Airframes Knowledge Test Question Bank

Please Note:

Subject matter codes appear above each item.

A.8.0.0.1.A.1 A01

Laminated wood spars may be substituted for solid rectangular wood spars

A. only in certain instances where the primary load is shared by one or more other original structural member.

B. if the same quality wood is used in both.

C. only upon specific approval by the manufacturer or the FAA.

A.8.0.0.2.A.1 A01

The strength of a well designed and properly prepared wood splice joint is provided by the

A. bearing surface of the wood fibers.

B. glue.

C. reinforcement plates.

A.8.0.0.3.A.1 A01

Where is information found concerning acceptable species substitutions for wood materials used in aircraft repair?

A. Aircraft Specifications or Type Certificate Data Sheets.

B. AC 43.13-1B.

C. Technical Standard Orders.

A.8.0.0.4.A.1 A01

In cases of elongated boltholes in a wood spar or cracks in the vicinity of boltholes,

A. the spar may be reinforced by using hardwood reinforcing plates.

B. it is permissible to ream the hole, plug with hardwood, and redrill.

C. a new section of spar should be spliced in or the spar replaced entirely.

A.8.0.0.5.A.1 A02

A faint line running across the grain of a wood spar generally indicates

A. shear failure.

B. decay.

C. compression failure.

A.8.0.0.6.A.1 A02

Which statement about wood decay is correct?

A. Decay that occurs before the wood is seasoned does not affect the strength of the finished piece.

B. A limited amount of certain kinds of decay is acceptable in aircraft woods since decay affects the binding between the fibers and not the fibers themselves.

C. Decay is not acceptable in any form or amount.

A.8.0.0.7.A.1 A02

Which of the following conditions will determine acceptance of wood with mineral streaks?

A. Careful inspection fails to reveal any decay.

B. They produce only a small effect on grain direction.

C. Local irregularities do not exceed limitations specified for spiral and diagonal grain.

A.8.0.0.8.A.1 A02

The I beam wooden spar is routed to

A. reduce weight.

B. increase strength.

C. obtain uniform strength.

A.8.0.0.9.A.1 A02

Pin knot clusters are permitted in wood aircraft structure provided

A. they produce a small effect on grain direction.

B. they have no mineral streaks.

C. no pitch pockets are within 12 inches.

A.8.0.1.0.A.1 A02

The cantilever wing uses

A. the skin to carry most of the load to the wing butt.

B. external struts or wire bracing.

C. no external bracing.

A.8.0.1.1.A.1 A03

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

A. parallel grain construction.

B. similarity to standard plywood construction.

C. perpendicular grain construction.

A.8.0.1.2.A.1 A03

When patching a plywood skin, abrupt changes in cross sectional areas which will develop dangerous stress concentration should be avoided by using

A. doublers with any desired shaped patches.

B. square patches.

C. circular or elliptical patches.

A.8.0.1.3.A.1 A03

Glue deterioration in wood aircraft structure is indicated

A. when a joint has separated and the glue surface shows pieces of wood and/or wood fibers clinging to the glue.

B. when a joint has separated and the glue surface shows only the imprint of the wood with no wood fibers clinging to the glue.

C. by any joint separation.

A.8.0.1.4.A.1 A03

Compression failures in wood aircraft structures are characterized by buckling of the fibers that appear as streaks on the surface

A. parallel to the grain.

B. at right angles to the grain.

C. at right angles to the growth rings.

B.8.0.1.5.A.1 B01

When and how is finishing tape applied on a fabric covered aircraft?

A. Doped on immediately prior to the finish coat.

B. Doped on after the first or second coat of dope.

C. Sewed or laced on before dope is applied.

B.8.0.1.6.A.1 B01

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

A. speed of the aircraft.

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

C. maximum wing loading.

B.8.0.1.7.A.1 B01

How many fabric thicknesses will be found in a French fell seam?

