Patent ID: 7806364

Claim:
An aircraft comprising: a fuselage wherein the fuselage defines a chamber; a pedestal; and a gas turbine engine mounted to the fuselage via the pedestal, the gas turbine engine having ancillary components situated within the chamber, and having a containment system that includes: a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine, the force absorbing arrangement including a casing circumferentially surrounding at least a major proportion of the axial length of the engine; the ancillary components including a power off take arrangement to extract power from a main shaft of the engine, the power off take arrangement including: an off take shaft extending from the aforesaid main shaft to the chamber; and a gear box arrangement to transmit rotary power from the shaft to the components, wherein the force absorbing arrangement comprises a force absorbing material wrapped around the casing circumferentially surrounding the engine, the casing having an outer skin formed of a corrugated material to allow radially outward deformation of the outer skin upon impact of the force absorbing material, the impact on the outer skin allowing radial outward deformation of the force absorbing material.