On a large transport aeroplane the auto slat system ? [ Experience registration ]

Question 36-1 : Extends part of the slats automatically when a certain value of angle of attack is exceeded provides for automatic slat retraction after take off ensures that the part of slats are always extended when the ground/flight system is in the 'ground' position assist the ailerons

exemple 136 Extends (part of) the slats automatically when a certain value of angle of attack is exceeded. — The auto slat system is designed to enhance airplane stall characteristics at high angles of attack during takeoff or approach to landing . as the airplane approaches the stall angle the slats automatically begin driving to the full extended position prior to stick shaker activation the slats return to the extend position when the pitch angle is sufficiently reduced below the stall critical attitude Extends (part of) the slats automatically when a certain value of angle of attack is exceeded.

Most transport aeroplanes are provided with protection against control jamming ?

Question 36-2 : The flight control system has provisions to disconnect the part of the control system that becomes blocked the aeroplane is protected against the adverse effects of strong electromagnetic radiation seized brakes can be released from the cockpit in case of seizure engine control is taken over automatically by an alternate electric circuit

exemple 140 The flight control system has provisions to disconnect the part of the control system that becomes blocked. — Fcom boeing 737 .the columns and wheels are connected through transfer mechanisms which allow the pilots to bypass a jammed control or surface . elevator control column override mechanism .in the event of a control column jam an override mechanism allows the control columns to be physically separated applying force against the jam will breakout either the captain's or first officer's control column whichever column moves freely after the breakout can provide adequate elevator control .. aileron transfer mechanism .if the ailerons or spoilers are jammed force applied to the captain's and the first.officer's control wheels will identify which system ailerons or spoilers is usable.and which control wheel captain's or first officer's can provide roll control if the aileron control system is jammed force applied to the first officer's control wheel provides roll control from the spoilers the ailerons and the captain's control wheel are inoperative if the spoiler system is jammed force applied to the captain's control wheel provides roll control from the ailerons the spoilers and the first officer's control wheel are inoperative . rudder .the rudder provides yaw control about the airplane's vertical axis each set of rudder pedals is mechanically connected by cables to the input levers.of the main and standby rudder pcus the main pcu consists of two independent input rods two individual control valves and two separate actuators one for hydraulic system a and one for hydraulic system b the standby rudder pcu is controlled by a separate input rod and control valve and powered by the standby hydraulic system all three input rods have individual jam override mechanisms that allows input commands to continue to be transferred to the remaining free.input rods if an input rod or downstream hardware is hindered or jammed The flight control system has provisions to disconnect the part of the control system that becomes blocked.

A flight control surface actuator is said to be 'irreversible' when ?

Question 36-3 : There is no feedback to the pilot's controls of the aerodynamic forces acting on the control surface the pilot does not feel any force when moving that control surface in flight there is a need to lock the flight controls on the ground the flight control system has an alternate means of control in case of a control jam

exemple 144 There is no feedback to the pilot's controls of the aerodynamic forces acting on the control surface. — An irreversible flight control system is where there is not a direct mechanical linkage connection between the control lever in the cockpit and the flight control surface in an irreversible mechanical system the control lever in the cockpit moves a spool valve on a hydraulic power control unit pcu . a mechanical linkage drives the spool the mechanical linkage will consist of a combination of bellcranks pushrods cable systems pogos summing linkages etc the design of a mechanical irreversible system is similar to the design of a reversible flight control system the main difference will be the spool forces are better defined than surface hinge moments . also an artificial feel system is required for irreversible flight control systems because there is no feedback to the pilot's controls of the aerodynamic forces acting on the control surface There is no feedback to the pilot's controls of the aerodynamic forces acting on the control surface.

Given an aeroplane with irreversible primary flight controls how is control ?

Question 36-4 : The remaining systems will take over control sufficient reserve hydraulic fluid is available to compensate the effects of the leak by switching the flight control system to the reversible mode by switching to manual back up mode

exemple 148 The remaining systems will take over control. — The remaining systems will take over control.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 36-5 : I is incorrect ii is incorrect i is correct ii is incorrect i is correct ii is correct i is incorrect ii is correct

exemple 152 I is incorrect, ii is incorrect. — There is no need for a gust lock on irreversible flight controls because the hydraulic actuators will be in hydraulic lock therefore the control surface will not move . 852.look at the left and right ailerons of this airbus a330 irreversible flight controls they both are down and in locked postion as for the elevator . manual flight controls means reversible flight controls you need a gust lock systems inside the aircraft and outside . 848 I is incorrect, ii is incorrect.

