General

Question 1

JAR:

FAR:
stand for

Answer 1

The Joint Airworthiness Requirements are under the European authority called the JointAviation Authority (JAA

The Federal Aviation Regulations are under the US authority called the Federal Aviation Administration (FAA).

Question 2

Tropopause is located at an altitude of __________ ft and has a temperature of ________ as per ISA

Answer 2

36,089 ft and -56.5 deg C

Question 3

The international reference is based on a sea-level temperature of _____ at a
pressure of ____________ hPa
. The standard density of the air at sea level is _________ kg/m3 and air is considered to be a perfect gas.
.

Answer 3

15 , 1013.25 , 1.225

Question 4

Temperature decreases with altitude at a constant rate of
___________ or _________ up to the tropopause. The standard tropopause
altitude is _______ m or _______ feet.

Answer 4

-6.5°C/1000m, -1.98°C/1000ft , 11,000 , 36,089

Question 5

ISA temperature = T0 = +15°C = _______ K . ISA temperature (ºC) = To - 1.98 x [Alt(feet)/1000]

Answer 5

288.15 ,

Question 6

Let’s consider a flight in the following conditions:
Altitude = 33,000 feet
Actual Temperature = -41ºC . What is the temperature above ISA the flight is operating ?

Answer 6

The standard temperature at 33,000 feet is : ISA = 15 - 2 x 33 = -51ºC,
whereas the actual temperature is -41ºC, i.e. 10ºC above the standard.
Conclusion: The flight is operated in ISA+10 conditions

Question 7

An altimeter is a __________, which is calibrated following standard
pressure and temperature laws. Assuming the conditions are standard, Indicated Altitude is

Answer 7

manometer , the “Indicated Altitude” (IA) is the
vertical distance between the following two pressure surfaces

Question 8

The reference pressure surface, i.e. the point from which the height of the aircraft is being measured is given by corresponding to the pressure selected by
the pilot

Answer 8

through the altimeter’s pressure setting knob.

Question 9

The pressure setting and the indicated altitude move in the _____ direction: Any increase in the pressure setting leads to an __________ in the corresponding Indicated Altitude (IA).

Answer 9

same, increase

Question 10

• QFE is the pressure at the ____________. With the QFE setting, the altimeter indicates the altitude above the airport reference point.

Answer 10

airport reference point,

Question 11

QNH is the ________. The QNH is calculated through the measurement of the pressure at the airport reference point moved to Mean Sea Level, assuming the standard pressure law. With the
QNH setting, the altimeter indicates the altitude above ______ (if temperature is standard). Consequently, at the airport level in ISA conditions, the altimeter indicates the ____________.

Answer 11

Mean Sea Level pressure, Mean Sea Level, topographic altitude of the terrain

Question 12

The aim of Standard Altimeter Setting is to provide a vertical separation between aircraft while getting rid of the ____________the flight. After takeoff, crossing a given altitude referred to as ______
Altitude, the standard setting is selected.

Answer 12

local pressure variations throughout, Transition

Question 13

The ________ Altitude is the indicated altitude above which the standard setting must be selected by the crew

Answer 13

Transition

Question 14

The _________ is the first available flight level above the transition altitude.

Answer 14

Transition Level

Question 15

The change between the QNH setting and Standard setting occurs at the _________ when climbing, and at the ___________ when descending

Answer 15

transition altitude, transition level

Question 16

The transition altitude is generally given on the ___________ charts, whereas the transition level is usually given by the ___________

Answer 16

Standard Instrument Departure (SID), Air Traffic Control (ATC).

Question 17

What is the formula for calculating the True altitude from Indicated Altitude

Answer 17

True altitude = Indicated altitude + 28 x (QNH [hPa] - 1013)

Question 18

Flying at a given indicated altitude, the true altitude _________ with the increase in temperature. The formula for same is

Answer 18

increases, True Alt= Ind alt(temp/temp isa)

Question 20

When the ambient temp is lower than ISA the True Alt is _____ than Ind Alt and the terrain clearance __________

Answer 20

lower, reduces

Question 21

In order to maintain the same terrain clearence - If the temperature is higher, you fly _____.
If the temperature is lower, you fly _________. Therefore, temp correction is important when flying at _____ temperature.

