Method and arrangement for easily repairing electrical harness for aircraft jet engine
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Nov 7, 2000
Issued Date -
N/A
app pub date -
Apr 17, 1998
filing date -
Apr 19, 1996
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
An enhanced electrical harness arrangement for an aircraft engine that is arranged to provide optimum protection of the electrical conductors from extreme thermal, EMI, vibration and chafing problems encountered in service. The harness arrangement provides a high degree of repairability thereby ensuring a long service life for the harness wile also minimizing the time required for necessary repairs to the electrical conductor terminals. A repair splice member has an electrical conductor bundle inserted through it and is spaced from a connection of the electrical conductor bundle to an aircraft gas turbine engine. The repair splice member is placed within an outer protective layer of the harness and is provided with shoulder portions, as is the backshell, for accommodating removal and replacement, as required, of protective layers of the harness positioned between the repair splice member and the backshell thereby permitting unraveling or damaged portions of the protective layers to be replaced and electrical conductor connections to be repaired in an airworthy repair procedure without the necessity of replacement of the entire harness in the field. A method for conducting such repair procedures for the harness arrangement is disclosed.
First Claim
Other Claims data not available