Aircraft Materials Questions and Answers - Composite and Non-Metallic other than wood and fabric.

Question Number. 1. Adhesives containing phenol-formaldehyde, to cure, requires.
Option A. room temperature.
Option B. high temperature.
Option C. low temperature.
Correct Answer is. high temperature.
Explanation. NIL.


Question Number. 2. Two parts of the adhesive process are.
Option A. wetting and gripping.
Option B. spreading and setting.
Option C. wetting and setting.
Correct Answer is. wetting and setting.
Explanation. NIL.


Question Number. 3. Types of adhesive joints are.
Option A. mechanical and cemented.
Option B. cemented and specific.
Option C. mechanical and specific.
Correct Answer is. mechanical and specific.
Explanation. NIL.


Question Number. 4. What material would be used where a high temperature application is required, e.g. a firewall?.
Option A. Aramid (Kevlar) fibres.
Option B. Carbon/graphite fibres.
Option C. Ceramic fibres.
Correct Answer is. Ceramic fibres.
Explanation. Ceramic composites retain their strength at high temperatures.


Question Number. 5. Over extended honeycomb can bend in which direction?.
Option A. In all directions.
Option B. Across the ribbon.
Option C. Along the ribbon.
Correct Answer is. Along the ribbon.
Explanation. NIL.


Question Number. 6. Fibre weave strength is greatest in the direction of the.
Option A. weft.
Option B. warp.
Option C. bias.
Correct Answer is. warp.
Explanation. See Jeppesen Advanced Composites.


Question Number. 7. What is Alumina?.
Option A. An alloy of aluminium.
Option B. Aluminium ore.
Option C. A ceramic oxide of aluminium.
Correct Answer is. A ceramic oxide of aluminium.
Explanation. Alumina ia aluminium oxide - a ceramic.


Question Number. 8. Which of these core materials will be used in the making of a composite material flat panel?.
Option A. Hexagonal core.
Option B. Rectangular core.
Option C. Flexible core.
Correct Answer is. Hexagonal core.
Explanation. NIL.


Question Number. 9. Which of the following could best be manufactured from Perspex panel?.
Option A. A passenger window.
Option B. A radome.
Option C. A cockpit windscreen.
Correct Answer is. A passenger window.
Explanation. NIL.


Question Number. 10. Kevlar and Nomex are types of.
Option A. glass fibre composite.
Option B. advanced composite.
Option C. aluminium alloy.
Correct Answer is. advanced composite.
Explanation. Kevlar and Nomex are Aramid materials.


Question Number. 11. Strength of fibreglass is.
Option A. either direction.
Option B. along the fibre.
Option C. across the fibre.
Correct Answer is. along the fibre.
Explanation. NIL.


Question Number. 12. A composite flap panel has structural damage. What NDT method will you use to detect?.
Option A. High voltage x-ray.
Option B. Low voltage x-ray.
Option C. Coin tap test.
Correct Answer is. Coin tap test.
Explanation. NIL.


Question Number. 13. Sound is best absorbed by a material which is.
Option A. dense.
Option B. soft and porous.
Option C. hard.
Correct Answer is. soft and porous.
Explanation. Cellular' materials make good sound insulation. Sound is unaffected by density, nor hardness.


Question Number. 14. The maximum tensile strength of fibre reinforced plastic is achieved using.
Option A. fibres uniformly distributed at 45 degrees to each other.
Option B. unidirectional fibres.
Option C. chopped strand mat.
Correct Answer is. unidirectional fibres.
Explanation. NIL.


Question Number. 15. Polyester resin and glass fibre cloth, becomes.
Option A. PTFE.
Option B. PVC.
Option C. GRP.
Correct Answer is. GRP.
Explanation. NIL.


Question Number. 16. A thermoplastic can be.
Option A. heated and formed only once.
Option B. is not affected by even low temperatures.
Option C. can be reheated and reformed more than once.
Correct Answer is. can be reheated and reformed more than once.
Explanation. NIL.


Question Number. 17. An impact adhesive is part of the.
Option A. thermoplastic group.
Option B. thermoset group.
Option C. Anaerobic resin group.
Correct Answer is. thermoplastic group.
Explanation. NIL.


Question Number. 18. Sandwich panels made of metal honeycomb construction are used on modern aircraft because this type of construction.
Option A. may be repaired by gluing replacement skin to the inner core material with thermoplastic resin.
Option B. is lighter than single sheet skin of the same strength and is more corrosion resistant.
Option C. has a high strength to weight ratio.
Correct Answer is. is lighter than single sheet skin of the same strength and is more corrosion resistant.
Explanation. NIL.


Question Number. 19. A category of plastic material that is capable of softening or flowing when reheated is described as a.
Option A. thermoset.
Option B. thermoplastic.
Option C. thermocure.
Correct Answer is. thermoplastic.
Explanation. NIL.


Question Number. 20. The classification of high tensile strength fibreglass used in aircraft structures is.
Option A. G-glass.
Option B. E-glass.
Option C. S-glass.
Correct Answer is. S-glass.
Explanation. NIL.


Question Number. 21. Which is the identifying characteristic of acrylic plastics?.
Option A. Acetone will soften the plastic, but will not change its colour.
Option B. Has a yellowish tint when viewed from the edge.
Option C. Zinc chloride will have no effect.
Correct Answer is. Zinc chloride will have no effect.
Explanation. NIL.


Question Number. 22. The classification for fibreglass reinforcement material that is high resistivity and the most common is.
Option A. E-glass.
Option B. S-glass.
Option C. G-glass.
Correct Answer is. E-glass.
Explanation. NIL.


Question Number. 23. Composite fabric material is considered to be the strongest in what direction?.
Option A. Warp.
Option B. Bias.
Option C. Weft.
Correct Answer is. Warp.
Explanation. NIL.


Question Number. 24. Which of the following are generally characteristic of aramid fibre (Kevlar) composites?.
Option A. High tensile strength and flexibility.
Option B. Flexibility, stiffness and corrosive effect in contact with aluminium.
Option C. High tensile strength, stiffness and ability to conduct electricity.
Correct Answer is. High tensile strength, stiffness and ability to conduct electricity.  OR High tensile strength and flexibility.
Explanation. NIL.


Question Number. 25. Which of the following are generally characteristic of carbon/graphite fibre composites?.
Option A. Flexibility, High compressive strength and ability to conduct electricity.
Option B. Flexibility and high compressive strength.
Option C. Stiffness, high compressive strength and corrosive effect in contact with aluminium.
Correct Answer is. Stiffness, high compressive strength and corrosive effect in contact with aluminium.
Explanation. NIL.


Question Number. 26. Which of the following statements is true about thermosetting plastics?.
Option A. They are also known as Teflon.
Option B. Once moulded into shape they become set and cannot subsequently be softened by reheating.
Option C. They become plastic when heat is applied.
Correct Answer is. Once moulded into shape they become set and cannot subsequently be softened by reheating.
Explanation. NIL.

