How is an ice protection system designed and certified?

Ice protection prevents ice accumulation that degrades performance and control. Protected surfaces: Wings (leading edge), Empennage, Engine inlets, Propellers, Sensors (pitot, AOA), and Windshield. Methods: Thermal - Hot bleed air (piccolo tube), electric heaters; Mechanical - Pneumatic boots (expansion breaks ice), Electromechanical impulse; Chemical - TKS fluid (weeping system for GA). Design process: Define icing conditions (FAR 25 Appendix C, Appendix O for SLD), Heat/power analysis for anti-ice or de-ice, System architecture (zoning, redundancy). Analysis: Heat transfer, runback ice, and Performance degradation with ice shapes. Testing: Icing tunnel (NASA Glenn), Tanker spray, Natural icing flight test. Certification: Function and reliability, Performance in icing (flight test with simulated ice), Handling qualities degradation acceptable. System selection: Bleed air for large transports (most common), Electric for More Electric Aircraft (787), and Boots for smaller aircraft. Ice detectors activate systems; ice advisory to crew.