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A method and apparatus comprising a frame, a first linking system connected to the frame, and a second linking system connected to the frame. The frame may be configured to be connected to a support structure for an engine of an aircraft. The first linking system may be configured to be connected to

A method and apparatus comprising a frame, a first linking system connected to the frame, and a second linking system connected to the frame. The frame may be configured to be connected to a support structure for an engine of an aircraft. The first linking system may be configured to be connected to a fan case in the engine. The second linking system is configured to be connected to an engine core case in the engine.

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1. An aircraft engine mount apparatus that comprises: a frame that comprises a first connector section coplanar with and directly connected to elongate members directly connected to a second connector section, such that:the elongate members extend from the first connector section, along a length of

1. An aircraft engine mount apparatus that comprises: a frame that comprises a first connector section coplanar with and directly connected to elongate members directly connected to a second connector section, such that:the elongate members extend from the first connector section, along a length of an engine of an aircraft toward an inlet of the engine, to the second connector section; andthe first connector section configured to directly connect to a support structure of the engine via openings that penetrate through a thickness of the first connector section;a first linking system that comprises a fixed link and a floating link such that each fixed and floating link directly connects to the second connector section and each fixed and floating link directly connects to a bracket on a fan case of the engine; anda second linking system that comprises a bar and a number of angular-shaped links that directly connect to the bar secured between a number of lugs and directly connected to an underside of the first connector section and wherein each opposing side of the number of angular-shaped links is pivotably connected to a number of brackets on an engine core case. 2. The aircraft engine mount apparatus of claim 1, further comprising the second connector section configured to be connected to the first linking system via two clevis elements. 3. The aircraft engine mount apparatus of claim 1 further comprising: the bracket on the fan case comprising a number of devises that extended upward from a circumference of the fan case. 4. The aircraft engine mount apparatus of claim 1 further comprising: the number of brackets on the engine core case each comprises: a substantially planar section, and a flange that comprises a hole. 5. The aircraft engine mount apparatus of claim 1, wherein the first linking system comprises: clevis elements that comprise flanges and connect with the second connector section via the fixed link and the floating link. 6. The aircraft engine mount apparatus of claim 1, wherein the frame comprises: the first connector section that comprises a top side that comprises openings, and a bottom side that comprises flanges that extend away from the bottom side; andthe second connector section that comprises flanges, such that each flange respectively comprises a hole centered on an axis substantially perpendicular to a length of the frame. 7. The aircraft engine mount apparatus of claim 1, wherein the frame, the first linking system, and the second linking system are comprised of a number of materials selected from one of titanium, steel, and a steel alloy, and a distance between each elongate member being less near the second connector section than the distance between each elongate member near the first connector section. 8. The aircraft engine mount apparatus of claim 1, wherein the frame, the first linking system, and the second linking system form a forward mounting system for connecting the support structure to the engine. 9. The aircraft engine mount apparatus of claim 1, wherein the first linking system is configured to carry a number of side loads in a direction that is substantially perpendicular to an axis extending centrally through the fan case. 10. The aircraft engine mount apparatus of claim 1, wherein the second linking system is configured to carry a number of vertical loads in a direction substantially perpendicular to an axis extending centrally through the fan case. 11. The aircraft engine mount apparatus of claim 5, further comprising the floating link having fasteners of a variety of sizes. 12. The aircraft engine mount apparatus of claim 9, wherein a side load in the number of side loads is in a direction that is substantially parallel to a pitch axis through the aircraft. 13. The aircraft engine mount apparatus of claim 10, wherein a vertical load in the number of vertical loads is in a direction that is substantially parallel to a yaw axis through the aircraft. 14. A method for operating an engine, the method comprising: operating the engine connected to a wing of an aircraft by a mounting system comprising: a frame, a first linking system connecting the frame to a fan case in the engine, and a second linking system connecting the frame to an engine core case in the engine, the frame comprising:a first connector section coplanar with and directly connected to elongate members directly connected to a second connector section, the elongate members extending from the first connector section to the second connector section;the first linking system comprising a fixed link and a floating link, each fixed link and floating link directly connecting the second connector section to the fan case in the engine;the second linking system comprising: a bar, and a number of angular-shaped links directly connecting to the bar, secured between a number of lugs and directly connecting to an underside of the first connector section, and connecting the first connector section to the engine core case in the engine, such that each link in the number of links comprises an angular shape, each opposing side of the number of links pivotably connecting to a number of brackets on the engine core case;directly connecting, via openings that penetrate through a thickness of the first connector, the first connector section to a support structure on the wing with the elongate members extending toward an inlet of the engine;carrying a number of side loads using the first linking system; andcarrying a number of vertical loads using the second linking system. 