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9/27/01 AC 43.13-1B CHG 1 2-30. GENERAL. All components of the covering should be inspected for general con- dition. Loose finishing tape and reinforcing patches; chafing under fairings; brittle, crack- ing, peeling, or deteriorated coatings; fabric tears and rock damage; broken or missing rib lacing; and rodent nests are unacceptable. The entire fabric covering should be uniformly taut with no loose or wrinkled areas, or excess ten- sion which can warp and damage the airframe. a. Excess Tension. There are no methods or specifications for measuring acceptable fab- ric tension other than observation. Excess ten- sion may warp critical components, such as longerons, wing rib, and trailing edges out of position, weakening the airframe structure. (1) Excess tension with cotton, linen, and glass fiber fabric covering is usually caused by excessive dope film on a new cov- ering, or continuous shrinking of an originally satisfactory dope film as the plasticizers mi- grate from the dope with age. Heat from sun exposure accelerates plasticizer migration. (2) Excess tension with polyester fabric, coated with dope, is usually caused by the combined tension of the heat tautened polyes- ter fabric and continuous shrinking of the dope film as the plasticizers migrate from the dope with age. b. Loose Fabric. Fabric that flutters or ripples in the propeller slipstream, balloons, or is depressed excessively in flight from the static position, is unacceptable. (1) Loose or wrinkled cotton, linen, and glass fabric covering may be caused by inade- quate dope film; poor quality dope; fabric in- stalled with excess slack; or by a bent, broken, or warped structure. (2) Loose or wrinkled polyester fabric covering, finished with coatings other than dope, may be caused by inadequate or exces- sive heat application; excess slack when the fabric was installed; or bent or warped struc- ture. Polyester fabric which does not meet air- craft quality specifications will very likely be- come loose after a short period of time. (3) Glass fabric covering should be tested with a large suction cup for rib lacing cord failure and reinforcing tape failure caused by chafing on all wing ribs and other structural attachments throughout the airframe. Particu- lar attention should be given to the area within the propeller slipstream. If failure is indicated by the covering lifting from the static position, the rib lacing cord and reinforcing tape must be reinstalled with double the number of origi- nallaces. NOTE: Temporary wrinkles will de- velop in any fabric coated and fin- ished with dope, when moisture from rain, heavy fog, or dew is absorbed into a poor-quality dope film, causing the film to expand. Temporary wrin- kles may also develop with any type of thick coatings, on any type of fabric, when an aircraft is moved from a cold storage area to a warm hangar or parked in the warming sunshine, causing rapid thermal expansion of the coating. c. Coating Cracks. Fabric exposed through cracks in the coating may be initially tested for deterioration by pressing firmly with a thumb to check the fabric’s strength. Natural fibers deteriorate by exposure to ultraviolet ra- diation, mildew, fungus from moisture, high acid-content rain, dew, fog, pollution, and age. Polyester filaments will deteriorate by expo- sure to UV radiation. Par 2-30 Page 2-33 SECTION 3. INSPECTION AND TESTINGPDF Image | AFS-640
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