RONALD ALAN ROSSWAY
Pilots in Denver, CO

6073973, Jun 13, 2000

Apr 30, 1998

9/070229

Ronald W. Boscaljon - Denver CO
Ronald A. Rossway - Aurora CO
David E. Jewell - Golden CO
Eric Hazelwood - Divide CO

Stanley Aviation Corporation - Aurora CO

F16L 3500

285 81

In the first embodiment, a coupling assembly is provided wherein the inner peripheral diameter of an annular spring is sized to be threadably received over the threads of a coupler and is held in a recess formed by the ends of threads and the edge of a shoulder. This structure minimizes the diameter of the annular spring and lock ring to minimize both the size and weight of coupling assembly. Additionally, it provides a quick connect, quick disconnect coupling and has a peripheral stripe to provide a visual indication of its connected or disconnected status. In the second embodiment, a wavy spring is split which allows its diameter to be temporarily enlarged so that it can be received over the threads of the coupler and then spring back to its original smaller diameter so that it is held in a recess formed by the ends of the threads and a coupler flange. This structure also minimizes the diameter of the annular spring and lock ring to minimize both the size and weight of coupling assembly. This structure also provides a quick connect, quick disconnect coupling and has an indicator stripe to identify whether or not the coupler is in locked position.

6292999, Sep 25, 2001

Sep 11, 2000

9/658975

Ronald A. Rossway - Aurora CO
Robert F. Hatch - Aurora CO
Behzad B. Suroosh - Evergreen CO

Stanley Aviation Corporation - Aurora CO

B23Q 700

29559

An aircraft engine shipping system includes a frame assembly for supporting the aircraft engine, and a cradle assembly mounted on the frame assembly for securing the aircraft engine to the frame assembly. The frame assembly includes shock absorbers to provide continual shock absorption to an aircraft engine loaded thereon. The shipping system may be configured in either a truck or air transport mode. In the truck transport mode, the aircraft engine is secured to the cradle assembly by way of an aft ring which attaches to the aft portion of the aircraft, and a pair of cradle arms which attach to the forward portion of the aircraft engine. In the air transport mode, the aircraft engine is attached to the cradle assembly by way of the aft ring, and a forward ring which attaches directly to the fan of the aircraft engine. In the air transport mode, the cradle arms are disconnected from the aircraft engine and rotated away from the engine in a stowed position. While in the air transport mode, the aircraft engine may be rotated wherein the forward and aft rings cooperate to achieve rotation of the aircraft engine.

6298536, Oct 9, 2001

Sep 19, 2000

9/665551

Ronald A. Rossway - Aurora CO
Robert F. Hatch - Aurora CO
Behzad B. Suroosh - Evergreen CO

Stanley Aviation Corporation - Aurora CO

B25B 2714

292811

An aircraft engine shipping system includes a frame assembly for supporting the aircraft engine, and a cradle assembly mounted on the frame assembly for securing the aircraft engine to the frame assembly. The frame assembly includes shock absorbers to provide continual shock absorption to an aircraft engine loaded thereon. The shipping system may be configured in either a truck or air transport mode. In the truck transport mode, the aircraft engine is secured to the cradle assembly by an aft ring which attaches to the aft portion of the aircraft, and a pair of cradle arms which attach to the forward portion of the aircraft engine. In the air transport mode, the aircraft engine is attached to the cradle assembly by the aft ring, and a forward ring which attaches directly to the fan of the aircraft engine. In the air transport mode, the cradle arms are disconnected from the aircraft engine and rotated away from the engine in a stowed position. While in the air transport mode, the aircraft engine may be rotated wherein the forward and aft rings cooperate to achieve rotation of the aircraft engine.

