Abstract: A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket for mounting to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage; and a releasable connector that engages with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.

Abstract: In a first aspect, there is a helicopter skid landing gear assembly including a front cross tube configured to interconnect two skid tubes; and a rear cross tube configured to interconnect two skid tubes; wherein at least one of the cross tubes comprises a monolithic metallic tube having a cross-section with a round exterior shape and an elliptical hollow portion therein. In a second aspect, there is a method for retrofitting a helicopter with a landing gear assembly; the method including providing a front cross tube and a rear cross tube, at least one of the front cross tube and the rear cross tube comprises a monolithic metallic tube having a cross-section with a substantially round exterior shape and an elliptical hollow portion therein; and connecting the front cross tube and rear cross tube to a fuselage.

Abstract: A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket for mounting to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage; and a releasable connector that engages with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.

Abstract: A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket configured to mount to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage: and a releasable connector configured to engage with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.

Abstract: In a first aspect, there is a helicopter skid landing gear assembly including a front cross tube configured to interconnect two skid tubes; and a rear cross tube configured to interconnect two skid tubes; wherein at least one of the cross tubes comprises a monolithic metallic tube having a cross-section with a round exterior shape and an elliptical hollow portion therein. In a second aspect, there is a method for retrofitting a helicopter with a landing gear assembly; the method including providing a front cross tube and a rear cross tube, at least one of the front cross tube and the rear cross tube comprises a monolithic metallic tube having a cross-section with a substantially round exterior shape and an elliptical hollow portion therein; and connecting the front cross tube and rear cross tube to a fuselage.

Abstract: In one aspect, there is provided a rotary blade movement system including a retaining member configured to receive a rotor blade, a graspable arm, and a coupling mechanism operable to removably couple the retaining member to the graspable arm. The rotor blade movement system is configured to enable a user to adjust the position of the rotor blade by moving the graspable arm. The coupling mechanism can be a ball and socket joint. In one aspect, there is a method of rotating a rotor blade using a rotary blade movement system.

Abstract: A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket configured to mount to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage: and a releasable connector configured to engage with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.

Abstract: In one aspect, there is provided a rotary blade movement system including a retaining member configured to receive a rotor blade, a graspable arm, and a coupling mechanism operable to removably couple the retaining member to the graspable arm. The rotor blade movement system is configured to enable a user to adjust the position of the rotor blade by moving the graspable arm. The coupling mechanism can be a ball and socket joint. In one aspect, there is a method of rotating a rotor blade using a rotary blade movement system.

Abstract: One example of a retention system for a rotorcraft pedal assembly includes an insertion member, an axial retention member, and a transverse retention member. The insertion member, which is inserted through a side of a pedal assembly, includes a spring compressible against the side of the pedal assembly in response to the insertion member being inserted through the side. The axial retention member receives and retains the insertion member on an opposing side of the pedal assembly. The transverse retention member is inserted through a passage formed in the axial retention member to secure the axial retention member against the side of the pedal assembly.

Abstract: One example of a retention system for a rotorcraft pedal assembly includes an insertion member, an axial retention member, and a transverse retention member. The insertion member, which is inserted through a side of a pedal assembly, includes a spring compressible against the side of the pedal assembly in response to the insertion member being inserted through the side. The axial retention member receives and retains the insertion member on an opposing side of the pedal assembly. The transverse retention member is inserted through a passage formed in the axial retention member to secure the axial retention member against the side of the pedal assembly.