Abstract: A lightweight airplane seat using composite material to form a four-bar linkage, pivotal at the corners to reduce torque stresses and including a frangible compressible strut to absorb the forces generated during a crash.

Abstract: An eccentric fastening device is provided. The eccentric fastening device includes a first threaded fastener, a base and a rotary lug providing a non-fastened pre-assembled position. The base includes a top, a bottom, a stem and a hole, where the stem axially extends from the bottom of the base, and the hole axially extends from the top through the stem of the base. The rotary lug is releasably retained in the hole of the base by the first threaded fastener. The rotary lug includes a cylindrical portion having a thread and a head, wherein the head is offset from the cylindrical portion. The cylindrical portion is substantially axially concentric with the hole of the base, allowing the head to be eccentrically rotated on or off of the stem, whereby a selective structure may be variably clamped and releasably retained between said head and said base. An aircraft having an eccentric fastening device is also provided. A method of installing the same is also provided.

Abstract: An eccentric fastening device is provided. The eccentric fastening device includes a first threaded fastener, a base and a rotary lug providing a non-fastened pre-assembled position. The base includes a top, a bottom, a stem and a hole, where the stem axially extends from the bottom of the base, and the hole axially extends from the top through the stem of the base. The rotary lug is releasably retained in the hole of the base by the first threaded fastener. The rotary lug includes a cylindrical portion having a thread and a head, wherein the head is offset from the cylindrical portion. The cylindrical portion is substantially axially concentric with the hole of the base, allowing the head to be eccentrically rotated on or off of the stem, whereby a selective structure may be variably clamped and releasably retained between said head and said base. An aircraft having an eccentric fastening device is also provided. A method of installing the same is also provided.

Abstract: A latch assembly is disclosed. An illustrative embodiment of the latch assembly includes at least one latch unit having a latch unit housing, a latch notch provided in the latch unit housing, a lock bracket pivotally mounted in the latch unit housing adjacent to the latch notch and positional between latched and unlatched positions and an actuating arm engaging the lock bracket; a torque shaft coupled to the actuating arm; a handle unit having a handle housing and a handle plate pivotally mounted in the handle housing and coupled to the torque shaft; and at least one position indicator lip provided on the handle plate.

Abstract: A dead bolt lock apparatus specifically adapted for use with a flight deck door of an aircraft. The apparatus includes a dead bolt member which can be moved between locked and unlocked positions via a key. A lockout handle is included on the side of the apparatus which faces the flight deck area of the aircraft. The lockout handle is movable rotationally from a first position, wherein it has no affect on the use of the key to unlock the dead bolt, to a second position wherein it prevents the dead bolt from being moved out of a locked position by use of the key. The apparatus thus provides an additional degree of security to occupants of the flight deck by allowing them to prevent unlocking of the apparatus even with the key.

Abstract: A differential pressure sensing release system and apparatus specifically adapted for use with an aircraft or spacecraft compartment panel. The apparatus utilizes a mechanism activated by a pressure differential acting on a diaphragm(s) to trigger a single latch bolt or series of latch bolts or other retention mechanisms, thereby releasing the panel. The apparatus thus provides a means of equalizing the pressure differential between adjacent compartments, eliminating potential damage due to forces created by the pressure differential.

Abstract: A dead bolt lock apparatus specifically adapted for use with a flight deck door of an aircraft. The apparatus includes a dead bolt member which can be moved between locked and unlocked positions via a key. A lockout handle is included on the side of the apparatus which faces the flight deck area of the aircraft. The lockout handle is movable rotationally from a first position, wherein it has no affect on the use of the key to unlock the dead bolt, to a second position wherein it prevents the dead bolt from being moved out of a locked position by use of the key. The apparatus thus provides an additional degree of security to occupants of the flight deck by allowing them to prevent unlocking of the apparatus even with the key.

Abstract: A quick release panel assembly comprising a panel which is releasably fastened to a structure by a release and locking assembly. The release and locking assembly includes a driver element and four actuating arms that are pivotally connected to the driver element, the cover, and to four respective locking mechanisms located at each edge of the panel. The driver element moves the actuating arms between first and second positions to move the locking mechanisms between a locking position to fasten the cover to the structure and an unlocking position.

Abstract: A dual pivot expandable lavatory for use in limited spaces such as on an airplane. The lavatory may be positioned proximate the doorway area of the airplane, and is provided with a primary and a secondary pivotable module. Each module is pivotably attached to a stationary assembly conventionally affixed to the ceiling and floor of the airplane. During take-off and landing both modules are locked, by means of a locking system, in a stowed position within the stationary assembly. During routine flight, the locking system is unlocked and both modules are pivoted into a deployed position within the doorway area. A flight attendant's seat may be affixed to the exterior of the primary module. If the seat is used, an additional support foot is affixed to the primary module to accommodate the additional loading on the lavatory.

Abstract: Disclosed is an aircraft clip for attaching insulation blankets and other nonstructual items, such as wire bundles and hydraulic conduits, to structural members. The clip has a molded plastic shaped base and a "T" shaped grip rotatably connected to the base. The grip is rotated to secure the nonstructural item by a "C" shaped clamp which is pushed into a detent to assure that the clip is locked. The "T" shaped grip is allowed to rotate by a flexible and thin tab interconnecting the base and "T" shaped grip which, in a preferred embodiment, are integrally molded. Optionally, the "C" shaped clamp may be made of spring steel rather than molded of plastic. Also optionally, the "T" shaped grip may be allowed to rotate into position by a metal hinge pin.

Abstract: A quick setting and releasing system for installing and removing fixtures in a longitudinal track comprises a bottom track having an inverted, T-shaped, longitudinal channel and a fixture track having a T-shaped, longitudinal channel. The actuating and locking mechanisms comprise a pair of wing shaped lugs which float on and pivot around a longitudinal pin to lock the lugs in the fixture channel when upward pressure is applied to the pin and in the bottom track when downward pressure is applied to the pin.

Abstract: An elongated latch body has an eyelet on one end, and an open ended clevis shape on the other end. A pair of cooperating, laterally extending, and partially overlapping linkages are pivotally mounted near the open end of the clevis part of the latch body and a U-shaped rocker arm, also mounted within the clevis part of the latch body, controls rotational movement of the linkages.

Abstract: An articulated hinge having a movable pivot axis cooperates with an energy storage device for automatically opening and securing an unlatched compartment door in a first open position. Primary and secondary linking members are rotatively mounted to a support structure adjacent the interior of the compartment door opening, and are also rotatively mounted on a hinge base member. The hinge base member forms a pivot axis about which the compartment door is mounted for rotation. A coupling member is associated with the compartment door and the primary and secondary linking members. When the compartment door is rotated, the coupling member causes the primary and secondary linking members to rotate about their attachment points to the support structure and thereby causes the pivot axis of the compartment door to move along a predetermined path.