초록 ▼

A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions. Display means (6) presents a sin

A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions. Display means (6) presents a single dial (8) furnished with two needles (9.sub.1, 9.sub.2), each of them corresponding to a respective engine, and positioned in such a way that, when the engines are operating normally, the two needles are merged.

대표청구항 ▼

[ What is claimed is:] [1.] A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft, comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions, com

[ What is claimed is:] [1.] A flight control indicator for twin-engine aircraft, in particular a rotary-wing aircraft, comprising two turboengines for driving at least one rotor, intended to provide the power margin available on the engines of the aircraft as a function of the flight conditions, comprising:sensors (2, 3, 4) able to deliver information relating to various parameters for monitoring the engines, namely the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm),means (5) for processing the information arising from said sensors, and display means (6) which present, on display screen (7), the processed information relating to the parameter, from among said monitoring parameters, whose current value is closest to the limit value for said parameter, wherein said display means (6) presents a single dial (8) furnished with two needles (9.sub.1, 9.sub.2), each of them corresponding to a respective engine, and positioned in such a way that, when the engines are operating normally, the two needles are merged, and each needle (9.sub.1, 9.sub.2) presenting the smallest margin between the gas generator regime (Ng), the free turbine inlet gas ejection temperature (T4), and the engine torque (Cm), said display means having two distinct graduations making it possible to differentiate, in flight, an idling engine from an engine which is faulty or has almost shut down.