| |
| United States Patent
|
7,032,862 |
| Landes , et al. |
April 25, 2006 |
Method and system for mounting radio avionics
Abstract
A mounting bar system permitting infinite adjustability in
mounting avionics-components trays and Dzus-mounted avionics in at
least one aircraft cockpit instrument panel assembly. Each mounting
bar is slotted along its longitudinal axis. The slot is made to
include the shape of a T such that a wider channel exists below the
opening of the slot. Spring-loaded nut assemblies set to receive
mounting screws from the avionics-components trays are fit within
the T slot. Friction provided by the spring holds the nut assembly
at any desired location within the T slot. As the nut assembly can
be positioned at any location within the T slot, the mounting bar
can readily be adjusted to support any avionics-components tray
intended for at least one aircraft cockpit instrument panel
assembly.
| Inventors: |
Landes; Mark James
(Sylmar, CA), L'Esperance; Victor D. (Claremont, CA)
|
| Appl. No.:
|
10/391,039 |
| Filed: |
March 17, 2003 |
Related U.S. Patent Documents
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Application Number |
Filing Date |
Patent Number |
Issue Date |
|
60394119 |
Jul., 2002 |
|
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60365482 |
Mar., 2002 |
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| Current U.S.
Class: |
244/129.1
; 211/103; 211/126.15; 211/187; 211/207; 248/125.1 |
| Current
International Class: |
B64C
1/00 (20060101); A47H 1/00 (20060101) |
| Field of
Search: |
211/26,103,126.15,187,207 248/125.1,295.11 244/1R,129.1 |
References Cited
[Referenced By]
U.S. Patent
Documents
Primary Examiner: Eldred; J. Woodrow
Attorney, Agent or Firm:
Stoneman Law Offices, Ltd. Stoneman; Martin L.
Parent Case Text
CROSS-REFERENCE TO RELATED APPLICATIONS
The present application is related to and claims priority from
applicant's prior U.S. Provisional Application Ser. No. 60/394,119,
filed Jul. 3, 2002, entitled "METHOD AND SYSTEM FOR MOUNTING RADIO
AVIONICS", and from applicant's prior U.S. Provisional Application
Ser. No. 60/365,482, filed Mar. 18, 2002, entitled "METHOD AND
SYSTEM FOR MOUNTING RADIO AVIONICS", the contents of which are
herein incorporated by reference and are not admitted to be prior
art with respect to the present invention by their mention in this
cross-reference section.
Claims
The invention claimed is:
1. A system for mounting in at least one aircraft cockpit instrument
panel assembly at least one avionics-components tray having at least
one side, at least one mounting hole in the side, and at least one
mounting connector for making a connection through the mounting
hole, comprising, in combination: a) at least one support bar,
comprising at least one longitudinal axis and at least one first
longitudinal face, structured and arranged to support the at least
one avionics-component tray; b) at least one attacher adapted to
attach the at least one avionics-component tray to said at least one
support bar; c) wherein said at least one attacher comprises at
least one receiver adapted to receive the at least one mounting
connector; d) at least one slide structured and arranged to permit
slicing said at least one attacher within said at least one support
bar; e) wherein said at least one slide comprises at least one
holder adapted to slideably hold said at least one attacher within
said at least one support bar; and f) at least one connection system
structured and arranged to nonslideably connect said at least one
attacher within said at least one support bar when the at least one
mounting connector is connected with said at least one receiver; g)
wherein, said at least one slide comprises at least one
T-shaped-cross-section slot portion, of said at least one support
bar, defining at least one continuous slot opening portion within
said at least one first longitudinal face of said at least one
support bar; h) wherein said at least one support bar comprises at
least one additional slot portion adapted to receive at least one
mounting connector portion; and i) wherein said at least one
additional slot portion and said at least one T-shaped-cross-section
slot portion, in combination, comprise at least one
plus-shaped-cross-section slot portion.
2. The system according to claim 1 wherein each said at least one
attacher comprises, in combination: a) at least one retaining
bracket; b) at least one threaded nut in said retaining bracket; c)
at least one resilient spring in said retaining bracket; d) wherein
said at least one resilient spring is located between said at least
one retaining bracket and said at least one nut.
3. The system according to claim 2 wherein said holder is structured
and arranged so that said spring applies separation force between
said at least one retaining bracket and said at least one nut.
4. The system according to claim 3 wherein said support bar is
structured and arranged to removably attach to the cockpit
instrument panel assembly.
5. The system according to claim 4 wherein said at least one support
bar further comprises: a) at least one substantially rectangular
cross section; and b) at least one second longitudinal face; c)
wherein said at least one second longitudinal face is located
parallel to said at least one first longitudinal face.
6. The system according to claim 5 wherein: a) each said at least
one support bar further comprises at least two of said at least one
T-shaped-cross-section slot portions; b) at least one of said at
least two T-shaped-cross-section slot portions defines at least one
continuous slot opening portion within said at least one second
longitudinal face of said at least one support bar.
7. The system according to claim 5 wherein said at least one
continuous slot opening portion comprises at least one countersink
receiver adapted to receive at least one countersunk mounting hole
of the at least one avionics-component tray.
8. The system according to claim 5 wherein said wherein said at
least one support bar further comprises: a) at least one mountable
portion; and b) at least one mounting extension adapted to extend
said at least one mountable portion beyond the substantially
rectangular cross section.
9. The system according to claim 4 further comprising: a) at least
one quick-release adapter to adapt at least one quick-release
connector to said at least one attacher; b) wherein said at least
one quick-release adapter comprises i) at least one mount, to mount
at least one avionics-component compatible with the at least one
quick-release connector, in a position adjacent to said at least one
support bar, ii) at least one adjuster adapted to permit
substantially-transverse positional adjustment of said at least one
mount relative to said at least one longitudinal axis of said at
least one support bar, and iii) at least one mounting connector to
connect said at least one quick-release adapter to said at least one
attacher; and c) wherein said at least one mount comprises at least
one quick-release receiver adapted to receive and removably retain
the at least one quick-release fastener.
10. The system according to claim 9 wherein said at least one
quick-release receiver is adapted to receive a Dzus-type mounting
connector.
11. The system according to claim 9 wherein: a) said at least one
adjuster comprises at least one first interlocker; b) said at least
one mount further comprises at least one second interlocker; c) said
at least one erst interlocker and said at least one second
interlocker are structured and arranged to firmly interlock; and d)
said at least one first interlocker and said at least one second
interlocker, when interlocked, prevent relative movement between
said at least one adjuster and said at least one mount.
12. The system according to claim 11 wherein: a) at least one
portion of said at least one first interlocker comprises at least
one first interlocking detent; b) at least one portion of said at
least one second interlocker comprises at least one second
interlocking detent; and c) said first at least one interlocking
detents and said second at least one interlocking detents, when
meshed, prevent relative movement between said at least one adjuster
and said at least one mount; d) wherein meshing of said said first
and said second at least one interlocking detents prevents
substantially-transverse positional movement of said at least one
mount relative to the longitudinal axis of said at least one support
bar.
13. The system according to claim 10 further comprising: a) at least
one spacer adapted to fit between said at least one mount and said
at least one adjuster; b) wherein said at least one spacer permits
at least one Dzus-type avionics-component to be mounted in at least
one aircraft cockpit instrument panel assembly adapted to receive
the at least one avionics-components fray.
14. The system according to claim 4 further comprising: a) at least
one tray adjuster structured and arranged to permit positional
adjustment of the at least one avionics-component tray relative to
said at least one support bar; b) wherein said at least one tray
adjuster comprises, i) at least one engager adapted to engage at
least one portion of the at least one avionics-component tray; ii)
at least one cam adjuster structured adapted to adjust the position
of said at least one engager; iii) at least one mounting aperture to
permit passage of the at least one mounting connector; c) wherein
rotation of said at least one cam adjuster produces at least one
substantially-transverse movement, relative to said at least one
longitudinal axis of said at least one support bar, of both said at
least one engager and the at least one avionics-component tray.
15. The system according to claim 14 wherein: a) said at least one
engager comprises at least one essentially cylindrical member having
at least one central axis, at least one radius and at least one
outer circumference; b) said at least one engager further comprises
at least one rotation assister to assist in rotating said at least
one engager; and c) said at least one cam adjuster comprises said at
least one mounting aperture passing through said at least one
engager such that said at least one mounting aperture is
eccentrically located at a point adjacent to said at least one
central axis.
16. The system according to claim 15 further comprising: a) at least
one avionics-components tray; b) wherein said at least one
avionics-components tray comprises, i) at least one side, and ii) at
least one mounting hole in said at least one side.
17. The system according to claim 16 wherein said at least one
mounting hole is adapted to receive said at least one essentially
cylindrical member.
18. The system according to claim 15 wherein the at least one radius
of said at least one essentially cylindrical member is about
one-half inch.
19. A system for mounting in at least one aircraft cockpit
instrument panel assembly at least one avionics-components tray
having at least one side, at least one mounting hole in the side,
and at least one mounting connector for making a connection through
the mounting hole, comprising, in combination: a) at least one
support bar, comprising at least one longitudinal axis and at least
one first longitudinal face, structured and arranged to support the
at least one avionics-component tray; b) at least one attacher
adapted to attach the at least one avionics-component tray to said
at least one support bar; c) wherein said at least one attacher
comprises at least one receiver adapted to receive the at least one
mounting connector; d) at least one slide structured and arranged to
permit sliding said at least one attacher within said at least one
support bar; e) wherein said at least one slide comprises at least
one bolder adapted to slideably bold said at least one attacher
within said at least one support bar; f) at least one connection,
system structured and arranged to nonslideably connect said at least
one attacher within said at least one support bar when the at least
one mounting connector is connecting with said at least one
receiver; and g) at least one blanking cover adapted to cover unused
portions of the general aviation aircraft cockpit instrument panel;
h) wherein said at least one blanking cover comprises, i) at least
one filler panel to fill such unused portions, ii) at least one
retainer to removably retain said at least one filler panel on said
at least one support bar, iii) at least one adjuster to adjust the
position of said filler panel relative to the general aviation
aircraft cockpit instrument panel.
20. The system according to claim 19 wherein: a) said at least one
filler panel comprises a substantially planar member having at least
one front face and at least one rear face; b) said at least one
retainer comprises at least one spring loaded engager adapted to
removably engage said at least one support bar; c) said at least one
adjuster comprises at least one retainer holder, firmly coupled to
said at toast one rear face; and d) said at least one retainer
holder is adapted to adjustably hold said at least one retainer in
at least one selected position relative to said at least one front
face.
