MIL-STD-1530C(USAF)
data and generate analysis test data shall be formulated and performed for new materials and those existing materials for which there are insufficient data available. The variability in material properties shall be considered when material and joint allowables are established.
5.2.2 Loads analysis.
Loads analysis shall determine the magnitude and distribution of significant static and dynamic loads which the aircraft structure may encounter when operated within the envelope established by the structural design criteria. This analysis consists of a determination of the flight loads, ground loads, powerplant loads, control system loads, and weapon effects. When applicable, this analysis shall include the effects of temperature, aeroelasticity, and dynamic response of the aircraft structure.
5.2.3 Design service loads spectra.
Design service loads spectra shall be developed to establish the distribution, frequency, and sequencing of loadings that the aircraft structure will experience based on the design service life and usage. The design service loads spectra and chemical/thermal environment spectra as defined in 5.2.4 shall be used to develop flight-by-flight stress/environment spectra, as appropriate, to support the analyses and tests described herein.
5.2.4 Design chemical/thermal environment spectra.
Design chemical/thermal environmental spectra shall be developed to establish the intensity, duration, frequency of occurrence, etc., of the environment which the aircraft structure will experience based on the design service life and usage.
5.2.5 Stress analysis.
A stress analysis shall include the analytical determination of the internal loads, stresses, strains, deformations, and margins-of-safety which result from the external loads and environments imposed on the aircraft structure. In addition to verification of strength, the stress analysis shall be used as a basis for durability and damage-tolerance analyses, selection of critical structural components for design development tests, material review actions, and selection of loading conditions to be used in the structural strength tests. The stress analysis shall be used as the basis to determine the adequacy of structural changes throughout the life of the aircraft and to determine the adequacy of the structure for new loading conditions which result from increased performance or new mission requirements. The stress analysis shall be revised to reflect any major changes to the aircraft structure or to the loading conditions applied
to the aircraft structure.
5.2.6 Damage tolerance analysis.
Damage tolerance analysis shall be conducted to substantiate the ability of the structural components to comply with the detail requirements for damage tolerance. The design flight-by-flight stress/environment spectra based on the requirements of 5.2.3 and 5.2.4 shall be used in the damage growth analysis and verification tests. The calculations of critical flaw sizes, residual strengths, safe damage growth periods, and inspection intervals shall be based on existing fracture test data and basic fracture allowables data generated as a part of the design development test program.
5.2.7 Durability analysis.
Durability analysis shall be conducted to substantiate the ability of the structure to comply with the detail requirements for durability. The design flight-by-flight stress/environment spectra based on the requirements of 5.2.3 and 5.2.4 shall be used in the durability analysis and verification tests. Durability analysis shall be performed for all airframe structural components and shall include analysis that pertains to the onset of WFD as described in 5.2.7.1 and economic life as described in 5.2.7.2.
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