A system (300) for protecting the structural integrity of an engine strut (200) may include a first monitor (302), a second monitor (304), and a controller (360) communicatively coupled to the first monitor (302) and the second monitor (304). The first monitor (302) may be mounted proximate an engine strut (200) coupling a turbine engine (118) to an airframe (102) of an aircraft (100). The second monitor (304) may be mounted proximate the first monitor (302). The first monitor (302) and the second monitor (304) may each be configured to fail upon reaching a triggering temperature indicative of a burn-through in an engine case (152) during operation of the turbine engine (118). The controller (360) may be configured to automatically reduce an operating parameter (170) of the turbine engine (118) upon a failure of both the first monitor (302) and the second monitor (304).
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