Mounting for coupling a turbofan gas turbine engine to an aircraft structure

A mounting for coupling a turbofan gas turbine engine to an aircraft structure, the turbofan gas turbine engine having an axis and comprising a core engine and a fan, the core engine having compressor means, combustor means, turbine means and a core casing, the fan operating within a fan duct defined in part by a fan casing, the fan casing extending from a fan duct intake to a fan duct nozzle,

• the aircraft structure having three mounting points on the aircraft structure, the three mounting points being arranged at the vertices of a first triangle,
• the fan casing having three mounting points arranged at the vertices of a second triangle,
• support means connecting the three mounting points on the fan casing with the core casing to support the core engine,
• first connecting means connecting a first one of the mounting points on the aircraft structure with the three mounting points on the fan casing,
• second connecting means connecting a second one of the mounting points on the aircraft structure with two of the mounting points on the fan casing,
• and third connecting means connecting a third one of the mounting points on the aircraft structure with at least one of the mounting points on the fan casing;
• the first connecting means comprising a first link connecting the first mounting point on the aircraft structure with the first mounting point on the fan casing, a second link connecting the first mounting point on the aircraft structure with the second mounting point on the fan casing and a third link connecting the first mounting point on the aircraft structure with the third mounting point on the fan casing, and
• wherein the first link comprises means to control the length of the first link to vary the pitch angle of the turbofan gas turbine engine relative to the aircraft structure.

A mounting for coupling a turbofan gas turbine engine to an aircraft structure, the turbofan gas turbine engine having an axis and comprising a core engine and a fan, the core engine having compressor means, combustor means, turbine means and a core casing, the fan operating within a fan duct defined in part by a fan casing, the fan casing extending from a fan duct intake to a fan duct nozzle,

• the aircraft structure having three mounting points on the aircraft structure, the three mounting points being arranged at the vertices of a first triangle,
• the fan casing having three mounting points arranged at the vertices of a second triangle,
• support means connecting the three mounting points on the fan casing with the core casing to support the core engine,
• first connecting means connecting a first one of the mounting points on the aircraft structure with the three mounting points on the fan casing,
• second connecting means connecting a second one of the mounting points on the aircraft structure with two of the mounting points on the fan casing,
• and third connecting means connecting a third one of the mounting points on the aircraft structure with at least one of the mounting points on the fan casing, at least some of said connecting means including first and second links connected by length controlling means operable to vary the length of said respective connecting means so as to vary the position of a portion of the fan casing to vary the tip clearance between the fan and the fan casing.