ACM-170 FAA

Question 1

8219. Magnetic particle. inspection is used primarily to detect.

A-distortion.
8-deep subsurface flaws.
C-flaws on or near the surface.

Answer 1

C

Magnetic particle inspection is used to detect flaws in ferromagnetic material on or near the surface. These flaws form north and south magnetic poles when the part is magnetized. Iron oxide suspended in a fluid pumped over the part is attracted to and held by the magnetism and it outlines the flaw.

(AM.I.E.K1) - FAA-H-8083-30

Question 2

8220. Liquid penetrant inspection methods may be used on which of the following?

A-Ferrous metals and nonporous plastics.
8-Porous and nonporous plastics and nonferrous metals.
C-Ferrous and nonferrous metals and nonporous plastics.

Answer 2

C

Liquid penetrant inspection methods may be used to detect faults that extend to the surface on both ferrous and nonferrous metals and nonporous plastics.

(AM.I.E.K1) - FAA-H-8083-30

Question 3

8224. Which of the following factors are considered essential knowledge for X-ray exposure?

A- Processing of the film and its characteristics.
8-Material thickness and density and the type of defect to be detected.
C-Processing of the film, characteristics of X-ray machine used, and film characteristics.

Answer 3

B

The factors of radiographic exposure are so interdependent that it is necessary to consider all factors for any particular radiographic exposure. These factors include, but are not limited to, the following:

1. Material thickness and density.
2. Shape and size of the object.
3. Type of defect to be detected.
4. Characteristics of X-ray machine used.
5. Exposure distance.
6. Exposure angle.
   Z Film characteristics.
7. Type of intensifying screen, if used.

(AM.I.E.K1) - FAA-H-8083-30

Question 4

8230. One way a part may be demagnetized after magnetic particle inspection is by:

A-subjecting the part to high voltage, low amperage AC.
B-slowly moving the part out of an AC magnetic field of sufficient strength.
C-slowly moving the part into an AC magnetic field of sufficient strength.

Answer 4

B

A steel part is magnetized by holding it in a strong, steady magnetic field that aligns all of the magnetic domains in the material. It is demagnetized by placing it in an AC magnetic field that continually reverses its polarity. This causes the domains to continually reverse their direction. As the domains are reversing, the part is slowly moved from the field so the domains remain in a disoriented state
when the demagnetizing force is removed.

(AM.I.E.K1) - FAA-H-8083-30

Question 5

8231. Which type crack can be detected by magnetic particle inspection using either circular or longitudinal
      magnetization?

A-45°.
8-Longitudinal.
C- Transverse.

Answer 5

A

Longitudinal magnetization produces a magnetic field that extends lengthwise in the material. It is used to detect faults that extend across the part, perpendicular to the lines of magnetic flux. Circular magnetization produces a magnetic field that extends across the material. It can detect faults that are oriented along the length of the part. Either type of magnetization can detect a fault that runs at
45° to the length of the part.

{AM.I.E.K1)- FAA-H-8083-30

Question 6

8238. The pattern for an inclusion is a magnetic particle buildup forming

A. A fernlike pattern.
B. A single line.
C. Parallel lines.

Answer 6

C

Inclusions are impurities trapped inside a piece of metal when it was cast. When the part is inspected by magnetic particle inspection, the inclusion does not show up as a clearly defined fault but the indication is fuzzy. Rather than sharply defined poles, there are several sets of poles that cause the oxide to form in a in a series of parallel lines.

(AM.I.E.K1) - FAA-H-8083-30

Question 7

8242. What defects will be detected by magnetizing a part using continuous longitudinal magnetization with a cable?

A-Defects perpendicular to the long axis of the part.
8-Defects parallel to the long axis of the part.
C-Defects parallel to the concentric circles of magnetic force within the part.

Answer 7

A

A part magnetized longitudinally by current flowing through a cable wrapped around it will show up defects that are perpendicular (at right angles) to the long axis of the part.

(AM.I.E.K1) - FAA-H-8083-30

Question 8

8243. Circular magnetization of a part can be used to detect which defects?

A- Defects parallel to the long axis of the part.
8-Defects perpendicular to the long axis of the part.
C-Defects perpendicular to the concentric circles of magnetic force within the part.

Answer 8

A

A part magnetized circularly by the magnetizing current flowing lengthwise through it, will show up defects parallel to the long axis of the part.

(AM.I.E.K1)- FAA-H-8083-30

Question 9

8246. Which of the following describe the effects of annealing steel and aluminum alloys?

A- Decreasing internal stresses and softening of the metal.
B-Softening of the metals and improved corrosion resistance.
C-lmproved corrosion resistance.

