FADEC

1. FADEC (Propulsion Control System)
Milind D Patil

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FADEC (Propulsion Control System)
Contents
1 Definition
2 Description
3 Safety
4 Applications
5 Advantages
6 Disadvantages
7 FADEC Faults

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Definition
FADEC is a system consisting of a digital computer, called an electronic engine
controller (EEC) or engine control unit (ECU), and its related accessories that
control all aspects of aircraft engine performance.

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True full authority digital engine controls have no form of manual override
available, placing full authority over the operating parameters of the engine in the
hands of the computer.
If a total FADEC failure occurs, the engine fails.
If the engine is controlled digitally and electronically but allows for manual
override, it is considered solely an EEC or ECU. An EEC, though a component of
a FADEC, is not by itself FADEC.
When standing alone, the EEC makes all of the decisions until the pilot wishes to
intervene.
Description

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FADEC works by receiving multiple input variables of the current flight condition
including air density, throttle lever position, engine temperatures, engine
pressures, and many other parameters.
The inputs are received by the EEC and analyzed up to 70 times per second.
Engine operating parameters such as fuel flow, stator vane position, bleed valve
position, and others are computed from this data and applied as appropriate.
FADEC also controls engine starting and restarting.
The FADEC's basic purpose is to provide optimum engine efficiency for a given
flight condition.
Description

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FADEC not only provides for efficient engine operation, it also allows the
manufacturer to program engine limitations and receive engine health and
maintenance reports.
For example, to avoid exceeding a certain engine temperature, the FADEC can
be programmed to automatically take the necessary measures without pilot
intervention.
Description

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With the operation of the engines so heavily relying on automation, safety is a
great concern.
Redundancy is provided in the form of two or more separate but identical digital
channels.
Each channel may provide all engine functions without restriction.
FADEC also monitors a variety of data coming from the engine subsystems and
related aircraft systems, providing for fault tolerant engine control.
Safety

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A typical civilian transport aircraft flight may illustrate the function of a FADEC.
The flight crew first enters flight data such as wind conditions, runway length, or
cruise altitude, into the flight management system (FMS).
The FMS uses this data to calculate power settings for different phases of the
flight.
At takeoff, the flight crew advances the throttle to a predetermined setting, or opts
for an auto-throttle takeoff if available.
The FADECs now apply the calculated takeoff thrust setting by sending an
electronic signal to the engines; there is no direct linkage to open fuel flow. This
procedure can be repeated for any other phase of flight.
In flight, small changes in operation are constantly made to maintain efficiency.
Maximum thrust is available for emergency situations if the throttle is advanced to
full, but limitations can not be exceeded; the flight crew has no means of manually
overriding the FADEC.
Applications

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• Better fuel efficiency
• Automatic engine protection against out-of-tolerance operations
• Safer as the multiple channel FADEC computer provides redundancy in case
of failure
• Care-free engine handling, with guaranteed thrust settings
• Ability to use single engine type for wide thrust requirements by just
reprogramming the FADECs
• Provides semi-automatic engine starting
• Better systems integration with engine and aircraft systems
• Can provide engine long-term health monitoring and diagnostics
• Number of external and internal parameters used in the control processes
increases by one order of magnitude
• Reduces the number of parameters to be monitored by flight crews
• Due to the high number of parameters monitored, the FADEC makes possible
"Fault Tolerant Systems" (where a system can operate within required
reliability and safety limitation with certain fault configurations)
• Saves weight
Advantages

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• Full authority digital engine controls have no form of manual override available,
placing full authority over the operating parameters of the engine in the hands
of the computer.
• If a total FADEC failure occurs, the engine fails.
• Upon total FADEC failure, pilots have no manual controls for engine restart,
throttle, or other functions.
• Single point of failure risk can be mitigated with redundant FADECs (assuming
that the failure is a random hardware failure and not the result of a design or
manufacturing error, which may cause identical failures in all identical
redundant components).
• High system complexity compared to hydromechanical, analogue or manual
control systems
• High system development and validation effort due to the complexity
• Whereas in crisis (for example, imminent terrain contact), a non-Fadec engine
can produce significantly more than its rated thrust, a FADEC engine will
always operate within its limits.
Disadvantages

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• The FADECs have two redundant channels; loss of a single channel does not
generally require crew action. Single channel FADEC faults during start may
be considered spurious on successful application of the reset procedure
detailed in FCOM PRO.AEP.ENG
• If both channels of a FADEC are lost, the thrust lever should be set to idle.
Engine indications will be lost. If all other parameters are normal (check all
ECAM system pages), the engine can be left running. Otherwise, shut it down.
• If a FADEC overheats, reducing engine power may reduce temperature in the
ECU area sufficiently to prevent shutdown. If on the ground the engine must be
shut down and the FADEC depowered.
FADEC faults