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Question 32-1 : The inner surface of a heated windscreen is of ? [ Questionnaire LAPL ]

Soft polycarbonate

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 132 Soft polycarbonate.

Question 32-2 : The purpose of stringers used in fuselage construction is to ?

Assist the skin withstand longitudinal compressive loads

exemple 136 Assist the skin withstand longitudinal compressive loads.

Question 32-3 : Significant torsion effects in a wing during flight can be caused by ?

Aileron deflection

exemple 140 Aileron deflection.

Question 32-4 : The two deformation modes that cause wing flutter are ?

Torsion and bending

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 144 Torsion and bending.

Question 32-5 : One design method to avoid control surface flutter is ?

Ensuring correct mass distribution within the control surface

exemple 148 Ensuring correct mass distribution within the control surface.

Question 32-6 : A composite structural component consists of ?

A matrix and fibres

exemple 152 A matrix and fibres.

Question 32-7 : The fuselage structure of a pressurised transport aeroplane is an example of a ?

Semi monocoque 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 156 Semi-monocoque structure.

Question 32-8 : When a wing bends downwards aileron flutter might occur if the aileron deflects ?

Upwards because the location of the aileron centre of gravity lies behind 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 160 Upwards, because the location of the aileron centre of gravity lies behind the hinge line.

Question 32-9 : A structure in which the skin takes all of the load is ?

A monocoque 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 164 A monocoque structure.

Question 32-10 : A cantilever wing is ?

A wing attached to the fuselage at the wing root only

A good example for a cantilever wing airplane is the cessna 177 . 807 exemple 168 A wing attached to the fuselage at the wing root only.

Question 32-11 : A non cantilever wing is ?

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

exemple 172 A wing supported by braces or a strut connected to the fuselage.

Question 32-12 : A sandwich structural part ?

Consists of two thin sheets separated by a light core material

Img814 exemple 176 Consists of two thin sheets separated by a light core material.

Question 32-13 : To achieve control flutter damping the balance mass must be located ?

In front of 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

Question 32-14 : Which of these statements concerning a sandwich structural part are correct or incorrect .i the main function of the core material is to stabilise the covering sheets .ii a sandwich structural part is well suited for absorbing concentrated loads ?

I is correct ii is incorrect

exemple 184 I is correct, ii is incorrect.

Question 32-15 : When a wing bends upwards aileron flutter might occur if the aileron deflects ?

Downwards because the location of the aileron centre of gravity lies behind 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

Question 32-16 : Which of these statements regarding cockpit windows are correct or incorrect .i on some aeroplanes the cockpit windows have an additional speed restriction related to bird impact when window heating is inoperative .ii cockpit side windows are always provided with a de icing system ?

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 192 I is correct, ii is incorrect.

Question 32-17 : Which of these statements concerning a sandwich structural part are correct or incorrect . i the main function of the core material is sound insulation . ii a sandwich structural part is well suited for absorbing concentrated loads ?

I is incorrect ii is incorrect

exemple 196 I is incorrect, ii is incorrect.

Question 32-18 : Which of these statements regarding cockpit windows are correct or incorrect .i cockpit windows never have an additional speed restriction related to bird impact when window heating is inoperative .ii cockpit side windows are usually defogged only ?

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 200 I is incorrect, ii is correct.

Question 32-19 : Which of these statements about sandwich structural parts are correct or incorrect .i a sandwich structural part consists of fibres and a resin .ii a sandwich structural part is suitable for absorbing concentrated loads ?

I is incorrect ii is incorrect

exemple 204 I is incorrect, ii is incorrect.

Question 32-20 : Which of these statements regarding cockpit windows are correct or incorrect .i cockpit windows never have an additional speed restriction related to bird impact when window heating is inoperative .ii cockpit side windows are always provided with a de icing system ?

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

Question 32-21 : Which of these statements regarding cockpit windows are correct or incorrect .i on some aeroplanes the cockpit windows have an additional speed restriction related to bird impact when window heating is inoperative .ii cockpit side windows are usually defogged only ?

I is correct 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 correct, ii is correct.

