Tap testing a sandwich panel construction.

is crude, but works remarkably well

is not an approved method of testing.

will not give very reliable results.

Aircraft transparent plastics are cleaned using.

warm soapy water, rinsed and dried.

A thermosetting adhesive.

undergoes a chemical transformation and creates an insoluble substance

Metal fasteners used with carbon/graphite composite structures.

must be made of materials such as titanium or corrosion resistant steel.

must be made of high strength aluminium alloy.

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

Which methods can be used to inspect fibreglass/honeycomb structures for entrapped water?.

Acoustic emission and back-lighting

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

the grain is perpendicular to the skin.

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

the grain is parallel to the skin.

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

100 times the thickness of the metal

whatever is desired for a neat clean appearance.

two times the thickness of the metal.

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

have mixed enough for a test sample.

test the viscosity of the resin immediately after mixing.

perform a chemical composition analysis

Composite inspections by means of acoustic emissions monitoring.

create sonogram pictures of the areas being inspected.

analyse ultrasonic signals transmitted into the parts being inspected.

pick up the 'noise' of corrosion or other deterioration taking place

Which of the following are advantages of using microballoons in repairs to laminate honeycomb sandwich panels?.

Less density, lower stress concentrations.

Greater concentrations of resin in edges and corners, improved strength to weight ratio, less density, lower stress concentrations.

Improved strength to weight ratio, less density, lower stress.

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

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

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

use dye-penetrant inspection procedures, exposing the entire damaged area to the penetrant

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

an area of too much matrix between the fibres.

less than full strength curing of the matrix.

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

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

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

a piece of resin-impregnated glass fabric facing.

The strength and stiffness of a properly constructed composite lay-up depends primarily on.

the orientation of the plies to the load direction.

the ability of the fibres to transfer stress to the matrix.

a 60% matrix to 40% fibre ratio.

Fibreglass damage that extends completely through a laminated sandwich structure.

may be filled with resin to eliminate dangerous stress concentrations.

may be filled with putty which is compatible with the resin

Fibreglass laminate damage that extends completely through one facing and into the core.

requires replacement of the damaged core and facing.

can be repaired by using a typical facing patch.

Which of the following, when added to wet resins, provide strength for the repair of damaged fastener holes in composite panels?.

Cotton flock and chopped fibres.

microballoons, cotton flock and chopped fibres.

Microballoons and chopped fibres.

What is an open assembly time?.

The time between the adhesive being applied to the joint surfaces and their assembly.

The time elapsing between the application of the adhesive and the assembly of the joint components.

The time elapsed from the adhesive being applied to the joint surfaces to them being clamped

The basic structure of an aircraft made of wood can be.

non-monocoque, monocoque, semi-monocoque.

When a full inspection for corosion is to be carried out on a wooden aircraft you would.

Remove all the fabric/cloth prior to inspection.

Bring the aircraft into the hangar for 2 to 3 days prior to the inspection.

Jack and trestle the aircraft to the rigging position.

How is the moisture content within the wood of a wood aircraft structure determined?.

By inserting the probe of a moisture meter.

By measuring the size of the water stains at joints.

By weighing the wood structure before and after drying it.

Except where specified by the manufacturer, a wooden spar may be spliced.

at any point except under the wing attachment fittings.

Replacement of a wooden spar is.

only permitted by the manufacturer.

A crack is found in a wooden spar, you.

might be able to repair the spar.

Wood sealants used on wooden aircraft structures are for.

helping to prevent wood cracking.

improving aerodynamic efficiency.

reducing the requirement for sanding

An aircraft wooden structure must be surface finished and sealed.

on both the outer and inner surfaces.

Hard knots in wood are acceptable.

up to 3/8 inch diameter in any location.

Wood with checks, shakes or splits.

can be used providing the damage is repaired by gluing and clamping.

can be used for certain secondary structure.

Quiz

Materiales hadware 2

oriol arrufat 200 questions

Take the quiz

Questions in this quiz (200)