Answer 21

higher, lower , Low

Question 22

The Calibrated Air Speed (CAS) is obtained from the difference between the _____ (Pt) and the ______ pressure (Ps). This difference is called ______ pressure (q).

Answer 22

total pressure, static , dynamic

Question 23

Flying at a constant CAS during a climb phase enables the ________ effect to remain the same as at sea level and, consequently, to eliminate speed variations. AD effects such as stalling speed.

Answer 23

aerodynamic

Question 24

The Indicated Air Speed (IAS) is the speed indicated by the airspeed indicator. Whatever the flight conditions, if the pressure measurement were accurate, then the IAS should ideally be ____ to the CAS. Nevertheless, depending on the aircraft angle of attack, the flaps configuration, the ground proximity (ground effect or not), the wind direction and other influent parameters, some measurement errors are
introduced, mainly on the static pressure. This leads to a small difference between
the CAS and the IAS values. This difference is called _______ correction or antenna error (Ki).

Answer 24

equal, instrumental

Question 25

The True Air Speed (TAS) represents the aircraft speed in a moving reference system linked to this air ss, or simply the aircraft speed in the airflow. It can be obtained from the CAS, using the _______ and a ___________ correction (K).

Answer 25

air density, compressibility

Question 26

The ground speed (GS) represents the aircraft speed ________. It is equal to the TAS corrected for the _____ component

Answer 26

in a fixed ground reference system, wind

Question 27

The speed of sound is solely dependent on _________. The formula for M.No. is ____ . The formula for Mach no can also be represented as a ratio between _________ and _________

Answer 27

static air temperature, 39Xsqrt(static air temp in kelvin) , Dynamic Pr and Static Pr.

Question 28

When the pressure altitude increases, the SAT decreases and thus the True Air Speed (TAS)

Answer 28

decreases

Question 30

The altitude at which a given CAS is equal to a given Mach number, during a clim with constant CAS , is called the ________.

Answer 30

cross-over altitude

Question 31

The lift coefficient, CL, is a function of the ________ , the ________ , and the _____________.

Answer 31

angle of attack, Mach number, aircraft configuration (AMC)

Question 32

The drag coefficient, CD, is a function of the _______

Answer 32

angle of attack (α), the Mach number (M) and the aircraft configuration. (AMC)

Question 33

Lift and drag equations may be expressed with the Mach number M. As a result, the equations are:

Answer 33

W=0.7 X PsXSXM2XCl

Question 34

Except when the lift force is equal to the weight and nz=1 (for instance in straight and level flight), the aircraft’s apparent weight is different from its real weight (mg):

Answer 34

Apparent weight = nz.m.g = Lift

Question 35

VLO: Landing Gear Operating Speed

Answer 35

VLO may not exceed the speed at which it is safe both to extend and to retract the landing gear. If the extension speed is not the same as the retraction speed, the two speeds must be designated as VLO(EXT) and VLO(RET)respectively.

Question 36

VLE: Landing Gear Extended Speed.

Answer 36

VLE may not exceed the speed at which it is safe to fly with the landing gear secured in the fully extended position.

Question 37

VMCG, the minimum control speed on the ground

Answer 37

, is the calibrated airspeed during the take-off run, at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the aeroplane with the use of the primary aerodynamic controls alone (without the use of nose-wheel steering) to enable the take-off to be safely continued using normal piloting skill.

Question 38

Define the LAteral Deviation limit at Vmcg

Answer 38

In the determination of VMCG, assuming that the path of the aeroplane accelerating with all engines operating is along the centreline of the runway, its path from the point at which the critical engine is made inoperative to the point at which recovery to a direction parallel to the centreline is completed, may not deviate more than 30 ft laterally from the centreline at any point.”

