as represented in fig1 and 5 the spacing between the first leg distal ends 48 50 52 and the second leg distal ends 48 u2032 50 u2032 52 u2032 enables the legs to be positioned on an interior surface of the aircraft structure on opposite sides of a previously constructed component to be protected by the apparatus as represented in fig8 additionally the distance between the first leg distal ends 48 50 52 and the second leg distal ends 48 u2032 50 u2032 52 u2032 enables the support legs to be positioned against adjacent stringers 82 84 in the interior of the aircraft structure as represented in fig8 this engagement of the support legs 38 40 42 38 u2032 40 u2032 42 u2032 with the adjacent stringers 82 84 provides further support to the apparatus 10 in the second relative positions of the first part 12 and the second part 14 the first support surface area 16 and the second support surface area 16 u2032 form a continuous support surface over the previously constructed components in the interior of the aircraft structure the continuous support surface protects the previously constructed components from potential damage by the worker working at the work site for example from a dropped tool or a worker inadvertently exerting a force against the previously constructed component as various modifications could be made in the construction of the apparatus and its method of operation herein described and illustrated without departing from the scope of the invention it is intended that all matter contained in the foregoing description or shown in the accompanying drawings shall be interpreted as illustrative rather than limiting thus the breadth and scope of.