AFS-640

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AFS-640 ( afs-640 )

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9/27/01 AC 43.13-1B CHG 1 FIGURE 2-12. Fabric attachment spacing b. When the original lace spacing on the empennage surfaces and fuselage, is not known, a maximum spacing of two times the spacing shown in figure 2-12 for the slipstream area (prop wash) on the wings may be used. c. The installations of fabric attach- ments such as screws, rivets, wire clips, and rib lacing should be delayed until the fabric is stabilized and pulled taut with dope. This ac­ tion is delayed to avoid pulling wing ribs and other structures out of alignment or tearing the fabric at attachment points as the fabric be­ comes taut. All lacing should be installed ad­ jacent to the structure to which the fabric is being laced, to avoid tearing the fabric and/or creating slack in the cord loop when a load is applied. Where plastic washers were used by the aircraft manufacturer to provide increased pull-through resistance, under the heads of riv­ ets or screws, the same diameter aluminum washer may be used as replacement. Alumi­ num washers are used because they are not affected by solvents found in adhesives or dopes, nor do they become brittle because of age or cold weather. 2-12. FASTENERS. Several light aircraft designs employ screws, rivets, or single-wire metal clips to secure the fabric to the wing. a. Screws holding the old fabric can be removed after spinning a small sharpened tube around each screw or using a razor blade to cut and peel away the finishing tape. Care must be taken not to mark or scribe the underlying metal or wood structure. Blind rivets through ribs can be removed by drilling in the center to undercut the head. b. Single-wire clips may be removed without damage to the rib by inserting a wide, thin screwdriver blade under the clip and care­ fully twisting. Apply a lifting force at the clip end to pull it up through the hole. Par 2-11 Page 2-21

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