A device for fabricating a section of an aircraft via automated composite lamination on a mandrel surface of a tool, the device comprising: a tool comprising a rotational axis and a mandrel surface; a mechanical supporting structure moveable relative to the mandrel, wherein the tool is rotatable relative to said mechanical supporting structure; a plurality of material delivery heads supported by said mechanical supporting structure; said mechanical supporting structure comprises a ring surrounding said mandrel surface and said device further comprises a ring cradle, wherein said ring cradle supports said ring, and said ring cradle moves along the direction of the rotational axis of the tool; the device further comprises a plurality of arm mechanisms, each arm mechanism connecting one of the plurality of material delivery heads to said mechanical supporting structure and providing motion of the connected material delivery head relative to the mandrel surface in a direction normal to the mandrel surface; and wherein the circumferential position of each material delivery head is adjustable in a hoop direction relative to the mandrel surface, and wherein the axial position of each material delivery head is adjustable relative to the mandrel surface; and characterised in that: the mandrel surface conforms to the section of an aircraft fuselage; each arm mechanism provides: the circumferential position adjustment of the connected material delivery head in the hoop direction relative to the mandrel surface, the axial position adjustment of the connected material delivery head relative to the mandrel surface, and a rotation of the connected material delivery head relative to the mandrel surface about an axis normal to the mandrel surface; each of said plurality of material delivery heads is arranged to be controlled by a computer numerical control application: to control the plurality of material delivery heads simultaneously to apply composite material along the mandrel surface during fabrication of the section of the aircraft fuselage, and to adjust the position of each of the plurality of material delivery heads individually relative to the mandrel surface and the other material delivery heads during application of the composite material by the material heads during fabrication of the section of the aircraft fuselage. a tool comprising a rotational axis and a mandrel surface; a mechanical supporting structure moveable relative to the mandrel, wherein the tool is rotatable relative to said mechanical supporting structure; a plurality of material delivery heads supported by said mechanical supporting structure; said mechanical supporting structure comprises a ring surrounding said mandrel surface and said device further comprises a ring cradle, wherein said ring cradle supports said ring, and said ring cradle moves along the direction of the rotational axis of the tool; the device further comprises a plurality of arm mechanisms, each arm mechanism connecting one of the plurality of material delivery heads to said mechanical supporting structure and providing motion of the connected material delivery head relative to the mandrel surface in a direction normal to the mandrel surface; and wherein the circumferential position of each material delivery head is adjustable in a hoop direction relative to the mandrel surface, and wherein the axial position of each material delivery head is adjustable relative to the mandrel surface; the mandrel surface conforms to the section of an aircraft fuselage; each arm mechanism provides: the circumferential position adjustment of the connected material delivery head in the hoop direction relative to the mandrel surface, the axial position adjustment of the connected material delivery head relative to the mandrel surface, and a rotation of the connected material delivery head relative to the mandrel surface about an axis normal to the mandrel surface; the circumferential position adjustment of the connected material delivery head in the hoop direction relative to the mandrel surface, the axial position adjustment of the connected material delivery head relative to the mandrel surface, and a rotation of the connected material delivery head relative to the mandrel surface about an axis normal to the mandrel surface; each of said plurality of material delivery heads is arranged to be controlled by a computer numerical control application: to control the plurality of material delivery heads simultaneously to apply composite material along the mandrel surface during fabrication of the section of the aircraft fuselage, and to adjust the position of each of the plurality of material delivery heads individually relative to the mandrel surface and the other material delivery heads during application of the composite material by the material heads during fabrication of the section of the aircraft fuselage. to control the plurality of material delivery heads simultaneously to apply composite material along the mandrel surface during fabrication of the section of the aircraft fuselage, and to adjust the position of each of the plurality of material delivery heads individually relative to the mandrel surface and the other material delivery heads during application of the composite material by the material heads during fabrication of the section of the aircraft fuselage.