Answer 9

A

Steel and aluminum alloys may be annealed to decrease internal stresses and soften the metal. Annealing does not improve corrosion resistance.

(AM.I.E.K1) - FAAH - 8083-30

Question 10

8257. What is generally used in the construction of aircraft exhaust collectors, stacks, and manifolds?

A-Stainless steel.
B- Titanium.
C-Aluminum.

Answer 10

A

The material most generally used for firewalls, exhaust collectors, stacks, and manifolds on aircraft is stainless steel at least 0.015 inch thick. Mild steel, at least 0.018 inch thick and protected from corrosion, terneplate at least 0.018 inch thick, and Mone/ at least 0.018 inch thick may also be used.

(AM.I.E.K1)-FAA-H-8083-30

Question 11

8257-1.
What metal has special short-time heat properties and is used in the construction of aircraft firewalls?

A-Stainless steel.
8-Chrome molybdenum alloy steel.
C- Titanium alloy.

Answer 11

C

Titanium has some merit for short-time exposure up to 3, 000°F where strength Is not important. Aircraft firewalls demand this requirement.

(AM.I.E.K1)- FAA-H-8083-30

Question 12

8259. Alclad is a metal consisting of:

A-aluminum alloy surface layers and a pure _aluminum core.
8-pure aluminum surface layers on an aluminum alloy core.
C-a homogeneous mixture of pure aluminum and aluminum alloy.

Answer 12

B

Alclad is the registered trade name for an aluminum alloy sheet that has pure aluminum rolled onto its surfaces. The pure aluminum protects the alloy core from corrosion.

(AM.I.E.K1) - FAA-H-8083-30

Question 13

8273. The core material of Alclad 2024-T4 is:

A-heat-treated aluminum alloy, and the surface material is commercially pure aluminum.
B. Commercially pure aluminum, and the surface material is heat-treated aluminum alloy.
C-strain-hardened aluminum alloy, and the surface material is commercially pure aluminum.

Answer 13

A

Alclad 2024-T4 is a type of sheet metal that has a core of 2024-T4 solution-heat-treated aluminum alloy. Commercially pure aluminum is rolled onto the surfaces of the sheet for corrosion protection. The name A/clad is a registered trade name.

(AM.I.E.K1) - FAA-H-8083-30

Question 14

8274. The aluminum code number 1100 identifies what type of aluminum?

A-Aluminum alloy containing 11 percent copper.
B-Aluminum alloy containing zinc.
C-99 percent commer9ially pure aluminum.

Answer 14

C

Aluminum identified by the code number 1100 is 99 percent commercially pure aluminum.

(AM.I.E.K1)- FAAH - 8083-30

Question 15

8237. (1) An aircraft part may be demagnetized by subjecting it to a magnetizing force from alternating current that is gradually reduced in strength.
      (2) An aircraft part may be demagnetized by subjecting it to a magnetizing force from direct current that is alternately reversed in direction and gradually reduced in strength.

Regarding the above statements,
A~both 1 and 2 are true.
8-only 1 is true.
C-only 2 is true.

Answer 15

A

Statement 1 is true. A part is demagnetized by placing it in an AC magnetic field whose strength is gradually reduced while it continually reverses its polarity. This leaves the domains in a disoriented state when the demagnetizing force is removed. Statement 2 is also true. A DC magnetic field whose direction is continually reversed and the strength is gradually reduced may be used to demagnetize an aircraft part that has been inspected by the magnetic particle inspection method.

(AM.I.E.K2)- FAA-H-8083-30

Question 16

8245. What type of corrosion may attack the grain boundaries of aluminum alloys when the heat treatment process has been improperly accomplished?

A-Concentration cell.
8-lntergranular.
C-Fretting.

Answer 16

B

An aluminum alloy part is heat-treated by being heated in an oven and then removed and immediately quenched in cold water. If there is a delay between the time the part is removed from the oven and the time it is quenched, the grains in the metal will grow. Because of this, there is a good probability that intergranular corrosion will develop along the boundaries of the grains within the metal.

(AM.I.E.K2) - FAA-H-8083-30

Question 17

8247. Which heat-treating process of metal produces a hard, wear-resistant surface over a strong, tough core?

A-Case hardening.
B-Annealing.
C- Tempering.

Answer 17

A

Case hardening is a heat treatment process for steel in which the surface is hardened to make it wear resistant, but the inside of the metal remains strong and tough. Annealing is a heat treatment process for either ferrous or nonferrous metal that makes the metal softer. Tempering is a method of heat treatment in which some of the hardness is removed from a hardened metal. Removing some
of the hardness makes the metal less brittle.

