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Loads on the cylindrical part of the fuselage during pressurisation are carried ? [ License IFR ]

Question 31-1 : Skin spars stringers ribs

exemple 131 Skin.Skin.

The bending loads on a cantilever wing due to lift are carried by the .1 upper ?

Question 31-2 : 1 2 4 2 3 1 3 4 3 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, 4.1, 2, 4.

Which of these statements about structural design principles are correct or ?

Question 31-3 : I is correct ii is correct i is incorrect ii is incorrect i is correct ii is incorrect 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 exemple 139 I is correct, ii is correct.I is correct, ii is correct.

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

Question 31-4 : I is correct ii is correct i is incorrect ii is incorrect i is incorrect ii is correct i is correct ii is incorrect

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.I is correct, ii is correct.

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

Question 31-5 : I is correct ii is correct i is incorrect ii is incorrect i is incorrect ii is correct i is correct ii is incorrect

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.I is correct, ii is correct.

According jar/cs 25 the worst effect of a hazardous failure on the occupants of ?

Question 31-6 : Serious or fatal injury to a small number of passengers or cabin crew multiple fatalities physical distress possibly including injuries physical discomfort

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

For safe life designed structural components .1 there is more than one load ?

Question 31-7 : 2 3 1 4 2 4 1 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, 3.2, 3.

According jar/cs 25 the allowable average failure probability per flight hour ?

Question 31-8 : Between 10^ 5 and 10^ 7 remote between 10^ 3 and 10^ 5 probable less than 10^ 9 extremely improbable 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 159 Between 10^ -5 and 10^ -7. (remote)Between 10^ -5 and 10^ -7. (remote)

According jar/cs 25 the allowable average failure probability per flight hour ?

Question 31-9 : Between 10^ 3 and 10^ 5 probable between 10^ 5 and 10^ 7 remote between 10^ 7 and 10^ 9 extremely remote less than 10^ 9 extremely improbable

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

According jar/cs 25 the allowable quantitative average failure probability per ?

Question 31-10 : Less than 10^ 9 extremely improbable between 10^ 7 and 10^ 9 extremely remote between 10^ 5 and 10^ 7 remote between 10^ 3 and 10^ 5 probable

. 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)Less than 10^ -9. (extremely improbable)

According jar/cs 25 the worst effect of a hazardous failure on the flight crew ?

Question 31-11 : Physical distress or excessive workload impairs ability to perform tasks fatalities or incapacitation physical discomfort or a significant increase in workload 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 171 Physical distress or excessive workload, impairs ability to perform tasks.Physical distress or excessive workload, impairs ability to perform tasks.

According jar/cs 25 the worst effect of a hazardous failure on the aeroplane ?

Question 31-12 : Large reduction in functional capabilities or safety margins hull loss significant reduction in functional capabilities or safety margins 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 175 Large reduction in functional capabilities or safety margins.Large reduction in functional capabilities or safety margins.

Which of these statements about structural design principles are correct or ?

Question 31-13 : I is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect 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 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.I is incorrect, ii is incorrect.

Which of these statements about structural design principles are correct or ?

Question 31-14 : I is correct ii is correct i is correct ii is incorrect i is incorrect ii is incorrect 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 183 I is correct, ii is correct.I is correct, ii is correct.

Which of these statements about structural design principles are correct or ?

Question 31-15 : I is incorrect ii is correct i is correct ii is incorrect i is incorrect ii is incorrect 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 187 I is incorrect, ii is correct.I is incorrect, ii is correct.

Which of these statements about structural design principles are correct or ?

Question 31-16 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is incorrect 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 .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.I is incorrect, ii is correct.

According jar/cs 25 the worst effect of a minor failure on the occupants of an ?

Question 31-17 : Physical discomfort inconvenience serious or fatal injury to a small number of passengers or cabin crew 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 195 Physical discomfort.Physical discomfort.

According jar/cs 25 the worst effect of a major failure on the occupants of an ?

Question 31-18 : Physical distress possibly including injuries inconvenience serious or fatal injury to a small number of passengers or cabin crew physical discomfort

. 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.Physical distress, possibly including injuries.

According jar/cs 25 the worst effect of a catastrophic failure on the aeroplane ?

Question 31-19 : Hull loss large reduction in functional capabilities or safety margins significant reduction in functional capabilities or safety margins 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 203 Hull loss.Hull loss.

According jar/cs 25 the allowable quantitative average failure probability per ?

Question 31-20 : Between 10^ 7 and 10^ 9 extremely remote less than 10^ 9 extremely improbable between 10^ 5 and 10^ 7 remote between 10^ 3 and 10^ 5 probable

. 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)Between 10^ -7 and 10^ -9. (extremely remote)

According jar/cs 25 the worst effect of a minor failure on the flight crew ?

Question 31-21 : A slight increase in workload no effect on flight crew physical distress or excessive workload impairs ability to perform tasks 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 211 A slight increase in workload.A slight increase in workload.

According jar/cs 25 the worst effect of a major failure on the flight crew ?

Question 31-22 : Physical discomfort or a significant increase in workload no effect on flight crew physical distress or excessive workload impairs ability to perform tasks 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 215 Physical discomfort or a significant increase in workload.Physical discomfort or a significant increase in workload.

