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2. Sayfa - Toplam 3 Sayfa var BirinciBirinci 123 SonuncuSonuncu
Gösterilen sonuçlar: 11 ile 20 ve 25

Konu: Teknisyen Lisansi Ders Konulari

  1. #11
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    Kategori B1 lisansı
    sahibine lisansında ve yetkilendirme belgesinde belirtilen sınırlamalar dahilinde kalmak kaydıyla, hava aracının yapısı, motorları, mekanik ve elektriksel sistemleri üzerindeki hat bakım ve arıza giderme işlemleriyle hat bakımda aviyonik komponentlerin değiştirilmesi ve bu komponentlerin çalışır durumda olduğunu göstermek için yapılan basit testler sonrasında bakım çıkış sertifikası düzenleyebilme yetkisi verir.

    *Part 66’da hat ve hangar bakım olarak genişletildi.

    Kategori B1 lisansı,hava aracının motor yapısına göre aşağıdaki gibi sınıflandırılır:

    Alt kategori B1.1: Türbin motorlu uçaklar,

    2) Alt kategori B1.2: Piston motorlu uçaklar,

    3) Alt kategori B1.3: Türbin motorlu helikopterler,

    4) Alt kategori B1.4: Piston motorlu helikopterler.
    Konu turkishairliner tarafından (05.Aralık.2007 Saat 01:06 ) değiştirilmiştir. Sebep: Kısıtlamayı kaldırmak...

  2. #12
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    Kategori B2: Kategori B2 lisansı sahibine lisansında ve yetkilendirme belgesinde belirtilen sınırlamalar dahilinde kalmak kaydıyla, hava aracının aviyonik ve elektriksel sistemleri üzerindeki hat bakım ve arıza giderme işlemleri sonrasında bakım çıkış sertifikası düzenleyebilme yetkisi verir.




    Part 66’da hat ve hangar bakım olarak genişletildi.
    Konu turkishairliner tarafından (05.Aralık.2007 Saat 01:06 ) değiştirilmiştir. Sebep: Kısıtlamayı kaldırmak!..

  3. #13
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    Kategori C lisansı sahibine lisansında ve yetkilendirme belgesinde belirtilen sınırlamalar dahilinde kalmak kaydıyla, hava aracının hangar bakım işlemleri sonrasında bakım çıkış sertifikası düzenleyebilme yetkisi verir.

    Bu yetki hava aracının tüm sistemleriyle beraber tümü için geçerlidir.
    Konu turkishairliner tarafından (05.Aralık.2007 Saat 01:07 ) değiştirilmiştir. Sebep: Kısıtlamayı kaldırmak!..

  4. #14
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    SHY-66 LİSANSI İÇİN GEREKLİ HAVA ARACI BAKIM DENEYİMİ SÜRELERİ
    LİSANS KATEGORİSİ TEKNİK EĞİTİM DURUMU BAKIM DENEYİMİ SÜRESİ (YIL)
    A1,A2,A3,A4,B1.2 ,B1.4
    Teknik temel eğitimi yok 3
    *Kalifiye personel 2
    SHY/JAR-147 bakım eğitimini tamamladı. 1
    .................................................. .................................................. ....

    B 1.1, B1.3, B2
    Teknik temel eğitimi yok 5
    Kalifiye personel 3 yıl
    SHY/JAR-147 bakım eğitimini tamamladı. 2 yıl
    .................................................. .................................................. ....

    Geniş Gövde Hava Araçları C
    Kategori B1.1,B1.3 veya B2 lisanslı bakım personeli 3 yıl
    Kategori B1.2 veya B1.4 lisanslı bakım personeli 5 yıl
    ......................................
    Dar Gövde Hava Araçları C
    B1 veya B2 bakım personeli 3 yıl


    Yüksek Öğrenim Mezunları C Uçak,Uzay, makine, elektrik, elektronik, elektrik-elektronik, mekatronik mühendislikleri ile havacılıkla ilgili teknik bölümlerden mezun olmuş veya bunlara denkliği Yüksek Öğretim Kurulu tarafından onaylanmış yabancı fakülte veya yüksekokullardan mezun olmuş adaylar 3** yıl


    * Kalifiye personel: mekanik, elektrik veya elektronik cihazların imalat, tamir, bakım, servis, kontrol veya revizyonlarını kapsayan ve SHGM tarafından kabul edilen bir eğitim sürecini başarı ile tamamlayan personeldir.

