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1. (WO2019041030) LATCH ASSEMBLY FOR AIRCRAFT MONUMENT
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CLAIMS

1. A latch assembly for selectively preventing a relative movement between first and second components of an aircraft cabin monument, the latch assembly comprising: a latch configured for connection to the first component, the latch having a first connection member; and

a striker plate configured for connection to the second component, the striker plate having a second connection member complementary to the first connection member and selectively engageable with the first connection member;

wherein the engaged latch and striker plate in use are subjected to a load having a use threshold value determined based on a movable mass of the monument and on accelerations generated by predetermined flight conditions, and having a decompression threshold value determined based on decompression pressure conditions;

wherein the striker plate is designed to have a predetermined first failure load corresponding to a value of the load upon failure of the striker plate when the first engagement member is subjected to the load, the first failure load being higher than the use threshold value and lower than the decompression threshold value; and

wherein the latch has a second failure load corresponding to a value of the load upon failure of the latch when the second engagement member is subjected to the load, the second failure load being higher than the use threshold value and higher than the decompression threshold value.

2. The latch assembly as defined in claim 1 , wherein the striker plate has an opening defined therethrough, the striker plate including at least one zone of weakness adjacent the opening, the at least one zone of weakness determining the first failure load.

3. The latch assembly as defined in claim 2, wherein the first connection member of the latch is a latch bolt movable with respect to a housing of the latch, and the second connection member of the striker plate has the opening defined therethrough, the latch bolt engageable within the opening.

The latch assembly as defined in claim 2, wherein the opening in the striker plate is configured for receiving a fastener for connecting the striker plate to the second component of the monument.

The latch assembly as defined in claim 2, wherein the opening is defined adjacent an edge of the striker plate, the striker plate including an edge portion extending between the edge and the opening, the at least one zone of weakness including two spaced apart zones of weakness defined at opposed ends of the edge portion.

The latch assembly as defined in claim 6, wherein each of the two spaced apart zones of weakness is defined by a notch in the striker plate, each notch extending from the opening to the edge of the striker plate.

The latch assembly as defined in claim 2, wherein the at least one zone of weakness includes a portion of the striker plate having a thickness smaller than a thickness of a remainder of the striker plate.

The latch assembly as defined in claim 2, wherein the at least one zone of weakness includes a portion of the striker plate having a cross-sectional area smaller than a cross-sectional area of a remainder of the striker plate, the cross-sectional areas being defined in a plane containing a thickness of the striker plate.

A latch assembly for selectively preventing a relative movement between first and second components of an aircraft cabin monument, the latch assembly comprising: a latch configured for connection to the first component, the latch having a housing and a latch bolt movable with respect to the housing; and a striker plate configured for connection to the second component, the striker plate having an opening defined therethrough, the latch bolt selectively receivable and engageable within the opening;

wherein each of the latch and striker plate has a respective failure load with respect to a load transferred to the latch and striker plate when the latch bolt is engaged in the opening and the first and second components are forced away from each other;

wherein the striker plate has at least one zone of weakness designed to determine the failure load of the striker plate; and

wherein the failure load of the striker plate is smaller than the failure load of the latch.

10. The latch assembly as defined in claim 9, wherein the opening is defined adjacent an edge of the striker plate, the striker plate including an edge portion extending between the edge and the opening, the at least one zone of weakness being adjacent the opening.

11. The latch assembly as defined in claim 10, wherein the at least one zone of weakness includes two spaced apart zones of weakness defined at opposed ends of the edge portion.

12. The latch assembly as defined in claim 10, wherein each of the two spaced apart zones of weakness is defined by a notch in the striker plate, each notch extending from the opening to the edge of the striker plate.

13. The latch assembly as defined in claim 9, wherein the at least one zone of weakness includes a portion of the striker plate having a thickness smaller than a thickness of a remainder of the striker plate.

14. The latch assembly as defined in claim 9, wherein the at least one zone of weakness includes a portion of the striker plate having a cross-sectional area smaller than a cross-sectional area of a remainder of the striker plate, the cross- sectional areas being defined in a plane containing a thickness of the striker plate.

15. A method of tailoring a failure of a latch assembly selectively preventing a relative movement between first and second components of an aircraft cabin monument, the method comprising:

determining a use threshold value of a load applied to the latch assembly during predetermined flight conditions based on a movable mass of the monument and on accelerations generated by the predetermined flight conditions;

determining a decompression threshold value of the load applied to the latch assembly based on decompression pressure conditions;

selecting a latch of the latch assembly for connection to the first component of the monument, the latch being selected to have a failure load higher than the use threshold value and higher than the decompression threshold value; and

configuring a striker plate of the latch assembly for connection to the second component of the monument and for selectively engaging the latch, the striker plate being configured to have a failure load higher than the use threshold value and lower than the decompression threshold value.

16. The method as defined in claim 15, wherein the striker plate has an opening defined therethrough, and configuring the striker plate includes defining at least one zone of weakness adjacent the opening, the at least one zone of weakness determining the failure load of the striker plate.

17. The method as defined in claim 16, wherein the opening in the striker plate is configured to receive and engage a latch bolt of the latch.

18. The method as defined in claim 16, wherein the opening in the striker plate is configured for receiving a fastener connecting the striker plate to the second component of the monument.

19. The method as defined in claim 15, wherein the striker plate has an opening defined therethrough, and configuring the striker plate includes defining two spaced apart zones of weakness adjacent the opening, the zones of weakness designed to determine the failure load of the striker plate.

20. The method as defined in claim 16, wherein defining the at least one zone of weakness includes reducing a thickness of a portion of the striker plate.

21. The method as defined in claim 16, wherein defining the at least one zone of weakness includes reducing a thickness of a cross-sectional area of a portion of the striker plate, the cross-sectional areas being defined in a plane containing a thickness of the striker plate.