Aircraft Type	Default Vibration Profiles	Notes Regarding Default Vibration Profiles
Fixed Wing Jet Aircraft	Method 514, Table 514.8 D-I	As stated in Method 514, Annex D, default vibration profiles for fixed wing jet aircraft are based on empirical data and time compression information is unknown. The vibration profile should be computed for each segment of the mission profile. Functional vibration tests should be conducted at the amplitudes computed from Table 514.8-D-I for sufficient time to fully verify equipment functionality.
Fixed Wing Propeller Aircraft	Method 514, Tables 514.8 D-II	As stated in Method 514, Annex D, Paragraph 2.2d, default functional test vibration levels for fixed wing propeller aircraft can be derived by scaling the endurance ASD levels described in Table 514.8D-II.
Helicopters	Method 514, Tables 514.8D-III	As stated in Method 514, Annex D, Paragraph 2.3e(4), default functional test vibration levels for helicopters can be derived by scaling the endurance levels described in Table 514.8D-III.