Indicator for piloting an aircraft, designed to provide a power parameter of at least one turboprop engine of said aircraft

A flight control indicator for an aircraft, intended to provide a power parameter pertaining to at least one turboprop of said aircraft, said turboprop comprising a gas turbine driving the rotation of at least one propeller, said flight control indicator (1) comprising:

• data sources (2) which determine at least the values of parameters relating to the aircraft;
• data processing means (3) for processing the data received from said data sources (2);
• and
• display means (5) capable of displaying, on at least one display screen (7), data from said processing means (3), and at least one characteristic sign (11) illustrating said power parameter, wherein:
• said data sources (2) additionally determine the values of parameters relating to the propeller and to the turbine of the turboprop;
• said processing means (3) calculate, from the values determined by said data sources (2), a power parameter that takes account of the ratio between the current power of the turboprop and the maximum power obtained without air bleed at sea level in a standard atmosphere;
• and
• said processing means (3) calculate said power parameter PIT using the following expression:
• PIT=100.A.(TQc.NPc−PWRr)/(PWRmax−PWRr) in which:
• A corresponds to the sign of β-β0, β representing the current measured angle of incidence of the blades of the propeller of the turboprop, and β0 representing the angle of incidence of said blades on the ground at idle;
• TQc represents the current torque on the shaft of the free turbine;
• NPc represents the current measured speed of the propeller of the turboprop, the product TQc.NPC forming said current power;
• PWRmax represents said maximum power;
• and
• PWRr represents a predetermined reference power.