cockpittechnologie
Tu Dresden cockpittechnologie 2021
Tu Dresden cockpittechnologie 2021
MCC part communication
tool to synchronize actions and distribute responsibilities
target
- same knowlade of flight
- relevant information must be exchaged
- clear, structureed language, precisely
Incapacity check
Standard Operating Procedures - SOPs / wichtig
target (component of the MCC): Undoubted, safe and efficient work processes in the cockpit even in abnormal situations. Permanent guarantee of situational awareness
Pre-Flight Briefing inhalt
MCDU what can be put in INIT A page
From / to -> start lande fluzghafen
co mpanie routee
FLT NBR - flight number
CRZ FL -> cruising hreight / temperature
MCDU what can be put in INIT B page
Input fuel data (INIT B page):
−Zero Fuel Weight/CG
−block fuel
−Characteristic speeds displayed on MCDU are based on the ZFW entered by the crew
−Unit: [t] or [min]
MCDU what can be put in Performance page
−inputtakeoffdata(PERF TAKEOFF page)
−V1, VR, V2
−climb, cruise, descent, speedpreselection
−couplingtoPFD
MCDU Flight plan
beim taxi überprüfen der steuerflächen, wo wird dieses angezeigt
SD -> F/CTL
Wieviel speed fliegen wir, was bedeutet NAV
Econ speed -> speed abhängig vom cost index
NAV: consequences of the flight plan
MCDU during cruise phase, what is diusplayed
wie erkenne ich im flugdisplay, dass ich in den managed mode wechsle
es erscheint HDG statt NAV
-> zeiten und verbrauch werden auf der MCDU falsch angezeigt
RNV und RNP was bedeuten deren 1km und 10km
navigation RAW vs FM data
Raw: simple location by relative position to a beacon with automatically or manually selected frequency
FM: Self-location: Information is generated internally (by relative position to a beacon from AIRAC database, GPS, inertial navigation system...) (FM - FLight Managment)
Navigation what is the total error
PSE = pilot error
How to cross check navigation accuracy - wichtig
definition and meaning of CI - Cost index - wichtig
CT - Zeitkosten Crew, verspätung
dT - zeit
Cc - fix kosten
CF - Cost Fuel
CI - kg/min
dF - amount of fuel
CI-> klein wert -> der stellenwert des C_fuel ist sehr hoch
CI-> großer wert -> stellenwert für C_time ist sehr hoch
Reason for fixed coste -> diagram of fuel cost, fixed cost, time cost
was bedeuten diese zahlen
what require in the cockpit additionally
(FCOM
Check lists
Briefing )
Where are the cockpit regulation written
EASA CS-25 e.g. Subpart C: Control Surface and System Loads
what are important factors concerning duality
No/minimise excessive concentration or fatigue
controlled equally safely by the seating positions of both pilots
each pilot has a sufficiently clear view + minimum change in view (head movement)
other seats must be installed so make tasks effectively and without negative influence
what are important regularization besides duality
avoid misunderstandings, while allow mutual control of both pilots
priority: frequently observed information is displayed in the center
redundancy: more important information are displayed multipolar times
instrument arrangement EASA CS-25
Overhead panel, how are the buttons&switches organized
More often used buttons in a general flight are in the front, less often are far back.
