B. Operation after an electrical failure In this case the solenoid valve is de-energized and the operation is identical to the one of paragraph A. (2).
C. Operation after a hydraulic failure The closing valves (2) and (3) close and isolate the servocontrol from the hydraulic system of the aircraft. If there is a rupture of the aircraft return line, the return relief valve holds the volume of fluid in the fluid reserve. The mode selector valve moves under the action of its spring. Then the servocontrol operates in the damping mode.
D. Special Case After hydraulic depressurization, a difference in droop speed and travel between the two ailerons is possible. This is because of the variations of friction in the attachments and the servo control. This difference is correct.
E. Maintenance and rigging facilities The maintenance is "on condition". The items given below are Line Replaceable Units :
-filter
-servovalve
-solenoid valve
-linear variable-differential transducer. After replacement of the servocontrol, it is necessary to adjust the feedback transducer (10) . It is necessary to get an equal voltage in the secondary windings (electrical zero) when the aileron is in the neutral position. This is done through an action on the feedback transducer adjustment device located on the actuator.
AILERON AND HYDRAULIC ACTUATION - DEACTIVATION/REACTIVATION
___________________________________________________________
TASK 27-14-00-040-001
Deactivation of the Aileron Servo Control
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
_______ START A TASK ON OR NEAR:
-
THE FLIGHT CONTROLS
-
THE FLIGHT CONTROL SURFACES
-
THE LANDING GEAR AND THE RELATED DOORS
-COMPONENTS THAT MOVE.
WARNING : DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON
_______ THE UNSERVICEABLE SERVOCONTROL.
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______ CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
1. Reason for the Job
__________________
Refer to the MMEL TASK: 27-14-01
Aileron Hydraulic Actuation
Aileron Servo Control
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------
No specific blanking caps
No specific circuit breaker(s) safety clip(s)
No specific tie-wrap
No specific warning notice
No specific access platform 1.60 m (5 ft. 3 in.)
No specific access platform 4.20 m (13 ft. 9 in.)
B. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 27-14-00-710-001 Operational Test of the Aileron and Hydraulic Actuation
R 27-96-00-740-001 BITE Test of the EFCS (Ground Scanning) 29-10-00-864-001 Depressurize the Green Hydraulic System 29-10-00-864-003 Depressurize the Blue Hydraulic System 27-14-00-991-002 Fig. 401
3. Job Set-up
__________
Subtask 27-14-00-860-057
A. Aircraft Maintenance Configuration
(1)
Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
(2)
Do a ground scanning (Ref. TASK 27-96-00-740-001) to make sure that there is no maintenance indication related to the rudder pedal transducer units 25CE1(25CE2).
(3)
Make sure that the hydraulic systems are depressurized (Ref. TASK 29-10-00-864-001) (Ref. TASK 29-10-00-864-003).
Subtask 27-14-00-010-052
B. Get Access
(1)
Put the access platform in position:
(a)
at the zone 575 for the left aileron,
(b)
at the zone 675 for the right aileron.
(2)
Open the access door:
(a)
575KB for the left aileron,
(b)
675KB for the right aileron.
(3)
Put the access platform in position at the access door 822.
(4)
Open the access door 822.
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