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CAR 66 Module 5.15 Typical Aircraft Instrument Systems
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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
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