21. The system according to claim 20 wherein: a) said at least one
retainer holder comprises a plurality of holding apertures adapted
to receive and removably bold said at least one retainer; b) each
one of said plurality of holding apertures is uniquely positioned
relative to said at least one filler panel; and c) at least two of
said plurality of holding apertures are arranged to permit at least
one matching alignment of at least two of said at least one
retainers relative to said at least one front face.
22. The system according to claim 19 wherein said at least one
support bar comprises at least two of said at least one slides.
23. The system according to claim 19 wherein said at least one
support bar further comprises: a) at least one mountable portion;
and b) at least one mounting extension adapted to extend said at
least one mountable portion of said at least one support bar.
24. The system according to claim 19 wherein: a) said at least one
support bar comprises at least one contour structured and arranged
to match at least one contoured portion of the general aviation
aircraft cockpit instrument panel assembly.
25. A method of using, in at least one aircraft cockpit instrument
panel assembly, side mounting bars for mounting at least one
avionics-components tray having at least one side, at least one
mounting hale in the side, and at least one mounting connector for
making a connection through the mounting hole, comprising in
combination, the steps of: a) accessing at least one mounting bar
comprising at least one longitudinal slot portion holding at least
one unattached spring loaded slideably adjustable attacher; b)
selecting an unattached one of such at least one unattached spring
loaded slideably adjustable attacher; c) pressing such spring loaded
slideably adjustable attacher to release friction between such
spring loaded slideably adjustable attacher and such longitudinal
slot portion; d) moving such spring loaded slideably adjustable
attacher to a user preferred location within such longitudinal slot
portion; and e) releasing such spring loaded slideably adjustable
attacher within such longitudinal slot portion at such user
preferred location.
26. The method according to claim 25 further comprising the step of
attaching the at least one mounting connector of the at least one
avionics-components tray to such at least one spring loaded
slideably adjustable attacher.
27. The method according to claim 26 further comprising the steps
of: a) inserting at least one tray adjuster through the at least one
mounting hole; b) inserting the at least one mounting connector
through such at least one tray adjuster to loosely engage the at
least one mounting connector of the at least one avionics-components
tray to such at least one spring loaded slideably adjustable
attacher; c) adjusting such at least one tray adjuster to move the
at least one avionics-components tray to at least one user preferred
position; and d) tightening the at least one mounting connector to
firmly attach the at least one avionics-components tray to such at
least one spring loaded slideably adjustable attacher.
Description
BACKGROUND
The present invention relates generally to the installation and
mounting of radio avionics in aircraft. The principles of flight are
relatively simply thrust creates lift sufficient to overcome gravity
and drag. The tools necessary to actually pilot an aircraft are far
from simple. Weather may limit visibility, flights may be made at
night, and the distance of the flight may be such that it is
important to very carefully adhere to the federally-approved airways
and altitudes. Unseen in the first early airplanes, radios are now
perhaps the most important piece of equipment available to the
pilot. Radio communications play an essential part in the piloting
of aircraft, including, for example, spacecraft. Typically, aircraft
have a multiplicity of radio equipment enabling the pilot to
communicate with ground-based control operators, other aircraft,
VOR, and the like, to navigate along a flight route and to fly
within the Federal Airways of the United States and elsewhere.
It is generally appreciated that advances made in electronics and
computer technology are occurring at a rapid pace. It is therefore
not surprising that advances are being made in computerization
within the cockpits of aircraft as well, including, for example,
helicopters. As improved radio avionics equipment is developed, the
useful life of existing equipment grows ever shorter.
Understandably, pilots and owners of aircraft desire to make use of
newer components providing more features and abilities. The terms
"general aviation" and "general aviation aircraft" as used herein
are expressly intended to include such vehicles as helicopters,
commercial aircraft, military aircraft, spacecraft, both small and
large aircraft, and similar present and future vehicles requiring
avionics support.
The forces applied to an aircraft in its normal operation can be
rather severe. It is therefore important that equipment, especially
components used in flight and navigation, be properly secured within
the structural assembly most commonly identified as the instrument
panel. Installation of the radio avionics and similar components has
been facilitated by competitive market forces, driving manufacturers
to produce components to an unofficial size. More specifically, the
unofficial standard of sizing generally is applicable to the width
of the component so that it will fit between the supporting rails of
the cockpit instrument panel avionics rack. Width is, however, only
one dimension; and height and depth are far from standard. In most
instances, a mounting tray must first be installed into which the
component will be nested and further secured. As used herein, it is
understood and appreciated that the term "mounting rack" includes
the associated mounting boxes and mounting trays. Mounting trays are
typically specifically designed for each given component and cannot
accommodate new equipment. The process of upgrading avionics
equipment therefore frequently requires the removal of old and the
installation of new mounting trays within the mounting rack.
Typically, one or more mounting racks are incorporated within the
structure of the instrument panel. Today, these mounting racks
comprise vertical mounting rails specifically set for securing the
mounting trays. Typically, these rails are initially provided with a
set of vertically-repeating oval holes. Under conventional theory,
the installer simply places a slip-nut over the rail aligned with
the hole so that a screw set through the side of the mounting tray
will pass through the oval hole and into the slip nut, thus binding
the mounting tray rigidly to the mounting rail. As space is limited
in the cockpit, as well as for aesthetic appearances, it is desired
to place the mounting trays such that there are no gaps between
components. As a result, the mounting holes provided by the
manufacturer of the component's mounting tray does not always align
with the provided oval holes in the rails. Typically, a considerable
amount of grinding and drilling is therefore required by the
installer to properly position at least one hole in each rail at the
appropriate location required by the mounting tray within the rack.
Over time, as new mounting trays are installed for new components
with improved functions, the re-drilling and modification of the
support rails leads to considerable degradation in the structural
integrity of the mounting rails and rack. Breakage, bending, and
slipping of the components can result if the rails are modified too
extensively. Further, weakened rails may require the addition of
unplanned support affixed to the rear of the mounting tray to
alleviate stress on the weakened rails.
Thus, a great need exists for a mounting system capable of infinite
adjustment and re-usable fasteners that requires no modification,
drilling or grinding to accommodate current and future
avionics-components mounting trays.
OBJECTS OF THE INVENTION
It is a primary object and feature of this invention to fill the
above-mentioned needs. More specifically, it is an object and
feature of the present invention to provide a system and method for
installing and mounting radio avionics components that is infinitely
adjustable and re-usable.
Still another object and feature of the present invention is to
provide a system and method that is structurally sound and capable
of supporting increasingly heavy avionics components without
additional rear support.
A further object and feature of the present invention is to provide
a system and method that may be installed and employed easily in a
wide variety of general aviation aircraft.
Yet another object and feature of the present invention is to
provide a system and method that improves overall structural
integrity of the cockpit instrument panel.
Still another object and feature of the present invention is to
provide a system and method that may be upgraded if desired without
full replacement.
Yet another object and feature of the present invention is to
provide a system that accommodates two or more adjacent vertical
stacks of avionics components.
An additional object and feature of the present invention is to
provide a system that provides user-selected system adjustability.
Additionally, it is an object and feature of the present invention
to provide a system compatible with quick-release Dzus-type
fasteners.
SUMMARY OF THE INVENTION
In accordance with a preferred embodiment hereof, this invention
provides a system for mounting in a general aviation aircraft
cockpit instrument panel assembly at least one avionics-components
tray having at least one side, at least one mounting hole in the
side, and at least one mounting connector for making a connection
through the mounting hole, comprising, in combination: supporting
means for supporting the avionics-component tray; attaching means
for attaching the avionics-component tray to such supporting means;
wherein such attaching means comprises receiving means for receiving
the at least one mounting connector; sliding means for permitting
sliding of such attaching means within such supporting means;
wherein such sliding means comprises holding means for slideably
holding such attaching means within such supporting means; and
connecting means for nonslideably connecting such attaching means
within such supporting means when the at least one mounting
connector is connected with such receiving means.
In accordance with another preferred embodiment hereof, this
invention provides a system for mounting in a general aviation
aircraft cockpit instrument panel assembly at least one
avionics-components tray having at least one side, at least one
mounting hole in the side, and at least one mounting connector for
making a connection through the mounting hole, comprising, in
combination: at least one support bar, comprising at least one
longitudinal axis and at least one first longitudinal face,
structured and arranged to support the at least one
avionics-component tray; at least one attacher adapted to attach the
at least one avionics-component tray to such at least one support
bar; wherein such at least one attacher comprises at least one
receiver adapted to receive the at least one mounting connector; at
least one slide structured and arranged to permit sliding such at
least one attacher within such at least one support bar; wherein
such at least one slide comprises at least one holder adapted to
slideably hold such at least one attacher within such at least one
support bar; and at least one connection system structured and
arranged to nonslideably connect such at least one attacher within
such at least one support bar when the at least one mounting
connector is connected with such at least one receiver.
Moreover, it provides such a system wherein such at least one slide
comprises at least one T-shaped slot portion, of such at least one
support bar, defining at least one continuous slot opening portion
within such at least one first longitudinal face of such at least
one support bar. Additionally, it provides such a system wherein
such at least one support bar further comprises at least on end cap
adapted to cap at least one end portion of such at least one
T-shaped slot portion. Also, it provides such a system wherein: such
at least one support bar comprises at least one additional slot
portion adapted to receive at least one mounting connector portion;
and such at least one additional slot portion and such at least one
T-shaped portion, in combination, comprise at least one plus-shaped
slot portion. In addition, it provides such a system wherein each
such at least one attacher comprises, in combination: at least one
retaining bracket; at least one threaded nut in such retaining
bracket; at least one resilient spring in such retaining bracket;
wherein such at least one resilient spring is located between such
at least one retaining bracket and such at least one nut. And, it
provides such a system wherein such holder is structured and
arranged so that such spring applies separation force between such
at least one retaining bracket and such at least one nut. Further,
it provides such a system wherein such support bar is structured and
arranged to removably attach to the cockpit instrument panel
assembly.
Additionally, it provides such a system wherein such at least one
support bar further comprises: at least one substantially
rectangular cross section; and at least one second longitudinal
face; wherein such at least one second longitudinal face is located
parallel to such at least one first longitudinal face. Moreover, it
provides such a system wherein: each such at least one support bar
further comprises at least two of such at least one T-shaped slot
portions; at least one of such at least two T-shaped slot portions
defines at least one continuous slot opening portion within such at
least one second longitudinal face of such at least one support bar.