(AM.I.E.K2) - FAA-H-8083-30

Question 18

8248. Which heat-treating operation would be performed when the surface of the metal is changed chemically by introducing a high carbide or nitride content?

A- Tempering.
B-Normalizing.
C-Case hardening.

Answer 18

C

In case hardening, the surface of the metal is changed chemically by introducing a high carbide or nitride content. The core is unaffected chemically. When heat-treated, the surface responds to hardening while the core remains tough.

(AM.I.E.K2) - FAA-H-8083-30

Question 19

8249. Normalizing is a process of heat treating

A-aluminum alloys only.
B-iron-base metals only.
C-both aluminum alloys and iron-base metals.

Answer 19

B

Normalizing is a heat treating process in which an ironbase metal is heated to a temperature above its critical temperature and allowed to cool in still air. Normalizing reduces the stresses in the metal that were put there by the fabrication process.

(AM.I.E.K2) - FAA-H-8083-30

Question 20

8251. The reheating of a heat treated metal, such as with a welding torch
      A-has little or no effect on a metal’s heat treated characteristics.
      B-has a cumulative enhancement effect on the original heat treatment.
      C-can significantly alter a metal’s properties in the reheated area.

Answer 20

C

When a heat-treated metal is reheated with a welding torch there is no close control of the temperature and the metal’s properties in the reheated area may be significantly altered.

(AM.I.E.K2) - FAA-H-8083-30

Question 21

8253. What aluminum alloy designations indicate that the metal has received no hardening or tempering treatment?

A-3003-F.
B-5052-H36.
C-6061-O.

Answer 21

A

In the temper designations used with aluminum alloy, these letters have the following meanings:
F means “as fabricated.,, There has been no control over its temper. H36 means the metal is non heat - treatable, but it has been strain-hardened and stabilized to its 3/4 hard state.
0 means the metal has been annealed.

(AM.I.E.K2) - FAA-H-8083-30

Question 22

8254. Which material cannot be heat treated repeatedly without harmful effects?

A-Unclad aluminum alloy in sheet form.-/
B-6061-T9 stainless steel.
C-Clad aluminum alloy.

Answer 22

C

Clad aluminum alloy sheets have a core of high-strength aluminum alloy onto whose surface have been rolled a thin layer of pure aluminum. When clad sheets are heated in the process of heat treatment, some of the pure aluminum diffuses into the core alloy and weakens the sheet.
The manufacturer of the aluminum specifies the number of times clad sheets can be heat-treated. Typically, they allow the sheet to be heat-treated only one to three times.

(AM.I.E.K2) - FAA-H-8083-30

Question 23

8255. What is descriptive of the annealing process of steel during and after it has been annealed?

A- Rapid cooling; high strength.
8-Slow cooling; low strength.
C-Slow cooling; increased resistance to wear.

Answer 23

B

Annealing of steel is accomplished by heating the metal to just above the upper critical point, soaking at that temperature and cooling very slowly in the furnace. Annealing of steel produces a fine-grained, soft, ductile metal without internal stresses or strains. In the annealed state steel has its lowest strength.

(AM.I.E.K2) - FAA-H-8083-30

Question 24

8250. Which of the following occurs when a mechanical force such as rolling, hammering, or bending is repeatedly applied to most metals at room temperature?

A- The metals become artificially aged.
8- The metals become stress corrosion cracked.
C- The metals become strain or work hardened or cold worked.

Answer 24

C

When a mechanical force such as rolling, hammering, or bending is repeatedly applied to most metals at room temperature, the metals become strain or work hardened or cold worked. They may become so hard and brittle that they break.

(AM.I.E.K3) - FAA-H-8083-30

Question 25

8252. Why is steel tempered after being hardened? A-To increase its hardness and ductility. B-To increase its strength and decrease its internal stresses. C- To relieve its internal stresses and reduce its brittleness.

Answer 25

C Steel is tempered after it is hardened to remove some of the internal stresses and make it less brittle. Tempering is done by heating it to a temperature quite a way below its critical temperature and allowing it to cool in still air. (AM.I.E.K3) - FAA-H-8083-30

Question 26

8258. Unless otherwise specified or required, aircraft bolts should be installed so that the bolthead is A-upward, or in a rearward direction. B-upward, or in a forward direction. C-downward, or in a forward direction.

Answer 26

B An accepted rule of thumb for installing bolts in an aircraft structure is to have the bolt head up, forward, or outboard. When the bolt is installed in this way, it is least likely to fall out if the nut should ever back off. (AM.I.E.K4) - FAAH- 8083-30

Question 27

8260. A fiber-type, self-locking nut must never be used on an aircraft if the bolt is: A-under shear loading. 8-under tension loading. C-subject to rotation.

