Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.

Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.

Abstract: A method and a device for detecting an edge glow phenomenon in a composite panel, including at least one cable for introducing current into the said composite panel, at least one current return cable, at least one insulating panel bracketed to the composite panel, and means for detecting an edge glow on an outer surface of the said composite panel.

Abstract: In the method of electrically characterizing a composite material for manufacturing an aircraft, the following steps are performed: compressing two spacers against at least one test piece made of a composite material; determining an electrical resistance value for the assembly formed by the spacers and the test piece; and deducing from said value a value for the electrical resistance of the composite material.

Abstract: The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part.

Abstract: A method and a device for detecting an edge glow phenomenon in a composite panel, including at least one cable for introducing current into the said composite panel, at least one current return cable, at least one insulating panel bracketed to the composite panel, and means for detecting an edge glow on an outer surface of the said composite panel.

Abstract: The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part.

Abstract: In the method of electrically characterizing a composite material for manufacturing an aircraft, the following steps are performed: compressing two spacers against at least one test piece made of a composite material; determining an electrical resistance value for the assembly formed by the spacers and the test piece; and deducing from said value a value for the electrical resistance of the composite material.