Additionally, it provides such a system wherein such at least one
continuous slot opening portion comprises at least one countersink
receiver adapted to receive at least one countersunk mounting hole
of the at least one avionics-component tray. Also, it provides such
a system wherein such wherein such at least one support bar further
comprises: at least one mountable portion; and at least one mounting
extension adapted to extend such at least one mountable portion
beyond the substantially rectangular cross section.
In addition, it provides such a system further comprising: at least
one quick-release adapter to adapt at least one quick-release
connector to such at least one attacher; wherein such at least one
quick-release adapter comprises at least one mount, to mount at
least one avionics-component compatible with the at least one
quick-release connector, in a position adjacent to such at least one
support bar, at least one adjuster adapted to permit
substantially-transverse positional adjustment of such at least one
mount relative to such at least one longitudinal axis of such at
least one support bar, and at least one mounting connector to
connect such at least one quick-release adapter to such at least one
attacher; and wherein such at least one mount comprises at least one
quick-release receiver adapted to receive and removably retain the
at least one quick-release fastener. And, it provides such a system
wherein such at least one quick-release receiver is adapted to
receive a Dzus-type mounting connector.
Further, it provides such a system, wherein: such at least one
adjuster comprises at least one first interlocker; such at least one
mount further comprises at least one second interlocker; such at
least one first interlocker and such at least one second interlocker
are structured and arranged to firmly interlock; and such at least
one first interlocker and such at least one second interlocker, when
interlocked, prevent relative movement between such at least one
adjuster and such at least one mount. Even further, it provides such
a system wherein: at least one portion of such at least one first
interlocker comprises at least one first interlocking detent; at
least one portion of such at least one second interlocker comprises
at least one second interlocking detent; and such first at least one
interlocking detents and such second at least one interlocking
detents, when meshed, prevent relative movement between such at
least one adjuster and such at least one mount; wherein meshing of
such said first and such second at least one interlocking detents
prevents substantially-transverse positional movement of such at
least one mount relative to the longitudinal axis of such at least
one support bar.
Moreover, it provides such a system further comprising: at least one
spacer adapted to fit between such at least one mount and such at
least one adjuster; wherein such at least one spacer permits at
least one Dzus-type avionics-component to be mounted in a general
aviation aircraft cockpit instrument panel assembly adapted to
receive the at least one avionics-components tray.
Additionally, it provides such a system further comprising: at least
one tray adjuster structured and arranged to permit positional
adjustment of the at least one avionics-component tray relative to
such at least one support bar; wherein such at least one tray
adjuster comprises, at least one engager adapted to engage at least
one portion of the at least one avionics-component tray; at least
one cam adjuster structured adapted to adjust the position of such
at least one engager; at least one mounting aperture to permit
passage of the at least one mounting connector; wherein rotation of
such at least one cam adjuster produces at least one
substantially-transverse movement, relative to such at least one
longitudinal axis of such at least one support bar, of both such at
least one engager and the at least one avionics-component tray.
Also, it provides such a system wherein: such at least one engager
comprises at least one essentially cylindrical member having at
least one central axis, at least one radius and at least one outer
circumference; and such at least one cam adjuster comprises such at
least one mounting aperture passing through such at least one
engager such that such at least one mounting aperture is
eccentrically located at a point adjacent to such at least one
central axis. In addition, it provides such a system further
comprising: at least one avionics-components tray; wherein such at
least one avionics-components tray comprises, at least one side, and
at least one mounting hole in such at least one side. And, it
provides such a system wherein such at least one mounting hole is
adapted to receive such at least one essentially cylindrical member.
Further, it provides such a system wherein the at least one radius
of such at least one essentially cylindrical member is about
one-half inch.
Even further, it provides such a system further comprising: at least
one blanking cover adapted to cover unused portions of the general
aviation aircraft cockpit instrument panel; wherein such at least
one blanking cover comprises, at least one filler panel to fill such
unused portions, at least one retainer to removably retain such at
least one filler panel on such at least one support bar, at least
one adjuster to adjust the position of such filler panel relative to
the general aviation aircraft cockpit instrument panel.
Moreover, it provides such a system wherein: such at least one
filler panel comprises a substantially planar member having at least
one front face and at least one rear face; such at least one
retainer comprises at least one spring loaded engager adapted to
removably engage such at least one support bar; such at least one
adjuster comprises at least one retainer holder, firmly coupled to
such at least one rear face; and such at least one retainer holder
is adapted to adjustably hold such at least one retainer in at least
one selected position relative to such at least one front face.
Additionally, it provides such a system wherein: such at least one
retainer holder comprises a plurality of holding apertures adapted
to receive and removably hold such at least one retainer; each one
of such plurality of holding apertures is uniquely positioned
relative to such at least one filler panel; and at least two of such
plurality of holding apertures are arranged to permit at least one
matching alignment of at least two of such at least one retainers
relative to such at least one front face.
Also, it provides such a system wherein such at least one support
bar comprises at least two of such at least one slides. In addition,
it provides such a system wherein such at least one support bar
further comprises: at least one mountable portion; and at least one
mounting extension adapted to extend such at least one mountable
portion of such at least one support bar. And, it provides such a
system wherein: such at least one support bar comprises at least one
contour structured and arranged to match at least one contoured
portion of the general aviation aircraft cockpit instrument panel
assembly; and such at least one contour permits such at least one
support bar to replace at least one sheet metal portion of the
general aviation aircraft cockpit instrument panel assembly.
In accordance with another preferred embodiment hereof, this
invention provides a method of installing, in a general aviation
aircraft cockpit instrument panel assembly, mounting bars for
mounting at least one avionics-components tray having at least one
side, at least one mounting hole in the side, comprising, in
combination, the steps of: removing any existing mounting rails from
the cockpit instrument panel assembly; providing at least one
mounting bar comprising at least one longitudinal slot portion
holding at least one slideably adjustable attacher; sizing such at
least one mounting bar to substantially match a length of at least
one existing rail; determining locations of mounting screws on such
at least one mounting bar using such at least one existing rail as a
template; preparing receiving holes at such locations for mounting
screws in such at least one mounting bar; placing such at least one
slideably adjustable attacher into such at least one longitudinal
slot portion; blocking the ends of such at least one longitudinal
slot portion to retain such at least one slideably adjustable
attacher; and attaching such at least one mounting bar containing
such at least one slideably adjustable attacher to the cockpit
instrument panel assembly substantially proximate to a location of
at least one such removed existing side mounting rail in a position
suitable to mount the at least one avionics-components tray.
In accordance with another preferred embodiment hereof, this
invention provides a method of installing, in a general aviation
aircraft cockpit instrument panel assembly comprising at least one
mounting bar having at least one longitudinal slot portion, at least
one avionics-components tray having at least one side, at least one
mounting hole in the side, comprising, in combination, the steps of:
establishing at least one suitable mounting position of the at least
one avionics-components tray adjacent to such at least one
longitudinal slot portion; and providing within the at least one
side of the at least one avionics-components tray at least one new
mounting hole, aligning with such at least one longitudinal slot
portion, to permit the at least one avionics-components tray to be
mounted in the at least one suitable mounting position.
In accordance with another preferred embodiment hereof, this
invention provides a method of using, in a general aviation aircraft
cockpit instrument panel assembly, side mounting bars for mounting
at least one avionics-components tray having at least one side, at
least one mounting hole in the side, and at least one mounting
connector for making a connection through the mounting hole,
comprising in combination, the steps of: accessing at least one
mounting bar comprising at least one longitudinal slot portion
holding at least one unattached spring loaded slideably adjustable
attacher; selecting an unattached one of such at least one
unattached spring loaded slideably adjustable attacher; pressing
such spring loaded slideably adjustable attacher to release friction
between such spring loaded slideably adjustable attacher and such
longitudinal slot portion; moving such spring loaded slideably
adjustable attacher to a user preferred location within such
longitudinal slot portion; and releasing such spring loaded
slideably adjustable attacher within such longitudinal slot portion
at such user preferred location. Further, it provides such a method
further comprising the step of attaching the at least one mounting
connector of the at least one avionics-components tray to such at
least one spring loaded slideably adjustable attacher. Even further,
it provides such a method further comprising the steps of: inserting
at least one-tray adjuster through the at least one mounting hole;
inserting the at least one mounting connector through such at least
one tray adjuster to loosely engage the at least one mounting
connector of the at least one avionics-components tray to such at
least one spring loaded slideably adjustable attacher; adjusting
such at least one tray adjuster to move the at least one
avionics-components tray to at least one user preferred position;
and tightening the at least one mounting connector to firmly attach
the at least one avionics-components tray to such at least one
spring loaded slideably adjustable attacher.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is an artistic rendering of a general aviation aircraft.
FIG. 2 is a perspective partial view of a general aviation aircraft
instrumentation panel illustrating the prior art.
FIG. 3 is a detailed partial perspective view of a preferred rack
component embodying the present invention.
FIG. 4 is a cross-sectional view through the section 4--4 of FIG. 5,
as shown.
FIG. 5 is a partially-exploded perspective view of a preferred rack
component.
FIG. 6 is a partial cross-sectional view, through the section 6--6
of FIG. 3, of the mounting nut assembly of a preferred rack
component.
FIG. 7 is a partial cross-sectional view, through the section 7--7
of FIG. 3, of the end of a preferred rack component.
FIG. 8 is a schematic illustration of the removal of original rail
components.
FIG. 9 is a schematic illustration of sizing a preferred rack
component to the original rail component.
FIG. 10 is a schematic illustration of the installation of a
preferred rack component.
FIG. 11 is a schematic illustration of the using of a preferred rack
component.
FIG. 12 is a schematic illustration of a multiple rack installation
utilizing a double support rail mounted within a general aviation
aircraft instrumentation panel according to an alternate embodiment
of the present invention.
FIG. 12A is a detailed partial perspective view of a preferred
double support rail according to the preferred embodiment of FIG.
12.
FIG. 13 is a cross-sectional view, through the section 13--13 of
FIG. 12, of the midsection of a preferred multiple rack component.
FIG. 13A is a cross-sectional view, similar to cross-sectional view
13--13, of the midsection of another double support rail according
to an alternate preferred embodiment of the present invention.
FIG. 13B is a cross-sectional view, through the section 13'--13' of
FIG. 12, showing the midsection of a typical multiple rack
installation, illustrating the multiple rack component of FIG. 13A
in use.
FIG. 13C is another cross-sectional view, similar to cross-sectional
view 13--13, taken along the midsection of another multiple rack
component according to an alternate preferred embodiment of the
present invention.
FIG. 13D is a cross-sectional view through the section 13'--13' of
FIG. 12 through the midsection of a typical multiple rack
installation, illustrating the multiple rack component of FIG. 13B
in use.