    ** Altı aylık kısmı üs bakım incelemeleri olmak üzere bakım işlerinde planlama, kalite güvence, kayıt tutma, onaylı yedek parça kontrolü ya da SHY-M kapsamındaki mühendislik işlerinde çalışılmasına karşılık gelir.

  5. #15
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    Kategori C lisansı için ......mühendislikleri ile havacılıkla ilgili teknik bölümlerden mezun olmuş ...

  6. #16
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    A1 Lisansı( Türbin motorlu uçaklar),
    Sorumlu oldukları modüller


    1. Matematik
    2. Fizik
    3. Temel Elektrik
    5. Dijital Teknikleri / Elektronik Alet Sistemleri
    6. Malzeme ve Donanım
    7. Bakım Uygulamaları
    8. Temel Aerodinamik
    9. İnsan Faktörleri
    10. Havacılık Kanunları
    11. Uçak Aerodinamiği, Yapıları ve Sistemleri
    15. Gaz Türbinli Motor
    17. Pervane

  7. #17
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    B1.1 Lisansı (Türbin motorlu uçaklar)
    Sorumlu oldukları modüller
    1. Matematik
    2. Fizik
    3. Temel Elektrik
    4. Temel Elektronik
    5. Dijital Teknikleri / Elektronik Alet Sistemleri
    6. Malzeme ve Donanım
    7. Bakım Uygulamaları
    8. Temel Aerodinamik
    9. İnsan Faktörleri
    10. Havacılık Kanunları
    11. Uçak Aerodinamiği, Yapıları ve Sistemleri
    15. Gaz Türbinli Motor
    17. Pervane

  8. #18
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    B2 Aviyonik modülleri
    1. Matematik
    2. Fizik
    3. Temel Elektrik
    4. Temel Elektronik
    5. Dijital Teknikleri / Elektronik Alet Sistemleri
    6. Malzeme ve Donanım
    7. Bakım Uygulamaları
    8. Temel Aerodinamik
    9. İnsan Faktörleri
    10. Havacılık Kanunları
    13. Hava Aracı Aerodinamiği, Yapıları ve Sistemleri
    14. İtme (Propulsion)

  9. #19
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    Kategori C lisansı

    alacak personel Kategori B1 veya B2 nin ilgili bilgi seviyesine sahip olmak zorundadır.

    * İlk tip için ATA 104 Level 3 seviyesinde bir havaaracı tip eğitimi alması zorunludur. Diğerleri level 1.

  10. #20
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    Exclamation

    [
    [B]Module 8 questions [/B]

    COLOR="LightBlue"]airmech.co.uk forumundan bulmuştum. [/COLOR] kolay gelsin...

    where you can test your knowledge!
    Please try to answer the questions!

    1. Which statement is correct for a side slip condition at constant speed and side slip angle, where the geometric dihedral of an aeroplane is increased:

    A the stick force per g decreases
    B the required lateral control force increases
    C the required lateral control force does not change
    D the required lateral control force decreases

    2. Spoiler deflection causes:

    A an increase in drag and decrease in lift
    B a decrease in lift and drag
    C an increase in lift only
    D an increasse in lift and drag

    3. The value of the parasite drag in straight and level flight at constant weight varies linearly with:

    A square speed
    B speed
    C AOA
    D square AOA

    4. If you increase the propeller pitch during glide with idle powwer at constant IAS the lift to drag ratio will:

    A increase and the ROD will increase
    B decrease and the ROD will decrease
    C increase and the ROD will decrease
    D decrease and the ROD will increase

    5. Shoch induced seperation results in:

    A decreasing lift
    B decreasing drag
    C increasing lift
    D constant lift