03.1b. Aircraft Materials - Composite and Non-Metallic other than wood and fabric.


Question Number. 1. Which of the following is susceptible to the ingress of moisture?.
Option A. Glass fibre.
Option B. Carbon fibre.
Option C. Kevlar.
Correct Answer is. Kevlar.
Explanation. NIL.


Question Number. 2. What tests are done on adhesive joints?.
Option A. Shear and peel.
Option B. Impact and peel.
Option C. Impact and shear.
Correct Answer is. Shear and peel.
Explanation. NIL.


Question Number. 3. When using a hot bonder to effect a composite repair, you use.
Option A. inorganic resin adhesives.
Option B. organic resin adhesives.
Option C. synthetic resin adhesives.
Correct Answer is. synthetic resin adhesives.
Explanation. NIL.


Question Number. 4. In a composite repair lay-up, how much should each layer extend beyond the layer below it?.
Option A. 3 - 4 inches.
Option B. 1 - 2 inches.
Option C. 2 - 3 inches.
Correct Answer is. 1 - 2 inches.
Explanation. FAA AC43 Page 3-5.


Question Number. 5. What is the effect of heat on a cold cure resin?.
Option A. No effect on pot life.
Option B. Decrease pot life.
Option C. Increase pot life.
Correct Answer is. Decrease pot life.
Explanation. NIL.


Question Number. 6. If you increase the amount of catalyst in a resin mixture,.
Option A. the material will become stronger.
Option B. the material will become weaker.
Option C. the pot life will be decreased.
Correct Answer is. the pot life will be decreased.
Explanation. NIL.


Question Number. 7. What two components of a three part polyester resin are dangerous to mix together directly?.
Option A. Accelerator and free catalyst.
Option B. Catalyst and resin.
Option C. Accelerator and resin.
Correct Answer is. Accelerator and free catalyst.
Explanation. CAIP AL/7-6 page 2 para 4.


Question Number. 8. What is the effect of adding too much hardener to a resin?.
Option A. No effect.
Option B. Makes the repair more brittle.
Option C. The resin will not harden.
Correct Answer is. Makes the repair more brittle.
Explanation. NIL.


Question Number. 9. What is the largest hole in honeycomb repairable with microballoons?.
Option A. 2.54 inches.
Option B. 2.54 mm.
Option C. 2.54 cm.
Correct Answer is. 2.54 cm.
Explanation. Answer is 1 inch.


Question Number. 10. An air driven router is used to remove honeycomb material for repairs.
Option A. when one outer skin is damaged.
Option B. to stainless steel honeycomb only.
Option C. when both outer skins are damaged.
Correct Answer is. when one outer skin is damaged.
Explanation. NIL.


Question Number. 11. Where would you use a Templestick?.
Option A. For the boundary marking of a composite repair.
Option B. To indicate temperature when a repaired composite item is cured with heat lamps.
Option C. As a temporary repair in a glass fibre internal.
Correct Answer is. To indicate temperature when a repaired composite item is cured with heat lamps.
Explanation. NIL.


Question Number. 12. The vacuum connections on a fibreglass repair must be placed onto the.
Option A. top layer of glass fabric directly.
Option B. breather mat.
Option C. peel ply.
Correct Answer is. breather mat.
Explanation. The breather mat allows the air to flow from the repair.


Question Number. 13. What do you do if you forget to add hardener to a composite repair?.
Option A. Add hardener at the edges and it will cure.
Option B. It will cure eventually anyway.
Option C. Remove all resin and start again.
Correct Answer is. Remove all resin and start again.
Explanation. NIL.


Question Number. 14. Why would you use microballoons as a filler?.
Option A. It is the lightest filler material.
Option B. It is the cheapest filler material.
Option C. It cross-links with the panel.
Correct Answer is. It is the lightest filler material.
Explanation. Microballoons is the lightest filler material.


Question Number. 15. When using a backing former on a composite repair you need to use.
Option A. a vacuum bag.
Option B. cellophane.
Option C. breather cloth.
Correct Answer is. cellophane.
Explanation. See Jeppesen Advanced Composites.


Question Number. 16. Heater mats should overlap the repair by.
Option A. 4 inches.
Option B. 6 inches.
Option C. 2 inches.
Correct Answer is. 2 inches.
Explanation. See Jeppesen Advanced Composites.


Question Number. 17. A thermoplastic fibre reinforced composite is prepared by.
Option A. a solvent wipe.
Option B. corona method.
Option C. etching.
Correct Answer is. corona method.
Explanation. Corona method is used to prepare a thermoplastic material. http://www.bondmaster.com/surfacePrep.asp


Question Number. 18. During vacuum bag lay-up the vacuum gauge is placed where?.
Option A. Next to the vacuum port.
Option B. Opposite side to the vacuum port.
Option C. Over the repair.
Correct Answer is. Opposite side to the vacuum port.
Explanation. Although the vacuum gauge can be placed anywhere, the easiest being on the same side as the vacuum nozzle, the most logical answer (and probably the one the CAA want) is opposite side of the repair to the nozzle. See Jeppesen Advanced Composites shows a diagram with it opposite side (fig 7-4) and one showing it combined with the vacuum nozzle (fig 7-6).


Question Number. 19. Stepped curing has.
Option A. 2 or more arrest points.
Option B. no arrest point.
Option C. 1 arrest point.
Correct Answer is. 2 or more arrest points.
Explanation. See Jeppesen Advanced Composites (dwell time = soak time = arrest point). Or A&P Technician Airframe Textbook.


Question Number. 20. Maximum repair dimensions for use of microballoons is.
Option A. 10mm.
Option B. 20mm.
Option C. 30mm.
Correct Answer is. 10mm.
Explanation. Maximum repair with microballoons is approximately 3/8 inch - closest here is 10 mm. AL/7-6 7.4.


Question Number. 21. In an autoclave what pressure would the vacuum alarm be set at?.
Option A. Operating pressure.
Option B. Higher than operating pressure.
Option C. Lower than operating pressure.
Correct Answer is. Lower than operating pressure.
Explanation. An autoclave uses pressure, so the alarm must sound if the pressure drops below normal.


Question Number. 22. In an autoclave what would you cover the repair in?.
Option A. High temp nylon.
Option B. Polypropelene.
Option C. Polythene.
Correct Answer is. High temp nylon.
Explanation. See Jeppesen Advanced Composites.


Question Number. 23. When mixing resin it is dangerous to add.
Option A. accelerator and catalyst before resin.
Option B. catalyst and resin before accelerator.
Option C. resin and accelerator before catalyst.
Correct Answer is. accelerator and catalyst before resin.
Explanation. AL/7-6 4.


Question Number. 24. In an autoclave, to apply pressure.
Option A. a vacuum bag is used.
Option B. weights are used.
Option C. clamps are used.
Correct Answer is. a vacuum bag is used.
Explanation. See Jeppesen Advanced Composites.


