<div class="section abstract"><div class="htmlview paragraph">A system has been designed for the A400M wherein engine air intake ice protection is provided by hot air bled from the engine cooled by air from inside the nacelle with a jet pump.</div><div class="htmlview paragraph">Two variants of the system were developed. The first had an active temperature and pressure control downstream of the jet pump, and the second was without temperature control.</div><div class="htmlview paragraph">Maximum temperature was a constraint for the design of the system since the engine air intake is manufactured in aluminum. In addition, several other constraints appeared during the detailed design of the system; <ul class="list disc"><li class="list-item"><div class="htmlview paragraph">the tight space allocation inside the nacelle limited the length of the jet pump,</div></li><li class="list-item"><div class="htmlview paragraph">the low temperature provided by the engine bleed in flight idle limited the secondary flow used to cool the engine bleed, and</div></li><li class="list-item"><div class="htmlview paragraph">the complex air distribution needed to supply air to the intake areas.</div></li></ul></div><div class="htmlview paragraph">The design, validation and verification of the system went through several stages; <ul class="list disc"><li class="list-item"><div class="htmlview paragraph">analyses,</div></li><li class="list-item"><div class="htmlview paragraph">hot air mass flow validation testing of the intake in icing tunnel,</div></li><li class="list-item"><div class="htmlview paragraph">testing of the ice protection system, intake and engine all together in an Altitude Test Facility and,</div></li><li class="list-item"><div class="htmlview paragraph">testing in the aircraft natural icing flight test campaign</div></li></ul></div><div class="htmlview paragraph">All of them were used to show compliance with EASA CS-25 regulation.</div></div>