Method of inspecting aircraft

• US 20060186260A1
• Filed: 02/18/2005
• Published: 08/24/2006
• Est. Priority Date: 02/18/2005
• Status: Abandoned Application

• Current Assignee: American Airlines Incorporated (American Airlines Group Incorporated)
• Original Assignee: American Airlines Incorporated (American Airlines Group Incorporated)
• Inventors: Doughty, Parker J., Magnuson, Gregory A.
• Application Number:
  US11/061,077
• Publication Number:
  US 20060186260A1
• Time in Patent Office: Days
• US Class Current: 244/1.R
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

A method of inspecting aircraft for evidence of stress fracture and other external abnormalities comprising: (a) identifying an aircraft surface to be inspected; (b) determining if the surface to be inspected is visually impeded by a coating compound selected from the group of compounds including paint, topcoats, and primers; (c) if present removing all visually impeding compounds identified in (b); (d) inspect the aircraft surface identified in (a); (e) identify and procure adhesive tape patch with properties generally consistent to those demonstrated in 3M product 8681 HS Polyurethane Protective Tape; and, (f) applying the adhesive patch of (e) over the inspected aircraft surface.

Claims

1. A method of inspecting aircraft for evidence of stress fracture and other external abnormalities comprising:

(a) identifying an aircraft surface to be inspected;

(b) determining if the surface to be inspected is visually impeded by a coating compound selected from the group of compounds including paint, topcoats, and primers;

(c) if present removing all visually impeding compounds identified in (b);

(d) inspect the aircraft surface identified in (a);

(e) identify and procure adhesive tape patch with properties generally consistent to those demonstrated in 3M product 8681 HS Polyurethane Protective Tape; and

,

(f) applying the adhesive patch of (e) over the inspected aircraft surface.

2. The method of claim 1 further comprising the verifying the presence of cadmium plating in the area of the surface to be inspected.

3. The method of claim 1 wherein applying the adhesive patch further comprises the attachment of the patch to an airplane surface via an adhesive edge tape in simultaneous communication with one or more external surface portions of the adhesive patch and an airplane surface.

4. The method of claim 1 further comprising application of a corrosion inhibiting compound over the inspected surface area, subsequent to inspection and in advance of applying the adhesive patch.

5. The method of claim 1 wherein the inspection of the aircraft surface further comprises performing a fluorescent dye penetrant inspection.

6. The method of claim 1 wherein the inspection of the aircraft surface further comprises performing a fluorescent magnetic particle inspection.

7. The method of claim 1 wherein the inspection of the aircraft surface further comprises performing a fluorescent dye penetrant inspection and a fluorescent magnetic particle inspection.

8. The method of claim 1 wherein the inspection of the airplane surface is selected from the group of inspection processes including, visual, eddy, current, ultrasonic, and radiographic inspection processes.

12. The method of claim 1 wherein the aircraft surface to be inspected is identified on a Boeing 737 aircraft.

13. The method of claim 1 wherein the aircraft surface to be inspected is identified on a Boeing 757 aircraft.

14. The method of claim 1 wherein the aircraft surface to be inspected is identified on a Boeing 767 aircraft.

18. The method of claim 1 wherein the surface to be inspected is a surface identified on an aircraft selected from the group of aircraft including:

Canadair CL-600

Embraer ERJ-135, -145, -170, -175, -190

Boeing 707, 717, 727, 737, 747, 757, 767, 777, 787

McDonnell-Douglas DC-8, DC-9, DC-10, MD-80, MD-11, MD-90;

Airbus A300, A310, A318, A319, A320, A321, A330, A340, A380; and

Fokker F70, F100 aircraft.

20. The method of claim 1 further comprising the removal of an adhesive tape patch with properties generally consistent to those demonstrated in 3M product 8681 HS Polyurethane Protective Tape prior to inspecting the aircraft surface.

22. The method of claim 1 wherein the inspection of the airplane surface is selected from the group of inspection processes including, visual, eddy, current, ultrasonic, and radiographic inspection processes.

9. A method of inspecting aircraft for evidence of stress fracture and other external abnormalities comprising:

(a) identify an aircraft surface to be inspected;

(b) determine if the surface to be inspected is visually impeded by a coating compound selected from the group of compounds including paint, topcoats, and primers;

(c) if present removing all visually impeding compounds identified in (b);

(d) verify the presence of cadmium plating in the area of the surface to be inspected;

(e) perform a fluorescent dye penetrant inspection and a fluorescent magnetic particle inspection of the aircraft surface identified in (a);

(f) identify and procure adhesive tape patch with properties generally consistent to those demonstrated in 3M product 8681 HS Polyurethane Protective Tape;

(g) apply a corrosion inhibiting compound over the inspected surface area, subsequent to the surface'"'"'s inspection;

(h) apply the adhesive patch of (f) over the inspected aircraft surface and corrosion inhibiting compound.

10. The method of claim 9 further comprising verifying the presence of cadmium plating in the area of the surface to be inspected.

11. The method of claim 9 wherein applying the adhesive patch further comprises the attachment of the patch to an airplane surface via an adhesive tape in simultaneous communication with one or more external surface portions of the adhesive patch and an airplane surface.

15. The method of claim 9 wherein the aircraft surface to be inspected is identified on a Boeing 737 aircraft.

16. The method of claim 9 wherein the aircraft surface to be inspected is identified on a Boeing 757 aircraft.

17. The method of claim 9 wherein the aircraft surface to be inspected is identified on a Boeing 767 aircraft.

19. The method of claim 9 wherein the surface to be inspected is a surface identified on an aircraft selected from the group of aircraft including:

Canadair CL-600;

Embraer ERJ-135, -145, -170, -175, -190;

Boeing 707, 717, 727, 737, 747, 757, 767, 777, 787;

McDonnell-Douglas DC-8, DC-9, DC-10, MD-80, MD-11, MD-90;

Airbus A300, A310, A318, A319, A320, A321, A330, A340, A380; and

Fokker F70, F100 aircraft.

21. The method of claim 9 further comprising the removal of an adhesive tape patch with properties generally consistent to those demonstrated in 3M product 8681 HS Polyurethane Protective Tape prior to inspecting the aircraft surface.