(b)
 Slat Control Lift Augmenting
 Achieved on each wing by five slats.
 (Ref. Fig. 004)

 1EFF : ALL 1 27-00-00Page 12 1 1 Aug 01/04R 1 1 1CES 1

 Slats and Flaps Architecture Figure 004
 1EFF : 1 1R 1CES  ALL  1 11 1 27-00-00 Page 13 Aug 01/04

 2. Flight Controls Power Supply
____________________________
 A. Electrical Power Supply (Ref. Fig. 005) The ELAC 1 and SEC 1 are each supplied from a DC essential busbar (4PP for the ELAC 1 and SEC 1), the battery 1 taking over instantaneously through a dedicated diode device (Power Supply Uncoupling Unit) when the voltage level drops below the battery output voltage. A relay ensures the battery supply line breaking on the ground 30s after the second engine shut down. The ELAC 2, and the THS motor 1 are normally supplied from the DC normal busbar 2PP. In case of loss of this busbar (particularly after the loss of both main generation channels, or after a double main TRU failure), these supplies are automatically switched over to the battery 2 by means of two relays, for a fixed period of 30s. The SEC 2, the SEC 3, the THS electrical motor 3 , and FCDC 2 are supplied from the DC normal busbar 2PP. The THS electrical motor 2 is supplied from the DC essential busbar 4PP. The FCDC 1 is supplied from the DC essential busbar 8PP.
 B. Hydraulic Power Supply (Ref. Fig. 006) The flight controls are powered by the three independent hydraulic systems ; redundancy is such that with two hydraulic systems failed, the remaining system can operate the aircraft within an acceptable range of the flight envelope. Hydraulic characteristics of flight control components are given in the component description paragraphs.
 (1)
 Priority Valves Priority valves are installed upstream of the components below :

 -Blue system : slat power control unit (PCU) motor
 -Green system : flap and slat PCU motors
 -Yellow system : flap PCU motor in order to avoid supply pressure of the main flight control components dropping below approximately 130 bars (1885 psi) when various hydraulic user systems are operated simultaneously.

 (2)
 Leakage Measurement Valves Ground maintenance isolation valve blocks are installed in the flight controls hydraulic supply lines to allow measurement of internal leakage of the components installed downstream of these valves and valve jamming detection tests.

 1EFF : ALL 1 27-00-00Page 14 1 1 Aug 01/04R 1 1 1CES 1

 Flight Control Electrical Power Supply Figure 005
 1EFF : 1 1R 1CES  ALL  1 11 1 27-00-00 Page 15 May 01/04

 Flight Control Hydraulic Power Supply Figure 006
 1EFF : 1 1R 1CES  ALL  1 11 1 27-00-00 Page 16 May 01/04

 (3) Safety Valve To preserve the Green system in case of engine burst, a safety valve is installed.
 3. Cockpit Flight Control And Indicating
_____________________________________ These figures represent all the controls and indicators for the flight controls located in the cockpit. (Ref. Fig. 007)
 1EFF : ALL 1 27-00-00Page 17 1 1 Aug 01/04R 1 1 1CES 1

 INTENTIONALLY BLANK

 1 1
27-00-00Page 18
1 1 May 01/04R 1 1
1CES 1

 Cockpit Control and Indicating
 Figure 007

 1EFF : ALL 1 27-00-00Page 19/20 1 1 May 01/04 1 1 1CES
1

 FLIGHT CONTROLS - GENERAL - MAINTENANCE PRACTICES
_________________________________________________ TASK 27-00-00-480-001 Installation of the Pitch-Trim Control Locking Tool (98D27403500000)
 1.
 Reason for the Job

__________________
 Self Explanatory

 2.
 Job Set-up Information

______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
98D27403500000 1 PITCH TRIM CONTROL LOCKING
 B. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-00-00-991-001 Fig. 201
 3. Job Set-up
__________ Subtask 27-00-00-869-053
 A. On the center pedestal, make sure that the trim control wheels are in the 0 position.
 4. Procedure
_________ (Ref. Fig. 201/TASK 27-00-00-991-001) Subtask 27-00-00-480-050
 A. Installation of the Pitch-Trim Control Locking Tool
 (1)
 Lift the cover (1).

 (2)
 Fully loosen the two nuts (3).
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM FLIGHT CONTROLS 飛行操縱1(72)