Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.

Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.

Abstract: A baseboard corner and a method of use thereof for joining adjacent baseboard pieces at the corner of wall surfaces. The baseboard corner includes a trim member and a base member which is integral to the trim member. The trim member can flush mount with the intersection wall surfaces and surfaces of the adjacent baseboard pieces. The base member forms a left bracket and a right bracket for receiving the adjacent baseboard pieces. The baseboard corner eliminates the need for making mitered joints at the intersection of walls.

Abstract: In some examples, a drain pan comprises a composite material forming a reservoir and a drain. The composite material comprises a polymeric resin and a reinforcing fiber. The reservoir is to catch a liquid from an engine and to support a step load. The drain is to drain the liquid from the reservoir. In some examples, a method comprises attaching a drain pan to an aircraft proximate an engine. The drain pan comprises a composite material forming a reservoir and a drain. The method further comprises catching a liquid from the engine in the reservoir of the drain pan and draining the liquid from the reservoir through the drain. In addition, the method comprises supporting a step load on the reservoir of the drain pan.

Abstract: The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface.

Abstract: The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface.

Abstract: One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion.

Abstract: A cooling apparatus includes a shared cooling device for one or more systems or components, and a plurality of primary cooling pathways. Each of the primary cooling pathways includes a transition duct and a fan. The transition duct is in fluid communication with the shared cooling device. The fan is in fluid communication with the transition duct.

Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.

Abstract: A fairing is provided in one example embodiment and may include a first edge portion to provide a first clearance distance between the fairing and rotor flight controls of a rotorcraft; a second edge portion to provide a second clearance distance between the fairing and the rotor flight controls of the aircraft, wherein the second clearance distance is greater than the first clearance distance; and a support structure attached to the fairing below the second edge portion. A rotorcraft is provided in another example embodiment and may include a fairing in which the fairing can include a handhold portion along an edge of the fairing. The handhold portion can include a handhold clearance distance between the handhold portion and rotor flight controls of the rotorcraft; and a support structure attached to the fairing below the handhold portion.

Abstract: In one embodiment of the present disclosure, there is provided an aircraft that includes a cowling having a j-track mounted on the inwardly facing surface and a rod pivotally connected to a stationary part of the aircraft at a first end and moveable within the j-track at a second end, so that, when the cowling is opened, the second end moves to lock into the j-shaped portion and hold the cowling open. In various embodiments, the first end may be pivotally connected to the aircraft by a quick release pin, and the second end may be connected to the j-track by a torsion spring. In another embodiment of the present disclosure, the cowling is a bi-folding cowl having an upper portion and a lower portion, where the rod and the lower portion may include structures for retaining the lower portion in an opened position.

Abstract: In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.

Abstract: One embodiment is a passive particle separation system including a plenum; an inlet for feeding outside air into the plenum, wherein the outside air has particles entrained therewith; a housing for enclosing the plenum; and a standpipe installed on the housing. The outside air enters the plenum via the inlet and plenum, housing, and standpipe interact to impact the outside air entering the plenum to cause the particles to be released from the outside air.

Abstract: A duct interface system and method includes a duct having a first end and a second end; a first receptacle for the first end of the duct and/or a second receptacle for the second end of the duct; and one or more first seals between the first end of the duct and the first receptacle and/or one or more second seals between the second end of the duct and the second receptacle.

Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.

Abstract: This disclosure relates to an air inlet for an aircraft with an integrated hand hold. One innovative aspect of the subject matter described herein can be implemented as an air inlet on the exterior surface of a cowling for a rotorcraft, wherein the air inlet having a scoop that includes a bottom surface having a wide, flat, front edge that angles downward towards the back, an opening in the back for air to enter, and two lateral sides coupled to the bottom surface, where the two sides are planar on a top surface and become longer in height towards the opening in the back, and hand hold, where the hand hold is a trough or an indentation in the bottom surface of the scoop that extends along a side.

Abstract: A fairing is provided in one example embodiment and may include an apparatus to receive at least one of a foot traffic load and a hand traffic load, wherein the apparatus can include: a step portion that is to receive at least a portion of the foot traffic load; a handhold portion that is to receive at least a portion of the hand traffic load, wherein the handhold portion extends downward from the step portion; and a support structure, wherein the support structure extends downward from of the step portion. The apparatus can include an outer flange attached to the fairing. At least a portion of the step portion the apparatus can be recessed within the fairing at a distance between one inch and three inches from a top surface of the fairing. The handhold portion can include one or more drain holes.

Abstract: One example of a cowling assembly for a rotorcraft includes a stationary fairing affixed to an airframe of the rotorcraft, an articulated fairing hinged on the stationary fairing for articulation relative to the stationary fairing between a closed position, a first partially open maintenance position and a second fully open maintenance position. The articulated fairing is supported in the first maintenance position by a for example gas-charged strut and is releasably locked in the second maintenance position against the stationary fairing by a locking mechanism. The locking mechanism includes a latch blade disposed on the stationary fairing and a latch arranged on the articulated fairing, wherein a latch pin engages with a hole or recess in the latch blade when the latch blade extends through a slot in the articulated fairing.

Abstract: In one embodiment, there is described an inlet plenum assembly for a rotary aircraft, including: an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly; the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine; wherein the forward firewall assembly includes a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.

Abstract: One embodiment is an inlet plenum assembly for a rotary aircraft that includes an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly, the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably coupled to an engine; and a seal connected to the forward firewall assembly via a seal retainer disposed around a periphery of the inlet aperture. The forward firewall assembly may further include a forward firewall upper portion and a forward firewall lower portion, the forward firewall upper portion configured to removably seat to the forward firewall lower portion. The seal retainer may be attached to the forward firewall assembly via a plurality of bolts disposed around the periphery of the seal retainer. In some embodiments, the seal is connected to an inlet duct of the engine.