-Disengagement of the FD.
 2 AP/FD common conditions (Ref. para. 2. A. (3).
_
 3 AP/FD/A THR common conditions (Ref. para. 2. A. (4).
_
 (3) AP/FD Common Conditions : AP/FD COND
 (Ref. Fig. 005)

 (a)
 FAC parameters monitoring This monitoring takes into account the validity (refresh and status matrix) of the data on the bus selected by the FMGC. Selection of the FAC bus is in function of the FAC HEALTHY wired discretes (two CMD and MON discretes per FAC).

 -The monitoring of the parameters linked to the flight envelope is not taken into account in LAND TRACK phase.
 -Parameters such as; weight, center of gravity, maneuvering speed in clean configuration, are not monitored in LAND TRACK or GO AROUND modes.

 (b)
 Radio altimeter monitoring Each FMGC monitors the validity of the radio altimeter data delivered by each bus (refresh, status matrix validity). This monitoring selects the appropriate bus and causes disengagement of the AP/FD in case of total loss of the two radio altimeters at LAND ARM mode selection or at GLIDE CAPTURE or GLIDE TRACK or LAND TRACK mode selection.

 (c)
 ROLL OUT mode validity Two monitoring functions define the validity of the ROLL OUT mode:

 -Monitoring of the runway heading delivered by the ILS (refresh and status matrix validity)
 -Deviation between runway heading and magnetic track delivered
 by the ADIRS less than 7 deg. between 700 ft and 100 ft. These functions are effective as soon as the LAND Mode is selected.
 (d) ILS monitoring R Each FMGC monitors the parameters transmitted by both ILS/MMR R receivers.
 Total loss of ILS information at LAND ARM or LOC ARM selection results in AP and FD disengagement (except in the event of glide deviation loss below 100 ft.).
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 AP/FD COND Logic
 Figure 005
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 (e)
 Validities of lateral and longitudinal flight plans The AP/FD is disengaged when the validity of lateral or longitudinal flight plan is lost, with FINAL DES mode armed or active.

 (f)
 FCU parameter monitoring This monitoring takes into account the validity of the FCU bus data (refresh and status matrix). It is inhibited in LAND TRACK or GO AROUND mode.

 (4) AP/FD/A THR Common Conditions (Ref. Fig. 006) This logic covers all the conditions common to the AP, FD and A/THR functions.
 (a)
 Monitoring of ADIRS parameters Two types of monitoring functions performed on the ADR and IR labels.

 (b)
 Validity of the FM part This validity which is necessary to engage the cruise modes, is no longer taken into account in the following modes : G/S TRACK below 700 ft., LAND TRACK and GO AROUND.

 (c)
 Landing-gear data availability The FAC delivers the information related to landing-gear data availability. This item of information is not taken into account in LAND and GO AROUND modes.

 1_ For all the data
 Status matrix and refresh monitoring (failure detected by
 self-test) through the peripheral).
 2_ For some important data
 - comparison of the data from the 3 ADIRS
 - 2 by 2 comparison of with respect to the voted value
 (failure not detected by self-test through the peripheral).
 At first failure (detected by self-test or not) the considered
 FMGC can change over automatically on the ADIRS 3 data (manual
 switching can also be performed on the panel 8VU).
 A second failure causes disengagement of the AP, FD and A/THR
 systems.

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 AP/FD/A THR Common Conditions
 Figure 006
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 (5)
 FD Command Generation (Ref. Fig. 007) The following basic loops generate the FD commands:

 (a)
 FD pitch control command This command is generated from the outer loop command - DELTA THETA C FD. The bar control command takes into account data feedback. It is limited to plus or minus 22.5 deg. A vertical acceleration term is added when the commands are displayed in FPV mode (flight path vector).

 (b)
 FD roll control command This command is generated from the outer loop command - PHI C. When the FD commands are presented by crossed bars, the roll FD command is limited to plus or minus 45 deg..

 (c)
　
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