    6. A deployed slat will:

    A increase the boundary layer energy, move the suction peak from the fixed part of the wing to the slat, the stall is postponed to higher AOA
    B increase the camber of the aerfoil and increase the effective AOA, peak so that Clmax is reached at higher AOA
    C decrease the boundary layer energy and decrease the suction peak in the slat, so that CL max is reached at lower AOA
    D increase the boundary layer energy and increase the suction peak on the fixed part of the wing, so that the stall is postponed to higher AOA

    7. The function of the slot between an extended slat and the leading edge of the wing is to:

    A reduce the wingloading
    B cause venturi effect which energizes the boundary layer
    C allow space for vibration of the slat
    D slow the air flow in the slot so that more pressure is created under the wing

    8. Jet: descend with constant mach and weight, operational limit that may be exceeded is:

    A Mmo
    B Vd
    C Vmo
    D Vne

    9. Which statement with respect to the climb is correct:
    D at constant IAS the mach number increases

    10. Winglets:

    A increase the manoevryability
    B decrease the static lateral stability
    C create an elliptical lift distrubution
    D decrease the induced drag

    11. An advantage of locating engines at the rear of the fuselage, in comparison to a location beneath on the wing is:

    A lighter wing construction
    B a wing is less sensitive to flutter
    C less influence on longitudinal control on thrust changes
    D easier maintenance of the engines

    12. Why is Vmcg determined with the nosewheel steering disconnected:

    A because the nosewheel steering has no effect on the value of Vmcg
    B because the nosewheel steering could become inoparative after an engine has failed
    C because it must be possible to abort the take off even after the nosewheel has already been lifted off the ground
    D because the value of Vmcg must also be applicable on wet and/or slippery runways

    13. Differential ailleron deflection:

    A is required to achieve the required roll rate
    B equals the drag of the right and left ailleron
    C increases Clmax
    D is required to keep the totall lift constant when aillerons are deflected

    14. Trailing edge flaps extended will:

    A increase the critical AOA and decrease the value of Clmax
    B decrease the critical AOA and decrease the value of Clmax
    C increase the critical AOA and increase the value of Clmax
    D decrease the critival AOA and increase the value of Clmax

    15. One of the requirements for dynamic stability is:

    A a large deflection range of the stabilizer trim
    B effective elavator
    C a small C.G range
    D positive static stability

    16. Tuck under is:

    A the tendency to nose down when the control colum is pulled back
    B shaking of the control colum at high mach numbers
    C the tendency to nose down when speed is increased into the transonic flight regime
    D the tendency to nose up when speed is increased into the transonic flight regime

    17. When comparing a rectangular wing and a swept wing, the swept wing has the advantage of:

    A higher critical mach number
    B increased longitudinal stability
    C lower stalling speed
    D greater strength

    18. Aeroplane drag in straight and level flight is lowest when:

    A parasite drag equals induced drag
    B parasite drag equals twice the induced drag
    C induced drag is lowest
    D induced drag is equal to zero

    19. Which statement about spin is correct:

    A an aeroplane is prone to spin when the stall starts at the wing root
    B everu aeroplane should be designed such that it can be never enter a spin
    C in the spin, airspeed continuously increase
    D during spin recovery aillerons should be kept neutral

    ,


    Module 8, Q1 - 50

    1. On a swept wing aircraft if both wing tip sections lose lift simultaneously the aircraft will
    a) roll
    b) pitch nose up
    c) pitch nose down

    2. Lift on a delta wing aircraft
    a) increases with an increased angle of incidence (angle of attack)
    b) decreases with an increase in angle of incidence (angle of attack)
    c) does not change with a change in angle of incidence (angle of attack)

    3. On a straight wing aircraft, stall commences at the
    a) root on a high thickness ratio wing
    b) tip on a high thickness ratio wing
    c) tip on a low thickness ratio wing

    4. On a high wing aircraft in a turn
    a) the up-going wing loses lift causing a de-stabilising effect
    b) the down-going wing gains lift causing a stabilising effect
    c) the down-going wing loses lift causing a de-stabilising effect

