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Engine compartment decking and firewalls are manufactured from ? [ Questionnaire LAPL ]

Question 32-1 : Stainless steel or titanium sheet composite materials such as carbon kevlar and fibre glass aluminium alloy sheet asbestos blankets

exemple 132 Stainless steel or titanium sheet.Stainless steel or titanium sheet.

The inner surface of a heated windscreen is of ?

Question 32-2 : Soft polycarbonate triplex glass hard perspex

It is not the case for all aircraft but most of the time the inner surface of a heated windscreen is of soft polycarbonate or an equivalent product it allows high resistance and very expandable seal regarding temperature change constraints exemple 136 Soft polycarbonate.Soft polycarbonate.

The purpose of stringers used in fuselage construction is to ?

Question 32-3 : Assist the skin withstand longitudinal compressive loads withstand shear stresses provide sound and thermal isolation carry the loads due to pressurisation and convert them into tensile stress

exemple 140 Assist the skin withstand longitudinal compressive loads.Assist the skin withstand longitudinal compressive loads.

Significant torsion effects in a wing during flight can be caused by ?

Question 32-4 : Aileron deflection wing tip vortices propwash wing dihedral

exemple 144 Aileron deflection.Aileron deflection.

The two deformation modes that cause wing flutter are ?

Question 32-5 : Torsion and bending torsion and shearing bending and elongation shearing and elongation

Flutter is a divergent oscillatory motion of a control surface caused by the interaction of aerodynamic forces inertia forces and the stiffness of the structure it is a combination of bending and torsion of the structure . aero elastic coupling affects flutter characteristics . the risk of flutter increases as ias increases . if flutter occurs ias should be reduced . resistance to flutter increases with increasing wing stiffness exemple 148 Torsion and bending.Torsion and bending.

One design method to avoid control surface flutter is ?

Question 32-6 : Ensuring correct mass distribution within the control surface through the correct use of balance tabs through the correct use of trim tabs providing the wing structure with sufficient flexibility

exemple 152 Ensuring correct mass distribution within the control surface.Ensuring correct mass distribution within the control surface.

A composite structural component consists of ?

Question 32-7 : A matrix and fibres two thin metal sheets and a light core material aluminium alloy with a covering layer of pure aluminium two metal sheets bonded together

exemple 156 A matrix and fibres.A matrix and fibres.

The fuselage structure of a pressurised transport aeroplane is an example of a ?

Question 32-8 : Semi monocoque structure truss type structure pure monocoque structure sandwich structure

An egg is a good example of a monocoque structure monocoque means 'single shell' .semi monocoque is a compromise which uses longerons stringers to take some of the strain sandwich structure is a part of the 'shell' of an airframe .semi monocoque fuselage is the standard construction in nowadays this has solved the problem with the thick of the sheet of the lining of the monocoque structure this fuselage uses a thinner sheet by the use of structural members between the members have the function of step up the union and shape the fuselage . 811. 812. semi monocoque structure on a modern pressurised transport aeroplane exemple 160 Semi-monocoque structure.Semi-monocoque structure.

When a wing bends downwards aileron flutter might occur if the aileron deflects ?

Question 32-9 : Upwards because the location of the aileron centre of gravity lies behind the hinge line upwards because the location of the aileron centre of gravity lies in front of the hinge line downwards because the location of the aileron centre of gravity lies behind the hinge line downwards because the location of the aileron centre of gravity lies in front of the hinge line

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces as the airspeed increases there may be a point at which the structural damping is insufficient to damp out the motions which are increasing due to aerodynamic energy being added to the airfoil this vibration can cause structural failure and therefore considering flutter characteristics is an essential part of designing an aircraft . 813.if the cg is aft of the torsional axis inertia causes the cg of the aileron to lag behind any movement of the axis caused by changes in lift this lag can cause still further changes in incidence and hence lift making the matter worse .by having the cg on or forward of the hinge the torsion axis now uses the property of inertia to counter the effect exemple 164 Upwards, because the location of the aileron centre of gravity lies behind the hinge line.Upwards, because the location of the aileron centre of gravity lies behind the hinge line.

A structure in which the skin takes all of the load is ?