According jar/cs 25 the worst effect of a minor failure on the aeroplane could ?

Question 31-23 : Slight reduction in functional capabilities or safety margins no effect on operational capabilities or safety large reduction in functional capabilities or safety margins significant 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.Slight reduction in functional capabilities or safety margins.

According jar/cs 25 the worst effect of a catastrophic failure on the flight ?

Question 31-24 : Fatalities or incapacitation physical distress or excessive workload impairs ability to perform tasks physical discomfort or a significant increase in workload 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 223 Fatalities or incapacitation.Fatalities or incapacitation.

The principle of damage tolerance in structural design of an aircraft is based ?

Question 31-25 : Capability to withstand a certain amount of weakening of the structure without catastrophic failure replacement of parts after a given number of cycles or hours of use fact that there is no need to inspect the structure monitoring of critical parameters and the replacement of parts if a limit value is exceeded

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

The principle of 'on condition maintenance' is based on the ?

Question 31-26 : Monitoring of critical parameters and the replacement of parts if a limit value is exceeded replacement of parts after a given number of cycles or hours of use redundancy of the structure or equipment capability to withstand a certain amount of weakening of the structure without catastrophic failure

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

The principle of 'fail safe' design of an aircraft is based on the ?

Question 31-27 : Redundancy of the structure or equipment replacement of parts after a given number of cycles or hours of use capability to withstand a certain amount of weakening of the structure without catastrophic failure monitoring of critical parameters and the replacement of parts if a limit value is exceeded

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.Redundancy of the structure or equipment.

According jar/cs 25 the worst effect of a catastrophic failure on the occupants ?

Question 31-28 : Multiple fatalities serious or fatal injury to a small number of passengers or cabin crew physical distress possibly including injuries physical discomfort

. certification specifications for large aeroplanes cs 25 book 2 acceptable means of compliance .click here see table on last page .pdf652 exemple 239 Multiple fatalities.Multiple fatalities.

A safe life aircraft structural component ?

Question 31-29 : May be used during a declared number of cycles or flight hours should have enough strength during the whole lifetime of an aircraft is so strong that it never will fail during a declared time period has parallel load paths

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

Whilst stationary on the ground in a hangar the most important loads on a ?

Question 31-30 : Tension in the upper surface compression in the lower surface tension in both the upper and the lower surfaces compression in the upper surface tension in the lower surface compression in both the upper and the lower surfaces

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 exemple 247 Tension in the upper surface, compression in the lower surface.Tension in the upper surface, compression in the lower surface.

In straight and level flight the most important loads on a cantilever wing are ?

Question 31-31 : Compression in the upper surface tension in the lower surface tension in the upper surface compression in the lower surface compression in both the upper and the lower surfaces tension in both the upper and the lower surfaces

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 251 Compression in the upper surface, tension in the lower surface.Compression in the upper surface, tension in the lower surface.

Define the term 'fatigue' ?

Question 31-32 : If a material is continually loaded and unloaded it will eventually break even though the load remains the same a one off loading that breaks the material a loading on the material but it returns fully to its former state when the load is removed the material suffers progressively more permanent damage each time that it is loaded and unloaded

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

Which of these statements about structural design principles are correct or ?

Question 31-33 : I is correct ii is incorrect i is incorrect ii is incorrect i is correct ii is correct 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 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 259 I is correct, ii is incorrect.I is correct, ii is incorrect.

At point 1 the load moment is . 2760 ?

Question 31-34 : Tension shear compression torsion

exemple 263 Tension.Tension.

On modern transport aircraft cockpit windows are protected against icing by ?

Question 31-35 : Electric heating anti icing fluid vinyl coating rain repellent system

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 267 Electric heating.Electric heating.

In flight a cantilever wing of an aeroplane containing fuel is subjected to ?

Question 31-36 : Highest at the wing root equal to the zero fuel weight multiplied by the span equal to half the weight of the aircraft multiplied by the semi span lowest 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 271 Highest at the wing root.Highest at the wing root.

The purpose of static wick dischargers is to ?

Question 31-37 : Dissipate static charge of the aircraft in flight thus avoiding radio interference as a result of static electricity dissipate static charge from the aircraft skin after landing provide a path to ground for static charges when refuelling be able to fly higher because of less electrical friction

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

Electrical bonding of an aircraft is used to .1 protect the aircraft against ?

Question 31-38 : 1 3 and 4 1 2 and 3 3 and 4 2 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 279 1, 3 and 41, 3 and 4

One indication of inadequate bonding of aircraft components may be ?

Question 31-39 : Static noises can be heard on the radio there is interference on the vor receiver a circuit breaker pops out there is heavy corrosion on the fuselage skin mountings

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 283 Static noises can be heard on the radio.Static noises can be heard on the radio.

The reason for the fact that an aeroplane designed for long distances cannot ?

Question 31-40 : The lifetime of the fatigue sensitive parts has been based on a determined load spectrum the procedures and checklists for this kind of aeroplanes will take too much time these aeroplanes often consume too much fuel on short haul flights in that case some fuel tanks remain empty during the whole flight which stresses the aeroplane's structure in an unacceptable way

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

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