The reason for a double switch on the elevator trim is ?

Question 36-6 : To reduce the probability of a trim runaway to prevent both pilots from performing opposite trim inputs because there are two trim motors to be able to use two different trim speeds slow trim rate at high speed and high trim rate at low speed

exemple 156 To reduce the probability of a trim runaway. — To reduce the probability of a trim runaway.

A flight control surface actuator is said to be 'reversible' when ?

Question 36-7 : There is feedback to the pilot's controls of the aerodynamic forces acting on the control surface the pilot does not feel any force when moving that flight control surface in flight there is a need to have an artificial feel system the flight control system has an alternate means of control in case of a control jam

exemple 160 There is feedback to the pilot's controls of the aerodynamic forces acting on the control surface. — There is feedback to the pilot's controls of the aerodynamic forces acting on the control surface.

For a jar25 aeroplane spoilers are ?

Question 36-8 : Upper wing surface devices their deflection can be symmetrical or asymmetrical lower wing surface devices their deflection can be symmetrical or asymmetrical upper wing surface devices their deflection is always asymmetrical lower wing surface devices their deflection is always asymmetrical

exemple 164 Upper wing surface devices, their deflection can be symmetrical or asymmetrical. — Upper wing surface devices, their deflection can be symmetrical or asymmetrical.

Which of these statements regarding most gust lock systems is correct ?

Question 36-9 : When the gust lock is on there is protection to prevent take off a gust lock is only fitted on the elevator and the rudder a gust lock can be used in flight to reduce the effect of turbulence on reversible flight controls there is no need for a gust lock

exemple 168 When the gust lock is on there is protection to prevent take-off. — When the gust lock is on there is protection to prevent take-off.

The expression 'secondary flight control' applies to the .1 stabiliser.2 ?

Question 36-10 : 1 3 1 2 3 4 2 4 2 3

exemple 172 1, 3. — In addition to the primary flight controls for roll pitch and yaw there are often secondary controls available to give the pilot finer control over flight or to ease the workload the most commonly available control is a wheel or other device to control stabiliser trim so that the pilot does not have to maintain constant backward or forward pressure to hold a specific pitch attitude other types of trim for rudder and ailerons are common on larger aircraft but may also appear on smaller ones . many aircraft have wing flaps controlled by a switch or a mechanical lever or in some cases are fully automatic by computer control which alter the shape of the wing for improved control at the slower speeds used for takeoff and landing other secondary flight control systems may be available including slats spoilers and air brakes 1, 3.

Ruddertrim adjustment in an aeroplane with irreversible flight controls is ?

Question 36-11 : An adjustment of the zero force rudder position an adjustment of the rudder ratio changer an adjustment of the rudder trim tab unnecessary because this aeroplane does not need rudder trim

exemple 176 An adjustment of the zero force rudder position. — .your flight controls are subjected to aerodynamic forces light aircraft will always have trim for the elevator to reduce these forces but as you climb out at low speed and high power you will have to apply a lot of leg force and hold in a lot of rudder right rudder on most aircraft due to right hand rotation of the propeller if you had a rudder trim you would adjust it until the force was zero .the question is about a fully powered rudder control irreversible there is no mechanical connection between rudder pedals and rudder the pilot is provided with artificial feel/force and when trimmed this is adjusted to give zero force on the pedals a conventional trim tab would have no feedback to the pilot because of the design of irreversible controls An adjustment of the zero force rudder position.

Which of these statements about trimming in a irreversible flight control ?

Question 36-12 : I is correct ii is correct i is incorrect ii is incorrect i is correct ii is incorrect i is incorrect ii is correct

.irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit .reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface .here we are talking about an irreversible flight control system.on a conventional aeroplane using an irreversible flight control system e g b737 ng with variable incidence trimming tailplane the trim is achieved by changing the full elevator deflection the zero force position of the control column does not change .for the aileron trim a variable incidence wing system does not exist on commercial airplane you can not 'trim' the wing thus when trimmed the control wheel will be biased to the right or to the left artificially and the zero force position of the control wheel will change

Which of these statements about trimming in a irreversible flight control ?

Question 36-13 : I is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct

exemple 184 I is incorrect, ii is incorrect. — .irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit .reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface .here we are talking about an irreversible flight control system.on a conventional aeroplane using an irreversible flight control system e g b737 ng with variable incidence trimming tailplane the trim is achieved by changing the full elevator deflection the zero force position of the control column does not change .for the aileron trim a variable incidence wing system does not exist on commercial airplane you can not 'trim' the wing thus when trimmed the control wheel will be biased to the right or to the left artificially and the zero force position of the control wheel will change I is incorrect, ii is incorrect.

