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discrete data.
The DMA I/O devices receive the ARINC 429 and analog
discrete data. After conversion, this data then goes to the DMA
controller.
The DMA I/O devices also receive digital data from the CPU.
The DMA I/O devices changes the data to ARINC 429 data or
analog discretes before it goes to other systems.
The DMA controller controls all data to and from the A/T
computer.
CPU
The A/T CPU does these:
* Decides when the A/T engages and disengages
* Decides mode of operation
* Calculates thrust lever commands
* Monitors system operation.
The CPU monitors and decides if the control law data is
satisfactory. If it is, the CPU allows the A/T to engage. While
engaged, the CPU sends a signal to hold the A/T ARM switch in
the ARM position. The CPU also allows an excitation voltage to
go to the AT servo motors (ASMs).
If the CPU decides that control law data is not satisfactory, the
logic disengages the A/T system. The CPU sends a signal to the
autoflight status annunciators (ASAs) to give an annunciation.
The CPU permits selection of different autothrottle modes. The
DFCS system normally selects the mode during different flight
phases. You can also select the modes manually with the MCP
mode switches.
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The CPU calculates the A/T commands using A/T control laws.
The control laws give the desired command and compares this
command to the actual airplane condition. A difference in this
comparison produces a thrust lever rate command for the
ASMs.
The CPU continuously monitors system operation. If there is
fault, it stores this fault in a non-volatile maintenance memory.
Memory
The ROM stores the computer operational program. The
operational program is the computer instructions. The CPU
gets these instructions during its operation. The memory also
has a non-volatile maintenance memory. The maintenance
memory stores the results of BITE.
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A/T SYSTEM - A/T COMPUTER - FUNCTIONAL DESCRIPTION
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General
The A/T servo motors (ASMs) receive commands from the A/T
computer. The ASMs use these commands to individually move
the thrust levers forward or aft through two separate gear box
assemblies. Each thrust lever has its own servo motor and gear
box.
Physical Description
An ASM assembly weighs about 2 pounds and measures 3
inches by 3.3 inches by 3.5 inches. An electrical connector at the
front of the ASM supplies the interface to other aircraft
components. An output shaft at the rear joins the ASM to a
gearbox.
Operation
The ASM consists of these components:
* Control unit
* Digital receiver
* Digital transmitter
* Motor
* Power supply.
The A/T sends thrust rate commands to the ASM. The ASM
uses this rate command to control the dc motor rotation. The
ASM connects an output shaft to a gearbox and sends rate
feedback to the A/T.
Training Information Point
A built-in test (BITE) program in the A/T does a check of the
ASM operation. If BITE finds a fault, the A/T records the fault in
its memory. The technician uses the FMCS CDUs to see the
results of A/T BITE. The technician also uses A/T BITE to check
system operation.
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A/T SYSTEM - A/T SERVO MOTOR
A/T SYSTEM - A/T SERVO MOTOR
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