1 What is the separation of an aramid panel layers described as?.
1. ADelamination.
2. BDebonding.
3. CDetachment.
2Tap testing a sandwich panel construction.
1. Ais not an approved method of testing.
2. Bwill not give very reliable results.
3. Cis crude, but works remarkably well
3Which product is a serious health hazard when handling?.
1. ACeramic.
2. BAsbestos.
3. CGlass fibre.
4Aircraft transparent plastics are cleaned using.
1. Awarm soapy water, rinsed and dried.
2. Bparaffin and soft cotton pad.
3. Cclean dry soft leather.
5A thermosetting adhesive.
1. Awill be resistant to heat.
2. Bcan be re-formed when hot.
3. Cundergoes a chemical transformation and creates an insoluble substance
6Metal fasteners used with carbon/graphite composite structures.
1. Amust be made of materials such as titanium or corrosion resistant steel.
2. Bmust be made of high strength aluminium alloy.
3. Cmay be made of any of the metals commonly used in aircraft fasteners.
7Which methods can be used to inspect fibreglass/honeycomb structures for entrapped water?.
1. AAcoustic emission and X-ray.
2. BX-ray and back-lighting.
3. CAcoustic emission and back-lighting
8When balsa wood is used to replace a damaged honeycomb core, the plug should be cut so that.
1. Ait is about 1/8 inch undersize to allow sufficient bonding material to be applied.
2. Bthe grain is parallel to the skin.
3. Cthe grain is perpendicular to the skin.
9When repairing puncture-type damage of a metal faced laminated honeycomb panel, the edges of the doubler should be tapered to.
1. Awhatever is desired for a neat clean appearance.
2. Btwo times the thickness of the metal.
3. C100 times the thickness of the metal
10One of the best ways to assure that a properly prepared batch of matrix resin has been achieved is to.
1. Atest the viscosity of the resin immediately after mixing.
2. Bhave mixed enough for a test sample.
3. Cperform a chemical composition analysis

