How is a fan blade containment test for aircraft engines done? <br>
How is an altitude test of an aircraft engine done?<br>
How should you inspect and test an aircraft engine to certify it safe?


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(a) The following must be shown by tests and analyses, or other methods acceptable to the Administrator, that, in lieu of the fan blade containment test with the fan blade failing at the point specified in Sec. 33.94 paragraph (a) subparagraph (1), a fan blade containment test with the fan blade failing at the inner flowpart diameter demonstrates:

(1) That the disk and fan blade retention system can withstand without failure a centrifugal load equal to two times the maximum load which the engine could experience within approved operating limitations, and

(2) That by a procedure approved by the Administrator an operating limitation must be established which specifies the maximum allowable number of start-stop stress cycles for the fan blade retention system. The fan blade retention system includes the portion of the fan blade from the inner flowpath diameter inward to the blade dovetail, the blade retention components, and the fan disk and fan blade attachment features.

(b) It must be shown that the probability of fan blade retention system failure, for any cause, during the service life of the engine to be extremely improbable.

(c) It must be shown by test or analysis that a lightning strike on the composite fan blade structure will not result in a hazardous condition, and that the engine will meet the requirements of Sec. 33.75.

(d) The tests and analyses required by (a)(1) and (a)(2) of these special conditions must account for the effects of in-service deterioration, manufacturing and materials variations, and environmental effects.