Abstract: A system for controlling bleed air flow in an aircraft is described herein. High-pressure compressor bleed air is regulated in a stepped manner with a bleed full open/full closed valve and a second, bleed half open/full open valve, or with a complex multi-step valve. This mitigates severe pressure transient conditions and results in a less drastic pressure differential across a downstream pressure or flow control valve before the bleed air is repurposed for other uses in the aircraft. The system allows for better downstream system stability across the aircraft operational envelope.