A tube support structure for an aircraft, which is intended to support a tube arranged so as to extend in an X direction inside an aircraft, the tube support structure comprising: a parallel movement mechanism configured to support the tube and to allow movement of the tube in parallel; and an angle adjustment mechanism configured to support the tube and to allow an angle of the tube to be adjusted; wherein the parallel movement mechanism includes: an eccentric sleeve, through which the tube can pass, configured to adjust a position of the tube in a Z direction perpendicular to the X direction, and a Y direction adjustment mechanism configured to adjust a position of the eccentric sleeve in a Y direction perpendicular to the X direction and the Z direction, wherein the angle adjustment mechanism includes: a first member having a first curved surface and configured to support the eccentric sleeve, and a second member configured to be joined to a structure body of the aircraft and having a second curved surface with a shape corresponding to that of the first curved surface which is configured to have sliding contact with the first curved surface at the second curved surface, and to support the first member by the second curved surface, wherein each of the first curved surface and the second curved surface has a shape along an outer circumference surface of an imaginary cylinder with a central axis toward the Y direction and is formed such that a cross-sectional shape of the first curved surface and the second curved surface in an XZ plane is a circular arc shape, and wherein the angle of the tube can be adjusted by sliding the first curved surface with respect to the second curved surface. a parallel movement mechanism configured to support the tube and to allow movement of the tube in parallel; and an angle adjustment mechanism configured to support the tube and to allow an angle of the tube to be adjusted; wherein the parallel movement mechanism includes: an eccentric sleeve, through which the tube can pass, configured to adjust a position of the tube in a Z direction perpendicular to the X direction, and a Y direction adjustment mechanism configured to adjust a position of the eccentric sleeve in a Y direction perpendicular to the X direction and the Z direction, wherein the angle adjustment mechanism includes: a first member having a first curved surface and configured to support the eccentric sleeve, and a second member configured to be joined to a structure body of the aircraft and having a second curved surface with a shape corresponding to that of the first curved surface which is configured to have sliding contact with the first curved surface at the second curved surface, and to support the first member by the second curved surface, wherein each of the first curved surface and the second curved surface has a shape along an outer circumference surface of an imaginary cylinder with a central axis toward the Y direction and is formed such that a cross-sectional shape of the first curved surface and the second curved surface in an XZ plane is a circular arc shape, and wherein the angle of the tube can be adjusted by sliding the first curved surface with respect to the second curved surface. an eccentric sleeve, through which the tube can pass, configured to adjust a position of the tube in a Z direction perpendicular to the X direction, and a Y direction adjustment mechanism configured to adjust a position of the eccentric sleeve in a Y direction perpendicular to the X direction and the Z direction, wherein the angle adjustment mechanism includes: a first member having a first curved surface and configured to support the eccentric sleeve, and a second member configured to be joined to a structure body of the aircraft and having a second curved surface with a shape corresponding to that of the first curved surface which is configured to have sliding contact with the first curved surface at the second curved surface, and to support the first member by the second curved surface, wherein each of the first curved surface and the second curved surface has a shape along an outer circumference surface of an imaginary cylinder with a central axis toward the Y direction and is formed such that a cross-sectional shape of the first curved surface and the second curved surface in an XZ plane is a circular arc shape, and wherein the angle of the tube can be adjusted by sliding the first curved surface with respect to the second curved surface. a first member having a first curved surface and configured to support the eccentric sleeve, and a second member configured to be joined to a structure body of the aircraft and having a second curved surface with a shape corresponding to that of the first curved surface which is configured to have sliding contact with the first curved surface at the second curved surface, and to support the first member by the second curved surface, wherein each of the first curved surface and the second curved surface has a shape along an outer circumference surface of an imaginary cylinder with a central axis toward the Y direction and is formed such that a cross-sectional shape of the first curved surface and the second curved surface in an XZ plane is a circular arc shape, and wherein the angle of the tube can be adjusted by sliding the first curved surface with respect to the second curved surface.