Question 39

“VMCG must be established with following conditions : •

Answer 39

- The aeroplane in each take-off configuration or, at the option of the applicant, in the most critical take-off configuration; • Maximum available take-off power or thrust on the operating engines; • The most unfavourable centre of gravity;i.e rearmost CG position for shortest moment arm of rudder • The aeroplane trimmed for take-off; and • The most unfavourable weight in the range of take-off weights.”

Question 40

(b) VMC[A] is the calibrated airspeed,

Answer 40

at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the aeroplane with that engine still inoperative, and maintain straight flight with an angle of bank of not more than 5 degrees.

Question 41

VMC[A] may not exceed ____ VS with following conditiobs During recovery, the aeroplane may not assume any dangerous attitude or require exceptional piloting skill, alertness, or strength to prevent a heading change of more than _______ degrees.”

Answer 41

1.2, • Maximum available take-off power or thrust on the engines; • The most unfavourable centre of gravity; • The aeroplane trimmed for take-off; • The maximum sea-level take-off weight - The aeroplane in the most critical take-off configuration existing along the flight path after the aeroplane becomes airborne, except with the landing gear retracted; and • The aeroplane airborne and the ground effect negligible 20 degrees

Question 42

VMCL,

Answer 42

the minimum control speed during approach and landing with all engines operating, is the calibrated airspeed at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the aeroplane with that engine still inoperative, and maintain straight flight with an angle of bank of not more than 5º.

Question 43

VMCL must be established with:

Answer 43

• The aeroplane in the most critical configuration (or, at the option of the applicant, each configuration) for approach and landing with all engines operating; • The most unfavourable centre of gravity; • The aeroplane trimmed for approach with all engines operating; • The most unfavourable weight, or, at the option of the applicant, as a function of weight. • Go-around thrust setting on the operating engines

Question 44

In demonstrations of VMCL and VMCL-2, … lateral control must be sufficient to roll the aeroplane from an initial condition of steady straight flight, through an angle of ______ degrees in the direction necessary to initiate a turn away from the inoperative engine(s) in not more than ___ seconds.”

Answer 44

20 deg, 5 seconds

Question 45

As the AOA of the aircraft increases - Air velocity over the wing ________ with the angle of attack, so that air pressure _____________ and the lift coefficient ______________.

Answer 45

increases , decreases, increases

Question 46

During stall two speeds can be identified : - VS1g, which corresponds to the maximum lift coefficient (i.e. just before the lift starts decreasing). At that moment, the load factor is ______ (JAR 25 reference stall speed). - VS, which corresponds to the conventional stall (i.e. when the lift suddenlycollapses). At that moment, the load factor is __________ (FAR 25 reference stall speed).

Answer 46

still equal to one, always less than one

Question 47

The reference stall speed

Answer 47

is a speed defined by the applicant. It cannot be less than the 1 g stalling speed of the aircraft.

Question 48

Stalling Speed. )

Answer 48

VS is the calibrated stalling speed, or the minimum steady flight speed, in knots, at which the airplane is controllable, with Zero thrust at the stalling speed, or […] with engine idling”.

Question 49

Manufacturer’s Empty Weight (MEW) :

Answer 49

The weight of the structure, power plant, furnishings, systems and other items of equipment that are considered an integral part of the aircraft. It is essentially a “dry” weight,including only those fluids contained in closed systems (e.g. hydraulic fluid).

Question 50

Operational Empty Weight (OEW) :

Answer 50

The manufacturer’s weight empty plus the operator’s items, i.e. the flight and cabin crew and their baggage, unusable fuel, engine oil, emergency equipment, toilet chemicals and fluids, galley structure, catering equipment, seats, documents, etc…

Question 51

Dry Operating Weight (DOW) :

Answer 51

The total weight of an aircraft ready for a specific type of operation excluding all usable fuel and traffic load. Operational Empty Weight plus items specific to the type of flight, i.e.catering, newspapers, pantry equipment, etc…

Question 52

Zero Fuel Weight (ZFW)

Answer 52

The weight obtained by addition of the total traffic load (payload including cargo loads, passengers and passenger’s bags) and the dry operating weight.