Which of these statements about trimming in a irreversible flight control ?

Question 36-14 : I is correct ii is incorrect i is incorrect ii is incorrect i is correct ii is correct i is incorrect ii is correct

Cabin pressure is controlled by ?

Question 36-15 : Delivering a substantially constant flow of air into the cabin and controlling the outflow controlling the flow of air into the cabin with a constant outflow the cabin air re circulation system the cabin air mass flow control inlet valve s

exemple 192 Delivering a substantially constant flow of air into the cabin and controlling the outflow. — Delivering a substantially constant flow of air into the cabin and controlling the outflow.

During level flight at a constant cabin pressure altitude which could be ?

Question 36-16 : Partially open at the pre set position for take off fully closed until the cabin climbs to a selected altitude fully closed until the cabin descends to a selected altitude

exemple 196 Partially open. — Cabin altitude is the pressure altitude inside the pressurized zone of the fuselage it is expressed in 'altitude' generally in feet rather than with a unit of pressure in hectopascal for example .the cabin pressure is regulated like this .constant inlet flow regulation by air conditioning valves variable output flow action of the relief valves . 853 Partially open.

The cabin pressure is regulated by the ?

Question 36-17 : Outflow valve air cycle machine air conditioning pack cabin inlet airflow valve

exemple 200 Outflow valve. — Cabin altitude is the pressure altitude inside the pressurized zone of the fuselage it is expressed in 'altitude' generally in feet rather than with a unit of pressure in hectopascal for example .the cabin pressure is regulated like this .constant inlet flow regulation by air conditioning valves variable output flow action of the relief valves . 853 Outflow valve.

Cabin differential pressure means the pressure difference between ?

Question 36-18 : Cabin pressure and ambient air pressure cockpit and passenger cabin cabin pressure and ambient air pressure at mean sea level msl actual cabin pressure and selected pressure

exemple 204 Cabin pressure and ambient air pressure. — Cabin pressure and ambient air pressure.

Under normal conditions easa cs 25 the cabin pressure altitude is not allowed ?

Question 36-19 : 8000 ft 4000 ft 10000 ft 6000 ft

exemple 208 8000 ft. — Pressurisation .cs 25 841 pressurised cabins. a pressurised cabins and compartments to be occupied must be equipped to provide a cabin pressure altitude of not more than 2438 m 8000 ft at the maximum operating altitude of the aeroplane under normal operating conditions if certification for operation over 7620 m 25 000 ft is requested the aeroplane must be able to maintain a cabin pressure altitude of not more than 4572 m 15 000 ft in the event of any reasonably probable failure or malfunction in the pressurisation system 8000 ft.

Cabin altitude is the ?

Question 36-20 : Cabin pressure expressed as altitude altitude at maximum differential pressure difference in height between the cabin floor and ceiling flight level at which the aeroplane is flying

exemple 212 Cabin pressure expressed as altitude. — Cabin altitude is the pressure altitude inside the pressurized zone of the fuselage it is expressed in 'altitude' generally in feet rather than with a unit of pressure in hectopascal for example .the cabin pressure is regulated like this .constant inlet flow regulation by air conditioning valves variable output flow action of the relief valves Cabin pressure expressed as altitude.

On a modern large pressurized transport aircraft the maximum cabin differential ?

Question 36-21 : 7 9 psi 3 5 psi 13 15 psi 22 psi

The 'cabin differential pressure' is ?

Question 36-22 : Cabin pressure minus ambient pressure approximately 5 psi at maximum approximately 15 psi at maximum the pressure differential between the air entering and leaving the cabin

exemple 220 Cabin pressure minus ambient pressure. — Cabin pressure minus ambient pressure.

The cabin rate of descent is ?

Question 36-23 : A cabin pressure increase a cabin pressure decrease is not possible at constant airplane altitudes always the same as the airplane's rate of descent

exemple 224 A cabin pressure increase. — As we climb the cabin altitude 'climbs' to 6000ft/8000ft when the aircraft altitude climbs to fl260/fl410 .the cabin pressure is reducing from ground pressure mean 1013 hpa to less than 750 hpa in cruising flight .thus while descending cabin rate of descent is a cabin pressure increase A cabin pressure increase.

The maximum cabin differential pressure of a pressurised aeroplane operating at ?