    5. For the same angle of attack, the lift on a delta wing
    a) is greater than the lift on a high aspect ratio wing
    b) is lower than the lift on a high aspect ratio wing
    c) is the same as the lift on a high aspect ratio wing

    6. The ISA
    a) is taken from the equator
    b) is taken from 45 degrees latitude
    c) assumes a standard day

    7. At higher altitudes as altitude increases, pressure
    a) decreases at constant rate
    b) increases exponentially
    c) decreases exponentially

    8. The thrust-drag couple overcomes the lift-weight couple. What direction of force is required to be produced by the tail of the aircraft to maintain straight and level flight
    a) upwards
    b) downwards
    c) sideways

    9. When the pressure is half of that at sea level, what is the altitude?
    a) 12,000 ft
    b) 8,000 ft
    c) 18,000 ft

    10. During a turn, the stalling angle
    a) increases
    b) decreases
    c) remains the same

    11. If gauge pressure on a standard day at sea level is 25 PSI, the absolute pressure is
    a) 10.3 PSI
    b) 43.8 PSI
    c) 39.7 PSI

    12. The C of G moves in flight. The most likely cause of this is
    a) movement of passengers
    b) movement of the centre of pressure
    c) consumption of fuel and oils

    13. The C of P is the point where
    a) all the forces on an aircraft act
    b) the three axis of rotation meet
    c) the lift can be said to act

    14. The three axis of an aircraft act through the
    a) C of G
    b) C of P
    c) stagnation point

    15. Pressure decreases
    a) proportionally with a decreases in temperature
    b) inversely proportional to temperature
    c) Pressure and temperature are not related

    16. As air gets colder, the service ceiling of an aircraft
    a) reduces
    b) increases
    c) remains the same

    17. What is sea level pressure?
    a) 1013.2 mb
    b) 1012.3 mb
    c) 1032.2 mb

    18. When the weight of an aircraft increases, the minimum drag speed
    a) decreases
    b) increases
    c) remains the same

    19. An aircraft will have
    a) less gliding distance if it has more payload
    b) more gliding distance if it has more payload
    c) the same gliding distance if it has more payload

    20. When an aircraft experiences induced drag
    a) air flows under the wing span-wise towards the tip and on top of the wing span-wise towards the root
    b) air flows under the wing span-wise towards the root and on top of the wing span-wise towards the tip
    c) Neither a) or b) since induced drag does not caused by span-wise flow

    21. At stall, the wingtip stagnation point
    a) moves toward the lower surface of the wing
    b) moves toward the upper surface of the wing
    c) doesn’t move

    22. How does IAS at the point of stall vary with height?
    a) It is practically constant
    b) It increases
    c) It decreases

    23. The rigging angle of incidence of an elevator is
    a) the angle between the mean chord line and the horizontal in the rigging position
    b) the angle between the bottom surface of the elevator and the horizontal in the rigging position
    c) the angle between the bottom surface of the elevator and the longitudinal datum

    24. What is the lapse rate with regard to temperature?
    a) 1.98°C per 1000 ft
    b) 1.98°F per 1000 ft
    c) 4°C per 1000 ft

    25. What happens to load factor as you decrease turn radius?
    a) It increases
    b) It decreases
    c) It remains constant

    26. If you steepen the angle of a banked turn without increasing airspeed or angle of attack, what will the aircraft do?
    a) It will remain at the same height
    b) It will sideslip with attendant loss of height
    c) It will stall

    27. An aircraft wing tends to stall first at
    a) the tip due to a higher ratio thickness/chord
    b) the tip due to a lower ratio thickness/chord
    c) the root due to a higher ratio thickness/chord

    28. Dihedral wings combat instability in
    a) pitch
    b) yaw
    c) sideslip

    29. To stop aircraft decreasing in height during a sideslip, the pilot can
    a) advance the throttle
    b) pull back on the control column
    c) adjust the rudder position