Answer 27

C Fiber-type, self-locking nuts depend upon the fiber insert in the end of the nut gripping the bolt threads tight enough to prevent the nut backing off. Since there is no mechanical lock between the nut and the bolt, the FAA recommends that a fiber-type self-locking nut not be used in any installation in which the fastener is subject to rotation. (AM.I.E.K4)-AC 43.13-18

Question 28

8260-1. Self-locking nuts may be used on aircraft provided that: A-the head of the bolt is safety wired. B-they are installed with a lock washer. C-the bolt or nut is not subject to rotation.

Answer 28

C Self-locking nuts are used on aircraft to provide tight connections which will not shake loose under severe vibration. Do not use self-locking nuts at joints that subject either the nut or bolt to rotation. (AM.I.E.K4)- FAA-H-8083-30

Question 29

8267. (Refer to Figure 43.) Identify the clevis bolt illustrated. A-1 8-3 C-2

Answer 29

B The bolt shown in View 3 is a clevis bolt. The bolt shown in View 1 is a drilled-head, hex-head bolt. The bolt shown in View 2 is an eyebolt. (AM.I.E.K4) - FAA-H-8083-30

Question 30

8271. Where is an AN clevis bolt used in an airplane? A-For· tension and shear load conditions. 8-Where external tension loads are applied. C-Only for shear load applications.

Answer 30

C A clevis bolt should be used only where the load to which the bolt is applied is a shear load. A clevis bolt is not designed to take any type of tensile load. The threaded portion of a clevis bolt is short and there is a groove between the threads and the shank. The head of a clevis bolt has a screwdriver slot rather than flats for the use of a wrench. (AM.I.E.K4) - FAA-H-8083-30

Question 31

8275. Aircraft bolts are usually manufactured with a: A-class 1 fit for the threads. 8-class 2 fit for the threads. C-class 3 fit for the threads.

Answer 31

C A class-3 fit is a medium fit. It is used on almost all standard aircraft bolts. A class-1 fit is a loose fit. This is used for coarse-thread stove bolts and square nuts. A class-2 fit is a free fit. It is used on some machine screws. (AM.I.E.K4) - FAA-H-8083-30

Question 32

8277. How is the locking feature of the fiber-type locknut obtained? A-By the use of an unthreaded fiber locking insert. B-By a fiber insert held firmly in place at the base of the load carrying section. C-By making the threads in the fiber insert slightly smaller than those in the load carrying section.

Answer 32

A A fiber-type lock nut is held firmly on the threads of a bolt by pressure caused by an unthreaded fiber insert locked into a recess in the end of the nut. When the bolt is screwed through the nut, it forces its way through the unthreaded fiber. The fiber grips the threads and applies a downward force between the threads in the nut and those on the bolt. This force prevents the nut vibrating loose. (AM.I.E.K4) - FAA-H-8083-30

Question 33

8261-1. Which is an acceptable safety device for a castle nut when installed on secondary structures? A-Star washer. B-Lockwasher. C-Cotter pin.

Answer 33

C The only safety device listed here that is suitable for a castle nut is a cotter pin. When a castle nut is installed on a stud that is screwed into a casting, it should be safetied with safety wire. (AM.I.E.K4)-AC 43.13-18

Question 34

8261-2 When installing a castle nut, start alignment with the cotter pin hole at the A-minimum recommended torque without friction drag torque. B-maximum recommended torque minus friction drag torque. C-minimum recommended torque plus friction drag torque.

Answer 34

C When installing a castle nut, start alignment with the cotter pin hole at the minimum recommended torque plus friction drag torque. Do not exceed the maximum torque plus the friction drag. If the hole and nut castellation do not align, change washer or nut and try again. (AM. I.E. K4) -AC43.13-1B

Question 35

8262-1 When used in close proximity to magnetic compasses, cotter pins are made of what material? A-Corrosion resisting steel. B-Anodized aluminum alloy. C-Cadmium-plated low carbon steel.

Answer 35

A Any metal parts installed near a magnetic compass should be nonmagnetic. The only nonmagnetic metal of which cotter pins are made that is listed among the alternatives is corrosion-resisting steel. (AM.I.E.K4)-FAA-H-8083-30

Question 36

8263-1 When a fiber or nylon insert-type self-locking nut can be threaded on a bolt or stud through the insert with only the fingers, it should be A-re-torqued frequently. B-rejected. C-reused only in a different location.

