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TECHGEN-SB-AIRFRAME-MODULE1-TEST&LEARN
1.
The maximum cabin differential pressure of a pressurised aeroplane operating at FL370 is approximately:
a) 9.0 ps
b) 15.5 psi
c) 3.5 psi
d) 13.5 psi
2.
Pneumatic mechanical ice protection system are mainly used for:
a) propellers.
b) wings
c) pitot tubes.
d) windscreens.
3.
On most transport jet aircraft, the low pressure pumps of the fuel system are supplied with electric power of the following type:
a) 115 V DC
b) 115 V A
c) 28 V AC
d) 28 V DC
4.
The types of fuel tanks used on most modern transport aircraft are:
a) Cell tanks.
b) Fixed built-in tanks.
c) Integral tanks
d) Combined fuel tanks.
5.
Cabin air for a large airplane, during flight:
a) has an increased oxygen ratio.
b) is temperature controlled
c) has a constant oxygen ratio regulated to a preset value.
d) has a reduced oxygen ratio.
6.
When air is compressed for pressurization purposes, the percentage oxygen content is:
a) dependent on the degree of pressurisation.
b) decreased.
c) increased.
d) unaffected
7.
Engine bleed air used for air conditioning and pressurization in turbo-jet aeroplanes is usually taken from the:
a) by-pass ducting.
b) fan section.
c) compressor section
d) turbine section.
8.
The type of brake unit found on most transport aeroplanes is a:
a) Drum type brake.
b) Multiple disk brake
c) Belt brake.
d) Single disk brake.
9.
In flight, a cantilever wing of an airplane containing fuel undergoes vertical loads which produce a bending moment:
a) equal to half the weight of the aircraft multiplied by the semi span
b) highest at the wing roo
c) lowest at the wing root
d) equal to the zero -fuel weight multiplied by the span
10.
The reason for fitting thermal plugs to aircraft wheels is that they:
a) prevent the brakes from overheating.
b) release air from the tyre in the event of overpressure.
c) release air from the tyre in the event of overheating
d) prevent heat transfer from the brake disks to the tyres.
11.
The trim tab:
a) increases hinge moment and control surface efficiency.
b) reduces hinge moment and control surface efficiency
c) reduces hinge moment and increases control surface efficiency.
d) increases hinge moment and reduces control surface efficiency.
12.
The purpose of a trim tab (device) is to:
a) reduce or to cancel control forces
b) trim the aeroplane during normal flight.
c) lower manoeuvring control forces.
d) trim the aeroplane at low airspeed.
13.
A torsion link assembly is installed on the landing gear to:
a) control the wheels.
b) avoid rotation of the piston rod relative to the gear oleo strut
c) absorb the spring tension.
d) lock the landing gear.
14.
In a commercial transport aircraft the landing gear operating system is usually:
a) Electrically driven.
b) Hydraulically driven
c) Mechanically driven.
d) Pneumatically driven.
15.
Generally, on modern jet transport aircraft, how can the landing gear be extended if there is a complete hydraulic system failure.
a) By hydraulic accumulators.
b) Electrically.
c) Mechanicall
d) Pneumatically.
16.
Thermal plugs are installed in:
a) cabin windows.
b) fire warning systems.
c) cargo compartments.
d) wheel rims
17.
The advantages of fly-by-wire control are:
1. reduction of the electric and hydraulic power required to operate the control surfaces.
2. lesser sensitivity to lightning strike.
3. direct and indirect weight saving through simplification of systems.
4. immunity to different interfering signals.
5. improvement of piloting quality throughout the flight envelope.
The combination regrouping all the correct statements is:
a) 1 and 2
b) 3 and
c) 3, 4 and 5
d) 1 and 5
18.
An artificial feel unit is necessary in the pitch channel when:
a) the elevators are fitted with servo-tabs or trim tabs.
b) the elevators are actuated by reversible servo-control units.
c) the elevators are actuated by irreversible servo-control units
d) there is a trimmable stabilizer.
19.
Hydraulic fluids must have the following characteristics:
1. thermal stability.
2. low emulsifying characteristics.
3. corrosion resistant.
4. good resistance to combustion.
5. high compressibility.
6. high volatility.
7. high viscosity.
The combination regrouping all the correct statements is:
a) 1, 2, 5, 7
b) 1, 2, 3,
c) 2, 3, 4, 5
d) 1, 3, 4, 6
20.
