Abstract: A method of applying an ice-removal fluid (113) to a folding wing aircraft (100) is described, the method comprising applying the ice-removal fluid (113) to the folding wing portion (103) and holding the folding wing portion in an over-folded position (111) once the ice-removal fluid (113) has been applied. A method of operating an aircraft (100) during ground based operations is further described using the method of applying an ice-removal fluid (113).

Abstract: An aircraft including a wing with a fixed wing portion and a wing tip device rotatably hingedly attached at a fixed wing portion outboard end. The wing includes a wing fold mechanism configured to actuate the wing tip device to rotate relative to the fixed wing portion to at least three commanded and predetermined wing fold angles and to restrain rotational movement of the wing tip device at each commanded position. A first position corresponds to high-speed flying, a second position to ground-based operations and a third position to low-speed flying. The flying positions rotate the wing tip to a position where upper and lower wing tip surfaces are continuations of the upper and lower surfaces of the fixed wing, with a low-speed incidence angle being less than a high-speed incidence angle. The ground-based position reduces the wing span to the greatest degree of the three positions.

Abstract: A method of applying an ice-removal fluid (113) to a folding wing aircraft (100) is described, the method comprising applying the ice-removal fluid (113) to the folding wing portion (103) and holding the folding wing portion in an over-folded position (111) once the ice-removal fluid (113) has been applied. A method of operating an aircraft (100) during ground based operations is further described using the method of applying an ice-removal fluid (113).

Abstract: A method of actuating a wing tip device on an aircraft, from a flight configuration to a ground configuration in which the span is reduced. The method includes receiving data indicative of a condition, such as the location or speed of the aircraft, and determining an actuation profile in dependence on the condition. The actuation profile may include determining a time period, and/or speed profile of the wing tip actuation over that time period. In this manner the actuation of the wing tip device can be tailored to minimize loads and wear on the actuator assembly.

Abstract: An aircraft including a wing with a fixed wing portion and a wing tip device rotatably hingedly attached at a fixed wing portion outboard end. The wing includes a wing fold mechanism configured to actuate the wing tip device to rotate relative to the fixed wing portion to at least three commanded and predetermined wing fold angles and to restrain rotational movement of the wing tip device at each commanded position. A first position corresponds to high-speed flying, a second position to ground-based operations and a third position to low-speed flying. The flying positions rotate the wing tip to a position where upper and lower wing tip surfaces are continuations of the upper and lower surfaces of the fixed wing, with a low-speed incidence angle being less than a high-speed incidence angle. The ground-based position reduces the wing span to the greatest degree of the three positions.