Answer 36

B A fiber stop nut should be rejected if it can be screwed onto the bolt or stud through the fiber using only the fingers. When the fiber is worn to this point, the nut can no longer be depended upon to hold against vibration. (AM.J.E.K4) -AC 43.13-1B

Question 37

8268 A particular component is attached to the aircraft structure by the use of an aircraft bolt and a castle tension nut combination. If the cotter pin hole does not align within the recommended torque range, the acceptable practice is to A-exceed the recommended torque range by no more than 10 percent. B. tighten below the torque range. C-change washers and try again.

Answer 37

C When tightening castle nuts on bolts, the cotter pin holes may not line up with the slots in the nuts at maximum recommended torque, plus friction drag. If the hole and nut castellation do not align, change washers and try again. Exceeding the maximum recommended torque is not recommended. (AM.I.E.K5) -AC 43.13-1B

Question 38

8270 How is a clevis bolt used with a fork-end cable terminal secured? A-With a shear nut tightened to a snug fit, but with no strain imposed on the fork and safetied with a cotter pin. B-With a castle nut tightened until slight binding occurs between the fork and the fitting to which it is being attached. C-With a shear nut and cotter pin or a thin self-locking nut tightened enough to prevent rotation of the bolt in the fork

Answer 38

A When a clevis bolt is used to secure a fork-end cable terminal, a shear castle nut should be used on the clevis bolt. The nut should be tightened until it is snug, but there must be no strain on the fork. The nut is secured to the clevis bolt with a cotter pin. (AM.I.E.K5)- FAA-H-8083-30

Question 39

8223 What method of magnetic particle inspection is used most often to inspect aircraft parts for invisible cracks and other defects? A-Residual. B-lnductance. C-Continuous.

Answer 39

C The continuous method of magnetic particle inspection is used for most aircraft parts because it provides the strongest magnetic field to attract the oxide from the fluid. In the continuous method of magnetic particle inspection, the part is either placed between the heads of the magnetizing machine or held inside the solenoid (coil). Magnetizing current flows while the fluid is pumped over the part. In the residual method of magnetic particle inspection, used for some smaller parts, the parts are magnetized and the magnetizing current is shut off. Only residual magnetism is left in the part to attract the oxide. (AM.I.E.K6) - FAA-H-8083-30

Question 40

8225 The testing medium that is generally used in magnetic particle inspection utilizes a ferromagnetic material that has: A-high permeability and low retentivity. 8-low permeability and high retentivity. C-high permeability and high retentivity.

Answer 40

A The testing medium used to indicate the presence of a fault in magnetic particle inspection is a finely ground iron oxide that has a high permeability and low retentivity, and is nontoxic. It is usually suspended in a light oil such as kerosine. (AM.I.E.K6) - FAA-H-8083-30

Question 41

8226 Which statement relating to the residual magnetizing inspection method is true? A-Subsurface discontinuities are made readily apparent. B-lt is used in practically all circular and longitudinal magnetizing procedures. C-lt may be used with steels which have been heat treated for stressed applications.

Answer 41

C In the residual method of magnetic particle inspection, the part is magnetized and removed from the magnetic field before the oxide-carrying fluid is pumped over it. Steel that has a high retentivity (retains its magnetism after the magnetizing force has been removed) can be inspected by the residual method. Steel that has been heat-treated for stressed applications has a high retentivity and it can be inspected by the residual method. (AM.I.E.K6) - FAAH- 8083-30

Question 42

8228 What two types of indicating mediums are available for magnetic particle inspection? A-Iron and ferric oxides. B-Wet and dry process materials. C-High retentivity and low permeability material.

Answer 42

B The magnetic medium used for magnetic particle inspection can be applied either as a dry oxide powder dusted over the surface or (as is more commonly done) suspended in a light oil such as kerosine and pumped over the surface. The iron oxide used as the indicating medium is often treated with a fluorescent dye that causes it to glow with a green light when an ultraviolet light {black light) is shone on it. (AM.I.E.K6) 1- FAA-H-8083-30

Question 43

8229 Which of the following materials may be inspected using the magnetic particle inspection method? A-Copper alloys. B-Aluminum alloys. C-lron alloys.

Answer 43

C In order for a part to be inspected by the magnetic particle method, it must be magnetizable. The only magnetizable metals listed are iron alloys. (AM.I.E.K6)- FAA-H-8083-3

Question 44

8232 Which of the following methods may be suitable to use to detect cracks open to the surface in aluminum forgings and castings? A-Dye penetrant inspection and eddy current inspection. B-Dye penetrant inspection and magnetic particle inspection. C-Magnetic particle inspection and metallic ring inspection.