    30. What control surface movements will make an aircraft fitted with ruddervators yaw to the left?
    a) Left ruddervator lowered, right ruddervator raised
    b) Right ruddervator lowered, left ruddervator raised
    c) Both ruddervators raised

    31. When a leading edge slat opens, there is a gap between the slat and the wing. This is
    a) to allow it to retract back into the wing
    b) to allow air through to re-energize the boundary layer on top of the wing
    c) to keep the area of the wing the same

    32. Which of the following is true?
    a) Lift acts at right angles to the wing chord line and weight acts vertically down
    b) Lift acts at right angles to the relative airflow and weight acts vertically down
    c) Lift acts at right angles to the relative airflow and weight acts at right angles to the aircraft centre line

    33. If the wing tips stall before the root on a swept wing aircraft, the aircraft will
    a) roll
    b) pitch nose up
    c) pitch nose down

    34. Lift on a delta wing aircraft
    a) increases with an increased angle of incidence (angle of attack)
    b) decreases with an increase in angle of incidence (angle of attack)
    c) does not change with a change in angle of incidence (angle of attack)

    35. On a straight wing aircraft, stall commences at the
    a) root on a high thickness ratio wing
    b) tip on a high thickness ratio wing
    c) tip on a low thickness ratio wing

    36. On a high wing aircraft in a turn
    a) the up-going wing loses lift causing a de-stabilizing effect
    b) the down-going wing gains lift causing a stabilizing effect
    c) the down-going wing loses lift causing a de-stabilizing effect

    37. For the same angle of attack, the lift on a delta wing
    a) is greater than the lift on a high aspect ratio wing
    b) is lower than the lift on a high aspect ratio wing
    c) is the same as the lift on a high aspect ratio wing

    38. Standard sea level temperature is
    a) 0 degrees Celsius
    b) 15 degrees Celsius
    c) 20 degrees Celsius

    39. As altitude increases, pressure
    a) decreases at constant rate
    b) increases exponentially
    c) decreases exponentially

    40. Deployment of a split flap will
    a) increase wing area and increase drag
    b) pitch the nose down and decrease drag
    c) increase camber and increase drag

    41. Lapse rate usually refers to
    a) Pressure
    b) Density
    c) Temperature

    42. During a turn, the stalling angle
    a) increases
    b) decreases
    c) remains the same

    43. The vertical fin of a single engined aircraft is
    a) parallel with both the longitudinal axis and vertical axis
    b) parallel with the longitudinal axis but not the vertical axis
    c) parallel with the vertical axis but not the longitudinal axis

    44. Aircraft flying in the transonic range most often utilize
    a) sweptback wings
    b) advanced supercritical airfoils
    c) high wings

    45. Which type of flap changes the area of the wing?
    a) Fowler
    b) Split
    c) Slotted

    46. Forward swept wings tend to stall at the root first so the aircraft retains lateral control, so why are they never used on passenger aircraft?
    a) Because the wing tips wash in at high wing loads
    b) Because the wing tips wash out at high wing loads
    c) Because at high loads their angle of incidence increases and the loads imposed on the wing can increase until they destroy it

    47. What happens to air flowing at the speed of sound when it enters a converging duct?
    a) Velocity decreases, pressure and density increase
    b) Velocity increases, pressure and density decreases
    c) Velocity, pressure and density increase

    48. As the angle of attack of an airfoil increases the centre of pressure
    a) moves forward
    b) moves aft
    c) remains stationary

    49. An aircraft, which is longitudinally stable, will tend to return to level flight after a movement about which axis?
    a) Pitch
    b) Roll
    c) Yaw

    50. Vapour trails from the wingtips of an aircraft in flight are caused by
    a) low pressure above the wing and high pressure below the wing causing vortices
    b) high pressure above the wing and low pressure below the wing causing vortices
    c) low pressure above the wing and high pressure below the wing causing a temperature rise


    Module 8, Q51 - 95

    51. Vortex generators on the wing are most effective at
    a) high speed
    b) low speed
    c) high angles of attack

    52. The chord line of a wing is a line that runs from
    a) the centre of the leading edge of the wing to the trailing edge
    b) half way between the upper and lower surface of the wing
    c) one wing tip to the other wing tip

