MIL-STD-1530C(USAF)
5.3.3 Flight tests.
Flight tests shall be conducted on a fully-instrumented aircraft. An additional aircraft, sufficiently late in the production program to ensure obtainment of the final configuration, shall be the backup aircraft for these flight tests and shall be instrumented similarly to the primary test aircraft. These tests shall include dynamic response, flutter, and aeroacoustic and vibration tests, as well as a flight and ground loads survey.
5.3.3.1 Flight and ground loads survey.
The flight and ground loads survey program shall consist of an instrumented and calibrated aircraft operated within and to the extremes of its limit structural design envelope to measure the resulting loads and, if appropriate, to also measure pertinent temperature profiles on the aircraft structure. Load measurements shall be made in a build-up fashion by the strain gage or pressure survey methods commensurate with the state-of-the-art, usually installed during production buildup. The objectives of the loads survey are to:
a. verify the structural loads and thermal analyses used in the design of the aircraft structure;
b. evaluate loading conditions which produce the critical structural load and temperature distribution; and
c. determine and define suspected new critical loading conditions which may be indicated by the investigations of structural flight conditions within the design-limit envelope.
5.3.3.2 Dynamic response tests.
The dynamic response tests shall consist of an instrumented and calibrated aircraft operated to measure the structural loads and inputs while flown through atmospheric turbulence; and during taxi, takeoff, towing, landing, refueling, store ejection, etc. The objectives shall be to obtain flight verification and evaluation of the elastic response characteristics of the structure to these dynamic load inputs.
5.3.3.3 Flutter tests.
Flight flutter tests shall be conducted to verify the aircraft structure is free from aeroelastic instabilities and has satisfactory damping throughout the operational flight envelope. Test aircraft should have sufficient instrumentation installed and acceptable methods of in-flight excitation shall be used to determine the frequency and amount of damping of the primary modes of interest at each flight test condition. The tests shall be performed with test data taken at predetermined test points, defined by Mach number and altitude, in a prescribed order of ascending criticality. For aircraft with a flight control augmentation system, flight aeroservoelastic stability tests shall be conducted in conjunction with flight flutter testing.
5.3.3.4 Aeroacoustic tests.
The aeroacoustic environments shall be measured on a full-scale aircraft to verify the acoustic loads/environment used in the sonic fatigue analysis. Measurements of sound pressure levels shall be made of those areas determined to be sonic-fatigue critical. Sufficient instrumentation shall be in place for both flight and ground operations which produce the significant aeroacoustic loads.
5.3.3.5 Vibration tests.
Flight vibration tests shall be conducted to verify and correct analysis of the vibration environment. Measurements shall be made at a sufficient number of locations to define the vibration characteristics of the aircraft structure with the test results being the basis for equipment environmental requirements. In addition, the test results shall be used to demonstrate that vibration control measures are adequate to
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