Question Number. 25. What does MSDS stand for?.
Option A. Metal Surface Dimension Sector.
Option B. Material Safety Data Sheet.
Option C. Maximum Structural Design System.
Correct Answer is. Material Safety Data Sheet.
Explanation. MSDS - Material Safety Data Sheet.


Question Number. 26. Honeycomb for repair can be removed with.
Option A. a drill.
Option B. locally manufactured concave knife.
Option C. a router.
Correct Answer is. a router.
Explanation. CAIPs AL/7-6.


Question Number. 27. The pot life of a cold cured resin.
Option A. is not reliant upon temperature fluctuations.
Option B. decreases with an increase in temperature.
Option C. increases with increase of temperature.
Correct Answer is. decreases with an increase in temperature.
Explanation. CAIPs AL/7-6.


Question Number. 28. Thermosetting adhesive, during their curing cycle give off.
Option A. static radiation.
Option B. heat.
Option C. carbon monoxide.
Correct Answer is. heat.
Explanation. plastics (or adhesives) require heat to make them cure. The heat can be applied externally (endothermic) or created internally by a catalyst or hardener (exothermic). The latter gives off heat.


Question Number. 29. The effect of a lower temperature than ambient during the curing period of a resin, will cause the curing time to.
Option A. decrease.
Option B. increase.
Option C. remain unchanged.
Correct Answer is. increase.
Explanation. A colder temperature will cause a resin to take longer to cure. AL/7-6 4.3.

Question Number. 30. What is used as the base covering on a honeycomb repair?.
Option A. Glass cloth or thin aluminium sheet.
Option B. Thick aluminium sheet.
Option C. Plywood.
Correct Answer is. Glass cloth or thin aluminium sheet.
Explanation. Most correct answer for a repair to a honeycomb sandwhich structure. AL/7-6 7.5.5.


Question Number. 31. When drilling a carbon fibre reinforced plastic use.
Option A. a steel drill and carbarundum powder.
Option B. a tungsten drill with a pointed tip.
Option C. a tungsten carbide drill.
Correct Answer is. a tungsten carbide drill.
Explanation. Airbus A340 SRM - states Carbide or Carbide tipped drill for composite materials.


Question Number. 32. When laying up a glass fibre repair, the extra layer of fibre is.
Option A. a sacrificial layer for sanding.
Option B. for extra strength.
Option C. for shrinkage.
Correct Answer is. for extra strength.
Explanation. AC43 3-3(3) page 3-4.


Question Number. 33. Bubbles are removed from a wet composite lay-up by.
Option A. application of pressure.
Option B. use of a roller.
Option C. application of vacuum.
Correct Answer is. use of a roller.
Explanation. Bubbles (large ones anyway) are removed with a roller.


Question Number. 34. Use of excessive hardener in polyester resin leads to.
Option A. a less stiff joint.
Option B. reduced pot life.
Option C. stiffer joint.
Correct Answer is. reduced pot life.
Explanation. Too much hardener will greatly reduce pot life as well as make the polyester brittle.


Question Number. 35. When the temperature increases on a hot bond repair is paused it is known as.
Option A. arrest point.
Option B. ramping down.
Option C. ramping up.
Correct Answer is. arrest point.
Explanation. Ramp-up' and 'ramp-down' refer to the heating and cooling rates (in   °C per minute). When the heating is paused it is called 'hold' or 'soak' at the 'arrest point'.


Question Number. 36. Slight waviness on a fibre composite structure.
Option A. may cause fatigue crack eventually.
Option B. may be tolerable if lightly loaded.
Option C. could be reinforce with additional plies over the weakened area.
Correct Answer is. may be tolerable if lightly loaded.
Explanation. NIL.


Question Number. 37. The maximum length of time a component is held in stores is known as the.
Option A. package life.
Option B. storage life.
Option C. shelf life.
Correct Answer is. shelf life.
Explanation. NIL.


Question Number. 38. On a pre-preg composite.
Option A. life can be extended by 12 months if stored below 10  °C.
Option B. life can be extended by 12 months if stored above 40  °C.
Option C. no life extension is allowed, it must be used immediately.
Correct Answer is. life can be extended by 12 months if stored above 40  °C.
Explanation. NIL.


Question Number. 39. Hot bond composite pane has a crack. When it reaches the ribbon it will.
Option A. carry on along the ribbon.
Option B. have no effect on its direction.
Option C. stop.
Correct Answer is. stop.
Explanation. NIL.


Question Number. 40. In an autoclave the air is removed by.
Option A. pressure.
Option B. roller.
Option C. vacuum.
Correct Answer is. vacuum.
Explanation. Air is removed by vacuum whether an autoclave is used or not.


Question Number. 41. What is the separation of an aramid panel layers described as?.
Option A. Delamination.
Option B. Debonding.
Option C. Detachment.
Correct Answer is. Delamination.
Explanation. NIL.


Question Number. 42. Tap testing a sandwich panel construction.
Option A. is not an approved method of testing.
Option B. will not give very reliable results.
Option C. is crude, but works remarkably well.
Correct Answer is. is crude, but works remarkably well.
Explanation. NIL.


Question Number. 43. Which product is a serious health hazard when handling?.
Option A. Ceramic.
Option B. Asbestos.
Option C. Glass fibre.
Correct Answer is. Asbestos.
Explanation. NIL.


Question Number. 44. Aircraft transparent plastics are cleaned using.
Option A. warm soapy water, rinsed and dried.
Option B. paraffin and soft cotton pad.
Option C. clean dry soft leather.
Correct Answer is. warm soapy water, rinsed and dried.
Explanation. AL/7-4 6.1.


Question Number. 45. A thermosetting adhesive.
Option A. will be resistant to heat.
Option B. can be re-formed when hot.
Option C. undergoes a chemical transformation and creates an insoluble substance.
Correct Answer is. undergoes a chemical transformation and creates an insoluble substance.
Explanation. NIL.


Question Number. 46. Metal fasteners used with carbon/graphite composite structures.
Option A. must be made of materials such as titanium or corrosion resistant steel.
Option B. must be made of high strength aluminium alloy.
Option C. may be made of any of the metals commonly used in aircraft fasteners.
Correct Answer is. must be made of materials such as titanium or corrosion resistant steel.
Explanation. NIL.


Question Number. 47. Which methods can be used to inspect fibreglass/honeycomb structures for entrapped water?.
Option A. Acoustic emission and X-ray.
Option B. X-ray and back-lighting.
Option C. Acoustic emission and back-lighting.
Correct Answer is. X-ray and back-lighting.
Explanation. Acoustic emission will detect corrosion only.


Question Number. 48. When balsa wood is used to replace a damaged honeycomb core, the plug should be cut so that.
Option A. it is about 1/8 inch undersize to allow sufficient bonding material to be applied.
Option B. the grain is parallel to the skin.
Option C. the grain is perpendicular to the skin.
Correct Answer is. the grain is perpendicular to the skin.
Explanation. NIL.


