Electrical power distribution assembly for an aircraft

1. An airplane comprising:

an electrical power distribution assembly for an airplane, the electrical power distribution assembly comprising

a primary electric switch device located in a Kaman fairing of the airplane, the Karman fairing including an aerodynamic bulge situated at a junction between a wing of the airplane and a fuselage of the airplane, an interior volume of the Karman fairing being not pressurized, the primary electric switch device receiving power from a jet of the airplane via a first cable, the primary electric switch including contactors and a circuit breaker and providing power to a first load provided in proximity to the wing of the airplane, and

a secondary electric switch device disposed in the fuselage of the airplane and electrically connected to the primary electric switch device via a second cable so as to receive power from the primary electric switch device, the secondary electric switch device including a circuit breaker and providing power to a second load provided in the fuselage of the airplane,

wherein a venturi tube causes air to leak from the cabin into the Karman fairing so that a temperature inside the Karman fairing does not drop below a threshold temperature,

wherein a grid made of electrically conductive material is positioned so as to reduce an electromagnetic field in the Karman fairing, and

wherein the contactors of the primary electric switch device are reinforced and proof against water runoff.

2. The airplane according to claim 1 , wherein the primary electric switch device is adapted to perform primary distribution of electrical power from its generation to consumer devices.

3. The airplane according to claim 1 , wherein the secondary electric switch device is placed in a rear hold triangle of the airplane.

4. The airplane according to claim 3 , wherein the second cable is longer than the first cable.

5. The airplane according to claim 1 , wherein the secondary electric switch device is placed at a front of the airplane.

6. The airplane according to claim 5 , wherein the second cable is longer than the first cable.

7. The airplane according to claim 1 , wherein the primary electric switch device is located in a top Karman fairing.

8. The airplane according to claim 1 , wherein the primary electric switch device is located in a bottom Karman fairing.

9. The airplane according to claim 1 , wherein a portion of the venturi tube is provided on the Karman fairing.

10. A method of putting electrical power distribution into place in an airplane comprising:

placing a primary electric switch device in a Karman fairing of the airplane, the Karman fairing including an aerodynamic bulge situated at a junction between a wing of the airplane and a fuselage of the airplane, an interior volume of the Karman fairing being not pressurized, the primary electric switch device receiving power from a jet of the airplane via a first cable, the primary electric switch including contactors and a circuit breaker and providing power to a first load provided in proximity to the wing of the airplane, the contactors of the primary electric switch device being reinforced and proof against water runoff;

placing a secondary electric switch device in the fuselage of the airplane, the second electric switch device being electrically connected to the primary electric switch device via a second cable so as to receive power from the primary electric switch device, the secondary electric switch device including a circuit breaker and providing power to a second load provided in the fuselage of the airplane;

providing a venturi tube which causes air to leak from the cabin into the Karman fairing so that a temperature inside the Karman fairing does not drop below a threshold temperature; and

positioning a grid made of electrically conductive material so as to reduce an electromagnetic field in the Karman fairing.

11. The method according to claim 10 ,

wherein the secondary electric switch device is placed in a rear hold triangle of the airplane,

and

wherein the second cable is longer than the first cable.

12. The method according to claim 10 ,

wherein the secondary electric switch device is placed in a front of the airplane,

and

wherein the second cable is longer than the first cable.

13. The method according to claim 10 , wherein a portion of the venturi tube is provided on the Karman fairing.