Abstract: A method electrically connects by crimping electrical conductors in a connector for equipotential connection of a planar and flexible layer formed by the conductors, to metal components. The method includes positioning the electrical conductors in individual longitudinal and parallel cells which are formed between two planar walls of the connector, crimping the conductors crimped in a crimping zone by simultaneous transverse punching of at least one wall of the connector, and forming by the transverse punching at least one corresponding transverse groove line on the at least one connector wall and, by load transfer, on each of the conductors to electrically connect the conductors.

Abstract: A connection which is reproducible, uniform and reliable both for intermediate and terminal connections of a conductor layer wiring loom, by making provision for simultaneous crimping of the conductors in connectors by applying continuous and uniform pressure in a crimping zone. The crimping is carried out by a tool including two shells, each shell including a main wall that forms an inner face including transverse ribs and end edges folded over perpendicularly relative to the walls to define an inner space. In the inner space, a connector of non-insulated conductors arranged perpendicularly relative to the ribs is introduced to form transverse grooves by compression of the ribs on the walls of the connector. The tool can find use in current return networks of aircraft passenger cabins having composite skin.

Abstract: The object of the invention is to produce equipotential connections that are electrically efficient in terms of resistivity between portions of a current-return network in a non-conductive architecture, such as an airplane fuselage. The approach adopted by the invention is to impart an equipotential-bonding function to an aluminum cable having a large cross section, said bond being electrically connected, via direct contact, to as many devices as is physically possible to connect thereby. According to one embodiment, an electrical connection assembly of an aircraft fuselage (100) having a composite skin comprises in-line shunt connections (2) for electrically interconnecting an aluminum-alloy-based cable (1) of large cross section acting as an equipotential connection to brackets (113, 141) for primary current-return networks and to brackets (111) for electrical devices via connectors (202).

Abstract: The terminal for electrical connection includes a pin (2) with a recess (9), partially filled with a contact grease, to accommodate the end of an electric cable (22) and including a crimping section (5) designed to be radially deformed and further includes a stopper (15) to retain the grease (14) in the recess (9). The stopper has a transverse membrane (16) designed to be broken by the electric cable (22) on insertion thereof into the recess (9) and at least one portion arranged in the crimping section (5) such that the stopper (15) leads to the sealing of the connection after crimping. The grease (14) is arranged between the base (12) of the recess (9) and the membrane (16). The assembly method includes the step of breaking the transverse membrane (16) by element of the end of the electric cable (22) on insertion thereof in the recess (9).