The document summarizes the electronic instrument and electrical power systems on an aircraft. It describes the six display units that make up the Electronic Instrument System and how they are divided into the ECAM and EFIS subsystems. It also explains how the main electrical power is supplied by two engine-driven generators that each supply an AC bus to convert power to DC buses and batteries.

1. UTA
AVIONICA
INSTRUMENTO
PACIE
FABIAN ESPARZA SILVA

2. ELECTRONIC INSTRUMENT SYSTEM
The 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 give
information on the A/C systems,
- the EFIS for which each pilot has tw displays.

3. GENERAL
The Engine/Warning Display (EWD) is normally on the upper Display Unit (DU), it is divided into upper and lower
areas. The EWD is dedicated to the presentation of information.
EWD INFORMATION
On 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. During
TakeOff (TO) and landing, most of the warnings are inhibited.

4. The two control knobs on the LH side are used to adjust
ECAM 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 an
messages.
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.
MASTER
Below 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 a
control panel.
loudspeaker on
each side of the cockpit for aural alerts and synthetic voice
messages.

5. EFIS CONTROL AND INDICATING
Flight parameters are displayed on the PFDs while navigation data is
displayed on the NDs.
Outboard of the PFDs, there are control knobs to adjust the brightness
of the associated PFD and ND, and to turn the displays off.
Two EFIS control panels are used to select what is displayed on the
EFIS screens.
The EFIS control panels are divided into two sections, one section
associated with the PFD and the other one with the ND.
Just below the ECAM screens, on the center pedestal, there is a
switching panel with, on the right, 2 rotary selectors to restore data
to the EFIS and ECAM displays in abnormal operation.

6. CENTRALIZED FAULT DISPLAY SYSTEM
The Centralized Fault Display Interface Unit (CFDIU) centralizes and
memorizes all information concerning A/C system failures.
Reading or printing of the failure information is done in the cockpit with
any MCDU or the printer.
Most A/C system computers have a BITE. The BITE permanently
monitors the system operation. When a failure is detected, it is stored in
the BITE memory and is transmitted to the CFDIU.
The ECAM also monitors the A/C systems. The warning information is
delivered to the CFDIU.
The failure information is available in various reports.
The reading of the failure information is made from two different MCDU
menus depending on if the A/C is in flight or on ground.
The SYSTEM REPORT/TEST function is available on ground only. It
enables a dialogue between the CFDIU and a system computer.
The SYSTEM REPORT/TEST menu page presents the list of all the
systems 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 and
the fault messages, occurred during the last flight, with the associated
time, flight phase and ATA reference.
.

8. RADIO COMMUNICATIONS CONTROL AND INDICATING
RMP
The Radio Management Panels (RMPs) give the capability of tuning all communication radios. The frequencies
are 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).

9. ELECTRICAL POWER SYSTEM PRESENTATION
Here 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 is
controlled by a P/B Switch (SW).
Both main generators and the APU generator are controlled by their
associated P/B SW.
There are two identical engine driven generators called Integrated Drive Generators (IDGs). They are used as
the 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 electrical
network can be supplied by an external power source.

10. ELECTRICAL POWER LEVEL
There are two identical engine driven generators called Integrated Drive
Generators (IDGs). They are used as the main power source to supply
the 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 DC
buses, DC 1 and DC 2.
DC bus 1 then supplies the DC BATtery bus.

11. ELECTRICAL POWER LEVEL