Abstract: An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover.

Abstract: A system for dissipating a lightning current produced by a thunderstorm discharge on an avionic equipment installed on the external skin of an aircraft, the external skin being made of a composite material covered with a layer of expanded metal and including an orifice in which there is positioned an aerodynamic plate covering the avionic equipment. The aerodynamic plate is attached to the external skin by a doubler. The system includes at least one metal plate at least partially surrounding the aerodynamic plate and mounted so as to ensure electrical continuity between the doubler and the layer of expanded metal so as to dissipate the lightning current into the layer of expanded metal.

Abstract: A system for spraying liquid (100) for a windshield (111) of an aircraft including a spray-liquid supply circuit (101), a pressurized-gas supply circuit (102) designed to purge the spray-liquid supply circuit, and at least one nozzle (114) disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on a windshield, characterized in that the system includes an auxiliary means of compression (107) ready to compress gas designed to circulate in the pressurized-gas supply circuit, the auxiliary means of compression being positioned near the nozzle. Also, an aircraft cockpit provided with at least such a spray system.

Abstract: An aircraft including a cabin, on at least one wall of which are attached first portions of plural multisystem connection devices, each device including a male portion or plug and a female portion or socket capable of fitting into each other. Each male and female portion includes: a first mechanism connecting to a liquid or gas supply of the aircraft; and a second mechanism connecting to a supply of electricity and/or electric signals of the aircraft.

Abstract: A system for dissipating a lightning current produced by a thunderstorm discharge on an avionic equipment installed on the external skin of an aircraft, the external skin being made of a composite material covered with a layer of expanded metal and including an orifice in which there is positioned an aerodynamic plate covering the avionic equipment. The aerodynamic plate is attached to the external skin by a doubler. The system includes at least one metal plate at least partially surrounding the aerodynamic plate and mounted so as to ensure electrical continuity between the doubler and the layer of expanded metal so as to dissipate the lightning current into the layer of expanded metal.

Abstract: A support for holding a cable harness capable of being attached to a structure to hold the aforementioned harness in position and orientation with respect to the aforementioned structure. The aforementioned support comprises means of positioning and holding the harness close to means of connecting the support to the structure and rails that extend on either side of the means, substantially in the direction in which the harness must be held. Each rail is attached to the aforementioned first means at one end and free at the other end.

Abstract: An aircraft including a cabin, on at least one wall of which are attached first portions of plural multisystem connection devices, each device including a male portion or plug and a female portion or socket capable of fitting into each other. Each male and female portion includes: a first mechanism connecting to a liquid or gas supply of the aircraft; and a second mechanism connecting to a supply of electricity and/or electric signals of the aircraft.

Abstract: A system for spraying liquid for a windshield of an aircraft includes a spray-liquid supply circuit, a pressurized-gas supply circuit designed to purge the spray-liquid supply circuit, and at least one nozzle disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on an aircraft windshield, wherein the system includes a control device able to simultaneously actuate the temporary spraying of spray liquid and of pressurized gas respectively in the spray-liquid spraying circuit and in the pressurized-gas spray circuit in such a way that a pressurized-gas spraying time is strictly greater than a spraying-liquid spraying time. For example, the control device includes a time-lag relay controlling the pressurized-gas supply circuit.

Abstract: A system for spraying liquid for a windshield of an aircraft includes a spray-liquid supply circuit, a pressurized-gas supply circuit designed to purge the spray-liquid supply circuit, and at least one nozzle disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on an aircraft windshield, wherein the system includes a control device able to simultaneously actuate the temporary spraying of spray liquid and of pressurized gas respectively in the spray-liquid spraying circuit and in the pressurized-gas spray circuit in such a way that a pressurized-gas spraying time is strictly greater than a spraying-liquid spraying time. For example, the control device includes a time-lag relay controlling the pressurized-gas supply circuit.

Abstract: A system for spraying liquid (100) for a windshield (111) of an aircraft including a spray-liquid supply circuit (101), a pressurized-gas supply circuit (102) designed to purge the spray-liquid supply circuit, and at least one nozzle (114) disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on a windshield, characterized in that the system includes an auxiliary means of compression (107) ready to compress gas designed to circulate in the pressurized-gas supply circuit, the auxiliary means of compression being positioned near the nozzle. Also, an aircraft cockpit provided with at least such a spray system.