Abstract: A self-aligning structural attachment and a corresponding method are disclosed. The self-aligning structural attachment includes a main body having a proximal end and a distal end, wherein the main body is attached to (i) a CIP of a support system and (ii) a clevis on an airframe of an aircraft. Further, the self-aligning structural attachment includes a first attachment fitting disposed on the proximal end, wherein the first attachment fitting is a slide-and-swivel attachment fitting. Still further, the self-aligning structural attachment includes a second attachment fitting disposed on the distal end, wherein the second attachment fitting is a slide attachment fitting. Yet still further, the self-aligning structural attachment includes a pivoting hinge disposed between the first attachment fitting and the second attachment fitting.

Abstract: A dual-bracketed support system and a corresponding method are disclosed. The dual-bracketed support system includes (i) a first bracket connected to a support structure for a crown portion of an aircraft, (ii) a second bracket, and (iii) a support rod having a proximal end and a distal end. The proximal end is connected to the first bracket and the distal end is connected to the second bracket. The second bracket is configured to allow the support rod to translate along a longitudinal axis defined by the support rod.

Abstract: A self-aligning structural attachment and a corresponding method are disclosed. The self-aligning structural attachment includes a main body having a proximal end and a distal end, wherein the main body is attached to (i) a CIP of a support system and (ii) a clevis on an airframe of an aircraft. Further, the self-aligning structural attachment includes a first attachment fitting disposed on the proximal end, wherein the first attachment fitting is a slide-and-swivel attachment fitting. Still further, the self-aligning structural attachment includes a second attachment fitting disposed on the distal end, wherein the second attachment fitting is a slide attachment fitting. Yet still further, the self-aligning structural attachment includes a pivoting hinge disposed between the first attachment fitting and the second attachment fitting.

Abstract: A system for adjusting a height of a ceiling panel in an aircraft and a corresponding method is disclosed. The system includes an arm and at least one ceiling support latch, wherein each of the at least one ceiling support latches is attached to the arm. The system further includes an adjustable fitting attached to the arm, wherein the adjustable fitting includes (i) a first sliding block attached to the arm, (ii) a second sliding block attached to a support structure, and (iii) an adjustment screw. Adjustment of the adjustment screw forces the first and second sliding blocks to move relative to one another.

Abstract: A self-aligning structural attachment and a corresponding method are disclosed. The self-aligning structural attachment includes a main body having a proximal end and a distal end, wherein the main body is attached to (i) a CIP of a support system and (ii) a clevis on an airframe of an aircraft. Further, the self-aligning structural attachment includes a first attachment fitting disposed on the proximal end, wherein the first attachment fitting is a slide-and-swivel attachment fitting. Still further, the self-aligning structural attachment includes a second attachment fitting disposed on the distal end, wherein the second attachment fitting is a slide attachment fitting. Yet still further, the self-aligning structural attachment includes a pivoting hinge disposed between the first attachment fitting and the second attachment fitting.

Abstract: A support system for a crown area of an aircraft and a corresponding method is disclosed. The support system includes a crown integration panel (CIP). The CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide an electrical ground for at least one of the aircraft equipment of the plurality of aircraft equipment. The system further includes a first attachment and a second attachment attached to the CIP. The first attachment and the second attachment are configured to attach to an airframe of the aircraft. The system further includes a crown raceway support (CRS) having a first end and a second end, where the first end is attached to a first end of the CIP and the second end is configured to attach to an outboard rail of the aircraft.

Abstract: A support system for a crown area of an aircraft and a corresponding method is disclosed. The support system includes a crown integration panel (CIP). The CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide an electrical ground for at least one of the aircraft equipment of the plurality of aircraft equipment. The system further includes a first attachment and a second attachment attached to the CIP. The first attachment and the second attachment are configured to attach to an airframe of the aircraft. The system further includes a crown raceway support (CRS) having a first end and a second end, where the first end is attached to a first end of the CIP and the second end is configured to attach to an outboard rail of the aircraft.

Abstract: A system for adjusting a height of a ceiling panel in an aircraft and a corresponding method is disclosed. The system includes an arm and at least one ceiling support latch, wherein each of the at least one ceiling support latches is attached to the arm. The system further includes an adjustable fitting attached to the arm, wherein the adjustable fitting includes (i) a first sliding block attached to the arm, (ii) a second sliding block attached to a support structure, and (iii) an adjustment screw. Adjustment of the adjustment screw forces the first and second sliding blocks to move relative to one another.

Abstract: A self-aligning structural attachment and a corresponding method are disclosed. The self-aligning structural attachment includes a main body having a proximal end and a distal end, wherein the main body is attached to (i) a CIP of a support system and (ii) a clevis on an airframe of an aircraft. Further, the self-aligning structural attachment includes a first attachment fitting disposed on the proximal end, wherein the first attachment fitting is a slide-and-swivel attachment fitting. Still further, the self-aligning structural attachment includes a second attachment fitting disposed on the distal end, wherein the second attachment fitting is a slide attachment fitting. Yet still further, the self-aligning structural attachment includes a pivoting hinge disposed between the first attachment fitting and the second attachment fitting.

Abstract: A dual-bracketed support system and a corresponding method are disclosed. The dual-bracketed support system includes (i) a first bracket connected to a support structure for a crown portion of an aircraft, (ii) a second bracket, and (iii) a support rod having a proximal end and a distal end. The proximal end is connected to the first bracket and the distal end is connected to the second bracket. The second bracket is configured to allow the support rod to translate along a longitudinal axis defined by the support rod.

Abstract: An illumination system for an aircraft interior has an illumination source. An optical module is coupled to the illumination source. The optical module collects the light emissions from the light source and distributes the collected light over a desired area with a specified intensity profile.

Abstract: An illumination system for an aircraft interior has an illumination source. An optical module is coupled to the illumination source. The optical module collects the light emissions from the light source and distributes the collected light over a desired area with a specified intensity profile.