15. The method of claim 14, wherein the step of carrying the number of side loads using the first linking system comprises: carrying the number of side loads using the first linking system and the frame. 16. The method of claim 14, wherein the step of carrying the number of side loads using the first linking system comprises: carrying the number of side loads using the first linking system and the frame, wherein a bracket is configured to connect the first linking system to the fan case. 17. The method of claim 14, wherein the step of carrying the number of vertical loads using the second linking system comprises: carrying the number of vertical loads using the second linking system, wherein the bar is configured to connect the second linking system to a bottom side of the frame. 18. The method of claim 14, wherein the step of carrying the number of vertical loads using the second linking system comprises: carrying the number of vertical loads using the second linking system, wherein a number of brackets is configured to connect the second linking system to the engine core case. 19. The method of claim 14, wherein the first linking system comprises clevis elements that comprise flanges and connect with the second connector section via the fixed link and the floating link. 20. The method of claim 14, further comprising the frame, the first connector section, the second connector section, and the elongate members comprising a number of materials selected from one of titanium, steel, and a steel alloy, and a distance between each elongate member being less near the second connector section than the distance between each elongate member near the first connector section. 21. The method of claim 14 further comprising: carrying a number of thrust loads using the second linking system. 22. The method of claim 14, wherein the mounting system is a forward mounting system configured to connect an engine pylon to the engine. 23. The method of claim 14 further comprising: reducing drag during operation of the engine using a fairing comprising a smaller fairing than a fairing required when mounting the engine without applying the method of claim 14; andthe smaller fairing covering the mounting system and the support structure connected to the engine by the mounting system. 24. An aircraft engine mounting system that comprises: a frame configured to be connected to a support structure in an engine pylon for an engine of an aircraft in which the frame has a first end directly connected to the support structure for the engine and a second end configured to be connected to a first linking system, such that the frame comprises a first connector section at the first end of the frame; a second connector section at the second end of the frame; and a number of elongate members that extend between and directly connect to the first connector section and the second connector section;the first connector section comprising openings, configured to directly connect the first connector section to a support structure for the engine, that penetrate through a thickness of the first connector;the first linking system connected to the frame and directly connected to a bracket on a fan case in the engine, such that the elongate members extend, from the first end toward an inlet of the engine and coplanar to the first end, to the second end, and the first linking system comprises a fixed link and a floating link, each fixed link and floating link configured to carry a number of side loads in a first direction that is substantially parallel to a pitch axis through the aircraft; anda second linking system directly connected to the frame and comprising a bar, and a number of angular-shaped links, directly connected to the bar, secured between a number of lugs and directly connecting to an underside of the first connector section, and to a number of brackets on an engine core case in the engine such that the second linking system is configured to carry a number of vertical loads in a second direction that is substantially parallel to a yaw axis through the aircraft. 25. A method for operating an engine, the method comprising: operating the engine connected to an engine pylon of a wing of an aircraft by a forward mounting system comprising: a frame comprising: a first end, a second end, a top side, and a bottom side;a first linking system comprising a fixed link and a floating link, each fixed link and floating link directly connecting to the frame and to a bracket on a fan case in the engine; anda second linking system comprising a bar secured between a number of lugs and directly connected to an underside of a first connector section, and a number of angular-shaped links directly connecting to the bottom side of the frame and a number of brackets on an engine core case in the engine;connecting the top side of the first end to a support structure for the engine and to the second end to the first linking system, such that the frame comprises a first connector section at the first end; a second connector section at the second end; and a number of elongate members extending between and connecting the first connector section to the second connector section such that with the first end connecting to the support structure, via openings that penetrate through a thickness of the first connector section, the elongate members extend, toward an inlet of the engine, coplanar to and from the first end, to the second end;carrying a number of side loads using the first linking system; andcarrying a number of vertical loads using the second linking system.