A. Five.

B. Four.

C. Three.

B.8.0.1.8.B.1 B01

Finishing tape (surface tape) is used for what purpose?

A. To provide additional anti-tear resistance under reinforcement tape.

B. To help prevent "ripple formation" in covering fabric.

C. To provide additional wear resistance over the edges of fabric forming structures.

B.8.0.1.9.A.1 B01

Moisture, mildew, chemicals, and acids have no effect on

A. linen fabric.

B. glass fabric.

C. dacron fabric.

B.8.0.2.0.A.1 B02

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

A. sew from the end of each leg to the center of the tear with a baseball stitch and then dope on a patch.

B. re-cover the entire bay in which the tear is located.

C. sew with a baseball stitch from the center of the tear out toward the extremity of each leg and then dope on a patch.

B.8.0.2.1.A.1 B02

The strength classification of fabrics used in aircraft covering is based on

A. shear strength.

B. bearing strength.

C. tensile strength.

B.8.0.2.2.A.1 B02

Fabric rejuvenator

A. restores fabric strength and tautness to at least the minimum acceptable level.

B. penetrates the fabric and restores fungicidal resistance.

C. restores the condition of dope coatings.

B.8.0.2.3.A.1 B02

(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.

Regarding the above statements,

A. both No. 1 and No. 2 are true.

B. only No. 2 is true.

C. only No. 1 is true.

B.8.0.2.4.A.1 B02

When testing the strength of Grade A cotton fabric covering an aircraft that requires only intermediate grade, the minimum acceptable strength the fabric must have is

A. 70 percent of the original strength for intermediate fabric.

B. 70 percent of its original strength.

C. 56 pounds per inch warp and fill.

B.8.0.2.5.A.1 B02

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?

1. Aluminum foil.

2. Resin impregnated cloth tape.

3. Any one-part type metal primer.

4. Cellulose tape.

A. 1 and 4.

B. 3 and 4.

C. 1 and 2.

C.8.0.2.6.A.1 C01

If registration numbers are to be applied to an aircraft with a letter height of 12 inches, what is the minimum space required for the registration mark N1683C?

Note:

2/3 x height = character width.

1/6 x height = width for 1.

1/4 x 2/3 height = spacing.

1/6 x height = stroke or line width.

A. 52 inches.

B. 48 inches.

C. 57 inches.

C.8.0.2.7.A.1 C01

If masking tape is applied to an aircraft such as for trim spraying, and is left on for several days and/or exposed to heat, it is likely that the tape will

A. cure to the finish and be very difficult to remove.

B. not seal out the finishing material if the delay or heating occurs before spraying.

C. be weakened in its ability to adhere to the surface.

C.8.0.2.8.A.1 C02

What is used to slow the drying time of some finishes and to prevent blush?

A. Rejuvenator.

B. Reducer.

C. Retarder.

C.8.0.2.9.A.1 C02

Which type of coating typically includes phosphoric acid as one of its components at the time of application?

A. Epoxy primer.

B. Wash primer.

C. Zinc chromate primer.

C.8.0.3.0.A.1 C02

Which properly applied finish topcoat is the most durable and chemical resistant?

A. Synthetic enamel.

B. Acrylic lacquer.

C. Polyurethane.

C.8.0.3.1.A.1 C02

Aluminum-pigment in dope is used primarily to

A. provide a silver color.

B. exclude sunlight from the fabric.

C. aid in sealing out moisture from the fabric.

C.8.0.3.2.A.1 C02

A correct use for acetone is to

A. remove grease from fabric.

B. thin dope.

C. thin zinc chromate primer.

C.8.0.3.3.A.1 C03

Which of the following is a hazard associated with sanding on fabric covered surfaces during the finishing process?

A. Embedding of particles in the finish.

B. Overheating of the fabric/finish, especially with the use of power tools.

C. Static electricity buildup.

C.8.0.3.4.A.1 C03

What is likely to occur if unhydrated wash primer is applied to unpainted aluminum and then about 30 to 40 minutes later a finish topcoat, when the humidity is low?

