INNER COWL ARRANGEMENT FOR GAS TURBINE ENGINE

An inner cowl arrangement (110) for a gas turbine engine (10) includes a first hinge (124) and a second hinge (126) pivotally connecting a first cowl member (112) and a second cowl member (118), respectively, to a mounting structure (106). The inner cowl arrangement (110) further includes a latch (128) detachably securing the first and second cowl members (112, 118). At least one of the first hinge (124), the second hinge (126), and the latch (128) includes a pressure relief component (130) that deforms or breaks when an applied load (L) on the pressure relief component (130) due to a pressure (P1) within an engine core (11) is greater a normal operating load (N), causing at least one of the first cowl member (112) and the second cowl member (118) to move relative to the engine core (11), and forming an opening (132).