FIG. 14 is a partial perspective view of an adapter assembly
according to another preferred embodiment of the present invention.
FIG. 15 is a cross-sectional view through the section 15--15 of FIG.
14 of the midsection of a preferred rack component.
FIG. 16 is a schematic illustration of a typical mounting
arrangement of rack components, having an adapter assembly,
according to a preferred embodiment of the present invention.
FIG. 17 is a cross-sectional view, similar to cross-sectional view
4--4 of FIG. 5, through the midsection of another rack component
according to an alternate embodiment of the present invention.
FIG. 18 is a cross-sectional view, similar to cross-sectional view
4--4 of FIG. 5, through the midsection of another rack component
according to an alternate embodiment of the present invention.
FIG. 19 is a cross-sectional view, similar to cross-sectional view
4--4 of FIG. 5, through the midsection of another rack component
according to an alternate embodiment of the present invention.
FIG. 20 is a cross-sectional view through the midsections of an
alternate set of rack components according to another embodiment of
the present invention.
FIG. 21 is an exploded view, partially in section, illustrating an
adjustable cam mounting assembly according to a preferred embodiment
of the present invention.
FIG. 22 is a rear perspective view of the tray cam insert according
to the embodiment of FIG. 21.
FIG. 23 is a diagram illustrating the operation of the cam mounting
assembly according to the embodiment of FIG. 21.
FIG. 24 is a perspective view, partially in section, illustrating
the assembled adjustable cam mounting assembly of FIG. 21.
FIG. 25 is a front view of the tray cam insert according to the
embodiment of FIG. 21.
FIG. 26 is a sectional view 26--26 according to FIG. 25 of the tray
cam insert.
FIG. 27 is a front perspective view illustrating a blanking plate
according to a preferred embodiment of the present invention.
FIG. 28 is a top view illustrating the blanking plate according to
the embodiment of FIG. 27.
FIG. 29 is a top view, in partial section, illustrating the
engagement of the retainer within the mounting rack component
according to the embodiment of FIG. 27.
FIG. 30 is a rear view of the blanking plate according to the
embodiment of FIG. 27.
FIG. 31 is a side view of the blanking plate according to the
embodiment of FIG. 27.
DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT OF THE INVENTION
FIG. 1 is an artistic rendering of a general aviation aircraft 100
with a cockpit instrument panel 110.
FIG. 2 is a perspective view illustrating a prior art and
currently-used system employed for positioning radio
avionics-components mounting tray(s) 120 and 125 within a general
aviation cockpit instrument panel 110. As shown, right-hand mounting
rail 130 has mounting holes 140 and oval mounting holes 145 spaced
at intervals throughout the length of rail 130. As shown in the top
enlargement, slip nuts 150 are typically placed around rail 130 and
proximate to an oval mounting hole 145. As shown in the bottom
enlargement, mounting tray 120 is affixed to rail 130 by screw 170
passing through upper attachment screw hole 160 to bind in slip nut
150. Lower attachment screw hole 165 is not proximately located to
oval hole 145.
Typically, the avionics components are not directly mounted to the
rails 130 and 130'; rather, a mounting tray 120, having a bottom 124
and two parallel sides 122 and 122' with mounting holes 160 and 165
positioned in side 122 substantially proximate to the cockpit panel
110 and open cockpit, is attached to the rails 130 in the proper
location. Corresponding holes, not shown due to perspective, located
in side 122' are used to attach the mounting tray 120 to rail 122'.
When secured, the avionics component is then placed within the
affixed tray 120.
To achieve attachment of mounting tray 120, the installer must drill
or grind a new hole 140 proximate to the required location of the
lower attachment screw hole 165, as shown in the side of mounting
tray 120, or omit use of the lower screw hole 165 for attachment of
mounting tray 120 to rail 130. Over time, replacement of components
and their corresponding mounting tray(s) 120 and 125 will likely
lead to multiple custom holes placed in random locations throughout
rail 130. Such multiple holes lead to reduced structural integrity
of the rail, an undesirable condition for the mounting and support
of avionics component mounting tray(s) 120 and 125, as well as an
undesirable condition for the overall structural integrity and
support of the cockpit instrument panel 110. It is understood that
there is a corresponding left-hand mounting rail 130' for securing
the left-hand side of mounting tray(s) 120 and 125, with the same
features and limitations as discussed in relation to rail 130.
As shown in FIG. 3 and FIG. 4, a preferred embodiment of the present
invention is mounting rack component 200, preferably comprised of a
bar 210, preferably of aluminum. With respect to FIG. 11, it is
observed that the mounting rack component 200 and 200' of the
present invention, each comprised of bar 210 and mounting nut
assemblies 300 (discussed below), are preferred for mounting and
supporting avionics-components mounting rack(s) 690, 692, and 694
(embodying herein at least one support bar structured and arranged
to support the avionics-component rack). Together, mounting rack
component 200 and 200' preferably comprise a mounting rack system
175, as shown. As shown in FIG. 3, a first channel 220 is set within
first surface 230, parallel to sides 240 and 250. A second chapel
260, transverse to and intersecting the first channel 220, is
preferably set within the core of bar 210 parallel to first surface
230, as shown. Preferably, the first channel 220 and second channel
260 serve to create a T-shaped-cross-section slot portion 270,
wherein second channel 260 serves to hold and permit sliding of a
slideable attacher 300, while first channel 220 permits access to
the slideable attacher 300 (embodying herein at least one slide
structured and arranged to permit sliding the at least one attacher
within the at least one support bar, wherein the at least one slide
comprises at least one holder structured and arranged to slideably
hold the at least one attacher within the at least one support bar).
Under appropriate circumstances wherein the slideable attacher is a
nut assembly 300, it may be preferable for the first channel 220 to
extend below the second channel 260 so as to accommodate a greater
range of lengths of attaching screw 280, which may extend through
the nut assembly 300 (embodying herein at least one attacher
structured and arranged to attach the avionics-component to the at
least one supporting bar). As shown, first channel 220 and second
channel 260 together comprise the required T-shaped-cross-section
slot portion 270 opening within bar 210 (herein embodying wherein
such at least one slide comprises at least one T-shaped slot
portion, of such at least one support bar). Most preferably, first
channel 220 extends through second channel 260 to form optional
additional slot portion 232 (as an addition to portion 270, the same
reference number 270 being used whether referring to the entire
slot-portion shape or only the "T" portion), thereby accommodating
both the mounting nut assembly 300 and varying lengths of attaching
screws 280 (herein embodying wherein such at least one support bar
comprises at least one additional slot portion adapted to receive at
least one mounting connector portion). First channel 220, second
channel 260 and additional slot portion 232 together comprise the
highly-preferred "plus"-shaped-cross-section slot 270 (herein
embodying wherein such at least one additional slot portion and such
at least one T-shaped portion, in combination, comprise at least one
plus-shaped slot portion), as shown. Preferably, first channel 220
intersects first surface 230 to form a continuous slot opening 292
along first surface 230 (herein embodying at least one continuous
slot opening portion within such at least one first longitudinal
face of such at least one support bar). Preferably, the first
channel 220 is sufficiently deep and wide to accommodate an
attachment screw 280. Preferably, the second channel is sufficiently
wide and tall to accommodate the mounting nut assembly 300.
FIG. 4 is a cross-sectional view through the section 4--4 of FIG. 5
of the midsection of mounting rack component 200. Preferably,
mounting rack component 200 comprises an essentially rectangular
cross-section having a preferred length "A" at side 240 and side 250
of about 0.625 inch, and a preferred width "B" at first surface 230
of about 0.575 inch, as shown. Under appropriate circumstances, such
as to produce a rail with extended accommodations for various tray
mountings, the position of slot 270 may be shifted toward side 250
by a distance of about 0.075 inch.
The exploded view of FIG. 5 shows mounting nut assembly 300 is
preferably comprised of retainer 310, nut 320 (preferably square)
(embodying herein a receiver structured and arranged to receive the
at least one mounting connector), and spring 330. As shown, spring
330 is preferably a spring washer. Preferably, nut 320 is structured
and arranged to receive an attachment screw 280, which is commonly
used. As shown, retainer 310 preferably has a flat base section 340
defined by two raised ends 350 and 360. For ease of manufacturing,
retainer 310 is preferably formed from a flat "U" washer, having the
ends of the arms of the "U" and the base of the "U" bent upward to
form substantially perpendicular ends 350 and 360. Preferably, the
"U" washer is sized such that the remaining flat base is
substantially equal to the width of nut 320, and the height of ends
350 and 360 is substantially equal to the height of nut 320. Spring
330 is preferably slightly smaller than the width of nut 320, so
that when placed between the flat base 340 of retainer 310 and nut
320, spring 330 does not protrude beyond the edges of nut 320, and
spring 330 does not intrude upon threaded hole 325 in nut 320,
frustrating or prohibiting passage of a screw 280 through nut 320
(embodying herein at least one retaining bracket; at least one
threaded nut in said retaining bracket, at least one resilient
spring in said retaining bracket; wherein the at least one resilient
spring is between the at least one bracket and the at least one
nut).
Under appropriate circumstances and/or in accordance with
manufacturing preferences, it is understood that retainer 310 itself
may be formed from spring steel or other spring material. Under such
appropriate circumstances, base section 340 would preferably be
curved to operate as spring 330, more clearly shown in FIG. 6.
FIG. 6 provides a cross-sectional view of mounting rack component
200, further illustrating the arrangement of components comprising
mounting nut assembly 300. As shown, preferably, spring washer 330
is an expansive spring such that when mounting nut assembly 300 is
placed in second channel 260, spring 330 provides sufficient
expansion force between retainer 310 and nut 320 to frictionally
hold mounting nut assembly 300 within second channel 260 and prevent
sliding due to gravity (embodying herein a holder structured and
arranged so that the spring applies separation force between the at
least one retaining bracket and the at least one nut). Preferably,
such friction may be overcome by an installer using screw 280 or
other desired implement to overcome the friction hold imparted by
spring 330 and slide mounting nut assembly 300 to the desired
location in slot 270. Such preferred arrangement allows placement of
mounting nut assembly at any point within second channel 260 such
that nut 320 may receive an attachment screw through first channel
220. As shown in FIG. 6, it is noted that the preferred binding
force imparted by screw 280 securing mounting tray 690 to mounting
rack component 200 by securing to nut 320 does not compress or
otherwise load spring 330. This is preferred, as it insures spring
330 remains resilient and ready to provide the frictional holding
force for mounting nut assembly 300 when and if screw 280 is
removed. It is also noted that the binding force imparted by screw
280 securing mounting tray 690 to mounting rack component 200 by
securing to nut assembly 300 preferably binds mounting tray 690
firmly against first surface 230, such that mounting tray 690 will
not slip or slide (this arrangement embodying herein at least one
connection system structured and arranged to non-slideably connect
said at least one attacher within said at least one support bar when
the at least one mounting connector is connected with said at least
one receiver).