For example lights ins the front
turbines kill switch far in the back
far back are fused
Historical development of the cockpit
the growing number of instruments and their information still needed to be presented in a manageable way
instrument diversity has given way to a few highly integrated cockpit displays (The right information at the right time) -> Development of so-called information hierarchies
complex systems required new forms of presentation over conventional clock instruments: Graphics and colour play a decisive role -> the equipment industry (Honeywell, Aerospatiale, Sextant, Diehl) are entering fierce competition
manufacturers e.g. Boeing and Airbus compete in display and operating concept
Two-pilot-cockpit:
Captain + First Office
Three-pilot-cockpit:
Two-pilot-cockpit +Flight engineer
Five-pilot-cockpit
Captain + First Office + Flight engineer
Three-pilot-cockpit + Navigator + Radio Operator
six-pilot-cockpit
Captain + First Office + Flight engineer
Three-pilot-cockpit + Navigator + Radio Operator + Second flight engineer
since when two pilto cockpit
80s with B767 und A310
Function and visibility of all panels
captain's (CAPT) and First Officer (F/O) panels are readily visible on the respective seating positions -> installation of the most important display systems
central panel of CAPT and F/O readily visible ->installation of simple designed or back-up display systems
central pedestal easily accessible for CAPT and F/O, but less visible _>installation of controls devices
overhead panel for CAPT and F/O equally well/badly accessible ->installation of control devices that are less relevant or rare to operate during standard flights
light-/glareshield-panel are readily visible and can be easily used from any pilot's seat ->installation of frequently used control devices and displays-
engineers, navigators and radio panel are equipped with controls devices and displays depending on the cockpit type (three to six-pilot-cockpit), which are not necessarily needed by the pilots
What is EIS
EIS (Electronic Instrument System with 6-8 CRT consisting of
ECAM (Electronic Centralized Aircraft Monitoring) and
EFIS (Electronic Flight Instrument System) and
important instruments as a mechanical back-up
What is ECAM
Electronic centralised aircraft monitoAn electronic centralised aircraft monitoring (ECAM) is a system that monitors aircraft functions and relays them to the pilots. It also produces messages detailing failures and in certain cases, lists procedures to undertake to correct the problem.r
What is EFIS
An electronic flight instrument system (EFIS) is a flight deck instrument display system that displays flight data electronically rather than electromechanically.
primary flight display (PFD),
multi-function display (MFD),
engine indicating and crew alerting system (EICAS)
. Early EFIS models used cathode ray tube (CRT) displays, but liquid crystal displays (LCD) are now more common. The complex electromechanical attitude director indicator (ADI) and horizontal situation indicator (HSI) were the first candidates for replacement by EFIS. Now, however, few flight deck instruments cannot be replaced by an electronic display.
What is a family concept and its results
concept:
- design of a basic type
- extension/shortening of the fuselage while retainingthe wing unit, landing gear, engines, avionics, cockpit design, etc.
result:
-different ranges and capacities of the aircraft
-savings on high development and approval costs
-simplified maintenance and spare parts provision, as often identical in construction
Draw a payload - range diagram including a bigger and smaller family model
What is the advantage of the cockpit commonality of family concepts
What are the three major functions of sensor systems
Communication
Navigation
Surveillance
Name four communications systems
VHF
HF
ELT
SATCOM
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Lernkarten
Where are the cockpit regulation written
EASA CS-25 e.g. Subpart C: Control Surface and System Loads
what are important factors concerning duality
No/minimise excessive concentration or fatigue
controlled equally safely by the seating positions of both pilots
each pilot has a sufficiently clear view + minimum change in view (head movement)
other seats must be installed so make tasks effectively and without negative influence
what are important regularization besides duality
avoid misunderstandings, while allow mutual control of both pilots
priority: frequently observed information is displayed in the center
redundancy: more important information are displayed multipolar times
instrument arrangement EASA CS-25
Overhead panel, how are the buttons&switches organized
More often used buttons in a general flight are in the front, less often are far back.
For example lights ins the front
turbines kill switch far in the back
far back are fused
Historical development of the cockpit
the growing number of instruments and their information still needed to be presented in a manageable way
instrument diversity has given way to a few highly integrated cockpit displays (The right information at the right time) -> Development of so-called information hierarchies
complex systems required new forms of presentation over conventional clock instruments: Graphics and colour play a decisive role -> the equipment industry (Honeywell, Aerospatiale, Sextant, Diehl) are entering fierce competition
manufacturers e.g. Boeing and Airbus compete in display and operating concept
Two-pilot-cockpit:
Captain + First Office
Three-pilot-cockpit:
Two-pilot-cockpit +Flight engineer
Five-pilot-cockpit
Captain + First Office + Flight engineer
Three-pilot-cockpit + Navigator + Radio Operator
six-pilot-cockpit
Captain + First Office + Flight engineer
Three-pilot-cockpit + Navigator + Radio Operator + Second flight engineer
since when two pilto cockpit
80s with B767 und A310
Function and visibility of all panels
captain's (CAPT) and First Officer (F/O) panels are readily visible on the respective seating positions -> installation of the most important display systems
central panel of CAPT and F/O readily visible ->installation of simple designed or back-up display systems
central pedestal easily accessible for CAPT and F/O, but less visible _>installation of controls devices
overhead panel for CAPT and F/O equally well/badly accessible ->installation of control devices that are less relevant or rare to operate during standard flights
light-/glareshield-panel are readily visible and can be easily used from any pilot's seat ->installation of frequently used control devices and displays-
engineers, navigators and radio panel are equipped with controls devices and displays depending on the cockpit type (three to six-pilot-cockpit), which are not necessarily needed by the pilots
What is EIS
EIS (Electronic Instrument System with 6-8 CRT consisting of
ECAM (Electronic Centralized Aircraft Monitoring) and
EFIS (Electronic Flight Instrument System) and
important instruments as a mechanical back-up
What is ECAM
Electronic centralised aircraft monitoAn electronic centralised aircraft monitoring (ECAM) is a system that monitors aircraft functions and relays them to the pilots. It also produces messages detailing failures and in certain cases, lists procedures to undertake to correct the problem.r
What is EFIS
An electronic flight instrument system (EFIS) is a flight deck instrument display system that displays flight data electronically rather than electromechanically.
