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The stall warning system of a large aeroplane includes:

1 – an angle of attack sensor
2 – a computer
3 – an independent pitot probe
4 – a transmitter of the flap/slat position indicating system.

The combination that regroups all of the correct statements is:

  • A
    1, 2, 3.
  • B
    1, 2, 4.
  • C
    2, 4.
  • D
    1, 3.
On a large transport airplane and according to the CS25, when the airspeed is becoming increasingly lower, the stall warning must begin at a speed exceeding the stall speed by not less than 5kt or 5% CAS, whichever is greater. This is because the stall warning system needs to generate the alarm with sufficient margins in order to prevent inadvertent stalling with the flaps and landing gear in any normal position. The stall warning will typically consist of an aural warning with a voice warning such as ‘STALL, STALL’, and a stick shaker connected to the control column. Caution! The stall warning is only alerting the pilot that the aircraft has entered a stall while the stick pusher is a protection – it acts on the control column to prevent the aircraft from entering the stall conditions.
The input data of the stall warning system are:
  • Angle of attack
  • Configuration (slats/flaps deflection)
Note: The stall warning is inhibited while on the ground.

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