MIL-STD-1796A(USAF)
1) Mechanical. Characteristics such as allowable circuit board deflection, sizes, and configurations for anticipated vibration and shock levels, defect sizes, fatigue and fracture characteristics of the materials.
2) Thermal. The allowable stress or strains for temperature, temperature cycles and manufacturing and repair processes.
3) Chemical. The allowable degradation caused by various moisture and corrosive environments and by material couples.
4) Electrical. The allowable power dissipation, electrical stress, static discharge, voltage fluctuation, tolerance limits, and electrical parts/connectors derating considerations.
5.2.3 Characterizing environment.
The contractor shall assemble system level environmental data and document the environment that each subsystem will experience. This is generally documented in an environmental criteria document that defines the environment in the various zones of an aircraft (typically documented at the weapon system level, and provided to the subsystems).
5.2.4 Characterizing materials and components.
The contractor shall characterize the durability and reliability of materials and components that are to be used in the design. Where possible, this should make use of data available from existing designs used in similar applications. Studies, analysis and testing should be performed for any new or unproven devices. Parts which may become obsolete or difficult to support within the life of the system shall be identified. Initial identification, risks and potential mitigations to use of lead-free electronics shall be addressed.
The contractor shall analyze the system risks and criticalities, and determine which electronics shall be subject to Parts Integrity management and verification. The results of this analysis shall be subject to procuring activity approval. The contractor shall define the processes used to prevent and manage Parts Integrity risks. Risks shall be addressed.
5.2.5 Identification and tracking of critical items/critical functions.
The contractor shall assess each avionics system/subsystem which contributes to performance of a critical function to determine its level of criticality. The contractor shall assign corresponding levels of environmental and life verification and establish criteria for when verification must be complete, using TABLE II for guidance and providing rationale for any deviations from the table.
5.2.6 Analysis.
The contractor shall perform a FMECA at the system level to identify any failure modes that require mitigation in the final design. The contractor shall complete preliminary analysis to determine the effects of the environments on the avionics.
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