Aircraft wire harness

1 . A transition assembly of a wire harness configured to be coupled to a plate in an aircraft, the transitional assembly including:

a slotted flange configured to abut a first side of the plate;

a junction having a flange configured to abut a second side of the plate, the flange including inwardly extending cutouts on opposite sides thereof forming a reduced width portion of the flange; and

a nut configured to couple to the junction.

2 . The transition assembly according to claim 1 , wherein the junction additionally includes a body a body having a first end, a second end configured to extend through an opening in the plate, and a passage extending therethrough, and wherein the flange surrounds the body.

3 . The transition assembly according to claim 2 , wherein the junction additionally includes an attachment area on an outer surface of the body between the second end and the flange, and wherein the nut is configured to couple to the junction at the attachment area.

4 . The transition assembly according to claim 1 , wherein the flange of the junction includes a first portion between the cutouts with a first width in a lateral direction perpendicular to a longitudinal direction of the junction and a second portion with a second width in the lateral direction greater than the first width.

5 . The transition assembly according to claim 4 , wherein the second portion includes a pair of abutment regions above and below the first portion that abut the second side of the plate.

6 . The transition assembly according to claim 5 , wherein the second portion includes a ledge configured to abut an inner surface of an opening in the mounting plate.

7 . The transition assembly according to claim 1 , wherein the slotted flange includes a first side configured to abut the first side of the plate, a second side configured to be abutted by a washer, a through hole, and a slot into the through hole.

8 . The transition assembly according to claim 7 , wherein the slotted flange additionally includes a pair of openings for receiving respective fasteners for coupling the slotted flange to the plate, and an orientation projection configured to be received in an orientation opening in the plate for aligning the slotted flange.

9 . The transition assembly according to claim 1 , further including a washer configured to be positioned between the nut and the slotted flange and to abut the slotted flange.

10 . The transition assembly according to claim 9 , wherein the washer includes a through hole to allow for positioning over the junction and a projection having an opening, and wherein the nut includes a through hole to allow for positioning over the junction and at least two openings in the side thereof.

11 . The transition assembly according to claim 10 , further including a cable extending through the opening in the projection and the at least two openings in the nut to prevent the nut from uncoupling form the junction.

12 . A junction configured to be coupled to a plate in an aircraft, the junction including:

a body having a first end, a second end configured to extend through an opening in the plate, and a passage extending therethrough between the first and second ends,

a flange surrounding the body and configured to abut a side of the plate, the flange including a first portion with a first width in a lateral direction perpendicular to a longitudinal direction of the body and a second portion with a second width in the lateral direction greater than the first width; and

an attachment area on an outer surface of the body between the second end and the flange.

13 . The junction according to claim 12 , wherein the flange includes cutouts on opposite sides thereof reducing the width of the flange, and wherein the first portion is formed between the cutouts.

14 . The junction according to claim 12 , wherein the attachment area includes threads for mating with corresponding threads on a nut.

15 . The junction according to claim 12 , wherein the second portion includes a pair of abutment regions above and below the first portion that abut the side of the plate.

16 . The junction according to claim 15 , wherein the second portion includes a ledge configured to abut an inner surface of the opening in the mounting plate.

17 . A method of installing a wire harness in a compartment in an aircraft, the wire harness including a high temperature section and a low temperature section separated by a transition assembly, the transition assembly including a junction having a flange with cutouts on opposite sides thereof, the method including:

advancing the high temperature section of the wire harness through an opening in a plate in the compartment of the aircraft;

navigating the transition assembly around components in the compartment;

coupling the transition assembly to the plate; and

coupling connectors of the wire harness with corresponding connectors in the aircraft.

18 . The method according to claim 17 , wherein the cutouts on the flange enable navigation of the junction around the components in the compartment.

19 . The method according to claim 17 , wherein coupling the transition assembly to the plate includes:

positioning the junction such that an end of the junction extends through the opening in the plate and the flange abuts a second side of the plate;

positioning a slotted flange relative to the plate such that the slotted flange abuts a first side of the plate;

securing the slotted flange to the plate;

advancing a washer of the transition assembly until the washer abuts the slotted flange; and

advancing a nut of the transition assembly over the end of the junction to threadably couple the nut to the junction.

20 . The method according to claim 19 , wherein coupling the transition assembly further includes coupling a cable to the washer and the nut to prevent accidental removal of the nut.