Patent ID: 6935591

Claim:
A mounting arrangement for mounting a gas turbine engine on an aircraft, the gas turbine engine having at least one casing, the mounting arrangement comprises at least one mounting for mounting the at least one casing on the aircraft, the mounting comprises at least one elastic hinge arranged parallel to the axis of the gas turbine engine or at least one elastic hinge arranged in a plane perpendicular to the axis of the gas turbine engine, the at least one elastic hinge is arranged to allow small elastic movements of the mounting within the fatigue limits of the material of the mounting; the gas turbine engine comprises a core engine and a fan, the core engine having a core engine casing, the fan having a fan casing, the mounting arrangement comprises a first mounting for mounting the fan casing on the aircraft, a second mounting for mounting the core engine casing on the aircraft and a third mounting for mounting the core engine casing on the aircraft, the first mounting comprises a first hinge, a second hinge and a third hinge, the first hinge is arranged parallel to the axis of the gas turbine engine to form a roll hinge, the second hinge is arranged in a plane perpendicular to the axis of the gas turbine engine, the third hinge is arranged in a plane perpendicular to the axis of the gas turbine engine, the second mounting comprises a fourth hinge adjacent the core engine casing and a fifth hinge adjacent the aircraft, the fourth hinge is arranged in a plane perpendicular to the axis of the gas turbine engine, the fifth hinge is arranged in a plane perpendicular to the axis of the gas turbine engine, the third mounting comprises at least one thrust strut extending from the core engine casing to the aircraft and the hinges are elastic hinges.