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Question 79-1 : In order to provide an adequate stall margin in level flight a speed of 1 3vs is used at a mass of 120000 kg this is a cas of 180 kt if the mass of the aeroplane is increased to 135000 kg the value of 1 3vs will be ? [ Attainment AIM ]

Increased to 191 kt drag will increase and air distance per kg of fuel will decrease

135000/120000 = 1 125.180 x square root of 1 125 = 191 kt.if speed increases drag increases thus for a same unit of fuel the air distance will be lesser exemple 179 Increased to 191 kt, drag will increase and air distance per kg of fuel will decrease.

Question 79-2 : What are the effects of a cg in front of the forward limit .range ?

And absolute ceiling decrease

A forward cg means that the pitch down moment is high the elevator must provide a moment opposing this pitch down moment adding a high downward force to the weight of the aircraft which is then increased therefore the climb performance and ceiling will be decreased the increased drag of the elevator will cause a higher fuel consumption for a given airspeed thus decreasing range and endurance exemple 183 And absolute ceiling decrease.

Question 79-3 : The centre of gravity of an aircraft ?

Can be allowed to move between defined limits

Centre of gravity cg is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector exemple 187 Can be allowed to move between defined limits.

Question 79-4 : Which statement regarding the relationship between traffic load and range is correct ?

The traffic load can be limited by the desired range

Traffic load might be exchanged for fuel to extend range exemple 191 The traffic load can be limited by the desired range.

Question 79-5 : The term 'useful load' as applied to an aircraft includes ?

Traffic load and usable fuel only

exemple 195 Traffic load and usable fuel only.

Question 79-6 : If other factors are unchanged the fuel mileage nautical miles per kg is ?

Lower with a forward centre of gravity position

With a forward cg the aircraft is 'nose heavy' it has a nose down moment thus the downforce on the tail on a steady flight must be increased .the total aircraft weight increases and therefore more weight = more drag = more power .the fuel mileage nautical miles per kg is lower with a forward centre of gravity position .example . with a aft cg fuel mileage = 10 nm for 100 kg . with a forward cg fuel mileage = only 8 nm for 100 kg exemple 199 Lower with a forward centre of gravity position.

Question 79-7 : The stalling speed of an aeroplane will be highest when it is loaded with a ?

High gross mass and forward centre of gravity

A forward cg requires more lift and generates more drag the stalling speed will be greater than with an aft cg .also for a higher gross mass it is mandatory to generates more lift which generates more induced drag the stalling speed increases exemple 203 High gross mass and forward centre of gravity.

Question 79-8 : With the centre of gravity on the forward limit which of the following is to be expected ?

A decrease in range

The most forward the cg is the more down force the tail needs to generate to compensate and keep the airplane from pitching down this increased down force must be counteracted by increased lift from the wing that of course means an increase in angle of attack or airspeed = the stall speed increases = consumption increases = range decreases exemple 207 A decrease in range.

Question 79-9 : If the centre of gravity of an aeroplane moves forward during flight the elevator control will become ?

Heavier making the aeroplane more difficult to manoeuvre in pitch

When the centre of gravity moves forward during flight the aeroplane will be more stable but requires more forces to change pitch elevator control will become heavier exemple 211 Heavier making the aeroplane more difficult to manoeuvre in pitch.

Question 79-10 : The determination of the centre of gravity in relation to the mean aerodynamic chord consists of defining the centre of gravity longitudinally in relation to the ?

Length of the mean aerodynamic chord and the leading edge

Longitudinal cg location is normally expressed as a percentage of the mean aerodynamic chord mac from its leading edge exemple 215 Length of the mean aerodynamic chord and the leading edge.

Question 79-11 : The maximum zero fuel mass ?

Is calculated for a maximum load factor of +2 5 g

exemple 219 Is calculated for a maximum load factor of +2.5 g.

Question 79-12 : When has the centre of gravity to be computed ?

Prior to every flight

exemple 223 Prior to every flight.

Question 79-13 : The operating mass om is ?

The take off mass minus the traffic load

The operating mass is the dry operating mass plus the take off fuel mass .or/also .the operating mass is the take off mass minus the traffic load ./pdf/031 mass definitions pdf exemple 227 The take-off mass minus the traffic load.

Question 79-14 : The 'regulated landing mass' is the ?

Lowest of the structural limited landing mass and the performance limited landing mass

exemple 231 Lowest of the structural limited landing mass and the performance limited landing mass.

Question 79-15 : Given .dry operating mass= 29 800 kg.maximum take off mass= 52 400 kg.maximum zero fuel mass= 43 100 kg.maximum landing mass= 46 700 kg.trip fuel= 4 000 kg.fuel quantity at brakes release= 8 000 kg.the maximum traffic load is ?

12 900 kg

Traffic load is the total mass of passengers baggage and cargo including any non revenue load . 127.the lowest mass is our limitation exemple 235 12 900 kg.

Question 79-16 : The take off mass of an aircraft is 117 000 kg comprising a traffic load of 18 000 kg and fuel of 46 000 kg .what is the dry operating mass ?

