(c)
Also clean the areas of the remaining conducting strip above the static discharger.
(d)
Use a clean gauze or cheesecloth to absorb the solvent before it dries.
NOTE: To prevent contamination on the surfaces, permit no more
____ than 1 hour span from the time you clean to the time you you bond.
(e)
Apply a thin layer of adhesive to the trailing edge of the winglet and to the conducting strip.
(f)
Do not apply adhesive to the ends of the strip where it makes an overlap with the remaining strip.
NOTE: New and remaining strips must have full electrical
____ contact at areas that make an overlap.
(g) Remove the unwanted adhesive with a clean gauze or cheesecloth lightly moist with solvent, Series 89 (AMM 20-30-89).
NOTE: Do not permit the solvent to get in the area that
____
you bond.
(h) Apply pressure and dry the bond (SRM 51-70-03).
S 418-008
(4) To complete the static discharger installation, you must obey AMM 23-61-00/201 and the instructions that follow:
(a) Apply sealant if it is necessary to fill the space where the new conducting strip makes an overlap with the remaining strip.
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(b)
Use the bonding meter to measure the resistance between the discharger base and the conducting strip (AMM 20-22-01/601).
(c)
To make sure that there is electrical contact between the strips, measure to the remaining conducting strip and to the new conducting strip.
NOTE: The resistance must be no more than 0.010 ohms.
____
(d) Measure the resistance between the rod and the base of the static dischargers that you installed during this repair (AMM 23-61-00/201).
S 378-020
(5) Apply the conductive strip finish.
(a)
Use smooth grit sandpaper to make the open surface of the conducting strip shiny.
(b)
Wash and rub the area clean.
(c)
Use a brush to apply Alodine 1200S or 1200 to the open surface of the strip.
NOTE: You will apply this last finish if it is necessary.
____
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PLATES/SKIN - DESCRIPTION AND OPERATION
_______________________________________
1. General_______
A. The exterior surface of the wing is formed by the wing skin, which can be divided into skin of primary and secondary structural importance. The primary wing skin forms the upper and lower external surface of the main frame. The secondary wing skins are those which do not carry primary loads and comprise wing leading and trailing edges, winglet, fairings, and the inspar skins outboard of the rib at wing station 1548.2.
2. Wing Primary Skin (Fig. 1)_________________
A. The outboard wing main frame beams do not incorporate production breaks between the wing root and the tip, and thus are adapted to the use of continous spanwise skin panels. The panels are preformed to fit the wing contour and are machine sculptured to provide the desired tapered basic thickness with thicker pads around access openings and at panel attachment areas. The skin panels extend chordwise beyond the front and rear spar chords and have machined recesses for leading and trailing edge skin attachments as required. The three upper skin panels are tapered so that the basic thickness increases from the root to the area of inboard nacelle, then reduces from the inboard nacelle to the wingtip. The outboard wing lower primary skin consists of five panels. As with the upper panels, no chordwise splices are used. Spanwise skin panel splices are made at stringers S5, S10 (mid spar), S15, and S20. Inspar structure access doors are provided in the No. 2 panel. The panels taper so that the basic skin thickness increases from the wing root to the area of the outboard track of the inboard trailing edge flaps, and then decreases on the remaining wing span to the wingtip. Spanwise stringers are attached to the inner surface of the skin panels. In the integral fuel tank areas, the skin panels are sealed to contain the fuel.
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