Fatigue justification of a thread bolt

[Claudio_F84]

Hello everybody,
for an urgent repair on an Airbus airplane, the designer creater a doubler of steel, connected to the aluminium fitting through two bolts.
I need to justify the threads for the bolt and the aluminium fitting taking in account shear and tension load simultenously.
Now, I do not find any method that takes in account both of them but only pure tension or pure shear and ISAMI as well does not have any module for that.

Do you have any method to suggest? I need to reach 2000 FC to start the repair action.

Thanks and best regards,

 

[SWComposites]

1) suggest you delete and repost in the Aircraft Engineering forum
2) can you show a sketch of the joint?
3) is the bolt threaded into the fitting? (I hope not) or a thru bolt with proper nut/collar on it?