    53. The angle of incidence of a wing is an angle formed by lines
    a) parallel to the chord line and longitudinal axis
    b) parallel to the chord line and the lateral axis
    c) parallel to the chord line and the vertical axis

    54. The centre of pressure of an aerofoil is located
    a) 30 - 40% of the chord line back from the leading edge
    b) 30 - 40% of the chord line forward of the leading edge
    c) 50% of the chord line back from the leading edge

    55. Compressibility effect is
    a) drag associated with the form of an aircraft
    b) drag associated with the friction of the air over the surface of the aircraft
    c) the increase in total drag of an aerofoil in transonic flight due to the formation of shock waves

    56. Lateral control of an aircraft at high angle of attack can be maximised by using
    a) fences
    b) vortex generators
    c) wing slots

    57. Stall strips are always
    a) made of metal
    b) on the leading edge of a wing
    c) fitted forward of the ailerons

    58. Stall strips
    a) cause the wing root to stall
    b) cause the wing tip to stall
    c) cause the wings to stall symmetrically

    59. Due to the interference of the airflow on a high wing aircraft between the fuselage and the wings, the lateral stability of the aircraft in a gusty wind situation will cause
    a) the upper wing to increase its lift
    b) the upper wing to decrease its lift
    c) the lower wing to decrease its lift

    60. Slats
    a) reduce the stall speed
    b) reduce the tendency of the aircraft to Yaw
    c) decrease the aerofoil drag at high speeds

    61. A high aspect ratio wing will give
    a) high profile and low induced drag
    b) low profile and high induced drag
    c) low profile and low induced drag

    62. Aerofoil efficiency is defined by
    a) lift over drag
    b) drag over lift
    c) lift over weight

    63. An aircraft banks into a turn. No change is made to the airspeed or angle of attack. What will happen?
    a) The aircraft enters a sideslip and begins to lose altitude
    b) The aircraft turns with no loss of height
    c) The aircraft yaws and slows down

    64. The relationship between induced drag and airspeed is, induced drag is
    a) directly proportional to the square of the speed
    b) inversely proportional to the square of the speed
    c) directly proportional to speed

    65. What is the definition of Angle of Incidence?
    a) The angle the underside of the mainplane or tailplane makes with the horizontal
    b) The angle the underside of the mainplane or tailplane makes with the longitudinal datum line
    c) The angle the chord of the mainplane or tailplane makes with the horizontal

    66. What is Boundary Layer?
    a) Separated layer of air forming a boundary at the leading edge
    b) Turbulent air moving from the leading edge to trailing edge
    c) Sluggish low energy air that sticks to the wing surface and gradually gets faster until it joins the free stream flow of air

    67. The normal axis of an aircraft passes through
    a) the centre of gravity
    b) a point at the centre of the wings
    c) at the centre of pressure

    68. On a high winged aircraft, what effect will the fuselage have on the up-going wing?
    a) The up-going wing will have a decrease in angle of attack and therefore a decrease in lift
    b) The down-going will have a decrease in angle of attack and therefore a decrease in lift
    c) The up-going wing will have an increase in angle of attack and therefore a decrease in lift

    69. What is the collective term for the fin and rudder and other surfaces aft of the centre of gravity that helps directional stability?
    a) Effective keel surface
    b) Empennage
    c) Fuselage surfaces

    70. Temperature above 36,000 feet will
    a) decrease exponentially
    b) remain constant
    c) increase exponentially

    71. A decrease in incidence toward the wing tip may be provided to
    a) prevent adverse yaw in a turn
    b) prevent span-wise flow in manoeuvres
    c) retain lateral control effectiveness at high angles of attack

    72. The angle of attack which gives the best L/D ratio
    a) decreases with a decrease in density
    b) in unaffected by density changes
    c) increases with a decrease in density

    73. For a given aerofoil producing lift, where P = pressure and V = velocity:

    a) P1 is greater than P2, and V1 is greater than V2
    b) P1 is less than P2 and V1 is greater than V2
    c) P1 is greater than P2, and V1 is less than V2

