Tail-cone of an aircraft with movable fairing

1. A tail-cone of an aircraft comprising:

a skin whose interior houses an auxiliary power unit (APU) supported by fixing means; wherein the tail-cone has a longitudinal axis, the skin includes an upper half fixed to the tail-cone and a movable fairing which consists of a lower longitudinal section of the skin, a perimeter of said lower longitudinal section mates with a perimeter of said upper half, the upper half being located above the longitudinal axis of the tail-cone and the lower longitudinal section being located below the longitudinal axis of the tail-cone, the upper half always is positioned above the lower longitudinal section relative to the longitudinal axis, the movable fairing being displaceable by a swing articulated mechanism configured to swing the movable fairing from a closed position in which the skin is kept closed housing the APU to an open position in which access is permitted to the APU.

2. The tail-cone of claim 1 , wherein the swing articulated mechanism comprises at least one forward rod and one rear rod, lower ends of the at least one forward rod and one rear rod are articulately joined to the movable fairing and upper ends of the at least one forward rod and one rear rod are joined to an element selected among the inner part of the skin, the fixing means of the APU and a combination of them.

3. The tail-cone of claim 2 , wherein the swing articulated mechanism comprises at least one actuator for an operation selected among a manual operation, an automatic operation and a combination of them; the at least one actuator being selected between pneumatic and hydraulic actuators.

4. The tail-cone of claim 3 , wherein the actuator is coupled to a rod of the swing articulated mechanism, said rod being selected among the forward arm, the rear arm and a combination of both.

5. The tail-cone of claim 4 , wherein the swing articulated mechanism comprises two pairs of rods; one pair of forward rods and one pair of rear rods; and the mechanism includes two actuators.

6. The tail-cone of claim 1 , wherein the longitudinal section of the skin constituting the movable fairing is defined by the lower longitudinal half of said skin.

7. The tail-cone of claim 6 , wherein the swing articulated mechanism comprises two pairs of rods; one pair of forward rods and one pair of rear rods; and the mechanism includes two actuators.

8. The tail-cone of claim 1 , wherein the swing articulated mechanism comprises two pairs of rods; one pair of forward rods and one pair of rear rods; and the mechanism includes two actuators.

9. The tail-cone of claim 1 , further comprising:

blocking means for blocking the movable fairing in the open position.

10. The tail-cone of claim 9 , wherein the blocking means of the movable fairing in the open position comprise at least one rod which is fixed in an articulated way to the inner part of the movable fairing and an other end is fixed to an element selected between the fixing means of the APU and the inner part of the upper skin when the movable fairing is in the open position.

11. The tail-cone of claim 10 , wherein the blocking means of the movable fairing in the open position comprise two rods which are arranged longitudinally and articulately connected to the inner and to the lower part of the movable fairing, so that, when carrying out the opening of the movable fairing, the rods can be opened out and free ends fixed to an element selected between the fixing means of the APU and the inside of the upper skin in the open position of the movable fairing, the two rods forming a “V” shaped arrangement.

12. The tail-cone of claim 1 , wherein the fixing means of the APU present an arrangement supported on a structure selected among a separation structure of a rest of a fuselage, the inner structure of the skin and a combination of both.

13. The tail-cone of claim 1 , further comprising:

means for sealing of a zone of attachment of the movable fairing with the skin and with a rest of a fuselage in the closed position.