Aircraft engine assembly with isolation valve outside uncontained rotor impact area

An aircraft comprising:

• a fuselage;
• a left wing connected to the fuselage and extending on a left side of the fuselage;
• a right wing connected to the fuselage and extending on a right side of the fuselage;
• a left engine assembly connected to the left wing;
• and
• a right engine assembly connected to the right wing,
• each of the left and right engine assemblies comprising:
• a nacelle;
• an engine housed in the nacelle, the engine having a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area;
• a pylon connecting the nacelle to a corresponding one of the left wing and the right wing;
• an aft fairing connected to a rear of the pylon and to a bottom of the corresponding one of the left wing and the right wing;
• at least one hydraulic actuator connected to at least one of the engine and the nacelle;
• at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator;
• and
• at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the corresponding one of the left wing and the right wing, rearward of the pylon, and inside the aft fairing.

An aircraft comprising:

• a fuselage;
• a left wing connected to the fuselage and extending on a left side of the fuselage;
• a right wing connected to the fuselage and extending on a right side of the fuselage;
• a left engine assembly connected to the left wing;
• and
• a right engine assembly connected to the right wing,
• each of the left and right engine assemblies comprising:
• a nacelle;
• an engine housed in the nacelle, the engine having a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area;
• a pylon connecting the nacelle to a corresponding one of the left wing and the right wing;
• at least one hydraulic actuator connected to at least one of the engine and the nacelle;
• at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator;
• an aft fairing connected to a rear of the pylon and to a bottom of the corresponding one of the left wing and the right wing;
• and
• at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the corresponding one of the left wing and the right wing, rearward of the pylon, inside the aft fairing, rearward of a leading edge of the corresponding one of the left wing and the right wing and forward of a trailing edge of the corresponding one of the left wing and the right wing.

A hydraulic system for actuating a thrust reverser of an aircraft engine assembly, the aircraft engine assembly being connected to an aircraft wing and comprising a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area, the hydraulic system comprising:

• at least one hydraulic actuator for actuating the thrust reverser;
• at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator, the at least one directional control valve being within the uncontained rotor impact area;
• and
• at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the aircraft wing, rearward of a pylon, inside an aft fairing connected to a rear of the pylon and to a bottom of the aircraft wing, rearward of the uncontained rotor impact area and forward of a trailing edge of the aircraft wing.