    74. Low wing loading
    a) increases stalling speed, landing speed and landing run
    b) increases lift, stalling speed and manoeuvrability
    c) decreases stalling speed, landing speed and landing run

    75. Due to the change in downwash on an un-tapered wing (i.e. one of constant chord length) it will
    a) not provide any damping effect when rolling
    b) tend to stall first at the root
    c) not suffer adverse yaw effects when turning

    76. True stalling speed of an aircraft increases with altitude
    a) because reduced temperature causes compressibility effect
    b) because air density is reduced
    c) because humidity is increased and this increases drag

    77. As a general rule, if the aerodynamic angle of incidence (angle of attack) of an aerofoil is slightly increased, the centre of pressure will
    a) never move
    b) move forward towards the leading edge
    c) move towards the tip

    78. The "wing setting angle" is commonly known as
    a) angle of incidence
    b) angle of attack
    c) angle of dihedral

    79. On a very humid day, an aircraft taking off would require
    a) a shorter take off run
    b) a longer take off run
    c) humidity does not affect the take off run

    80. An aircraft is flying at 350 MPH, into a head wind of 75 MPH, what will its ground speed be?
    a) 175 mph
    b) 275 mph
    c) 200 mph

    81. When does the angle of incidence change?
    a) When the aircraft attitude changes
    b) When the aircraft is ascending or descending
    c) It never changes

    82. As the angle of attack decreases, what happens to the centre of pressure?
    a) It moves forward
    b) It moves rearwards
    c) Centre of pressure is not affected by angle of attack decrease

    83. A decrease in pressure over the upper surface of a wing or aerofoil is responsible for
    a) approximately 2/3 (two thirds) of the lift obtained
    b) approximately 1/3 (one third) of the lift obtained
    c) approximately ½ (one half) of the lift obtained

    84. Which of the four forces act on an aircraft?
    a) Lift, gravity, thrust and drag
    b) Weight, gravity, thrust and drag
    c) Lift, weight, gravity and drag

    85. Which of the following types of drag increases as the aircraft gains altitude?
    a) Parasite drag
    b) Induced drag
    c) Interference drag

    86. Correcting for a disturbance, which has caused a rolling motion about the longitudinal axis, would re-establish which of the following?
    a) Lateral stability
    b) Directional stability
    c) Longitudinal stability

    87. The layer of air over the surface of an aerofoil which is slower moving, in relation to the rest of the airflow, is known as
    a) camber layer
    b) boundary layer
    c) none of the above

    88. What is a controlling factor of turbulence and skin friction?
    a) Aspect ratio
    b) Fineness ratio
    c) Counter-sunk rivets used on skin exterior

    89. Changes in aircraft weight
    a) will not affect total drag since it is dependant only upon speed
    b) cause corresponding changes in total drag due to the associated lift change
    c) will only affect total drag if the lift is kept constant

    90. The aircraft stalling speed will
    a) increase with an increase in weight
    b) be unaffected by aircraft weight changes since it is dependant upon the angle of attack
    c) only change if the MTMA were changed

    91. In a bank and turn
    a) extra lift is not required
    b) extra lift is not required if thrust is increased
    c) extra lift is required

    92. To maintain straight and level flight on the aeroplane shown, with a decrease in tail-plane download the mainplane lift would have to

    a) remain constant
    b) decrease
    c) increase

    93. To achieve the maximum distance in a glide, the recommended air speed is
    a) as close to the stall as practical
    b) as high as possible with VNE
    c) the speed where the L/D ratio is maximum

    94. If the C of G is aft of the Centre of Pressure
    a) changes in lift produce a pitching moment which acts to increase the change in lift
    b) when the aircraft sideslips, the C of G causes the nose to turn into the sideslip thus applying a restoring moment
    c) when the aircraft yaws the aerodynamic forces acting forward of the Centre of Pressure

    95. Porpoising is an oscillatory motion in the
    a) pitch plane
    b) roll plane
    c) yaw plane

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