A. Corrosion.

B. A glossy, blush-free finish.

C. A dull finish due to the topcoat ``sinking in'' to primer that is still too soft.

C.8.0.3.5.A.1 C03

Fungicidal dopes are used in aircraft finishing as the

A. first, full-bodied, brushed-on coat to prevent fungus damage.

B. final, full-bodied, brushed-on coat to reduce blushing.

C. first coat to prevent fabric rotting and are applied thin enough to saturate the fabric.

C.8.0.3.6.A.1 C03

Before spraying any finishing materials on unpainted clean aluminum,

A. remove any conversion coating film.

B. wipe the surface with avgas or kerosene.

C. avoid touching the surface with bare hands.

C.8.0.3.7.A.1 C03

What is likely to occur if hydrated wash primer is applied to unpainted aluminum and then about 30 to 40 minutes later a finish topcoat, when the humidity is low?

A. A dull finish due to the topcoat ``sinking in'' to primer that is still too soft.

B. Corrosion.

C. A glossy, blush-free finish.

C.8.0.3.8.A.1 C04

What is the usual cause of runs and sags in aircraft finishes?

A. Low atmospheric humidity.

B. Too much material applied in one coat.

C. Material is being applied too fast.

C.8.0.3.9.A.1 C04

Which defect in aircraft finishes may be caused by adverse humidity, drafts, or sudden changes in temperature?

A. Blushing.

B. Orange peel.

C. Pinholes.

C.8.0.4.0.A.1 C04

Which statement is true regarding paint system compatibility?

A. Old type zinc chromate primer may not be used directly for touchup of bare metal surfaces.

B. Old wash primer coats may be overcoated directly with epoxy finishes.

C. Acrylic nitrocellulose lacquers may be used over old nitrocellulose finishes.

D.8.0.4.1.A.1 D01

A well designed rivet joint will subject the rivets to

A. shear loads.

B. tension loads.

C. compressive loads.

D.8.0.4.2.A.1 D01

A main difference between Lockbolt/ Huckbolt tension and shear fasteners (other than their application) is in the

A. shape of the head.

B. method of installation.

C. number of locking collar grooves.

D.8.0.4.3.A.1 D01

Alloy 2117 rivets are heat treated

A. by the manufacturer but require reheat treatment before being driven.

B. by the manufacturer and do not require heat treatment before being driven.

C. to a temperature of 910 to 930 °F and quenched in cold water.

D.8.0.4.4.A.1 D01

The general rule for finding the proper rivet diameter is

A. three times the thickness of the thickest sheet.

B. three times the thickness of the materials to be joined.

C. two times the rivet length.

D.8.0.4.5.B.1 D01

The shop head of a rivet should be

A. one-half times the diameter of the rivet shank.

B. one and one-half times the diameter of the manufactured head of the rivet.

C. one and one-half times the diameter of the rivet shank.

D.8.0.4.6.A.1 D01

One of the main advantages of Hi-Lok type fasteners over earlier generations is that

A. the squeezed on collar installation provides a more secure, tighter fit.

B. they can be installed with ordinary hand tools.

C. they can be removed and reused again.

D.8.0.4.7.A.1 D01

The markings on the head of a Dzus fastener identify the

A. manufacturer and type of material.

B. body type, head diameter, and type of material.

C. body diameter, type of head, and length of the fastener.

D.8.0.4.8.A.1 D01

The Dzus turnlock fastener consists of a stud, grommet, and receptacle. The stud length is measured in

A. sixteenths of an inch.

B. hundredths of an inch.

C. tenths of an inch.

D.8.0.4.9.A.1 D01

The Dzus turnlock fastener consists of a stud, grommet, and receptacle. The stud diameter is measured in