As shown in FIG. 4 and FIG. 6, to aid in guiding screw 280 to meet
nut 320, and to provide a proper seat for the preferred countersink
of screw 280, preferably, edges 290 are angled (herein embodying
wherein such at least one continuous slot opening portion comprises
at least one countersink receiver adapted to receive at least one
countersunk mounting hole of the at least one avionics-component
tray). Further, in many instances, mounting hole 710 of mounting
tray 690 is formed so as to accommodate screw 280 flush with the
interior side wall of mounting tray 690. Often, the exterior portion
of the mounting tray 690 is distorted outward in response to
providing a dimpled area for screw 280 to nest. As can be seen, the
angle 296 preferably accommodates this exterior bump 695 surrounding
the exterior of mounting hole 710. Such accommodation is preferred,
for such nesting between bump 695 and angles 290 results in improved
alignment of the mounting tray 690. Further, as external bump 695 is
secured within channel 220 when screw 280 is tightened to secure
mounting tray 690 against first surface 230, external bump 695
serves to help lock mounting tray 690 in place and prevent rotation
of mounting tray 690 relative to mounting rack component 200.
Mounting nut assemblies 300 are preferably confined to mounting rack
component 200 by means of two end caps 400 (herein embodying wherein
such at least one support bar further comprises at least on end cap
adapted to cap at least one end portion of such at least one
T-shaped slot portion). As shown in FIG. 5 and the cross-sectional
view of FIG. 7, preferably end cap 400 is comprised from right angle
bar 410, cut to a width 450 substantially equal to the width 450 of
bar 200. Tongue 420 is substantially equal in width to second
channel 260 and is affixed to angle bar 410, preferably by welding.
Under appropriate circumstances, casting, milling, gluing, and
welding may be used to affix tongue 420 to angle bar 410. As shown
in the partial sectional view of FIG. 7, hole 430 in side 460 is
aligned with threaded hole 435 in tongue 420 to receive screw 440.
When end cap 400 is placed in the end of bar 210 such that tongue
420 is inserted in second channel 260 of slot 270, screw 440, when
tightened, provides compression between tongue 420 and side 460,
binding end cap 400 to bar 210.
Under appropriate circumstances, it may be desired to use additional
mounting nut assemblies 300 tightened in place at either end of
mounting rack component 200 in place of end caps 400. The angle 290
of first channel 220 permits screw 280 to bind against first surface
230. Thus, it is to be appreciated that mounting nut assemblies 300
may be left loose within slot 270, or bound in place, even if
unattached, at the preference of the installer.
Preferably, in operation, mounting rack component 200 has a
plurality of mounting nut assemblies 300, sufficient to enable
installation of the desired number of avionics-components mounting
trays.
FIG. 8 through FIG. 11 depicts the preferred general steps of
installing a preferred embodiment of the mounting rack components
200 in a general aviation aircraft instrument panel 600. As the
mounting rack component 200 (a preferred embodiment of the present
invention) is intended to replace the existing rail 610, the
installer must begin with the removal of the original/current
existing rails 610. Preferably, all existing component mounting
trays are also removed.
As shown in FIG. 8, typically, removal of original rails 610 is
accomplished by removing the instrument panel screws 620 securing
the instrument panel 600 to the left and right rails 610 and 610'.
Further, the rails themselves 610 and 610' are removed from the
instrument panel frame assembly 630 (embodying herein the step of
removing any existing side mounting rails from the cockpit
instrument panel assembly). Typically, the original/current rails
are affixed in place by rivets or screws. Removal of original rail
610 from the instrument panel frame assembly 630 may easily be
accomplished by removing the fastening screws, or by drilling out
the attaching rivets 640 with an appropriately-sized drill bit.
Preferably, mounting rack components 200 are provided in a series of
standard pre-cut lengths and with an appropriate number of the
preferred mounting nut assemblies 300 (embodying herein the step of
providing at least one side mounting bar comprising at least one
longitudinal slot holding at least one slideably adjustable
attacher). For installation, an installer selects mounting rack
components 200 of a length slightly greater than required for his or
her general aviation aircraft. Under appropriate circumstances,
mounting rack components 200 of specific lengths for specific
aircraft may be produced; however, mounting rack components 200 of
general lengths may be preferred as a method of limiting
aircraft-specific inventory.
Following removal of the left and right original rails 610, the
original rails 610 are used as templates to insure proper size and
mounting hole location and orientation of a preferred embodiment of
the mounting rack component 200. Preferably, each existing rail is
placed directly upon a mounting rack component 200 for proper length
sizing of the mounting rack component 200, and excess bar 650 is
preferably cut for removal from bar 210 (embodying herein the step
of sizing the at least one mounting bar to substantially match a
length of at least one existing rail). Following such length sizing
and cutting, if required, original rail 610 is again used as a
template to properly identify instrument panel mounting screw hole
660 placements and mounting holes 670 for attachment of mounting
rack component 200 to the instrument panel frame assembly 630
(embodying herein the step of determining locations of mounting
screws on such at least one mounting bar using such at least one
existing rail as a template). Required holes of a preferably
appropriate size are then drilled and tapped, as shown in FIG. 9
(embodying herein the step of preparing receiving holes at such
locations for mounting screws in such at least one mounting bar).
Certain general aircraft instrumentation panels may have additional
mounting hardware attached to the original rails 610 for connection
to the instrument panel 600. Under appropriate circumstances, such
additional mounting hardware may be attached to the mounting rack
components 200 to effectuate proper support for the instrument panel
600.
As shown in FIG. 9, the installer inserts the preferred number of
mounting nut assemblies 300 into slot 270 (embodying herein the step
of placing such at least one slideably adjustable attacher into such
at least one longitudinal slot). To secure mounting nut assemblies
300 within slot 270, preferably end caps 400, as shown in FIG. 7,
are applied to either end of mounting rack component 200 (embodying
herein the step of blocking the ends of such at least one
longitudinal slot to retain such at least one slideably adjustable
attacher). Under appropriate circumstances, the ends may be secured
by welding, crimping, or such other activity sufficient to
substantially block the ends of slot 270 such that mounting nut
assemblies 300 preferably cannot fall out or be lost. Mounting rack
component 200 is then placed in the location and position occupied
by original rail 610, now removed. Screws 680 are then preferably
used to attach mounting rack component 200 to the instrument panel
frame assembly 630 in the location previously occupied by original
rail 610. Under appropriate circumstances, rivets, welds or other
means of attachment to the cockpit frame assembly desired by the
installer may be used in place of screws. Screws 620 reattach
cockpit instrument panel 600 to mounting rack component 200. This
procedure, as depicted for right-hand side mounting rack component
200 is, of course, duplicated for the left-hand side mounting rack
component 200. When completed for both, right-and-left-hand-side
mounting rack components 200 are properly set to receive and support
mounting rack(s) 690, 692, and 694, as shown in FIG. 11 (embodying
herein the step of attaching such at least one side mounting bar
containing such at least one slideably adjustable attacher to the
cockpit instrument panel assembly substantially proximate to a
location of at least one such removed existing side mounting rail in
a position suitable to mount the at least one avionics-components
tray).
Mounting tray(s) 690, 692, and 694, appropriate for receiving the
desired radio avionics equipment are installed, as shown in FIG. 11.
Each mounting tray 690, 692, and 694 is affixed to the corresponding
left-and-right-side mounting rack component 200 by screws 700. As
shown, the mounting nut assemblies 300 for receiving screws 700 are
easily moved to the desired and preferred location where they
remain, frictionally-held within slot 270, until engaged by a
corresponding screw 700 in the process of attaching a mounting tray
694.
More specifically, preferably, the installer will remove the
existing defunct component and its mounting tray so as to have
access to the left-and-right mounting rails 300, and the mounting
nut assemblies 300 held within slot 270 (embodying herein the step
of accessing at least one side mounting bar comprising at least one
longitudinal slot holding at least one unattached spring-loaded
slideably adjustable attacher).
As described above, the mounting nut assemblies 300 are preferably
spring-loaded such that they frictionally hold themselves within
slot 270. Preferably, the installer selects an unattached mounting
nut assembly 300 (embodying herein the step of selecting an
unattached one of the at least one unattached spring-loaded
slideably adjustable attacher). By means of a screw, screwdriver, or
other suitable device, the installer will press in on the selected
mounting nut assembly 300 such that the frictional hold within slot
270 is broken (embodying herein the step of pressing the
spring-loaded slideably adjustable attacher to release friction
between the spring-loaded slideably adjustable attacher and the
longitudinal slot).
While maintaining pressure sufficient to defeat the expansion of the
internal spring 330, the installer moves the mounting nut assembly
300 within slot 270 to the preferred location for alignment with the
mounting hole in the side of the new mounting tray to be installed
(embodying herein the step of moving the spring-loaded slideably
adjustable attacher to a user-preferred location within the
longitudinal slot). The precise method of determining the location
of placement will be determined by the preference of the installer.
Upon determination of the preferred new location for the mounting
nut assembly 300, the installer simply releases the pressure he or
she has been applying to the mounting nut assembly 300. Preferably,
by design, the internal spring 330 described above with respect to
FIG. 6, expands to separate the internal components of the nut
assembly 300, the nut 320 and retainer 310. Such expansion imparts
friction to return between the mounting nut assembly and slot 270
such that, preferably, mounting nut assembly remains fixed in the
chosen location (embodying herein the step of releasing the
spring-loaded slideably adjustable attacher within the longitudinal
slot at such user-preferred location).
As shown in FIG. 11, preferably, mounting tray 694 has a bottom 730,
and two parallel sides 720 and 720' with mounting holes 710, as
shown, positioned substantially proximate to the cockpit instrument
panel 600. Mounting tray 694 is placed between mounting rack
components 200 and 200', moved to the desired new location,
positioned and mounted securely in place by affixing screw 700
through the side mounting hole 710 of mounting tray 694 and into
mounting nut assembly 300 (embodying herein the step of attaching
the at least one mounting connector of the at least one
avionics-components tray to the at least one spring-loaded slideably
adjustable attacher).