11Composite inspections by means of acoustic emissions monitoring.
1. Aanalyse ultrasonic signals transmitted into the parts being inspected.
2. Bcreate sonogram pictures of the areas being inspected.
3. Cpick up the 'noise' of corrosion or other deterioration taking place
12Which of the following are advantages of using microballoons in repairs to laminate honeycomb sandwich panels?.
1. AGreater concentrations of resin in edges and corners, improved strength to weight ratio, less density, lower stress concentrations.
2. BLess density, lower stress concentrations.
3. CImproved strength to weight ratio, less density, lower stress.
13The length and time that a catalyzed resin will remain in a workable state is called the.
1. Ashelf life.
2. Bservice life.
3. Cpot life.
14One method of inspecting a laminated fibreglass structure that has been subjected to damage is.
1. Astrip the damaged area of all paint and shine a strong light through the structure.
2. Buse an eddy current probe on both sides of the damaged area.
3. Cuse dye-penetrant inspection procedures, exposing the entire damaged area to the penetrant
15When inspecting a composite panel using the ring test/tapping method, a dull thud may indicate.
1. Aan area of too much matrix between the fibres.
2. Bless than full strength curing of the matrix.
3. Cseparation of the laminates
16Superficial scars, scratches, surface abrasion, or rain erosion on fibreglass laminates can generally be repaired by applying.
1. Aone or more coats of suitable resin (room-temperature catalyzed) to the surface.
2. Ba sheet of polyethylene over the abraded surface and one or more coats of resin cured with infrared heat lamps.
3. Ca piece of resin-impregnated glass fabric facing.
17A potted compound repair on honeycomb can usually be made on damages less than.
1. A4 inches in diameter.
2. B2 inches in diameter.
3. C1 inch in diameter.
18What reference tool is used to determine how the fibre is to be oriented for a particular ply or fabric?.
1. ABias clock.
2. BWeft clock.
3. CWarp clock
19The strength and stiffness of a properly constructed composite lay-up depends primarily on.
1. Athe ability of the fibres to transfer stress to the matrix.
2. Ba 60% matrix to 40% fibre ratio.
3. Cthe orientation of the plies to the load direction.
20Which fibre to resin (%) ratio for advanced composite wet lay-ups is generally considered the best?.
1. A60:40.
2. B50:50.
3. C40:60.
21What is the material layer used within the vacuum bag pressure system to absorb excess resin during curing called?.
1. ABreather.
2. BBleeder.
3. CRelease.
22When necessary, what type of cutting fluid is usually acceptable for machining composite laminates?.
1. AWater soluble oil.
2. BWater only.
3. CWater displacing oil.
23Fibreglass damage that extends completely through a laminated sandwich structure.
1. Amay be filled with resin to eliminate dangerous stress concentrations.
2. Bmust be repaired.
3. Cmay be filled with putty which is compatible with the resin
24 Fibreglass laminate damage that extends completely through one facing and into the core.
1. Acan be repaired by using a typical facing patch.
2. Brequires replacement of the damaged core and facing.
3. Ccannot be repaired.
25Which of the following, when added to wet resins, provide strength for the repair of damaged fastener holes in composite panels?.
1. Amicroballoons, cotton flock and chopped fibres.
2. BCotton flock and chopped fibres.
3. CMicroballoons and chopped fibres.
26The part of a replacement honeycomb core that must line up with the adjacent original is the.
1. Acell edge.
2. Bcell side.
3. Cribbon direction.
27With what would you check the bonded joints of a wooden aircraft structure?.
1. AA feeler gauge.
2. BA plastic strip.
3. CA screwdriver.
28What is an open assembly time?.
1. AThe time elapsing between the application of the adhesive and the assembly of the joint components.
2. BThe time between the adhesive being applied to the joint surfaces and their assembly.
3. CThe time elapsed from the adhesive being applied to the joint surfaces to them being clamped
29The defects not allowed at all on wooden structures are.
1. Amineral streaks.
2. Bpitch pockets.
3. Cchecks, shakes and splits.
30The basic structure of an aircraft made of wood can be.
1. Amonocoque.
2. Bnon-monocoque.
3. Cnon-monocoque, monocoque, semi-monocoque.
31When a full inspection for corosion is to be carried out on a wooden aircraft you would.
1. ABring the aircraft into the hangar for 2 to 3 days prior to the inspection.
2. BJack and trestle the aircraft to the rigging position.
3. CRemove all the fabric/cloth prior to inspection.
32For fungus to cause wood decay in a wood structure, the moisture content in the wood must be at least.
1. A20%.
2. B85%.
3. C5%.
33The normal moisture content in the wood of a wooden aircraft structure is.
1. A10-12%.
2. B20-30%.
3. C0-2%.
34How is the moisture content within the wood of a wood aircraft structure determined?.
1. ABy inserting the probe of a moisture meter.
2. BBy measuring the size of the water stains at joints.
3. CBy weighing the wood structure before and after drying it.
35Except where specified by the manufacturer, a wooden spar may be spliced.
