-Get the SYSTEM REPORT/TEST NAV
 page (Ref. TASK 31-32-00-860-010).

 -Push the line key adjacent to  The IR3 page comes into view. the IR3 indication.
 -Get acess to the INTERFACE TEST
 of the IR3 (Ref. TASK 34-14-00-740-001).

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 Servo Actuator - Yaw Damper (3CC1,3CC2)
 Figure 601/TASK 27-26-51-991-004

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 -------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
NOTE : For the test below, ignore
____
 the warnings and the
 attitude changes.

 3.
 Push the line key adjacent to the START TEST indication.

4.
 Push the line key adjacent to the RETURN (TEST STOP) indication.

5.
 On the MCDU2 (or 3):

-Push the the line key adjacent to the RETURN indication until the CFDS menu page comes into view.

 6.
 On the FLT CTL panel 24VU(23VU):

 -Push the FAC2(FAC1) pushbutton switch.
-
The rudder moves to the left, thenslowly moves back to zero.

-
The rudder moves to the right, thenslowly moves back to zero.

On the MCDU2 (or 3):

-
The CFDS MENU page comes into view.

-On this pushbutton switch, the OFFlegend goes off.
 (1)
 Put the PIN - RIGGING (98D27207548000) (1) in the bellcrank of the rudder control unit.

 (2)
 Do a visual check of the yaw damper servo actuators for external leakages.

 Subtask 27-26-51-210-058
 B. Leakage Rates
 (1)
 If the leakage rate is less than 4 drops per minute, no further action is necessary. Do the check of the external leakage of the yaw damper servo actuators again after 600 flight hours.

 (2)
 If the leakage rate is between 4 and 14 drops drops per minute, replace the yaw damper servo actuator(s) before the next 600 flight hours (Ref. TASK 27-26-51-000-001) and (Ref. TASK 27-26-51-400-001).

 (3)
 If the leakage rate is between 15 and 30 drops drops per minute, replace the yawdamper servo actuator(s) before the next 100 flight hours (Ref. TASK 27-26-51-000-001) and (Ref. TASK 27-26-51-400-001).

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 (4) If the leakage rate is more than 30 drops per minute, replace the yaw damper servo actuator(s) immediately (Ref. TASK 27-26-51-000-001) and (Ref. TASK 27-26-51-400-001). ________
5. Close-up
 Subtask 27-26-51-410-054-A
 A. Put the aircraft back to the serviceable condition.
 (1)
 On the overhead panel, on the ADIRS CDU:

 -Set the OFF/NAV/ATT selector switch related to IR3 to OFF.

 (2)
 Do the EIS stop procedure (ECAM system only) (Ref. TASK 31-60-00-860-002).

 (3)
 De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).

 (4)
 Remove the rigging pin (1) from the bellcrank of the rudder control unit.

 (5)
 Depressurize the aircraft hydraulic systems (Ref. TASK 29-23-00-864-001) and (Ref. TASK 29-10-00-864-003).

 (6)
 Make sure that the work area is clean and clear of tool(s) and other items.

 (7)
 Close the access panel 325BL and 325BR at the trailing edge of the vertical stabilizer (Ref. TASK 55-33-13-410-002).

 (8)
 Remove the warning notice(s).

 (9)
 Remove the access platform(s).

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____________________________________
 1. General
_______ (Ref. Fig. 001) two elevators hinged on the trimmable horizontal stabilizer (THS) ensure the pitch control (Ref. 27-40). The elevators are controlled by :
 -
the Elevator and Aileron Computers (ELAC : Ref. 27-93) in the normal mode

 -
the Spoiler and Elevator Computers (SEC : Ref. 27-94) in case of ELAC

 failure. The control orders are computed from signals that the two electrically-coupled side stick controllers send. The artificial feel system (Ref. 27-92) operates independently of the flight conditions. Two electrohydraulic servocontrols (Ref. 27-34) hydraulically actuate each elevator. The position of the elevators is shown on the lower display unit of the ECAM system via the Flight Control Data Concentrator (FCDC : Ref. 27-95). On ground, with hydraulic systems not pressurized, the elevators may or may not droop down to the servocontrol stop depending on the scatter of bearing and seal friction.
　
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