Answer 44

A Dye penetrant, eddy current, ultrasonic, and visual inspections may be used on aluminum forgings and castings. Magnetic particle inspection can only be used on ferrous metals, and the metallic ring inspection is used to check for delaminations in bonded composite structural materials. (AM.I.E.K6) - FAA-H-8083-30

Question 45

8233 To detect a minute crack using dye penetrant inspection usually requires A-that the developer be applied to a flat surface. B-a longer-than-normal penetrating time. C-the surface to be highly polished.

Answer 45

B The amount of penetrant that can enter a small crack is determined by both the length of time the penetrant is allowed to remain on the surface and the temperature of the part. When looking for very small cracks, the part can be heated {but not enough to cause the penetrant to evaporate from the surface), and the penetrant can be allowed to stay on the surface for a longer than normal time before it is washed off. (AM.I.E.K6)- FAA-H-8083-30

Question 46

8233-1 Which of the following is a main determinant of the dwell time to use when conducting a dye or fluorescent penetrant inspection? A- The size and shape of the discontinuities being looked for. B- The size and shape of the part being inspected. C- The type and/or density of the part material.

Answer 46

A The dwell time (the time the penetrant is allowed to remain on the surface) is determined by the size and shape of the discontinuity being looked for. (AM.I.E.K6) - FAAH - 8083-30

Question 47

8234 When checking an item with the magnetic particle inspection method, circular and longitudinal magnetization should be used to A-reveal all possible defects. B-evenly magnetize the entire part. C-ensure uniform current flow.

Answer 47

A Since longitudinal magnetization detects faults that lie across a part, and circular magnetization detects faults that lie parallel to its length, a complete inspection that will show up all possible defects requires that the part be magnetized twice, longitudinally and circularly, and given two separate inspections. (AM.I.E.K6)- FAA-H-8083-30

Question 48

8235 In magnetic particle inspection, a flaw that is perpendicular to the magnetic field flux lines generally causes: A-a large disruption in the magnetic field. B-a minimadl isruptionin the magneticfi eld. C-no disruption in the magnetic field.

Answer 48

A In order to locate a defect in a part by the magnetic particle inspection method, it is essential that the magnetic lines of force pass approximately perpendicular to the defect. This causes the maximum disruption of the magnetic field and forms magnetic poles which attract the indicating medium across the defect. (AM.I.E.K6) - FAA-H-8083-30

Question 49

8236 If dye penetrant inspection indications are not sharp and clear, the most probable cause is that the part A-was not correctly degaussed before the developer was applied. B-has no appreciable damage. C-was not thoroughly washed before the developer was applied.

Answer 49

C After the penetrant has been on the surface of a part for the correct dwell time, the surface must be thoroughly washed to remove all traces of the penetrant. When the surface is clean and dry, the developer is sprayed or dusted on. Any penetrant left on the surface or in the pores of the material will stain the developer and faults will not show up as sharp and clear marks. (AM.I.E.K6)- FAA-H-8083-30

Question 50

8239 A part which is being prepared for dye penetrant inspection should be cleaned with: A-a volatile petroleum-base solvent: B-the penetrant developer. C-water-base solvents only.

Answer 50

A It is important when performing a dye penetrant inspection that the surface of the part be as clean as possible. Volatile petroleum-based solvents such as Stoddard solvent and naphtha are widely used for cleaning parts to be inspected. (AM.I.E.K6)-AC 43.13-1B

Question 51

8240 Under magnetic particle inspection, a part will be identified as having a fatigue crack under which condition? A- The discontinuity pattern is straight. B-The discontinuity is found in a nonstressed area of the part. C- The discontinuity is found in a highly stressed area of the part.

Answer 51

C Fatigue cracks usually show up in areas that have been subjected to high concentrations of stresses. They are likely to form where the cross-sectional area of the part changes sharply. (AM.I.E.K6) - FAA-H-8083-30

Question 52

8241 In performing a dye penetrant inspection, the developer A-seeps into a surface crack to indicate the presence of a defect. B-acts as a blotter to produce a visible indication. C-thoroughly cleans the surface prior to inspection.

Answer 52

B To perform a dye penetrant inspection, the part to be inspected is thoroughly cleaned and soaked in a liquid penetrant which seeps into any cracks or defects that extend to the surface. After the part is soaked for the required dwell time, the penetrant is washed from the surface, and the surface is covered with a developer which, acting as a blotter, pulls the penetrant from the fault. The penetrant pulled out by the developer shows up as a visible indication. (AM.I.E.K6) - FAA-H-8083-30

Question 53

8289 Which tool can be used to measure the alignment of a rotor shaft or the plane of rotation of a disc? A-Dial indicator. B-Shaft gauge. C-Protractor.

