EICAS-ECAM

8/10/2019 EICAS-ECAM

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Aircraft and Spacecraft Instrumentation

LectureEFIS, EICAS, ECAM, FMS


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EFISElectronic Flight Instrument System



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EFIS architecture


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EFIS on B747-400


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EFIS pictorial display


Torque indicators Primary displays

EFIS displays


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Primary flight displays:


attitude

heading altitude

airspeed

vertical speed

lateral/vertical path

engine power

selected heading selected course

autopilot/flight director

navigation

timer


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Multifunction display:


radio management

aircraft systems

engine instruments

checklists

moving map

flight plan

terrain datalink (traffic/weather)

charts

runways diagrams

wind direction/speed

ground track cautions/warnings

geographic overlays

lightning/weather

traffic information


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Multifunction display Apollo MX-20


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Multifunction display Apollo MX-20 - continuation



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Engine/warning display


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Dynon

Integrated EFIS on small aircraft boards

TL-elektronic


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EICASEngine Indicating and Crew Alerting System


EICAS is designed to provide all engine instrumentation and crew

advisory/caution/warning alert messages in an integrated format. The crew alerting

feature provides EICAS messages, flight deck lamp control and aural alerts

The system provides:

Primary engine data: N1, EGT and warning and alert messages, (EPR)

Secondary engine data: N2, fuel flow, oil quantity, pressure and temperature, vibration

+

non-engine parameters: flight control surface position, hydraulic & pneumatic system,power system including APU, deicing system etc.

The system has two computers (R, L). Only one is in the control at the time and the

other is standby.


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EICAS



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EICAS combined display



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EICAS modes


EICAS categorizes displays and alerts according to function and usage into modes:

operational: engine operating information and any alerts required to be

actioned by the crew in flight. Only upper display presents information.

status:provides details about the readiness of the aircraft maintenance:trouble-shooting and verification testing of the major sub-systems

EICAS distinguishes 7 colors:

white:all scales, normal operating range of pointers, digital readouts

red:warning messages, maximum operating limit marks, digital readouts

green:thrust mode readout, selected EPR/N1 speed marks or target cursors blue:testing of the system only

yellow:caution and advisory messages, caution limit marks on scales, digital readouts

magenta:during in-flight engine starting

cyan: names of all parameters being measured and status marks

EICAS levels:Level Awarnings requiring immediate correction activity

Level Bcautions requiring immediate crew awareness and possible activity

Level Cadvisories requiring crew awareness


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ECAMElectronic Centralized Aircraft Monitoring system


ECAM data relate essentially to the primary aircraft systems and are displayed in check-

list and in pictorial or synoptic format.

Engine operating data are displayed by conventional types of instruments.

ECAM uses two displaysside-by-side.

The left-hand display is dedicated to inform in check-list format about:

status of systems

warnings

corrective actions.The right-hand display is dedicated to show left-hand-display information in pictorial or

synoptic format.

ECAM modes:

flight-phase related: provides the information about the current phase of aircraft

operation (pre-flight, take-off, climb, cruise, descent, approach, and after landing) advisory:(mode & status)

failure related: when a failure occurs

manual:permits the selection of diagrams related to any one of 12 systems for

routine checking and status messages provided no warnings


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ECAM



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ECAM control panel


FAULT

OFF

FAULT

OFF

LEFT DISPLEY

OFF BRT

LEFT DISPLEY

OFF BRT

STS

RCL

CLR ENG

BLEED

APU

HYD

COND

F/CTL

AC

PRESS

DOOR

DC

FUEL

WHEEL

1 ECAM SGU 2

Display onand brightness control

SGW select switches

System synoptic display switches

Recall switch

Status

message switch

Message

clearance

switch

ECAM selective systems:

ENGengine system, HYDhydraulic system,AC/DCAC/DC power system, BLEEDair

bleed system, CONDair-conditioning, PRESSpressure in cabin system, FUELfuel

system,APUauxiliary power unit, F/CTLsurface flight control, DOORdoor system,

WHEELlanding gear system


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ECAM displays


MEMO

APU RUNNING

NO SMOKING ON

SEAT BELTS ON

PARKING BRAKE ON

DOOR

CABIN

FWD COMPT

EMEN

EXIT

CABIN

CARGO

BULK

CARGO

AVIONIC

ARM

ARM

ARM

ARM

ARM

ARM

Left-hand display Right-hand display


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ECAM displays - failure


TEMP HOT

FANS...............ON

DELAY T.O. FOR COOL

TEMP: BRAKES

Left-hand display

BRAKES

105

1

102

2

111

3

90

4

108

5

213

6

93

7

99

8

R

ROLL ROLLSPLR

SPD BRK

Right-hand display


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FMSFlight Management System


FMS advises the flight crew the optimum settings of various control parameters (EPR,

climb rate etc.) under varying flight conditions. It can isolate a flight crew from the

control loopfully automatic FMS.

DECREASE A WORKLOAD OF THE FLIGHT CREW

GREAT PRECISION OF ENGINE POWER CONTROL

FLIGHT PATH CONTROL (lateral & vertical)

THE MOST ECONOMICAL USE OF THE AVAILABLE FUEL

INCREASE OF SAFETY

The FMS can be found on most commercial & business aircraft.

FMS assists the pilot in navigation, flight planning & aircraft control. Providesreal-time

navigation information such as the programmed route, database waypoints & standard

departure/arrival procedures. Calculates performance data and vertical profiles based on

weight, cost index, cruise altitude and predicted winds.


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A typical FMS consists of:

Flight Management Computer

Control Display Unit

Visual Display (EFIS)


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FMC


Aircraft Position

- IRS/INS/GPS

- Nav aids (VOR/DME/ADF)

FMC- Navigation Database

- Performance Calculations

Auto-Flight System- Auto-throttle

- Flight Directors

EFIS- Attitude Indicator

- Heading Indicator

The Flight Management Computer is supplied with information from:

Navigation systems

Inertial reference system

Air data computer

Engine and system status

Aircraft specific performance database Route, procedure and terrain database

EGPWS

TCAS

Datalink

Pilot inputs


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FMSdata interfacing



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FMS configuration



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FMS - operation


1. The pilot must initialize and program the FMS with relevant route information.

2. The navigation and aircraft performance database must be verified as current and

correct. (performance must reflect the specific aircraft)3. An initial position must be entered. (Lat and Long)

4. A GPS augmented system will take less time to initialize.

5. The required route must be entered. This can include specific departure, en-route,

arrival, and approach procedures. (manually entered or previously stored)

6. Routing must be confirmed accurate and correct and any ATC changes to expected

routing must be entered manually en-route.7. The pilot becomes a manager of this sophisticated system, monitoring progress and

updating or changing parameters as necessary.

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