In a hydraulic braking system, an accumulator is pre-charged to 1200 psi. An electrically driven hydraulic pump is started and provides a system pressure of 3000 psi. The hydraulic pressure gauge which is connected to the gas section of the accumulator, reads:
a) 4200 psi
b) 3000 ps
c) 1200 psi
d) 1800 psi
21.
In a hydraulic system overheat detectors are mostly installed:
a) at the pumps
b) at the actuators.
c) in the reservoirs.
d) at the coolers.
22.
Hydraulic fluids:
a) Do not require special care.
b) Cause high fire risk.
c) Are irritating to eyes and skin and cause high fire risk.
d) Are irritating to eyes and skin
23.
Hydraulic fluids used in systems of large modern airliners are:
a) Phosphate ester base fluids
b) Mineral base fluids.
c) Water base fluids.
d) Vegetable base fluids.
24.
The type of hydraulic oil used in modern hydraulic systems is:
a) mixture of mineral oil and alcohol
b) synthetic oi
c) mineral oil
d) vegetable oil
25.
Hydraulic power is a function of:
a) Pump RPM only.
b) System pressure and volume flow
c) System pressure and tank capacity.
d) Pump size and volume flow.
26.
Large transport aeroplane hydraulic systems usually operate with a system pressure of approximately:
a) 2000 psi
b) 3000 ps
c) 4000 psi
d) 1000 psi
27.
In hydraulic systems of large modern transport category aircraft the fluids used are:
a) Vegetable oil.
b) Mineral oil.
c) Water and glycol.
d) Synthetic oil
28.
In a modern hydraulic system, "hydraulic fuses" can be found. Their function is:
a) To isolate a part of the system and protect it against accidental pollution.
b) To switch to the secondary system in case of a leak in the primary brake system.
c) To allow by-passing of a hydraulic pump in case it is subject to excessive pressure, without further damage to the system.
d) To prevent total system loss in case of a leaking hydraulic line
29.
In a hydraulic system, the reservoir is pressurized in order to:
a) reduce fluid combustibility
b) seal the system
c) keep the hydraulic fluid at optimum temperature
d) prevent pump cavitatio
30.
Shuttle valves will automatically:
a) switch hydraulically operated units to the most appropriate pressure supply
b) reduce pump loads.
c) shut down systems which are overloaded.
d) guard systems against overpressure.
31.
One of the functions of an accumulator in a hydraulic system is:
a) to damp pressure surges in the system
b) to store fluid.
c) to store pressure.
d) to act as a pressure relief valve.
32.
If the cabin altitude rises (aircraft in level flight), the differential pressure:
a) decrease
b) increases
c) may exceed the maximum permitted differential unless immediate preventative action is taken.
d) remains constant
33.
The purpose of the cabin pressure controller, in the automatic mode, is to perform the following functions:
1. control of cabin altitude,
2. control of cabin altitude rate-of-change,
3. limitation of differential pressure,
4. balancing aircraft altitude with cabin altitude,
5. cabin ventilation,
6. keeping a constant differential pressure throughout all the flight phases. The combination regrouping all the correct statements is:
a) 5, 6, 1
b) 4, 5, 3
c) 1, 2,
d) 2, 6, 4
34.
Assuming cabin differential pressure has reached the required value in normal flight conditions, if flight altitude and air conditioning system setting are maintained:
a) the pressurisation system ceases to function until leakage reduces the pressure.
b) the outflow valves will move to the fully open position.
c) the mass air flow through the cabin is constant
d) the outflow valves will move to the fully closed position.
35.
During a normal pressurised climb after take-off:
a) the cabin differential pressure is maintained constant
b) absolute cabin pressure increases to compensate for the fall in pressure outside the aircraft
c) the pressurisation system is inoperative until an altitude of 10 000 feet is reached
d) cabin pressure decreases more slowly than atmospheric pressur
36.
(For this question use annex 021-786A- PRECEDING SLIDE) In a pressurized aircraft whose cabin altitude is 8000 ft, a crack in a cabin window makes it necessary to reduce the differential pressure to 5 psi. The flight level to be maintained in order to keep the same cabin altitude is:
a) FL 340
b) FL 23
c) FL 180
d) FL 280
37.
Main cabin temperature is:
a) Only controllable at maximum cabin differential pressure.
b) controlled by individual passenger.
c) not controllable at the maximum cabin differential pressure.
d) controlled automatically, or by flight crew selection
38.
