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EFFECTIVITY 27-90-00 Page 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
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EFCS COMPONENTS
Spoiler Elevator Computer (SEC)
IDENTIFICATION
FIN: 1CE1, 1CE2, 1CE3
LOCATION
ZONE: 83VU, 84VU, 93VU
TMUFCLP02-T02 LEVEL 3
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EFCS COMPONENTS - SEC
TMUFCLP02-P02 LEVEL 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
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EFCS COMPONENTS
Flight Control Data Concentrator (FCDC)
IDENTIFICATION
FIN: 3CE1, 3CE2
LOCATION
ZONE: 83VU, 84VU
TMUFCLP02-T03 LEVEL 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
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EFCS COMPONENTS - FCDC
TMUFCLP02-P03 LEVEL 3
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EFCS COMPONENTS
SIDE STICK
IDENTIFICATION
FIN: 4CE
LOCATION
ZONE: 182VU, 193VU
SIDE STICK TRANSDUCER UNIT (SSTU)
IDENTIFICATION
FIN: 4CE1, 4CE4
LOCATION
ZONE: 182VU, 193VU
COMPONENT DESCRIPTION
The SSTU is a part of the sidestick assembly.
TMUFCLP02-T04 LEVEL 3
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MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
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EFCS COMPONENTS - SIDE STICK - SSTU
TMUFCLP02-P04 LEVEL 3
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MECHANICS / ELECTRICS & AVIONICS COURSE 27 FLIGHT CONTROLS
UF94200
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EFCS COMPONENTS
SPEED BRAKE CONTROL TRANSDUCER UNIT
IDENTIFICATION
FIN: 7CE
LOCATION
ZONE: 11VU
COMPONENT DESCRIPTION
There are two potentiometers per SEC in the speed brake
control transducer unit.
ACCELEROMETER
IDENTIFICATION
FIN: 12CE1, 12CE2, 12CE3, 12CE4.
LOCATION
ZONE: 131VU, 132VU
TMUFCLP02-T05 LEVEL 3
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EFCS COMPONENTS - SPEED BRAKE CONTROL TRANSDUCER UNIT - ACCELEROMETER
TMUFCLP02-P05 LEVEL 3
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27 - FLIGHT CONTROLS
27-00-00 SLATS/FLAPS SYSTEM PRESENTATION
CONTENTS:
General
Slat / Flap Lever
Slat / Flap Control Computers (SFCCs)
Power Control Units (PCUs)
Position Pick-Off Units (PPUs)
Wing Tip Brakes (WTBs)
Flap Sensors
Self Examination
TMUFCTA02 LEVEL 1
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SLATS/FLAPS SYSTEM PRESENTATION
GENERAL
The high lift system includes two trailing edge flaps
(double slotted for the A321) and five leading edge
slats on each wing. The surfaces are numbered from the
wing root to the wing tip.
The position of the surfaces is selected from a control
lever which transmits the demand to the Slat Flap
Control Computers (SFCCs) through a Command Sensor
Unit.
The SFCCs, which are identical, ensure the control and
monitoring of the slat and flap system. On lever
demand, the SFCCs send signals to the Power Control
Units (PCUs) to energize the valve blocks. Two
hydraulic motors in each Power Control Unit provide
hydraulic actuation. Each of them is powered by a
　
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