R Center Pedestal - THS Position Indicating
R Figure 001B
1EFF : 301-399, 1 27-45-00 Page 4
1 1 May 01/04
1 1
1CES 1
FLAPS - DESCRIPTION AND OPERATION
_________________________________
1. General
_______
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
A. System Configuration
The aircraft has four flaps (two on each trailing edge of the wing) and ten slats (five on each leading edge of the wing) (Ref. 27-80-00) to increase lift during take-off and landing.
The outboard flap is connected to the flap track carriage at the track 3 and the track 4 positions by a failsafe bolt assembly. The inboard flap is connected to the track 2 carriage by a failsafe bolt assembly and to the pendulum assembly on the track 1 carriage by the flap trunnion. The carriages move along the tracks which are part of the flap-track beam assemblies. An interconnecting strut connects the inboard and the outboard flaps. Proximity sensors on the interconnecting strut send signals to stop the flap movement, if the strut moves more than the specified limit.
**ON A/C 301-399,
A. System Configuration
The aircraft has four flaps (two on each trailing edge of the wing) and ten slats (five on each leading edge of the wing) (Ref. 27-80-00) to increase lift during take-off and landing. The inboard flap and the outboard flap each have tabs attached to their trailing edges.
The outboard flap is connected to the flap track carriage at the track 3 and the track 4 positions by a failsafe bolt assembly. The inboard flap is connected to the track 2 carriage by a failsafe bolt assembly and to the pendulum assembly on the track 1 carriage by the flap trunnion. The carriages move along the tracks which are part of the flap-track beam assemblies.
An interconnecting strut connects the inboard and the outboard flaps. Proximity sensors on the interconnecting strut send signals to stop the flap movement, if the strut moves more than the specified limit.
The tabs are attached to the rear spar of the inboard and the outboard flaps by hinges. They are operated by control rods connected to the hinge 1A mechanism and to the track 2, 3 and 4 roller carriages. A fairing covers each track and hinge.
**ON A/C ALL
Two Slat/Flap Control Computers (SFCC1 and SFCC2) monitor and control the flaps. An Instrumentation Position Pick-Off Unit (IPPU) is installed on the Power Control Unit (PCU). The IPPU sends signals to the Electronic Instrument System (EIS), which shows the position of the flaps.
A Feedback Position Pick-Off Unit (FPPU) gives signals of the output shaft position of the PCU. Two Asymmetry Position Pick-Off Units (APPU) give signals of the flap position or speed. The SFCC1 and the SFCC2 receive and monitor the signals from the FPPU and the APPUs. __________________
2. Component Location
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 001)
**ON A/C 301-399,
(Ref. Fig. 001A)
**ON A/C ALL
3. System Description
__________________ R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 002)
**ON A/C 301-399,
(Ref. Fig. 002A)
Flap System - Component Location
Figure 001
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-50-00Page 3 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
R Flap System - Component Location
R Figure 001A
R 1EFF : 301-399, 1 27-50-00 Page 4
1 1 May 01/04
1 1
1CES 1
Flaps Electrical Control and Monitoring - Schematic
Figure 002
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-50-00Page 5 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1R Flaps Electrical Control and Monitoring - Schematic R Figure 002A
R 1EFF : 301-399, 1 27-50-00Page 6 1 1 May 01/04 1 1 1CES 1 **ON A/C ALL
A. Electrical Control and Monitoring System (Ref. 27-51-00)
The slat and flap control lever controls the position of the flaps. The Command Sensor Unit (CSU) identifies the position of the slat and flap control lever and sends related signals to each SFCC. Each SFCC controls the valve block of a hydraulic motor, which is part of the flap PCU.
The FPPU, which is part of the flap PCU, and the two APPUs send related signals to the SFCCs. If the SFCCs find a failure in the system, the Wing Tip Brakes (WTB) operate to hold the transmission and the PCU is stopped.
B. Hydraulic Actuation and Power Transmission (Ref. 27-54-00)
A hydro-mechanical PCU supplies mechanical power to the power transmission system. The PCU has two separate hydraulic motors and two Pressure-Off Brakes (POB). Each hydraulic motor has an electrically controlled valve block, which receives signals from a SFCC.
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3(187)