Answer 53

A A dial indicator is used to measure the alignment of a rotor shaft. The dial indicator is clamped to the structure, the contact finger is placed against the surface of the shaft, and the indicator is zeroed. The shaft is rotated and the dial indicator measures the amount the shaft is out of alignment. The plane of rotation of a disc may also be measured with a dial indicator. (AM.I.E.K6) - FAAH - 8083-30

Question 54

8295 Which tool is used to find the center of a shaft or other cylindrical work? A-Combination set. B-Dial indicator. C-Micrometer caliper.

Answer 54

A The center of a shaft or other circle can be found with the center head of a combination set. A combination set consists of a steel scale that has three heads that can be moved to any position on the scale and locked in place. The three heads are a stock head that measures go0 and 45° angles, a protractor head that can measure any angle between the head and the blade, and the center head that uses one side of the blade as the bisector of a go0 angle. The center head is placed against the circumference of the circle and a diameter is drawn along the edge of the blade. The head is moved about a quarter of the way around the circle and another diameter is drawn. The two diameters cross in the center of the circle. (AM.I.E.K6) - FAA-H-8083-30

Question 55

8256 Torque values for aircraft bolts normally consider A-the threads to be clean and dry. 8-tightening the bolt head. C-lubricating the threads.

Answer 55

A The amount of torque used to screw a nut onto a bolt is critical in determining the integrity of a bolted joint. For torque to be uniform and to allow the torque specified by the manufacturer to be duplicated in the field, the following rule applies: Unless it is specified otherwise, the values given in a torque chart relate to clean, dry threads. (AM.I.E.KB)- FAA-H-8083-30

Question 56

8264 Which statement regarding aircraft bolts is correct? A-When tightening castellated nuts on drilled bolts, if the cotter pin holes do not line up, it is permissible to overtighten the nut to permit alignment of the next slot with the cotter pin hole. B-ln general, bolt grip lengths should equal the material thickness. C-Alloy steel bolts smaller than 1/4-inch diameter should not be used in primary structure.

Answer 56

B Bolts for installation in an aircraft structure should be selected so that their grip length (the length of the unthreaded shank) is equal to the thickness of the material being joined. (AM.I.E.KB) -AC 43.13-1B

Question 57

8266 When the specific torque value for nuts is not given, where can the recommended torque value be found? A-AC 43.13-18. B-Technical Standard Order. C-AC 43.13-2A.

Answer 57

A A list of recommended torque values for nut-bolt combinations (without lubrication) are found in the AC 43.13-1B. (AM.I.E.KB)-AC 43.13-1B

Question 58

8546 The advantages of HI-LOK™ fasteners include A-light weight, high fatigue resistance, high strength, and inability to be over-torqued. B-light weight, high fatigue resistance, high strength, and ease of removal and reuse. C-light weight, high damage tolerance, high strength, and inability to be over-torqued.

Answer 58

A The advantages of HI-LO~™ two-piece fastener include its light weight, high fatigue resistance, high strength, and its inability to be over-torqued. (AM.I.E.KB)-FAAH - 8083-30

Question 59

8221-1 Which of the following defects are not acceptable for metal lines? A-Scratches or nicks on the inside of a bend less than 10% of wall thickness. B-Dents in straight section that are 10% of tube diameter. C-Dents in straight section that are 20% of tube diameter.

Answer 59

C Scratches or nicks less than 10% of the wall thickness of the tube are repairable if they are not in the heel of the bend, as are dents that are 10% of tube diameter. A dent of more than 20% of the tube diameter is not acceptable. (AM.I.E.K9)-AC 43.13-1

Question 60

8265 Generally speaking, bolt grip lengths should be A-equal to the thickness of the material which is fastened together, plus approximately one diameter. B-equal to the thickness of the material which is fastened together. C-one and one half times the thickness of the material which is fastened together.

Answer 60

B Bolts for installation in an aircraft structure should be selected so that their grip length (the length of the unthreaded shank) is equal to the thickness of the material being joined. (AM.I.E.K9) -AC 43.13-1 B

Question 61

8261 The Society of Automotive Engineers (SAE) and the American Iron and Steel Institute use a numerical index system to identify the composition of various steels. In the number"4130" designating chromium molybdenum steel, the first digit indicates the: A-percentage of the basic element in the alloy. B-percentage of carbon in the alloy in hundredths of a percent. C-basic alloying element.

