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AC 43.13-1B 9/8/98 A, B, C, D = ORIGINAL DIMENSIONS FIGURE 1-8. Method of splicing box spar flanges (plate method). shown in section B-B, is continued the full distance between spars. (3) Figure 1-12(C) illustrates a com- pression rib of the āIā type with a rectangular vertical member on each side of the web. The method of repair is essentially the same as in figure 1-12(A) except the plywood reinforce- ment plates on each side, shown as striped blocks in section C-C, are continued the full distance between spars. 1-47. PLYWOOD SKIN REPAIR. Make extensive repairs to damaged stressed skin plywood structures in accordance with specific recommendations from the aircraft manufac- turer. It is recommended that repairs be made by replacing the entire panel, from one struc- tural member to the next, if damage is very extensive. When damaged plywood skin is re- paired, carefully inspect the adjacent internal structure for possible hidden damage. Repair any defective frame members prior to making skin repairs. 1-48. DETERMINATION OF SINGLE OR DOUBLE CURVATURE. Much of the outside surface of plywood aircraft is curved. On such areas, plywood used for repairs to the skin must be similarly curved. Curved skins are either of single curvature or of double (compound) curvature. A simple test to de- termine which type of curvature exists may be made by laying a sheet of heavy paper on the surface in question. If the sheet can be made to conform to the surface without wrinkling, the surface is either flat or single curvature. If the sheet cannot be made to conform to the surface without wrinkling, the surface is of double curvature. 1-49. REPAIRS TO SINGLE CURVA- TURE PLYWOOD SKIN. Repairs to single curvature plywood skin may usually be formed from flat plywood, either by bending it dry or after soaking it in hot water. The degree of curvature to which a piece of plywood can be bent will depend upon the direction of the grain and the thickness. Table 1-2 is a guide Page 1-20 Par 1-46PDF Image | AFS-640
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