Question Number. 49. When repairing puncture-type damage of a metal faced laminated honeycomb panel, the edges of the doubler should be tapered to.
Option A. whatever is desired for a neat clean appearance.
Option B. two times the thickness of the metal.
Option C. 100 times the thickness of the metal.
Correct Answer is. 100 times the thickness of the metal.
Explanation. NIL.


Question Number. 50. One of the best ways to assure that a properly prepared batch of matrix resin has been achieved is to.
Option A. test the viscosity of the resin immediately after mixing.
Option B. have mixed enough for a test sample.
Option C. perform a chemical composition analysis.
Correct Answer is. have mixed enough for a test sample.
Explanation. NIL.


Question Number. 51. Composite inspections by means of acoustic emissions monitoring.
Option A. analyse ultrasonic signals transmitted into the parts being inspected.
Option B. create sonogram pictures of the areas being inspected.
Option C. pick up the 'noise' of corrosion or other deterioration taking place.
Correct Answer is. create sonogram pictures of the areas being inspected. OR pick up the 'noise' of corrosion or other deterioration taking place.
Explanation. NIL.


Question Number. 52. Which of the following are advantages of using microballoons in repairs to laminate honeycomb sandwich panels?.
Option A. Greater concentrations of resin in edges and corners, improved strength to weight ratio, less density, lower stress concentrations.
Option B. Less density, lower stress concentrations.
Option C. Improved strength to weight ratio, less density, lower stress.
Correct Answer is. Less density, lower stress concentrations.
Explanation. NIL.


Question Number. 53. The length and time that a catalyzed resin will remain in a workable state is called the.
Option A. shelf life.
Option B. service life.
Option C. pot life.
Correct Answer is. pot life.
Explanation. CAIP AL/7-6 para 4.2.


Question Number. 54. One method of inspecting a laminated fibreglass structure that has been subjected to damage is.
Option A. strip the damaged area of all paint and shine a strong light through the structure.
Option B. use an eddy current probe on both sides of the damaged area.
Option C. use dye-penetrant inspection procedures, exposing the entire damaged area to the penetrant solution.
Correct Answer is. strip the damaged area of all paint and shine a strong light through the structure.
Explanation. NIL.


Question Number. 55. When inspecting a composite panel using the ring test/tapping method, a dull thud may indicate.
Option A. an area of too much matrix between the fibres.
Option B. less than full strength curing of the matrix.
Option C. separation of the laminates.
Correct Answer is. separation of the laminates.
Explanation. NIL.


Question Number. 56. Superficial scars, scratches, surface abrasion, or rain erosion on fibreglass laminates can generally be repaired by applying.
Option A. one or more coats of suitable resin (room-temperature catalyzed) to the surface.
Option B. a sheet of polyethylene over the abraded surface and one or more coats of resin cured with infrared heat lamps.
Option C. a piece of resin-impregnated glass fabric facing.
Correct Answer is. a sheet of polyethylene over the abraded surface and one or more coats of resin cured with infrared heat lamps. OR one or more coats of suitable resin (room-temperature catalyzed) to the surface.
Explanation. CAIP AL/7-6 para 7.2 a-d.


Question Number. 57. A potted compound repair on honeycomb can usually be made on damages less than.
Option A. 4 inches in diameter.
Option B. 2 inches in diameter.
Option C. 1 inch in diameter.
Correct Answer is. 1 inch in diameter.
Explanation. NIL.



Question Number. 58. What reference tool is used to determine how the fibre is to be oriented for a particular ply or fabric?.
Option A. Bias clock.
Option B. Weft clock.
Option C. Warp clock.
Correct Answer is. Warp clock.
Explanation. NIL.


Question Number. 59. The strength and stiffness of a properly constructed composite lay-up depends primarily on.
Option A. the ability of the fibres to transfer stress to the matrix.
Option B. a 60% matrix to 40% fibre ratio.
Option C. the orientation of the plies to the load direction.
Correct Answer is. the orientation of the plies to the load direction.
Explanation. NIL.


Question Number. 60. Which fibre to resin (%) ratio for advanced composite wet lay-ups is generally considered the best?.
Option A. 60:40.
Option B. 50:50.
Option C. 40:60.
Correct Answer is. 40:60.
Explanation. NIL.


Question Number. 61. What is the material layer used within the vacuum bag pressure system to absorb excess resin during curing called?.
Option A. Breather.
Option B. Bleeder.
Option C. Release.
Correct Answer is. Bleeder.
Explanation. NIL.


Question Number. 62. When necessary, what type of cutting fluid is usually acceptable for machining composite laminates?.
Option A. Water soluble oil.
Option B. Water only.
Option C. Water displacing oil.
Correct Answer is. Water only.
Explanation. NIL.


Question Number. 63. Fibreglass laminate damage not exceeding the first layer or ply can be repaired by.
Option A. filling with putty consisting of compatible resin and clean, short glass fibres.
Option B. sanding the damaged are until aerodynamically smooth.
Option C. trimming the rough adges and sealing with paint.
Correct Answer is. sanding the damaged are until aerodynamically smooth. OR filling with putty consisting of compatible resin and clean, short glass fibres.
Explanation. NIL.


Question Number. 64. Fibreglass damage that extends completely through a laminated sandwich structure.
Option A. may be filled with resin to eliminate dangerous stress concentrations.
Option B. must be repaired.
Option C. may be filled with putty which is compatible with the resin.
Correct Answer is. must be repaired.
Explanation. AC43 - must be repaired using a stepped-joint or scarfed repair.


Question Number. 65. Fibreglass laminate damage that extends completely through one facing and into the core.
Option A. can be repaired by using a typical facing patch.
Option B. requires replacement of the damaged core and facing.
Option C. cannot be repaired.
Correct Answer is. requires replacement of the damaged core and facing.
Explanation. AC43.


Question Number. 66. Which of the following, when added to wet resins, provide strength for the repair of damaged fastener holes in composite panels?.
Option A. microballoons, cotton flock and chopped fibres.
Option B. Cotton flock and chopped fibres.
Option C. Microballoons and chopped fibres.
Correct Answer is. Cotton flock and chopped fibres.
Explanation. NIL.


Question Number. 67. The part of a replacement honeycomb core that must line up with the adjacent original is the.
Option A. cell edge.
Option B. cell side.
Option C. ribbon direction.
Correct Answer is. ribbon direction.
Explanation. NIL.


Question Number. 68. Which of the following is the definition of cure time?.
Option A. The period after which the surface of the compound no longer exhibits adhesive properties.
Option B. The time required for the mixed compound to reach an initial rubbery state.
Option C. The time taken for the mixed compound to reach a final rubbery state.
Correct Answer is. The time required for the mixed compound to reach an initial rubbery state. OR The period after which the surface of the compound no longer exhibits adhesive properties.
Explanation. NIL.


Question Number. 69. In order to prevent dermatitis caused due to contact with polymer resin, one should.
Option A. avoid inhaling fumes.
Option B. remember to close the autoclave door during curing.
Option C. use disposable gloves or barrier cream.
Correct Answer is. remember to close the autoclave door during curing. OR use disposable gloves or barrier cream.
Explanation. CAIP AL/7-6 para 4.