The purpose of cabin air flow control valves in a pressurization system is to:
a) discharge cabin air to atmosphere if cabin pressure rises above the selected altitude.
b) Maintain a constant and sufficient mass air flow to ventilate the cabin and minimise cabin pressure surges
c) regulate cabin pressure at the maximum cabin pressure differential.
d) regulate cabin pressure to the selected altitude.
39.
Cabin pressure is controlled by:
a) controlling the flow of air into the cabin with a constant outflow.
b) the cabin air mass flow control inlet valve(s).
c) delivering a substantially constant flow of air into the cabin and controlling the outflow
d) the cabin air re-circulation system.
40.
During level flight at a constant cabin pressure altitude (which could be decreased, even at this flight level), the cabin outflow valves are:
a) fully closed until the cabin climbs to a selected altitude.
b) At the pre-set position for take-off.
c) Partially open
d) Fully closed until the cabin descends to a selected altitude.
41.
The cabin pressure is regulated by the:
a) Air conditioning pack.
b) Air cycle machine.
c) Outflow valve
d) Cabin inlet airflow valve.
42.
Cabin pressurization is controlled by the:
a) cabin outflow valve
b) cabin inlet airflow.
c) engine's RPM.
d) engine's bleed valves.
43.
Cabin differential pressure means the pressure difference between:
a) cockpit and passenger cabin.
b) actual cabin pressure and selected pressure.
c) cabin pressure and ambient air pressure at MSL.
d) cabin pressure and ambient air pressure
44.
Under normal conditions (JAR 25) the cabin pressure altitude is not allowed to exceed:
a) 6000 ft
b) 8000 f
c) 4000 ft
d) 10000 ft
45.
Cabin altitude means the:
a) cabin pressure expressed as altitude
b) flight level the aircraft is flying at.
c) flight level altitude at maximum differential pressure.
d) difference in height between the cabin floor and ceiling.
46.
On a modern large pressurized transport aircraft, the maximum cabin differential pressure is approximately:
a) 3 - 5 psi
b) 7 - 9 ps
c) 22 psi
d) 13 - 15 psi
47.
On most modern airliners the cabin pressure is controlled by regulating the:
a) RPM of the engine.
b) Bleed air valve.
c) Airflow leaving the cabin
d) Airflow entering the cabin.
48.
If the maximum operating altitude of an airplane is limited by the pressurized cabin, this limitation is due to the maximum:
a) Positive cabin differential pressure at maximum operating ceiling.
b) Negative cabin differential pressure at maximum operating ceiling.
c) Positive cabin differential pressure at maximum cabin altitude
d) Negative differential pressure at maximum cabin altitude.
49.
The "cabin differential pressure" is:
a) the pressure differential between the air entering and leaving the cabin.
b) approximately 5 psi at maximum.
c) cabin pressure minus ambient pressure
d) approximately 15 psi at maximum.
50.
The cabin rate of descent:
a) is always the same as the airplane's rate of descent.
b) results in a cabin pressure decrease.
c) is not possible at constant airplane altitudes.
d) results in a cabin pressure increase
51.
The purpose of the pack cooling fans in the air conditioning system is to:
a) supply the Passenger Service Unit (PSU) with fresh air.
b) supply the heat exchangers with cooling air during slow flights and ground operation
c) cool the APU compartment.
d) supply the heat exchangers with cooling air during cruise flight.
52.
Generally, for large aeroplanes, electrical heating for ice protection is used on:
a) pitot tubes
b) elevator leading edges.
c) slat leading edges.
d) fin leading edges.
53.
In flight, the cabin air for modern airplanes with jet engines is usually supplied by:
a) ram air intakes.
b) engine compressors
c) piston compressors.
d) single radial compressors.
54.
Cabin air for modern aircraft is usually taken from:
a) the low pressure compressor and from the high pressure compressor if necessary
b) the second fan stage.
c) the high pressure compressor.
d) the low pressure compressor.
55.
In an aircraft air conditioning system the air cannot be treated for:
a) pressure.
b) purity.
c) temperature.
d) humidity
56.
On modern transport aircraft, cockpit windows are protected against icing by:
a) Vinyl coating.
b) Rain repellent system.
c) Electric heating
d) Anti-icing fluid.
57.
On most transport aircraft, the low pressure pumps of the fuel system are:
a) centrifugal pumps, driven by an electric motor
b) removable only after the associated tank has been emptied.
c) electro-mechanical wobble pumps, with self-regulated pressure.
d) mechanically driven by the engine's accessory gearbox.
58.
