MIL-STD-1530C(USAF)
3.8 Damage tolerance.
Damage tolerance is the attribute of a structure that permits it to retain its required residual strength for a period of unrepaired usage after the structure has sustained specific levels of fatigue, corrosion, accidental, and/or discrete source damage.
3.9 Design loads/environment spectrum.
The design loads/environment spectrum is the spectrum of external loads and environments (chemical, thermal, etc.) used in the design of the aircraft and is representative of the spectrum that the typical force aircraft is expected to encounter within the design service life.
3.10 Design service life.
The design service life is the period of time (e.g., years, flight cycles, hours, landings, etc.) established at design, during which the structure is expected to maintain its structural integrity when flown to the design loads/environment spectrum.
3.11 Durability.
Durability is the ability of the aircraft structure to resist cracking, corrosion, thermal degradation, delamination, wear, and the effects of foreign object damage for a prescribed period of time.
3.12 Economic life.
The economic life is the period during which it is more cost-effective to maintain and repair an aircraft than to replace it. Economic life can be applied on a component, aircraft, or force basis.
3.13 Equivalent flight hours.
Equivalent flight hours are the actual flight hours accumulated by an aircraft adjusted for the actual usage severity compared to the design spectrum or to the baseline spectrum.
3.14 Equivalent initial flaw size (EIFS) distribution.
The equivalent initial flaw size distribution is a characterization of the initial quality of the aircraft structure. The EIFS distribution is derived by analytically determining the initial flaw size distribution that must be used to obtain the measured flaw size distribution discovered following exposure to the test or actual usage stress spectra.
3.15 Fail-safe structure.
A fail-safe structure is a structure that retains its required residual strength for a period of unrepaired usage after the failure or partial failure of safety-of-flight structure.
3.16 Fracture-critical part.
As shown on figure 1, a fracture-critical part is a safety-of-flight structural component that is not single load path nor sized by durability or damage tolerance requirements but requires special emphasis due to the criticality of the component.
3.17 Fracture-critical traceable part.
As shown on figure 1, a fracture-critical traceable part is a safety-of-flight structural component that is either single load path or sized by durability or damage tolerance requirements.
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