US 11,811,200 B2
Installation tool and method
Timothy Sanderson, Bristol (GB); and Stuart Quayle, Bristol (GB)
Assigned to AIRBUS OPERATIONS LIMITED, Bristol (GB)
Filed by Airbus Operations Limited, Bristol (GB)
Filed on Mar. 28, 2019, as Appl. No. 16/367,745.
Claims priority of application No. 1805158 (GB), filed on Mar. 29, 2018.
Prior Publication US 2019/0305530 A1, Oct. 3, 2019
Int. Cl. H02G 1/08 (2006.01); H02G 3/22 (2006.01); H02G 1/06 (2006.01); B64F 5/40 (2017.01); B64F 5/10 (2017.01); B60P 7/14 (2006.01); F16L 41/12 (2006.01); F16L 47/16 (2006.01); F16L 47/20 (2006.01); B64D 37/00 (2006.01); B64C 1/10 (2006.01); B25B 27/16 (2006.01); B25B 27/14 (2006.01)
CPC H02G 1/085 (2013.01) [B25B 27/14 (2013.01); B25B 27/16 (2013.01); B60P 7/14 (2013.01); B64C 1/10 (2013.01); B64D 37/005 (2013.01); B64F 5/10 (2017.01); B64F 5/40 (2017.01); F16L 41/12 (2013.01); F16L 47/16 (2013.01); F16L 47/20 (2013.01); H02G 1/06 (2013.01); H02G 3/22 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A combination of an aircraft bulkhead connector and an installation tool, wherein:
the bulkhead connector comprises a female end portion and the installation tool comprises a male end portion opposing a distal end portion of the installation tool;
the male end portion of the installation tool is removably engaged with the female end portion of the bulkhead connector, such that the installation tool protrudes beyond the female end portion of the bulkhead connector in a direction away from the bulkhead connector such that the installation tool passes through the bulkhead; and,
wherein the installation tool tapers at the distal end portion protruding beyond the bulkhead.