Abstract: A propulsion system assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an outer airflow inlet passage, an inner airflow inlet passage, an inlet structure and a center body structure. The outer airflow inlet passage is between the inlet structure and the center body structure. The inner airflow inlet passage is formed within the center body structure. The center body structure includes a valve configured to regulate air flow through the inner airflow inlet passage. The valve includes a first door configured to pivot between a closed position and an open position. The inlet duct is configured to receive air from the outer airflow inlet passage when the first door is in the closed position. The inlet duct is configured to receive air from the outer airflow inlet passage and the inner airflow inlet passage when the first door is in the open position.

Abstract: A propulsion system assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an outer airflow inlet passage, an inner airflow inlet passage, an inlet structure and a center body structure. The outer airflow inlet passage is between the inlet structure and the center body structure. The inner airflow inlet passage is formed within the center body structure. The center body structure includes a valve configured to regulate air flow through the inner airflow inlet passage. The valve includes a first door configured to pivot between a closed position and an open position. The inlet duct is configured to receive air from the outer airflow inlet passage when the first door is in the closed position. The inlet duct is configured to receive air from the outer airflow inlet passage and the inner airflow inlet passage when the first door is in the open position.

Abstract: A ducted fan engine module and method of assembling the same is disclosed. In various embodiments, the ducted fan engine module includes a ducted fan engine having a ducted fan case configured to house a fan; a lower V-blade fitting secured to a lower frame; and an upper V-blade fitting secured to an upper frame.

Abstract: A propulsion system assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an outer airflow inlet passage, an inner airflow inlet passage, an inlet structure and a center body structure. The outer airflow inlet passage is between the inlet structure and the center body structure. The inner airflow inlet passage is formed within the center body structure. The center body structure includes a valve configured to regulate air flow through the inner airflow inlet passage. The valve includes a first door configured to pivot between a closed position and an open position. The inlet duct is configured to receive air from the outer airflow inlet passage when the first door is in the closed position. The inlet duct is configured to receive air from the outer airflow inlet passage and the inner airflow inlet passage when the first door is in the open position.

Abstract: An acoustic panel is provided that includes a first skin, a second skin and a core structure. The core structure is connected to and forms a plurality of cavities between the first skin and the second skin. The cavities include a first cavity and a second cavity. The first cavity is fluidly coupled with one or more first perforations in the first skin. The second cavity is fluidly coupled with one or more second perforations in the second skin.

Abstract: In accordance with at least one aspect of this disclosure, a system for preventing spread of contagion in a passenger vehicle includes, a barrier housing configured to mount to a first surface in the passenger vehicle, a retractable barrier housed in the barrier housing configured to move between a deployed position and a retracted position, a retraction mechanism operatively connected to the retractable barrier within the barrier housing configured to bias the retractable barrier to the retracted position, and a barrier retainer configured to mount to a second surface in the passenger vehicle opposite the first surface to retain the retractable barrier in the deployed position. In certain embodiments, the retractable barrier can include a free end configured to be pulled by a user.

Abstract: A ducted fan engine module and method of assembling the same is disclosed. In various embodiments, the ducted fan engine module includes a ducted fan engine having a ducted fan case configured to house a fan; a lower V-blade fitting secured to a lower frame; and an upper V-blade fitting secured to an upper frame.

Abstract: A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes an aircraft propulsion system and a pylon configured to mount the aircraft propulsion system to an airframe member. The pylon includes a first pylon structure and a second pylon structure. The first pylon structure is configured to mount to the airframe member. The second pylon structure is mounted to the aircraft propulsion system. The second pylon structure is configured to disconnect from the first pylon structure while mounted to the airframe member.

Abstract: A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.

Abstract: An acoustic panel is provided that includes a first skin, a second skin and a core structure. The core structure is connected to and forms a plurality of cavities between the first skin and the second skin. The cavities include a first cavity and a second cavity. The first cavity is fluidly coupled with one or more first perforations in the first skin. The second cavity is fluidly coupled with one or more second perforations in the second skin.

Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.

Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.

Abstract: Aspects of the disclosure are directed to a system for isolating at least one of a fire zone and a high-pressure zone from at least one of a non-fire zone and a low-pressure zone, comprising a seal and a flexible spring retainer coupled to the seal that is configured to bias the seal. The biasing may be based in terms of a compression of the seal within a predetermined range of compression. A shielding of the seal from the at least one of the fire zone and the high-pressure zone may be provided.

Abstract: A thrust reverser system is provided with an axial centerline. This thrust reverser system includes a first translating element, a second translating element and an actuator mechanism. The actuator mechanism is attached to the first translating element and the second translating element. The actuator mechanism is configured to translate the first translating element along the axial centerline at a first rate. The actuator mechanism is configured to translate the second translating element along the axial centerline at a second rate, which may be different than the first rate.

Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a first component, a second component and a seal assembly configured to seal a gap between the first and the second components. The seal assembly includes a metal spring seal element and an elastomeric seal element. The metal spring seal element is mounted to the first component. The metal spring seal element is sealingly engaged with the second component. The elastomeric seal element is mounted to the metal spring seal element. The elastomeric seal element is sealingly engaged with the second component.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes an aircraft propulsion system and a pylon configured to mount the aircraft propulsion system to an airframe member. The pylon includes a first pylon structure and a second pylon structure. The first pylon structure is configured to mount to the airframe member. The second pylon structure is mounted to the aircraft propulsion system. The second pylon structure is configured to disconnect from the first pylon structure while mounted to the airframe member.

Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a first component, a second component and a seal assembly configured to seal a gap between the first and the second components. The seal assembly includes a metal spring seal element and an elastomeric seal element. The metal spring seal element is mounted to the first component. The metal spring seal element is sealingly engaged with the second component. The elastomeric seal element is mounted to the metal spring seal element. The elastomeric seal element is sealingly engaged with the second component.

Abstract: A latch handle is disclosed. The latch handle may comprise a first portion and a second portion. The first portion may comprise a high aspect ratio. The second portion may have a width greater than the second portion. A nacelle is disclosed. The nacelle may comprise a first panel and a latch assembly. The latch assembly may include a latch housing and a latch handle. The latch handle may include a first portion and a second portion. The first portion may comprise an aspect ratio greater than one. The second portion may have a width greater than the width of the first portion. A cut-out configured to accommodate the latch assembly may be disposed on the first panel. The first panel may be a fan cowl panel.

Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.