1. Aat no point.
2. Bat any point except under the wing attachment fittings.
3. Cat any point.
36Replacement of a wooden spar is.
1. Aonly permitted by the manufacturer.
2. Ba minor repair.
3. Ca major repair
37A crack is found in a wooden spar, you.
1. Amust replace the spar section.
2. Bmight be able to repair the spar.
3. Cmust replace the entire spar
38Wood sealants used on wooden aircraft structures are for.
1. Ahelping to prevent wood cracking.
2. Bimproving aerodynamic efficiency.
3. Creducing the requirement for sanding
39To determine whether an aircraft wooden structure surface is compound curvature, you would use.
1. Aa curvature gauge.
2. Ba sheet of paper.
3. Ca trammel.
40To assist the bending of plywood, a heated bending former must be heated to a temperature of.
1. A300 °C.
2. B150 °C.
3. C100 °C.
41A splayed patch repair may be used on plywood damage which does not exceed.
1. A20 times the skin thickness.
2. B15 times the skin thickness.
3. C10 times the skin thickness
42A surface patch to a plywood structure may be a large as.
1. A50 sq.inch area.
2. B50 inch perimeter.
3. C50 inch diameter.
43The steepest slope permitted on the scarf of a scarfed plywood repair is.
1. A1 in 20.
2. B1 in 4.
3. C1 in 12.
44The maximum size damage to plywood skin that may be repaired with a fabric patch is.
1. A3.0 inch diameter.
2. B0.5 inch diameter.
3. C1.0 inch diameter.
45The doubler used to support a scarfed patch plywood repair should be made from plywood of a minimum.
1. A1/4 inch thick.
2. B1/8 inch thick.
3. C3/8 inch thick.
46An aircraft wooden structure must be surface finished and sealed.
1. Aon both the outer and inner surfaces.
2. Bon the inner surfaces only.
3. Con the outer surfaces only
47Pine wood has a strength, compared to that of spruce.
1. Aless than.
2. Bexceeding.
3. Cthe same as.
48The standard wood type for aircraft wood structures is.
1. Aspruce.
2. Bdouglas fir.
3. Cpine
49Hard knots in wood are acceptable.
1. Ain certain locations.
2. Bnever.
3. Cup to 3/8 inch diameter in any location.
50A 'shake' in a piece of wood is a crack.
1. Aacross annual rings.
2. Binduced by artificial stress.
3. Cbetween two annual rings.
51Wood with checks, shakes or splits.
1. Acan be used providing the damage is repaired by gluing and clamping.
2. Bcan be used for certain secondary structure.
3. Cmust be rejected.
52Compression wood.
1. Ais a hard-wood.
2. Bshould be rejected.
3. Cis preferred because of its superior strength qualities.
53Red heart and purple heart.
1. Aare types of hard-wood.
2. Bare forms of decay in wood.
3. Care harmless natural defects in wood
54The greatest amount of shrinkage in wood is in which direction?.
1. ATangential.
2. BRadial.
3. CThe shrinkage is equal in tangential and radial directions
55 Shrinkage of wood is.
1. Aequal along and across the fibres.
2. Bleast along the fibres.
3. Cleast across the fibres
56Shrinkage of wood is.
1. Agreatest in the longitudinal direction.
2. Bnegligible in the longitudinal direction.
3. Cnegligible in the radial direction.
57The maximum permissible grain deviation in wood is.
1. A1:8.
2. B1:20.
3. C1:15.
58Nails used on wood structures should be.
1. A50 mm apart.
2. B12 mm apart.
3. C25 mm apart.
59Small (up-to 3/8 inch diameter) hard-knots are allowed in a wooden spar.
1. Ain the middle 1/3 portion.
2. Bnowhere.
3. Cin the outer 1/3 portions.
60If metal fasteners are removed from an aircraft's wood structure, and are found to have corrosion on them, this can indicate.
1. Aacidity of the adjoining wood structure.
2. Bdeterioration of the fastener.
3. Cdecay of the adjoining wood structure.
61Bolt holes through wooden structures should be.
1. Asealed, and the sealant allowed to dry before fitting the bolt.
2. Bleft unsealed and unvarnished inside the hole.
3. Csealed with varnish and wet-assembled with the bolt before the varnish has dried.
62Wood end-grain.
1. Ahas the same susceptibility to moisture ingress as the side of the grain.
2. Bis less susceptible to moisture ingress as the side of the grain.
3. Cis more susceptible to moisture ingress as the side of the grain
63 In cases of elongated boltholes in a wood spar or cracks in the vicinity of the boltholes.
1. Ait is permissible to ream the hole, plug with hardwood and re-drill.
2. Ba new section of spar should be spliced in or the spar entirely replaced.
3. Cthe spar may be reinforced by using hardwood reinforcing plates.
64A faint line running across the grain of a wood spar generally indicates.
1. Ashear failure.
2. Bdecay.
3. Ccompression failure.
65The I-beam wooden spar is routed to.
1. Aobtain uniform strength.
2. Bdecrease weight.
3. Cincrease strength.
66Pin knot clusters are permitted in wood aircraft structure provided.
1. Athey have no mineral streaks.
2. Bno pitch pockets are within 12 inches.
3. Cthey produce a small effect of grain direction.
67Compression failures in wood aircraft structures are characterised by buckling of the fibres that appear as streaks on the surface.
1. Aparallel to the grain.
2. Bat right-angles to the growth rings.
3. Cat right angles to the grain.
68Fabrics may be fitted to airframe structures by.
