-a CPU AFS board
-an EXTENSION MON board
A memory module is located on the CPU AFS board.
It ensures these functions:
-ARINC acquisition of GUIDANCE peripherals
-
computation of the operational logic
-
computation of the AP/FD outer loop signals for the monitored modes
-
computation of the inner loops control laws and vote of the AP signals between the command and monitoring channels.
-transmission of computed data to the command channel through a low-speed ARINC bus called INTERNAL bus
-
monitoring of the AP/FD signals through comparison with the command signals
-
monitoring of the alpha floor detection.
(2)
Hardwired logic It is identical with the logic of the command channel although it does not include the FCU monitoring circuits.
(3)
Power supply unit It is identical with the power supply unit of the command channel although it does not include a 5 V battery.
C. Back Connector (Ref. Fig. 006) The back of the computer is equipped with a size 3 connector.
D. Carry on Loader A system loading is provided (FMGC data base loading) in the cockpit (Ref. 31-38-00).
R **ON A/C 106-149, 151-199, 211-299, 301-399, 401-499,
Post SB 22-1089 For A/C 151-199,211-212,
A. Command Channel
(Ref. Fig. 004A)
(1)
Flight management The FM card assembly is set on only one slot of the FMGC. This FM card assembly comprises a Processor card, a Memory card and an I/O controller card.
(a)
Processor card (CPM = Core Processing Module) This CPM fullfills all the flight management functions. This module exchanges data:
-
with the I/O controller card through the Inter-Module Memory (IMM)
-
with the FG/FE through the FM/FG common memory. This module contains Flash EEPROM memory to store the FMS sotware.
(b)
Memory card this card is plugged to the CPM card and provides:
-FM/FG common memory
-Flash data memory
-Battery-backed memory.
(c)
I/O controller card (IOM = Input Output Module)
This card consists of two lanes (IOC 1 and IOC 2).
Each lane is comprised of :
- one processor
-Flash Memory
-dual port RAM (called Inter Module Memory IMM)
-several I/O ports (ARINC 429, RS-485, Ethernet, RS232). The IOC 1 ensures additional functions:
-system synchronization with the FG timing
-generation of the CPM host interrupt signal for partition scheduling
-synchronization between IOM and CPM.
The FMS provides an RS-485 intersystem bus with a transport
capability of 625 Kbytes/s.
This bus allows the FMS to be run in dual mode.
(2)
Guidance function
(a) Digital part This part uses two processors : the INNER LOOP processor and the GUIDANCE COMMAND processor. The dialogue between the two processors is performed through a shared memory. The correct running of the program is checked by a watchdog. The result is directly taken into account in the system engagement hardwired logic on the EXTENSION COM board. Safety tests are activated at power-up when the aircraft is on the ground. The guidance part, command channel, is integrated on three boards:
-
a ILCPU (Inner Loop CPU)
-
a CPU AFS
-an EXTENSION COM
1 ILCPU board
_ This board which includes the INNER LOOP processor is equipped with a memory module. It ensures the following functions:
-ARINC acquisition of the peripherals for the INNER LOOP processor and transmission to the GUIDANCE processor.
-transmission of data to the peripherals by means of two ARINC buses : bus A (high speed) and bus B (low speed). These buses are looped back on the GUIDANCE MONITOR for monitoring purposes.
-computation of the AP, FD and A/THR inner loops control laws and vote of the AP signals between the command and monitoring channels
-monitoring through comparison of the AP signals between the two channels.
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