Surface pre-treatment method for pre-coated heat-treatable, precipitation-hardenable stainless steel ferrous-alloy components and components coated thereby
First Claim
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1. A method for coating a ferrous-alloy aircraft structural component comprising the steps of:
- providing an aircraft structural component made from a ferrous-alloy precursor having a pre-determined treatment temperature;
providing a flash plate pre-treatment;
subjecting the component to the flash plate pre-treatment;
providing a curable organic coating material having a non-volatile portion that is curable at about the pre-determined ferrous-alloy heat-treatment temperature;
applying the coating material to the component; and
substantially simultaneously curing the coating and the component by heat-treating the ferrous-alloy precursor to a pre-determined heat-treatment temperature.
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Abstract
The present invention relates to the use, in a pre-coating process, of a flash plating, without a subsequent chromate seal, as a surface pre-treatment for a ferrous-alloy substrate prior to applying a corrosion-inhibiting coating to improve the overall corrosion protection of the pre-treatment component. Preferably the ferrous alloy is a heat-treatable, precipitation-hardenable stainless steel and the pre-treatement is a cadmium flash plate or a zinc-nickel alloy flash plate.
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Citations
50 Claims
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1. A method for coating a ferrous-alloy aircraft structural component comprising the steps of:
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providing an aircraft structural component made from a ferrous-alloy precursor having a pre-determined treatment temperature;
providing a flash plate pre-treatment;
subjecting the component to the flash plate pre-treatment;
providing a curable organic coating material having a non-volatile portion that is curable at about the pre-determined ferrous-alloy heat-treatment temperature;
applying the coating material to the component; and
substantially simultaneously curing the coating and the component by heat-treating the ferrous-alloy precursor to a pre-determined heat-treatment temperature. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19)
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20. A method for improving the corrosion protection of a ferrous-alloy substrate comprising the steps of:
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providing a ferrous-alloy substrate;
applying to the ferrous-alloy substrate a flash plate pre-treatment without a subsequent chromate seal treatment; and
applying a curable organic coating material having a non-volatile portion that is curable at about a pre-determined heat-treatment temperature of the ferrous alloy. - View Dependent Claims (21, 22)
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23. A corrosion resistant aircraft structural ferrous-alloy component prepared according to a method comprising the steps of:
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providing an aircraft structural component made from a ferrous-alloy precursor having a pre-determined heat-treatment temperature;
providing a flash plate pre-treatment without a subsequent chromate seal;
subjecting the component to the flash plate pre-treatment;
providing a curable organic coating material having a non-volatile portion that is curable at about the pre-determined ferrous-alloy heat-treatment temperature;
applying the organic coating material to the component to form a coated component; and
curing the coated component to a pre-determined temperature. - View Dependent Claims (24, 25, 26, 27)
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28. A ferrous-alloy aircraft structural component comprising:
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a ferrous-alloy precursor having a pre-determined heat-treatment temperature;
a flash plate pre-treatment without a subsequent chromate seal; and
a curable, organic coating made from a material having a non-volatile portion that is curable at about the pre-determined ferrous-alloy heat-treatment temperature, wherein the precursor and the coating are substantially simultaneously heat-treated. - View Dependent Claims (29, 30, 31, 32, 33, 34, 35, 36, 37, 38, 39, 40, 41)
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42. An aircraft comprising a ferrous-alloy aircraft structural component comprising:
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a ferrous-alloy precursor having a pre-determined heat-treatment temperature, said precursor pre-treated with a flash plate pre-treatment deposited to a thickness of from about 0.0002 inch to about 0.0004 inch without a subsequent chromate sealant; and
a curable, organic coating made from a material having a non-volatile portion that is curable at about the pre-determined ferrous-alloy heat-treatment temperature, wherein the precursor and the coating are substantially simultaneously heat-treated. - View Dependent Claims (43, 44, 45, 46, 47, 48, 49, 50)
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Specification