1. Aalways riveting.
2. Bwood nails.
3. Ctying on with string
69Aircraft fabric covering is made from.
1. Asilk.
2. Bpolyester.
3. Cnylon
70At manufacture, aircraft fabric is.
1. Ashrunk.
2. Bdoped.
3. Cstretched.
71Recovering or repairing of an aircraft with a fabric other than the original fabric type is.
1. Aa major modification and requires approval.
2. Bprohibited.
3. Ca minor modification, providing the fabric is the same strength as the original.
72Reinforcing tape used on aircraft fabric covering must have a minimum strength of.
1. A80 lb.
2. B40 lb.
3. C120 lb
73Lacing cord used on aircraft fabric covering must have a minimum breaking strength of.
1. A120 lb.
2. B80 lb.
3. C40 lb.
74Fabric seams are preferable.
1. Aparallel to the line of flight.
2. Bspanwise to the line of flight.
3. Coblique to the line of flight.
75Single stitched machine sewn seams are permissible.
1. Aat all locations on the aircraft.
2. Bnever.
3. Conly when positioned over a structure.
76The minimum pitch of hand-sewn stitch is.
1. A1/4 inch.
2. Bequal to 10 times the thread thickness.
3. C4 inches
77Hand sewn stitch must be locked at a minimum of.
1. Athe end of the stitch only.
2. B20 stitch intervals.
3. C10 stitch intervals.
78Fabric to be hand sewn must be doubled under at the edge to a minimum distance of.
1. A1/2 inch.
2. B3/8 inch.
3. C1/4 inch.
79Holes are cut in fabric for inspection panels, spar fittings, drain grommets etc.
1. Aafter doping.
2. Bbefore doping.
3. Cbefore attaching the fabric to the structure.
80Aircraft fabric lacing cord is reinforced with.
1. Aepoxy.
2. Bwax.
3. Clanolin.
81The dope applied to an aircraft's fabric covering causes shrinkage.
1. Aon the last coat only.
2. Bon the first coat only.
3. Con all coats.
82The two preferred types of dope used on aircraft fabric covering is.
1. Acellulose and polyester.
2. Bcellulose and butyrate.
3. Cnitrate and butyrate.
83Aircraft dope, during storage in adverse conditions in a store-room, will become.
1. Aacidic.
2. Bdiscoloured.
3. Calkaline.
84What type of dope is preferred for use on natural fiber aircraft covering?.
1. ANitrate.
2. BAny type of dope is suitable.
3. CButyrate.
85Which of the following is true regarding aircraft dope type?.
1. ANitrate dope may be applied over the top of butyrate dope.
2. BButyrate dope may be applied over the top of nitrate dope.
3. CEither type of dope may be applied over the top of any type of dope
86What type of shoes should be worn by the technician applying a dope finish to a fabric covered aircraft?.
1. ARubber soled.
2. BLeather soled.
3. CPlastic uppers
87What are the limits of the environmental conditions for applying dope to a fabric covered aircraft?.
1. ARelative humidity 50 - 70%, temperature range 40 ° to 60 °F.
2. BRelative humidity 50 - 75%, temperature range 65 ° to 75 °F.
3. CRelative humidity 20 - 60%, temperature range 65 ° to 75 °F
88Applying dope to a fabric covered aircraft should be done by.
1. Aspraying all coats to avoid brush marks.
2. Bspray all coats except the first three.
3. Cbrushing all coats to ensure it is absorbed into the fabric.
89Regarding the thinning of aircraft dope.
1. Aunderthinning is preferred to overthinning.
2. Bdope should be thinned with automotive thinners.
3. Coverthinning is preferred to underthinning.
90A retarder is added to aircraft dope to.
1. Ato extend the shelf life.
2. Bproduce a smoother finish.
3. Cto retard the application time
91Doped fabric.
1. Ais not to be treated after application.
2. Bis treated with varnish.
3. Cis treated with wax compound.
92Dope should be applied to an aircraft's fabric coating in a relative humidity not exceeding.
1. A50%.
2. B85%.
3. C65%.
93Dressing out' of a fabric covering refers to.
1. Athe trimming of excess fabric after fitting.
2. Bapplying finishing tapes, reinforcing patches, inspection ports etc.
3. Claying the fabric out on the floor and cutting it to size prior to fitting to the aircraf
94Coats of clear dope are applied to an aircraft's fabric.
1. Abefore coats of aluminium pigmented dope are applied.
2. Bbefore or after coats of aluminium pigmented dope are applied, it does not matter.
3. Cafter coats of aluminium pigmented dope are applied.
95What is the reason for using aluminium-pigmented dope on a fabric covered aircraft?.
1. ATo provide an aluminium colour to the aircraft.
2. BTo block UV radiation.
3. CTo provide strength.
96Aircraft sheet plywood skins are.
1. Asealed and varnished or painted.
2. Bsealed and doped.
3. Ccovered in fabric.
97Blushing' of a doped fabric surface is an indication of.
1. Amoisture enterring into the wood/fabric structure during service.
2. Bmoisture condensing on the surface during drying of the dope.
3. Coil contamination of the doped fabric.
98Orange peeling of a doped surface may be caused by.
1. Adope viscosity too low.
2. Bdope viscosity too high.
3. Cair temperature too low.
99Orange peeling of a doped surface may be caused by.
1. AOrange peeling of a doped surface may be caused by.
2. Bair temperature too low.
3. Cspray gun pressure too low
100Butyrate dope burns.
1. Aslower than nitrate dope.
2. Bfaster than nitrate dope.
3. Cthe same rate as nitrate dope.
