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Uluç ATPL > AGK > Flashcards

AGK Flashcards

1
Q

Torsion in a wing can be caused by Positive Sweep

A

Significant torsion effects in a wing during
flight can be caused by: aileron deflection.

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2
Q

Significant torsion effects in a wing during flight can be caused by: Aileron Deflection

A
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3
Q

In flight, cantilever wing of an aeroplane containing fuel is subjected to vertical loads that produce a bending moment, which is highest at the WING ROOT

A
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4
Q

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 (kiriş) of the torsion from the wing root to the wing tip is Compression and then Torsion

A

Motorlar uçuş sırasında sparlara longitudinal axiste ileri doğru kuvvet uyguluyor. Kökte baskı, uçta gerilme

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5
Q

Safe Life

A

Operation life (of hours) limits. Number of cycles

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6
Q

Fail safe

A

Redundancy - parallel load paths - redundant

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7
Q

Damage tolerant

A

Detectability - structure can be damaged without catastrophic failure

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8
Q

Failure types and probabilities

A

Catastrophic - Hazardous - Major - Minor

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9
Q

Magnesium alloys

A

Gearbox casing

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10
Q

Steel

A

Good fatigue resistance, rotor brake disk

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11
Q

Aluminum

A

High conductivity, anti corros

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12
Q

Titanium

A

Light - strong - expensive - Firewalls

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13
Q

Composite

A

Higher strength weight ratio
Can be tailored to the direction of the load

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14
Q

Monocoque

A

İki parçadan oluşuyor 1) skin 2) frame (former)
Heavy structure.
Yekpare
External skin takes all the load

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15
Q

Semi-monocoque

A

Ara destek parçaları var (stringer)
The purposes of stringers is to assist the skin withstand longitudinal compressive loads.

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16
Q

Modern pressurized aircrafts are an example of

A

Semi-monocoque fusilage

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17
Q

Windows

A

Glass and polycarbonate laminate. Inner (mid layer) surface soft polycarbonate. Heating is usually 3 phase AC (115V / 400 hz) - heating inop > speed restriction - cockpit side windows usually defogged only.

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18
Q

Rain repellent

A

Rain repellent should never be sprayed onto the windshield unless the rainfall is very heavy

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19
Q

Components of wing structure

A

Skin - Stingers - Spars

The spar is a beam which takes the load along the wing, from wing tip to fusilage.

On a non stressed skin type wing, the wing str. Elements which take up to the vertical bending moments are spars

A wing spar typically consists of a web and girders.

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20
Q

Rib

A

Rib is to maintain the aerodynamic shape of the wing

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21
Q

Torsion box

A

Torsion box is formed by wing spars, ribs and wing skin reinforced by stringers

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22
Q

Sandwich (honeycomb) structures

A

Two thin sheets separated by a light core material
Core material stabilizes the covering sheets
Core material is not used for sound isolation
Unsuitable for absorbing concentrated loads (rüzgara karşı iyi ama kalem batırsan girer)
Low mass and high stiffness

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23
Q

Primary controls

A

Rudder aileron elevator, roll (flight) spoilers

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24
Q

Rudder Ratio Changer

A

Reduces the rudder deflection for a given rudder pedal deflection as IAS increases

Hız arttığında rudder’ın hassasiyetini azaltır.

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25
Q

’’’ pistte hızla giderken rudderda frenleme yapmamak için topukları aşağıya verirsin ve hocaya söylersin.

A

Yanlışlıkla takeoffta frene değip takla atanlar var.

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26
Q

’’’

I Pti
C. Cold
E. Drink
T

A

Indicated

Position error
Calibrated

Compressibility error
Equivalent

Density error
True

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27
Q

’’’

IAS TAS FARKI YAKLAŞIK OLARAK %2/1000ft

A

YANİ 6000 FT DE KIAS=100 KTAS=112 knots

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28
Q

Uçakta pervane etkisini en çok ne zaman görürüz?

A

High power setting - low airspeed - (kalkış ve inişte sağ rudder basarsın)

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29
Q

GROUND SPEED = TAS (+-) WIND

A

GS Süre zaman yakıt hesaplamalarında işe yarıyor.
TAS - seyrüsefer hesaplarda kullanılır.
IAS - flap açma tasarım parametreleri hep IAS. Çünkü

IAS > TAS olabilir (deniz seviyesi )

Autopilot CAS Veya EAS ı kullanıyor.