The fuel supply system on a jet engine includes a fuel heating device, upstream of the main fuel filter so as to:
a) ease low pressure pumps work by increasing fuel fluidity.
b) maintain and improve fuel heating power.
c) prevent fuel from freezing in fuel pipes due to low temperatures at high altitude.
d) prevent, at low fuel temperature, the risk of ice formation from water contained in the fuel
59.
The fuel cross-feed system:
a) is only used to feed an engine from the tank of the opposite wing.
b) is only used on the ground for fuel transfer from one tank to another.
c) is only used in flight for fuel transfer from one tank to another.
d) allows feeding of any engine from any fuel tank
60.
The purpose of baffles in an aeroplane's integral fuel tank is to:
a) prevent mixture of the fuel and hydraulic fluid.
b) prevent overpressure in the tank.
c) prevent the fuel from flowing in the vent lines.
d) restrict the fuel movements in the tank
61.
On a transport type aircraft the fuel tank system is vented through:
a) Ram air scoops on the underside of the wing
b) The return lines of the fuel pumps.
c) Bleed air from the engines.
d) A pressure regulator in the wing tip.
62.
The purpose of baffle check valves fitted in aircraft fuel tanks is to:
a) close the vent lines in case of turbulence.
b) prevent fuel movement to the wing tip
c) damp out movement of the fuel in the tank.
d) prevent positive pressure build up inside the tank.
63.
On most transport aircraft, the low pressure pumps of the fuel system are:
a) Diaphragm pumps.
b) Centrifugal pumps
c) Piston pumps.
d) Gear type pumps.
64.
The pressurization of fuel tanks is maintained by:
a) the fuel vent system
b) the fuel top off unit.
c) the fuel tank drains.
d) the fuel dump system.
65.
In a turbo compressor air conditioning system (bootstrap system), the purpose of the heat exchangers is to:
a) cool the bleed air in front and behind the compressor of the air cycle machine
b) allow a homogeneous temperature by mixing air flows from various air conditioning groups in operation.
c) allow a steady compressor outlet temperature.
d) cool bleed air before entering the complete pneumatic system.
66.
In a turbo compressor air conditioning system (bootstrap system), the main water separation unit is:
a) before the cooling turbine.
b) after the cooling turbine
c) just after the heat exchangers.
d) before the heat exchangers.
67.
A turbo compressor air conditioning system (bootstrap system) includes two heat exchangers; the primary exchanger (P) and the secondary exchanger (S). The functions of these heat exchangers are as follows:
a) P: warms up engine bleed air . S: recirculates the cabin air, reducing its temperature.
b) P: precools the engine bleed air. S: cools air behind the pack's compressor
c) P: pre-cools the engine bleed air. S: increases the temperature of the air used for air-conditioning of cargo compartment (animals).
d) P: warms up engine bleed air. S: increases the temperature of air originating from the compressor of the pack.
68.
The term "bootstrap", when used to identify a cabin air conditioning and pressurisation system, refers to the:
a) source of the charge air.
b) cold air unit (air cycle machine) arrangement
c) means by which pressurisation is controlled.
d) charge air across the inter-cooler heat exchanger.
69.
In a turbo compressor air conditioning system (bootstrap system) the supply of air behind the primary heat exchanger is:
a) passed across an expansion turbine, then directly to the heat exchanger.
b) compressed, passed through a heat exchanger, and then across an expansion turbine
c) compressed, then passed across an expansion turbine and finally across a heat exchanger.
d) passed across an expansion turbine, compressed and then passed through a heat exchanger.
70.
In a cabin air conditioning system, equipped with a bootstrap, the mass air flow is routed via the:
a) secondary heat exchanger outlet to the turbine inlet of the cold air unit
b) turbine outlet of the cold air unit to the primary heat exchanger inlet.
c) compressor outlet of the cold air unit to the primary heat exchanger inlet.
d) secondary heat exchanger outlet to the compressor inlet of the cold air unit.
71.
In an air cycle machine:
a) the temperature drop across the turbine is the main contributor to the cooling effect of the air cycle machine.
b) the turbine drives the compressor which provides pressurisation.
c) the turbine drives the compressor of the machine which causes a higher temperature, and so increases the second heat exchanger efficiency
d) the turbine increases the pressure of the air supply to the cabin.
72.
In large modern aircraft, in the air conditioning system, reduction of air temperature and pressure is achieved by:
a) an evaporator.
b) a condenser.
c) a compressor.
d) an expansion turbine
73.