Answer 61

C In the SAE four-digit numbering system for identifying the composition of steel, the first two digits identify the basic alloy, and the second two digits show the percentage of carbon in hundredths of a percent. (AM.I.E.K11) - FAAH - 8083-30

Question 62

8262. (Refer to Figure 42.) Which of the bolthead code markings shown identifies an AN corrosion resistant steel bolt? A-1. B-2. C-3.

Answer 62

C The single dash on the head of a bolt identifies it as a standard bolt made of corrosion-resistant steel. The cross on the head of a bolt identifies it as a standard AN bolt made of nickel alloy steel. The cross inside a triangle identifies the bolt as an NAS close-tolerance bolt. (AM.I.E.K11-)A C 43.13-1B

Question 63

8263 Aircraft bolts with a cross or asterisk marked on the bolt head are A-made of aluminum alloy. B-close tolerance bolts. C-standard steel bolts.

Answer 63

C A cross or asterisk on the head of a bolt identifies it as a standard AN bolt made of nickel alloy steel. (AM.I.E.K11) - FAA-H-8083-30

Question 64

8269 A bolt with a single raised dash on the head is classified as an A-AN corrosion-resistant steel bolt. B-NAS standard aircraft bolt. C-NAS close tolerance bolt.

Answer 64

A An AN corrosion-resistant steel bolt is identified by a single raised dash on its head. (AM.I.E.K11)- FAA-H-8083-30

Question 65

8272 A bolt with an X inside a triangle on the head is classified as an A-NAS standard aircraft bolt. B-NAS close tolerance bolt. C-AN corrosion-resistant steel bolt.

Answer 65

B An NAS close-tolerance bolt has a cross or an X inside a triangle on its head. An NAS or an AN standard aircraft bolt has a raised cross or asterisk on its head. An AN corrosion-resistant steel bolt has a single raised dash on its head. (AM.I .E.K 11)- AC 43.13-1B

Question 66

8276 In the four-digit aluminum index system number 2024, the first digit indicates: A-the major alloying element. B-the number of major alloying elements used in the metal. C-the percent of alloying metal added.

Answer 66

A In the four-digit numbering system for identifying aluminum alloys, the first digit shows the major alloy used with the aluminum. The 1000 series is commercially pure aluminum. The 2000 series has copper as the main alloy. The 3000 series has manganese as the main alloy. The 4000 series has silicon as the main alloy. The 5000 series has magnesium as the main alloy. The 6000 series has magnesium and silicon in it. The 7000 series has zinc as the main alloy. (AM.I.E.K11)-FAA-H-8083-30

Question 67

8283 Select a characteristic of a good gas weld. A- The depth of penetration shall be sufficient to ensure fusion of the filler rod. B- The height of the weld bead should be 1/8 inch above the base metal. C- The weld should taper off smoothly into the base metal

Answer 67

C The bead of a gas weld that has good penetration and good fusion is uniform and straight. It has a slightly crowned surface that tapers off smoothly into the base metal. (AM.I.E.K12-) FAA-H-8083-30

Question 68

8284 One characteristic of a good weld is that no oxide should be formed on the base metal at a distance from the weld of more than A-1/2 inch. B-1 inch. C-1/4 inch.

Answer 68

A When making a good weld, the heat should be concentrated in the area being welded. The oxides that form on the base metal give an indication of the amount of heat put into the metal. Oxides formed for a distance of much more than 1/2 inch from the weld show that too much heat was put into the metal. The metal may have been weakened. (AM.I.E.K12)-AC 43.13-1B

Question 69

8278 (Refer to Figure 44.) Identify the weld caused by an excessive amount of acetylene. A-4. B-1. C-3.

Answer 69

C The weld in view 3 has been made with a flame that had an excess of acetylene. There are bumps along the center of the bead and craters at the edge of the weld. Cross checks are apparent where the body of the weld is sound. If this weld were cross-sectioned, it would show pockets and porosity. The weld in view 1 was made too rapidly. The long and pointed appearance of the ripples was caused by an excessive amount of heat or by an oxidizing flame. If this weld were cross-sectioned, it would probably show gas pockets, porosity, and slag inclusions. The weld in view 2 has improper penetration and cold laps caused by insufficient heat. It appears rough and irregular and its edges are not feathered in to the base metal. The weld in view 4 has considerable variations in depth of penetration. It often has the appearance of a cold weld. {AM.I.E.K13)- FAA-H-8083-30

Question 70

8279 (Refer to Figure 44.) Select the illustration which depicts a cold weld. A-3. B-2. C-4.

Answer 70

B The weld in view 2 is a cold weld. It has improper penetration and cold laps caused by insufficient heat. It appears rough and irregular and its edges are not feathered into the base metal. (AM.I.E.K13) - FAA-H-8083-30