Multi-function orifice subassembly for flow limiters

An aircraft comprising:

• a fuselage;
• a hydraulic system disposed in the fuselage;
• a flow limiter operably disposed in the hydraulic system, the flow limiter comprising a flow limiter component comprising:
• a monocoque body having a first section, a second section, and a third section arranged along a longitudinal axis of the monocoque body;
• the first section comprising:
• a first end defining a first edge of the monocoque body and a second end bordering the second section;
• and
• a first inner diameter relative to the longitudinal axis, the first inner diameter defining a first chamber inside the first section;
• the second section comprising:
• a solid wall;
• wherein an orifice is disposed in the solid wall, in fluid communication with the first chamber, and
• wherein the orifice is defined by a second inner diameter relative to the longitudinal axis;
• the third section comprising:
• a third end bordering the second section and a fourth end defining a second edge of the monocoque body;
• a third inner diameter relative to the longitudinal axis, the third inner diameter defining a second chamber in the third section,
• wherein the second chamber is in fluid communication with the orifice, and
• wherein the first inner diameter is greater than the third inner diameter, and the third inner diameter is greater than the second inner diameter;
• a cut-out defined in the third section, proximate the fourth end, wherein the cut-out is further defined between the second chamber and a flange of the fourth end of the third section, wherein the flange forms at least a part of an outer edge of the third section, and wherein the cut-out has a cut-out diameter greater than the third inner diameter;
• and
• a strainer disposed in the cut-out and having a strainer diameter that is larger than the third inner diameter but smaller than or equal to the cut-out diameter, wherein the strainer and the solid wall further define borders of the second chamber, and wherein the flange retains the strainer.

A method comprising:

• installing a flow limiter in a hydraulic system of an aircraft, the flow limiter comprising a flow limiter component comprising:
• a monocoque body having a first section, a second section, and a third section arranged along a longitudinal axis of the monocoque body;
• the first section comprising:
• a first end defining a first edge of the monocoque body and a second end bordering the second section;
• and
• a first inner diameter relative to the longitudinal axis, the first inner diameter defining a first chamber inside the first section;
• the second section comprising:
• a solid wall;
• wherein an orifice is disposed in the solid wall, in fluid communication with the first chamber, and
• wherein the orifice is defined by a second inner diameter relative to the longitudinal axis;
• the third section comprising:
• a third end bordering the second section and a fourth end defining a second edge of the monocoque body;
• a third inner diameter relative to the longitudinal axis, the third inner diameter defining a second chamber in the third section,
• wherein the second chamber is in fluid communication with the orifice, and
• wherein the first inner diameter is greater than the third inner diameter, and the third inner diameter is greater than the second inner diameter;
• a cut-out defined in the third section, proximate the fourth end, wherein the cut-out is further defined between the second chamber and a flange of the fourth end of the third section, wherein the flange forms at least a part of an outer edge of the third section, and wherein the cut-out has a cut-out diameter greater than the third inner diameter;
• and
• a strainer disposed in the cut-out and having a strainer diameter that is larger than the third inner diameter but smaller than or equal to the cut-out diameter, wherein the strainer and the solid wall further define borders of the second chamber, and wherein the flange retains the strainer.