5.15 TYPICAL AIRCRAFT INSTRUMENT SYSTEMS

THE EFIS

• The electronic flight instruments have the following advantage:– Versatile – pilot can select the information– Display as required, less clutter– Reduce pilot’s workload.

EADI

THE EADI DISPLAY CAPABILITY

• Pitch and Roll information• Slip/ skid inclinometer.• Speed and speed error• Flight Director information• Glide slope and localizer• Warning and Status Message

DISPLAYED AS REQUIRED

Some of the display are not available all the time. It is displayed when in use. These are:– Radio altimeter– Decision Height– Marker Beacon– Rising Runway– Glide slope– Vertical Nav

EHSI

• Originate from magnetic compass• The gyro was added to provide stability during

turn.• The name was changed to HSI with the added

function of navigation and flight information.• With glass cockpit, the name was changed to

EHSI

EHSI – DISPLAYED INFORMATION

• Magnetic Heading• Radio Steering Command • Way Point, Nav Aids• Distant to Go• ILS steering command

EHSI

Electronic HSI

EICAS - Engine Indication and Crew Alert System

ECAM - Electronic Centralised Aircraft Monitoring

Engine Indication and Crew Alert

• Boeing – EICAS – Two Displays

• Top – Engine Parameters• Bottom – Blank

– Fault Situation• Top - Fault message• Bottom – Fault

parameters.

• Airbus – ECAM– Two Displays

• Top – Engine Parameters• Pictorial Diagram

– Fault Situation• Check list is provided• System limitation is given

EICAS

Electronic Centralized Aircraft Monitor (ECAM)

• The upper ECAM screen displays engine, flaps setting, fuel quantity and alert information.

• The lower ECAM displays the various systems parameters.

3. Electronic Centralized Aircraft Monitor (ECAM)

• ECAM also known as MFD (Multifunction Display)• ECAM monitors the overall aircraft systems, including

its fuel, electrical and engine systems. • Give the pilots warning when there is a malfunction. • For example, if an engine begins to lose oil pressure,

the ECAM might sound an alert, switch the display to the page with the oil system information and outline the low oil pressure data with a red box.

ECAM A320

ACARS ARINC COMMUNICATION, ADDRESSING & REPORTING SYSTEM

MAINTENANCEOPERATIONS

FLIGHTOPERATIONS

PASSENGERSERVICES

AIRLINECOMPUTER

SYSTEM

A/C SYSTEMS ACARS VHF 3

TRANSMISSIONNETWORK

VHF TRANSMITTER/RECEIVER

PURPOSE

• The ACARS is a digital data link for either ground-air or air-ground connections. The system reduces the flight crew’s workload because it transmits routine reports automatically and simplifies other reporting

Components

• Management Units (MU)• Multipurpose Interactive Display Units

(MPIDU)• Thermal Printer

MANAGEMENT UNIT (MU)

MANAGEMENTUNIT

VHF 3TX/RX

FLIGHT DATAACQUISTION UNIT

AIRCRAFTSYSTEMS

Collins

DATA

LIN

K

1 2 3

4 5 6

7 8 9

0

CLR RET DEL

FLT : 01230008

IN SENDDFDAU FAIL

NUMERIC ENTRY 13 : 02 : 58

MULTIPURPOSE INTERACTIVEDISPLAY UNIT

THERMAL PRINTER

VHF 3ANTENNA

• Management VHF3 Communication

• Respond to the request from ground and acquire data from FDAU.

ECAMELECTRONIC CENTRALIZED AIRCRAFT MONITORING

DMC 1 DMC 3 DMC 2

FWC 1 FWC 2

CAUT

WARN

CAUT

WARN

ECAMCONTROL PANEL

A/C SYSTEM SENSORSRED WARNINGSSYSTEM PAGESFLIGHT PHASE

A/C SYSTEM SENSORSAMBER WARNINGS

SYSTEM PAGESNAV & AFS SENSORS

SDAC 1 SDAC 1

FLIGHT WARNING COMPUTER (FWC)

• 2 FWCs acquire all data to generation the alert messages.– form the aircraft sensors (mostly Red)– Through the SDACs for cautions from the aircraft

systems (amber) • Generate codes for ECAM display units.

– Procedures associated to failures.– Status functions (aircraft and procedures).– Memo function (reminder of functions/systems, which

are temporarily used or items of normal checklist).

ECAM COMPONENTSSYSTEM DATA ACQUISITION

CONCENTRATORS (SDAC)

• Acquire cautions inputs and input to FWCs.

• Alert DMCs for display on ECAM

DISPLAY MANAGEMENT COMPUTER (DMC)

• Inputs– SDAC– Nav and AFS Sensors– FWCs

• Process inputs for display– Graphic– Generate code

DISPLAY UNIT

4 MODES OF DISPLAY

• Automatic– 1. Flight Modes– 2. Advisory– 3. Failure Mode

• 4. Manual– Selection from 12 systems

AUTOMATIC – FLIGHT PHASES

• The flight phases are:– Preflight– Take off– Climb– Cruize– Descent– Approach– Post Landing

EXAMPLE OF AUTOMATIC ECAM DISPLAY

Pre Take Off Cruize

ECAM CONTROL PANEL

EFIS• With the introduction of fully integrated, computer-based navigation

system, most electro/mechanical instrumentation has been replaced with TV type colour displays. The EFIS system provides the crew with two displays:

• • Electronic Attitude Direction Indicator (EADI).• • Electronic Horizontal Situation Indicator (EHSI).• • The EADI is often referred to as the Primary Flight Display (PFD) and the

EHSI as the Navigation Display (ND). The EADI and EHSI are arranged either side by side, with the EADI positioned on the left, or vertically, with the EADI on the top.

