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The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connectin

The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connecting the engine structure to the pylon, and a flexible connection provided between the hinged connections and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position.

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1. A mounting system for mounting a turbofan engine to an aircraft, the turbofan engine having a main rotational axis and an associated transverse axis laterally perpendicular to the main axis, and a nacelle including two annular halves, each half having a hinged end adjacent the pylon and a free en

1. A mounting system for mounting a turbofan engine to an aircraft, the turbofan engine having a main rotational axis and an associated transverse axis laterally perpendicular to the main axis, and a nacelle including two annular halves, each half having a hinged end adjacent the pylon and a free end, the system comprising: a pylon;a connection configured for mounting the engine to the pylon and configured to maintain the position of the engine relative to the pylon during operation of the aircraft;at least two hinged connections, each hinged connection being provided between the hinged end of a half and the pylon, the hinges operable to permit closing and opening the halves between open and closed positions;a flexible connection extending between at least one of the hinged connections and the pylon, the flexible connection configured to elastically deform in response to a lateral force exerted on a corresponding half while the halves are in the closed position, the force exceeding a pre-selected threshold, said elastic deformation permitting at least a portion of a corresponding hinged connection to move relative to the engine structure. 2. The mounting system of claim 1 wherein the flexible connection extends between each one of the at least two hinged connections and the pylon and is in a transversal plane coinciding with or adjacent a fan of the turbofan gas turbine engine. 3. The mounting system of claim 1 wherein the hinged connections include a plurality of hinge unit pairs, each hinge unit including a pylon hinge member engaged with a corresponding duct hinge member, the hinge units of each pair are aligned lengthwisely with one another along a corresponding hinge axis, and the flexible connection is associated to at least one of the hinge unit pairs. 4. The mounting system of claim 3 wherein the flexible connection includes two flexible members, each one of the two flexible members being associated with a corresponding hinge unit of one of the hinge unit pairs. 5. The mounting system of claim 4 wherein the flexible members each independently connect a corresponding pylon hinge member to a structure of the pylon. 6. The mounting system of claim 3 wherein at least one of the hinge unit pairs has the corresponding pylon hinge members provided at corresponding ends of a transverse beam, the transverse beam being connected to a structure of the pylon via the flexible connection. 7. The mounting system of claim 6 wherein the transverse beam is mounted to a sheet-metal floor of the pylon, the sheet-metal floor of the pylon being connected to the pylon structure. 8. The mounting system of claim 7 wherein the flexible connection is provided at least partially by way of a flexibility of the sheet-metal floor of the pylon. 9. The mounting system of claim 6 wherein the flexible connection includes a flexible member on each side and associated with each hinge unit of the at least one hinge unit pair. 10. The mounting system of claim 9 wherein the flexible members include at least one flexible sheet metal component. 11. The mounting system of claim 10 wherein the flexible members are provided in the form of sheet metal brackets. 12. The mounting system of claim 9 wherein the flexible members include at least one elastomeric member made of elastomeric material. 13. The mounting system of claim 6 wherein the flexible connection includes linkages. 14. The mounting system of claim 1 further comprising at least one structural fuse connection member structurally resistant to forces up to a significant force threshold to bypass the flexible connection, and breaking when subjected to the significant force at or above the significant force threshold to allow said movement of the hinge. 15. The mounting system of claim 1 wherein the primary connection includes at least two main engine mounts, and wherein the hinged connection movement corresponds to at least five times a corresponding movement of any one of the main engine mounts for a same significant force. 16. A method of managing a significant force event on a gas turbine engine supported by a pylon of an operating aircraft, the turbofan gas turbine engine having a core engine with an engine structure, a main axis and an associated radial orientation, a primary connection connecting the engine structure to the pylon and maintaining the position of the engine structure relative to the pylon; a nacelle including two halves, each half having a hinged end adjacent the pylon and a free end; and two hinged connections, each hinged connection being provided between the hinged end of a corresponding one of the halves and the pylon and operable for selectively closing the halves concentrically around the core engine and opening the halves, the halves being lockingly engageable with the engine structure when in the closed position; the significant force being exerted in a transversal plane and exerted upon one of the halves in the closed position; the method comprising: transferring the significant force to a flexible connection provided between the corresponding half and the pylon, thereby elastically deforming the flexible connection and moving a corresponding hinge relative to the engine structure. 17. The method of claim 16 wherein the flexible connection is in a transversal plane near a fan of the turbofan gas turbine engine. 18. The method of claim 16 wherein the step of transferring the significant force includes breaking at least one structural fuse connection member structurally resistant to forces of a magnitude up to a predetermined significant force threshold. 19. The method of claim 16 wherein the moving includes moving the corresponding hinge by a distance at least five times a corresponding distance of movement of the engine structure. 20. A mounting system for mounting a turbofan gas turbine engine to a pylon of an aircraft, the turbofan gas turbine engine having a core engine with an engine structure, a main axis and an associated transverse axis, and a nacelle including two halves, each half having a hinged end adjacent the pylon and a free end, the mounting system comprising: a primary connection connecting the engine structure to the pylon and maintaining the position of the engine core relative to the pylon during operation of the aircraft;a plurality of pairs of hinges aligned lengthwisely along a corresponding pair of hinge axes, each hinge axis being on a corresponding side of the primary connection; each pair of hinges having a pair of pylon hinge members engaged with a corresponding pair of nacelle hinge members; the plurality of pairs of hinges hingedly connecting a hinged end of the halves to the pylon for selectively closing the halves concentrically around the core engine and opening the halves about the hinge axes, the free end of the halves being lockingly engageable with the engine structure when in the closed position;a flexible connection provided between the halves and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position, the significant force thereby moving at least a corresponding hinge relative to the engine structure.