NON METALLIC STRUCTURE 3

Fiberglass laminate damage not exceeding the first layer or ply can be repaired by. Filling with a putty consisting of a compatible resin and clean, short glass fibers. sanding the damaged area until aerodynamic smoothness is obtained. trimming the rough edges and sealing with paint.

If a new safety belt is to be installed in an aircraft, the belt must conform to the strength requirements in which document?. STC 1282. 14 CFR Part 39. TSO C22.

The classification for high tensile strength fiberglass used in aircraft structures is. E-glass. S-glass. G-glass.

If an aircraft's transparent plastic enclosures exhibit fine cracks which may extend in a network over or under the surface or through the plastic, the plastic is said to be. hazing. brinelling. crazing.

The part of a replacement honeycomb core that must line up with the adjacent original is the. cell side. ribbon direction. cell edge.

When making repairs to fiberglass, cleaning of the area to be repaired is essential for a good bond. The final cleaning should be made using. MEK (methyl ethyl ketone). soap, water, and a scrub brush. a thixotropic agent.

Which is an identifying characteristic of acrylic plastics?. Zinc chloride will have no effect. Acrylic has a yellowish tint when viewed from the edge. Acetone will soften plastic, but will change its color.

What reference tool is used to determine how the fiber is to be oriented for a particular ply of fabric?. Fill clock (or compass). Bias clock (or compass). Warp clock (or compass).

Where is information found concerning acceptable species substitutions for wood materials used in aircraft repair?. AC 43.13-1. Aircraft Specifications or Type Certificate Data Sheets. Technical Standard Orders.

Hole filling fasteners (for example, MS20470 rivets) should not be used in composite structures primarily because of the. possibility of causing delamination. increased possibility of fretting corrosion in the fastener. difficulty in forming a proper shop head.

Servicing diagrams that show the arrangement of equipment and location of quick access doors on an aircraft can be found in the. Type Certificate Data Sheets. pilot's operating handbook. aircraft manufacturer's maintenance manual.

Which type of monocoque structure has the skin reinforced by a complete framework of structural members?. Semimonocoque. Reinforced shell. Monocoque.

When and how is finishing tape applied on a fabric-covered aircraft?. Sewed or laced on before dope is applied. Doped on immediately prior to the finish coat. Doped on after the first or second coat of dope.

Metal fasteners used with carbon/ graphite composite structures. may be constructed of any of the metals commonly used in aircraft fasteners. must be constructed of material such as titanium or corrosion resistant steel. must be constructed of high strength aluminum-lithium alloy.

Laminated wood is sometimes used in the construction of highly stressed aircraft components. This wood can be identified by its. parallel grain construction. similarity to standard plywood construction. perpendicular grain construction.

For doped and overlapping span- wise seams on a wing's leading edge, overlap the fabric at least 4 inches, and. cover with finishing tape at least 3 inches wide, with the tape centered on the leading edge of the wing. cover with finishing tape at least 4 inches wide, with the tape centered on the leading edge of the wing. cover with finishing tape at least 4 inches wide, with the tape centered at the outside edge of the overlap seam.

Which of the following drill bit types work best when drilling an aramid fiber (Kevlar) composite laminate?. Tool steel with standard grind. Diamond dust coated. Carbide W-point.

When dope-proofing the parts of the aircraft structure that come in contact with doped fabric, which of the following provide an acceptable protective coating?. Resin impregnated cloth tape and cellulose tape. Aluminum foil and resin impregnated cloth tape. Aluminum foil and cellulose tape.

When inspecting a composite panel using the ring test/tapping method, a dull thud may indicate. less than full strength curing of the matrix. separation of the laminates. an area of too much matrix between fiber layers.

Which of these methods may be used to inspect fiberglass/honeycomb structures for entrapped water?. Backlighting and acoustic emission monitoring. X-ray and acoustic emission monitoring. X-ray and backlighting.