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John W Standley, Age 70Pahrump, NV

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Known as:
John Wayne Standley John W Standlee John W Stanfley
Related to:
Sammie L Gallimore 80

John Standley Phones & Addresses

Pahrump, NV

Rancho Cucamonga, CA

386 Emma Ave, Ventura, CA 93003 (805) 658-7896

11155 Citrus Dr #75, Ventura, CA 93004 (805) 658-7896

Las Vegas, NV

Renton, WA

Camarillo, CA

7137 Sixshooter Dr, Las Vegas, NV 89119

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Work

Company: United states air force May 2009 Position: Accounting technician

Education

School / High School: Citrus College- Glendora, CA 2006 Specialities: Emergency Medical Technician

Mentions for John W Standley

John Standley resumes & CV records

Resumes

John Standley Photo 32

John Standley

John Standley Photo 33

Certified Medical Assistant

Work:

Certified Medical Assistant
John Standley Photo 34

John Standley

John Standley Photo 35

John Standley

John Standley Photo 36

John Standley - Glendale, AZ

Work:
United States Air Force May 2009 to 2000
Accounting Technician Chipotle Mexican Grill - Glendora, CA Jul 2006 to Apr 2009
Crew Member
Education:
Citrus College - Glendora, CA 2006 to 2007
Emergency Medical Technician Sierra High School Glendora - Glendora, CA 2002 to 2006

Publications & IP owners

Us Patents

Systems And Methods For Controlling Aircraft Flaps And Spoilers

US Patent:
7891611, Feb 22, 2011
Filed:
Dec 28, 2007
Appl. No.:
11/966361
Inventors:
Neal V. Huynh - Bellevue WA, US
Robert J. Bleeg - Mercer Island WA, US
Ralph Scott Pepper - Everett WA, US
John A. Standley - Seattle WA, US
Brian L. Bocksch - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 3/50
US Classification:
244215, 244217, 244213
Abstract:
Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned at least partially aft of the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.

Systems And Methods For Controlling Aircraft Flaps And Spoilers

US Patent:
2006017, Aug 10, 2006
Filed:
Feb 4, 2005
Appl. No.:
11/051738
Inventors:
Neal Huynh - Seattle WA, US
Robert Bleeg - Seattle WA, US
Ralph Pepper - Seattle WA, US
John Standley - Seattle WA, US
Brian Bocksch - Seattle WA, US
International Classification:
B64C 9/22
US Classification:
244212000
Abstract:
Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.

Methods And Apparatus For Integrating Rotary Actuators In Flight Control Systems

US Patent:
2018022, Aug 9, 2018
Filed:
Mar 28, 2018
Appl. No.:
15/938077
Inventors:
- Chicago IL, US
John A. Standley - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 13/30
Abstract:
Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

Methods And Apparatus For Integrating Rotary Actuators In Flight Control Systems

US Patent:
2016022, Aug 11, 2016
Filed:
Oct 31, 2014
Appl. No.:
14/529694
Inventors:
- Chicago IL, US
John A. Standley - Seattle WA, US
Assignee:
THE BOEING COMPANY - Chicago IL
International Classification:
B64C 13/30
B64C 9/00
Abstract:
Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

Systems, Methods, And Apparatus For Rotary Vane Actuators

US Patent:
2016003, Feb 4, 2016
Filed:
Jul 31, 2014
Appl. No.:
14/448785
Inventors:
- Chicago IL, US
Steven P. Walker - Arlington WA, US
Michael K. Klein - Bothell WA, US
John A. Standley - Seattle WA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
F01D 17/14
Abstract:
Systems, methods, and devices are disclosed for implementing hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Possible Relatives

Earl D Standley  Gary S Standley  Gerald Standley  Harry A Standley  Jason J Standley  Jeffrey M Standley  Jennifer R Standley  John J Last  John J Stan  John C Stanaway 

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