A. sixteenths of an inch.

B. tenths of an inch.

C. hundredths of an inch.

D.8.0.5.0.A.1 D01

Threaded rivets (Rivnuts) are commonly used to

A. join two or more pieces of sheet metal where bearing strength is desired.

B. attach parts or components with screws to sheet metal.

C. join two or more pieces of sheet metal where shear strength is desired.

D.8.0.5.1.A.1 D01

Cherrymax and Olympic-Lok rivets

A. utilize a pulling tool for installation.

B. utilize a rivet gun, special rivet set, and bucking bar for installation.

C. may be installed with ordinary hand tools.

D.8.0.5.2.A.1 D01

Hole filling fasteners (for example, MS20470 rivets) should not be used in composite structures primarily because of the

A. difficulty in forming a proper shop head.

B. possibility of causing delamination.

C. increased possibility of fretting corrosion in the fastener.

D.8.0.5.3.A.1 D01

Metal fasteners used with carbon/graphite composite structures

A. must be constructed of material such as titanium or corrosion resistant steel.

B. may be constructed of any of the metals commonly used in aircraft fasteners.

C. must be constructed of high strength aluminum-lithium alloy.

D.8.0.5.4.A.1 D02

Sandwich panels made of metal honeycomb construction are used on modern aircraft because this type of construction

A. is lighter than single sheet skin of the same strength and is more corrosion resistant.

B. has a high strength to weight ratio.

C. may be repaired by gluing replacement skin to the inner core material with thermoplastic resin.

D.8.0.5.5.A.1 D02

(1) When performing a ring (coin tap) test on composite structures, a change in sound may be due to damage or to transition to a different internal structure.

(2) The extent of separation damage in composite structures is most accurately measured by a ring (coin tap) test.

Regarding the above statements,

A. both No. 1 and No. 2 are true.

B. only No. 2 is true.

C. only No. 1 is true.

D.8.0.5.6.A.1 D02

Which of these methods may be used to inspect fiberglass/honeycomb structures for entrapped water?

1. Acoustic emission monitoring.

2. X-ray.

3. Backlighting.

A. 2 and 3.

B. 1 and 2.

C. 1 and 3.

D.8.0.5.7.A.1 D02

When balsa wood is used to replace a damaged honeycomb core, the plug should be cut so that

A. the grain is parallel to the skin.

B. the grain is perpendicular to the skin.

C. it is about 1/8-inch undersize to allow sufficient bonding material to be applied.

D.8.0.5.8.A.1 D02

When repairing puncture type damage of a metal faced laminated honeycomb panel, the edges of the doubler should be tapered to

A. two times the thickness of the metal.

B. 100 times the thickness of the metal.

C. whatever is desired for a neat, clean appearance.

D.8.0.5.9.A.1 D02

One of the best ways to assure that a properly prepared batch of matrix resin has been achieved is to

A. perform a chemical composition analysis.

B. have mixed enough for a test sample.

C. test the viscosity of the resin immediately after mixing.

D.8.0.6.0.A.1 D02

Composite inspections conducted by means of acoustic emission monitoring

A. pick up the ``noise'' of corrosion or other deterioration occurring.

B. create sonogram pictures of the areas being inspected.

C. analyze ultrasonic signals transmitted into the parts being inspected.

D.8.0.6.1.A.1 D02

What precaution, if any, should be taken to prevent corrosion inside a repaired metal honeycomb structure?

A. None. Honeycomb is usually made from a man made or fibrous material which is not susceptible to corrosion.

B. Prime the repair with a corrosion inhibitor and seal from the atmosphere.

C. Paint the outside area with several coats of exterior paint.

D.8.0.6.2.A.1 D02

One method of inspecting a laminated fiberglass structure that has been subjected to damage is to

A. use dye penetrant inspection procedures, exposing the entire damaged area to the penetrant solution.

B. strip the damaged area of all paint and shine a strong light through the structure.

C. use an eddy current probe on both sides of the damaged area.

D.8.0.6.3.A.1 D02

When inspecting a composite panel using the ring test/tapping method, a dull thud may indicate

A. an area of too much matrix between fiber layers.

B. less than full strength curing of the matrix.

C. separation of the laminates.

D.8.0.6.4.B.1 D02

How many of the following are benefits of using microballoons when making repairs to laminated honeycomb panels?