03.2. Aircraft Materials - Wooden Structures.


Question Number. 1. With what would you check the bonded joints of a wooden aircraft structure?.
Option A. A feeler gauge.
Option B. A plastic strip.
Option C. A screwdriver.
Correct Answer is. A feeler gauge.
Explanation. AC43 Chapter 1 Section 3 Para 1-29.,CAAIPs Leaflet 6-1 Figure 3.


Question Number. 2. What is an open assembly time?.
Option A. The time elapsing between the application of the adhesive and the assembly of the joint components.
Option B. The time between the adhesive being applied to the joint surfaces and their assembly.
Option C. The time elapsed from the adhesive being applied to the joint surfaces to them being clamped.
Correct Answer is. The time between the adhesive being applied to the joint surfaces and their assembly. OR The time elapsing between the application of the adhesive and the assembly of the joint components.
Explanation. CAAIPs Leaflet 2-4 Page 7.


Question Number. 3. The defects not allowed at all on wooden structures are.
Option A. mineral streaks.
Option B. pitch pockets.
Option C. checks, shakes and splits.
Correct Answer is. checks, shakes and splits.
Explanation. A&P Technician Airframe Textbook 3-5.


Question Number. 4. The basic structure of an aircraft made of wood can be.
Option A. monocoque.
Option B. non-monocoque.
Option C. non-monocoque, monocoque, semi-monocoque.
Correct Answer is. non-monocoque, monocoque, semi-monocoque.
Explanation. NIL.


Question Number. 5. When a full inspection for corosion is to be carried out on a wooden aircraft you would.
Option A. Bring the aircraft into the hangar for 2 to 3 days prior to the inspection.
Option B. Jack and trestle the aircraft to the rigging position.
Option C. Remove all the fabric/cloth prior to inspection.
Correct Answer is. Remove all the fabric/cloth prior to inspection.
Explanation. AC43 Para 1-29.


Question Number. 6. For fungus to cause wood decay in a wood structure, the moisture content in the wood must be at least.
Option A. 20%.
Option B. 85%.
Option C. 5%.
Correct Answer is. 20%.
Explanation. AC43 Para 1-28 a.


Question Number. 7. The normal moisture content in the wood of a wooden aircraft structure is.
Option A. 10-12%.
Option B. 20-30%.
Option C. 0-2%.
Correct Answer is. 10-12%.
Explanation. AC43 Para. 1-29 g.


Question Number. 8. How is the moisture content within the wood of a wood aircraft structure determined?.
Option A. By inserting the probe of a moisture meter.
Option B. By measuring the size of the water stains at joints.
Option C. By weighing the wood structure before and after drying it.
Correct Answer is. By inserting the probe of a moisture meter.
Explanation. AC43 Para. 1-29 g.


Question Number. 9. Except where specified by the manufacturer, a wooden spar may be spliced.
Option A. at no point.
Option B. at any point except under the wing attachment fittings.
Option C. at any point.
Correct Answer is. at any point except under the wing attachment fittings.
Explanation. AC43 Para 1-40.


Question Number. 10. Replacement of a wooden spar is.
Option A. only permitted by the manufacturer.
Option B. a minor repair.
Option C. a major repair.
Correct Answer is. a major repair.
Explanation. AC43 Para. 1-41.


Question Number. 11. A crack is found in a wooden spar, you.
Option A. must replace the spar section.
Option B. might be able to repair the spar.
Option C. must replace the entire spar.
Correct Answer is. might be able to repair the spar.
Explanation. AC43 Para. 1-44.


Question Number. 12. Wood sealants used on wooden aircraft structures are for.
Option A. helping to prevent wood cracking.
Option B. improving aerodynamic efficiency.
Option C. reducing the requirement for sanding.
Correct Answer is. helping to prevent wood cracking.
Explanation. AC43 Para. 1-44 c.


Question Number. 13. To determine whether an aircraft wooden structure surface is compound curvature, you would use.
Option A. a curvature gauge.
Option B. a sheet of paper.
Option C. a trammel.
Correct Answer is. a sheet of paper.
Explanation. AC43 Para. 1-48.


Question Number. 14. To assist the bending of plywood, a heated bending former must be heated to a temperature of.
Option A. 300  °C.
Option B. 150  °C.
Option C. 100  °C.
Correct Answer is. 150  °C.
Explanation. AC43 Para.1-49 b.


Question Number. 15. A splayed patch repair may be used on plywood damage which does not exceed.
Option A. 20 times the skin thickness.
Option B. 15 times the skin thickness.
Option C. 10 times the skin thickness.
Correct Answer is. 15 times the skin thickness.
Explanation. AC43 Para.1-51 a.


Question Number. 16. A surface patch to a plywood structure may be a large as.
Option A. 50 sq.inch area.
Option B. 50 inch perimeter.
Option C. 50 inch diameter.
Correct Answer is. 50 inch perimeter.
Explanation. AC43 Para.1-51 b.


Question Number. 17. The steepest slope permitted on the scarf of a scarfed plywood repair is.
Option A. 1 in 20.
Option B. 1 in 4.
Option C. 1 in 12.
Correct Answer is. 1 in 12.
Explanation. AC43 Para.1-51 c.


Question Number. 18. The maximum size damage to plywood skin that may be repaired with a fabric patch is.
Option A. 3.0 inch diameter.
Option B. 0.5 inch diameter.
Option C. 1.0 inch diameter.
Correct Answer is. 1.0 inch diameter.
Explanation. AC43 Para 1-52.


Question Number. 19. The doubler used to support a scarfed patch plywood repair should be made from plywood of a minimum.
Option A. 1/4 inch thick.
Option B. 1/8 inch thick.
Option C. 3/8 inch thick.
Correct Answer is. 1/4 inch thick.
Explanation. AC43 Para.1-51 d and Figure 1-16.


Question Number. 20. An aircraft wooden structure must be surface finished and sealed.
Option A. on both the outer and inner surfaces.
Option B. on the inner surfaces only.
Option C. on the outer surfaces only.
Correct Answer is. on both the outer and inner surfaces.
Explanation. AC43 Para 1-64.


Question Number. 21. Pine wood has a strength, compared to that of spruce.
Option A. less than.
Option B. exceeding.
Option C. the same as.
Correct Answer is. less than.
Explanation. AC43 Table 1-1.


Question Number. 22. The standard wood type for aircraft wood structures is.
Option A. spruce.
Option B. douglas fir.
Option C. pine.
Correct Answer is. spruce.
Explanation. AC43 Table 1-1.


Question Number. 23. Hard knots in wood are acceptable.
Option A. in certain locations.
Option B. never.
Option C. up to 3/8 inch diameter in any location.
Correct Answer is. in certain locations.
Explanation. AC43 Para 1-2.


Question Number. 24. A 'shake' in a piece of wood is a crack.
Option A. across annual rings.
Option B. induced by artificial stress.
Option C. between two annual rings.
Correct Answer is. between two annual rings.
Explanation. AC43 Para.1-2.


