Crown raceway support (CRS) for crown integration panel (CIP)

1. A dual-bracketed support system for a crown portion of an aircraft, comprising:

a first bracket directly connected to a support structure of the crown portion of the aircraft;

a second bracket;

a support rod having a proximal end and a distal end, wherein the proximal end is directly connected to the first bracket and the distal end is directly connected to the second bracket, wherein a first fastener directly connects the proximal end of the support rod to the first bracket, wherein the support rod comprises a slot and a second fastener directly connects the distal end to the second bracket via the slot;

wherein the first bracket is configured to allow the support rod to rotate relative to the first bracket;

wherein the second bracket is connected to the support rod in a manner that enables the support rod to translate along a longitudinal axis of the support rod by the second fastener moving within the slot of the support rod.

2. The dual-bracketed support system of claim 1 , wherein the first fastener comprises a tightened fastener.

3. The dual-bracketed support system of claim 2 , wherein the tightened fastener comprises a nut and a bolt, and wherein the first bracket comprises a slot configured to receive the proximal end of the support rod, and wherein a width of the slot is greater than a width of the proximal end so as to allow the support rod to rotate relative to the first bracket.

4. The dual-bracketed support system of claim 1 , wherein the first fastener comprises a pin fastener, and wherein the pin fastener allows the support rod to rotate about a longitudinal axis of the pin fastener.

5. The dual-bracketed support system of claim 1 , wherein the second bracket is further configured to prevent rotations of the support rod relative to the second bracket and to prevent translations of the support rod other than translation along the longitudinal axis of the support rod.

6. The dual-bracketed support system of claim 1 , wherein the support structure is a crown integration panel (CIP) configured to provide a mounting surface for a plurality of additional aircraft equipment mounted to the CIP and to provide a ground for at least one of the aircraft equipment of the plurality of additional aircraft equipment.

7. The dual-bracketed support system of claim 1 , wherein the second bracket is directly connected to an outboard rail of the aircraft.

8. The dual-bracketed support system of claim 1 , the system further comprising a plurality of wires, wherein the plurality of wires are mounted to the support rod.

9. The dual-bracketed support system of claim 1 , wherein motion along an X axis corresponds to fwd or aft motion, motion along a Y axis corresponds to inboard or outboard motion, and motion along a Z axis corresponds to up or down motion, and

wherein translation along the longitudinal axis of the support rod corresponds to translation in a YZ direction.

10. A dual-bracketed support system for a crown portion of an aircraft, comprising:

a first bracket directly connected to a support structure of the crown portion of the aircraft;

a second bracket directly connected to an outboard rail of the aircraft;

a support rod having a proximal end and a distal end, wherein the proximal end is directly connected to the first bracket and the distal end is directly connected to the second bracket, wherein a first fastener directly connects the proximal end of the support rod to the first bracket, wherein the support rod comprises a slot and a second fastener directly connects the distal end to the second bracket via the slot;

wherein the first bracket is configured to allow the support rod to rotate relative to the first bracket;

wherein the second bracket is connected to the support rod in a manner that enables the support rod to translate along a longitudinal axis of the support rod by the second fastener moving within the slot of the support rod, and wherein the second bracket is further configured to prevent rotations of the support rod relative to the second bracket.

11. The dual-bracketed support system of claim 10 , wherein the support structure is a crown integration panel (CIP) configured to provide a mounting surface for a plurality of additional aircraft equipment mounted to the CIP and to provide a ground for at least one of the aircraft equipment of the plurality of additional aircraft equipment.

12. The dual-bracketed support system of claim 10 , wherein the first fastener comprises a nut and bolt.

13. The dual-bracketed support system of claim 12 , wherein the first bracket comprises a slot configured to receive the proximal end of the support rod, and wherein a width of the slot is greater than a width of the proximal end so as to allow the support rod to rotate relative to the first bracket.

14. The dual-bracketed support system of claim 10 , wherein the second bracket is further configured to prevent translations of the support rod other than translation along the longitudinal axis of the support rod.

15. The dual-bracketed support system of claim 10 , further comprising additional equipment attached to the support rod, wherein translation of the support rod along the longitudinal axis of the support rod limits strain on the additional equipment attached to the support rod.

16. The dual-bracketed support system of claim 10 , wherein the first fastener comprises a tightened fastener.

17. The dual-bracketed support system of claim 10 , the system further comprising a plurality of wires, wherein the plurality of wires are mounted to the support rod.

18. A method comprising:

providing the dual-bracketed support system for a crown portion of an aircraft of claim 1 ;

attaching a plurality of wires to the support rod, wherein during the attaching of the plurality of wires the support rod is arranged in a first position; and

after attaching the plurality of wires, rotating the support rod from the first position to a second position.

19. The method of claim 18 , wherein rotating the support rod from the first position to a second position comprises rotating the support rod at least 100 degrees.

20. The method of claim 18 , further comprising:

after rotating the support rod from the first position to the second position, attaching the second bracket to an outboard rail of the aircraft,

wherein attaching the wires takes place outside of the aircraft, and wherein attaching to the outboard rail takes place within the aircraft.