Assembly for an aircraft, said assembly having a pylon and a reservoir containing an extinguishing agent
An assembly having a pylon with two side walls provided with apertures, a reservoir for extinguishing agent, a support which has two support elements, wherein each support element has an upwardly facing first bearing face to which the reservoir is fastened, a distal end, and a proximal end fastened by a first removable fastener, wherein the distal end is rotatable about a horizontal axis, and wherein each support element is movable between a use position, in which the first bearing face is horizontal, and a fitted position, in which the first bearing face is tilted downwards.
1 . An assembly for an aircraft, said assembly comprising:
a pylon extending along a longitudinal direction and having a chassis and two side walls disposed on either side of the chassis, each provided with an aperture, and,
at least one reservoir, which has fastening means and is configured to contain an extinguishing agent,
for each reservoir, a support which has two support elements and is offset along the longitudinal direction with respect to said apertures, wherein each support element has an upwardly facing first bearing face against which the fastening means bear, wherein each support element has a proximal end at said apertures and a distal end on an opposite side to said apertures, wherein each proximal end is fastened to the chassis by at least one first fastening means which is configured to provide removable fastening of said proximal end, wherein each distal end is mounted on the chassis rotatably about a horizontal axis of rotation perpendicular to the longitudinal direction, and wherein each support element is configured to be moved between a use position, in which the associated first bearing face is horizontal, and a fitted position, in which the associated first bearing face is tilted downwards,
for each reservoir and for each support element, fastening elements which fasten the fastening means of said reservoir to said support element.
2 . The assembly according to claim 1 , further comprising, for each support element, a stop against which said support element bears in the fitted position.
3 . The assembly according to claim 1 , wherein each first bearing face comprises at least one step arranged such that, in the fitted position, a fastening means is located to the rear of a step in relation to a descending direction of the first bearing face.
4 . The assembly according to claim 1 , wherein each first fastening means, at the proximal end, comprises a bolt having a first nut fastened to the chassis and a first clamping screw which is screwed in the first nut through a first bore in the associated support element.
5 . An aircraft comprising:
the assembly according to claim 1 .
6 . The assembly according to claim 4 , wherein a screw head of each first clamping screw is configured to be accessed from an inside of the chassis between the two support elements.
7 . The assembly according to claim 1 , wherein each support element is configured to be rotated by a fitting of a second fastening means which comprises, at the distal end, a bolt having a second nut fastened to the chassis and a second clamping screw screwed in the second nut through a second bore in said support element.
8 . The assembly according to claim 7 , wherein in that a screw head of each second clamping screw is accessible from an inside of the chassis between the two support elements.
9 . The assembly according to claim 7 , further comprising, at the distal end of each support element, a first fastening means having a bolt with a first nut fastened to the chassis and a first clamping screw which is screwed in the first nut through a first bore in the associated support element.
10 . The assembly according to claim 9 , wherein, at each distal end, the first fastening means is disposed below the second fastening means.