Question Number. 25. Wood with checks, shakes or splits.
Option A. can be used providing the damage is repaired by gluing and clamping.
Option B. can be used for certain secondary structure.
Option C. must be rejected.
Correct Answer is. must be rejected.
Explanation. AC43 Para 1-2.


Question Number. 26. Compression wood.
Option A. is a hard-wood.
Option B. should be rejected.
Option C. is preferred because of its superior strength qualities.
Correct Answer is. should be rejected.
Explanation. AC43 Para 1-2.


Question Number. 27. Red heart and purple heart.
Option A. are types of hard-wood.
Option B. are forms of decay in wood.
Option C. are harmless natural defects in wood.
Correct Answer is. are forms of decay in wood.
Explanation. AC43 Para 1-2.


Question Number. 28. The greatest amount of shrinkage in wood is in which direction?.
Option A. Tangential.
Option B. Radial.
Option C. The shrinkage is equal in tangential and radial directions.
Correct Answer is. Tangential.
Explanation. AC43 Para 1-2.


Question Number. 29. Shrinkage of wood is.
Option A. equal along and across the fibres.
Option B. least along the fibres.
Option C. least across the fibres.
Correct Answer is. least along the fibres.
Explanation. AC43 Para 1-2.


Question Number. 30. Shrinkage of wood is.
Option A. greatest in the longitudinal direction.
Option B. negligible in the longitudinal direction.
Option C. negligible in the radial direction.
Correct Answer is. negligible in the longitudinal direction.
Explanation. AC43 Para 1-2.


Question Number. 31. The maximum permissible grain deviation in wood is.
Option A. 1:8.
Option B. 1:20.
Option C. 1:15.
Correct Answer is. 1:15.
Explanation. AC43 Para 1-1.


Question Number. 32. Nails used on wood structures should be.
Option A. 50 mm apart.
Option B. 12 mm apart.
Option C. 25 mm apart.
Correct Answer is. 25 mm apart.
Explanation. AC43 Para 1-11 c.


Question Number. 33. Small (up-to 3/8 inch diameter) hard-knots are allowed in a wooden spar.
Option A. in the middle 1/3 portion.
Option B. nowhere.
Option C. in the outer 1/3 portions.
Correct Answer is. in the middle 1/3 portion.
Explanation. AC43 Para 1-1.


Question Number. 34. If metal fasteners are removed from an aircraft's wood structure, and are found to have corrosion on them, this can indicate.
Option A. acidity of the adjoining wood structure.
Option B. deterioration of the fastener.
Option C. decay of the adjoining wood structure.
Correct Answer is. decay of the adjoining wood structure.
Explanation. AC43 1-28 j.


Question Number. 35. Bolt holes through wooden structures should be.
Option A. sealed, and the sealant allowed to dry before fitting the bolt.
Option B. left unsealed and unvarnished inside the hole.
Option C. sealed with varnish and wet-assembled with the bolt before the varnish has dried.
Correct Answer is. sealed, and the sealant allowed to dry before fitting the bolt.
Explanation. AC43 1-71.


Question Number. 36. Wood end-grain.
Option A. has the same susceptibility to moisture ingress as the side of the grain.
Option B. is less susceptible to moisture ingress as the side of the grain.
Option C. is more susceptible to moisture ingress as the side of the grain.
Correct Answer is. is more susceptible to moisture ingress as the side of the grain.
Explanation. AC43 1-69.


Question Number. 37. In cases of elongated boltholes in a wood spar or cracks in the vicinity of the boltholes.
Option A. it is permissible to ream the hole, plug with hardwood and re-drill.
Option B. a new section of spar should be spliced in or the spar entirely replaced.
Option C. the spar may be reinforced by using hardwood reinforcing plates.
Correct Answer is. a new section of spar should be spliced in or the spar entirely replaced.
Explanation. AC43.


Question Number. 38. A faint line running across the grain of a wood spar generally indicates.
Option A. shear failure.
Option B. decay.
Option C. compression failure.
Correct Answer is. compression failure.
Explanation. AC43.


Question Number. 39. The I-beam wooden spar is routed to.
Option A. obtain uniform strength.
Option B. decrease weight.
Option C. increase strength.
Correct Answer is. decrease weight.
Explanation. NIL.


Question Number. 40. Pin knot clusters are permitted in wood aircraft structure provided.
Option A. they have no mineral streaks.
Option B. no pitch pockets are within 12 inches.
Option C. they produce a small effect of grain direction.
Correct Answer is. they produce a small effect of grain direction.
Explanation. AC43.


Question Number. 41. Compression failures in wood aircraft structures are characterised by buckling of the fibres that appear as streaks on the surface.
Option A. parallel to the grain.
Option B. at right-angles to the growth rings.
Option C. at right angles to the grain.
Correct Answer is. at right angles to the grain.
Explanation. NIL.

03.3. Aircraft Materials - Fabric Covering.


Question Number. 1. Fabrics may be fitted to airframe structures by.
Option A. always riveting.
Option B. wood nails.
Option C. tying on with string.
Correct Answer is. tying on with string.
Explanation. NIL.


Question Number. 2. Aircraft fabric covering is made from.
Option A. silk.
Option B. polyester.
Option C. nylon.
Correct Answer is. polyester.
Explanation. AC43 Para 2-3 a.


Question Number. 3. At manufacture, aircraft fabric is.
Option A. shrunk.
Option B. doped.
Option C. stretched.
Correct Answer is. stretched.
Explanation. AC43 Para 2-3 b.


Question Number. 4. Recovering or repairing of an aircraft with a fabric other than the original fabric type is.
Option A. a major modification and requires approval.
Option B. prohibited.
Option C. a minor modification, providing the fabric is the same strength as the original.
Correct Answer is. a major modification and requires approval.
Explanation. AC43 Para 2-5 NOTE.


Question Number. 5. Reinforcing tape used on aircraft fabric covering must have a minimum strength of.
Option A. 80 lb.
Option B. 40 lb.
Option C. 120 lb.
Correct Answer is. 40 lb.
Explanation. AC43 Para 2-5 a.


Question Number. 6. Lacing cord used on aircraft fabric covering must have a minimum breaking strength of.
Option A. 120 lb.
Option B. 80 lb.
Option C. 40 lb.
Correct Answer is. 40 lb.
Explanation. AC43 Para 2-5 c.


Question Number. 7. Fabric seams are preferable.
Option A. parallel to the line of flight.
Option B. spanwise to the line of flight.
Option C. oblique to the line of flight.
Correct Answer is. parallel to the line of flight.
Explanation. AC43 Para 2-7.


Question Number. 8. Single stitched machine sewn seams are permissible.
Option A. at all locations on the aircraft.
Option B. never.
Option C. only when positioned over a structure.
Correct Answer is. only when positioned over a structure.
Explanation. AC43 Para 2-7 a 1.