Question 32-10 : A monocoque structure a semi monocoque structure a semi braced structure a box structure

The monocoque design uses stressed skin to support almost all imposed loads this structure can be very strong but cannot tolerate dents or deformation of the surface this characteristic is easily demonstrated by a thin aluminum beverage can you can exert considerable force to the ends of the can without causing any damage .however if the side of the can is dented only slightly the can will collapse easily the true monocoque construction mainly consists of the skin formers and bulkheads the formers and bulkheads provide shape for the fuselage . 657.since no bracing members are present the skin must be strong enough to keep the fuselage rigid thus a significant problem involved in monocoque construction is maintaining enough strength while keeping the weight within allowable limits .due to the limitations of the monocoque design a semi monocoque structure is used on many of today's aircraft exemple 168 A monocoque structure.A monocoque structure.

A cantilever wing is ?

Question 32-11 : A wing attached to the fuselage at the wing root only a wing planform other than rectangular a high wing configuration a low wing configuration

A good example for a cantilever wing airplane is the cessna 177 . 807 exemple 172 A wing attached to the fuselage at the wing root only.A wing attached to the fuselage at the wing root only.

A non cantilever wing is ?

Question 32-12 : A wing supported by braces or a strut connected to the fuselage a wing planform other than rectangular a high wing configuration a low wing configuration

exemple 176 A wing supported by braces or a strut connected to the fuselage.A wing supported by braces or a strut connected to the fuselage.

A sandwich structural part ?

Question 32-13 : Consists of two thin sheets separated by a light core material always uses honeycomb as core material is a so called integral construction is unsuitable for fuel tanks

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To achieve control flutter damping the balance mass must be located ?

Question 32-14 : In front of the control surface hinge behind the control surface hinge directly above the control surface hinge directly below the control surface hinge

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces as the airspeed increases there may be a point at which the structural damping is insufficient to damp out the motions which are increasing due to aerodynamic energy being added to the airfoil this vibration can cause structural failure and therefore considering flutter characteristics is an essential part of designing an aircraft . 813.to counteract this phenomenon the control surface's cg must be as close as possible of the hinge the torsion axis exemple 184 In front of the control surface hinge.In front of the control surface hinge.

Which of these statements concerning a sandwich structural part are correct or ?

Question 32-15 : I is correct ii is incorrect i is correct ii is correct i is incorrect ii is correct i is incorrect ii is incorrect

When a wing bends upwards aileron flutter might occur if the aileron deflects ?

Question 32-16 : Downwards because the location of the aileron centre of gravity lies behind the hinge line downwards because the location of the aileron centre of gravity lies in front of the hinge line upwards because the location of the aileron centre of gravity lies behind the hinge line upwards because the location of the aileron centre of gravity lies in front of the hinge line

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces as the airspeed increases there may be a point at which the structural damping is insufficient to damp out the motions which are increasing due to aerodynamic energy being added to the airfoil this vibration can cause structural failure and therefore considering flutter characteristics is an essential part of designing an aircraft . 813.if the cg is aft behind of the torsional axis inertia causes the cg of the aileron to lag behind any movement of the axis caused by changes in lift this lag can cause still further changes in incidence and hence lift making the matter worse .by having the cg on or forward of the hinge the torsion axis now uses the property of inertia to counter the effect exemple 192 Downwards, because the location of the aileron centre of gravity lies behind the hinge line.Downwards, because the location of the aileron centre of gravity lies behind the hinge line.

Which of these statements regarding cockpit windows are correct or incorrect .i ?

Question 32-17 : I is correct ii is incorrect i is correct ii is correct i is incorrect ii is incorrect i is incorrect ii is correct

The force from a bird impact increases with the square of the speed a hot windshield is more pliable and less likely to shatter if it gets hit . 815.bird strike example on a challenger .on modern aircraft example for the boeing 737 800 and max windows l1 r1 and l2 r2 have a conductive coating on the outer pane that permits electrical heating to prevent the build up of ice and fogging .for those models of the aircraft without electric heat to window l3 and r3 cabin air is circulated around the windshield to prevent fogging of the window . 816 exemple 196 I is correct, ii is incorrect.I is correct, ii is incorrect.

Which of these statements concerning a sandwich structural part are correct or ?

Question 32-18 : I is incorrect ii is incorrect i is correct ii is correct i is incorrect ii is correct i is correct ii is incorrect

exemple 200 I is incorrect, ii is incorrect.I is incorrect, ii is incorrect.

