(c) Operation of Type 3 systems and the CFDIU The only functions possible are Test (GCU emergency) or Reset (TR1, 2 and 3) depending on the systems When these items are selected:
 -
The CFDIU connects the CFDIU-to-the-system discrete to ground.

 -
The system BITE executes its Test or Reset.

 -At the end of the Test or the Reset, the system BITE transmits, on its output discrete, the test result (correct or faulty
 1EFF : ALL 1 31-32-00Page 61 1 1 Feb 01/01R 1 1 1CES 1

 operation depending on discrete status) or the Reset result
 (Reset performed or not, depending on discrete status).
 -
The CFDIU decodes the result (reads discrete status).

 -
The CFDIU displays this result on the MCDU by creating a correct or faulty operation text.

 NOTE : - For the TEST function, the command (ground connection)
____ lasts 500 ms ; for the RESET it lasts 60 ms.
 -GCU emergency:
 discrete open = fault.
 discrete connected to ground = correct operation.
 not monitored by the CFDIU in flight and on ground.
 only test function available.

 -TR1, 2 and 3:
 discrete open = correct operation.
 discrete connected to ground = fault.

 E. Flight/Ground Conditions of Systems and the CFDIU
 Depending on the ground or flight conditions, the systems use different memorization and transmission modes and the CFDIU uses different modes for processing this information.
 So the systems and the CFDIU require a flight/ground indication; this indication depends on the type of system.
 (1) Type 1 systems
 **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
 (Ref. Fig. 014)
 **ON A/C ALL
 (Ref. Fig. 015)
R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
 (Ref. Fig. 016, 017)
 **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
 (Ref. Fig. 018)
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 CFDIU - Maintenance Phase Logic (Nominal Case)
 Figure 014

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 CFDIU - Computation of Maintenance Phases (Downgraded Case - Loss of Both FWCs)

 Figure 015
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 Maintenance Phases - Logic Diagram (transition to flight "at the soonest". FLT
 N.. parameter entered prior to engine)

 Figure 016 
R 1EFF :  106-149, 155-199, 208-299, 301-399,  1  31-32-00 Page 65 
1401-499,  1 Aug 01/05
 1  1
 1CES  1

 Maintenance Phases - Logic Diagram (transition to flight "at the latest". FLT N. . parameter not entered)
 Figure 017 
R 1EFF :  106-149, 155-199, 208-299, 301-399,  1  31-32-00 Page 66 
1401-499,  1 Aug 01/05
 1  1
 1CES  1

 CFDIU - CFDIU Transmission to BITE - Normal Mode (Label 227)

 Figure 018 
R 1EFF : 001-049, 051-099, 101-105, 151-154, 1201-207, 1 1CES  1 111 31-32-00 Page 67 May 01/05

R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
 (Ref. Fig. 018A)
 **ON A/C ALL

 The flight/ground condition is sent to the system by the CFDIU on the CFDIU to the system buses. This condition is coded on label 227, it is generated by the CFDIU.
 The flight condition is coded DC2 and DC1 and corresponds:
 -
for DC2: . memorized phase : NULL (confirmed over 120s) and . Engine running (CONF 180s) : running and . (flight phase more than or equal to 4 and less than 9b) or ((SSM

 of acquired flight number at NO) and (acquired flight number different from memorized flight number)).

 -
for DC1: . memorized phase : DC2 (confirmed over 30s)

 -
for NULL:

 . memorized phase : DC1 or DC2 and
 . (flight phase more than or equal to 9b and less than 4) or
 (engine running: shutdown (CONF 4s))
 A flight change is given by a NULL/DC2 transition.
 If the CFDIU is not available (input bus coming from the CFDIU declared invalid by the system because of the SSM, or refreshment, ...) the systems use a second condition sent directly as a result of aircraft configuration information (landing gear, engines, ...).
 Furthermore, given their functionalities, certain systems (e.g. brakes which in theory only operate on the ground) cannot use these transition signals and generate their flight/ground logic using aircraft configuration information.
　
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