Question Number. 9. The minimum pitch of hand-sewn stitch is.
Option A. 1/4 inch.
Option B. equal to 10 times the thread thickness.
Option C. 4 inches.
Correct Answer is. 1/4 inch.
Explanation. AC43 Para 2-7 a 2.


Question Number. 10. Hand sewn stitch must be locked at a minimum of.
Option A. the end of the stitch only.
Option B. 20 stitch intervals.
Option C. 10 stitch intervals.
Correct Answer is. 10 stitch intervals.
Explanation. AC43 Para 2-7 a 2.


Question Number. 11. Fabric to be hand sewn must be doubled under at the edge to a minimum distance of.
Option A. 1/2 inch.
Option B. 3/8 inch.
Option C. 1/4 inch.
Correct Answer is. 3/8 inch.
Explanation. AC43 Para 2-7 a 2.


Question Number. 12. Holes are cut in fabric for inspection panels, spar fittings, drain grommets etc.
Option A. after doping.
Option B. before doping.
Option C. before attaching the fabric to the structure.
Correct Answer is. after doping.
Explanation. AC43 Para 2-9 a.


Question Number. 13. Aircraft fabric lacing cord is reinforced with.
Option A. epoxy.
Option B. wax.
Option C. lanolin.
Correct Answer is. wax.
Explanation. AC43 Para 2-10 d 2.


Question Number. 14. The dope applied to an aircraft's fabric covering causes shrinkage.
Option A. on the last coat only.
Option B. on the first coat only.
Option C. on all coats.
Correct Answer is. on all coats.
Explanation. AC43 Para 2-20.


Question Number. 15. The two preferred types of dope used on aircraft fabric covering is.
Option A. cellulose and polyester.
Option B. cellulose and butyrate.
Option C. nitrate and butyrate.
Correct Answer is. nitrate and butyrate.
Explanation. AC43 Para 2-20.


Question Number. 16. Aircraft dope, during storage in adverse conditions in a store-room, will become.
Option A. acidic.
Option B. discoloured.
Option C. alkaline.
Correct Answer is. acidic.
Explanation. AC43 Para 2-20 b.


Question Number. 17. What type of dope is preferred for use on natural fiber aircraft covering?.
Option A. Nitrate.
Option B. Any type of dope is suitable.
Option C. Butyrate.
Correct Answer is. Nitrate.
Explanation. AC43 Para 2-20 c.


Question Number. 18. Which of the following is true regarding aircraft dope type?.
Option A. Nitrate dope may be applied over the top of butyrate dope.
Option B. Butyrate dope may be applied over the top of nitrate dope.
Option C. Either type of dope may be applied over the top of any type of dope.
Correct Answer is. Butyrate dope may be applied over the top of nitrate dope.
Explanation. AC43 Para 2-20 c.


Question Number. 19. What type of shoes should be worn by the technician applying a dope finish to a fabric covered aircraft?.
Option A. Rubber soled.
Option B. Leather soled.
Option C. Plastic uppers.
Correct Answer is. Leather soled.
Explanation. AC43 Para 2-20 f table 2-3.


Question Number. 20. What are the limits of the environmental conditions for applying dope to a fabric covered aircraft?.
Option A. Relative humidity 50 - 70%, temperature range 40 ° to 60  °F.
Option B. Relative humidity 50 - 75%, temperature range 65 ° to 75  °F.
Option C. Relative humidity 20 - 60%, temperature range 65 ° to 75  °F.
Correct Answer is. Relative humidity 20 - 60%, temperature range 65 ° to 75  °F.
Explanation. AC43 Para 2-20 f table 2-4.


Question Number. 21. Applying dope to a fabric covered aircraft should be done by.
Option A. spraying all coats to avoid brush marks.
Option B. spray all coats except the first three.
Option C. brushing all coats to ensure it is absorbed into the fabric.
Correct Answer is. spray all coats except the first three.
Explanation. AC43 Para 2-20 f table 2-4.


Question Number. 22. Regarding the thinning of aircraft dope.
Option A. underthinning is preferred to overthinning.
Option B. dope should be thinned with automotive thinners.
Option C. overthinning is preferred to underthinning.
Correct Answer is. overthinning is preferred to underthinning.
Explanation. AC43 Para 2-20 f table 2-4 and 2-20 c NOTE.


Question Number. 23. A retarder is added to aircraft dope to.
Option A. to extend the shelf life.
Option B. produce a smoother finish.
Option C. to retard the application time.
Correct Answer is. produce a smoother finish.
Explanation. AC43 Para 2-20 f table 2-4.


Question Number. 24. Doped fabric.
Option A. is not to be treated after application.
Option B. is treated with varnish.
Option C. is treated with wax compound.
Correct Answer is. is treated with wax compound.
Explanation. AC43 Para 2-20 f table 2-4.


Question Number. 25. Dope should be applied to an aircraft's fabric coating in a relative humidity not exceeding.
Option A. 50%.
Option B. 85%.
Option C. 65%.
Correct Answer is. 65%.
Explanation. AC43 Para 2-21 6.


Question Number. 26. Dressing out' of a fabric covering refers to.
Option A. the trimming of excess fabric after fitting.
Option B. applying finishing tapes, reinforcing patches, inspection ports etc.
Option C. laying the fabric out on the floor and cutting it to size prior to fitting to the aircraft.
Correct Answer is. applying finishing tapes, reinforcing patches, inspection ports etc.
Explanation. AC43 Para 2-21 d.


Question Number. 27. Coats of clear dope are applied to an aircraft's fabric.
Option A. before coats of aluminium pigmented dope are applied.
Option B. before or after coats of aluminium pigmented dope are applied, it does not matter.
Option C. after coats of aluminium pigmented dope are applied.
Correct Answer is. before or after coats of aluminium pigmented dope are applied, it does not matter.
Explanation. AC43 Para 2-21.


Question Number. 28. What is the reason for using aluminium-pigmented dope on a fabric covered aircraft?.
Option A. To provide an aluminium colour to the aircraft.
Option B. To block UV radiation.
Option C. To provide strength.
Correct Answer is. To block UV radiation.
Explanation. AC43 Para 2-21.


Question Number. 29. Aircraft sheet plywood skins are.
Option A. sealed and varnished or painted.
Option B. sealed and doped.
Option C. covered in fabric.
Correct Answer is. covered in fabric.
Explanation. AC43 Para 2-22.


Question Number. 30. Blushing' of a doped fabric surface is an indication of.
Option A. moisture enterring into the wood/fabric structure during service.
Option B. moisture condensing on the surface during drying of the dope.
Option C. oil contamination of the doped fabric.
Correct Answer is. moisture condensing on the surface during drying of the dope.
Explanation. AC43 Para 2-23.


Question Number. 31. Orange peeling of a doped surface may be caused by.
Option A. dope viscosity too low.
Option B. dope viscosity too high.
Option C. air temperature too low.
Correct Answer is. dope viscosity too high.
Explanation. AC43 Para 2-23 c.


