MIL-STD-1530 Aircraft Structural Integrity Program AsipThis standard describes the USAF Aircraft Structural Integrity Program ASIP which defines the requirements necessary to achieve structural integrity in USAF aircraft while managing cost and schedule risks through a series of disciplined, time-phased tasks. It provides direction to government personnel and contractors engaged in the development, production, modification, acquisition, and/or sustainment of USAF aircraft.

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MIL-STD-1530C(USAF)

5.3.2    First flight verification ground tests.

The following verification tests shall be conducted prior to first flight.

5.3.2.1    Mass properties tests.

Mass properties tests shall be conducted to verify the aircraft weight and balance are as predicted and within limits for all design conditions.

5.3.2.2    Functional proof tests.

Functional proof tests shall be conducted to design limit load to demonstrate the functionality of flight- critical structural systems, mechanisms, and components whose correct operation is necessary for safe flight.  These tests shall demonstrate the deformation requirements have been met.

5.3.2.3    Pressure proof tests.

Each pressurized compartment of each pressurized flight aircraft shall be pressure proof tested to the maximum pressure limit loads.  These proof tests shall demonstrate that deformation requirements have been met and shall validate the accuracy of the strength predictive methods.

5.3.2.4    Strength proof tests.

Strength proof tests of selected aircraft structural components and systems (e.g., flight control surfaces, hydraulic systems, etc.) shall be conducted when the full-scale static test schedule does not allow for adequate testing prior to first flight, when the full-scale test will not adequately demonstrate strength capability, or when flight restrictions to limit these component loads may be difficult to achieve without unreasonably restricting the aircraft.

5.3.2.5    Control surface rigidity and free-play tests.

Control surface rigidity and free-play tests shall be conducted to verify the flutter analysis as well as to ensure safe free-play limits.  These tests should be conducted prior to ground vibration tests and should be conducted for both design failure and normal conditions.  If mass balancing of controls surfaces is used to prevent any aeroelastic instability, stiffness tests of the mass balance attachments shall be conducted.  In addition, the mass and inertia of the control surfaces shall be measured in support of the flutter analysis and to verify the mass property analysis.

5.3.2.6    Ground vibration tests.

Ground vibration tests shall be conducted to verify the natural frequencies, mode shapes, and structural damping of the aircraft.  Test results are to be correlated against the structural model used in all aeroelastic analyses.  Consideration of the aircraft supporting system is required to ensure rigid body modes of the aircraft do not interfere with the capture of aircraft elastic modes.  To allow for changes in

the structural models, component ground vibrations tests shall be conducted prior to aircraft assembly and well in advance of full-scale aircraft tests.

5.3.2.7    Aeroservoelastic tests.

Aeroservoelastic ground tests to include open-loop transfer (frequency response) tests and closed-loop coupling (structural resonance) tests shall be conducted to correlate and verify the aeroservoelastic analysis.

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