Access panel(s) for an inner nacelle of a turbine engine

1. An assembly for a turbine engine with an axial centerline, the assembly comprising:

an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;

the inner nacelle including a nacelle wall, at least one first access panel adapted to at least partially cover a first aperture in the nacelle wall, and at least one second access panel adapted to at least partially cover a second aperture in the nacelle wall;

wherein the outer nacelle axially overlaps the access panel;

wherein the first access panel extends circumferentially to a top panel side, and the first access panel is hinged to the nacelle wall at the top panel side; and

wherein the second access panel extends circumferentially to a bottom panel side, and the second access panel is hinged to the nacelle wall at the bottom panel side.

2. The assembly of claim 1 , further comprising:

a bifurcation extending radially between the outer nacelle and the inner nacelle;

wherein the outer nacelle, the inner nacelle and the bifurcation form an O-duct through which the bypass flowpath axially extends.

3. The assembly of claim 1 , wherein the nacelle wall has an outer surface that extends axially along and at least three hundred and twenty degrees around the centerline.

4. The assembly of claim 1 , wherein

the nacelle wall extends axially along the centerline; and

the first aperture extends axially within and radially through the nacelle wall.

5. The assembly of claim 1 , wherein

the nacelle wall extends axially along the centerline; and

the first aperture extends circumferentially within and radially through the nacelle wall.

6. An assembly for a turbine engine with an axial centerline, the assembly comprising:

an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;

the inner nacelle including a nacelle wall and an access panel adapted to at least partially cover an aperture in the nacelle wall;

wherein the outer nacelle includes a thrust reverser cascade that axially overlaps the access panel;

wherein the outer nacelle axially overlaps the access panel; and

wherein the access panel is removably fastened to the nacelle wall.

7. The assembly of claim 1 , further comprising a third access panel attached to the nacelle wall, the third access panel adapted to at least partially cover a third aperture in the nacelle wall, wherein the third access panel extends circumferentially to a panel side, and the third access panel is hinged to the nacelle wall at the panel side.

8. The assembly of claim 1 , wherein

the outer nacelle includes a sleeve adapted to move axially between a forward position and an aft position; and

the sleeve axially overlaps the access panel in the forward position.

9. The assembly of claim 8 , wherein the first aperture in the inner nacelle is substantially axially aligned with an aperture in the outer nacelle that extends axially between a fixed portion of the outer nacelle and the sleeve in the aft position.

10. The assembly of claim 1 , wherein the outer nacelle includes a thrust reverser cascade that axially overlaps the access panel.

11. An assembly for a turbine engine with an axial centerline, the assembly comprising:

an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;

the inner nacelle including a nacelle wall, a first access panel adapted to at least partially cover a first aperture in the nacelle wall, and a second access panel adapted to at least partially cover a second aperture in the nacelle wall;

wherein the first access panel is on a first side of the nacelle and is configured to slide to at least partially expose the first aperture;

wherein the second access panel is on a second side of the nacelle, which is opposite the first side of the nacelle, and is configured to slide to at least partially expose the second aperture; and

wherein the outer nacelle axially overlaps the first aperture and the second aperture.