Which of these statements regarding cockpit windows are correct or incorrect .i ?

Question 32-19 : I is incorrect ii is correct i is correct ii is correct i is incorrect ii is incorrect i is correct ii is incorrect

The force from a bird impact increases with the square of the speed a hot windshield is more pliable and less likely to shatter if it gets hit . 815.bird strike example on a challenger .on modern aircraft example for the boeing 737 800 and max windows l1 r1 and l2 r2 have a conductive coating on the outer pane that permits electrical heating to prevent the build up of ice and fogging .for those models of the aircraft without electric heat to window l3 and r3 cabin air is circulated around the windshield to prevent fogging of the window . 816 exemple 204 I is incorrect, ii is correct.I is incorrect, ii is correct.

Which of these statements about sandwich structural parts are correct or ?

Question 32-20 : I is incorrect ii is incorrect i is correct ii is correct i is incorrect ii is correct i is correct ii is incorrect

exemple 208 I is incorrect, ii is incorrect.I is incorrect, ii is incorrect.

Which of these statements regarding cockpit windows are correct or incorrect .i ?

Question 32-21 : I is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct

The force from a bird impact increases with the square of the speed a hot windshield is more pliable and less likely to shatter if it gets hit . 815.bird strike example on a challenger .on modern aircraft example for the boeing 737 800 and max windows l1 r1 and l2 r2 have a conductive coating on the outer pane that permits electrical heating to prevent the build up of ice and fogging .for those models of the aircraft without electric heat to window l3 and r3 cabin air is circulated around the windshield to prevent fogging of the window . 816 exemple 212 I is incorrect, ii is incorrect.I is incorrect, ii is incorrect.

Which of these statements regarding cockpit windows are correct or incorrect .i ?

Question 32-22 : I is correct ii is correct i is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is incorrect

The force from a bird impact increases with the square of the speed a hot windshield is more pliable and less likely to shatter if it gets hit . 815.bird strike example on a challenger .on modern aircraft example for the boeing 737 800 and max windows l1 r1 and l2 r2 have a conductive coating on the outer pane that permits electrical heating to prevent the build up of ice and fogging .for those models of the aircraft without electric heat to window l3 and r3 cabin air is circulated around the windshield to prevent fogging of the window . 816 exemple 216 I is correct, ii is correct.I is correct, ii is correct.

Which of these statements about composite and metal structures are correct or ?

Question 32-23 : I is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct i is incorrect ii is incorrect

exemple 220 I is correct, ii is correct.I is correct, ii is correct.

Which of these statements about composite and metal structures are correct or ?

Question 32-24 : I is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct

For a structural component with given dimensions composite materials enable a structural component's strength to be tailored to the direction of the load .composite materials enable structures with higher strength/weight ratio than metal structures exemple 224 I is incorrect, ii is incorrect.I is incorrect, ii is incorrect.

Which of these statements about composite and metal structures are correct or ?

Question 32-25 : I is correct ii is incorrect i is incorrect ii is correct i is correct ii is correct i is incorrect ii is incorrect

For a structural component with given dimensions composite materials enable a structural component's strength to be tailored to the direction of the load .composite materials enable structures with higher strength/weight ratio than metal structures exemple 228 I is correct, ii is incorrect.I is correct, ii is incorrect.

What are the three elements of the fuselage structure of a large transport ?

Question 32-26 : Skin frames stringers skin ribs formers skin spars ribs skin girders webs

exemple 232 Skin, frames, stringers.Skin, frames, stringers.

Which of these statements about composite and metal structures are correct or ?

Question 32-27 : I is incorrect ii is correct i is correct ii is correct i is correct ii is incorrect i is incorrect ii is incorrect

For a structural component with given dimensions composite materials enable a structural component's strength to be tailored to the direction of the load .composite materials enable structures with higher strength/weight ratio than metal structures exemple 236 I is incorrect, ii is correct.I is incorrect, ii is correct.

A sandwich type structure is often used in aircraft because of its ?

Question 32-28 : Low mass and high stiffness low mass and low stiffness ease of deformation under load high temperature resistance

exemple 240 Low mass and high stiffness.Low mass and high stiffness.

A wing spar typically consists of ?