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30
Q

’’’ Crosswind = Wind Speed x sin(RwyDir - WDir)

Örn 50 pistinden kalkan bir uçağa 080’den 10kt rüzgar geliyorsa.
Crosswind = 10 x sin30 = 5

A

Rüzgar relativ geliş - Cross oranı
30’ = %50
45’ = %70
60’ = %90
90’ = %100

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31
Q

Tailwind = Wind Speed x cos(WD-RD)

A
32
Q

Variable stop system

A

Limits both rudder and rudder pedal deflection as IAS increases

33
Q

Rudder limiter system

A

To restrict rudder deflection during flight at high IAS

34
Q

Secondary controls
Flaps slats ground spoilers airbrakes trim tabs

A

For a JAR25 aeroplane, spoilers are upper wing surface devices, their deflection can be symmetrical or asymmetrical.

35
Q

FLUTTER results from two deformation modes are TORSION and BENDING

A HIGH TORSIONAL STIFFNESS of the structure

Locating a balancing mass IN FRONT OF the control hinge

Ensuring correct MASS DISTRIBUTION within the control surface

A

Büyük yolcu uçaklarında yakıt merkezden kullanılmaya başlanır. Fuel inbalance olmaması için.
Flutter kanatlardaki yalpalama hareketlerini engelliyor.

36
Q

FLUTTER

When a wing bends upwards, aileron flutter might occur if the aileron deflects downwards because the location of the aileron centre of gravity lies behind the hinge line

A

Flutter oluşursa behindda oluşur, önlemek için frontuna ağırlık takmak gerekir.

37
Q

BALANCE_TAB

The purpose of a trim tab is to reduce or to cancel control surfaces

A

Lövyedeki yükü hafifletmek içim yarar. Climb yapmaya çalışan uçakta trim down position a getirirsen uçağın burnunu dengeler.

38
Q

HORN BALANCE

Standart rate of turn (dönüş açısı) 3’/sec

Standard Bank angle= (TAS/10) +7

A

Örn:

360’ dönüş için 360/(3’/s) = 2min.

KTAS: 100
Bank angle = 17’

39
Q

ELEVATOR TRIM the zero force pos of the control column DOES NOT CHANGE WHEN USING THE ELEVATOR TRIM

Lövyede force feel hissedilmez.

A

AILERON TRIM
The zero force position of the control wheel CHANGES WHEN USING THE AILERON TRIM

Lövyede force feel hissedilir.

40
Q

RUDDER TRIM - the rudder moves , the rudder pedals move in the corresponding direction

A

Rudder pedallar benzer bir şekilde hareket ediyor.

41
Q

Rudder trim adjustment in an aeroplane with irreversible flight controls is an ADJUSTMENT OF THE ZERO FORCE RUDDER POSITION

A

Rudder trimi ayarladığında örn 5’ ayarlandığında nötrü o şekilde kalıyor.

42
Q

Primary vs secondary SSR radar.

A

Primary radarda ışın gelir yüzeyden seker ve bilgi gider. Secondary radarda ise hem receiver hem de transmitter var.

43
Q

Control (Gust) Locks

When the gust lock is on there is protection to prevent take-off

Control locks are fitted to prevent gust damage to control system and surfaces of parked aircraft

Suitable design precautions to prevent flight with gust lock engaged

Manual flight controls should have a gust lock

There should be suitable design precautions to prevent flight with the gust lock engaged

A

Gust lock yalnızca manual flight ve reversable (tamamen mekanik, rüzgarı tamamen hissettiğin) uçaklarda bulunur. Sadece park pozisyonunda kullandığımız bir parça.

44
Q

A wing spar consistes

A

Web and girders

45
Q

AGK Şıklarda NEVER görüyorsan kesinlikle yanlış ;)

A

ŞAKİR TIME ;) ;)

46
Q

Function of a rib is:

A

Rib shape verir :)

47
Q

Maximum power output and low mass of aeroplane hydraulics systems can be achieved with high system pressure and low volume flow

A

Hidrolik sistemler çok basınçlandırıp (3000 psi) az akışkan kullanıldığında yüksek gücü elde ederken hafif kalabiliyoruz.

