Patent ID: 8903570

Claim:
A standby instrument for an aircraft, the instrument comprising: at least one inertial sensor; at least one pressure sensor; calculation means to which said inertial and pressure sensors are connected and suitable for determining critical flight information for said aircraft; a memory connected to said calculation means; and a display unit capable of displaying said critical flight information in the event of a failure of a main information system of said aircraft; wherein the standby instrument incorporates in said memory stabilization relationships enabling said calculation means to determine stabilization control relationships in order to control actuators of an autopilot of said aircraft in the event of said autopilot failing, said calculation means including at least one output suitable for being connected to said actuators, said calculation means also including at least one input suitable for being connected to at least one FADEC engine computer enabling said standby instrument to display information on said display unit about a first utilization limit for one or more engines of the aircraft and about an available power or torque margin relative to said first utilization limit in the event of a failure of the first limitation instrument.