Airframe - Wood structures

Laminated wood spars may be substituted for solid rectangular wood spars. if the same quality wood is used in both. NIL.

The strenght of a well-designed and properly prepared wood slice joint is provided by the. glue. NIL.

Where is information found concerning acceptable species substitutions for wood materials used in aircraft repair?. AC 43.13-1B. NIL.

In cases of elongated boltholes in a wood spar or cracks in the vicinity to boltholes. a new section of spar should be spliced in or the spar replaced entirely. NIL.

A faint line running across the grain of a wood spar generally indicates. Compression failure. Nil.

Any wooden member that has been overstressed is subject to which type of failure?. Compression. NIL.

Which statement about wood decay is correct?. Decay is not acceptable in any form or amount. NIL.

Which statement concerning wood decay is correct?. Any form or amount of decay is not permitted. NIL.

Which of the following conditions will determine acceptance of wood with mineral streaks?. Careful inspection fails to reveal any decay. NIL.

Pin knot clusters are permitted in wood aircraft structure provided. They produce a small effect on grain direction. NIL.

The cantilever wing uses. No external bracing. NIL.

Laminated wood is sometimes used in the construction of highly stressed aircraft components. This wood can be identified by its. parallel grain construction. NIL.

When patching a plywood skin, abrupt changes in cross-sectional areas which will develop dangerous stress concentration should be avoided by using. Circular or elliptical patches. NIL.

Glue deterioration in wood aircraft structure is indicated. When a joint has separated and the glue surface shows only the imprint of the wood with no wood fibers clinging to the glue. NIL.

Compression failures in wood aircraft structures are characterized by buckling of the fibers that appear as streaks on the surface. at right angles to the grain. NIL.

When and how is finishing tape applied on a fabric covered aircraft?. Doped on after the first or second coat of dope. NIL.

The determining factor(s) for the selection of the correct weight of textile fabric to be used in covering any type of aircraft is the. Speed of the aircraft and the maximum wing loading. NIL.

How many fabric thicknesses will be found in a French-fell seam?. Four. N/A.

Finishing tape (surface tape) is used for what purpose?. To provide additional wear resistance over the edges of fabric forming structures. NIL.

Moisture, mildew, chemicals, and acids have no effect on. glass fabric. NIL.

Fungicide and mildewicide additives are important for fabric covered aircraft, such as. cotton and linen. NIL.

The best method of repair for fabric-covered surface which has a L-shaped tear, each leg of which is approximately 14 inches long, is to. sew with a baseball stitch from the center of the tear out toward the extremity of each leg and the dope on a patch. NIL.

The strenght classification of fabrics used in aircraft covering is based on. tensile strenght. NIL.

Fabric rejuvenator is used to. restore the condition of dope coatings. NIL.

(1) Machine-sewn seams in aircraft covering fabrics may be of the folded-fell or French-fell types. (2) A plain lapped seam is never permissible. only No. 1 is true. NIL.

When testing the strenght of Grade A cotton fabric covering an aircraft that requires only intermediate grade, the minumim acceptable strenght the fabric must have is. 70 percent of the original strenght for intermediate fabric. NIL.

When dope-proofing the parts of the aircraft structure that come in contact with dope fabric, which of the following provide an acceptable protective coating? 1. Aluminum foil. 2. Resin impregnated cloth tape 3. Any one-part type metal primer. 4. Cellulose tape. 1 and 4. NIL.