Those skilled in the art, upon reading the teachings of this
specification, will appreciate that, under appropriate
circumstances, general aviation aircraft manufacturers may desire to
install a preferred embodiment of the present invention as original
equipment manufacture, commonly termed as "OEM". In such
circumstances, a preferred embodiment will be present as shown in
FIG. 11, and use for mounting tray(s) 690, 692, and 694 will occur
as described above.
Future replacement or upgrade of radio avionics equipment is simply
accomplished by removing the defunct component and its corresponding
mounting tray. Mounting nut assembly(ies) 300 are then preferably
realigned in slot 270 to accommodate screw placement, as dictated by
the new component mounting tray.
FIG. 12, FIG. 12A, FIG. 13, FIG. 13B, FIG. 13C and FIG. 13D
illustrate preferred alternate embodiments of mounting rack system
175 adapted to permit two or more adjacent vertical columns of
avionics components to be mounted within a cockpit instrument panel
using mounting rack component(s) 200 in combination with double
mounting component 800.
FIG. 12 is a schematic illustration of multiple rack installation
500 utilizing double mounting component 800 mounted within
instrumentation panel 600, according to an alternate embodiment of
the present invention. Many aircraft cockpit designs utilize two or
more adjacent vertical columns (or stacks) of avionics components
502, as shown. In this type of side-by-side installation, a single
double mounting component 800, located between the two adjacent
vertical columns of avionics components 502, is preferably used to
simultaneously support one side of both adjacent vertical columns,
as shown. Those skilled in the art, upon reading the teachings of
this specification, will appreciate that, unless noted otherwise,
installation and use of double mounting component 800 is essentially
similar to that described for the single channel embodiments of FIG.
8, FIG. 9, FIG. 10 and FIG. 11.
FIG. 12A is a detailed partial perspective view of a preferred
double mounting component 800, according to the preferred embodiment
of FIG. 12. Preferably, double mounting component 800 comprises a
unitary bar 810, preferably of milled or extruded aluminum, having a
first surface 230, a second surface 231 (herein embodying at least
one second longitudinal face), side 240 and side 250, as shown.
Preferably, second surface 231 is essentially parallel to first
surface 230, as shown (herein embodying wherein such at least one
second longitudinal face is located parallel to such at least one
first longitudinal face). Preferably, unitary bar 810 comprises
first slot 870, preferably intersecting first surface 230, as shown.
Additionally, unitary bar 810 comprises second slot 870' (herein
embodying wherein each such at least one support bar further
comprises at least two of such at least one T-shaped slot portions),
as shown. Preferably, second slot 870' intersects second surface 231
to form a second continuous slot opening 293, as shown (herein
embodying wherein at least one of such at least two T-shaped slot
portions defines at least one continuous slot opening portion within
such at least one second longitudinal face of such at least one
support bar). As in the prior described single channel embodiments,
first slot 870 and second slot 870' are preferably adapted to
accommodate a plurality of mounting nut assemblies 300 and mounting
screw(s) 280 of sufficient number to enable installation of the
desired avionics-component mounting tray.
FIG. 13 is a cross-sectional view, through the section 13--13 of
FIG. 12, of the midsection of double mounting component 800.
Preferably, as illustrated in FIG. 13, first slot 870 and second
slot 870' are in opposing, approximately orthogonal, orientation to
allow for simultaneous mounting of avionics on two opposite sides of
double mounting component 800. Preferably, both first slot 870 and
second slot 870' comprises the required T-shaped-cross-section slot
portion and, most preferably, the "plus"-shaped-cross-section slot
portion configuration of slot 270 (described within FIG. 3). First
slot 870 and second slot 870' are preferably arranged in overlapping
and offset positions to permit side 240 and side 250 to have a
relatively narrow width, thereby reducing required width clearances
within the instrument panel.
Those skilled in the art, upon reading the teachings of this
specification, will appreciate that, under appropriate
circumstances, considering such issues as specific aircraft
application and configuration, a number of alternate double support
rail embodiments are possible within the scope of the present
invention (such as those described in the following figures).
FIG. 13A is a cross-sectional view through the section 13--13 of
FIG. 12 of the midsection of alternate double mounting component 801
according to an alternate preferred embodiment of the present
invention. Preferably, double mounting component 801 is essentially
rectangular in cross section and is essentially symmetrical in slot
arrangements about centerline 802, as shown. Side 240 and side 250
have a preferred width "X" of about 0.70 inch, as shown. First
surface 230 and second surface 231 each comprise a preferred width
"Y" of 0.575 inch, as shown. Preferably, first slot 870 and second
slot 870' are in opposing, approximately orthogonal, orientation, as
shown. Preferably, both first slot 870 and second slot 870' comprise
the required T-shaped slot and most preferably the "plus"-shaped
cross-section slot configuration of slot 270 (previously described
within FIG. 3). As in the prior described embodiments, first slot
870 and second slot 870' are preferably adapted to accommodate a
plurality of mounting nut assemblies 300 and mounting screw(s) 280
of sufficient number to enable installation of the desired
avionics-component mounting trays.
FIG. 13B is a cross-sectional view through the section 13'--13' of
FIG. 12 through the midsection of typical multiple rack installation
500, illustrating double mounting component 801 of FIG. 13A
installed within cockpit instrument panel 600, as shown. Preferably,
double mounting component 801 simultaneously supports one side of
mounting tray 814 and mounting tray 816 (both indicated by dashed
lines). In the illustrated example of FIG. 13B, single sided
mounting rack component(s) 200 are used to support the sides of
mounting tray 814 and mounting tray 816 opposite double mounting
component 801, as shown. The preferred symmetrical arrangement of
double mounting component 801 closely matches the installed position
of the original cockpit instrument panel rails thereby permitting
the use of existing side mounting hole(s) 710 within mounting tray
814 and mounting tray 816, as shown.
FIG. 13C is a cross-sectional view (13--13) from FIG. 12 taken along
the midsection of an alternate double mounting component 803
according to an alternate preferred embodiment of the present
invention. Preferably, double mounting component 803 is essentially
rectangular in cross section, as shown. Side 240 and side 250 have a
preferred width "X'" of about 0.385 inch, as shown. First surface
230 and second surface 231 each comprise a preferred width "Y'" of
1.00 inch, as shown. Preferably, first slot 870 and second slot 870'
are in opposing, approximately orthogonal, orientation, as shown. As
in the prior double support rail embodiments, both first slot 870
and second slot 870' comprise the required T-shaped slot and most
preferably the "plus"-shaped cross section slot configuration of
slot 270, described within FIG. 3. In the embodiment of FIG. 13C,
first slot 870 and second slot 870' are preferably stacked thereby
providing an efficiently narrow profile at side 240 and side 250, as
shown. Double mounting component 803 is therefore suited for used in
cockpit instrument panels having limited rail-to-rail clearances. As
in the prior described embodiments, first slot 870 and second slot
870' are preferably adapted to accommodate a plurality of mounting
nut assemblies 300 and mounting screw(s) 280 of sufficient number to
enable installation of the desired avionics-component mounting
trays.
FIG. 13D is a cross-sectional view (13'--13') taken from FIG. 12,
through the midsection of another preferred typical multiple rack
installation 500, illustrating double mounting component 803 of FIG.
13C installed within cockpit instrument panel 600, as shown.
Preferably, double mounting component 803 simultaneously supports
one side of mounting tray 814 and mounting tray 816 (both indicated
by dashed lines), as shown. Although the standard mounting tray 816
is readily attachable to double mounting component 803 without
modification, the preferred asymmetrical arrangement of double
mounting component 803 requires that one or more new mounting
hole(s) 712 be made in side 732 of mounting tray 814 to accommodate
the alternate mounting position of mounting nut assembly 300 within
first slot 870, as shown. Mounting tray 814 is preferably modified
by establishing a suitable mounting position for mounting tray 814
adjacent to double mounting component 803 with the installed
location of first slot 870 measured and marked on the adjacent side
732 of mounting tray 814. New mounting hole(s) 712 are then formed
in side 732 using an appropriate drill or punch (herein embodying
the steps of establishing at least one suitable mounting position of
the at least one avionics-components tray adjacent to such at least
one longitudinal slot portion and providing within the at least one
side of the at least one avionics-components tray at least one new
mounting hole, aligning with such at least one longitudinal slot
portion, to permit the at least one avionics-components tray to be
mounted in the at least one suitable mounting position).
It is preferred that, both new mounting hole(s) 712 and existing
mounting hole(s) 710 comprise a countersunk screw receiver 714 to
permit the flush installation of screw(s) 280 and to provide
additional stability to mounting tray 814 and mounting tray 816. In
some applications, removal of the existing countersunk screw
receiver at existing mounting hole 710 may be required to properly
fit mounting tray 814 between double mounting component 803 and
outer mounting rack component 200, as shown.
FIG. 14 is a partial perspective view of an adapter assembly 890
according to another preferred embodiment of the present invention
(herein embodying at least one quick-release adapter to adapt at
least one quick-release connector to such at least one attacher). A
number of aviation instrumentation applications preferably utilize a
system of quick-release fasteners, commonly known as one-quarter
turn, or Dzus-type fasteners. Dzus-type fasteners typically comprise
a rotatable stud having a spiral cam which engages on to a spring or
receptacle mounted permanently on the equipment frame or support.
Dzus-type fasteners are favored in applications requiring frequent
component fitting and/or service for the reason that the fasteners
are engaged or released with relatively small rotational movements,
typically, about one quarter turn. FIG. 14 shows a typical
arrangement comprising at least one preferred angle adapter 900
(herein embodying at least one mount, to mount at least one
avionics-component compatible with the at least one quick-release
connector, in a position adjacent to such at least one support bar)
engaging at least one support rail adapter 902 (herein embodying at
least one adjuster adapted to permit substantially-transverse
positional adjustment of such at least one mount relative to such at
least one longitudinal axis of such at least one support bar)
further engaging mounting rail 130. Both angle adapter 900 and
support rail adapter 902 preferably comprise at least one
lightweight cast or extruded metal, preferably aluminum, however,
those skilled in the art, upon reading the teachings of this
specification, will appreciate that, under appropriate
circumstances, considering such issues as aircraft application and
cost, other materials, such as steel, titanium or rigid plastics,
may suffice. Preferably, angle adapter 900 comprises a short angle
leg 901 having at least one, preferably two, Dzus receptacles 904
(herein embodying wherein such at least one mount comprises at least
one quick-release receiver adapted to receive and removably retain
the at least one quick-release fastener and further herein embodying
wherein such at least one quick-release receiver is adapted to
receive a Dzus-type mounting connector) and a long angle leg 903
having at least one, preferably three, slotted mounting holes 906,
as shown.