101Fabric coated with nitrate dope can be differentiated from fabric coated in butyrate dope by.
1. Acarrying out a burn test.
2. Bsmelling the fabric.
3. Cobserving the colour.
102Where 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.
1. Abe extended 3 inches past the structural member.
2. Bbe extended to meet the structural member.
3. Cbe designated a major repair.
103What width of finishing tape should be used on a tear in a fabric cover which is 10 inches long?.
1. A2 inches.
2. B6 inches.
3. C4 inches
104What width of finishing tape should be used on a tear in a fabric cover which is 20 inches long?.
1. A6 inches.
2. B2 inches.
3. C4 inches
105Lines of stitching of a fabric repair is locked at the end with.
1. Aa hitch knot.
2. Ba half hitch knot.
3. Ca double half hitch knot
106Wrinkles in a fabric covering of a wood/fabric aircraft are.
1. Anot permitted.
2. Ba minor aerodynamic detriment.
3. Cpermitted only if they are temporary due to damp/wet weather conditions
107The threads per inch of Grade 'A' aircraft fabric is.
1. A60-64.
2. B80-84.
3. C110-115.
108When and how is finishing tape applied on fabric covered aircraft?.
1. ADoped on immediately prior to the finish coat.
2. BSewed or laced on before dope is applied.
3. CDoped on after the first or second coat of dope
109The determining factor in the selection of the correct weight of textile fabric to be used in covering any type of aircraft is the.
1. Amaximum wing loading.
2. Bspeed of the aircraft.
3. Cspeed of the aircraft and the maximum wing loading
110How many fabric thicknesses will be found in a French-fell seam?.
1. AFive.
2. BThree.
3. CFour
111Finishing tape (surface tape) is used for what purpose?.
1. ATo prevent 'ripple formation' in covering fabric.
2. BTo provide additional wear resistance over the edges of fabric forming structures.
3. CTo provide additional anti-tear resistance under reinforcement tape.
112Moisture, mildew, chemicals and acids have no effect on.
1. Aglass fabric.
2. Blinen fabric.
3. CDacron fabric
113The strength classification of fabric used in aircraft covering is based upon.
1. Abearing strength.
2. Bshear strength.
3. Ctensile strength.
114When 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.
1. A56 pounds per inch warp and weft.
2. B70% of its original strength.
3. C70% of the original strength for intermediate fabric.
115What is used to slow the drying time of some dope finishes to prevent blush?.
1. ARejuvenator.
2. BReducer.
3. CRetarder.
116Aluminium-pigment in dope is used primarily to.
1. Aexclude sunlight from the fabric.
2. Bprovide a silver colour.
3. Caid in sealing out moisture from the fabric
117From the following list of metals, which is most cathodic?.
1. ANickel.
2. BMagnesium.
3. CStainless steel.
118Intergrannular corrosion is caused by.
1. Aimproperly assembled components.
2. Bimproper heat treatment.
3. Cdissimilar metal contact
119Corrosion caused by electrolytic action is the result of.
1. Acontact between two unlike metals.
2. Bexcessive anodization.
3. Cthe wrong quenching agent.
120Corrosion may be regarded as the destruction of metal by.
1. Aelectrochemical action.
2. Bhydroelectric action.
3. Celectromechanical action.
121Exfoliation corrosion is sometimes referred to as.
1. Alayer corrosion.
2. Bfiliform corrosion.
3. Csub-surface corrosion.
122When dissimilar metals are brought together, or the same metal in different states, one metal forms the anode and the other the cathode. Which will suffer from corrosion?.
1. ABoth will corrode equally.
2. BThe cathode.
3. CThe anode
123In corrosion, the electrode that loses electrons is.
1. Athe cathode.
2. Beither the cathode or the anode depending upon the electrolyte.
3. Cthe anode
124Which of these is a common cause of corrosion?.
1. AWater in fuel.
2. BSpilled battery acid.
3. CUntreated
125What is stress corrosion?.
1. ACorrosion in an area under cyclic loading.
2. BCorrosion due to fretting.
3. CCorrosion in an area under continuous loading.
126Electrochemical reaction is caused by the contact of.
1. Abonding.
2. Bmoisture on the surface of the metal.
3. Cdissimilar metals.
127Chemical attack is a direct result of.
1. Aintergranular corrosion.
2. Bcathodic & anodic changes in the material.
3. Cfiliform corrosion
128Galvanic corrosion is caused by.
1. Aincorrect heat treatments or incorrect alloying.
2. Bcyclic stressing and a decrease in cross sectional area.
3. Cthe joining of 2 dissimilar metals.
129In the galvanic series, the most noble metal will, if joined to another metal.
1. Aalways be at the top of the table.
2. Bcorrode before the less noble metal.
3. Callow the less noble metal to corrode first
130Stress corrosion is associated with.
1. Acyclic loading and a corrosion pit.
2. Ba corrosion pit in a member under a compressive load.
3. Ca corrosion pit in a member under stress
131Corrosion will spread more rapidly when metals are exposed to.
1. Acold climates.
2. Bhigh temperatures.
3. Cdry climates.
132Some metals are inherently stable. What does this suggest?.
1. AThey strongly resist corrosion.
2. BThey are highly prone to corrosion.
3. CThey try to revert to their natural state.
133The oxide film formed on the surface of aluminium is.
