Instrument Rating Ground School: Integrated Displays and PFD Indicators

PHOENIX EAST AVIATION DAYTONA BEACH, FLORIDA

Instrument Rating Ground School Day 3

Integrated Displays

Many of today's training airplanes are equipped with electronic integrated display instrumentation, commonly called "glass cockpit."

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Integrated Displays Operation

Compared to traditional electromechanical instruments, their operation is much different, and they also differ significantly in the way information is presented. Although many of you will still learn the basics of instrument flying using the traditional instrument systems, you should become familiar with the basics of integrated displays, since this technology is expected to gradually replace traditional instruments.

GARMIN SYSTEM OVERVIEW

PFD GDU 1040 or GDU 1044B

MFD GDU 1040 or GDU 1044B GMA 1347 Audio Panel Reversionary Control Reversionary Control

Flight Instruments

EIS GDC 74A Air Data Computer No. 1 GIA 63/63W Integrated Avionics Unit OAT Airspeed Altitude Vertical Speed No. 2 GIA 63/63W Integrated Avionics Unit & CNS

Audio Panel System Integration Processors

VO Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope System Integration Processors V/O Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope

GFC 700 Flight Director

(1728, 182, & 206) Attitude Rate of Turn Slip/Skid GPS Output

GMU 44 Magnetometer

Heading

Honeywell KAP 140 Autopilot

GTX 33 Transponder GEA 71 Engine/Airframe Unit GDL 90 Data Link ADS-B Traffic Data

GSA 81 Pitch Servo

Autopilot Calculations (172S/TD,182 & 206)

GSA 81 Pitch Trim

Autopilot Calculations (172S/TD,182 & 206)

GSA 81 Roll Servo

Autopilot Calculations (172S/TD,182 & 206)

* The GDU 1040 is available in systems not using the GFC 700 Automatic Flight Control System. The GDU 1044B is available in systems using the Garmin GFC 700 Automatic Flight Control System, Figure 1-1 Basic G1000 System

APPENDICES

INDEX

190-00498-06 Rev. B Garmin G1000 Pilot's Guide for Cessna Nav III 5

HAZARD AVOIDANCE

AFCS FEATURES

SYSTEM OVERVIEW

FLIGHT MANAGEMENT

GRS 77 AHRS

GPS Output

Integrated Displays Hallmarks

One of the hallmarks of integrated displays is the combining of most of the instruments that function separately in traditional systems.

AHRS Technology Transition

As aircraft displays have transitioned to new technology, the sensors that feed them have also undergone significant change. Traditional gyroscopic flight instruments have been replaced by Attitude and Heading Reference Systems (AHRS) improving reliability and thereby reducing cost and maintenance.

GARMIN PFD

GDU 1040 or GDU 1044B

MFD GDU 1040 or GDU 1044B GMA 1347 Audio Panel Reversionary Control Reversionary Control

Flight Instruments EIS

GDC 74A Air Data Computer No. 1 GIA 63/63W Integrated Avionics Unit OAT Airspeed Altitude Vertical Speed No. 2 GIA 63/63W Integrated Avionics Unit & CNS

Audio Panel System Integration

VO Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope System Integration Processors V/O Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope

GFC 700 Flight Director (1728, 182, & 206)

Attitude Rate of Turn Slip/Skid GPS Output

GMU 44 Magnetometer Heading

Honeywell KAP 140 Autopilot GTX 33 Transponder GEA 71 Engine/Airframe Unit GDL 90 Data Link ADS-B Traffic Data

GSA 81 Pitch Servo Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Pitch Trim Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Roll Servo Autopilot Calculations

(172S/TD,182 & 206)

* The GDU 1040 is available in systems not using the GFC 700 Automatic Flight Control System. The GDU 1044B is available in systems using the Garmin GFC 700 Automatic Flight Control System, Figure 1-1 Basic G1000 System