Question Number. 32. Orange peeling of a doped surface may be caused by.
Option A. Orange peeling of a doped surface may be caused by.
Option B. air temperature too low.
Option C. spray gun pressure too low.
Correct Answer is. spray gun pressure too low.
Explanation. AC43 Para 2-23 c.


Question Number. 33. Butyrate dope burns.
Option A. slower than nitrate dope.
Option B. faster than nitrate dope.
Option C. the same rate as nitrate dope.
Correct Answer is. slower than nitrate dope.
Explanation. AC43 Para 2-32.


Question Number. 34. Fabric coated with nitrate dope can be differentiated from fabric coated in butyrate dope by.
Option A. carrying out a burn test.
Option B. smelling the fabric.
Option C. observing the colour.
Correct Answer is. carrying out a burn test.
Explanation. AC43 Para 2-32.


Question Number. 35. If the fabric on a wood/fabric aircraft has lost its strength.
Option A. the fabric can be treated with a rejuvenator.
Option B. the fabric can be treated with additional coats of the approved type of dope.
Option C. the fabric must be replaced.
Correct Answer is. the fabric can be treated with additional coats of the approved type of dope. OR the fabric must be replaced.
Explanation. AC43 Para 2-35.


Question Number. 36. When repairing a section of aircraft fabric with a new fabric patch.
Option A. all the dope must be removed from the parent fabric faying surface before the patch is applied.
Option B. the patch can be applied to the parent fabric without preparation.
Option C. all the aluminium-pigmented dope layers must be removed from the parent fabric faying surface before the patch is applied.
Correct Answer is. the patch can be applied to the parent fabric without preparation. OR all the aluminium-pigmented dope layers must be removed from the parent fabric faying surface before the patch is applied.
Explanation. AC43 Para 2-42 b.


Question Number. 37. When does an aircraft fabric covering repair become a major repair?.
Option A. When the repair extends over a wing rib.
Option B. When the repair extends over three adjacent wing ribs.
Option C. When the repair extends over two adjacent wing ribs.
Correct Answer is. When the repair extends over three adjacent wing ribs. OR When the repair extends over two adjacent wing ribs
Explanation. AC43 Para 2-42 d.


Question Number. 38. Where the edge of a new fabric section will be located within 1 inch of a structural member to which the fabric is attached by rib lacing or other methods, the new fabric section should.
Option A. be extended 3 inches past the structural member.
Option B. be extended to meet the structural member.
Option C. be designated a major repair.
Correct Answer is. be extended 3 inches past the structural member.
Explanation. AC43 Para 2-42 f.


Question Number. 39. What width of finishing tape should be used on a tear in a fabric cover which is 10 inches long?.
Option A. 2 inches.
Option B. 6 inches.
Option C. 4 inches.
Correct Answer is. 4 inches.
Explanation. AC43 2-44 a.


Question Number. 40. What width of finishing tape should be used on a tear in a fabric cover which is 20 inches long?.
Option A. 6 inches.
Option B. 2 inches.
Option C. 4 inches.
Correct Answer is. 6 inches.
Explanation. AC43 2-44 c.


Question Number. 41. Lines of stitching of a fabric repair is locked at the end with.
Option A. a hitch knot.
Option B. a half hitch knot.
Option C. a double half hitch knot.
Correct Answer is. a double half hitch knot.
Explanation. AC43 2-43 Figure 2-13.


Question Number. 42. Wrinkles in a fabric covering of a wood/fabric aircraft are.
Option A. not permitted.
Option B. a minor aerodynamic detriment.
Option C. permitted only if they are temporary due to damp/wet weather conditions.
Correct Answer is. permitted only if they are temporary due to damp/wet weather conditions.
Explanation. AC43 2-30 b (3) NOTE.


Question Number. 43. The threads per inch of Grade 'A' aircraft fabric is.
Option A. 60-64.
Option B. 80-84.
Option C. 110-115.
Correct Answer is. 80-84.
Explanation. AC43 2-6 Table 2-1.


Question Number. 44. When and how is finishing tape applied on fabric covered aircraft?.
Option A. Doped on immediately prior to the finish coat.
Option B. Sewed or laced on before dope is applied.
Option C. Doped on after the first or second coat of dope.
Correct Answer is. Doped on after the first or second coat of dope.
Explanation. AC43.


Question Number. 45. The determining factor in the selection of the correct weight of textile fabric to be used in covering any type of aircraft is the.
Option A. maximum wing loading.
Option B. speed of the aircraft.
Option C. speed of the aircraft and the maximum wing loading.
Correct Answer is. speed of the aircraft and the maximum wing loading.
Explanation. AC43.


Question Number. 46. How many fabric thicknesses will be found in a French-fell seam?.
Option A. Five.
Option B. Three.
Option C. Four.
Correct Answer is. Four.
Explanation. The edges of the fabric are folded over each other, so the threads of a double row of stitches passes through four thicknesses of fabric.


Question Number. 47. Finishing tape (surface tape) is used for what purpose?.
Option A. To prevent 'ripple formation' in covering fabric.
Option B. To provide additional wear resistance over the edges of fabric forming structures.
Option C. To provide additional anti-tear resistance under reinforcement tape.
Correct Answer is. To provide additional wear resistance over the edges of fabric forming structures.
Explanation. AC43.


Question Number. 48. Moisture, mildew, chemicals and acids have no effect on.
Option A. glass fabric.
Option B. linen fabric.
Option C. Dacron fabric.
Correct Answer is. Dacron fabric.
Explanation. AC43 page 2-35 paragraph (1). http://www.ultralightnews.com/pilotslounge/cleaning_dacron.htm


Question Number. 49. The strength classification of fabric used in aircraft covering is based upon.
Option A. bearing strength.
Option B. shear strength.
Option C. tensile strength.
Correct Answer is. tensile strength.
Explanation. NIL.


Question Number. 50. Fabric rejuvenator.
Option A. penetrates the fabric and restores fungicidal resistance.
Option B. restores fabric strength and tautness to at least the minimum acceptable level.
Option C. restores the condition of the dope coatings.
Correct Answer is. restores fabric strength and tautness to at least the minimum acceptable level. OR restores the condition of the dope coatings.
Explanation. NIL.


Question Number. 51. 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.
Option A. 56 pounds per inch warp and weft.
Option B. 70% of its original strength.
Option C. 70% of the original strength for intermediate fabric.
Correct Answer is. 70% of the original strength for intermediate fabric.
Explanation. NIL.


Question Number. 52. What is used to slow the drying time of some dope finishes to prevent blush?.
Option A. Rejuvenator.
Option B. Reducer.
Option C. Retarder.
Correct Answer is. Retarder.
Explanation. NIL.


Question Number. 53. Aluminium-pigment in dope is used primarily to.
Option A. exclude sunlight from the fabric.
Option B. provide a silver colour.
Option C. aid in sealing out moisture from the fabric.
Correct Answer is. exclude sunlight from the fabric.
Explanation. NIL.

Credit :    Md Asdullah

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