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Question 31-1 : Loads on the cylindrical part of the fuselage during pressurisation are carried by the ? [ License IFR ]

Skin

exemple 131 Skin.

Question 31-2 : The bending loads on a cantilever wing due to lift are carried by the .1 upper skin surface .2 lower skin surface .3 wing root fairing .4 spar or spars .the combination that regroups all of the correct statements is ?

1 2 4

A good example for a cantilever wing airplane is the cessna 177 . 807.whilst stationary on the ground in a hangar the most important loads on a cantilever wing are tension in the upper surface compression in the lower surface stationary on the ground the wings are drooping under gravity stretching the top skin and compressing the bottom skin .in flight lift is pulling the wings up stretching the bottom and compressing the top .the wing structure elements which take up the vertical bending moments mx are the spars exemple 135 1, 2, 4.

Question 31-3 : Which of these statements about structural design principles are correct or incorrect .i in structural design fail safe implies redundant load paths .ii a safe life structure is based on a declared number of cycles or time period ?

I is correct ii is correct

.in a 'fail safe' construction the components were designed in a way that the loads are shared among adjacent components .if one component fails the adjacent components take up the load for a limited period of time enough to allow the detection at the next periodic inspection .the philosophy of 'fail safe' is to anticipate a possible failure with a minimum of harm .in a 'safe life' construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met .the 'safe life' design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property exemple 139 I is correct, ii is correct.

Question 31-4 : 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 not suitable for absorbing concentrated loads ?

I is correct ii is correct

A sandwich structural part is composed of two thin sheets and a light core material . 814.the mechanical properties of a sandwich structural part are not suitable for bending the honeycomb structure will break or undergo a permanent deformation . 814 exemple 143 I is correct, ii is correct.

Question 31-5 : 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 unsuitable for absorbing concentrated loads ?

I is correct ii is correct

A sandwich structural part is composed of two thin sheets and a light core material . 814.the mechanical properties of a sandwich structural part are not suitable for bending the honeycomb structure will break or undergo a permanent deformation . 937 exemple 147 I is correct, ii is correct.

Question 31-6 : According jar/cs 25 the worst effect of a hazardous failure on the occupants of an aeroplane excluding flight crew could be ?

Serious or fatal injury to a small number of passengers or cabin crew

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .pdf652 exemple 151 Serious or fatal injury to a small number of passengers or cabin crew.

Question 31-7 : For safe life designed structural components .1 there is more than one load carrying component .2 one load carrying component is sufficient for a given load provided it is strong enough .3 the component is removed at the end of the calculated life time or number of cycles .4 the design is based on ?

2 3

.the safe life principle is based on the replacement of parts after a given number of cycles or time period in structural design safe life implies the structure will shouldn't fail during a declared time period or number of cycles .the safe life design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property .safe life structures are employed when the cost or infeasibility of inspections outweighs the weight penalty and development costs associated with safe life structures .an example of a safe life component is the helicopter rotor blade due to the extremely large numbers of cycles endured by the rotating component an undetectable crack may grow to a critical length in a single flight and before the aircraft lands result in a catastrophic failure that regular maintenance could not have prevented exemple 155 2, 3.

Question 31-8 : According jar/cs 25 the allowable average failure probability per flight hour probability for a major failure should be on the order of ^ means to the power of ?

Between 10^ 5 and 10^ 7 remote

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 159 Between 10^ -5 and 10^ -7. (remote)

Question 31-9 : According jar/cs 25 the allowable average failure probability per flight hour for a 'minor' failure should be on the order of means to the power of ?

Between 10^ 3 and 10^ 5 probable

Certification specifications for large aeroplanes cs 25 . book 2 acceptable means of compliance .pdf652 exemple 163 Between 10^ -3 and 10^ -5. (probable)

Question 31-10 : According jar/cs 25 the allowable quantitative average failure probability per flight hour for a catastrophic failure should be on the order of ^ means to the power of ?

Less than 10^ 9 extremely improbable

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652. exemple 167 Less than 10^ -9. (extremely improbable)

Question 31-11 : According jar/cs 25 the worst effect of a hazardous failure on the flight crew could be ?

Physical distress or excessive workload impairs ability to perform tasks

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652. exemple 171 Physical distress or excessive workload, impairs ability to perform tasks.

Question 31-12 : According jar/cs 25 the worst effect of a hazardous failure on the aeroplane could be ?

Large reduction in functional capabilities or safety margins

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 175 Large reduction in functional capabilities or safety margins.

Question 31-13 : Which of these statements about structural design principles are correct or incorrect .1 in structural design fail safe implies the structure will never fail .2 in structural design safe life implies the structure will never fail during a declared time period or number of cycles ?

I is incorrect ii is incorrect

In a fail safe construction the components were designed in a way that the loads are shared among adjacent components .if one component fails the adjacent components take up the load for a limited period of time enough to allow the detection at the next periodic inspection .the philosophy of fail safe is to anticipate a possible failure with a minimum of harm .in a safe life construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met .the safe life design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property .statement ii is incorrect because you can not guarantee that a part will definitely not will never fail within its calculated number of cycles or its period exemple 179 I is incorrect, ii is incorrect.