1. Anon-porous.
2. Bporous.
3. Chard and porous.
134Corrosion control begins at the.
1. Aproduction stage.
2. Bmanufacturing stage.
3. Cdesign stage
135Aluminium is.
1. Anot resistant to corrosion.
2. Bhighly resistant to corrosion.
3. Creasonably resistant to corrosion
136When galvanic corrosion takes place, which part corrodes?.
1. AAnode.
2. BOxide film coating.
3. CCathode.
137Corrosion caused by galvanic action is the result of.
1. Acontact between two unlike metals.
2. Bexcessive anodization.
3. Cexcessive etching
138What sort of corrosion would a magneto be likely to encounter if completely enclosed?.
1. ANone, providing the magneto is completely enclosed.
2. BDirect chemical attack.
3. CPitting
139What are the signs of fretting corrosion?.
1. ABlack powder or cocoa staining.
2. BIntergranular cracking.
3. CFlaking
140Black streaks back from a rivet hole signify.
1. Agalvanic corrosion.
2. Bintergrannular corrosion.
3. Cfretting.
141 When a steel part is welded, corrosion occurs because.
1. Ait is affected by spatter.
2. Bthe strip has become anodic.
3. Cpaint has been removed
142Intergranular corrosion.
1. Acan be recognized by a grey powder deposit.
2. Bmay have no visual surface indication.
3. Ccan be recognized by its flaking and lifting of the material layers
143Active flux does what?.
1. AProtects.
2. BCleans.
3. CBoth cleans and protects
144Jointing compound is used for what reason?.
1. ATo prevent dissimilar metal corrosion.
2. BTo bond the components together.
3. CTo make the components easier to disassemble
145After welding, stainless steel is susceptible to a corrosion known as.
1. Aweld deterioration.
2. Bweld decay.
3. Cweld rot.
146The lifting or flaking of the metal at the surface due to delamination of grain boundaries caused by the pressure of corrosion is.
1. Aexfoliation.
2. Belectrolysis.
3. Ctransgranulation.
147The electrolytic process that forms an oxide film on the surface of aluminium alloys is known as.
1. Agalvanizing.
2. Banodizing.
3. Celectroplating.
148What is the indication of fretting corrosion on aluminium alloy?.
1. ABlack powder.
2. BBrown powder.
3. CWhite powder.
149What action is taken to protect integral tanks from corrosion due to micro-biological growth?.
1. AThe inside of the tank is coated with yellow chromate.
2. BRubber liners are installed in the tank.
3. CA biocidal additive is used in the fuel.
150What type of corrosion attacks grain boundaries of aluminium alloys which are improperly or inadequately heat treated?.
1. AStress corrosion.
2. BIntergranular corrosion.
3. CSurface corrosion.
151The artificial production of a film of oxide on the surface of aluminium or any of its alloys is commonly called.
1. Aalodizing.
2. Bparco lubrizing.
3. Canodizing.
152Intergrannular corrosion in structural aluminium alloy parts.
1. Aare not likely to occur in parts fabricated from heat-treated sheet aluminium.
2. Bmay be detected by the white, powdery deposit formed on the surface of the metal.
3. Ccannot always be detected by surface indications
153Corrosion will spread more rapidly when metals are exposed to.
1. Adry climates.
2. Bcold climates.
3. Chigh temperatures.
154Magnesium alloy components are protected by.
1. Aan electro process.
2. Ba chemical process.
3. Ca painted process.
155If it is necessary to remove corrosion from a steel component in-situ, the base of a suitable solution for this purpose is.
1. Achromic acid.
2. Bphosphoric acid.
3. Cnitric acid.
156 A type of protection which is applicable to magnesium alloys is the.
1. Aphosphate process.
2. Bchromating process.
3. Ccoslettising process.
157 Heavy corrosion deposits on clad aluminium alloys should be removed.
1. Amechanically using a pneumatic vibrator.
2. Bchemically by use of trichloroethylene.
3. Cchemically by use of phosphoric acid
158What action should be taken on finding intergrannular corrosion?.
1. AReplace complete component part.
2. BDe-corrode and reprotect.
3. CRenew corroded area by patching
159Anodic treatment of aluminium alloy gives.
1. Aa purple finish.
2. Ba shorter life due to hardening.
3. Ca pure coating of aluminium oxide on the surface.
160Corrosion at the grain boundaries is called.
1. Aintergrannular.
2. Bfretting.
3. Cfiliform
161Fretting corrosion occurs where.
1. Atwo material are subject to very slight movement between the two.
2. Ba deep scratch increases to become fretting corrosion.
3. Cpitting corrosion is allowed to become more pronounced.
162What is used to remove corrosion from magnesium?.
1. APhosphate acid solution.
2. BChromic acid solution.
3. CSulphuric acid solution.
163Surface corrosion on stainless steel is identified by.
1. Ared rust.
2. Bwhite film.
3. Cblack pitting
164Hooks, wires and other suspension devices used in an anodic bath should be made of.
1. Abrass or copper.
2. Baluminium or titanium.
3. Csteel or copper
165What are the signs of fretting corrosion on steel?.
1. ADark staining around area.
2. BSurface cracking as corrosion breaks through to surface of component.
3. CRust on surface.
166Spilled mercury on aluminium.
1. Aincreases susceptibility to hydrogen embrittlement
