5. Close-up
________ Subtask 29-17-11-942-050
A. Remove the container. Subtask 29-17-11-410-050
B. Close Access
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Close the right main door of the main gear (Ref. TASK 32-12-00-410-001).
(3)
Close the access door 196BB.
GROUND INTERNAL LEAK TEST SYSTEM - DESCRIPTION AND OPERATION
____________________________________________________________
1. General
_______
The ground internal leak test system makes it possible to check the total leakage of specified parts of the hydraulic systems. It is necessary to measure the leakage to make sure that the system performance keeps in the specified limits. It is also possible to make sure of the condition of components during maintenance. A ground test rig and flowmeter are used to supply and measure the flow of fluid.
2. Component Location
__________________
**ON A/C 001-049, 051-058, 101-101,
(Ref. Fig. 001)
R **ON A/C 059-099, 102-149, 151-199, 201-299, 301-399, 401-499,
(Ref. Fig. 001A)
**ON A/C ALL
(Ref. Fig. 002)
**ON A/C 001-049, 051-058, 101-101,
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF. -------------------------------------------------------------------------------1146GM MANIFOLD-GND LEAKAGE MEAS, G 146 734 29-19-41 2146GM MANIFOLD-GND LEAKAGE MEAS, B 195 195BB 29-19-41 3146GM MANIFOLD-GND LEAKAGE MEAS, Y 196 196BB 29-19-41 1150GP SOL VALVE-LEAKAGE MEAS, G 146 734 29-19-51 2150GP SOL VALVE-LEAKAGE MEAS, B 195 195BB 29-19-51 3150GP SOL VALVE-LEAKAGE MEAS, Y 196 196BB 29-19-51
Component Location Figure 001
R 1EFF : 1 1 1CES 001-049, 051-058, 101-101, 1 111 29-19-00 Page 2 May 01/05
Component Location
Figure 001A
R 1EFF : 059-099, 102-149, 151-199, 201-299, 1 29-19-00Page 3 1301-399, 401-499, 1Aug 01/05 1 1 1CES 1
Component Location Figure 002
1EFF : 1 1R 1CES ALL 1 11 1 29-19-00 Page 4 May 01/99
R **ON A/C 059-099, 102-149, 151-199, 201-299, 301-399, 401-499,
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. -------------------------------------------------------------------------------
1146GM MANIFOLD-GND LEAKAGE MEAS, G 146 734 29-19-41 2146GM MANIFOLD-GND LEAKAGE MEAS, B 195 195BB 29-19-41 3146GM MANIFOLD-GND LEAKAGE MEAS, Y 196 196BB 29-19-41
**ON A/C ALL
3. System Description
__________________
**ON A/C 001-049, 051-058, 101-101,
(Ref. Fig. 003)
R **ON A/C 059-099, 102-149, 151-199, 201-299, 301-399, 401-499,
(Ref. Fig. 003A)
**ON A/C ALL
The ground internal leak test system is divided into three parts, one for
each of the Green, Blue and Yellow hydraulic systems. Each part has:
-
a ground leakage-measurement manifold,
-
a solenoid valve,
-
a pushbutton switch in the cockpit.
The ground leakage-measurement manifold and the solenoid valve are installed in the high pressure (HP) circuit of the applicable system. The solenoid valve controls the flow of the hydraulic fluid between the HP manifold and the ground leakage-measurement manifold. The pushbutton switch controls the solenoid valve. When the solenoid valve is energized the supply of fluid goes only to the manual valves of the manifold. Thus it is possible to control the supply of fluid to different parts of the aircraft.
System Description - Schematic
Figure 003
R 1EFF : 001-049, 051-058, 101-101, 1 29-19-00Page 6 1 1 May 01/05 1 1 1CES 1
System Description - Schematic
Figure 003A
R 1EFF : 059-099, 102-149, 151-199, 201-299, 1 29-19-00Page 7 1301-399, 401-499, 1Aug 01/05 1 1 1CES 1 **ON A/C 001-049, 051-058, 101-101,
When the Yellow electric pump starts because of the operation of the cargo doors, the movement of the flight controls is prevented. Electrical power is supplied to the solenoid valve 3150GP and the two solenoid valves 1012GL and 3012GL. Thus no hydraulic power is supplied to the power transfer unit (PTU) and the flight controls.
R **ON A/C 059-099, 102-149, 151-199, 201-299, 301-399, 401-499,
When the Yellow electric pump starts because of the operation of the cargo doors, the movement of the flight controls is prevented. Electrical power is supplied to the leakage measurement solenoid valve of the Yellow hydraulic system and the two PTU solenoid valves. Thus no hydraulic power is supplied to the power transfer unit (PTU) and the flight controls.
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