Patent ID: 7655320

Claim:
A corrosion resistant aircraft structural ferrous-alloy component prepared according to a method comprising the steps of: 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 without a subsequent chromate seal, wherein subjecting the component to the flash plate pre-treatment thereby provides a pre-treated surface on the component; 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 following the flash plate pre-treatment and without a chromate seal to form a coated component, wherein the curable organic coating material is applied directly onto the pre-treated surface provided by the flash plate pre-treatment; and curing the coated component to the pre-determined temperature, wherein the organic coating applied to the ferrous alloy precursor and the ferrous alloy precursor are heat-treated substantially simultaneously.