Question 32-22 : Which of these statements about composite and metal structures are correct or incorrect .i for a structural component with given dimensions composite materials enable a structural component's strength to be tailored to the direction of the load .ii composite materials enable structures with higher ?

I is correct ii is correct

exemple 216 I is correct, ii is correct.

Question 32-23 : Which of these statements about composite and metal structures are correct or incorrect .i in a structural component with given dimensions constructed of composite materials the strength is the same in all directions .ii composite materials enable structures with lower strength/weight ratio than ?

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 220 I is incorrect, ii is incorrect.

Question 32-24 : Which of these statements about composite and metal structures are correct or incorrect .i for a structural component with given dimensions composite materials enable a structural component's strength to be tailored to the direction of the load .ii composite materials enable structures with lower ?

I is correct 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 224 I is correct, ii is incorrect.

Question 32-25 : What are the three elements of the fuselage structure of a large transport aeroplane ?

Skin frames stringers

exemple 228 Skin, frames, stringers.

Question 32-26 : Which of these statements about composite and metal structures are correct or incorrect .i in a structural component with given dimensions constructed of composite materials the strength is the same in all directions .ii composite materials enable structures with higher strength/weight ratio than ?

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 232 I is incorrect, ii is correct.

Question 32-27 : A sandwich type structure is often used in aircraft because of its ?

Low mass and high stiffness

exemple 236 Low mass and high stiffness.

Question 32-28 : A wing spar typically consists of ?

A web and girders

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 240 A web and girders.

Question 32-29 : A semi monocoque aircraft fuselage structure usually consists of ?

Skin frames stringers

exemple 244 Skin, frames ,stringers.

Question 32-30 : A sandwich structural part is unsuitable for absorbing ?

Concentrated loads

exemple 248 Concentrated loads.

Question 32-31 : Which of these statements concerning a sandwich structural part are correct or incorrect .i the main function of the core material is sound insulation .ii a sandwich structural part is unsuitable for absorbing concentrated loads ?

I is incorrect ii is correct

exemple 252 I is incorrect, ii is correct.

Question 32-32 : Which of these statements about sandwich structural parts are correct or incorrect .i a sandwich structural part consists of two thin sheets enclosing a light core material .ii a sandwich structural part is suitable for absorbing concentrated loads ?

I is correct ii is incorrect

exemple 256 I is correct, ii is incorrect.

Question 32-33 : Which of these statements about sandwich structural parts are correct or incorrect .i a sandwich structural part consists of fibres and a resin .ii a sandwich structural part is not suitable for absorbing concentrated loads ?

I is incorrect ii is correct

.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 260 I is incorrect, ii is correct.

Question 32-34 : The function of ribs in a wing is to ?

Give the wing the desired aerodynamic shape

exemple 264 Give the wing the desired aerodynamic shape.

Question 32-35 : The pressurisation load on the skin of a fuselage is ?

Tension

exemple 268 Tension.

Question 32-36 : When the wing skin is not able to carry loads the structural elements of the wing which carry the bending moment are ?

The spars

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 272 The spars.

Question 32-37 : Which of these statements about the wing structure is correct ?

A torsion box is formed by wing spars ribs and wing skin reinforced by stringers

exemple 276 A torsion box is formed by wing spars, ribs and wing skin reinforced by stringers.

Question 32-38 : The purpose of bonding the metallic parts of an aircraft is to .1 prevent electrolytic corrosion between mating surfaces of similar metals.2 ensure zero voltage difference between aircraft components.3 isolate all components electrically.4 provide a single earth for electrical devices.the ?

2 4

.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 280 2, 4.

Question 32-39 : Which sequence correctly places the fuselage shapes illustrated in order of decreasing structural strength . 818 ?

2 3 4 1

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 284 2, 3, 4, 1.

Question 32-40 : Hydraulic fluids must have the following characteristics .1 thermal stability.2 low emulsifying characteristics.3 corrosion resistance.4 good resistance to combustion.5 high compressibility.6 high volatility.7 high viscosity.the combination regrouping all the correct statements is ?

1 2 3 and 4

exemple 288 1, 2, 3 and 4.


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1239 Free Training Exam Other source study: Cca theorique examen 32