Pneumatic start system with integrated electric generator powered by engine environmental control bleed supply

A pneumatic start system with an integrated generator for an aircraft, the system comprising:

• a compressor system, the compressor system comprising a high pressure compressor and a low pressure compressor;
• an air turbine starter (ATS) fluidly coupled to the compressor system, and fluidly coupled to ambient atmosphere and an environmental control system (ECS) bleed system in parallel, the ATS comprising the integrated generator, wherein:
• bleed air from the compressor system is configured to flow through an inlet of the air turbine starter, thereby exciting the integrated generator;
• the ATS is configured to regulate a pressure of the bleed air from the compressor system via operation of the integrated generator;
• a first fluid connection between the ECS bleed system and the ATS is regulated by a starter air valve (SAV);
• a second fluid connection between the ECS bleed system and the ATS is regulated by an ECS shut off valve;
• pressure regulated fluid flow from the compressor system is configured to deliver pressure regulated fluid flow to the ECS bleed system via the second fluid connection between the ECS bleed system and the ATS based upon operation of the ECS shut off valve;
• and
• the ambient release valve and the ECS shut off valve are implemented in a single switching valve configured to direct fluid flow from the ATS to ambient atmosphere and to close a path from the ATS to the ECS bleed system in response to a detected failure in pressure regulation.