MIL-STD-1530C(USAF)
5.1.3 Structural design criteria.
Detailed structural design criteria for the specific aircraft shall be established in accordance with the requirements of the applicable contracts. These shall include design criteria for loads, dynamics, strength, durability, damage tolerance, and mass properties.
5.1.3.1 Loads criteria.
Criteria shall be established such that all critical limit load conditions are developed. These limit loads are those which can result from authorized ground and flight usage of the aircraft including maintenance activity, system failures from which recovery is expected, and those that occur within the design service life. Ultimate loads for the aircraft shall be obtained by multiplying the limit loads by the appropriate factor of safety.
5.1.3.2 Dynamics criteria.
Criteria shall be established to ensure the aircraft in all configurations including store carriage is free from flutter, whirl flutter, divergence, and other related aeroelastic or aeroservoelastic instabilities for all combinations of altitude and speed within the approved flight envelope by the required airspeed margin of safety. Criteria shall be established such that the aircraft structure can withstand the aeroacoustic loads
and vibrations due to aerodynamic and mechanical excitations throughout the design service life.
5.1.3.3 Strength criteria.
Criteria shall be established to ensure the aircraft structure has adequate strength capability. This capability requires that, for the design environments, no detrimental deformation or damage occurs at
115-percent design limit loads and no structural failure occurs at design ultimate loads.
5.1.3.4 Durability criteria.
Criteria shall be established to ensure the aircraft structure can achieve the design service life and that in- service maintenance is economically viable. In addition, durability criteria shall be established to ensure the aircraft structure can achieve the damage tolerance criteria described in 5.1.3.5. Durability criteria apply to all airframe structural components and shall include criteria that pertain to the onset of WFD as described in 5.1.3.4.1 and economic life as described in 5.1.3.4.2.
5.1.3.4.1 Onset of WFD.
Criteria shall be established to ensure the onset of WFD does not occur within the design service life of the aircraft structure. The onset of WFD is the end of the service life for the affected component. Full- scale durability testing described in 5.3.4 shall demonstrate that the onset of WFD occurs at a time equal to or greater than the design service life by the specified margin.
5.1.3.4.2 Economic life.
Additional criteria shall be established to ensure the aircraft structure's economic life as defined in 3.12 is greater than the design service life by the specified margin. This shall be demonstrated by the full-scale durability test described in 5.3.4.
5.1.3.5 Damage tolerance criteria.
Criteria shall be established to ensure the aircraft structure can safely withstand undetected flaws, corrosion, impact damage, and other types of damage throughout its design service life. The damage tolerance criteria shall be applied to all safety-of-flight structure and other selected structure. Criteria shall consider establishment of a minimum critical flaw size for those locations which are difficult to inspect. The damage tolerance evaluation criteria for rotary-wing aircraft dynamic components are addressed in 5.1.3.5.2.
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