53 000 kg

Dry operating mass = the total mass of an aircraft ready for a specific type of operation excluding all usable fuel and traffic load .this mass includes items such.as .+ crew and crew baggage .+ catering and removable passenger service equipment food beverages potable water lavatory chemicals etc .+ special operational equipment e g stretchers rescue hoist cargo sling ..dry operating mass = take off mass traffic load fuel.dry operating mass = 117000 18000 46000 = 53000 kg exemple 239 53 000 kg.

Question 79-17 : The dry operating mass includes ?

Crew and crew baggage catering removable passenger service equipment potable water and lavatory chemicals

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf

Question 79-18 : The maximum load per running metre of an aircraft is 350 kg/m the width of the floor area is 2 metres the floor strength limitation is 300 kg per square metre .which one of the following crates length x width x height can be loaded directly on the floor ?

A load of 400 kg in a crate with dimensions 1 2 m x 1 2 m x 1 2 m

Maximum load per running metre 400 / 1 2 = 333 kg/m.floor strength limitation 400 / 1 2 x 1 2 = 277 77 kg/m².both limitations are respected exemple 247 A load of 400 kg in a crate with dimensions 1.2 m x 1.2 m x 1.2 m.

Question 79-19 : Given the following . maximum structural take off mass 48 000 kg. maximum structural landing mass 44 000 kg. maximum zero fuel mass 36 000 kg. taxi fuel 600 kg. contingency fuel 900 kg. alternate fuel 800 kg. final reserve fuel 1 100 kg. trip fuel 9 000 kg .the actual tom can never be higher than ?

47 800 kg

Img128.the actual take off mass is the lowest of the three it can never be higher if we don't want structural troubles exemple 251 47 800 kg.

Question 79-20 : The maximum zero fuel mass .1 is a regulatory limitation.2 is calculated for a maximum load factor of +3 5 g.3 is based on the maximum permissible bending moment at the wing root.4 is defined on the assumption that fuel is consumed from the outer wings tank first.5 is defined on the assumption ?

1 3 5

The maximum zero fuel mass is a regulatory limitation cs23 and cs25 it is a design limitation to prevent wing bending and it is defined on the assumption that fuel is consumed from the centre wing tank first exemple 255 1, 3, 5.

Question 79-21 : At the flight preparation stage the following parameters in particular are available for determining the mass of the aircraft .1 dry operating mass.2 operating mass.which statement is correct ?

The dry operating mass includes fixed equipment needed to carry out a specific flight

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf exemple 259 The dry operating mass includes fixed equipment needed to carry out a specific flight.

Question 79-22 : Which of the following corresponds to zero fuel mass ?

The take off mass of an aeroplane minus all usable fuel

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf exemple 263 The take-off mass of an aeroplane minus all usable fuel.

Question 79-23 : Given that . maximum structural take off mass 146000 kg. maximum structural landing mass 93900 kg. maximum zero fuel mass 86300 kg. trip fuel 27000 kg. taxi fuel 1000 kg. contingency fuel 1350 kg. alternate fuel 2650 kg. final reserve fuel 3000 kg.determine the actual take off mass ?

120 300 kg

Without the dry operating mass our traffic load will depend on maximum zero fuel mass or a maximum structural mass .we have two possibility the lowest will be our answer .actual take off mass = maximum structural landing mass + trip fuel.actual take off mass = 93900 + 27000 = 120 900 kg .or .actual take off mass = maximum zero fuel mass + trip fuel + contingency + alternate + final reserve.actual take off mass = 86300 + 27 000 + 1350 + 2650 + 3000 = 120 300 kg exemple 267 120 300 kg.

Question 79-24 : Given . maximum structural take off mass 72 000 kg. maximum structural landing mass 56 000 kg. maximum zero fuel mass 48 000 kg. taxi fuel 800 kg. trip fuel 18 000 kg. contingency fuel 900 kg. alternate fuel 700 kg. final reserve fuel 2 000 kg .determine the actual take off mass ?

69 600 kg

Img130.the actual take off mass is the lowest of the three it can never be higher if we don't want structural troubles exemple 271 69 600 kg.

Question 79-25 : The actual take off mass is equal to 41 545 kg . catering 300 kg. safety and rescue material nil. fly away kit nil. crew inclusive crew baggage 365 kg. fuel at take off 3 000 kg. unusable fuel 120 kg. passengers baggage cargo 8 000 kg.the basic empty mass is ?

30 665 kg

The basic empty mass includes unusable fuel .41 545 kg 8000 kg + 3000 kg + 120 kg = 30 665 kg exemple 275 30 665 kg.

Question 79-26 : The zero fuel mass of an aeroplane is always ?

The take off mass minus the mass of take off fuel

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf exemple 279 The take-off mass minus the mass of take-off fuel.

Question 79-27 : Given .maximum structural take off mass 146 900 kg.maximum structural landing mass 93 800 kg.maximum zero fuel mass 86 400 kg.trip fuel 27 500 kg.block fuel 35 500 kg.engine starting and taxi fuel 1 000 kg.the maximum take off mass is equal to ?