FIG. 15 is cross-sectional view of 15--15 according to FIG. 14 of
the midsection of a preferred rack component. Preferably, angle
adapter 900 and support rail adapter 902 further comprise at least
one opposing set of linearly positioned teeth 905 (herein embodying
wherein at least one portion of such at least one first interlocker
comprises at least one first interlocking detent and at least one
portion of such at least one second interlocker comprises at least
one second interlocking detent) that, when meshed, prevents movement
of angle adapter 900 relative to support rail adapter 902 (herein
embodying wherein such at least one adjuster comprises at least one
first interlocker, such at least one mount further comprises at
least one second interlocker, such at least one first interlocker
and such at least one second interlocker are structured and arranged
to firmly interlock and such at least one first interlocker, and
such at least one second interlocker, when interlocked, prevent
relative movement between such at least one adjuster and such at
least one mount). At least one, preferably two, screw(s) 280 (herein
embodying at least one mounting connector to connect such at least
one quick-release adapter to such at least one attacher) pass
through the slotted mounting holes 906 of angle adapter 900 and
further pass through at least one, preferably two, mounting screw
holes in support rail adapter 902, as shown. Preferably, mounting
rail 130 accommodates a plurality of mounting nut assemblies 300
(located within slot 270) to receive and retain screw(s) 280, as
shown. Under appropriate circumstances, where mounting 5.75 inch
wide Dzus mount equipment within a standard 6.25 inch wide avionic
rack is preferred, rack spacer 910 is preferably used to increase
the width of adapter assembly 890 (herein embodying at least one
spacer adapted to fit between such at least one mount and such at
least one adjuster, wherein such at least one spacer permits at
least one Dzus-type avionics-component to be mounted in a general
aviation aircraft cockpit instrument panel assembly adapted to
receive the at least one avionics-components tray). Preferably,
spacer 910 is installed between support rail adapter 902 and angle
adapter 900. Preferably, spacer 910 is fully adjustable for proper
alignment with the installed tray mount avionics.
FIG. 16 is a schematic illustration of a typical mounting
arrangement of rack components, having adapter assembly 890,
according to a preferred embodiment of the present invention. In
operation, adapter assembly 890 is adjustable for vertical position
along mounting rail 130, as well as for transverse positional
adjustment relative to the longitudinal axis 731 of mounting rail
130, as shown. Preferably, Dzus compatible avionic equipment 860 may
be mounted to adapter assembly 890 using one or more Dzus type
fasteners 908, as shown. Angle adapter 900 and support rail adapter
902 may be of varying widths and lengths to accommodate specific
installation requirements. It should be noted that the inherent
adjustability of adapter assembly 890 permits full compatibility
with double mounting component(s) 800, 801, 802 and 803 shown in
FIG. 12 through FIG. 13D.
FIG. 17 is a cross-sectional view similar to cross-sectional view
4--4 taken from FIG. 5 through the midsection of alternate mounting
rack component 716 according to an alternate embodiment of the
present invention. Mounting rack component 716 preferably comprises
a configuration essentially identical to that of mounting rack
component 200 with the following exception; both side 240 and side
250 preferably comprise a smaller width "A'" measuring about 0.385
inch. This reduced width preferably permits mounting rack component
716 to be installed in cockpit instrument panels having reduced
clearances. Additionally, mounting rack component 716 provides a
lightweight alternative to mounting rack component 200 in
installations where low aircraft weight is of concern. As in the
prior described embodiments, first slot 870 is preferably adapted to
accommodate a plurality of mounting nut assemblies 300 and mounting
screw(s) 280 (see FIG. 6) of sufficient number to enable
installation of the desired avionics-component mounting trays.
FIG. 18 is a cross-sectional view similar to cross-sectional view
4--4 of FIG. 3 through the midsection of alternate mounting rack
component 718 according to an alternate embodiment of the present
invention. Preferably, mounting rack component 718 comprises a
configuration essentially identical to that of mounting rack
component 716 with the following exception; side 250 comprises an
increased width "C" of about 0.700 inch to form mounting extension
724 (herein embodying at least one mountable portion; and at least
one mounting extension adapted to extend such at least one mountable
portion of such at least one support bar and herein embodying at
least one mountable portion; and at least one mounting extension
adapted to extend such at least one mountable portion beyond the
substantially rectangular cross section), as shown. Preferably,
mounting extension 724 provides a greater surface area to side 250
to facilitate the installation and mounting of required cockpit
panel elements. Mounting extension 724 preferably comprises a
preferred thickness "D" of about 0.150 inch, as shown. Those skilled
in the art, upon reading the teachings of this specification, will
appreciate that, under appropriate circumstances, considering such
issues as cockpit panel arrangements and aircraft type, portions of
mounting extension 724 may be removed to accommodate specific
installation requirements. As in the prior described embodiments,
first slot 870 is preferably adapted to accommodate a plurality of
mounting nut assemblies 300 and mounting screw(s) 280 (see FIG. 6)
of sufficient number to enable installation of the desired
avionics-component mounting trays.
FIG. 19 is a cross-sectional view similar to cross-sectional view
4--4 of FIG. 3 through the midsection of alternate mounting rack
component 722 according to an alternate embodiment of the present
invention. Preferably, mounting rack component 722 comprises a
configuration essentially identical to that of mounting rack
component 716 with the following exceptions; first surface 230
comprises a preferred width "E" of about 0.500 inch and a mounting
extension 725 (herein embodying at least one mountable portion; and
at least one mounting extension adapted to extend such at least one
mountable portion of such at least one support bar and herein
embodying at least one mountable portion; and at least one mounting
extension adapted to extend such at least one mountable portion
beyond the substantially rectangular cross section), projects from
side 250, as shown. Preferably, mounting extension 725 has an
orientation essentially parallel to first surface 230 as shown.
Preferably, length "F" of mounting extension 725 is about 0.500
inch, as shown. Preferably, thickness "G" of mounting extension 725
is about 0.100 inch. Preferably, mounting extension 725 is offset
from first surface 230 distance "H" of about 0.080 inch, as shown.
The unique arrangement of mounting extension 725 permits mounting
rack component 722 to be used in aircraft having pedestal style
cockpit instrument panels (as, for example, in aircraft made by the
Cirrus Design Corporation of Duluth, Minn., U.S.A.). As in the prior
described embodiments, first slot 870 is preferably adapted to
accommodate a plurality of mounting nut assemblies 300 and mounting
screw(s) 280 (see FIG. 6) of sufficient number to enable
installation of the desired avionics-component mounting trays. Those
skilled in the art, upon reading the teachings of this
specification, will appreciate that, under appropriate
circumstances, considering such issues as alternate pedestal style
instrument panel configuration and aircraft type, other sizes and
orientations of mounting extensions 724 and 725 may suffice.
Further, those skilled in the art, upon reading the teachings of
this specification, will appreciate that, under appropriate
circumstances, considering such issues as unique aircraft
configurations, specialized and or new aircraft designs,
combinations of the various above described embodiments of mounting
rack component 200 may be used to assemble mounting rack system 175
and multiple rack installation 500.
FIG. 20 is a cross-sectional view through the midsections of an
alternate embodiment of mounting rack system 175 utilizing aircraft
specific mounting rack components 176 according to another preferred
embodiment of the present invention. Preferably, mounting rack
system 175 is generally adaptable to a number of aircraft models and
instrument panel types, however, it is sometimes preferred that a
specific mounting rack component combination be developed to fit a
specific aircraft configuration. FIG. 20 illustrates one preferred
embodiment specifically designed for a single aircraft or range of
aircraft having a unique but related instrument panel configuration.
In the example of FIG. 20, aircraft specific mounting rack
components 176 are arrange to fit within the canted instrument panel
of a Beechcraft "Bonanza" or "Baron" (as produced by the Raytheon
Aircraft Corporation Lexington, Mass., U.S.A.). Preferably,
aircraft-specific mounting rack components 176 comprises left
mounting rack component 178 and complementary right mounting rack
component 180, as shown. Left mounting rack component 178 preferably
comprises first slot 870, as shown. Similarly, right mounting rack
component 180 preferably comprises second slot 870', as shown. Both
left mounting rack component 178 and right mounting rack component
180 preferably comprise mounting extension(s) 727 adapted to provide
appropriate points of mounting to the existing cockpit instrument
panel structure (herein embodying at least one mountable portion;
and at least one mounting extension adapted to extend such at least
one mountable portion of such at least one support bar). In the
Beechcraft "Bonanza" or "Baron" aircraft portions of the OEM
instrument panel sheet metal are formed to produce an instrument
orientation "canted" toward the pilot. Preferably, aircraft specific
mounting rack components 176 comprises a similar contoured profile
thereby permitting aircraft specific mounting rack components 176 to
replace some or all of the OEM instrument panel sheet metal (herein
embodying wherein such at least one support bar comprises at least
one contour structured and arranged to match at least one contoured
portion of the general aviation aircraft cockpit instrument panel
assembly and such at least one contour permits such at least one
support bar to replace at least one sheet metal portion of the
general aviation aircraft cockpit instrument panel assembly). Under
appropriate circumstances, both left mounting rack component 178 and
right mounting rack component 180 may preferably comprise such OEM
sheet metal replacement accommodations as lip 182 adapted to permit
aircraft specific mounting rack components 176 to provide a flush
and finished appearance to the final avionics installation. Those
skilled in the art, upon reading the teachings of this
specification, will appreciate that, under appropriate
circumstances, such as in the development of future aircraft;
additional alternate aircraft specific embodiments are within the
scope of the present invention. As in the prior described
embodiments, first slot 870 and second slot 870' are preferably
adapted to accommodate a plurality of mounting nut assemblies 300
and mounting screw(s) 280 (see FIG. 6) of sufficient number to
enable installation of the desired avionics-component mounting
trays.
Those skilled in the art, upon reading the teachings of this
specification, will appreciate that, installation and use of
aircraft specific mounting rack components 176 is essentially
similar to that described for the single channel embodiments of FIG.
8, FIG. 9, FIG. 10 and FIG. 11. It is further understood that
variations exist in the configurations of all manufactured aircraft
and that accommodations required to install the embodiments
described herein are within the abilities of those skilled in the
art of aircraft design, operation and maintenance.
