Abstract: An aircraft landing gear arrangement with an airbag attached inside a landing gear bay is disclosed. The airbag has a deflated configuration and a first inflated configuration, wherein, when the landing gear is in the extended position and when the airbag is in the first inflated configuration, the airbag closes off the landing gear bay. The airbag may substantially close off the landing gear bay. The airbag may comprise an external surface, wherein the external surface of the airbag closes off at least a significant proportion of the landing gear bay and lies substantially flush with an external surface of the aircraft body. An aircraft, methods of operating a landing gear arrangement, and methods of operating an aircraft are disclosed.

Abstract: An aircraft landing gear arrangement with an airbag attached inside a landing gear bay is disclosed. The airbag has a deflated configuration and a first inflated configuration, wherein, when the landing gear is in the extended position and when the airbag is in the first inflated configuration, the airbag closes off the landing gear bay. The airbag may substantially close off the landing gear bay. The airbag may comprise an external surface, wherein the external surface of the airbag closes off at least a significant proportion of the landing gear bay and lies substantially flush with an external surface of the aircraft body. An aircraft, methods of operating a landing gear arrangement, and methods of operating an aircraft are disclosed.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: A coating composition for coating an underwater structure which is subject to damage from water, the coating composition comprising (1) a cross-linkable polysiloxane; (2) a silane cross-linking agent; and (3) fumed silica.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: An aircraft insulation apparatus is disclosed having a variable thermal insulating member adjacent the inner fuselage wall and adjacent an aircraft heat source. The variable thermal insulating member is operable to provide variable thermal insulation between the heat source and the exterior of the inner fuselage wall by being changeable between a first state and a second state, the first state providing a first level of thermal insulation and the second state providing a second level of thermal insulation.

Abstract: A bi-directional flight control surface mechanism comprises a fixed part V of a vertical stabilizer having leading and trailing edges and a rudder having leading and trailing edges. The rudder is mounted relative to the fixed part of the vertical stabilizer so that the trailing edge of the fixed structure is adjacent the leading edge of the rudder. The rudder is movable from a neutral position in which the rudder lies in line with the fixed part of the vertical stabilizer to define a notional centerline to first and second angled positions in which the rudder is angled relative to the fixed part of the vertical stabilizer at a non-zero angle on one or other side of the notional centerline. An actuator is provided to drive the rudder relative to the fixed part of the vertical stabilizer so as to vary the distance between said part of the trailing edge of the fixed part of the vertical stabilizer and the leading edge of the rudder.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an ullage vent for use in combination with an eternal flamer barrier means during a refuelling process.

Abstract: A bi-directional flight control surface mechanism comprises a fixed part V of a vertical stabiliser having leading and trailing edges and a rudder having leading and trailing edges. The rudder is mounted relative to the fixed part of the vertical stabiliser so that the trailing edge of the fixed structure is adjacent the leading edge of the rudder. The rudder is movable from a neutral position in which the rudder lies in line with the fixed part of the vertical stabiliser to define a notional centreline to first and second angled positions in which the rudder is angled relative to the fixed part of the vertical stabiliser at a non-zero angle on one or other side of the notional centreline. An actuator is provided to drive the rudder relative to the fixed part of the vertical stabiliser so as to vary the distance between said part of the trailing edge of the fixed part of the vertical stabiliser and the leading edge of the rudder.

Abstract: Apparatus is disclosed for providing variable thermal insulation for an aircraft.

Abstract: System and method for managing a status of an application previously submitted by an applicant. Call information associated with a call is received and a determination is made whether a reason for the call is to inquire about the status of the previously submitted application based on the call information. Status information associated with the applicant is then retrieved and the applicant is automatically provided from the retrieved status information a message indicating the status of the previously submitted application if it is determined that the reason for the call is to inquire about the status of the previously submitted application.