Abstract: A tubular fluid conduit which is especially adapted for use in supplying pre-conditioned air to an aircraft being serviced, wherein the tubular conduit may be fabricated as a thermoplastic extrusion having a constant diameter dimension, whereby a first end portion may be fluidically connected to a large diameter supply conduit while a second end portion may be fluidically connected to a small diameter use conduit as a result of spiral wrapping the second end portion around the use conduit. Alternatively, the tubular conduit may be fabricated as a thermoplastic extrusion having repetitive sections with each section comprising relatively large diameter and relatively small diameter portions.

Abstract: A preconditioned air hose includes an abrasion-resistant external layer made of robust nylon, an insulating layer, and an inner layer. The robust external layer protects the air hose from wear and degradation due to abrasion. The external layer may be made of a fabric with an abrasion resistance of at least 22,000 cycles to failure as measured using the ASTM D 3884 standard. This external layer fabric may be composed of filaments having a linear density of about 1,000 denier. The external layer fabric may weigh about 10.8 ounces per square yard.

Abstract: An aircraft powering system is provided which includes an aircraft electrical connector is provided with features to allow facile engagement with an aircraft and strong retention forces. The aircraft powering system may include the aircraft electrical connector having a unique biasing mechanism and modular construction, wherein the biasing mechanism is configured to place differential forces onto mating electrical connectors from an aircraft. The biasing mechanism may be operatively coupled to a handle or trigger, which may be easily engageable by an operator.

Abstract: An aircraft powering system is provided which includes an aircraft electrical connector is provided with features to allow facile engagement with an aircraft and strong retention forces. The aircraft powering system may include the aircraft electrical connector having a unique biasing mechanism and modular construction, wherein the biasing mechanism is configured to place differential forces onto mating electrical connectors from an aircraft. The biasing mechanism may be operatively coupled to a handle or trigger, which may be easily engageable by an operator.

Abstract: A system and method for connecting a traditional air chute to an air hose delivering preconditioned air to an aircraft includes an adapter system. The adapter system includes a flexible stage having an exterior surrounding a hollow interior configured to receive air from the air hose and deliver the air to the air chute. The adapter system also includes a rotational stage coupled to the flexible stage and having an exterior surrounding a hollow interior configured to receive air from the air hose and deliver the air to the air chute. The flexible stage is adjustable relative to the rotational stage to selectively move the hollow interior of the flexible stage between extending along a common axis through the air chute and the rotational stage and not extending along the common axis.

Abstract: A preconditioned air hose includes an abrasion-resistant external layer made of robust nylon, an insulating layer, and an inner layer. The robust external layer protects the air hose from wear and degradation due to abrasion. The external layer may be made of a fabric with an abrasion resistance of at least 22,000 cycles to failure as measured using the ASTM D 3884 standard. This external layer fabric may be composed of filaments having a linear density of about 1,000 denier. The external layer fabric may weigh about 10.8 ounces per square yard.

Abstract: An aircraft electrical connector is provided with features to allow facile engagement with an aircraft and strong retention forces. The aircraft electrical system may include the aircraft electrical connector having a unique biasing mechanism and modular construction, wherein the biasing mechanism is configured to place differential forces onto mating electrical connectors from an aircraft. The biasing mechanism may be operatively coupled to a handle or trigger, which may be easily engageable by an operator. In one embodiment, an electrical connector may include a cam plate disposed between electrical connectors. The cam plate is configured to place differential forces on mating connectors inserted into the electrical connectors. In another embodiment, an electrical connector includes a moveable shaft that is disposed between electrical connectors.

Abstract: A new and improved aircraft power connector, for electrical connection to an aircraft electrical connector, has incorporated thereon a dual-position mechanism which can effectively alter the engagement force level defined between the electrical connector contact pins of the aircraft power connector and the aircraft electrical connector. When the mechanism is disposed at a first position, the force level is relatively low so as to easily permit connection and disconnection, whereas when the mechanism is disposed at a second position, the force level is relatively high so as to ensure the connection of the aircraft power connector to the aircraft electrical connector and thereby prevent the inadvertent disconnection of the aircraft power connector from the aircraft electrical connector.

