Dwight R Schaeffer

US Patent:

6587056, Jul 1, 2003

Filed:

Mar 31, 2000

Appl. No.:

09/540103

Inventors:

Charles R. Fraser - Kent WA
Robert W. Metzger - Marysville WA
Marshall T. Okamoto - Seattle WA
Dwight R. Schaeffer - Mercer Island WA
Richard A. Bohlander - Snohomish WA
Toan D. Le - Seattle WA
Barrie W. Hughlock - Redmond WA
Richard M. Schatz - Renton WA
Rex McCleary - Everett WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

G08B 2100

US Classification:

340945, 341 22, 341 32, 336130, 361680, 361697, 361704, 361707, 361714, 361748, 361753, 361760, 200 6139, 200 51 R, 200 11 R, 345156, 345168, 345184

Abstract:

A conventional light plate for a systems control panel is mounted on a machined front plate which, in turn, is maintained a predetermined uniform distance from a front printed wiring assembly (PWA). A plurality of systems control devices including one or more of switches (toggle switches, rotary switches, push button switches), rheostats and annunciators are mounted on the front plate and front PWA. Each of the systems control devices has one or more solid state elements mounted on the PWA. For example, the switches carry small magnets which, by manipulation of operating switch levers or knobs, move into and out of close proximity to magnet sensitive switching devices mounted on the front PWA.

US Patent:

6924744, Aug 2, 2005

Filed:

Dec 23, 2002

Appl. No.:

10/329111

Inventors:

Richard A. Bohlander - Snohomish WA, US
Robert W. Metzger - Marysville WA, US
Dwight R. Schaeffer - Mercer Island WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G08B005/22

US Classification:

34081545, 3408154, 340473, 340908, 362800, 362812

Abstract:

A Light Emitting Diode (LED) indicator that more efficiently dissipates heat generated by LEDs and other circuit components is provided. The LED indicator includes a housing and a printed circuit board contained within the housing. The printed circuit board includes first and second sides with two or more LEDs attached to the first and second sides of the printed circuit board and a regulating circuit for regulating current supplied to the LEDs. The regulating circuit includes a linear voltage regulator. The printed circuit board includes first and second thermal dissipation sections. The first thermal dissipation section is thermally connected with the two or more LEDs and the second thermal dissipation section is thermally connected with the linear voltage regulator. The housing is at least partially lined with a plurality of reflectors for reflecting light generated by the LEDs through a lens.

US Patent:

7327283, Feb 5, 2008

Filed:

Aug 8, 2005

Appl. No.:

11/199043

Inventors:

Paul W. Bandy - Kent WA, US
Darrell W. Gaston - Everett WA, US
Toan D. Le - Lynnwood WA, US
Dwight R. Schaeffer - Mercer Island WA, US
Robert W. Metzger - Marysville WA, US
Dai H. Pham - Bellevue WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G08B 21/00

US Classification:

340945, 340971, 34081545

Abstract:

An integrated communication system in an aircraft is provided. The system includes a plurality of solid state flight deck modules in an integrated flight deck panel, wherein the solid state flight deck modules include a microcontroller for interfacing with at least one data bus controller via a local bus; and a light emitting diode (LED) module for controlling backlit illumination of the integrated flight deck panel. The controller sends information to plural solid state flight deck modules via local buses and uses a system bus to communicate with aircraft subsystems. The controller also uses a central power supply module to supply regulated power to the plural solid state flight deck modules. Furthermore, at least one solid state flight deck module includes an integrated panel brightness control module, master brightness control module and/or a master dim and test control module.

