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The two igniters are selected “ON” during :
-An automatic start in flight.
- Manual start, either in flight or, on the ground.
-Continuous ignition.
System A, located on the right hand side, is connected to
upper ignition box #1.
System B, located on the left hand side, is connected to
lower ignition box #2.

 

EFG

 

CTC-201-172-02
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ALL CFM56-5B ENGINES FOR A319-A320-A321
ENGINE SYSTEMS Jan 03

CFMI PROPRIETARY INFORMATION
CFM56-5B TRAINING MANUAL
EFG
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EFG
POWER MANAGEMENT & FUEL CONTROL

EFFECTIVITY

PWR MAN Page 1
ALL CFM56-5B ENGINES FOR A319-A320-A321
ENGINE SYSTEMS Jan 03

CFMI PROPRIETARY INFORMATION
CFM56-5B TRAINING MANUAL
EFG

POWER MANAGEMENT
The power management function computes the fan speed (N1) necessary to achieve a desired thrust.
The FADEC manages power, according to two thrust modes :
-Manual mode, depending on the Thrust Lever Angle.
-Autothrust mode, according to the autothrust
function generated by the autoflight system.

Power management uses N1 as the thrust setting parameter.
It is calculated for the appropriate engine ratings (coded in the identification plug) and based upon ambient conditions, Mach number (ADIRU’s) and engine bleeds (ECS).

EFG

 

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CTC-201-255-01
EFFECTIVITY
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ALL CFM56-5B ENGINES FOR A319-A320-A321
ENGINE SYSTEMS Jan 03

CFMI PROPRIETARY INFORMATION
CFM56-5B TRAINING MANUAL
EFG
POWER MANAGEMENT
For the current flight conditions, the FADEC calculates the power setting for each of the different ratings defined in terms of N1. When the throttle is set between detents, the FADEC interpolates between them to set the power.
The different thrust levels are :
-Idle.
-
Maximum Climb (MCL).

-
Maximum Continuous (MCT).

-
 Flexible Take-off (FLX TO).

-
 Derated Take-off (DRT TO).

-
 Maximum Take-off or Go-Around (TO/GA).

-Maximum Reverse (REV).

EFG
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CTC-201-256-02
EFFECTIVITY
PWR MAN Page 5

ALL CFM56-5B ENGINES FOR A319-A320-A321
ENGINE SYSTEMS Jan 03

CFMI PROPRIETARY INFORMATION
CFM56-5B TRAINING MANUAL
EFG
POWER MANAGEMENT & FUEL CONTROL
Each N1 is calculated according to the following flight conditions :
-Temperature : the thrust delivered depends on outside air temperature (OAT). By design, the engine provides a constant thrust up to a pre-determined OAT value, known as “corner point”, after which the thrust decreases proportionally to maintain a constant EGT value.
　
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