STL 945.7136/97
8. Engine controls
8.1
STL 945.7136/97 8.3
A319/A320/A321 engine controls - FADEC
Thrust control is operated through Full Authority
Digital Engine Control (FADEC) computers which :
- command the engines to provide the best suited
power to each flight phase
- automatically provide all the associated protection
required :
either in manual (thrust lever)
or in automatic (autothrust) with a fixed thrust
lever.
Engine performance and safety better than with
current hydromechanical control system.
Simplification of engine/aircraft communication
architecture.
Reduction of crew workload by means of automatic
functions (starting, power management).
Ease of on-wing maintenance.
The system design is fault-tolerant being fully
duplicated, with “graceful degradation” for minor
failures (i.e. sensor failures may lose functions but not
the total system).
The engine shut-down rate resulting from FADEC
failures will be at least as good as today’s latest
hydromechanical systems with supervisory override.
FADEC is an electronic system which incorporates a
fully redundant Engine Control Unit (ECU) and an
Engine Interface Unit (EIU).
Each engine is equipped with a FADEC which provide
the following operational functions :
- gas generator control
- engine limit protection
- engine automatic starting
- power management
- engine data for cockpit indication
- engine condition parameters
- reverser control and feed back.
•
•
STL 945.7136/97 8.4
A319/A320/A321 engine controls – FADEC architecture
SYSTEMS
DISPLAYS
ENGINE/
WARNINGS
DISPLAY
ECU CHANNEL. A
ECU CHANNEL. B HYDROMECHANICAL
UNIT
START VALVE
THRUST REVERSER
SYSTEM
IGNITION SYSTEM
FUEL RECIRCULATION
VALVE
ENGINE
INTERFACE
UNIT 1
(ECU)
ZONE
CONTROLLER
GRND/FLT
BLEED STATUS
FMGS
ENG
MAN START
ADIRS 1+2
ADIRS 1+2
ENGINE
PARAMETERS
TLAA
TLAB
THRUST
LEVER 1
STL 945.7136/97 8.5
A319/A320/A321 engine controls – ECU and EIU
One ECU located on the engine with dual redundant
channels (active and standby) each having separate 28V
DC aircraft power sources to ensure engine starting on
ground and in flight.
In addition dedicated ECU alternator assures self power
above 12% N2 for CFM56 (10% N2 for IAE V2500).
Dual redundancy for electrical input devices (ADIRS 1+2,
TLAs, engine parameters).
Dual redundancy for electrical part of control actuator.
Simplex system for hydromechanical parts of the control.
Fault tolerance and fail operational capability.
High level of protection against electromagnetic
disturbance.
The interface between the FADEC system and the
other aircraft systems is mainly performed by the EIU
through digital data buses.
One EIU per engine is located in the avionics bay.
Care is taken to preserve systems segregation for
safety and integrity.
STL 945.7136/97 8.6
A319/A320/A321 engine controls – CFM56
28 VDC
Engine
control
unit
Monitoring signals (optional)
ARINC
data
buses
Starter air
valve / starter
Ignition
Thrust
reverser
Control
signals
Hydromech.
unit
Alternator
Feedback
T12
N1
N2 T25 PS12 PS12 PS3 Tcase T3
P0
Fuel PS13 P25 T5
T fuel flow
HPT
Fuel CC
VSV
VBV
STL 945.7136/97 8.7
A319/A320/A321 engine controls – V2500
28 VDC
Electronic
engine
control
Monitoring signals (optional)
ARINC
data
buses
Starter air
valve / starter
Ignition
Thrust
reverser
Control
signals
Hydromech.
unit
Alternator
Feedback
T2
N1
N2 Pb P2 P5 P3 T4.9 T3
P0
P12.5 P2.5 T2.5
Fuel
T fuel flow
HPT
Fuel CC
VSV
VBV
STL 945.7136/97 8.8
A319/A320/A321 engine controls – thrust control schematic
CFM56
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