Methods of applying a rapid cure sealant to an aircraft surface
Applicant discloses a novel method of spray applying multiple courses of a rapid cure, two part polymer sealant to an aircraft surface. The method sometimes uses a two part polymer mix for use in the aircraft industry that is applied with pneumatic mix and spray gun. The two part cartridge is used in the mix and spray gun so the mix is applied immediately upon mixing, but the two components are kept separated unless the gun is applying the mix. The multiple courses cure to form a clear sealant that allows for inspection of cracks and corrosion beneath the sealant. It cures quickly so that the coated part may be further processed, for example in the assembly line during aircraft build. Applicant further discloses multiple spray gun systems for applying such a two-part polymer mix to aircraft parts.
1. A method for sealing a surface of an aircraft part, the method comprising the steps of:
selecting a two component polymer sealant that will cure in less than 24 hours at 75° F. and will be clear upon curing to a peel strength of between 0.5 and 35 piw, 90-degree peel back;
providing a system having a spray tip for combining the two components and immediately emitting from the spray tip an atomized spray comprising the combined components;
applying to a painted or primed aluminum alloy aircraft part a first course of polymer sealant to a thickness of between 1 and 30 mil; and,
applying a subsequent course at room temperature, to the first course, within 2.5 hours or less of applying the first course to a thickness of between 1 and 30 mil.
2. The method of claim 1 wherein the applying steps are performed at a distance within 6-12″ from the aircraft part, measured from where the atomized spray is emitted.
3. The method of claim 1 further including the step of adjusting an air or fluid flow in the system.
4. The method of claim 1 further involving the step of adjusting, during the applying steps, a speed of the spray tip as it moves with respect to the aircraft part so as to control the thickness of the polymer sealant.
5. The method of claim 1 further including the step of determining, prior to applying, whether the surface of the aircraft has received a polymer sealant.
6. The method of claim 1 wherein the system of the providing step includes a cartridge with the two polymer components and a mixing straw.
7. The method of claim 1 wherein the polymer sealant of the selecting step is free of Volatile Organic Components (VOC).
8. The method of claim 1 wherein the polymer sealant of the selecting step passes the 12-second vertical burn test.
9. The method of claim 1 wherein the polymer sealant of the selecting step is resistant to degradation by Jet A fuel.
10. The method of claim 1 wherein the polymer sealant of the selecting step undergoes a color change while curing.
11. A method for sealing a surface of an aircraft part, the method comprising the steps of:
selecting a two component polymer sealant that will cure in less than 24 hours at 75° F. and will be clear upon curing to a peel strength between 0.5 and 35 piw, 90-degree peel back;
providing a system having a spray tip for combining the two components and immediately emitting from the spray tip an atomized spray comprising the combined components;
applying to a painted or primed aluminum alloy aircraft part a first course of polymer sealant to a thickness of between 1 and 30 mil;
applying a subsequent course at room temperature, to the first course, within 2.5 hours or less of applying the first course to a thickness of between 1 and 30 mil;
wherein the polymer sealant is free of Volatile Organic Components (VOC);
wherein the polymer sealant passes the 12-second vertical burn test; and,
wherein the polymer sealant is resistant to degradation by Jet A fuel.
12. The method of claim 11 further comprising the step of determining, prior to applying, whether the surface of the aircraft has received a polymer sealant.
13. A method for sealing a surface of an aircraft part, the method comprising the steps of:
selecting a two component polymer sealant that will cure in less than 24 hours at 75° F. and will be clear upon curing to a peel strength between 0.5 and 35 piw, 90-degree peel back;
providing a system having a spray tip for combining the two components and immediately emitting from the spray tip an atomized spray comprising the combined components;
applying to a painted or primed aluminum alloy aircraft part a first course of polymer sealant to a thickness of between 1 and 30 mil;
applying a subsequent course at room temperature, to the first course, within 2.5 hours or less of applying the first course to a thickness of between 1 and 30 mil;
wherein the polymer sealant is free of Volatile Organic Components (VOC);
wherein the polymer sealant passes the 12-second vertical burn test;
wherein the polymer sealant is resistant to degradation by Jet A fuel; and,
wherein the system of the providing step includes a cartridge with the two polymer components and a mixing straw.
14. A method for sealing a surface of an aircraft part, the method comprising the steps of:
selecting a two component polymer sealant that will cure in less than 24 hours at 75° F. and will be clear upon curing to a peel strength between 0.5 and 35 piw, 90-degree peel back;
providing a system having a spray tip for combining the two components and immediately emitting from the spray tip an atomized spray comprising the combined components;
applying to a painted or primed aluminum alloy aircraft part a first course of polymer sealant to a thickness of between 1 and 30 mil; and,
applying a subsequent course at room temperature, to the first course, within 2.5 hours or less of applying the first course to a thickness of between 1 and 30 mil;
wherein the applying steps are performed at a distance within 6-12″ from the aircraft part, measured from where the atomized spray is emitted;
further including the step of adjusting an air or fluid flow in the system; and,
further involving the step of adjusting, during the applying steps, a speed of the spray tip as it moves with respect to the aircraft part so as to control the thickness of the polymer sealant.
15. The method of claim 14 further comprising the step of determining, prior to applying, whether the surface of the aircraft has received a polymer sealant.
16. The method of claim 1 wherein aluminum alloy aircraft part of the applying step is selected from the following group: chemical toilets, under-lavatories, lavatory pans, aircraft interiors, forward or aft entry doors, shear plates, the top of floorboards, any area where chaffing may occur and between faying surface.
17. The method of claim 1 wherein the polymer sealant of the selecting step has a cured hardness of 20-80 Shore A.