A fluid check valve for use in an aircraft fluid handling system having a confined surrounding structure where a first distance is defined between a fluid duct and the surrounding structure where the design of the fluid check valve is configured to facilitate removal of a first flange and the flow duct by moving the first flange and flow duct a second distance that is less than the first distance. The check valve is offset into the upstream side of a second flange to provide the reduction in the distance that the first flange has to be displaced to remove the first flange and flow duct from the check valve. A first alternate configuration of the fluid check valve utilizes rotational stops attached to the downstream surface of the flow flaps and in a second alternate embodiment configuration, rotational stops extend upstream from the flow flaps.

A fluid check valve for use in an aircraft fluid handling system having a confined surrounding structure where a first distance is defined between a fluid duct and the surrounding structure where the design of the fluid check valve is configured to facilitate removal of a first flange and the flow duct by moving the first flange and flow duct a second distance that is less than the first distance. The check valve is offset into the upstream side of a second flange to provide the reduction in the distance that the first flange has to be displaced to remove the first flange and flow duct from the check valve. A first alternate configuration of the fluid check valve utilizes rotational stops attached to the downstream surface of the flow flaps and in a second alternate embodiment configuration, rotational stops extend upstream from the flow flaps.

A method for emergency ventilating and pressurizing an aircraft cabin comprises determining a cabin pressure within the aircraft cabin and determining an ambient pressure in an aircraft environment. Descent of the aircraft is initiated when the cabin pressure falls below a predetermined threshold value. A supply of ambient air from the aircraft environment into the aircraft cabin is initiated, when, during descent of the aircraft, a differential pressure between the cabin pressure and the ambient pressure falls below a first calculated threshold value. The supply of ambient air into the aircraft cabin and an operation of an air outflow valve of a cabin pressurization system of the aircraft are controlled such that a flow of ambient air into the aircraft cabin corresponds to at least a predetermined minimum value and the differential pressure between the cabin pressure and the ambient pressure does not fall below a second calculated threshold value.

A method for emergency ventilating and pressurizing an aircraft cabin comprises determining a cabin pressure within the aircraft cabin and determining an ambient pressure in an aircraft environment. Descent of the aircraft is initiated when the cabin pressure falls below a predetermined threshold value. A supply of ambient air from the aircraft environment into the aircraft cabin is initiated, when, during descent of the aircraft, a differential pressure between the cabin pressure and the ambient pressure falls below a first calculated threshold value. The supply of ambient air into the aircraft cabin and an operation of an air outflow valve of a cabin pressurization system of the aircraft are controlled such that a flow of ambient air into the aircraft cabin corresponds to at least a predetermined minimum value and the differential pressure between the cabin pressure and the ambient pressure does not fall below a second calculated threshold value.

A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler.

A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler.

A system is provided. The system includes a first inlet providing a medium from a source, a compressing device in communication with the first inlet, and at least one heat exchanger. The compressing device includes a compressor that receives the medium, a first turbine downstream of the compressor, and a second turbine that receives the medium. An outlet of the at least one heat exchanger is in fluid communication with an inlet of the compressor and an inlet of the first turbine.

A system is provided. The system includes a first inlet providing a medium from a source, a compressing device in communication with the first inlet, and at least one heat exchanger. The compressing device includes a compressor that receives the medium, a first turbine downstream of the compressor, and a second turbine that receives the medium. An outlet of the at least one heat exchanger is in fluid communication with an inlet of the compressor and an inlet of the first turbine.

A system is provided. The system includes an inlet providing a first medium; a compressing device comprising a compressor, and at least one heat exchanger located downstream of the compressor. The compressing device is in communication with the inlet providing the first medium. The at least one heat exchanger includes a first pass and a second pass. An outlet of the first pass of the at least one heat exchanger is in fluid communication with an inlet of the compressor.

A system is provided. The system includes an inlet providing a first medium; a compressing device comprising a compressor, and at least one heat exchanger located downstream of the compressor. The compressing device is in communication with the inlet providing the first medium. The at least one heat exchanger includes a first pass and a second pass. An outlet of the first pass of the at least one heat exchanger is in fluid communication with an inlet of the compressor.