The document provides information on typical aircraft instrument systems, including:
1. The electronic flight instrument system (EFIS) which replaces traditional mechanical instruments with electronic displays like the electronic attitude director indicator (EADI) and electronic horizontal situation indicator (EHSI).
2. The electronic centralized aircraft monitoring (ECAM) system which monitors aircraft systems and provides visual warnings to pilots such as the electronic centralized aircraft monitoring (ECAM) display.
3. The fly-by-wire (FBW) system which replaces traditional manual flight controls with an electronic interface for transmitting commands to flight surfaces through actuators.
2. 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.
4. 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
5. 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
6. 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
7. EHSI – DISPLAYED INFORMATION
• Magnetic Heading
• Radio Steering Command
• Way Point, Nav Aids
• Distant to Go
• ILS steering command
10. EICAS - Engine Indication and Crew Alert System
ECAM - Electronic Centralised Aircraft Monitoring
11. Engine Indication and Crew Alert
• Boeing – EICAS • Airbus – ECAM
– Two Displays – Two Displays
• Top – Engine Parameters • Top – Engine Parameters
• Bottom – Blank • Pictorial Diagram
– Fault Situation – Fault Situation
• Top - Fault message • Check list is provided
• Bottom – Fault • System limitation is given
parameters.
13. 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.
14. 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.
16. ACARS
ARINC COMMUNICATION, ADDRESSING & REPORTING SYSTEM
A/C SYSTEMS ACARS VHF 3
AIRLINE TRANSMISSION
COMPUTER NETWORK
SYSTEM
MAINTENANCE FLIGHT PASSENGER
OPERATIONS OPERATIONS SERVICES
VHF
TRANSMITTER/RECEIVER
17. 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
19. MANAGEMENT UNIT (MU)
• Management VHF3
Collins
VHF 3
Communication
ANTENNA
• Respond to the request
IN DFDAU FAIL SEND
NUMERIC ENTRY 13 : 02 : 58
FLT : 0123
D
0008
A 1 2 3
T
A 4 5 6
L
7 8 9
I
N
0
from ground and
K
CLR RET DEL
MULTIPURPOSE INTERACTIVE
DISPLAY UNIT
MANAGEMENT
UNIT
VHF 3
TX/RX acquire data from
FLIGHT DATA
FDAU.
ACQUISTION UNIT
THERMAL PRINTER
AIRCRAFT
SYSTEMS
20. ECAM
ELECTRONIC CENTRALIZED AIRCRAFT MONITORING
WARN WARN
CAUT CAUT
ECAM
CONTROL PANEL
DMC 1 DMC 3 DMC 2
FWC 1 SDAC 1 SDAC 1 FWC 2
A/C SYSTEM SENSORS
A/C SYSTEM SENSORS
RED WARNINGS
AMBER WARNINGS NAV & AFS SENSORS
SYSTEM PAGES
SYSTEM PAGES
FLIGHT PHASE
21.
22. 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).
23. ECAM COMPONENTS
SYSTEM DATA ACQUISITION DISPLAY MANAGEMENT
CONCENTRATORS (SDAC) COMPUTER (DMC)
• Acquire cautions inputs and • Inputs
input to FWCs. – SDAC
• Alert DMCs for display on – Nav and AFS Sensors
ECAM – FWCs
• Process inputs for display
– Graphic
– Generate code
29. 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.
•
30. • 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
31. EFIS
Honeywell
ATT 2 GS
AOA 20 20
F
10 10
G
FULL GS SC
WX ET REV
ARC TTG
MAP
CP 10 10
S
DIM DH BOT TOP CMD 20 20
CRS HDG
M .99 I
TEST 200DH DH 140RA
RASTER DIM
AIR EFIS SG No 1
DATA
COMP
NAV VLF FMS INS 1 INS 2 HDG ATT
Honeywell
ADF 2 VOR 2
VOR 1 CRS NAV 1
INERTIAL ADF 1
AUTO
OFF
ADF 2
ADF 1
OFF
345
+0
H 2.1NM
REF BRG BRG
W
SYSTEM VOR 1
ADF 1
HDG GSPD
NAV AID 013 130 KTS
ILS/VOR
EFIS SG No 3
RAD ALT
Honeywell
ATT 2 GS
WEATHER AOA 20 20
F
RADAR 10 10
G
10 10
S
DME CMD
M .99
20 20
FULL
ARC
WX
GS
TTG
ET MAP
SC
CP
REV 200DH DH 140RA
CRS DIM DH BOT TOP
HDG
FMS TEST
RASTER DIM
AFCS EFIS SG No 2
Honeywell
NAV VLF FMS INS 1 INS 2 HDG ATT
CRS NAV 1
GPWS 345
+0
H 2.1NM
ADF 2 VOR 2
VOR 1
ADF 1
ADF 2
AUTO
ADF 1
W
OFF OFF VOR 1
BRG BRG
ADF 1
HDG GSPD
013 130 KTS
32. FULL GS SC
WX ET MAP REV
ARC TTG CP
DIM DH BOT TOP
CRS HDG
TEST
33.
34.
35. 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.
36. EADI -
• Display the traditional
ADI
• Pitch and Roll attitude
information
• Altitudes and speed
information.
• Early EFIS - (CRT)
• Later instrument (LCD)
37. 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;
38. 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
41. FBW-Fly by Wire
• Video to Introduce – Keep Your Eye For.
Fly By Wire. • The Instruments
• Control Stick
• Flying characteristics
42. FBW Definition
HYDRAULIC
PROCESSED PRESSURE
COMMAND
COMMAND
SIGNAL
SIGNAL
SIGNAL
CONTROL
MODULE
SPOILER
PANEL
FEEDBACK
SIGNAL
POWER
POSITION CONTROL
TRANSDUCER ACTUATOR
COMMAND
SIGNAL
SPEEDBRAKE
LEVER
POSITION
TRANSDUCER
ELECTRICAL HYDRO-MECHANICAL
• The command from the • The electrical signals are
pilot to move the control generated, transmitted
surfaces transmitted by through computer to
electrical wires. operate a servo.
43. FBW Example
HYDRAULIC
PROCESSED PRESSURE
COMMAND
COMMAND
SIGNAL
SIGNAL
SIGNAL
CONTROL
MODULE
SPOILER
PANEL
FEEDBACK
SIGNAL
POWER
POSITION CONTROL
TRANSDUCER ACTUATOR
COMMAND
SIGNAL
SPEEDBRAKE
LEVER
POSITION
TRANSDUCER
ELECTRICAL HYDRO-MECHANICAL
• For B767 FBW is used to • Which actuated the
control spoiler. solenoid valve, operate
• The lateral signal given by the actuator and provide
the position transducer is position feedback to the
processed by signal control module.
control module.