1. Greater concentrations of resin in edges and corners.

2. Improved strength to weight ratio.

3. Less density.

4. Lower stress concentrations.

A. Four.

B. Three.

C. Two.

D.8.0.6.5.A.1 D03

The length of time that a catalyzed resin will remain in a workable state is called the

A. service life.

B. shelf life.

C. pot life.

D.8.0.6.6.A.1 D03

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

A. thermoplastic.

B. thermoset.

C. thermocure.

D.8.0.6.7.A.1 D03

The classification for high tensile strength fiberglass used in aircraft structures is

A. E.

B. G.

C. S.

D.8.0.6.8.A.1 D03

Which is an identifying characteristic of acrylic plastics?

A. Zinc chloride will have no effect.

B. Has a yellowish tint when viewed from the edge.

C. Acetone will soften plastic, but will not change its color.

D.8.0.6.9.A.1 D03

Superficial scars, scratches, surface abrasion, or rain erosion on fiberglass laminates can generally be repaired by applying

A. a piece of resin impregnated glass fabric facing.

B. one or more coats of suitable resin (room temperature catalyzed) to the surface.

C. a sheet of polyethylene over the abraded surface and one or more coats of resin cured with infrared heat lamps.

D.8.0.7.0.A.1 D03

The classification for fiberglass reinforcement material that has high resistivity and is the most common is

A. G.

B. E.

C. S.

D.8.0.7.1.A.1 D03

A potted compound repair on honeycomb can usually be made on damages less than

A. 4 inches in diameter.

B. 2 inches in diameter.

C. 1 inch in diameter.

D.8.0.7.2.A.1 D03

Composite fabric material is considered to be the strongest in what direction?

A. Bias.

B. Fill.

C. Warp.

D.8.0.7.3.A.1 D03

What reference tool is used to determine how the fiber is to be oriented for a particular ply of fabric?

A. Bias clock (or compass).

B. Warp clock (or compass).

C. Fill clock (or compass).

D.8.0.7.4.A.1 D03

The strength and stiffness of a properly constructed composite buildup depends primarily on

A. the orientation of the plies to the load direction.

B. the ability of the fibers to transfer stress to the matrix.

C. a 60 percent matrix to 40 percent fiber ratio.

D.8.0.7.5.A.1 D03

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

A. 40:60.

B. 50:50.

C. 60:40.

D.8.0.7.6.A.1 D03

What is the material layer used within the vacuum bag pressure system to absorb excess resin during curing called?

A. Bleeder.

B. Breather.

C. Release.

D.8.0.7.7.A.1 D03

Proper pre-preg composite lay-up curing is generally accomplished by

1. applying external heat.

2. room temperature exposure.

3. adding a catalyst or curing agent to the resin.

4. applying pressure.

A. 1, 3, and 4.

B. 2 and 3.

C. 1 and 4.

D.8.0.7.8.A.1 D03

When repairing large, flat surfaces with polyester resins, warping of the surface is likely to occur. One method of reducing the amount of warpage is to

A. add an extra amount of catalyst to the resin.

B. use short strips of fiberglass in the bonded repair.

C. use less catalyst than normal so the repair will be more flexible.

D.8.0.7.9.A.1 D03

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

A. a thixotropic agent.

B. soap, water, and a scrub brush.

C. MEK (methyl ethyl ketone).

D.8.0.8.0.A.1 D03

When necessary, what type of cutting fluid is usually acceptable for machining composite laminates?

A. Water soluble oil.

B. Water displacing oil.

C. Water only.

D.8.0.8.1.A.1 D03