PURPOSE: To obtain a de-icer of a front edge of an aircraft by partly operating another displacing tube when one of the displacing tubes is expanded, and enlarging an iced surface for distributing a fatigue stress by an increase in bending of a chordal direction of the iced surface.

CONSTITUTION: A de-icer 20 comprises a plurality of displacing elements directly under an iced surface 23, a composite base structure 30 at a lower side of the element, and an inflatable tubular member 21 connected so that a displacing means 26 receives supply of a pressure of a fluid. The de-icer 20 comprises a first tubular member 21 extended longitudinally along the surface 23, similarly at least another second tubular member 27, and expansion means for independently expanding the first and second members 27. The first and second members 27 are partly matched, and connected along a width direction part. When one of the tubes 21 is expanded, the other member 21 is partly operated, and bending of a chordal direction of the iced surface 23 is increased, and the surface 23 for distributing the stress is enlarged.