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

 Figure 018A 
R 1EFF : 106-149, 155-199, 208-299, 301-399, 1401-499, 1 1CES  1 111 31-32-00 Page 69 Aug 01/05

 NOTE : In order to satisfy safety requirements the majority of Type 1
____ systems use a combination of 2 means for confirming their flight/ground condition and for inhibiting access to the menu mode and in particular to the test function, in flight.
 (2) Type 2 or 3 systems
 **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,

 (Ref. Fig. 009) R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
 (Ref. Fig. 009A)
 **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,

 (Ref. Fig. 014)
 **ON A/C ALL

 (Ref. Fig. 015)
 The flight/ground condition is sent directly to the system by means of one or several pieces of aircraft configuration information (e.g. discrete from the landing gear and/or engines) which correspond to flight phases 5, 6 and 7 for the flight condition.
 (3) CFDIU
 **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,

 (Ref. Fig. 010) R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
 (Ref. Fig. 010A)
 1EFF : ALL 1 31-32-00Page 70 1 1 Aug 01/05 1 1 1CES 1 **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,

 (Ref. Fig. 011)

R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
 (Ref. Fig. 011A)
 **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 ALL
 The CFDIU generates its flight/ground condition using some parameters transmitted by the FWC, the FAC, the memorized maintenance phases and a discrete from the LGCIU1 (nose landing gear shock absorber compressed). For memorization of message in flight, the flight/ground condition is given by the flight phases from the FWC and depends on the type of system which is connected to it.
 -
For type 1 and 3 systems: Flight condition "at the latest" (flight number not acquired) corresponds to flight phases 4, 5, 6, 7, 8 and 9a. Flight condition "at the soonest" (flight number acquired prior to engine start up) corresponds to flight phases 2b, 3, 4, 5, 6, 7, 8 and 9a. Ground condition "at the latest" corresponds to flight phases 1, 2, 3, 9b and 10. Ground condition "at the soonest" corresponds to flight phases 1, 2a, 9b and 10.

 -
For Type 2 systems: The flight condition corresponds to flight phases 5b, 6 and 7.

 1EFF : ALL 1 31-32-00Page 71 1 1 Aug 01/05 1 1 1CES 1 The ground condition corresponds to phases 1, 2, 3, 4, 8, 9 and 10. A flight change is given by NULL/DC2 transition:

 *
 For in flight inhibition of the functions which are forbidden in flight, i.e presentation of the CFDS main menu and availability of some specific functions (e.g : system menu mode/test) the flight/ground condition is given by an "OR" between the flight phases from the FWC and the discrete from the LGCIU1.

 *
 For activation or non-activation of complete CFDIU power-up test (long or short test) in the event of CFDIU long power cutoff, the flight/ground condition is given by the discrete from the LGCIU1.

 F. Standby Clock Function
 (1)
 Principle The aircraft time base in normal operation is the clock located on the main instrument panel, it provides:

 -GMT/Date

 -Elapsed time

 -Chronometer.
 It has been shown that the CFDIU permanently acquires GMT and the
 date and retransmits these data to the systems on its output buses.
 In the event of clock fault, the CFDIU takes over and transmits GMT
 and date on its output buses.

 (2)
 Operation In normal operation, the CFDIU receives the time from the clock and synchronizes its internal clock with it. In the event of fault of the main clock detected by the CFDIU (using the scrutinization of the status matrices and/or refreshment rate), the CFDIU calculates and transmits the time and the date using its internal clock. This transition does not require any reinitialization. Reinitialization of the time and the date is only necessary after a long power cutoff (> 200 ms) and it must be carried out by the crew on the MCDU through the GMT/DATE INIT function displayed by the CFDIU on the MCDU, one minute after CFDIU power-up.

R **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
 G. Pin Programming Function The CFDIU generates and transmits on its output bus 2 aircraft configuration labels which contain pin programming of the electronic items of equipment which are optional on the aircraft. These configuration labels (155 and 156) are used by all BITEs to know the printer status (installed or not installed) and by some systems (e.g:
　
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