Question 31-14 : Which of these statements about structural design principles are correct or incorrect .1 the damage tolerance principle takes cracking of the structure into account .2 the safe life principle is based on the replacement of parts after a given number of cycles or flight hours ?

I is correct ii is correct

Damage tolerant components will not have a specfied life continued operation is based on frequent inspections and takes cracking of the structure into account .in a 'safe life' construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met exemple 183 I is correct, ii is correct.

Question 31-15 : Which of these statements about structural design principles are correct or incorrect .1 the damage tolerance principle assumes cracks in the structure will never occur .2 the safe life principle is based on the replacement of parts after a given number of cycles or time period ?

I is incorrect ii is correct

Damage tolerant components will not have a specfied life continued operation is based on frequent inspections and takes cracking of the structure into account .in a 'safe life' construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met exemple 187 I is incorrect, ii is correct.

Question 31-16 : Which of these statements about structural design principles are correct or incorrect .1 in structural design fail safe implies the structure will never fail .2 a safe life structure is based on a declared time period or number of cycles ?

I is incorrect ii is correct

In a fail safe construction the components were designed in a way that the loads are shared among adjacent components .if one component fails the adjacent components take up the load for a limited period of time enough to allow the detection at the next periodic inspection .the philosophy of fail safe is to anticipate a possible failure with a minimum of harm .in a safe life construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met .the safe life design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property .statement i is incorrect because you can not guarantee that a part will definitely not will never fail exemple 191 I is incorrect, ii is correct.

Question 31-17 : According jar/cs 25 the worst effect of a minor failure on the occupants of an aeroplane excluding flight crew could be ?

Physical discomfort

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 195 Physical discomfort.

Question 31-18 : According jar/cs 25 the worst effect of a major failure on the occupants of an aeroplane excluding flight crew could be ?

Physical distress possibly including injuries

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 199 Physical distress, possibly including injuries.

Question 31-19 : According jar/cs 25 the worst effect of a catastrophic failure on the aeroplane could be ?

Hull loss

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 203 Hull loss.

Question 31-20 : According jar/cs 25 the allowable quantitative average failure probability per flight hour for a hazardous failure should be on the order of ^ means to the power of ?

Between 10^ 7 and 10^ 9 extremely remote

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 207 Between 10^ -7 and 10^ -9. (extremely remote)

Question 31-21 : According jar/cs 25 the worst effect of a minor failure on the flight crew could be ?

A slight increase in workload

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 211 A slight increase in workload.

Question 31-22 : According jar/cs 25 the worst effect of a major failure on the flight crew could be ?

Physical discomfort or a significant increase in workload

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 215 Physical discomfort or a significant increase in workload.

Question 31-23 : According jar/cs 25 the worst effect of a minor failure on the aeroplane could be ?

Slight reduction in functional capabilities or safety margins

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 219 Slight reduction in functional capabilities or safety margins.

Question 31-24 : According jar/cs 25 the worst effect of a catastrophic failure on the flight crew could be ?

Fatalities or incapacitation

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 223 Fatalities or incapacitation.

Question 31-25 : The principle of damage tolerance in structural design of an aircraft is based on the ?

Capability to withstand a certain amount of weakening of the structure without catastrophic failure

Damage tolerant components will not have a specified life continued operation is based on frequent inspections and takes cracking of the structure into account exemple 227 Capability to withstand a certain amount of weakening of the structure without catastrophic failure.

Question 31-26 : The principle of on condition maintenance is based on the ?

Monitoring of critical parameters and the replacement of parts if a limit value is exceeded

On condition maintenance is a preventative process in which an item is monitored either continuously or at specified periods the item's performance is compared to an appropriate standard in order to determine if it can continue in service exemple 231 Monitoring of critical parameters and the replacement of parts if a limit value is exceeded.

Question 31-27 : The principle of 'fail safe' design of an aircraft is based on the ?

Redundancy of the structure or equipment

In a 'fail safe' construction the components were designed in a way that the loads are shared among adjacent components .if one component fails the adjacent components take up the load for a limited period of time enough to allow the detection at the next periodic inspection .the philosophy of 'fail safe' is to anticipate a possible failure with a minimum of harm exemple 235 Redundancy of the structure or equipment.

Question 31-28 : A safe life aircraft structural component ?

May be used during a declared number of cycles or flight hours

In a 'safe life' construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met .the 'safe life' design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property exemple 239 May be used during a declared number of cycles or flight hours.

Question 31-29 : Whilst stationary on the ground in a hangar the most important loads on a cantilever wing are ?

Tension in the upper surface compression in the lower surface

Howarthson .stationary on the ground the wings are drooping under gravity stretching the top skin and compressing the bottom skin in flight lift is pulling the wings up stretching the bottom and compressing the top

Question 31-30 : In straight and level flight the most important loads on a cantilever wing are ?

