Interchangeability (ICY) is the ideal condition to improve serviceability of fighter aircrafts.
Components of non-flying aircraft can be utilized to make the availability of aircraft during war
situations‘ By achieving ICY down time of fleet can be reduced, aircraft structure panels are one
of the classic example 6f ICY. Any time the damaged panel of one aircraft can be replaced with
same panel of other aircraft. The conventional layout method cannot ensure ICY, special fixture
and tools are required to accomplish the task of ICY.
BACKGROUND OF INVENTION
Conventional method of drilling of aircraft structure by clamping the drill plate on the aircraft
structure can lead to variation in dimension of holes, since there is uneven surface ofjoggles at
the point of clamping. New concept of Drilling with compact fixture ensures hole normality
since the loading of Drill plate is on the Jig and not on the aircraft structural profile. With this
new concept of same datum, it will ensure easiness for technician to load the panels which will
ensure fool proof and improve productivity with good quality.
SUMMARY OF INVENTION
1. A Master Model is made by taking the following two pre-requisites
a. Designed by considering the Panel outer surface with the part end marking and
hole position as per the product design requirement.
b‘ The reference for Jig Mounting.
2. Derived Tool of 2 Numbers are made, one for Drilling the holes on the panél and
the other for Fitting on the Jig Structure to Drill holes on the Aircraft( Note:- The Tool
will leave a gap of component thickness from the
Making of Machined master model with drill hole position, part end marking and
Fitment of L angles as per the Jig references and inspect and make sure the hole
positions are within acceptable tolerance. (Figure 1)
Derived Drill plate is made by (Figure 2)
Inserting the alignment pin on to the master holes and doing the lay up .
over it. To make the hardened bush fitted on to the Derived Drill plate ,
the hardened bush is inserted on to the alignment pin and the layup is
done on the master model, restricting the lay up to the part boundary
with harden Steel plate. (Make sure releasing agent is' applied on the
master model and Alignment pin, since the alignment is to be removed
letting the hardened bush on to-the derived Tool once the curing is
completed)
Before completing the layup, mount the Profiled L angle on to the
Mounting holes of the Master and continue the Layup and allow the
Profiled L angle to get fitted on to the Derived Tool. Also counter sunk the
Profile plate on to the Drill plate (after curing) maintaining mounting
holes from master.
Repeat the above two steps; to get one more Derived Tool. And name the
Derived tool one as Drill Jig for panel and other as Drill plate for
Structure.
Derived Tool 1 will be used for drilling Holes on the Panel (Figure 3) and second Derived
Tooi 2 will be fitted on to the Jig for Drilling hole on the Aircraft Structure (Figure 4).
The Derived Tool 2 of all the panels of the Aircraft will be fitted on the common