In flight, the most commonly used anti-icing method for the wings of modern commercial aircraft fitted with turbo-jet units is:
a) Electrical (electrical resistances).
b) Physical/chemical (glycol-based liquid).
c) Thermal (use of hot air)
d) Mechanical (pneumatic source which acts by deforming the profiles of the leading edge).
74.
In a "bootstrap" cooling system, the charge air is first compressed in the cold air unit to:
a) ensure an adequate pressure and temperature drop across the cooling turbine
b) ensure an adequate charge air flow across the inter-cooler heat exchanger.
c) maintain a constant cabin mass air flow.
d) increase the cabin air supply pressure when the charge pressure is too low.
75.
With regard to pneumatic mechanical devices that afford ice protection the only correct statement is:
a) They can be used as both de-icing and anti-icing devices.
b) They can only be used as de-icing devices
c) They can only be used as anti-icing devices.
d) They are used extensively on modern aircraft as they are inexpensive and easy to maintain.
76.
A turbo compressor air conditioning system (bootstrap system) will:
a) cause a pressure drop as well as an associated temperature drop in the charge air
b) not affect the charge air pressure.
c) decrease charge air pressure whilst causing the temperature to rise in the heat exchanger.
d) increase charge air pressure whilst causing the temperature to drop in the heat exchanger.
77.
The cabin heating supply in a heavy jet transport aircraft is obtained from:
a) an electrical heater system.
b) a fuel heater system.
c) hot air coming from the engine's turbines.
d) hot air coming from the engine's compressors
78.
The pack cooling fan provides:
a) cooling air to the primary and secondary heat exchanger during cruise.
b) cooling air to the primary and secondary heat exchanger during slow flight and ground operation
c) air to the eyeball outlets at the Passenger Service Unit (PSU).
d) cooling air to the pre-cooler.
79.
Concerning electrically powered ice protection devices, the only true statement is:
a) on modern aeroplanes, electrically powered thermal devices are used as de-icing devices for pitot-tubes, static ports and windshield.
b) on modern aeroplanes, electrically powered thermal devices are used to prevent icing on small surfaces (pitot-static, windshield...)
c) on modern aeroplanes, electrically powered thermal devices are very efficient, therefore they only need little energy.
d) on modern aeroplanes, electrical power supply being available in excess, this system is very often used for large surfaces de-icing.
80.
The elements specifically protected against icing on transport aircraft are:
1) engine air intake and pod.
2) front glass shield.
3) radome.
4) pilot tubes and waste water exhaust masts.
5) leading edge of wing.
6) cabin windows.
7) trailing edge of wings.
8) electronic equipment compartment.
The combination regrouping all the correct statements is:
a) 1, 2, 3, 8
b) 1, 2, 5, 6
c) 1, 2, 4,
d) 1, 4, 5, 7
81.
The heating facility for the windshield of an aircraft is:
a) Harmful to the integrity of the windows in the event of a bird strike.
b) Used only at low altitudes where there is a risk of ice formation.
c) Used on a continual basis as it reduces the thermal gradients which adversely affect the useful life of the components
d) Only used when hot-air demisting is insufficient.
82.
A tubeless tyre is a tyre:
1. which requires solid or branched wheels.
2. whose valve can be sheared in sudden accelerations.
3. whose mounting rim must be flawless.
4. which requires no rim protection between rim flange and tire removing device.
5. which does not burst in the event of a tire puncture.
6. which eliminates internal friction between the tube and the tire.
The combination regrouping all the correct statements is:
a) 1, 5, 6
b) 1, 2, 5.
c) 2, 3, 6.
d) 3, 4, 5.
83.
On a jet aircraft fuel heaters are:
a) Installed in each tank.
b) not necessary at all.
c) Installed only in the centre tank.
d) Located on the engines
84.
The automatic fuelling shut off valve:
a) cuts off the fuel in case of engine fire.
b) stops fuelling as soon as a certain pressure is reached.
c) stops fuelling as soon as a certain fuel level is reached inside the tank
d) stops fuelling as soon as the fuel spills into the vent line.
85.
During re-fuelling the automatic shut-off valves will switch off the fuel supply system when:
a) the surge vent tank is filled.
b) fuelling system has reached a certain pressure.
c) there is fire.
d) the fuel has reached a predetermined volume or mass.+
021-980 a.gif
86.
