Fatigue Critical Baseline Strucure
Fatigue Critical Baseline Strucure
(OP)
Can anyone tell me if "safe life" parts show up in FCBS listings or are these limited to "damage tolerant structure"?
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Fatigue Critical Baseline Strucure
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RE: Fatigue Critical Baseline Strucure
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RE: Fatigue Critical Baseline Strucure
Damage Tolerance assumes an initial flaw and does not take credit for any durability life prior to crack formation. The design service life is determined by crack growth analyses in conjunction with planned inspection intervals. The point of damage tolerance is that no flaw should be able to grow from it's minimum inspectable size to critical within one inspection interval. Some aircraft designed under damage tolerance may still have some safe-life-designed parts (often landing gear).
That's a long explanation to get to the point that any fatigue critical baseline structure should be identified in the list, regardless of the design paradigm of the aircraft.
Let me know if any of that doesn't make sense and I'll try to elaborate.
SuperStress
RE: Fatigue Critical Baseline Strucure
RE: Fatigue Critical Baseline Strucure
Different manufacturers may have different arrangements with the FAA though, and it can vary drastically based on the certification date of the aircraft as well.
RE: Fatigue Critical Baseline Strucure
certainly, the primary intent of part 26 is DTA; i think that part 26 only exists 'cause the FAA did a lousy job implementing 25.571 in the 1st place. but a change to an U/C would have to consider the impact on fatigue, no? if you want it is implicitly FCBS.
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