Methods for sealing an internal composite vent stringer

Patent metadata

Field	Value
Publication number	US-9725184-B2
Application number	US-201514744005-A
Country	US
Kind code	B2
Filing date	Jun 18, 2015
Priority date	Jun 18, 2015
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

A method of sealing an aircraft wing vent stringer may include placing a movable sealant sled in a vent stringer cavity of an aircraft wing. The sealant sled may include a sealant source configured to apply sealant to a wing portion within the vent stringer. The sealant sled may be transported through the cavity in a longitudinal direction defined by the wing, thereby applying a layer of sealant to the wing. In some cases, vent stringer may be abraded and/or washed before sealing. In some cases, two or more layers of sealant may be applied, one of which may be a secondary fuel barrier.

First claim

What is claimed is:

1. A method of sealing an aircraft wing vent stringer, comprising:
placing a movable first sealant sled in a vent stringer cavity of an aircraft wing, the first sealant sled including a sealant source configured to apply sealant to a wing portion within the vent stringer;
transporting the first sealant sled through the cavity in a longitudinal direction defined by the wing, thereby applying a first layer of sealant to the wing; and
prior to applying the first layer of sealant to the wing:
placing a movable abrasive sled in the vent stringer cavity, the abrasive sled including an abrasive surface configured to abrade the wing portion within the vent stringer; and
transporting the abrasive sled through the cavity in the longitudinal direction and thereby abrading the wing.

2. The method of claim 1 , further comprising, after abrading the wing and prior to applying the first layer of sealant to the wing:
placing a movable wash sled in the vent stringer cavity, the wash sled including a water source configured to wash the wing portion within the vent stringer; and
transporting the wash sled through the vent stringer cavity and thereby washing the wing.

3. A method of sealing an aircraft wing vent stringer, comprising:
placing a movable first sealant sled in a vent stringer cavity of an aircraft wing, the first sealant sled including a sealant source configured to apply sealant to a wing portion within the vent stringer;
transporting the first sealant sled through the cavity in a longitudinal direction defined by the wing, thereby applying a first layer of sealant to the wing; and
after applying the first layer of sealant to the wing:
placing a movable second sealant sled in the vent stringer cavity, the second sealant sled including a sealant source configured to apply sealant over the wing portion within the vent stringer; and
transporting the second sealant sled through the cavity in the longitudinal direction, thereby applying a second layer of sealant on top of the first layer of sealant.

4. The method of claim 3 , wherein the first layer of sealant is a secondary fuel barrier and the second layer of sealant is an electrically insulating sealant.

5. A method of sealing an aircraft wing vent stringer, comprising:
placing a movable first sealant sled in a vent stringer cavity of an aircraft wing, the first sealant sled including a sealant source configured to apply sealant to a wing portion within the vent stringer;
transporting the first sealant sled through the cavity in a longitudinal direction defined by the wing, thereby applying a first layer of sealant to the wing; and
before transporting the first sealant sled through the cavity:
placing a tug mechanism in the vent stringer cavity at a first end of the cavity;
attaching a collection line to the tug mechanism;
transporting the tug mechanism through the cavity in the longitudinal direction until the tug mechanism reaches a second end of the cavity;
while the collection line is located at the second end of the cavity, attaching a pull line to the collection line; and
pulling the collection line back to the first end of the cavity, thereby transporting the pull line to the first end of the cavity.

6. The method of claim 5 , further comprising attaching a task line to the collection line while the collection line is located at the second end of the cavity, and wherein pulling the collection line back to the first end of the cavity includes transporting the task line to the first end of the cavity.

7. The method of claim 6 , wherein the task line is a sealant line configured to transport sealant from a sealant supply reservoir to the first sealant sled.

8. A method of sealing an aircraft wing vent stringer, comprising:
placing a movable first sealant sled in a vent stringer cavity of an aircraft wing, the first sealant sled including a sealant source configured to apply sealant to a wing portion within the vent stringer;
transporting the first sealant sled through the cavity in a longitudinal direction defined by the wing, thereby applying a first layer of sealant to the wing; and
visually inspecting the cavity by transporting an imaging device through the cavity.

9. A method of electrically insulating a portion of an aircraft wing within a vent stringer, comprising:
attaching a wheeled abrasion tool to a pull line that extends along a long dimension of a hollow vent stringer interior, the abrasion tool including an abrasive surface configured to press against a wing skin portion of the vent stringer interior;
pulling the abrasion tool through the vent stringer from one end of the vent stringer to another end of the vent stringer with the pull line, thereby abrading material from an inner surface of the wing skin;
after abrading material from the wing skin, attaching a wheeled first sealant tool to the pull line, the first sealant tool including a source of sealant configured to dispense sealant onto the wing skin; and
pulling the first sealant tool through the vent stringer from one end of the vent stringer to another end of the vent stringer with the pull line, thereby dispensing sealant onto the inner surface of the wing skin.

10. The method of claim 9 , further comprising, before attaching the wheeled abrasion tool to the pull line:
placing a tug mechanism in the vent stringer at a first end of the vent stringer;
attaching a collection line to the tug mechanism;
transporting the tug mechanism through the vent stringer from the first end of the vent stringer to a second end of the vent stringer;
while the collection line is located at the second end of the vent stringer, attaching the pull line to the collection line; and
pulling the collection line back to the first end of the vent stringer, thereby extending the pull line along the long dimension of the hollow vent stringer.

11. The method of claim 10 , further comprising attaching a task line to the collection line while the collection line is located at the second end of the vent stringer, and wherein pulling the collection line back to the first end of the vent stringer includes pulling the task line to the first end of the vent stringer.

12. The method of claim 11 , wherein the task line is a sealant line configured to transport sealant from a sealant supply reservoir to the first sealant tool.

13. The method of claim 10 , further comprising attaching a water line to the collection line while collection line is located at the second end of the vent stringer, and wherein pulling the collection line back to the first end of the vent stringer includes pulling the water line to the first end of the vent stringer.

14. The method of claim 13 , further comprising, after pulling the abrasion tool through the vent stringer and prior to pulling the first sealant tool through the vent stringer,
attaching a wash tool to the water line, the wash tool configured to wash the wing skin portion of the vent stringer interior; and
pulling the wash tool through the vent stringer, thereby washing the wing.

15. The method of claim 10 , further comprising visually inspecting the vent stringer interior by attaching an imaging device to either of the collection line or the pull line and pulling the imaging device through the vent stringer.

16. The method of claim 9 , further comprising, after pulling the first sealant tool through the vent stringer,
attaching a wheeled second sealant tool to the pull line, the second sealant tool including a source of sealant configured to dispense sealant over the wing skin; and
pulling the second sealant tool thr

Assignees

• Boeing Co

Inventors

• Best Iii Donald Joe

Classifications

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B29C65/00

  Joining {or sealing} of preformed parts {, e.g. welding of plastics materials}; Apparatus therefor {(general aspects of processes or apparatus for joining preformed parts B29C66/00; using porous material formed by internal pressure generated therein for joining preformed parts B29C44/1228, B29C44/326)} · CPC title

• B05D3/12

  by mechanical means · CPC title

• B64C3/182

  Stringers, longerons · CPC title

• B64F5/45

  Repairing leakages in fuel tanks · CPC title