RUDDER - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General

One rudder surface provides the yaw control.
The main control is mechanical (Ref. 27-21).
The trim control is electrically signalled (Ref. 27-22).
The artificial feel (Ref. 27-23) is ensured by:

a spring rod, the stiffness of which is independent from the flight conditions,
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. AMM D/O 22-60-00-00).
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.

[Rev.10 from 2021] 2026.03.31 23:47:46 UTC