(2) Remove the warning notice(s).
F 『 EEFF : ALL E Page 40873-11-70
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
CONTROLLING - DESCRIPTION AND OPERATION
_______________________________________
1. General
_______
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-211,
The FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) provides full range of engine control to achieve steady state and transient engine performances when operated in combination with aircraft subsystems. The FADEC System consists of a dual channel ECU and the following peripherals.
- Hydromechanical Unit
- Dedicated Permanent Magnet Alternator
- VSV and VBV, HPTACC, LPTACC, TBV systems
- Start system (starter shutoff valve, ignition exciters)
- Thrust reverser system
- Oil/Fuel Temperature Control (IDG oil)
- Engine sensors
- Electrical harnesses
- Burner Selection Valve (BSV) The ECU is a vibration isolated single unit mounted on the fan case, air cooled by ducting ambiant air to the ECU. It is a part of the basic engine equipment.
R **ON A/C 106-149, 212-299, 301-399, 401-499,
The FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) provides full range of engine control to achieve steady state and transient engine performances when operated in combination with aircraft subsystems. The FADEC System consists of a dual channel ECU and the following peripherals.
- Hydromechanical Unit
- Dedicated Permanent Magnet Alternator
- VSV and VBV, HPTACC, LPTACC, RAC/SB systems
- Start system (starter shutoff valve, ignition exciters)
- Thrust reverser System
- Oil/Fuel Temperature Control (IDG oil)
- Engine sensors
- Electrical harnesses The ECU is a vibration isolated single unit mounted on the fan case, air cooled by ducting ambiant air to the ECU. It is a part of the basic engine equipment.
F 『 EEFF : ALL E Page 173-20-00
E E Aug 01/05 E E ECES ER **ON A/C ALL
F 『
E C F M E
E E
E 56-5B E
E E
2. System Description
__________________
A. Full Authority Digital Engine Control (FADEC)
(1) FADEC Functions (Ref. Fig. 001) for general FADEC system schematic The FADEC system operates compatibly with applicable aircraft systems to perform the following functions. (Ref. Fig. 001)
(a) GAS generator control for steady state and transient engine operation within safe limits.
- Fuel flow control
- Acceleration and deceleration schedules
- VSV and VBV schedules
- Turbine clearance control
- Idle setting.
(b) Engine limits protection
- Engine overspeed protection in term of fan speed (N1) and core speed (N2) to prevent exceedance of certified red lines
- Engine turbine exhaust gas temperature monitoring (EGT).
(c) Power management
- Automatic engine thrust rating control using N1 as the thrust setting parameter.
- Thrust parameter limits computation
- Manual power management through constant ratings versus throttle lever relationship :
- take-off/go-around at full forward throttle control lever position
- flex take-off at constant intermediate position whatever the reduced thrust is, and other ratings (max continuous, max climb, idle, max reverse) at constant unique throttle lever position.
- Automatic power management through direct engine power adjustment to the autothrust system demand.
(d) Automatic engine start sequencing
- Control of starter valve ON/OFF
- Control of HP fuel valve (ON/OFF on ground, ON in flight)
- Control of fuel schedule
- Control of ignition ON/OFF
F 『 EEFF : ALL E Page 273-20-00
E E May 01/05 E E ECES E F 『 E C F M E E E E 56-5B E
Full Authority Digital Electronic Control - Schematic Figure 001
F 『 EEFF : ALL E Page 373-20-00
E E May 01/05 ERE ECES E
F 『
E C F M E
E E
E 56-5B E E E - N1, N2, WF, EGT monitoring
- Abort/Recycle capability on ground.
(e) Thrust reverser control
- Control thrust reverser actuation (deploying and stowing) 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護手冊 AMM 發動機燃油和控制 ENGINE FUEL AND CONTRO(82)
