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Mark Kenyon Venskus

from Derby, KS
Age ~70
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Also known as:
Mark K Venskus, Mark Kenyon Vanskus, Mkark K Venskus
Phone and address:
2338 N Persimmon St, Derby, KS 67037
Related to:
James Adler, 96Julia DreilingJulia Dreiling, 43Michael Wanklyn, 38James Dobbs
Connected to:
Adrienne B Venson, 70Connie Venson, 34Daniel Venson, 41Joe E Venson, 38Marcus A Venson, 36Michael D Venson, 48Sheila M Venson, 70Tasha D Venson, 43Tony L Venson, 37Sasha M Venstone, 34

Mark Venskus Phones & Addresses

  • 2338 N Persimmon St, Derby, KS 67037
  • 1303 Ravenwood St, Derby, KS 67037 (316) 788-5444
  • 436 N Valley Rd, Belle Plaine, KS 67013 (620) 455-2578
  • Wichita, KS

Resumes

Resumes

Mark Venskus Photo 1

Mark Venskus

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Location:
2338 north Persimmon St, Derby, KS 67037
Industry:
Aviation & Aerospace
Work:
Spirit Aerosystems Jun 2005 - Nov 2014
Factory Consultant
Education:
Wichita State University 1972 - 1983
Bachelors, Management, Aviation
Skills:
Catia
Aerospace
Aircraft
Six Sigma
Lean Manufacturing
Composites
Process Improvement
Program Management
Systems Engineering
Aviation
Root Cause Analysis
Engineering
Continuous Improvement
Manufacturing
Value Stream Mapping
Engineering Management
Quality Management
Manufacturing Engineering
Kaizen
Earned Value Management
Integration
Cross Functional Team Leadership
Business Process Improvement
Certifications:
Private Pilot License
Mark Venskus Photo 2

Factory Consultant At Spirit Aerosystems, Inc.

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Position:
Factory Consultant at Spirit Aerosystems, Inc.
Location:
Wichita, Kansas Area
Industry:
Aviation & Aerospace
Work:
Spirit Aerosystems, Inc.
Factory Consultant

Publications

Us Patents

Virtual Production Testing Of Large Integrated Products

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US Patent:
8326959, Dec 4, 2012
Filed:
Sep 4, 2009
Appl. No.:
12/554526
Inventors:
Mark Kenyon Venskus - Derby KS, US
Assignee:
Spirit AeroSystems, Inc. - Wichita KS
International Classification:
G06F 15/16
G01R 31/00
US Classification:
709223, 709224, 701 314, 702118, 702121, 702123, 714 44, 714E11024, 714741, 714742, 370401, 370251
Abstract:
A communications system and method for testing components of an aircraft via Ethernet. The communications system may comprise one or more Ethernet links having software and hardware controls for timing, buffering, and messaging, and a dedicated Ethernet line. The Ethernet links may be configured to communicably link sections of a central communication system of the aircraft, each section being part of a separate aircraft component. The Ethernet links may also communicably link the sections with various databases over the Ethernet line. The databases may comprise loadable software, archived testing data, configuration data, and/or diagnostic data. Any of the central communication system sections and the databases may be located at geographically distant locations from each other, such as at separate production sites. The communications system may allow the aircraft components to test each other, or essentially for the aircraft to test itself prior to its components being physically joined together.

System And Method For Assembling Aircraft Components

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US Patent:
20130019446, Jan 24, 2013
Filed:
Jul 20, 2012
Appl. No.:
13/553946
Inventors:
Mark Kenyon Venskus - Derby KS, US
Troy Lynn Wampler - Derby KS, US
Stephen Eldred Walters - Wichita KS, US
Clark Ray Miller - Wichita KS, US
Michael Arthur Champa - Clearwater KS, US
Edwin H. Fenn - Wichita KS, US
David Scott Anderson - Derby KS, US
Assignee:
SPIRIT AEROSYSTEMS, INC. - Wichita KS
International Classification:
B23Q 17/00
US Classification:
2940709
Abstract:
A system and method for assembling a 360-degree section of an aircraft fuselage or nacelle by properly positioning a plurality of assembly panels relative to a machine datum representing an assembly-level datum schema, drilling full-sized holes proximate to a second skin edge of the panels with the machine, net-trimming a second edge of the panels with the machine, then using the full-sized holes proximate to the second skin edges as alignment features to properly orient and attach pairs of the panels together proximate to first skin edges, opposite of the second skin edges with an auxiliary machine, forming panel pairs. Control systems may be installed into the panel pairs separately and independently, then the panel pairs may be joined together, aligning the full-sized holes proximate to the second edges, and inserting fasteners through the aligned full-sized holes proximate to the second skin edges.
Control profile
Mark Kenyon Venskus from Derby, KS, age ~70 Get Report