KirbyWan
Aerospace
- Apr 18, 2008
- 585
Howdy all,
I dug around trying to find an old discussion about this topic and could not find it, but was able find the FAR (25.625) that mentions it.
From my understanding, when I design a repair I add a fitting factor of 1.15 so that my repair has to be at least 15% stronger then what broke. I do not need this added fitting factor if there are multiple load paths, i.e. more then 5 fastners, but I can not find a reference for this.
Could anyone point me to a discussion of substantiating repairs and the use of fitting factors? Could engineers experienced in the repair of aircraft talk about how they design repairs? I would like to avoid a discussion of damage tolerance to simplify the discussion and because I usually work on secondary structure.
Thanks,
-Kirby
Kirby Wilkerson
Remember, first define the problem, then solve it.
I dug around trying to find an old discussion about this topic and could not find it, but was able find the FAR (25.625) that mentions it.
From my understanding, when I design a repair I add a fitting factor of 1.15 so that my repair has to be at least 15% stronger then what broke. I do not need this added fitting factor if there are multiple load paths, i.e. more then 5 fastners, but I can not find a reference for this.
Could anyone point me to a discussion of substantiating repairs and the use of fitting factors? Could engineers experienced in the repair of aircraft talk about how they design repairs? I would like to avoid a discussion of damage tolerance to simplify the discussion and because I usually work on secondary structure.
Thanks,
-Kirby
Kirby Wilkerson
Remember, first define the problem, then solve it.