US Patent:

8398025, Mar 19, 2013

Filed:

Jan 24, 2005

Appl. No.:

11/041616

Inventors:

Mitchell J Piorkowski - Mill Creek WA, US
Paul W Bandy - Kent WA, US
Binh C Truong - Kirkland WA, US
Dwight R Schaeffer - Mercer Island WA, US
Shannon J Kupfer - Kirkland WA, US
Steven D Flickinger - Arlington WA, US
Julie M Shinn - Mukilteo WA, US
James J Johnson - Snohomish WA, US
Steven L Wehr - Everett WA, US
Mark E Smith - Renton WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/14
B64D 11/00

US Classification:

2441295, 2441185

Abstract:

A security system adapted for use on an aircraft to prevent unauthorized access into a cockpit area of the aircraft via a cockpit door. The system includes a keypad accessible by individuals in a cabin area of the aircraft. A logic system is in communication with the keypad and also with a switch disposed inside the cockpit. Occupants of the cockpit, via the switch, have the ability to manually unlock the cockpit door, to deny the request for entry, or to do nothing, in which case the door will be automatically unlocked after the expiration of a predetermined time interval. A pressure sensor in communication with the controller allows the electronic door locking member to be automatically overridden, and the door immediately opened, in the event of a decompression condition occurring in the cockpit.

US Patent:

20030173458, Sep 18, 2003

Filed:

Mar 18, 2002

Appl. No.:

10/100227

Inventors:

Paul Bandy - Kent WA, US
Darrell Gaston - Everett WA, US
Binh Truong - Kirkland WA, US
Dwight Schaeffer - Mercer Island WA, US
Shannon Kupfer - Kirkland WA, US

International Classification:

B64D011/00
B64D013/00

US Classification:

244/118500

Abstract:

A security system adapted for use on an aircraft to prevent unauthorized access into a cockpit area of the aircraft via a cockpit door. The system includes a keypad accessible by individuals in a cabin area of the aircraft. A logic system is in communication with the keypad and also with a switch disposed inside the cockpit. Occupants of the cockpit, via the switch, have the ability to manually unlock the cockpit door, to deny the request for entry, or to do nothing, in which case the door will be automatically unlocked after the expiration of a predetermined time interval. No amount of tampering with the keypad or destruction of the keypad can unlock the cockpit door if the cockpit occupants decide to deny a request for entry via appropriate positioning of the switch. A pressure sensor in communication with the controller allows the door to be automatically unlocked in the event of a decompression condition occurring in the cockpit.

US Patent:

20050218266, Oct 6, 2005

Filed:

May 13, 2005

Appl. No.:

11/128809

Inventors:

Paul Bandy - Kent WA, US
Darrell Gaston - Everett WA, US
Binh Truong - Kirkland WA, US
Dwight Schaeffer - Mercer Island WA, US
Shannon Kupfer - Kirkland WA, US
Steven Flickinger - Arlington WA, US
Steven Wehr - Everett WA, US
James Johnson - Snohomish WA, US
Julie Shinn - Mukilteo WA, US
Mark Smith - Renton WA, US

International Classification:

B64D011/00

US Classification:

244118500

Abstract:

A security system adapted for use on an aircraft to prevent unauthorized access into a cockpit area of the aircraft via a cockpit door. The system includes a keypad accessible by individuals in a cabin area of the aircraft. A logic system is in communication with the keypad and also with a switch disposed inside the cockpit. Occupants of the cockpit, via the switch, have the ability to manually unlock the cockpit door, to deny the request for entry, or to do nothing, in which case the door will be automatically unlocked after the expiration of a predetermined time interval. The switch further provides a cut-off switch which enables the power to be removed from the system if necessary. In addition, a display system may be employed to notify the occupants of the cockpit that entry into the cockpit has been requested.

US Patent:

56951566, Dec 9, 1997

Filed:

May 15, 1995

Appl. No.:

8/441284

Inventors:

Guner Firuz - Bellevue WA
Dwight R. Schaeffer - Mercer Island WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

G05D 108

US Classification:

244180

Abstract:

Aircraft input signals of selected altitude (h. sub. s), selected vertical speed (h. sub. s), current altitude (h), current vertical speed (h), current pitch attitude (. theta. ), current normal acceleration (N. sub. z) and current pitch rate (Q) are processed to produce an elevator command (. delta. sub. e) that will result in a smooth vertical transition of the aircraft for various autopilot vertical maneuvers, including altitude capture and hold, glideslope capture and hold, and flare control.