Question 36-24 : 9 psi 3 psi 13 psi 15 psi

exemple 228 9 psi. — Typically there will be two gauges in the cockpit one to show the cabin's rate of climb the small one looks like a vsi vertical speed indicator and the other with two needles . one for the inner scale indicates cabin altitude in feet . one for the outer scale indicates differential pressure between cabin and ambient in psi . 855.the value 9 psi must be known this is a common value on jet aircrafts 9 psi.

The purpose of the pack cooling fans in the air conditioning system is to ?

Question 36-25 : Supply the heat exchangers with cooling air during slow flights and ground operation cool the apu compartment supply the passenger service unit psu with fresh air supply the heat exchangers with cooling air during cruise flight

exemple 232 Supply the heat exchangers with cooling air during slow flights and ground operation. — Supply the heat exchangers with cooling air during slow flights and ground operation.

In flight the cabin air for modern airplanes with jet engines is usually ?

Question 36-26 : Engine compressors ram air intakes piston compressors single radial compressors

exemple 236 Engine compressors. — Engine compressors.

In an aircraft air conditioning system the air cannot be treated for ?

Question 36-27 : Humidity purity pressure temperature

exemple 240 Humidity. — Modern air conditioning systems will mix the hot and cold air in a more efficient manner thus humidity control systems are not required anymore today we do not treat the air for humidity .water is removed from the conditioned air by the water separator but it is not controlled .more over actual humidity treatements are responsible for the legionary disease and are therefore forbidden in such cases Humidity.

In a cabin air conditioning system equipped with a bootstrap the mass air flow ?

Question 36-28 : Secondary heat exchanger outlet to the turbine inlet of the cold air unit turbine outlet of the cold air unit to the primary heat exchanger inlet compressor outlet of the cold air unit to the primary heat exchanger inlet secondary heat exchanger outlet to the compressor inlet of the cold air unit

exemple 244 Secondary heat exchanger outlet to the turbine inlet of the cold air unit. — Bootstrap or turbo compressor uses a primary heat exchanger for pre cooling against the ambient air temperature .the compressor section of the cooling turbine to boost pressure and temperature to provide a significant pressure drop a secondary heat exchanger which also uses outside air as a coolant to remove the unwanted temperature rises across the compressor and the expansion turbine wich extracts work from the air by driving the compressor . 856.the term bootstrap refers to a self sustaining process that proceeds without external help Secondary heat exchanger outlet to the turbine inlet of the cold air unit.

Engine bleed air used for air conditioning and pressurization in turbo jet ?

Question 36-29 : Compressor section turbine section fan section by pass ducting

exemple 248 Compressor section. — If the engine has a fan then the air will be taken from the compressor not the fan section Compressor section.

In large modern aircraft in the air conditioning system reduction of air ?

Question 36-30 : An expansion turbine a compressor an evaporator a condenser

exemple 252 An expansion turbine. — Bootstrap or turbo compressor uses a primary heat exchanger for pre cooling against the ambient air temperature .the compressor section of the cooling turbine to boost pressure and temperature to provide a significant pressure drop a secondary heat exchanger which also uses outside air as a coolant to remove the unwanted temperature rises across the compressor and the expansion turbine wich extracts work from the air by driving the compressor . 856.the goal of a bootstrap system is to distribute suitable air to the cabin engine bleed air is compressed passed through a heat exchanger cooled and then across an expansion turbine An expansion turbine.

A turbo compressor air conditioning system bootstrap system will ?

Question 36-31 : Cause a pressure drop as well as an associated temperature drop in the charge air not affect the charge air pressure increase charge air pressure whilst causing the temperature to drop in the heat exchanger decrease charge air pressure whilst causing the temperature to rise in the heat exchanger

exemple 256 Cause a pressure drop as well as an associated temperature drop in the charge air. — Img856.the goal of a bootstrap system is to distribute suitable air to the cabin engine bleed air is compressed passed through a heat exchanger cooled and then across an expansion turbine Cause a pressure drop as well as an associated temperature drop in the charge air.

Cabin heating in a large jet transport aeroplane is obtained from ?

Question 36-32 : Hot air bled from the compressors hot air bled from the turbines a fuel heater system an electrical heater system

exemple 260 Hot air bled from the compressors. — Cabin heating in a large jet transport aeroplane is obtained from hot air bled from the compressors via a 'bootstrap' system .bootstrap or turbo compressor uses a primary heat exchanger for pre cooling against the ambient air temperature .the compressor section of the cooling turbine to boost pressure and temperature to provide a significant pressure drop a secondary heat exchanger which also uses outside air as a coolant to remove the unwanted temperature rises across the compressor and the expansion turbine wich extracts work from the air by driving the compressor . 856.the term bootstrap refers to a self sustaining process that proceeds without external help Hot air bled from the compressors.

