UTA                   AVIONICA           INSTRUMENTO                         PACIEFABIAN ESPARZA SILVA
ELECTRONIC INSTRUMENT SYSTEMThe Electronic Instrument System (EIS) has six display units.The EIS is divided into two subsy...
GENERALThe Engine/Warning Display (EWD) is normally on the upper Display Unit (DU), it is divided into upper and lowerarea...
The two control knobs on the LH side are used to adjustECAM CONTROL AND INDICATING                                 the bri...
EFIS CONTROL AND INDICATINGFlight parameters are displayed on the PFDs while navigation data isdisplayed on the NDs.Outboa...
CENTRALIZED FAULT DISPLAY SYSTEMThe Centralized Fault Display Interface Unit (CFDIU) centralizes andmemorizes all informat...
RADIO COMMUNICATIONS CONTROL AND INDICATINGRMPThe Radio Management Panels (RMPs) give the capability of tuning all communi...
ELECTRICAL POWER SYSTEM PRESENTATIONHere is the ELEC ECAM page in normal configuration with main generators supplying the ...
ELECTRICAL POWER LEVELThere are two identical engine driven generators called Integrated DriveGenerators (IDGs). They are ...
ELECTRICAL POWER LEVEL
Fabianesparzappt
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Fabianesparzappt

  1. 1. UTA AVIONICA INSTRUMENTO PACIEFABIAN ESPARZA SILVA
  2. 2. ELECTRONIC INSTRUMENT SYSTEMThe Electronic Instrument System (EIS) has six display units.The EIS is divided into two subsystems:- the ECAM system which uses the two displays in the center to giveinformation on the A/C systems,- the EFIS for which each pilot has tw displays.
  3. 3. GENERALThe Engine/Warning Display (EWD) is normally on the upper Display Unit (DU), it is divided into upper and lowerareas. The EWD is dedicated to the presentation of information.EWD INFORMATIONOn the upper area are permanently displayed:- Primary engine parameters,- Slat/flap position indication,- Fuel On Board (FOB).On the lower area are displayed:- Memos, failure messages and actions to be performed. DuringTakeOff (TO) and landing, most of the warnings are inhibited.
  4. 4. The two control knobs on the LH side are used to adjustECAM CONTROL AND INDICATING the brightness of the two ECAM screens and to turn them off.The EWD is divided into two main parts: The P/Bs on the RH side are mainly used to:- the upper area is used to display the main engine - display any of the system pages or the STATUS page,parameters, the - clear or recall a warning or caution message.Fuel On Board (FOB) and the slat/flap position, An A/C STATUS page may be also displayed on the SD to- the lower area is used for warning, caution and memo give anmessages. operational status of the A/C.The SD is divided into two areas: When things are not normal the STATUS page displays:- the upper part is used to display the various system - operational data on the LH side,pages, diagrams - INOPerative SYStem on the RH side.of the A/C systems, In front of each pilot, there are two attention getters, a red- the lower part is used to display permanent data. MASTERBelow the ECAM displays, on the center pedestal, there is WARNing and an amber MASTER CAUTion.the ECAM As a further means of getting the attention, there is acontrol panel. loudspeaker on each side of the cockpit for aural alerts and synthetic voice messages.
  5. 5. EFIS CONTROL AND INDICATINGFlight parameters are displayed on the PFDs while navigation data isdisplayed on the NDs.Outboard of the PFDs, there are control knobs to adjust the brightnessof the associated PFD and ND, and to turn the displays off.Two EFIS control panels are used to select what is displayed on theEFIS screens.The EFIS control panels are divided into two sections, one sectionassociated with the PFD and the other one with the ND.Just below the ECAM screens, on the center pedestal, there is aswitching panel with, on the right, 2 rotary selectors to restore datato the EFIS and ECAM displays in abnormal operation.
  6. 6. CENTRALIZED FAULT DISPLAY SYSTEMThe Centralized Fault Display Interface Unit (CFDIU) centralizes andmemorizes all information concerning A/C system failures.Reading or printing of the failure information is done in the cockpit withany MCDU or the printer.Most A/C system computers have a BITE. The BITE permanentlymonitors the system operation. When a failure is detected, it is stored inthe BITE memory and is transmitted to the CFDIU.The ECAM also monitors the A/C systems. The warning information isdelivered to the CFDIU.The failure information is available in various reports.The reading of the failure information is made from two different MCDUmenus depending on if the A/C is in flight or on ground.The SYSTEM REPORT/TEST function is available on ground only. Itenables a dialogue between the CFDIU and a system computer.The SYSTEM REPORT/TEST menu page presents the list of all thesystems connected to the CFDIU, in ATA chapter order.The maintenance Post Flight Report (PFR) can only be printed on ground.It summarizes and displays the list of the ECAM warning messages andthe fault messages, occurred during the last flight, with the associatedtime, flight phase and ATA reference..
  7. 7. RADIO COMMUNICATIONS CONTROL AND INDICATINGRMPThe Radio Management Panels (RMPs) give the capability of tuning all communication radios. The frequenciesare tuned by using the 2 concentric knobs.There are two RMPs located on the center pedestal and a third optional one on the overhead panel.Any RMP can tune any communication radio but each one is normally dedicated to a particular radio.- RMP 1 is dedicated to VHF 1,- RMP 2 is dedicated to VHF 2,- RMP 3 is dedicated to VHF 3 and HF 1/HF 2 (if installed).
  8. 8. ELECTRICAL POWER SYSTEM PRESENTATIONHere is the ELEC ECAM page in normal configuration with main generators supplying the entire network.The battery voltage can be monitored either on the overhead panel or the ECAM page. Each battery iscontrolled by a P/B Switch (SW).Both main generators and the APU generator are controlled by theirassociated P/B SW.There are two identical engine driven generators called Integrated Drive Generators (IDGs). They are used asthe main power source to supply the A/C electrical network.The entire electrical network can also be supplied by the APU generator. On the ground, the aircraft electricalnetwork can be supplied by an external power source.
  9. 9. ELECTRICAL POWER LEVELThere are two identical engine driven generators called Integrated DriveGenerators (IDGs). They are used as the main power source to supplythe A/C electrical network.- generator 1 supplies AC bus 1,- generator 2 supplies AC bus 2.Each AC bus supplies a Transformer Rectifier (TR):- AC bus 1 supplies TR 1,- AC bus 2 supplies TR 2.The TRs convert 115V AC into 28V DC to supply their associated DCbuses, DC 1 and DC 2.DC bus 1 then supplies the DC BATtery bus.
  10. 10. ELECTRICAL POWER LEVEL
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