IP Library › Granted Patent US 7,800,884
Granted Patent B2
US 7,800,884 · App. 12/008,987 · Granted Sep 21, 2010

Protective device against electrical discharges in fixing elements

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Quick Facts
Patent No.
US 7,800,884
App. No.
12/008,987
Granted
Sep 21, 2010
Kind
B2
Abstract

The invention relates to a device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft, comprising a cap ( 2 ) made of non-conductive material and a washer ( 3 ) made of non-conductive material insulating the fixing element ( 4 ) from electrical discharges, said cap being an open receptacle with a cylindrical shape closed at one of its ends and open at the other end, comprising at the lower part of its inner face a thread ( 15 ), the washer ( 3 ) being retained by the fixing element ( 4 ), said washer ( 3 ) having a thread ( 5 ) on its outer face coupling with the complementary thread ( 15 ) in the lower area of the inner face of the cap ( 2 ), relative movements between the washer ( 3 ) and the cap ( 2 ) being prevented.

Claims (9)

1. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft characterized in that the device ( 1 ) comprises a cap ( 2 ) made of non-conductive material and a washer ( 3 ) made of non-conductive material insulating the fixing element ( 4 ) from electrical discharges, the washer ( 3 ) being retained by the fixing element ( 4 ), said washer ( 3 ) having a thread ( 5 ) on its outer face coupling with a complementary thread ( 15 ) in the lower area of the inner face of the cap ( 2 ), relative movements between the washer ( 3 ) and the cap ( 2 ) being prevented.

2. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 1 , characterized in that the thread ( 5 , 15 ) has automatic locking properties, to thus prevent the cap ( 2 ) and the washer ( 3 ) from being separated during the operation of the aircraft.

3. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 1 , characterized in that the cap ( 2 ) comprises a recess ( 6 ) at the upper part of its outer face for facilitating the installation of the mentioned cap ( 2 ) with conventional tools during the application of the installation tightening torque.

4. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 1 , characterized in that the cap ( 2 ) is made of dielectric material.

5. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 4 , characterized in that the cap ( 2 ) is made of nylon.

6. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 4 , characterized in that the cap ( 2 ) is made of high-strength plastic.

7. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 1 , characterized in that the washer ( 3 ) is made of dielectric material.

8. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 7 , characterized in that the washer ( 3 ) is made of nylon.

9. A device ( 1 ) for the protection against electrical discharges of a conductive fixing element ( 4 ) of an aircraft according to claim 7 , characterized in that the washer ( 3 ) is made of high-strength plastic.