APPENDICES INDEX

190-00498-06 Rev. B Garmin G1000 Pilot's Guide for Cessna Nav III 5

HAZARD AVOIDANCE AFCS FEATURES

ADDITIONAL SYSTEM OVERVIEW

FLIGHT MANAGEMENT

GRS 77 AHRS GPS Output

SYSTEM OVERVIEW

Integrated Displays: AHRS Sensors

A suite of sensors provides input to an air data computer and an attitude and heading reference system (AHRS). These components derive the values that are displayed in the cockpit. Rather than using separate mechanical gyroscopes to operate individual instruments, the AHRS uses electronic gyroscopes and accelerometers to determine the aircraft's attitude relative to the horizon, as well as the direction in which it is moving. An electronic magnetometer provides magnetic heading data, so the pilot does not need to update the heading periodically as is necessary with a mechanical gyroscopic heading indicator.

GARMIN PFD GDU

GDU 1040 or GDU 1044B

MFD GDU 1040 or GDU 1044B GMA 1347 Audio Panel Reversionary Control Reversionary Control

Flight Instruments EIS GDC 74A

Air Data Computer No. 1 GIA 63/63W Integrated Avionics Unit OAT Airspeed Altitude Vertical Speed No. 2 GIA 63/63W Integrated Avionics Unit & CNS

Audio Panel System Integration Processors

VO Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope System Integration Processors V/O Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope

GFC 700 Flight Director (1728, 182, & 206)

Attitude Rate of Turn Slip/Skid GPS Output

GMU 44 Magnetometer Heading

Honeywell KAP 140 Autopilot GTX 33 Transponder GEA 71 Engine/Airframe Unit GDL 90 Data Link ADS-B Traffic Data

GSA 81 Pitch Servo Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Pitch Trim Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Roll Servo Autopilot Calculations

(172S/TD,182 & 206)

* The GDU 1040 is available in systems not using the GFC 700 Automatic Flight Control System. The GDU 1044B is available in systems using the Garmin GFC 700 Automatic Flight Control System, Figure 1-1 Basic G1000 System

APPENDICES INDEX

190-00498-06 Rev. B Garmin G1000 Pilot's Guide for Cessna Nav III 5

HAZARD AVOIDANCE AFCS FEATURES

ADDITIONAL SYSTEM OVERVIEW

FLIGHT MANAGEMENT

GRS 77 AHRS GPS Output

SYSTEM OVERVIEW

Integrated Displays: ADC Functionality

An Air Data Computer (ADC) is an aircraft computer that receives and processes pitot pressure, static pressure, and temperature to calculate very precise altitude, IAS, TAS, and air temperature. The ADC outputs this information in a digital format that can be used by a variety of aircraft systems including an EFIS. Modern ADCs are small solid-state units. Increasingly, aircraft systems such as autopilots, pressurization, and FMS utilize ADC information for normal operations.

NOTE: In most modern general aviation systems, both the AHRS and ADC are integrated within the electronic displays themselves thereby reducing the number of units, reducing weight, and providing simplification for installation resulting in reduced costs.

GARMIN PFD GDU 1040

GDU 1040 or GDU 1044B

MFD GDU 1040 or GDU 1044B GMA 1347 Audio Panel Reversionary Control Reversionary Control

Flight Instruments EIS GDC 74A

Air Data Computer No. 1 GIA 63/63W Integrated Avionics Unit OAT Airspeed Altitude Vertical Speed No. 2 GIA 63/63W Integrated Avionics Unit & CNS

System Integration Processors

VO Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope

GRS 77 AHRS

GFC 700 Flight Director (1728, 182, & 206) Attitude Rate of Turn Slip/Skid GPS Output

GMU 44 Magnetometer Heading

Honeywell KAP 140 Autopilot GTX 33 Transponder GEA 71 Engine/Airframe Unit GDL 90 Data Link ADS-B Traffic Data

GSA 81 Pitch Servo Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Pitch Trim Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Roll Servo Autopilot Calculations

(172S/TD,182 & 206)

* The GDU 1040 is available in systems not using the GFC 700 Automatic Flight Control System. The GDU 1044B is available in systems using the Garmin GFC 700 Automatic Flight Control System, Figure 1-1 Basic G1000 System