2. Bmay cause impaired corrosion resistance if left in prolonged contact.
3. Ccauses rapid and severe corrosion in prolonged contact.
167Intercrystalline corrosion.
1. Ais detectable by x-rays.
2. Bis the same as exfoliation corrosion.
3. Calways appears as small surface cracks
168The usual manufacturers anti-corrosion process to be applied to Fe aircraft parts is.
1. Acadmium plating.
2. Banodising.
3. Cmetal spraying.
169Chromate treatment is applied to.
1. AAl alloys.
2. BFe alloys.
3. Cmagnesium alloys.
170Anti-corrosion treatment used on Magnesium is.
1. Achromating.
2. Belectro-plating.
3. Cphosphating
171Fretting corrosion occurs with.
1. Awater trapped between moving parts.
2. Bvibration in bolted parts.
3. Cimproper heat treatment.
172Intergranular corrosion is also known as what?.
1. AStress corrosion.
2. BExfoliation.
3. CGalvanic.
173During construction, sharp internal corners and inaccessible places should be avoided to reduce.
1. Afiliform corrosion.
2. Bfretting corrosion.
3. Ccrevice corrosion
174To check the interior of tubular members for corrosion attack.
1. Aany form of test is acceptable.
2. Bultra sonic testing is necessary.
3. Cdye penetrant testing should be used
175Anodising is a form of.
1. Aartificial protection.
2. Bmetallic coating.
3. Csacrificial protection.
176The Alocrom 1200 process was designed to treat.
1. Achromium plating.
2. Bsmall surfaces.
3. Csurfaces too large for dip treatment
177The artificial production of a film of oxide on the surface of aluminium or any of its alloys is commonly called.
1. Aanodizing.
2. Bparco lubrizing.
3. Calodizing.
178Alodizing protects alloy metal from corrosion and does what else?.
1. AMakes a good surface for paint to adhere to.
2. BMakes the surface alkaline.
3. CSeals the surface from moisture.
179When cleaning aircraft faying surfaces, a cause for concern is.
1. Acorrosion acting on the end faces of panels.
2. Bsharp corners etc trapping corrosive chemicals.
3. Cleaks into the fuselage
180The form of corrosion most likely to cause stress concentration is.
1. ASurface Corrosion.
2. BFretting Corrosion.
3. CPitting Corrosion.
181Lead acid battery fluid has been found to be leaking on the surface of the aircraft structure. What substance would you use to neutralise the acid?.
1. ASulphur and Lime.
2. BHot distilled water.
3. CSodium bicarbonate of soda
182What colour is the corrosion found on the surface of aluminium alloys?.
1. AWhite/Grey.
2. BGreen/Blue.
3. CBlack.
183Corrosion on copper is identified by.
1. Ared/brown rust.
2. Bblack powder.
3. Cgreen discolouration.
184A composite flap panel has corrosion. What NDT method will you use to detect?.
1. ALow voltage x-ray.
2. BCoin tap test.
3. CHigh voltage x-ray.
185When examining a piece of metal through a magnifying glass, hair line cracks would indicate.
1. Acrevice corrosion.
2. Bintergrannular corrosion.
3. Csurface corrosion.
186In the anodic film inspection and sealing test, if a good seal has been accomplished.
1. Athe dye mark will not rub off.
2. Bthe dye mark has no importance.
3. Cthe dye mark will rub off.
187Aluminium alloy parts are often protected by the.
1. AAlocrom plating.
2. Bchromium plating process.
3. CAlocrom 1200 process.
188Corrosion is always completely removed.
1. Ato prevent further damage.
2. Bto fit new parts.
3. Cto permit the extent of damage to be assessed.
189Corrosion on a copper alloy can be recognised by.
1. Ablue/green deposit.
2. Bwhite deposit.
3. Cgrey deposit
190Which of the following is a temporary protective measure?.
1. ASacrificial protection.
2. BChromating.
3. CPaint finish
191Which anti-corrosion chemical treatment is normally applied to aluminium alloys?.
1. APure aluminium.
2. BAnodising.
3. CCadmium.
192Spilled mercury on aluminium causes.
1. Agreyish powder, fuzzy deposit or whiskery growth.
2. Byellowish stains on surface of the metal.
3. Cblack pits going into brown rust.
193A non-electrolytic chemical treatment for aluminium alloys to increase corrosion resistance and paint bonding qualities is called.
1. Aalodizing.
2. Banodizing.
3. Cdichromating.
194Which of the following are acceptable to use in cleaning anodized surfaces?.
1. ASteel wool, aluminium wool, fibre bristle brush.
2. BAluminium wool, fibre bristle brush.
3. CBrass wire brush, stainless steel wire brush.
195 A primary cause of intergranular corrosion is.
1. Aimproper heat treatment.
2. Bimproper application of primer.
3. Cdissimilar metal contact.
196Which of these materials is the most anodic?.
1. AMagnesium.
2. BCadmium.
3. C7075-T6 aluminium alloy.
197Which of these materials is the most cathodic?.
1. A2024 aluminium alloy.
2. BZinc.
3. CStainless steel.
198The pitch of a screw thread is.
1. Acrest to root.
2. B2 * crest to root.
3. Ccrest to crest.
199A single start thread the lead is.
1. A2 * pitch.
2. B1 * pitch.
3. C½ * pitch.
200A wire thread insert tap is.
1. Asupplied in a fitting kit.
2. Bslightly larger than the hole.
3. Cslightly smaller than the hole.

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Description: Quiz on Materiales hadware 2, created by oriol arrufat on 07/08/2018.
Author: oriol arrufat
Language: English
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