48
Q

Maximum power output and low mass of aeroplane hydraulics systems can be achieved with high system pressure and low volume flow

A

Hidrolik sistemler çok basınçlandırıp (3000 psi) az akışkan kullanıldığında yüksek gücü elde ederken hafif kalabiliyoruz.

49
Q

Rotor brake diSC

A

steel and carbon fiber

50
Q

Axial air velocity > rotor blade :)

Stall margin increases :)

A
51
Q

Shell structure transmits
1,2,3
Normal bending
Tangent bending
Torsional moment

A

Eğer yeni versiyonla karşılaşırsan
1,2,4
Normal bending
Compression
Tension

52
Q

Fuel tank vents - fitted to the top of the tank to prevent tank collapse

A
53
Q

A fault protection circuit in a fire detection system will:

Inhibit when detection line is connected to gnd

A
54
Q

Static gas temp decrease when subsonic speed through a jet engine exhaust nozzle

A

Is convergent

55
Q

Freezing point & flash point

A>a1>B

A

A’dan B’ye düşüyor.

56
Q

Vapour locking is caused by -

A

Vaporizing of fuel prior to the engine

57
Q

The oil supply to gas turbine engines bearings is maintained in the event of the main oil filter becoming clogged by:

A

Differential pressure opening the bypass valve of the main oil filter

58
Q

Limitation being imposed on the temperature of gas flow is to:

A

Ensure that the maximum acceptable temperature at the TURBINE blades is not exceeded.

59
Q

Primary input signals for a hydro mechanical gas turbine engine fuel control system include

A

N2 compressor discharge pressure compressor inlet temperature fuel shut off thrust lever angle

60
Q

Primary input signals for a hydro mechanical gas turbine engine fuel control system include

A

N2 compressor discharge pressure compressor inlet temperature fuel shut off thrust lever angle

61
Q

Severe compressor stall can be observed amongst others by

A

A rise in TGT and increase in vibration

62
Q

Passenger oxygen system be activated by:

A

Switching the passenger oxygen ON

63
Q

Ion detectors for

A

Smoke

64
Q

Advantages of a gaseous oxygen source for the passanger cabin are:

A

A greater autonomy
Reversible functioning
Possibility to regulate flow

65
Q

The richness of fuel/air mixture ratio is the:

A

Actual vs therotical

66
Q

When detonation is recognised in a piston engine, the correct procedure is to:

A

MANIFOLD PRESSURE: DÜŞÜR

RICHNESS OF THE MIXTURE: ARTTIR

Motor ısınıyor, gücü azalt motoru soğut

67
Q

Cadmium Nickel’de high low yok.
3456

A
68
Q

Fuel air ratio is the ratio between the

A

Mass of F&Air entering the CYLINDER

69
Q

What may happen during continuous climb with a mixture setting fully rich

A

Yükselirken hava yoğunluğu düşüyor ve richness artıyor. Yakıt motoru soğutuyor.

FOULING OF SPARK PLUGS

70
Q

As the flight altitude increases, if no leaning is made with the mixture control

A

Density of air entering the carburator decreases and the amount of fuel remans constant.

Leanleme olmadığı için yakıtta bir değişim olmuyor.

71
Q

Frequency which corresponds to a wavelength of 12cm

1(2) c(m)

A

Speed of Light (m/s) = Frequency (Hz) x Wavelength (m)
Transpose formula
Frequency (Hz) = Speed of Light (m/s) / Wavelength (m)
f = 300,000,000 / 0.12
f = 2,500,000,000 Hz
f = 2,500 MHz

72
Q

With which instrument(s) do you monitor the power output of an aeroplane fitted with a fixed pitch propeller?

A

RPM!!!

Fixed pitch uçaklarda yalnızca rpm’den gücü ayarlıyoruz.

Eğer constant speed propeller ise hem RPM hem de MAP ‘a bakabilirz.

73
Q

Ignition systems of piston engines are:

A

Independent of the electrical system of the aircraft

74
Q

For piston engines, mixture ratio is the ratio between the:

A

Mass of fuel and mass of air entering the cylinder

75
Q

The purpose of gas turbines engine tranding is to enhance maintenance planning and detect anomalies

A
76
Q

Turbojet - brayton cycle
Internal combustion engine - otto cycle

In a theoretical gas turbine, the combustion takes place at constant PRESSURE

A
77
Q

Octane rating

A

Resistance to detonation

Uluç ATPL (5 decks)

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