return to the top-level softkeys.

SYSTEM

ENGINE

LEAN INC FUEL RST FUELDEC FUEL BACK

SYSTEM

ENGINE

LEAN

BACK

ENGINE

CO RST

(optional)

SYSTEM

ENGINE

LEAN

BACK

ASSISTCYL SLCT

Select the BACK Softkey to
return to the top-level softkeys.

ENGINE

INC FUEL RST FUELDEC FUEL BACK

ENGINE FUEL BACK

ENGINE

SYSTEM

FUEL

SYSTEM

ENGINE FUEL BACK

SYSTEM

The Engine Display is shown by default. To return to the Engine Display from the System or Fuel Display,

select the ENGINE or BACK Softkey.

OVERVIEW

OVERVIEW

SYSTEM

SYSTEM

INSTRUMENTS

INSTRUMENTS

FLIGHT

FLIGHT

EIS

EIS

AUDIO PANEL

AUDIO PANEL

& CNS

& CNS

MANAGEMENT

MANAGEMENT

FLIGHT

FLIGHT

Figure 3-7 EIS Softkeys (Reversionary Mode)

•ENGINE

•SYSTEM

•FUEL

DEC FUEL
INC FUEL
RST FUEL

Displays second-level engine softkeys
Displays the EIS System Display
Displays the EIS Fuel Display
Decreases displayed fuel remaining in 1-gal increments
Increases displayed fuel remaining in 1-gal increments
Resets displayed fuel remaining to 170-gal and fuel used to zero

AVOIDANCE

AVOIDANCE

HAZARD

HAZARD

AFCS

AFCS

ADDITIONAL

ADDITIONAL

FEATURES

FEATURES

APPENDICES INDEX

APPENDICES INDEX

190-00870-00 Rev. B 87

Garmin G950 Pilot’s Guide for the Pilatus PC-6

ENGINE INDICATION SYSTEM

SYSTEM

SYSTEM

OVERVIEW

OVERVIEW

FLIGHT

FLIGHT

INSTRUMENTS

INSTRUMENTS

EIS

EIS

& CNS

& CNS

AUDIO PANEL

AUDIO PANEL

FLIGHT

FLIGHT

MANAGEMENT

MANAGEMENT

Bl a n k Pa g e

HAZARD

HAZARD

AVOIDANCE

AVOIDANCE

AFCS

AFCS

FEATURES

FEATURES

ADDITIONAL

ADDITIONAL

APPENDICESINDEX

APPENDICESINDEX

Garmin G950 Pilot’s Guide for the Pilatus PC-6

190-00870-00 Rev. B88