(For this question use annex 021-980A- PRECEDING SLIDE) The diagram shown in annex represents a jet fuel system. The fuel-flow measurement is carried out:
a) in the fuel control unit (item 3).
b) after low pressure valve (item 1).
c) after high pressure pump first stage (item 2).
d) after high pressure valve (item 4)
87.
The wing of an aircraft in flight, powered by engines located under the wing, is subjected to a bending moment due to thrust and drag. The loading on the front spar of the torsion box from the wing root to the wing tip is:
a) compression.
b) tension, and then compression.
c) tension.
d) compression, and then tension
88.
When a landing gear wheel is hydroplaning, its friction factor is equal to:
a) 1
b) 0.1
c) 0.5
89.
The colour of a fresh synthetic hydraulic fluids is:
a) red.
b) blue.
c) purple
d) pink.
90.
An aircraft with a pressurized cabin is settled at its cruise level. During the flight, a malfunction of the pressure controller is detected by the crew and the cabin rate indicator reads -200ft/min. Given that: DELTA P: Differential pressure Zc: Cabin altitude
a) The crew has to intermittently cut off the incoming air flow in order to maintain a zero Zc.
b) The aircraft has to climb to a higher flight level in order to reduce Zc to its initial value.
c) A descent must be initiated to prevent the oxygen masks dropping when Zc reaches 14000ft.
d) DELTA P will rise up to its maximum value, thus causing the safety relief valves to open
91.
The purpose of stringers, used in fuselage construction, is to:
a) withstand the shear stresses.
b) assist the skin in absorbing the longitudinal traction-compression stresses
c) integrate the strains due to pressurization to which the skin is subjected and convert them into a tensile stress.
d) provide sound and thermal isolation.
92.
Landing gear torque links are used to:
a) maintain the compass heading throughout taxiing and take-off.
b) take up the lateral stresses to which the gear is subjected.
c) prevent the extension of the landing gear oleo strut rod.
d) prevent rotation of the landing gear piston in the oleo strut
93.
Shimmy occurs on the nose wheel landing gear during taxiing when:
1. the wheels tend to describe a sinusoidal motion on the ground
2. the wheels no longer respond to the pilot's actions
This effect is overcome by means of:
4. a damper associated with the steering cylinder
The combination of correct statements is:
a) 1, 4
b) 2, 3.
c) 2, 4.
d) 1, 3.
94.
The illumination of the green landing gear light indicates that the landing gear is:
a) locked-down and its door is locked.
b) not in the required position.
c) locked-down
d) in the required position.
95.
The function of an accumulator in a hydraulic brake system is:
a) to store the hydraulic energy recovered by the anti skid system to prevent wheel blocking.
b) to damp pressure fluctuations of the auto brake system.
c) to supply a limited amount of brake energy in case the hydraulic system normally powering the brakes does not function anymore
d) to function as a buffer to assist the hydraulic system during heavy braking.
96.
On a non-stressed skin type wing, the wing structure elements which take up the vertical bending moments Mx are:
a) the webs.
b) the spars
c) the skin.
d) the ribs.
97.
An aircraft with a pressurized cabin flies at FL 310 and, following a malfunction of the pressure controller, the outflow valve runs to the open position. Given :
CAB V/S : Cabin rate of climb indication
CAB ALT: Cabin pressure altitude
DELTA P: Differential pressure
This will result in a:
a) CAB V/S decrease, CAB ALT increase, DELTA P decrease
b) CAB V/S increase, CAB ALT increase, DELTA P decreas
c) CAB V/S decrease, CAB ALT decrease, DELTA P increase
d) CAB V/S increase, CAB ALT increase, DELTA P increase
98.
The modern anti-skid processes are based on the use of a computer whose input data is:
1. idle wheel speed (measured)
2. braked wheel speed (measured)
3. brake temperature (measured)
4. desired idle wheel train slipping rate
5. tire pressure
The combination regrouping all the correct statements is:
a) 2, 4.
b) 1, 3.
c) 1, 2, 4
d) 1, 2, 3, 4, 5.
99.
VLO is the maximum:
a) cruising speed not to be exceeded except in still air with caution.
b) speed at which the landing gear can be operated with full safety
c) speed with flaps extended in a given position.
d) flight speed with landing gear down.
100.
Among the different types of aircraft structures, the shell structures efficiently transmit the:
1. normal bending stresses
2. tangent bending stresses
3. torsional moment
4. shear stresses
The combination regrouping all the correct statements is:
a) 1, 2,
b) 1, 3, 4
c) 2, 3, 4
d) 1, 2, 4
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