120 900 kg

We are looking for the maximum take off mass .maximum take off mass = maximum zero fuel mass + fuel at take off.maximum take off mass = 86 400 + 35 500 1 000 = 120 900 kg ..the maximum zero fuel mass is a structural limiting mass it is made up of the aeroplane dry operational mass + traffic load and unuseable fuel exemple 283 120 900 kg.

Question 79-28 : Traffic load is the ?

Zero fuel mass minus dry operating mass

Tl = zfm dom exemple 287 Zero fuel mass minus dry operating mass.

Question 79-29 : While making mass and balance calculation for a particular aircraft the term 'basic empty mass' applies to the sum of airframe engine s fixed ballast plus ?

Unusable fuel and full operating fluids

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf exemple 291 Unusable fuel and full operating fluids.

Question 79-30 : The term 'maximum zero fuel mass' consist of ?

The maximum permissible mass of an aeroplane with no usable fuel

exemple 295 The maximum permissible mass of an aeroplane with no usable fuel.

Question 79-31 : The actual 'zero fuel mass' is equal to the ?

Dry operating mass plus the traffic load

exemple 299 Dry operating mass plus the traffic load.

Question 79-32 : The actual 'take off mass' is equivalent to ?

Dry operating mass plus take off fuel and the traffic load

exemple 303 Dry operating mass plus take-off fuel and the traffic load.

Question 79-33 : With respect to aeroplane loading in the planning phase which of the following statements is always correct .lm = landing mass.tom = take off mass.mtom = maximum take off mass.zfm = zero fuel mass.mzfm = maximum zero fuel mass.dom = dry operating mass ?

Lm = tom trip fuel

Landing mass = take off mass trip fuel .'mzfm = traffic load + dom' is not correct to be correct it would have to say 'mzfm = dom + maximum traffic load' exemple 307 Lm = tom - trip fuel.

Question 79-34 : Given an aeroplane with .maximum structural landing mass 125000 kg.maximum zero fuel mass 108500 kg.maximum structural take off mass 155000 kg.dry operating mass 82000 kg.scheduled trip fuel is 17000 kg and the reserve fuel is 5000 kg .assuming performance limitations are not restricting the ?

130500 kg and 26500 kg

Img135.the lowest value is our maximum traffic load 26500 kg .now our maximum permitted take off mass is .maximum zero fuel mass + fuel at take off = 108500 + 22000 = 130500 kg exemple 311 130500 kg and 26500 kg.

Question 79-35 : For the purpose of completing the mass and balance documentation the traffic load is considered to be equal to the take off mass ?

Less the operating mass

Take off mass = operating mass + traffic load. operating mass is 'dom + fuel at take off' .therefore you can say that the traffic load = tom operating mass exemple 315 Less the operating mass.

Question 79-36 : For the purpose of completing the mass and balance documentation the operating mass is considered to be dry operating mass plus ?

Take off fuel mass

/pdf/031 mass definitions pdf exemple 319 Take-off fuel mass.

Question 79-37 : When establishing the mass breakdown of an aeroplane the empty mass is defined as the sum of the ?

Standard empty mass plus specific equipment mass plus trapped fluids plus unusable fuel mass

Basic empty mass is the mass of an aeroplane plus standard items such as . unusable fuel and other unusable fluids. lubricating oil in engine and auxiliary units. fire extinguishers. pyrotechnics. emergency oxygen equipment. supplementary electronic equipment exemple 323 Standard empty mass plus specific equipment mass plus trapped fluids plus unusable fuel mass.

Question 79-38 : For the purpose of completing the mass and balance documentation the dry operating mass is defined as ?

The total mass of the aircraft ready for a specific type of operation excluding all usable fuel and traffic load

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf exemple 327 The total mass of the aircraft ready for a specific type of operation excluding all usable fuel and traffic load.

Question 79-39 : An aircraft's weighing schedule indicates that the empty mass is 57320 kg .the nominal dry operating mass is 60120 kg and the maximum zero fuel mass is given as 72100 kg .which of the following is a correct statement in relation to this aeroplane ?

Operational items have a mass of 2800 kg and the maximum traffic load for this aeroplane is 11980 kg

Operational items are the difference between dry operating mass and empty mass .60120 57320 = 2800 kg .the traffic load is the difference between mzfm and dom .72100 60120 = 11980 kg exemple 331 Operational items have a mass of 2800 kg and the maximum traffic load for this aeroplane is 11980 kg.

Question 79-40 : An aeroplane is to depart from an airfield where the performance limited take off mass is 89200 kg .certificated maximum masses are as follows .ramp taxi mass 89930 kg.maximum take off mass 89430 kg.maximum landing mass 71520 kg.maximum zero fuel mass 62050 kg.fuel on board at ramp .taxi fuel 600 ?

21080 kg

Img137.lowest limitation is 21080 kg exemple 335 21080 kg.


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