Locking apparatus for a service access in an external structure of an aircraft, service access, aircraft and method for producing a locking apparatus for a service access in an external structure of an aircraft

Patent metadata

Field	Value
Publication number	US-2026070650-A1
Application number	US-202519323457-A
Country	US
Kind code	A1
Filing date	Sep 9, 2025
Priority date	Sep 12, 2024
Publication date	Mar 12, 2026
Grant date	—

Abstract

A locking apparatus for a service access in an external structure of an aircraft. A service access includes a locking apparatus of this kind, and an aircraft having a service access of this kind. A method includes producing a locking apparatus for a service access in an external structure of an aircraft.

First claim

1 . A locking apparatus for a service access in an external structure of an aircraft, the locking apparatus comprising:
a base structure for fixed attachment in an opening of a service access in an external structure, wherein the base structure has a through opening, which extends along a longitudinal axis; a covering device, which is supported to be movable along the longitudinal axis in the through opening and relative to the base structure, wherein the covering device is preloaded by a spring device and is held in a closure position by a stop in interaction with the spring device; and an actuating shaft, which extends along the longitudinal axis, has a handling end region for rotational handling by a tool, and a transmission end region for transmitting a torque to a lever unit coupled to the transmission end region, wherein the handling end region is surrounded by the covering device, and wherein the handling end region and the covering device are arranged with their surfaces flush in respect of a respective outer side.

2 . The locking apparatus according to claim 1 , wherein the covering device is movable axially along the longitudinal axis relative to the actuating shaft by a pressure force, such that the covering device is in a manipulation position, in which the handling end region is freely accessible.

3 . The locking apparatus according to claim 1 , wherein, when considered in cross section, the covering device is round or circular in relation to the longitudinal axis.

4 . The locking apparatus according to claim 1 , further comprising a housing, which is arranged on an inner side of the service access and rotatably supports the actuating shaft.

5 . The locking apparatus according to claim 1 , wherein the spring device is a compression spring, or is a conical compression spring.

6 . The locking apparatus according to claim 1 , wherein the stop is screwed to the covering device by a threaded joint, wherein the closure position can be adjusted along the longitudinal axis by the threaded joint.

7 . The locking apparatus according to claim 1 , wherein the base structure is a bush.

8 . The locking apparatus according to claim 1 , wherein the transmission end region is coupled to a lever unit.

9 . A service access for an aircraft, the service access comprising:
a portion of an external structure of an aircraft which can be removed nondestructively, wherein the portion has an opening; and the locking apparatus according to claim 1 , wherein the base structure is attached in a fixed manner in the opening.

10 . An aircraft comprising the service access according to claim 9 .

11 . A method for producing the locking apparatus of claim 1 , the method comprising:
attaching a base structure in an opening of a service access in an external structure, wherein the base structure has a through opening, which extends along a longitudinal axis; inserting a spring device into the base structure, wherein the spring device is preloaded and held in position by placement of a covering device, wherein the covering device is supported to be movable along the longitudinal axis in the through opening and relative to the base structure; connecting a stop to the covering device, such that the covering device is held in a closure position by the spring device in interaction with the stop; and fitting an actuating shaft, which extends along the longitudinal axis, has a handling end region for rotational handling by a tool, and a transmission end region for transmitting a torque to a lever unit coupled to the transmission end region, wherein the handling end region is surrounded by the covering device, and wherein the handling end region and the covering device are arranged with their surfaces flush in respect of a respective outer side.

12 . The method according to claim 11 , wherein, during the fitting of the actuating shaft, a housing is installed on an inner side of the service access and the actuating shaft is pushed in through a feed hole in the covering device.

13 . The method according to claim 11 , wherein the actuating shaft is pushed through a sliding bearing bush of the housing until a first retention ring pre-installed on the actuating shaft comes into contact with the sliding bearing bush.

14 . The method according to claim 11 , further comprising adjusting the closure position to minimize a step between the covering device and the handling end region or between the covering device and the base structure in relation to the respective outer side, wherein the closure position is adjusted along the longitudinal axis by a threaded joint.

15 . The method according to claim 11 , further comprising coupling the transmission end region to a lever unit.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Reinisch Christian
• Peters Sebastian

Classifications

• E05B35/008

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