Question 53

Landing Weight (LW)

Answer 53

The weight at landing at the destination airport. It is equal to the Zero Fuel Weight plus the fuel reserves.

Question 54

Takeoff Weight (TOW):

Answer 54

The weight at takeoff at the departure airport. It is equal to the landing weight at destination plus the trip fuel (fuel needed for the trip), or to the zero fuel weight plus the takeoff fuel (fuel needed at the brake release point including reserves).

Question 55

Give the correlation between TOW, ZFW and LW

Answer 55

TOW = DOW+ traffic load + fuel reserves + trip fuel LW = DOW+ traffic load + fuel reserves ZFW = DOW+ traffic load

Question 56

The takeoff weight (TOW) must never exceed a Maximum structural TOW (MTOW) which is determined in accordance with in flight structure resistance criteria, resistance of ___________

Answer 56

landing gear and structure criteria during a landing impact with a vertical speed equal to -1.83 m/s (-360 feet/min).

Question 57

The landing weight (LW) is limited, assuming a landing impact with a vertical speed __________ The limit is the maximum structural landing weight (MLW).

Answer 57

equal to -3.05 m/s (-600 feet/min).

Question 58

The landing weight must comply with the relation

Answer 58

actual LW = TOW – Trip Fuel ≤ MLW or actual TOW ≤ MLW + Trip Fuel

Question 59

Bending moments, which apply at the wing root during flying, are maximum when the quantity of fuel ____________

Answer 59

in the wings is minimum

Question 60

What is Maximum Zero Fuel Weight (MZFW).

Answer 60

1. During flight, the quantity of fuel located in the wings, mWF, decreases. As a consequence, it is necessary to limit the weight when there is no fuel in the tanks. This limit value is called Maximum Zero Fuel Weight (MZFW). actual ZFW ≤ MZFW, 2. The takeoff fuel is the sum of the trip fuel and the fuel reserves. Consequently:actual TOW ≤ MZFW + Takeoff Fuel

Question 62

What is Maximum Taxi Weight (MTW)

Answer 62

The Maximum Taxi Weight (MTW) is limited by the stresses on shock absorbers and potential bending of landing gear during turns on the ground. Nevertheless, the MTW is generally not a limiting factor and it is defined from the MTOW, so that: MTW – Taxi Fuel > MTOW

Question 63

What is TOGA

Answer 63

The TakeOff (TOGA) thrust represents the maximum thrust available for takeoff. It is certified for a maximum time of 10 minutes, in case of engine failure at takeoff, or 5 minutes with all engines operative.The Go Around (TOGA) thrust is the maximum thrust available for goaround. The time limits are the same as for takeoff.

Question 65

What is MCT

Answer 65

The Maximum Continuous Thrust (MCT) is the maximum thrust that can be used unlimitedly in flight. It must be selected in case of engine failure, when TOGA thrust is no longer allowed due to time limitation.

Question 66

What is CL thrust

Answer 66

The Climb (CL) thrust represents the maximum thrust available during the climb phase to the cruise flight level. Note that the maximum climb thrust is greater than the maximum cruise thrust available during the cruise phase.

Question 67

What is the significance of the Reference Temperature ?

Answer 67

At a given pressure altitude, temperature has no influence on engine takeoff thrust, below the so-called reference temperature (Tref) or flat rating temperature. Above this reference temperature, engine thrust is limited by the Exhaust Gas Temperature (EGT). The consequence is that the available thrust decreases as the temperature increases.

Question 68

At a given temperature, any increase in the pressure altitude leads to _______ thrust.

Answer 68

decreasing the available takeoff,