Abstract: An expansible and collapsible tubular conduit, which is especially adapted for use in supplying pre-conditioned air to an aircraft while the aircraft is located upon the ground and is being serviced, comprises a plurality of annular fabric membranes which are connected to the opposite sides of a plurality of annular structural dividers or frame members in a continuously repetitive alternating manner. The structural combination or assembly comprising the fabric membranes and the structural dividers or frame members renders the tubular conduit readily expansible and contractible in the form of a spring or accordion so as to be capable of being easily and rapidly deployed and stowed, as well as to be capable of being stored in a relatively compact state or mode.

Abstract: An aircraft powering system is provided which includes an aircraft electrical connector is provided with features to allow facile engagement with an aircraft and strong retention forces. The aircraft powering system may include the aircraft electrical connector having a unique biasing mechanism and modular construction, wherein the biasing mechanism is configured to place differential forces onto mating electrical connectors from an aircraft. The biasing mechanism may be operatively coupled to a handle or trigger, which may be easily engageable by an operator.

Abstract: A new and improved aircraft power connector, for electrical connection to an aircraft electrical connector, has incorporated thereon a dual-position mechanism which can effectively alter the engagement force level defined between the electrical connector contact pins of the aircraft power connector and the aircraft electrical connector. When the mechanism is disposed at a first position, the force level is relatively low so as to easily permit connection and disconnection, whereas when the mechanism is disposed at a second position, the force level is relatively high so as to ensure the connection of the aircraft power connector to the aircraft electrical connector and thereby prevent the inadvertent disconnection of the aircraft power connector from the aircraft electrical connector.

Abstract: A power delivery system for parked aircraft includes protective rings on the power cords. These protective rings protect the power cord jackets from wear and facilitate movement of the power cords across the ground. The rings may be configured for securement to the cable so as to compress the insulative jacket of the cable somewhat, thereby firmly maintaining the rings in place on the cable. The rings may be formed of two identical elements that are joined to envelope the cable. The rings may accommodate both round insulated cable, as well as bundled cable.

Abstract: A system for supporting a hose configured to deliver preconditioned air from a source to an aircraft is disclosed. The system includes a base support and a stationary bearing assembly connected to the base support proximate a first end of the stationary bearing assembly. The stationary bearing assembly is configured to engage the hose to support the hose. The system also includes a frame assembly connected to the stationary bearing assembly proximate a second end of the stationary bearing assembly. The frame assembly has a support extending away from the frame assembly that is configured to engage the hose.

Abstract: A system and method for connecting a traditional air chute to an air hose delivering preconditioned air to an aircraft includes an adapter system. The adapter system includes a flexible stage having an exterior surrounding a hollow interior configured to receive air from the air hose and deliver the air to the air chute. The adapter system also includes a rotational stage coupled to the flexible stage and having an exterior surrounding a hollow interior configured to receive air from the air hose and deliver the air to the air chute. The flexible stage is adjustable relative to the rotational stage to selectively move the hollow interior of the flexible stage between extending along a common axis through the air chute and the rotational stage and not extending along the common axis.

Abstract: A conduit system is described for providing fresh air to aircraft positioned on the ground. The conduit system includes self-similar conduit sections having a female or connection end in a male or insertion end. The conduit sections may be back-compatible with existing fresh air conduits. The connection end forms sides or flaps joined by integral flexible bellows or gussets. The connection end thus forms a closed ring. The male end may be secured within the connection end by means of hook-and-loop fastener material and the connection end may be closed over the male end. The connection end is then completely closed by securement of extension tabs to an exterior surface of the connection end, thereby collapsing the integral bellows.