FIG. 21 is an exploded view, partially in section, illustrating
adjustable cam mounting assembly 726 according to a preferred
embodiment of the present invention. The preferred use of cam
mounting assembly 726 facilitates the final installation and proper
alignment of mounting tray 814 by permitting transverse positional
movement 729 of mounting tray 814 with respect to the longitudinal
axis 731 of mounting rack component 200, as shown. Typical
variations in the design and construction of mounting trays are
accommodated by the preferred use of cam mounting assembly 726,
permitting the installer to provide a secure and finished appearance
to the final avionics installation. Preferably, cam mounting
assembly 726 (herein embodying at least one tray adjuster structured
and arranged to permit positional adjustment of the at least one
avionics-component tray relative to such at least one support bar)
comprises mounting aperture 734 and mounting hole 730 located in
side 732 of mounting tray 814, as shown. Preferably, mounting tray
814 is assembled to mounting rack component 200 by engaging tray cam
insert 728 within mounting hole 730 followed by passing screw 280
through mounting aperture 734 to loosely engage mounting nut
assembly 300, as shown. Rotation of tray cam insert 728, while so
engaged, provides transverse positional movement 729 of mounting
tray 814 with respect to the longitudinal axis 731 of mounting rack
component 200 (as further described in FIG. 23).
FIG. 22 is a rear perspective view of tray cam insert 728 according
to the embodiment of FIG. 21. Preferably, tray cam insert 728
comprises an essentially planar disk having center axis 740, as
shown. Tray cam insert 728 further preferably comprises engaging
portion 736 (herein embodying at least one engager adapted to engage
at least one portion of the at least one avionics-component tray),
mounting aperture 734 (herein embodying at least one mounting
aperture to permit passage of the at least one mounting connector)
and hex aperture 738, as shown. Preferably, engaging portion 736
comprises outer circumference 742 and as a subcomponent, shares
center axis 740 with tray cam insert 728, as shown. Preferably,
mounting aperture 734 is eccentrically located with respect to
center axis 740, passing through engaging portion 736 at a point
adjacent to center axis 740, as shown (herein embodying wherein such
at least one engager comprises at least one essentially cylindrical
member having at least one central axis, at least one radius and at
least one outer circumference and such at least one cam adjuster
comprises such at least one mounting aperture passing through such
at least one engager such that such at least one mounting aperture
is eccentrically located at a point adjacent to such at least one
central axis).
FIG. 23 is a diagram illustrating the operation of cam mounting
assembly 726 according to the preferred embodiment of FIG. 21. Screw
280, while engaged within mounting aperture 734, acts as pivot point
around which tray cam insert 728 may be rotated. Preferably, as
described in FIG. 22, mounting aperture 734 is eccentrically located
with respect to center axis 740 of tray cam insert 728, as shown.
Rotation of tray cam insert 728 permits engaging portion 736 to
function as a cam (herein embodying at least one cam adjuster
structured adapted to adjust the position of such at least one
engager), producing a transverse positional movement 729 with
respect to longitudinal axis 731, as shown (herein embodying wherein
rotation of such at least one cam adjuster produces at least one
substantially-transverse movement, relative to such at least one
longitudinal axis of such at least one support bar, of both such at
least one engager and the at least one avionics-component tray). As
engaging portion 736 is preferably engaged within mounting hole 730
during rotation, an essentially identical transverse positional
movement 729 is initiated in mounting tray 814, as shown.
With reference to FIG. 24 and with continued reference to FIG. 21
and FIG. 22, FIG. 24 is a perspective view, partially in section,
illustrating the assembled adjustable cam mounting assembly 726 of
FIG. 21. At least one, preferably, two tray cam insert(s) 728 are
used on each side 732 of mounting tray 814, as shown. Preferably,
mounting hole 730 is sized to provide a snug but rotatable fit
around outer circumference 742 of engaging portion 736 (herein
embodying wherein such at least one mounting hole is adapted to
receive such at least one essentially cylindrical member).
Preferably, mounting hole 730 has a preferred inner diameter
slightly greater than about 0.500 inch. Typically, mounting hole(s)
730 are retrofit within mounting tray 814 by drilling or punching
(herein embodying the steps of establishing at least one suitable
mounting position of the at least one avionics-components tray
adjacent to such at least one longitudinal slot portion and
providing within the at least one side of the at least one
avionics-components tray at least one new mounting hole, aligning
with such at least one longitudinal slot portion, to permit the at
least one avionics-components tray to be mounted in the at least one
suitable mounting position), however, under appropriate
circumstances, mounting hole(s) 730 may be provided as an OEM
feature. Preferably, to assist in rotation, tray cam insert 728
preferably comprises hex aperture 738 (herein embodying at least one
rotation assister to assist in rotating such at least one engager)
that is adapted to receive hand held hex wrench 744, as shown.
FIG. 25 is a front view of tray cam insert 728 according to the
embodiment of FIG. 21. Preferably, tray cam insert 728 has an outer
diameter "J" of about 0.625 inch, as shown. Preferably, mounting
aperture 734 comprises countersink screw receiver 746 to permit
flush installation of screw 280. Preferably, tray cam insert 728 is
comprised of a rigid material, preferably cast and or milled 304
stainless steel. Those skilled in the art, upon reading the
teachings of this specification, will appreciate that, under
appropriate circumstances, considering such issues as intended
service use and material cost, other materials, such as carbon
steel, titanium, aluminum, ceramics or plastic, may suffice.
FIG. 26 is a sectional view 26--26 according to FIG. 25 of tray cam
insert 728. Tray cam insert 728 has a preferred overall thickness
"K" of about 0.095 inch, as shown. Preferably, engaging portion 736
comprises a thickness "L" of about 0.065 inch, and a diameter "M" of
0.50 inch, as shown. Mounting aperture 734 has a preferred inner
diameter "N" of 0.150 with an inner diameter edge 748 located a
distance "O" of about 0.067 inch from outer circumference 742, as
shown.
In a series of preferred installation steps, adjustable cam mounting
assembly 726 is installed by inserting tray cam insert 728 through
mounting hole 730 followed by inserting Screw 280, through mounting
aperture 734 to loosely engage mounting nut assembly 300.
Preferably, using hand held hex wrench 744, tray cam insert 728 is
rotated to move mounting tray 814 to at least one user preferred
position. With mounting tray 814 in a preferred position, Screw 280
is tightened to firmly attach mounting tray 814 to mounting rack
component 200.
FIG. 27 is a front perspective view illustrating blanking plate 750
according to a preferred embodiment of the present invention. Often,
revisions and updates in the quantity and placement of aircraft
avionics leave portions of the instrument panel unused. Blanking
plate 750 is preferably adapted to snap securely into mounting rack
system 175 or multiple rack installation 500, permitting efficient
instrument panel closeout of a partial avionics stack.
Preferably, blanking plate 750 (herein embodying at least one
blanking cover adapted to cover unused portions of the general
aviation aircraft cockpit instrument panel) comprises filler panel
752, retainer(s) 754 and preferably two retainer holder(s) 756, as
shown. Preferably, filler panel 752 comprises blank front face 758
and rear face 760, as shown. Retainer holder 756 preferably
comprises a plurality of holding apertures 762 adapted to removably
hold one or more retainer(s) 754 in a fixed position relative to
front face 758, as shown (herein embodying wherein such at least one
retainer holder is adapted to adjustably hold such at least one
retainer in at least one selected position relative to such at least
one front face). Preferably, blanking plate 750 may comprise a
number of different factory supplied heights (to accommodate various
avionic combinations), and may be field cut to an exact height for
specific and non-standard installations.
Under appropriate circumstances, filler panel 752 may be used as the
base for an auxiliary switch 776 (shown in dashed lines) or circuit
breaker panel. Preferably, except as noted below, blanking plate 750
comprises substantially aluminum construction preferably with an
anodized finish, or under appropriate circumstances, a raw finish to
allow for custom panel matching.
FIG. 28 is a top view further illustrating the arrangements of
blanking plate 750 according to the embodiment of FIG. 27.
Preferably, both retainer holder(s) 756 are firmly mounted to rear
face 760, as shown. Preferably, each retainer holder 756 is
essentially L-shaped comprising a projecting leg 764 and mounting
leg 766 preferably joined to rear face 760, as shown. Preferably,
mounting leg 766 is preferably affixed to rear face 760 by bonding.
Those skilled in the art, upon reading the teachings of this
specification, will appreciate that, under appropriate
circumstances, considering such issues as cost and ease of
manufacture, other methods of affixing mounting leg 766 to rear face
760, such as welding and mechanical fastening, may suffice. To
prevent the bond between mounting leg 766 and rear face 760 from
acting as an electrical isolator, at least one electrical grounding
path (such as a point of metal-to-metal contact) is preferably
established between mounting leg 766 and rear face 760.
Preferably, retainer 754 is removable from holding apertures 762 of
retainer holder 756 to permit adjustments to the installed position
of front face 758, as shown.
FIG. 29 is a top view, in partial section, illustrating the
engagement of retainer 754 within mounting rack component 200
according to the embodiment of FIG. 27. Preferably, retainer 754
(herein embodying at least one spring loaded engager adapted to
removably engage such at least one support bar) comprises a
self-contained, spring-loaded plunger assembly having a rounded
cylindrical nose 768, tapered cylindrical body 770 and
circumferential flange 774, as shown. Preferably, cylindrical nose
768 is adapted to engage slot 772 of mounting rack component 200, as
shown, and is held in position by the frictional spring force
imparted by retainer 754. Preferably, retainer 754 comprises a
commercially available unit similar in specification to the push-fit
round-nose spring plunger model 8683A13 available from the
McMaster-CARR Corporation of Atlanta, Ga.
FIG. 30 is a rear view of blanking plate 750 according to the
embodiment of FIG. 27. Preferably, two retainer(s) 754 are used at
each retainer holder 756 of blanking plate 750, as shown.
FIG. 31 is a side view of the blanking plate 750 according to the
embodiment of FIG. 27. Preferably, retainer holder 756 (herein
embodying at least one adjuster to adjust the position of such
filler panel relative to the general aviation aircraft cockpit
instrument panel) comprises a plurality of holding aperture(s) 762
adapted to receive and removably hold retainer(s) 754, as shown.
Preferably, each holding aperture is uniquely positioned relative to
filler panel 752 to provide an efficient means of adjusting the
position of filler panel 752 relative to mounting rack component
200, as shown. Preferably, staggered pairs of holding aperture(s)
762 are arranged to permit at least one matching alignment of at
least two retainer(s) 754 relative to front face 758, as shown.
Although applicant has described applicant's preferred embodiments
of this invention, it will be understood that the broadest scope of
this invention includes such modifications as diverse shapes and
sizes and materials. Such scope is limited only by the below claims
as read in connection with the above specification.
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