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interfaces consist of discretes and ARINC 429 digital
buses.
DISCRETE INPUTS
The lights of each MCDU are tested via a discrete
issued from the annunciator light test relay.
The position of the MCDU is defined by two program
pins that are only read after long-term power cuts.
These pins define whether the MCDU is installed on the
left side (MCDU1), or on the right side (MCDU2).
Each MCDU receives the state of its own Flight
Management and Guidance Computer (FMGC) on the discrete
FMGC HEALTHY.
DISCRETE OUTPUT
The FMGCs receive the MCDU FAIL signal from each MCDU.
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MCDU INTERFACES - DISCRETE INPUTS/OUTPUT
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MCDU INTERFACES
ARINC INPUTS
The Centralized Fault Display Interface Unit (CFDIU)
sends maintenance information to MCDUs 1 and 2.
CFDIU specific pages are then displayed (e.g. SYSTEM
REPORT TEST). These CFDIU output buses allow the system
test and the trouble shooting to be done.
Each FMGC transmits Flight Management data to each
MCDU. This data is displayed on Flight Management
specific pages.
ARINC OUTPUTS
MCDUs 1 and 2 send background and dynamic Electronic
Instrument System (EIS) data to their associated FMGC.
MCDUs 1 and 2 also transmit data, entered by the pilot,
to the FMGCs and CFDIU. This data comprises messages
and system interrogations.
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22 - AUTO FLIGHT SYSTEM
22-00-00 AUTO FLIGHT SYSTEM COMPONENTS
CONTENTS:
Flight Augmentation Computers (FACs)
Flight Management and Guidance Computers (FMGCs)
Flight Control Unit (FCU)
Multipurpose Control and Display Units (MCDUs)
FAC Pushbutton Switches
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AUTO FLIGHT SYSTEM COMPONENTS
FLIGHT AUGMENTATION COMPUTERS (FACs)
IDENTIFICATION
FIN: 1CC1, 1CC2
LOCATION
ZONE: 127, RACK 83VU (FAC1)
128, RACK 84VU (FAC2)
COMPONENT DESCRIPTION
The Flight Augmentation Computer (FAC) is an 8MCU size
case in conformity with ARINC specification 600.
The FAC is of modular design.
The computer design is based on digital and analog
technologies.
Some boards in the computer are equipped with a memory
module, On Board Replaceable Memory (OBRM). Access to
these modules is from the front face of the unit.
The computer is divided into three parts:
- Two virtually identical channels, the COMMAND
channel and the MONITOR channel.
- One independent channel which performs the
Fault Isolation and Detection System (FIDS)
functions.
The COMMAND channel receives analog data, ARINC sensor
data and discrete signals in order to compute the
control laws. It then generates the flight commands
used to drive the corresponding servo actuators.
The interfaces between the computer and the actuators,
as well as the position feedbacks, are of the analog
type.
Similarly, the MONITOR channel receives the sensor
data required to compute the control laws.
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