Downloaded from https://www.everyspec.com MIL-STD-81OC c. For the UD and down directions, the increase shal1 be as follows for fuselage loca;ions: A Gp = d%, whereAGp = Additional acceleration due to pitch d= fore and aft distance from C.G. ~= maximum pitch acceleration in radians/sec2. (use ap = 5 unless otherwise known) s 32.17 ftlsec2 Add the ~Gp value obtained above to the table 513.2-II accelerationvalue for the operational test acceleration level. For the stmctural test level, multiply the new operational test value by 1.5. d. For follows the fore and aft directions, the G level shall be determined as for fuselage locations: GCP d(u)2, where Gcp .
centrifugal acceleration due to pitch g U = maximum pitch velocity, radians/see (use u = 2.5 unless otherwise known) d = fore or aft distance from C.G. !3 = 32.17 ft/sec2 G.- level COmDuted above for the operational test acceleration level when the ~~mputed val~e is larger than tha~ in table 513.2-II. For the structural test level, multiply the new operational test value by 1.5. Use the 3.3 Procedure I structural test. The test item shall be installed on the acceleration apparatus in accordance with General Requirements,3.2.2, by its normal mounting means. The G level shall be determined in accord- ance with 3.2, and shall be applied while the test item is nonoperating.
3.3.1 Performance of test. The G level determined for the test shall be applied along at least three mutually perpendicular axes in two opposite directions along each axis. The test time duration in each direction shal1 be at least 1 minute following centrifuge stabilization. On centrifuges, a test time of 1 minute is usually sufficient to determine structural soundness (proper operation); however, the test time may be increased. Test times for other apparatus will probably be shorter, depending upon the type of apparatus. At the conclusion of the test, the test item 513.2-7 METHOD 513.2