primary flight display (PFD),
multi-function display (MFD),
engine indicating and crew alerting system (EICAS)
. Early EFIS models used cathode ray tube (CRT) displays, but liquid crystal displays (LCD) are now more common. The complex electromechanical attitude director indicator (ADI) and horizontal situation indicator (HSI) were the first candidates for replacement by EFIS. Now, however, few flight deck instruments cannot be replaced by an electronic display.
What is a family concept and its results
concept:
- design of a basic type
- extension/shortening of the fuselage while retainingthe wing unit, landing gear, engines, avionics, cockpit design, etc.
result:
-different ranges and capacities of the aircraft
-savings on high development and approval costs
-simplified maintenance and spare parts provision, as often identical in construction
Draw a payload - range diagram including a bigger and smaller family model
What is the advantage of the cockpit commonality of family concepts
What are the three major functions of sensor systems
Communication
Navigation
Surveillance
Name four communications systems
VHF
HF
ELT
SATCOM
Name 3 Navigation system
VOR
DME
GPS
ADF
Marker
Localizer
Glide Slope
Name 3 surveillance:
Radar (Weather) -WXR
ATC Mode S (Transponder)–XPDR
Radio Altimeter -TAWS
TCAS
VHF
Function
Usage
Control Unit
VHF (Very High Frequency): 30 –300 MHz
communication a/c <-> Ground and a/c <-> a/c with the almost interference-free operation, independent of daytime or season
System:
antenna installation (bent rod antenna for small a/c, otherwise for high speeds usage of low drag antenna on top or bottom of the fuselage)
transmitter/receiver
control unit -> part of the Radio Management Panel (RMP)
disadvantage: earth‘s curvature limits VHF range
HF
Function
Usage
Control Unit
HF (High Frequency): 3 –30 MHz
application primarily for long-range and medium-range operations, since the depolarization characteristics of the HF sky wave facilitate communication over long distances
system:
antenna installation (rod antenna in vertical tail or wing tip)
transmitter/receiver
control unit Radio Management Panel (RMP)
disadvantage: strength of the received HF waves depends on the frequency, the time of day and the location
What is the RMI
(Purpose, modes of operation)
Radio Management Panel
purpose: selection and control of HF-und VHF-communication systems
modes of operation:
- Normal Mode (Communication frequency selection)
- Radio Navigation Back Up Mode(Frequency selection of radio navigation systems (VOR, DME, ILS, ADF) in case of FMGC* failure)
FMGC –Flight Management and Guidance Computer
ELT
Function
Usage
Control Unit
ELT-Emergency Locator
independent emergency transmitter, that activates itself in case of an accident
positioning of the transmitter is carried out by means of the satellite-supported search and rescue system COSPAS*-SARSAT** or by passing aircraft
must be equipped §22 LuftBO
SATCOM
Function
Usage
Control Unit
communication type for voice and/or data exchange for cockpit and cabin crew as well as PAX
implementation SATCOM:
6 voice channels for cockpit and cabin telephones 2 channels have priority for the communication of the cockpit + 1 data channel
technical Structure:
-antenna for signal exchange with the ground station (GES -Ground Earth Station) via geostationary satellites
-Satellite Date Unit (SDU) for (de)coding voice and data signals exchanged between a/c and ground station (GES)
-SDU as interface to the RMPs, AMUs* and ACR*
-high Power Amplifier (HPA) for amplification of SDU signals
-beam Steering Unit for electrically controlling the antenna in the direction of a selected satellite
Disadvantages: SATCOM systems only available between 80°N and 80°S
