(3)
Interface with the Speedbrake Control Transducer Unit. (Ref. Fig. 009) The Speedbrake Control Transducer Unit has two sets of three-tracks potentiometers. The COM unit of each SEC is connected to one potentiometer of one set, the MON unit is connected to one potentiometer of the other set.
(4)
Interface with RVDT or LVDT 6 wire transducers (ANI 2) : for surface position transducer. 4 wire transducers: (ANI 3) : for servovalve position transducer, (ANI 7) : for servo-actuator mode transducer.
(5)
Interface with the wheel tachometer. (Ref. Fig. 010) Each main landing gear wheel is fitted with a tachometer that transmits wheel speed information to the SEC COM and MON units (ANI 6).
(6)
Interface with the accelerometers. (Ref. Fig. 011) Each accelerometer is connected to the COM and MON units of one SEC (ANI 4). Each SEC is connected to two accelerometers.
SEC Links (General)
Figure 006
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Side Stick Transducer Unit
Figure 007
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Throttle Control Units
Figure 008
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Speedbrake Control Transducer Unit
Figure 009
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Tachometers
Figure 010
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Accelerometers
Figure 011
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B. Discrete Interface
(1)
Interface with pressure switches. (Ref. Fig. 012) Each SEC COM and MON unit is directly connected to one switch per system.
(2)
Interface with the SFCC.
(Ref. Fig. 013) R One discrete signal is transmitted from each SFCC slat channel to the R SEC: R - slat position equal to or greater than 17 deg.: ground R - slat position less than 17 deg.: open circuit
(3)
Ground Spoilers extended. (Ref. Fig. 014) Each SEC unit sends to the BSCU and ELAC the discrete signal (DS07) : Ground spoilers extended.
(4)
Interface with the ELACs. (Ref. Fig. 015, 016) The DGI 9 and DGI 11 (Ref. ARINC interface) digital data are validated by the discrete data DSI 14 and DSI 21 on each unit. The SEC sends and receives discrete information for pitch priority (Ref. Fig. 017, 018)
(5)
Interface with the other SECs
(Ref. Fig. 019, 020)
C. ARINC Interface
(1)
Interface with the LGCIU. (Ref. Fig. 021) Each SEC command and monitor unit receives (DGI 14) an ARINC 429 data-bus discrete word using the landing gear up/down information.
(2)
Interface with the SFCC. (Ref. Fig. 022) The SEC COM and MON units use the digital information from the SFCC for configuration determination
(3)
Interface with the ADIRS. (Ref. Fig. 023, 024) The connections of the ADIRS to the SEC consist of two ARINC 429 data buses transmitted from each ADC and two buses transmitted from each IRS.
(4)
SERVO DRIVE board
The SERVO DRIVE board performs the functions below :
Pressure Switches
Figure 012
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R R SFCC/ELAC-SEC (Discrete) Figure 013
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SEC Discrete Output: GND SPLR ON
Figure 014
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ELAC Discrete Output: DGO 1 Validation
Figure 015
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ELAC DIGITAL OUTPUT 1 (ARINC 429)
Figure 016
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本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵9(81)