Compression in the upper surface tension in the lower surface

The most important loads on a cantilever wing in flight are compression in the upper surface tension in the lower surface . 809.on the ground it's the opposite exemple 247 Compression in the upper surface, tension in the lower surface.

Question 31-31 : Define the term 'fatigue' ?

If a material is continually loaded and unloaded it will eventually break even though the load remains the same

The life of an airframe is limited by fatigue caused by the load cycles imposed during takeoff landing and pressurisation this life has been calculated over the years by using different design philosophies these being safe life fail safe and damage tolerant exemple 251 If a material is continually loaded and unloaded it will eventually break even though the load remains the same.

Question 31-32 : Which of these statements about structural design principles are correct or incorrect .i in structural design fail safe implies parallel structural parts .ii in structural design safe life implies the structure will never fail during a declared time period or number of cycles ?

I is correct ii is incorrect

.in a 'fail safe' construction the components were designed in a way that the loads are shared among adjacent components .if one component fails the adjacent components take up the load for a limited period of time enough to allow the detection at the next periodic inspection .the philosophy of 'fail safe' is to anticipate a possible failure with a minimum of harm .in a 'safe life' construction the components are given for a time period and/or number of cycles x landings x engine starts and must be removed from service when the appropriate criteria are met .the 'safe life' design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property .statement ii is incorrect because you can not guarantee that a part will definitely not will never fail within its calculated number of cycles or its period exemple 255 I is correct, ii is incorrect.

Question 31-33 : At point 1 the load moment is . 2760 ?

Tension

exemple 259 Tension.

Question 31-34 : On modern transport aircraft cockpit windows are protected against icing by ?

Electric heating

Admin .on boeing 777 for example the windshield consists of three plies of glass with exterior surface anti icing and exterior and interior surface anti fogging protection the plies are comprised of chemically tempered glass separated by interlayers of polyvinyl butyral and urethane the glass and interlayer materials are bonded together in an autoclave under specific time temperature and pressure conditions .the window is designed to withstand fail safe pressure loads with a single glass ply failed and normal pressure loads with multiple glass plies failed the windshield heat system is normally powered whenever the aircraft electrical system is powered .the anti ice and anti fog elements are connected to separate power and sensor terminal blocks located on the upper and lower edges of the windshield exemple 263 Electric heating.

Question 31-35 : In flight a cantilever wing of an aeroplane containing fuel is subjected to vertical loads that produce a bending moment which is ?

Highest at the wing root

A good example for a cantilever wing airplane is the cessna 177 . 807.on the ground and in flight the highest bending moment is at the wing root since there is no external supports as for a cessna 172 for example . 808 exemple 267 Highest at the wing root.

Question 31-36 : The purpose of static wick dischargers is to ?

Dissipate static charge of the aircraft in flight thus avoiding radio interference as a result of static electricity

The goal is to maintain the electrical airframe potential at around 10000 volts via the static dischargers by providing a path for the electrons .example of static dischargers on a wing . 810.without static dischargers the electrical airframe potential would rise up to a value 10 times higher and would disturb and/or damage the onboard equipment exemple 271 Dissipate static charge of the aircraft in flight thus avoiding radio interference as a result of static electricity.

Question 31-37 : Electrical bonding of an aircraft is used to .1 protect the aircraft against lightning effects .2 reset the electrostatic potential of the aircraft to a value approximating 0 volt.3 reduce radio interference on radio communication systems.4 set the aircraft to a single potential.the combination ?

1 3 and 4

Good electrical bonding will reduce the damage to the airframe structure in the event of a lightning strike .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 275 1, 3 and 4

Question 31-38 : One indication of inadequate bonding of aircraft components may be ?

Static noises can be heard on the radio

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 279 Static noises can be heard on the radio.

Question 31-39 : The reason for the fact that an aeroplane designed for long distances cannot simply be used for short haul flights at higher frequencies is that ?

The lifetime of the fatigue sensitive parts has been based on a determined load spectrum

Take for example the pressurization depressurizations cycles .the more cycles you do short flights the more fatigue the structure gets if you use an airbus a340 for short hauls as the aircraft has not been designed for that it is more susceptible to 'low cycle fatigue damages' compared to an airbus a320 .note once at cruise level the fatigue remains the same it is not time related it is cycle related .all nippon airways and japan airlines are the best known users for the special boeing 747 400d domestic a high density seating model developed for short haul domestic japanese flights the aircraft is capable of seating a maximum of 568 passengers in a 2 class configuration or 660 passengers in a single class configuration the 400d lacks the wing tip extensions and winglets included on other variants allowing for increased number of takeoffs and landings by lowering wing stresses the benefits of winglets would be minimal on short routes ..the 747 400d is also unusual in having more windows on both sides of the upper deck than the basic 400 series this allows for additional seating all the way down the upper deck where a galley is situated on most international models exemple 283 The lifetime of the fatigue sensitive parts has been based on a determined load spectrum.

Question 31-40 : Engine compartment decking and firewalls are manufactured from ?

Stainless steel or titanium sheet

exemple 287 Stainless steel or titanium sheet.


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