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Lyndon C Lamborn

from Shreveport, LA
Age ~66
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Also known as:
Lyndon Claudius Lamborn, Linden Lamborn
Related to:
Nancy M LambornStirling Shaw, 62Joseph LambornLarry E Moore, 71
Connected to:
Andrew B Lamborn, 66Andrew N Lamborne, 51Beckie L Lamborn, 63Dianne L Lamborn, 59Lee R Lamborn, 71Marianne M Lamborne, 75Mike E Lamborn, 64Roslyn A Lamborn, 80Scott L Lamborn, 62Shawn E Lamborn, 55

Lyndon Lamborn Phones & Addresses

  • Shreveport, LA
  • Logan, UT
  • Hamilton, MT
  • Kissimmee, FL
  • 8238 Mawson Rd, Mesa, AZ 85207 (480) 380-5075
  • Prescott, AZ
  • Missoula, MT
  • Maricopa, AZ

Emails

m***[email protected]

Professional Records

License Records

Lyndon C Lamborn

Address:
Logan, UT
License #:
165159-9925 - Expired
Category:
Engineer/Land Surveyor
Issued Date:
Jan 1, 1911
Expiration Date:
Dec 31, 1999
Type:
Engineer in Training - Obsolete

Business Records

Name / Title
Company / Classification
Phones & Addresses
Lyndon C Lamborn
Manager, Principal
PI BOOKS LLC
Whol Books/Newspapers
8238 E Mawson Rd, Mesa, AZ 85207

Publications

Us Patents

Method For Connecting A Tension-Torsion Strap

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US Patent:
8122586, Feb 28, 2012
Filed:
Nov 18, 2008
Appl. No.:
12/272957
Inventors:
Neal W. Muylaert - Apache Junction AZ, US
Lyndon Claudius Lamborn - Mesa AZ, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B23P 17/04
US Classification:
29592, 298972, 298973, 29428, 298896, 416134 A, 416135, 416168 R, 416158, 416141, 416 87, 416 89
Abstract:
A method for connecting a tension-torsion strap. The method includes sliding a sleeve into an arm of a hub; aligning holes in the sleeve with holes in the hub; installing a bushing in each aligned hole in the sleeve; sliding a first end of the tension-torsion strap through the sleeve; and placing a pin through the bushings and the tension-torsion strap.

Rigid Rotor Assembly For Folding Helicopter Blades

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US Patent:
8192159, Jun 5, 2012
Filed:
Dec 2, 2008
Appl. No.:
12/326400
Inventors:
Neal W. Muylaert - Apache Junction AZ, US
Lyndon Claudius Lamborn - Mesa AZ, US
Mark Stephen Durst - Laguna Beach CA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 11/28
B64C 27/50
US Classification:
416 1, 416134 A, 416134 R, 416142
Abstract:
Described herein is a rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position. The rigid rotor assembly includes a base including a shaft extending therethrough, a first spindle configured to engage the shaft, and a second spindle configured for placement onto the shaft. The second spindle is operable to maintain a first position with respect to the first spindle via an attachment mechanism therebetween, the second spindle further operable to maintain a second position with respect to the first spindle via the attachment mechanism.

Sculptured Throat Spool

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US Patent:
8235665, Aug 7, 2012
Filed:
Aug 7, 2008
Appl. No.:
12/187599
Inventors:
Neal W. Muylaert - Apache Junction AZ, US
Lyndon C. Lamborn - Mesa AZ, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 11/12
F01D 5/00
B21K 3/04
US Classification:
416135, 298896
Abstract:
A sculpted throat spool of a tension-torsion strap assembly is disclosed. Using the sculpted throat spool minimizes the stress riser typically present at the edge of the spool when a tension-torsion strap is articulated.

Ultra-Light Weight Self-Lubricating Propeller Hub

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US Patent:
8262358, Sep 11, 2012
Filed:
May 26, 2009
Appl. No.:
12/472201
Inventors:
Neal W. Muylaert - Apache Jct AZ, US
Lyndon C. Lamborn - Mesa AZ, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B63H 1/06
US Classification:
416134A, 416174
Abstract:
A propeller assembly includes a rotatable hub having a center metal hub portion and an outer composite hub portion. A set of composite propeller blades are mounted for pitch control rotation on the hub by a set of dry bearings.

Rotor Balance Device And Method

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US Patent:
8267661, Sep 18, 2012
Filed:
Jan 23, 2008
Appl. No.:
12/018596
Inventors:
Lyndon Lamborn - Mesa AZ, US
Neal Muylaert - Apache Junction AZ, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 27/46
US Classification:
416144, 415119
Abstract:
A rotor balance fitting to balance an aircraft rotor includes a ring, bore, and cup. The ring includes an inner surface configured to mate with an outer surface of a blade for the aircraft rotor. The bore is disposed through the ring and configured to receive a blade pin that passes perpendicularly through an axis of the blade and secures the blade to the rotor. The cup is disposed in the ring and is configured to secure a weight.

Bi-Axial Compliant Bearing

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US Patent:
8568100, Oct 29, 2013
Filed:
Dec 9, 2008
Appl. No.:
12/331272
Inventors:
Neal W. Muylaert - Apache Junction AZ, US
Lyndon Claudius Lamborn - Mesa AZ, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B63H 7/00
B64C 11/06
F01D 5/00
US Classification:
416174, 416205, 4151701
Abstract:
Embodiments of a bi-axial compliant bearing assembly and methods of assembling the bi-axial compliant bearing assembly are disclosed. A bi-axial compliant bearing assembly employs a transition bearing race. The transition bearing race comprises a cylindrical surface. The cylindrical surface is configured to rotatably engage a rotational bearing element and to slidably engage the rotational bearing element along an axis. The transition bearing race also includes a spherically-compliant surface. The spherically-compliant surface is configured to engage a spherically-compliant element and to enable the spherically-compliant element to rotate transversely to the axis.

Ultra-Light Weight Self-Lubricating Propeller Hub

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US Patent:
8632307, Jan 21, 2014
Filed:
Aug 17, 2012
Appl. No.:
13/588796
Inventors:
Lyndon C. Lamborn - Mesa AZ, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 11/02
B64C 11/04
US Classification:
416134A, 416244 A
Abstract:
A propeller assembly includes a rotatable hub having a center metal hub portion and an outer composite hub portion. A set of composite propeller blades are mounted for pitch control rotation on the hub by a set of dry bearings.

Tail Rotor Hub

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US Patent:
20090136351, May 28, 2009
Filed:
Nov 28, 2007
Appl. No.:
11/946817
Inventors:
Neal W. Muylaert - Apache Junction AZ, US
Lyndon C. Lamborn - Mesa AZ, US
Assignee:
THE BOEING COMPANY - Chicago IL
International Classification:
F01D 5/30
US Classification:
416219 R
Abstract:
A tail rotor hub system and methods are disclosed. In one embodiment, the system includes a helicopter fuselage connected to a tail rotor assembly that holds tail blades. The assembly includes an elongated tail rotor housing and an elongated blade root fitting that rotates within the housing. A tension torsion strap is connected at one end to the housing and is connected at its other end to the blade root fitting to hold the blade root fitting in the housing when the housing rotates. Coupled between outside walls of the blade root fitting and inside walls of the housing are self lubricating bearings to enable the blade root fitting to rotate within the housing to change the pitch of the tail blades.
Control profile
Lyndon C Lamborn from Shreveport, LA, age ~66 Get Report