Abstract: A gas turbine engine (10) includes a first fire zone (Zone 3) in the region of a core of the engine and a second fire zone (Zone 1) in the region of a fan case of the engine, the first and second fire zones being separated by fire walls. The first fire zone is located generally radially inwardly of the second fire zone but includes a bifurcation part which extends radially outwardly of the remainder of the zone for limited circumferential extent. The engine further includes a disconnect panel (52) mounted on the fan case (32) to extend radially outwardly therefrom, the disconnect panel (52) forming a fire wall and providing means for pipes and harnesses (44) to be routed therethrough.

Abstract: A gas turbine engine (10) includes a first fire zone (Zone 3) in the region of a core of the engine and a second fire zone (Zone 1) in the region of a fan case of the engine, the first and second fire zones being separated by fire walls. The first fire zone is located generally radially inwardly of the second fire zone but includes a bifurcation part which extends radially outwardly of the remainder of the zone for limited circumferential extent. The engine further includes a disconnect panel (52) mounted on the fan case (32) to extend radially outwardly therefrom, the disconnect panel (52) forming a fire wall and providing means for pipes and harnesses (44) to be routed therethrough.

Abstract: A gas turbine engine mounting arrangement (22) for attaching a gas turbine engine (10) to an aircraft via a pylon (18). The arrangement (22) comprising a main mounting means (23) which carries the engine loads under normal operating conditions, and an auxiliary mounting structure (25). The auxiliary mounting structure. (25) comprises a safety bracket (44), and auxiliary interconnection means (29) are arranged to connect the bracket (44) to the engine (10) independently of the main mounting means (23) and so that the auxiliary mounting structure (25) is substantially unloaded under normal operating conditions. The auxiliary interconnection means (29) and the safety bracket (44) engaging with the engine (10) and carrying substantial engine loads in the event of failure of the main mounting means (23). Preferably the safety bracket (44) is interposed and sandwiched between a main bracket (2), forming part of the main mounting structure (23), and the main bracket (2) and the pylon (18).