APPENDICES INDEX

190-00498-06 Rev. B Garmin G1000 Pilot's Guide for Cessna Nav III OVERVIEW SYSTEM MANAGEMENT FLIGHT HAZARD AVOIDANCE AFCS FEATURES ADDITIONAL 5

Audio Panel System Integration Processors

V/O Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope GPS Output

Integrated Displays: Magnetometer

A magnetometer is an instrument that senses magnetic fields. The magnetometers used in integrated avionics displays are optimized for sensing the earth's magnetic field. As such, it functions as a magnetic compass, but without some of the errors associated with a conventional compass. Instead of a suspended bar magnet, it uses a flux valve or flux gate, which is an electronic means of sensing magnetic lines of force. The magnetometer is usually located as far as possible from sources of magnetic fields within the aircraft, and connected by a cable to the AHRS.

GARMIN PFD GDU 1040

GDU 1040 or GDU 1044B

MFD GDU 1040 or GDU 1044B GMA 1347 Audio Panel Reversionary Control Reversionary Control

Flight Instruments EIS GDC 74A

Air Data Computer No. 1 GIA 63/63W Integrated Avionics Unit OAT Airspeed Altitude Vertical Speed No. 2 GIA 63/63W Integrated Avionics Unit & CNS

Audio Panel System Integration Processors

VO Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope System Integration Processors V/O Processors VHF COM VHF NAV/LOC GPS/WAAS Glideslope

GFC 700 Flight Director (1728, 182, & 206)

Attitude Rate of Turn Slip/Skid GPS Output

GMU 44 Magnetometer Heading

Honeywell KAP 140 Autopilot GTX 33 Transponder GEA 71 Engine/Airframe Unit GDL 90 Data Link ADS-B Traffic Data

GSA 81 Pitch Servo Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Pitch Trim Autopilot Calculations

(172S/TD,182 & 206)

GSA 81 Roll Servo Autopilot Calculations

(172S/TD,182 & 206)

* The GDU 1040 is available in systems not using the GFC 700 Automatic Flight Control System. The GDU 1044B is available in systems using the Garmin GFC 700 Automatic Flight Control System, Figure 1-1 Basic G1000 System

APPENDICES INDEX

190-00498-06 Rev. B Garmin G1000 Pilot's Guide for Cessna Nav III 5

HAZARD AVOIDANCE AFCS FEATURES

ADDITIONAL SYSTEM OVERVIEW

FLIGHT MANAGEMENT

GRS 77 AHRS GPS Output

Primary Flight Display (PFD)

PFDs Situational Awareness

PFDs provide increased situational awareness (SA) to the pilot by replacing the traditional six instruments used for instrument flight with an easy-to-scan display that provides the horizon, airspeed, altitude, vertical speed, trend, trim, rate of turn among other key relevant indications. At first glance, the top part of the PFD resembles the artificial horizon of a typical attitude indicator, while the lower portion looks much like a horizontal situation indicator.

GARMIN PFD Display

NAV1 108.00 NAV2 108.00 Attitude indicator Slip skid indicator 134.00 123.80 Altimeter COM1 COM2 PUSH 4000 NAV EMERG COM 20 20 -2 120 - 4200 Vertical speed indicator (VSI) 10 - 10 TREND rzu HUG 100 4000 g 90 10 10 3900 PUSH HOG SYNC 80 270 -2 70- TAS 106KT 29.92IN 30 Turn indicator 33 Y PUSH PAN VOR 1 S o o O Z Horizontal situation indicator C 270 270 CLA ENT ALT OAT 6℃ Turn rate indicator tick marks INSET PFD OBS COX DME X Turn rate trend vector PUSH CASA 110 - 4100 1-2 Airspeed indicator H CRS & BARO INDICATO ( 6 ) - 3800 PUSH CRS CTR RANGE MENU Slip/skid indicator 6 OFLT MAP FMS TRK 360"