Seal for an aircraft and aircraft incorporating at least one such seal

An aircraft, in particular an airplane or a helicopter, comprising:

• at least one pair of metallic or composite structural elements (1 and 2) configured to be connected to each other at least at one zone of the aircraft selected from among the main reactor and auxiliary engine zones, whose temperature in the absence of fire fan vary from −55° C. to 250° C. and which is referred to as fire zone according to § 2.1 of the standard ISO 2685;
• 1998 or according to the standard AC 20-135, and
• at least one seal (10) which tightly connects the structural elements (1 and 2) of said at least one pair to each other,
• wherein said at least one seal (10) comprises:
• a seal body (11) at least partially elastomeric, the seal body (11) defining at least one generally tubular or annular cavity (10A), and
• a fire-resistant structure (12) which is distinct from the seal body (11) and which is disposed inside said at least one cavity (10A), the fire-resistant structure (12) comprising at least one intumescent mass able to fill said at least one cavity (10A) in an expanded state,
• wherein said at least one intumescent mass is made of s rubber composition having an intumescence trigger temperature equal to or higher than 270° C. measured by a plane-piano rotary rheometer with a temperature scan from 23 to 380° C. according to a temperature ramp of 10° C./min, with 1% of deformation and with an evolution, starting from 23° C. of the normal force Fn starting from 0.07 N and of the air gap h between the planes starting from 2 mm.