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In landing phase, and on condition that LOC CPT has not been selected, the lateral attitude is limited to 15 deg. as long as speed is lower than the maneuvering speed of the flaps/slats configuration.
1EFF : ALL 1 22-11-00Page 28 1 1 Aug 01/05 1 1 1CES 1
Pitch Basic Loop
Figure 012
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 22-11-00Page 29/30 1201-299, 401-499, 1Aug 01/05 1 1 1CES R Pitch Basic Loop R Figure 012A
R 1EFF : 301-399, 1 22-11-00Page 31/32 1 1 May 01/04 1 1 1CES
Roll Basic Loop
Figure 013
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 22-11-00Page 33/34 1201-299, 401-499, 1Aug 01/05 1 1 1CES R Roll Basic Loop R Figure 013A
R 1EFF : 301-399, 1 22-11-00Page 35/36 1 1 May 01/04 1 1 1CES
**ON A/C 001-049, 051-099, 101-149, 201-299,
(c) Yaw basic loop (Ref. Fig. 014) The delta r command of the yaw basic loop is computed by the FMGC in the approach phase only. In the other cases, the basic loop is computed in the FACs. This command is then fed to the FACs to control the yaw power loop. In addition, the delta r command is integrated in the FAC and transmitted to the rudder trim actuator. This order is limited in amplitude (plus or minus 20 deg.) and in variation speed (30 deg./sec) in clean configuration. In approach phase (from LOC CPT to ALIGN) the delta r command is generated from the outer loop command-phi c and aircraft feedbacks. In roll out phase, the delta r command is generated from the delta r ROLL OUT signals computed in the LOC laws. In this phase the FMGC also generates a nosewheel steering command (delta NOSEWHEEL) for the BSCU. This command is limited in amplitude (plus or minus 6 deg.) and in variation speed (5 deg./s).
R **ON A/C 151-199, 301-399, 401-499,
(c) Yaw basic loop (Ref. Fig. 014) The delta r command of the yaw basic loop is computed by the FMGC in the approach phase only. In the other cases, the basic loop is computed in the FACs. This command is then fed to the FACs to control the yaw power loop. In addition, the delta r command is integrated in the FAC and transmitted to the rudder trim actuator. This order is limited in amplitude (plus or minus 20 deg.) and in variation speed (15 deg./sec) in clean configuration. In approach phase (from LOC CPT to ALIGN) the delta r command is generated from the outer loop command-phi c and aircraft feedbacks. In roll out phase, the delta r command is generated from the delta r ROLL OUT signals computed in the LOC laws. In this phase the FMGC also generates a nosewheel steering command (delta NOSEWHEEL) for the BSCU. This command is limited in amplitude (plus or minus 6 deg.) and in variation speed (5 deg./s).
1EFF : ALL 1 22-11-00Page 37 1 1 Aug 01/05 1 1 1CES 1
Yaw Basic Loop Figure 014
1EFF : 1 1R 1CES ALL 1 11 1 22-11-00 Page 38 May 01/04
**ON A/C ALL
(d) Deflection command consolidation (Ref. Fig. 015) The basic loop is computed for each axis in the command and monitoring channels. The peripherals use the deflection commands resulting from the vote performed on the commands delivered by each channel. The vote is made taking into account the smallest value (absolute value). Comparators permit to detect:
-
Differences between each input and output of voter
-
Differences between the outputs of voters.
The result of these comparisons is taken into account in the
generation of the FG HEALTHY signal.
In TAKE OFF, LANDING and GO AROUND modes, the outer loop commands
are computed separately by the command and monitoring channels.
This duplicates the generation of deflection commands in these
modes.
In cruise modes, the outer loop commands are limited in amplitude
and in speed in the basic loops. In cruise, this limits the
effects of failures affecting the outer loop commands.
(5) Increase of Load Thresholds on Side Stick Controllers and Rudder Pedals (Ref. Fig. 016) When the AP is engaged, the command and the monitoring channels supply the relays which control the pitch and roll lock solenoids (the command channel provides the +28V, the monitoring channel provides the ground). Each control has its own solenoid. Each AP has its own relays and can therefore lock the controls.
(a)
Side stick controllers The loads are increased on both axes. The pitch load threshold changes from 0.5 daN to 5 daN. The roll load threshold changes from 0.5 daN to 3.5 daN. Any load on the side stick controller which exceeds these values, results in AP disconnection (wired discrete from the ELACs, Ref. 22-10-00).
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