•

• SYSTEM LAYOUT

• • As is the case with conventional flight director systems, a complete EFIS installation

consists of two systems. The Captain’s EFIS on the left and the First Officer’s on the right.

• • The EFIS comprises the following units:• • Symbol Generator (SG).• • Display units X 2 (EADI & EHSI).• • Control Panel.• • Remote Light Sensor

EFIS

ICRS

TEST

DIM DH BOT TOP

RASTER DIM

HDG

GSTTG

FULLARC

WX ET MAPSCCP

REV

OFF

AUTO

ADF 1ADF 2

BRG BRG

NAV VLF FMS INS 1 INS 2 HDG ATT

ADF 2

ADF 1

OFF

VOR 1VOR 2

AIRDATACOMP

INERTIALREF

SYSTEM

NAV AIDILS/VOR

RAD ALT

WEATHERRADAR

DME

FMS

AFCS

GPWS

EFIS SG No 2

EFIS SG No 3

EFIS SG No 1

Honeywell

W

GSPD130 KTS

HDG013

NAV 12.1NMH

CRS345+0

VOR 1

ADF 1

Honeywell

ATT 2

AOA

CMDM .99200DH DH 140RA

G

GS

2020

10 10

20 20

10 10

F

S

CRS

TEST

DIM DH BOT TOP

RASTER DIM

HDG

GSTTG

FULLARC

WX ET MAPSCCP

REV

OFF

AUTO

ADF 1ADF 2

BRG BRG

NAV VLF FMS INS 1 INS 2 HDG ATT

ADF 2

ADF 1

OFF

VOR 1VOR 2

Honeywell

W

GSPD130 KTS

HDG013

NAV 12.1NMH

CRS345+0

VOR 1

ADF 1

Honeywell

ATT 2

AOA

CMDM .99200DH DH 140RA

G

GS

2020

10 10

20 20

10 10

F

S

CRS HDG

TEST

WXFULLARC

GSTTG

ET MAPSCCP

REV

DIM DH BOT TOP

EFIS DISPLAY UNITS

• Each display unit consists of the following modules:– Cathode Ray Tube.– Video Monitor Card.– Power Supply Unit.– Digital Line Receivers.– Analog Line Receivers.– Convergence Card.

EADI -

• Display the traditional ADI

• Pitch and Roll attitude information

• Altitudes and speed information.

• Early EFIS - (CRT) • Later instrument (LCD)

EADI• In normal use, the EADI is coupled directly to the autopilot and the display is

used by the pilot to monitor flight progress.• Alternatively, steering and attitude (pitch and roll) demand bars help the pilot

to fly manually.• The EADI provide steering information to follow, for example:• a manually input heading;• a route input on the Flight Management System (FMS);• a navigation beacon (VOR, ADF, etc.);• an IRS (Inertial Reference System) track; or,• an ILS localiser.• and to:• climb or descend to a level and maintain that level on reaching;• follow an ILS glidepath; or,• follow a Go-around procedure;

EHSI (Electronic Horizontal Situation Indicator)

• Electronic Horizontal Situation Indicator (EHSI)• The Electronic Horizontal Situation Indicator (EHSI) replaces a

number of different instruments found on a conventional aircraft, and may be used to depict some or all of the following information:

• heading flown;• heading or track selected;• bearing to or from a navigation beacon (VOR, DME);• lateral deviation from a selected track;• ground speed, distance and time to go;• aeronautical map;• weather information;• plus much more information according to design

EHSI

• Display – According to the selected mode

EFIS

P183

FBW-Fly by Wire

• Video to Introduce –Fly By Wire.

Keep Your Eye For.• The Instruments • Control Stick• Flying characteristics

FBW Definition

• The command from the pilot to move the control surfaces transmitted by electrical wires.

• The electrical signals are generated, transmitted through computer to operate a servo.

SIGNALCONTROLMODULE SPOILER

PANEL

HYDRAULICPRESSURE

ELECTRICAL HYDRO-MECHANICAL

COMMANDSIGNAL

COMMANDSIGNAL

POSITIONTRANSDUCER

POSITIONTRANSDUCER

PROCESSEDCOMMAND

SIGNAL

FEEDBACKSIGNAL POWER

CONTROLACTUATOR

SPEEDBRAKELEVER

FBW Example

• For B767 FBW is used to control spoiler.

• The lateral signal given by the position transducer is processed by signal control module.

• Which actuated the solenoid valve, operate the actuator and provide position feedback to the control module.

SIGNALCONTROLMODULE SPOILER

PANEL

HYDRAULICPRESSURE

ELECTRICAL HYDRO-MECHANICAL

COMMANDSIGNAL

COMMANDSIGNAL

POSITIONTRANSDUCER

POSITIONTRANSDUCER

PROCESSEDCOMMAND

SIGNAL

FEEDBACKSIGNAL POWER

CONTROLACTUATOR

SPEEDBRAKELEVER

A320 SIDESTICK CONTROLLER

• The sidestick