(4) Engage the nuts (4) on the lugs ant tighten. Subtask 27-93-34-865-052
 B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): FOR 2CE1 15CE1, 16CE1 FOR 2CE2 15CE2, 16CE2.
 Subtask 27-93-34-710-050
 C. Do the operational test of the ELAC (Ref. TASK 27-93-00-710-001). NOTE : If the airline operates the aircraft in CAT III conditions, do the
____ LAND CAT III capability test (Ref. TASK 22-97-00-710-001).
 1EFF : ALL 1 27-93-34Page 405 1 1 Aug 01/99R 1 1 1CES 1

 5. Close-up
________
 Subtask 27-93-34-410-050

 A. Close Access
 (1)
 Make sure that the work area is clean and clear of tool(s) and other items.

 (2)
 Install the protective cover on the battery power center 105VU.

 (3) Tighten the two screws. R (4) Close the access doors 822 and 824 (Ref. TASK 52-41-00-410-002).
 (5) Remove the access platform(s).

 SEC SYSTEM (SPOILER AND ELEVATOR COMPUTER) - DESCRIPTION AND OPERATION
______________________________________________________________________
R 1. General_______
R The Spoiler Elevator Computer (SEC) is a sub-system of the Electrical Flight
R Control System which controls the spoilers and, in standby mode, the pitch
R control surfaces.
R The role of the SEC is to convert pilot inputs into control surface
R movements, based on aircraft motion information from roll and pitch
R transducers, accelerometers, speedbrake control lever, etc.
R (Ref. Fig. 001)
R Each aircraft has three SECs
R The functions achieved are :
R - Roll
R - Ground Spoiler
R - Speedbrake
R - Elevator and THS controls
R Each computer has two units:
R - the COM unit which mainly calculates the deflection orders as a function
R of the received signal and slaves the control surfaces.
R - the MON unit which mainly checks that the orders are correctly executed.
R
 2. Component Location
__________________
 (Ref. Fig. 002)

 -------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
 -------------------------------------------------------------------------------1CE1 SEC-1 83VU 127 824 27-94-34 1CE2 SEC-2 84VU 128 824 27-94-34 1CE3 SEC-3 93VU 121 811 27-94-34
 3. Power Supply
____________
 (Ref. Fig. 003)
 The SEC1 is supplied from the DC essential busbar 4PP, the battery 1 taking
 over instantaneously through a dedicated diode device (Power Supply
 Decoupling Unit) when the voltage level drops below the battery output
 voltage.
 (Ref. Fig. 004)
 A relay ensures the battery supply line breaking on the ground 30s after the
 second engine is shut down.
 The SEC2 and SEC3 are supplied from the DC normal busbar 2PP
 (Ref. Fig. 005)

 SEC Architecture
 Figure 001
 1EFF :  ALL  1  27-94-00 Page 2 
1  1  Feb 01/98
 1  1
 1CES  1

 SECs Location
 Figure 002
 1EFF :  ALL  1  27-94-00 Page 3 
1  1  Feb 01/98
 1  1
 1CES  1

 SEC Electrical Power Supply
 Figure 003
 1EFF :  ALL  1  27-94-00 Page 4 
1  1  Feb 01/98
 1  1
 1CES  1

 SEC 1 Power Supply
 Figure 004
 1EFF :  ALL  1  27-94-00 Page 5 
1  1  Feb 01/98
 1  1
 1CES  1

 SEC 2 and SEC 3 Power Supply
 Figure 005
 1EFF :  ALL  1  27-94-00 Page 6 
1  1  Feb 01/98
 1  1
 1CES  1

 4. Interface
_________
 Each SEC receives and sends analog, digital and discrete data
 (Ref. Fig. 006)

 A. Analog Interface
 (1)
 Interface with the Side Stick Transducer Units. (Ref. Fig. 007) Each side stick (CAPT and F/O) has two transducer units ; one for the roll, the other one for the pitch. The transducer units transmit side stick information to the SEC command and monitoring units (ANI 1). The associated SEC unit ensures the power supply of each potentiometer track. There are also discrete signals for side stick priority.

 (2)
 Interface with the Throttle Control Unit. (Ref. Fig. 008) For ground spoiler logic, each SEC receives throttle position data from two potentiometers of one Throttle Control Unit.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM FLIGHT CONTROLS 飛行操縱9(80)