An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

A valve apparatus for an aircraft fluid system is disclosed including a valve housing and a valve member. The valve member is configured to move between a first position in which fluid is able to flow along the fluid flow path, and a second position in which the fluid flow path restricted. A valve member drive means is configured to operate the valve member via an actuator external to the housing. The valve apparatus further includes a sensor configured to monitor a feature in the housing to determine the position of the valve member.

A method for controlling at least a first turboshaft engine and a second turboshaft engine of a rotorcraft, which set a common kinematic linkage in motion, the rotorcraft having an output electric machine cooperating with a first output kinematic linkage of the first turboshaft engine, the rotorcraft having an input electric machine cooperating with a gas generator of the second turboshaft engine. The method includes the following steps: supplying fuel to the first turboshaft engine, operating the output electric machine in electrical energy generator mode, supplying fuel to the second turboshaft engine, and operating the input electric machine in motor mode in order to supply a second non-zero power to said common kinematic linkage.

A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.

A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.

A measurement system and method for liquid quantity in a receptable, the measurement system including a plurality of sensor units at various locations of the receptacle, the receptable including the liquid therein, each of the plurality of sensor units being on an outside surface of the receptacle, a data receiver coupled to the plurality of sensor units via one or more connectors and configured to receive measurements from the plurality of sensor units via the one or more connectors, and a processor coupled to the data receiver and configured to convert the received measurements from the plurality of sensor units to a measured quantity of liquid inside the receptable.

Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.

Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.

A flight control system for controlling an aircraft during a variable engine thrust takeoff operation operative to perform a method including calculating a calculated acceleration in response to a takeoff distance and a selection of a variable engine thrust takeoff mode, generating an initial thrust control signal in response to the calculated acceleration, controlling a thrust of an aircraft engine in response to the initial thrust control signal, measuring a measured acceleration of the aircraft, generating an updated thrust control signal in response to a difference between the calculated acceleration and the measured acceleration, and controlling the thrust of the aircraft engine in response to the updated thrust control signal.