6050609, Apr 18, 2000

Apr 30, 1998

9/070230

Ronald W. Boscaljon - Denver CO
Ronald A. Rossway - Aurora CO
David E. Jewell - Golden CO

Stanley Aviation Corporation - Aurora CO

F16L 3500

285 81

A first coupling member has a peripheral facing surface with a pair of annular slots, each of a different length and width. A second coupling member has a lock ring longitudinally slidable thereon with a facing surface having a pair of annular raised locking tabs sized to correspond to the respective annular slots. A resilient annular spring mounted within the lock ring urges it toward the first coupling member so that the locking tabs engage their respective slots when the coupling is tightened to a predetermined extent during rotation in the locking direction to releasably and positively lock the coupling. An indicator stripe on the peripheral edge of the first coupling member is exposed before the locking tabs and slots are engaged. Alignment between the respective locking tabs and slots allows longitudinal movement of the lock ring so that it covers the indicator stripe. One of the coupling members has a peripheral groove and two angularly spaced longitudinal keyways of differing widths which intersect the peripheral groove.

5871239, Feb 16, 1999

Oct 31, 1996

8/741647

Ronald W. Boscaljon - Denver CO
Ronald A. Rossway - Aurora CO
David E. Jewell - Golden CO

Stanley Aviation Corporation - Aurora CO

F16L 3500

285 81

A threaded coupling assembly is provided for interconnecting the ends of first and second fluid-carrying conduit members in fixed releasably locking relationship. First and second coupling members are circumferentially engageable with the ends of the conduit members to hold them in fluid communication. The coupling members are rotatable in a locking direction and in an opposite unlocking direction. The first coupling member has a peripheral facing surface with a pair of annular slots, each of a different length and width. The second coupling member has a lock ring longitudinally slidable thereon with a facing surface having a pair of annular raised locking tabs. Each locking tab is of a predetermined height but of a different length and width which corresponds to the respective length and width of the annular slots. A resilient annular spring urges the lock ring toward the first coupling member so that the locking tabs engage their respective slots when the coupling is tightened to a predetermined extent during rotation in the locking direction to releasably and positively lock the coupling. An indicator stripe is provided on the peripheral edge of the first coupling member which is exposed before the locking tabs and slots are engaged.

6000903, Dec 14, 1999

Jul 7, 1997

8/888688

Robert F. Hatch - Aurora CO
Ronald A. Rossway - Aurora CO
William J. Campion - Westminster CO

Stanley Aviation Corporation - Aurora CO

B65D 8568

414778

A fan shipping frame includes a frame assembly for supporting a loaded fan section of a jet aircraft engine. A plurality of caster assemblies attached to the shipping frame provide locomotive capability and adjustable height positioning so that a loaded fan section may be transferred onto the appropriate transport aircraft or vehicle. Rail members mounted on the frame assembly are alignable with rail members of a fan dolly so that the fan section may be directly transferred from the fan dolly onto the shipping frame. A template integral with the shipping frame enables the fan section to be mounted thereon. A platform assembly rotatably mounted to the shipping frame may be deployed to enable the fan section to be tilted or tipped from a vertical transport position to a horizontal transport position wherein the shipping frame may be transported in either position. A storage container mounted on the shipping frame stores the removed fan blades of the fan section in either position. In one embodiment, a telescoping template support group is provided enabling the template to be raised or lowered so that it is able to readily connect to fan sections which have differing heights when mounted to structures such as the fan dolly.

6170141, Jan 9, 2001

Sep 25, 1998

9/160739

Ronald A. Rossway - Aurora CO
Robert F. Hatch - Aurora CO
Behzad B. Suroosh - Evergreen CO

Stanley Aviation Corporation - Aurora CO

B25B 2714

292811

An aircraft engine shipping system includes a frame assembly for supporting the aircraft engine, and a cradle assembly mounted on the frame assembly for securing the aircraft engine to the frame assembly. The frame assembly includes shock absorbers to provide continual shock absorption to an aircraft engine loaded thereon. The shipping system may be configured in either a truck or air transport mode. In the truck transport mode, the aircraft engine is secured to the cradle assembly by means of an aft ring which attaches to the aft portion of the aircraft, and a pair of cradle arms which attach to the forward portion of the aircraft engine. In the air transport mode, the aircraft engine is attached to the cradle assembly by the aft ring the aft ring, and a forward ring which attaches directly to the fan of the aircraft engine. In the air transport mode, the cradle arms are disconnected from the aircraft engine and rotated away from the engine in a stowed position. While in the air transport mode, the aircraft engine may be rotated wherein the forward and aft rings cooperate to achieve rotation of the aircraft engine.