MIL-STD-1530C(USAF)
5.2.13 Survivability analysis.
Survivability analysis shall be conducted to ensure the aircraft structure can perform effectively in a combat environment.
5.2.13.1 Vulnerability analysis.
Vulnerability analysis shall be conducted to verify that the aircraft structure can withstand the operational loads after being damaged by specific threats.
5.2.13.2 Weapons effects analysis.
Weapons effects analysis shall be conducted to ensure the aircraft structure can withstand the loads due to thermal transients, overpressure, and gust associated with weapon detonation. Nuclear weapons effects analysis shall be conducted to determine the capability envelope for the aircraft structure and crew radiation protection for the specified range of variations of weapon delivery trajectories, weapon size, aircraft escape maneuvers, and the resulting damage limits.
5.2.14 Design development tests.
Design development tests shall be conducted to establish material, process, and joint allowables; to verify analysis methods and procedures; to obtain early evaluation of allowable stress levels, material selection, fastener systems, and the effect of the design chemical/thermal environment spectra; to establish aeroelastic and loads characteristics through wind tunnel tests; and to obtain early evaluation of the strength, durability, fatigue (sonic and vibratory), and damage tolerance capabilities of critical structural components and assemblies. Examples of design development tests are tests of coupons; small elements; splices and joints; panels; fittings; control system components and structural operating mechanisms; and major components such as wing carry through, horizontal tail spindles, wing pivots, and assemblies thereof. The plans shall consist of information such as rationale for selection of scope of tests; description of test articles, procedures, test loads and test duration; and analysis directed at the establishment of cost and schedule trade-offs used to develop the program.
5.2.14.1 Duration of durability tests.
Durability testing shall determine initial estimates of the onset of WFD and of the equivalent initial flaw size (EIFS) distribution.
5.2.14.2 Corrosion tests.
Corrosion testing shall be conducted to evaluate the effectiveness of the corrosion protection system to meet design service life requirements for the defined service environments. For corrosion protection system effectiveness, comparative tests on representative structure (including fasteners and dissimilar material contacts) shall be used to evaluate corrosion protection system choices. The comparative tests shall include corrosion protection systems used on legacy aircraft to ensure the new corrosion protection system provides adequate corrosion protection and to provide insight into the degree the new systems will protect aircraft.
5.2.15 Production NDI capability assessment.
The capability of nondestructive inspection processes used for production process monitoring and quality control of structural component shall be established to mitigate risk of missing defects. Special emphasis shall be given to fracture- and mission-critical parts. Capability demonstration of production NDI processes shall be addressed within the NDI Program.
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