Non-metallic part 2

Which of the following are generally characteristic of aramid fiber (Kevlar) composites?. High tensile strength and flexibility. High tensile strength and stiffness. Corrosive effect in contact with aluminum and ability to conduct electricity.

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.

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 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.

The classification for fiberglass reinforcement material that has high resistivity and is the most common is. E-glass. S-glass. G-glass.

When balsa wood is used to replace a damaged honeycomb core, the plug should be cut so that. the grain is parallel to the skin. it is about 1/8 inch undersize to allow sufficient bonding material to be applied. the grain is perpendicular to the skin.

The I-beam wooden spar is routed to. increase strength. obtain uniform strength. reduce weight.

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

Composite fabric material is considered to be the strongest in what direction?. Fill. Warp. Bias.

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.

Which statement is true regarding a cantilever wing?. It has nonadjustable lift struts. No external bracing is needed. It requires only one lift strut on each side.

When necessary, what type of cutting fluid is usually acceptable for machining composite laminates?. Water soluble oil. Water displacing oil. Water only.

Which fiber to resin (percent) ratio for advanced composite wet lay-ups is generally considered the best for strength?. 40:60. 50:50. 60:40.

Laminated wood spars may be substituted for solid rectangular wood spars. only in certain instances where the primary load is shared by one or more other original structural member. if the same quality wood is used in both. only upon specific approval by the manufacturer or the FAA.

Fabric rejuvenator is used to. restore the condition of dope coatings. restore fabric strength and tautness to at least the minimum acceptable level. penetrate the fabric and restore fungicidal resistance.

One of the best ways to assure that a properly prepared batch of matrix resin has been achieved is to. perform a chemical composition analysis. have mixed enough for a test sample. test the viscosity of the resin immediately after mixing.

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.

Machine-sewn seams in aircraft covering fabrics may be of which of the following types?. Folded-fell or plain lapped. Folded-fell, French-fell, or plain lapped. French-fell or plain lapped.

Which statement concerning wood decay is correct?. Decay that appears to be mineral streaks is acceptable. A limited amount of decay along the beveled edges of unrouted beams is acceptable. Any form or amount of decay is not permitted.

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.

What is the purpose of a gusset or gusset plate used in the construction and repair of aircraft structures?. To hold structural members in position temporarily until the permanent attachment has been completed. To provide access for inspection of structural attachments. To join and reinforce intersecting structural members.

Which is considered good practice concerning the installation of acrylic plastics?. When nuts and bolts are used, the plastic should be installed hot and tightened to a firm fit before the plastic cools. When rivets are used, adequate spacer or other satisfactory means to prevent excessive tightening of the frame to the plastic should be provided. When rivets or nuts and bolts are used, slotted holes are not recommended.

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

The length of time that a catalyzed resin will remain in a workable state is called the. pot life. work life. plyable life.

The monocoque fuselage relies largely on the strength of. longerons and formers. skin or covering. bulkheads and longerons.

The cantilever wing uses. external struts or wire bracing. no external bracing. the skin to carry most of the load to the wing butt.

Superficial scars, scratches, surface abrasion, or rain erosion on fiberglass laminates can generally be repaired by applying. a piece of resin-impregnated glass fabric facing. one or more coats of suitable resin (room-temperature catalyzed) to the surface. a sheet of polyethylene over the abraded surface and one or more coats of resin cured with infrared heat lamps.

When installing transparent plastic enclosures which are retained by bolts extending through the plastic material and self-locking nuts, the nuts should be. tightened to a firm fit, plus one full turn. tightened to a firm fit, then backed off one full turn. tightened to a firm fit.

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. maximum wing loading. speed of the aircraft. speed of the aircraft and the maximum wing loading.

In cases of elongated bolt holes in a wood spar or cracks in the vicinity of boltholes,. it is permissible to ream the hole, plug with hardwood, and redrill. the spar may be reinforced by using hardwood reinforcing plates. a new section of spar should be spliced in or the spar replaced entirely.

Pin knot clusters are permitted in wood aircraft structure provided. they produce a small effect on grain direction. they have no mineral streaks. no pitch pockets are within 12 inches.

How does acoustic emission testing detect defects in composite materials?. By picking up the 'noise' of any deterioration that may be present. By analyzing ultrasonic signals transmitted into the parts being inspected. By creating sonogram pictures of the areas being inspected.

A category of plastic material that is capable of softening or flowing when reheated is described as a. thermoplastic. thermocure. thermoset.

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

A faint line running across the grain of a wood spar generally indicates. compression failure. shear failure. decay.

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.

When conducting a tap test on a composite panel, which of the following sounds would indicate delamination?. Sharp ringing. Dull thud. Sharp thud.

The coefficient of expansion of most plastic enclosure materials is. greater than both steel and aluminum. greater than steel but less than aluminum. less than either steel or aluminum.

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

The preferred way to make permanent repairs on composites is by. bonding on metal or cured composite patches. riveting on metal or cured composite patches. laminating on new repair plies.

The strength of a well-designed and properly prepared wood splice joint is provided by the. bearing surface of the wood fibers. glue. reinforcement plates.

Which parts of a semi-monocoque fuselage prevent tension and compression from bending the fuselage?. Ribs and formers. Longerons and stringers. Bulkheads and skin.