ADF
Function
Usage
Control Unit
Automatic Direction Finder
ADF is part of radio navigation aids which are used to locate the relative direction
ADF-on-board antenna receives long and medium waves from omnidirectional radio beacons
Calculates the angle between two ground signals and the airplane long axis -> position und richtung des flugzeuges
components of the ADF unit on board:
antenna system on the a/c
receiver
control unit (e.g. RMP)
display unit (e.g. RMI, ND)
results of the ADF unit
angle between a/c‘s longitudinal axis and NDB -> rel bearing
therefore, 2 independent ground transmitter and ADF systems (ADF 1, 2) are required for direction finding
VOR
Function
Usage
Control Unit
VOR-Very High Frequency Omnidirectional Radio Range –VHF rotating radio beacon –as part of the Navigationsystem
directional transmitter
radio navigation system providing azimuth information about the angle between the azimuth line and north
components of the VOR on-board system:
antenna for frequency range 108 -117.95 MHz
receiver to measure the phase shift
control unit (e.g. RMP) Radio Managment Panel)
display unit (e.g. HSI*, ND)
eine drehende antenna zum senden und eine die konstant leuchtet -> eindeutiges signal -> über phasenverschiebung zwischen radial und konstantem licht gibt lage zum funkfeuer. Gelber strich in anzeige gibt abstand zum radial -> flugzeug würde an VOR vorbeifliegen (bild)
Shematic VOR
DME
Function
Usage
Control Unit
DME -Distance Measuring Equipment
radio navigation system providing slant range between a/c and ground station
theory of operation: runtime measurement of pulses sent by the a/c, received at the ground station, sent back with a time delay and received by the a/c
frequency range 960-1215 MHz, on-board and ground frequencies are assigned to each other in pairs and each offset by 63 MHz
DME-on-board equipment:
DME-on-board unit
antenna in the bottom of the fuselage
control unit (e.g. RMP)
display unit (e.g. HSI, ND) (Horizontal situation indicator, navigations display)
gibt schrägentfernung zwischen bodenstation und flugzeug an -> signal wird vom flugzeug gesand, am boden aufgenommen und nach fester verzögerungszeit wird signal zurückgechickt
GPS
Function
Usage
Control Unit
GPS –Global Positioning System
theory of operation: Propagation time measurement of radio signals from at least 4 satellites (3 for position determination, 1 for synchronization of the high-precision satellite time base)
carrier frequency: 1-2 GHz
navigation accuracy (actual):horizontal error < 10 mvertical error < 20 m
equipment
2 independent GPS receiver integrated in the multi mode receiver (MMR*)
data transfer to air data inertial reference units (ADIRU**) calculation of position
ILS
Function
Usage
Control Unit
Instrument landing system
standardized radio aid for precision approaches –as part of the Navigationsystem
theory of operation: horizontal and vertical guidance of the a/c by localizer beam and glide slope beam
Frequency ca 100-300 MHz
components of ILS on-board system>
localizer antenna
glide slope antenna
marker antenna
receiver
control unit (e.g. RMP, MCDU)
display unit (e.g. HSI, PFD)
Weather radar
Function
Usage
Control Unit
dient der sicherheit
kann auch küstenlinien oder inseln endecken
what is Weather radar (WXR)
technical limits:
limited opening angle
limited range (150NM, approx. 20min)
shading of distant areas during very strong thunderstorms
ice crystals reflect radar waves only weakly
RA
HF
Function
Usage
Control Unit
only usable at low altitude
wird im HMI durch in ezusätzliche zahl dargestellt
TWAS
Function
Usage
Control Unit
J
What is this
TWAS
GPWS and EGPWS
Were to get wether data besides radar
radio / XM Datalinkg (Satellite)