Question 32-29 : A web and girders ribs and stiffeners frames and webs ribs and frames

A typical metal spar in a general aviation aircraft usually consists of a sheet aluminium spar web and girders with 'l' or 't' shaped spar caps being welded or riveted to the top and bottom of the sheet to prevent buckling under applied loads exemple 244 A web and girders.A web and girders.

A semi monocoque aircraft fuselage structure usually consists of ?

Question 32-30 : Skin frames stringers ribs front spar rear spar ribs spars skin frames fittings stringers

exemple 248 Skin, frames ,stringers.Skin, frames ,stringers.

A sandwich structural part is unsuitable for absorbing ?

Question 32-31 : Concentrated loads bending loads torsional loads shear loads

exemple 252 Concentrated loads.Concentrated loads.

Which of these statements concerning a sandwich structural part are correct or ?

Question 32-32 : I is incorrect ii is correct i is correct ii is correct i is incorrect ii is incorrect i is correct ii is incorrect

exemple 256 I is incorrect, ii is correct.I is incorrect, ii is correct.

Which of these statements about sandwich structural parts are correct or ?

Question 32-33 : I is correct ii is incorrect i is incorrect ii is incorrect i is incorrect ii is correct i is correct ii is correct

exemple 260 I is correct, ii is incorrect.I is correct, ii is incorrect.

Which of these statements about sandwich structural parts are correct or ?

Question 32-34 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect

.composite materials such as sandwich structural parts are made from fibres generally embedded in epoxy resin covered with a skin of aluminium kevlar or nomex .sandwich structural parts need additional provisions to carry concentrated loads exemple 264 I is incorrect, ii is correct.I is incorrect, ii is correct.

The function of ribs in a wing is to ?

Question 32-35 : Give the wing the desired aerodynamic shape withstand the torsional loads withstand all the structural loads allow installation of fuel cells in the wing

exemple 268 Give the wing the desired aerodynamic shape.Give the wing the desired aerodynamic shape.

The pressurisation load on the skin of a fuselage is ?

Question 32-36 : Tension torsion bending compression

exemple 272 Tension.Tension.

When the wing skin is not able to carry loads the structural elements of the ?

Question 32-37 : The spars the ribs the webs the rivets

The spars are able to carry the upward resulting from the wing lift force that supports the fuselage in flight and downward whilst stationary on the ground due to the weight of the structure fuel carried in the wings and wing mounted engines if used bending moments exemple 276 The spars.The spars.

Which of these statements about the wing structure is correct ?

Question 32-38 : A torsion box is formed by wing spars ribs and wing skin reinforced by stringers a wing main spar consists of a web with stringers a semi monocoque structure consists of the skin and frames the slats are a part of the torsion box

exemple 280 A torsion box is formed by wing spars, ribs and wing skin reinforced by stringers.A torsion box is formed by wing spars, ribs and wing skin reinforced by stringers.

The purpose of bonding the metallic parts of an aircraft is to .1 prevent ?

Question 32-39 : 2 4 1 4 2 3 1 3

.bonding is the electrical interconnection of metallic aircraft parts normally at earth potential for the safe distribution of electrical charges and currents .bonding provides a means of protection against charges as a result of the build up of precipitation static and electrostatic induction as a result of lightning strikes so that the safety of the aircraft or its occupants is not endangered .bonding reduces the possibility of electric shock from the electrical supply system reduces interference with the functioning of essential services e g radio communications and navigational aids and provides a low resistance electrical return path for electric current in earth return systems exemple 284 2, 4.2, 4.

Which sequence correctly places the fuselage shapes illustrated in order of ?

Question 32-40 : 2 3 4 1 1 3 4 2 1 4 3 2 3 1 2 4

N°1 is clearly the weakest and would only be used on an unpressurised aircraft twin otter for example .n°2 is geometrically the strongest from a pressurisation point of view as the hoop stresses can be uniform on the whole cross section .n°3 'double bubble' type where two circles intersect connected via a floor not the best choice but clearly better than n°4 .n°4 the pressurization constraints will not be optimal on an oval format .this question also exists with the statement 'from the following fuselage profile sort them from the worst to the best one concerning the pressurization '.answer 1 4 3 2 exemple 288 2, 3, 4, 1.2, 3, 4, 1.

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1239 Free Training Exam Other source study: Furious atpl examen 32