-
a centering spring (Ref. 27-21).
At high speeds, a travel limitation unit limits the rudder travel in
relation to the airspeed (Ref. 27-23 and 22-61 for computation).
This is to prevent the transmission of excessive loads to the structure by
the rudder.
Three fixed-body servocontrols with mechanical input provide the hydraulic
actuation (Ref. 27-24).
The position of the rudder is shown on the lower display unit of the ECAM
system (Ref. 27-25).
A.
Interface with the Autoflight System Interface with the Autoflight System (Ref. 22-60-00). An electric trim actuator is connected to the artificial feel and trim unit upstream of the travel limitation unit. In all the modes, it drives the complete control via a spring device that the pilots can override. Two yaw damper servo-actuators are installed between the artificial feel and trim unit and the travel limitation unit. They drive the aft control via a differential linkage. The signals of the yaw damper servo-actuators are added to those of the pilots up to the maximum travel allowed by the travel limitation unit. Two transducer units near the pedals send data to the FACs via the ELACs.
B.
Interface with the Braking System Interface with the Braking System (Ref. 32-42). Levers attached to each pedal provide braking inputs when the pedals turn about their axis.
C.
Interface with the Nosewheel Steering System Interface with the Nosewheel Steering System (Ref. 32-51). The pedal transducer units send data to the BSCU via the ELACs for the nosewheel steering system.
INTENTIONALLY BLANK
1 1
27-20-00Page 2
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Rudder Block Diagram
Figure 001
1EFF : ALL 1 27-20-00Page 3/4 1 1 Feb 01/98 1 1 1CES
1 RUDDER MECHANICAL CONTROL - DESCRIPTION AND OPERATION
_____________________________________________________
1. General
_______
**ON A/C 001-049, 051-099, 101-149, 201-299,
(Ref. Fig. 001)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 001A)
**ON A/C 301-399,
(Ref. Fig. 001B)
**ON A/C ALL
Three mechanically-controlled fixed-body servocontrols operate the rudder.
Two interconnected pairs of pedals drive a mechanical linkage. This linkage
is single up to the artificial feel and trim unit and up to the actuating
lever of the middle servocontrol.
An adjuster which consists of a lever-controlled rack assembly is used to
adjust the position of the pedal assembly.
Downstream of the actuating lever of the middle servocontrol, the linkage is
duplicated up to the travel limitation unit (which is fail safe).
Thus, any single disconnection does not involve a loss of travel limitation
without a loss of rudder control. This is to avoid a hidden failure of the
travel limitation due to single failure.
The yaw damper signals are introduced through a differential mechanism,
located downstream of the aft cable run.
2. Component Location.
___________________
(Ref. Fig. 002)
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. -------------------------------------------------------------------------------103CM TENSION REG-RUDDER CONTROL CABLE 125 312AR 27-21-45
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Rudder Mechanical Control
Figure 001
R 1EFF : 001-049, 051-099, 101-149, 201-299, 1 27-21-00Page 3/4 1 1 May 01/05 1 1 1CES
1
Rudder Mechanical Control
Figure 001A
R 1EFF : 151-199, 401-499, 1 27-21-00Page 5 1 1 Aug 01/05 1 1 1CES 1
INTENTIONALLY BLANK
1 1
27-21-00Page 6
1 1 Aug 01/03R 1 1
1CES 1R Rudder Mechanical Control R Figure 001B
R 1EFF : 301-399, 1 27-21-00Page 7/8 1 1 May 01/04 1 1 1CES
Location of Rudder Mechanical Control Figure 002
1EFF : 1 1R 1CES ALL 1 11 1 27-21-00 Page 9 May 01/04
3. Component Description
_____________________
A. Cable Tension Regulator (Ref. Fig. 003) One cable tension regulator maintains a constant tension on the cable (22 daN plus or minus 3 daN (49.5 lbf plus or minus 7 lbf)). It has a provision for the installation of a special tool used to install the regulator on the aircraft.
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