The pack cooling fan provides ?

Question 36-33 : Cooling air to the primary and secondary heat exchanger during slow flight and ground operation cooling air to the pre cooler air to the eyeball outlets at the passenger service unit psu cooling air to the primary and secondary heat exchanger during cruise

exemple 264 Cooling air to the primary and secondary heat exchanger during slow flight and ground operation. — Img857. 858.the ram air inlets have their deflector doors opened because the aircraft is on the ground . 859 Cooling air to the primary and secondary heat exchanger during slow flight and ground operation.

If the cabin altitude rises aircraft in level flight the differential pressure ?

Question 36-34 : Decreases remains constant increases may exceed the maximum permitted differential unless immediate preventative action is taken

exemple 268 Decreases. — Standard pressurisation profil . 860.if cabin altitude rises difference between the red line and the blue line will reduce the differential pressure decreases Decreases.

During a normal pressurised climb after take off ?

Question 36-35 : Cabin pressure decreases more slowly than atmospheric pressure the pressurisation system is inoperative until an altitude of 10000 feet is reached the cabin differential pressure is maintained constant absolute cabin pressure increases to compensate for the fall in pressure outside the aircraft

exemple 272 Cabin pressure decreases more slowly than atmospheric pressure — Cabin pressure decreases more slowly than atmospheric pressure

If the maximum operating altitude of an aeroplane is limited by the pressurized ?

Question 36-36 : Positive cabin differential pressure at maximum cabin altitude negative differential pressure at maximum cabin altitude positive cabin differential pressure at maximum operating ceiling negative cabin differential pressure at maximum operating ceiling

exemple 276 Positive cabin differential pressure at maximum cabin altitude. — An aircraft may be able to operate at for example fl450 but in order to respect a positive cabin differential pressure cabin pressure minus ambient pressure it could be limited at a lower level .9 0 psi is a comon value for maximum differential pressure on jet aircrafts .it is a positive value .cabin pressure at fl 390 = 10 psi 700 hpa .ambient pressure at fl 390 = 3 psi 200 hpa .differential pressure = cabin pressure ambient pressure = 10 3 = 7 psi .in this example the aircraft may climb to a higher level until it will be limited by the 9 0 psi maximum differential pressure Positive cabin differential pressure at maximum cabin altitude.

Main cabin temperature is ?

Question 36-37 : Controlled automatically or by flight crew selection not controllable at the maximum cabin differential pressure only controllable at maximum cabin differential pressure controlled by individual passenger

exemple 280 Controlled automatically, or by flight crew selection. — Controlled automatically, or by flight crew selection.

A warning device alerts the crew in case of an excessive cabin altitude this ?

Question 36-38 : 10000 ft 8000 ft 12000 ft 24000 ft

exemple 284 10000 ft. — Pressurisation .cs 25 841 pressurised cabins. a . b . 6 warning indication at the pilot or flight engineer station to indicate when the safe or pre set pressure differential and cabin pressure altitude limits are exceeded .appropriate warning markings on the cabin pressure differential indicator meet the warning requirement for pressure differential limits and an aural or visual signal in addition to cabin altitude indicating means meets the warning requirement for cabin pressure altitude limits if it warns the flight crew when the cabin pressure altitude exceeds 3048 m 10000 ft 10000 ft.

In a turbo compressor air conditioning system bootstrap system the main water ?

Question 36-39 : After the cooling turbine before the heat exchangers before the cooling turbine just after the heat exchangers

exemple 288 After the cooling turbine. — After the cooling turbine.

A turbo compressor air conditioning system bootstrap system includes two heat ?

Question 36-40 : P precools the engine bleed air s cools air behind the pack's compressor p warms up engine bleed air s recirculates the cabin air reducing its temperature p warms up engine bleed air s increases the temperature of air originating from the compressor of the pack p cools the engine bleed air s increases the temperature of the air used for air conditioning of cargo compartment animals

exemple 292 P: precools the engine bleed air, s: cools air behind the pack's compressor. — Bootstrap or turbo compressor uses a primary heat exchanger for pre cooling against the ambient air temperature .the compressor section of the cooling turbine to boost pressure and temperature to provide a significant pressure drop a secondary heat exchanger which also uses outside air as a coolant to remove the unwanted temperature rises across the compressor and the expansion turbine wich extracts work from the air by driving the compressor . 856.the term bootstrap refers to a self sustaining process that proceeds without external help P: precools the engine bleed air, s: cools air behind the pack's compressor.

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1399 Free Training Exam Other source study: Furious atpl examen 36