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A method for assembling a gas turbine engine includes coupling a gearbox to a low-pressure turbine, the gearbox includes a plurality of planetary gears intermeshed with the sun gear, each of the planetary gears includes a first gear portion having a first diameter and a second gear portion having a

A method for assembling a gas turbine engine includes coupling a gearbox to a low-pressure turbine, the gearbox includes a plurality of planetary gears intermeshed with the sun gear, each of the planetary gears includes a first gear portion having a first diameter and a second gear portion having a second diameter that is different than the first diameter.

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What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: coupling a gearbox to a single rotation low-pressure turbine, the gearbox including a plurality of planetary gears intermeshed with a sun gear, wherein each of the planetary gears includes a first gear port

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: coupling a gearbox to a single rotation low-pressure turbine, the gearbox including a plurality of planetary gears intermeshed with a sun gear, wherein each of the planetary gears includes a first gear portion having a first diameter and a second gear portion axially displaced from the first gear portion and having a second diameter different than the first diameter; coupling a first fan assembly directly to the single rotation low-pressure turbine so that the first fan assembly is not driven by the gearbox; coupling a second fan assembly to the first gear portion; and coupling the sun gear to one of the first gear portion and the second gear portion; and coupling a booster compressor to the second gear portion such that the single rotation low-pressure turbine is configured to drive the first fan assembly, the second fan assembly, and the booster compressor and such that the first fan assembly is rotatable in a first rotational direction and the second fan assembly is rotatable in a second rotational direction that is different than the first rotational direction. 2. A method in accordance with claim 1 further comprising coupling the first fan assembly to the single rotation low-pressure turbine such that the first fan assembly is rotatable at a first rotational speed that is different than a second rotational speed of the second fan assembly and the booster compressor. 3. A method in accordance with claim 1 further comprising coupling the second fan assembly to the first gear portion such that the second fan assembly is rotatable at a first rotational speed and coupling the booster compressor to the second gear portion such that the booster compressor is rotatable at a second rotational speed that is different than the first rotational speed. 4. A method in accordance with claim 1 wherein the sun gear has a third diameter that is selected based on a rotational speed of at least one of the first fan assembly, the second fan assembly, and the booster compressor, said method further comprising coupling the sun gear to the planetary gears such that the sun gear is rotatable at a first rotational speed and such that at least one of the second fan assembly and the booster compressor is rotatable at a second rotational speed that is different than the first rotational speed. 5. A method in accordance with claim 1 further comprising coupling the sun gear to each planetary gear such that the sun gear is intermeshed only with the first gear portion. 6. A method in accordance with claim 1 further comprising coupling the sun gear to each planetary gear such that the sun gear is intermeshed only with the second gear portion. 7. A counter-rotating fan assembly comprising: a gearbox comprising a sun gear coupled to a single rotation low-pressure turbine; a plurality of planetary gears intermeshed with said sun gear, each of said planetary gears comprising a first gear portion having a first diameter and a second gear portion axially displaced from the first gear portion and having a second diameter that is different than the first diameter; a first fan assembly directly coupled to said single rotation low-pressure turbine so that the first fan assembly is not driven by the gearbox; a second fan assembly coupled to said first gear portion; and the sun gear coupled to one of the first gear portion and the second gear portion; and a booster compressor coupled to said second gear portion such that said single rotation low-pressure turbine is configured to drive said first fan assembly, said second fan assembly, and said booster compressor and such that said first fan assembly is rotatable in a first rotational direction and said second fan assembly is rotatable in a second rotational direction that is different than the first rotational direction. 8. A counter-rotating fan assembly in accordance with claim 7 wherein said first fan assembly is rotatable at a first rotational speed that is different than a second rotational speed of said second fan assembly and said booster compressor. 9. A counter-rotating fan assembly in accordance with claim 7, wherein the first diameter is less than the second diameter such that said second fan assembly is rotatable at a first rotational speed and such that said booster compressor is rotatable at a second rotational speed that is greater than the first rotational speed. 10. A counter-rotating fan assembly in accordance with claim 7 wherein said sun gear has a diameter that is selected based on a rotational speed of at least one of said first fan assembly, said second fan assembly, and said booster compressor. 11. A counter-rotating fan assembly in accordance with claim 7 wherein said sun gear is intermeshed only with said first gear portion. 12. A counter-rotating fan assembly in accordance with claim 7 wherein said sun gear is intermeshed only with said second gear portion. 13. A turbine engine assembly comprising: a core turbine engine; a single rotation low-pressure turbine coupled to said core turbine engine; a gearbox coupled to said single rotation low-pressure turbine, said gearbox comprising a sun gear and a plurality of planetary gears intermeshed with said sun gear, each of said planetary gears comprising a first gear portion having a first diameter and a second gear portion axially displaced from the first gear portion and having a second diameter that is different than the first diameter; a first fan assembly directly coupled to said single rotation low-pressure turbine so that the first fan assembly is not driven by the gearbox; a second fan assembly coupled to said first gear portion; and the sun gear coupled to one of the first gear portion and the second gear portion; and a booster compressor coupled to said second gear portion such that said single rotation low-pressure turbine is configured to drive said first fan assembly, said second fan assembly, and said booster compressor and such that said first fan assembly is rotatable in a first rotational direction and said second fan assembly is rotatable in a second rotational direction that is different than the first rotational direction. 14. A turbine engine assembly in accordance with claim 13 wherein said first fan assembly is rotatable at a first rotational speed that is different than a second rotational speed of said second fan assembly and said booster compressor. 15. A turbine engine assembly in accordance with claim 13 wherein the first diameter is less than the second diameter such that said second fan assembly is rotatable at a first rotational speed and said booster compressor is rotatable a second rotational speed that is different than the first rotational speed. 16. A turbine engine assembly in accordance with claim 13 wherein said sun gear has a third diameter that is selected based on a rotational speed of at least one of said first fan assembly, said second fan assembly, and said booster compressor. 17. A turbine engine assembly in accordance with claim 13 wherein said sun gear is intermeshed with only one of said first gear portion and said second gear portion.