Method for testing operation of an arresting unit for locking a foldable wing tip portion in an extended position

1. A method comprising a testing operation of an arresting unit for locking a foldable wing tip portion of a wing for an aircraft in an extended position, wherein the wing includes a fixed wing, a foldable wing tip portion mounted to the fixed wing pivotally about an axis of rotation between an extended position and a folded position, an actuation unit configured to actuate movement of the foldable wing tip portion between the extended position and the folded position, and an arresting unit configured to lock the foldable wing tip portion in the extended position, wherein the method includes:

locking the foldable wing tip portion in the extended position by the arresting unit;

controlling the actuation unit to move the foldable wing tip portion in a direction towards the folded position, such that the foldable wing tip portion urges against the arresting unit with a predefined test load,

detecting deformation of the arresting unit during or after application of the test load, and

comparing the detected deformation to the predefined threshold deformation.

2. The method according to claim 1 , wherein deformation of the arresting unit is detected by detecting displacement or movement of the foldable wing tip portion during application of the test load.

3. The method according to claim 1 , wherein deformation of the arresting unit is detected by inspecting the structure of the arresting unit after application of the test load.

4. The method according claim 1 , wherein the test load corresponds to an estimated maximum load occurring at the arresting unit during flight of the aircraft.

5. The method according to claim 1 , wherein the test load corresponds to a maximum load of the actuating unit.

6. The method according to claim 1 , wherein the arresting unit includes at least one latching device comprising a first latching part mounted to the fixed wing and a second latching part mounted to the foldable wing tip portion, wherein the method further includes:

moving the first and second latching parts relative to one another to a latched position at which the foldable wing tip portion is locked in the extended position, and

and thereafter the test load is applied between the first and second latching parts.

7. The method according to claim 6 , wherein the at least one latching device is a plurality of latching devices.

8. The method according to claim 7 , wherein the plurality of latching devices are movable independently from one another between the latched position and an unlatched position.

9. The method according to claim 7 , wherein all of the plurality of latching devices are in the latched position when the arresting unit is loaded with the test load.

10. The method according to claim 8 , wherein only a subset of the plurality of latching devices are in the latched position when the arresting unit is loaded with the test load, while other of the plurality of latching devices remain in in the unlatched position.

11. An aircraft comprising:

a fuselage,

wings mounted to the fuselage, and

a control unit,

wherein each wing includes a fixed wing, a foldable wing tip portion, an actuation unit, and an arresting unit,

wherein the foldable wing tip portion is mounted to the fixed wing pivotally about an axis of rotation between an extended position and a folded position,

wherein the actuation unit is configured for actuating movement of the foldable wing tip portion between the extended position and the folded position,

wherein the arresting unit is configured for locking the foldable wing tip portion in the extended position, and

wherein the control unit is configured to:

control the arresting unit to lock the foldable wing tip portion in the extended position,

control the actuation unit to move the foldable wing tip portion in the direction towards the folded position, such that the foldable wing tip portion urges against the arresting unit with a predefined test load,

detect deformation of the arresting unit during or after application of the test load, and

compare the detected deformation to a predefined threshold deformation.

12. The aircraft according to claim 11 , wherein the control unit comprises a sensor configured to detect deformation of the arresting unit by detecting displacement or movement of the foldable wing tip portion during application of the test load.

13. The aircraft according to claim 11 , wherein the arresting unit comprises a latching device,

wherein the latching device comprises a first latching part mounted to the fixed wing and a second latching part mounted to the foldable wing tip portion,

wherein first and second latching parts move relative to one another between a latched position, where the foldable wing tip portion is locked in the extended position, and an unlatched position, where the foldable wing tip portion is movable out of the extended position, and

wherein the test load is applied between the first and second latching parts.

14. The aircraft according to claim 13 , wherein the arresting unit comprises a plurality of latching devices.

15. The aircraft according to claim 14 , wherein the latching devices are movable independently from one another between the latched position and the unlatched position.

16. A method to test an arresting unit, wherein a wing of an aircraft includes a fixed wing, a foldable wing tip portion pivotably mounted to the fixed wing, an actuation unit configured to move pivot the foldable wing tip portion between an extended position and a folded position, and the arresting unit which is configured to lock the foldable wing tip portion in the extended position, wherein the method includes:

locking the foldable wing tip portion in the extended position by the arresting unit;

controlling the actuation unit to move the foldable wing tip portion towards the folded position, such that the foldable wing tip portion urges against the arresting unit with a predefined test load,

detecting deformation of the arresting unit during or after application of the test load;

comparing the detected deformation to the predefined threshold deformation, and

if the detected deformation exceeds the predefined threshold deformation, issuing a report of excessive deformation.

17. The method of claim 16 further including repairing or replacing the arresting unit if the detected deformation exceeds the predefined threshold deformation.