Yellow Hydraulic System - Right Wing Section
Figure 612/TASK 29-00-00-991-012
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 29-00-00Page 663 1201-299, 301-399, 1Aug 01/05 1 1 1CES 1R Yellow Hydraulic System - Right Wing Section R Figure 612A/TASK 29-00-00-991-012-A
1EFF : 401-499, 1 29-00-00Page 664 1 1 Aug 01/05 1 1 1CES 1 THS actuator servovalve: 0.75 l.min (0.1981 USgal.mn) Elevator servocontrol: 1.5 l.min (0.3962 USgal.mn) Rudder servocontrol: 2.1 l.min (0.5547 USgal.mn) Yaw damper actuator: 1.3 l.min (0.3434 USgal.mn) Flap PCU valve block: 0.2 l.min (0.0528 USgal.mn)
NOTE : The maximum leakage rates for components are given only to
____ assist in trouble shooting. The total leakage of components in a section (left wing, right wing, etc) of the system must be less than the permitted maximum for that section. Also the total leakages of the sections must not together be more than the leakage permitted for the complete system.
(b)
If the internal leakage rate is too high you can find the defective component if you:
(c)
If you think that a servocontrol is the cause, disconnect and cap the supply to the servocontrol. Do the test again and if the leakage rate is now in limits,the servocontrol is confirmed as defective.
1_ Listen to the pipes and components which may be the cause.
2_ Feel the pipes and components, a high leakage rate will cause
an increase in their temperature.
CAUTION : DO NOT DISCONNECT AND CAP THE RETURN LINE FROM A_______
SERVOCONTROL TO DO A LEAKAGE CHECK. IF A SUPPLY OF
SYSTEM PRESSURE GETS TO THE SERVOCONTROL IT CAN
CAUSE DAMAGE IF THERE IS NO RETURN FLOW.
5. Close-up
________
Subtask 29-00-00-860-057
A. Put the aircraft back to the serviceable condition.
(1)
On the overhead maintenance panel 50VU, lift the guard and set the HYD/LEAK MEASUREMENT VALVES/Y P/BSW to on. Make sure that the OFF light goes off.
(2)
Refer to the lower DU of the ECAM (HYD page) and make sure that the solenoid valve has operated correctly (the flow arrow of the Yellow hydraulic system is colored green and the system name is colored white).
(3)
On the overhead panel 40VU, set the PTU P/BSW to AUTO (the OFF and FAULT lights are not on).
(4)
Depressurize the Yellow hydraulic system (Ref. TASK 29-10-00-864-002).
(5)
Disconnect the ground hydraulic supply from the aircraft ground test connections.
(6)
Install the blanking caps on the test connections.
(7)
Connect the PTU isolation coupling (Ref. TASK 29-23-00-860-002).
(8)
Do the EIS stop procedure
(Ref. TASK 31-60-00-860-002).
(9)
De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
Subtask 29-00-00-410-056
B. Close Access
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Close the access doors 195BB, 198CB. Subtask 29-00-00-865-056
C.
Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 3801GX, 3802GX, 3803GX
TASK 29-00-00-280-004 Check of the Internal Leakage of the Power Transfer Unit (PTU) 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
__________________
To make sure that the internal leakage of the PTU is in limits.
2.
Job Set-up Information
______________________
A. 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
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