Abstract: The present invention discloses an apparatus for emergency landing comprising: an extraction vehicle (10), a first adjustable tower and a second adjustable tower (11), a first gearbox (4) wherein said gearbox is mounted on top of said first adjustable tower, a second gearbox wherein said second gearbox is mounted on the top of said second adjustable tower, a third gearbox wherein said third gearbox is mounted on lower right side of said chassis, a fourth gearbox unit wherein said unit is mounted on the lower left side of chassis, a first rubber restrainer (8) wrapped around said first gearbox unit and extended to said third gearbox unit wherein said rubber restrainer is wrapped around said third gearbox unit, a second rubber restrainer wrapped around said second gearbox unit and extended to said fourth gearbox unit, wherein said rubber restrainer is wrapped around said fourth gearbox unit, wherein said first and said second rubber restrainer stabilize said aircraft and reduce initial impact by said aircraft.

Abstract: The present invention discloses an apparatus for emergency landing comprising: an extraction vehicle (10), a first adjustable tower and a second adjustable tower (11), a first gearbox (4) wherein said gearbox is mounted on top of said first adjustable tower, a second gearbox wherein said second gearbox is mounted on the top of said second adjustable tower, a third gearbox wherein said third gearbox is mounted on lower right side of said chasse, a fourth gearbox unit wherein said unit is mounted on the lower left side of chasse, a first robber restrainer (8) rapped around said first gearbox unit and extended to said third gearbox unit wherein said robber restrainer is rapped around said third gearbox unit, a second robber restrainer rapped around said second gearbox unit and extended to said fourth gearbox unit, wherein said robber restrainer is rapped around said fourth gearbox unit, wherein said first and said second robber restrainer stabilize said aircraft and reduce initial impact by said aircraft.

Abstract: According to the present invention, In case of tail rotor failure in a helicopter, pilot will activate Cockpit control unit which is installed in cockpit, wherein said unit contains activation switch and electronic circuits that automatically performs steps of: determining and releasing a predetermined pressurized gas from a capsule, wherein said capsule is located within the helicopter, and wherein said predetermined pressurized gas is based on a level of pressure in said capsule, and feedback received form yaw movement; and thereby compensating tail rotors torque and stabilizing said helicopter.