MIL-STD-1822A(USAF)
Assembly Release (MAR). The MAR, or an assurance of a MAR, ACCD, CC, or SOC, is required prior to issuing a Nuclear Compatibility Certification Statement.
5.2.2 Air-launched cruise missiles
5.2.2.1 AMAC system.
The AMAC system will be analyzed and tested to ensure it meets the interface requirements. The results of these analyses and tests will be documented in the AMAC FDAR.
5.2.2.2 Mechanical Interface Control Drawing (MICD).
There is no MICD requirement for cruise missiles. Interface definition is handled by the ICDs with certification compliance documented in the CC.
5.2.2.3 Electrical Interface Control Drawing (EICD).
There is no EICD requirement for cruise missiles. Interface definition is handled by the ICDs with certification compliance documented in the CC.
5.2.2.4 Structural loads analyses and tests.
Joint analyses/tests will be conducted by the missile contractor against requirements specified by the Air Force in cooperation with the DoE and their prime contractors. The analyses/tests will determine the distribution of forces and pressures transmitted to the warhead to determine if the warhead environments are within design limits. The analyses/tests will include ground and flight environments as specified in the STS and MCs. Limitations will be identified and provided for inclusion in the MAR.
5.2.2.5 Environmental fly-around and data.
Support for environmental fly-around tests will be provided. These tests will be conducted by the appropriate Air Force flight test organization and will provide the basic data to demonstrate the warhead compatibility with the carriage/launch environments (thermal, vibration, and acoustic) for aircraft weapon carriage locations. Vibration analyses will be conducted to identify the important frequencies and modes transmitted to the warhead during aircraft carriage and during missile flight. Ground vibration tests of selected configurations may be performed to substantiate the vibration analysis results. In-flight measurements of the thermal, vibration, and acoustic environments will be made for selected carriage locations and flight conditions. Tests will be conducted with special instrumented warheads provided by the DoE through the Air Force.
5.2.2.6 Ejection characteristics.
Ejection characteristic (static drops) tests to assure proper weapon release, ejection velocity, separation, adequate fall-angle clearances, ejection forces and proper lanyard retention under static-level flight conditions prior to in-flight separation tests will be conducted. Test parameters and instrumentation will be jointly determined by the SPO, DoE laboratories, AFNWC/NCS, and contractors. Production or equivalent hardware is required.
5.2.2.7 Separation tests (in-flight).
Separation tests to assure compatibility of the aircraft with the cruise missile will be conducted. The tests will verify proper separation within the aircraft flight envelope to determine the nuclear weapon launch or delivery envelope. Detailed requirements and instrumentation will be jointly determined by the SPO, DoE laboratories, AFNWC/NCS, and contractors. The flight parameters of the drop tests will include specified portions of the aircraft flight envelope with
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