Question 85-1 : Which one of the statements below are correct regarding the maximum zero fuel mass mzfm 1 is a regulatory limitation2 is calculated for a maximum load factor of +35 g3 is based on the maximum permissible bending moment at the wing root4 is defined on the assumption that fuel is consumed from the ? [ Course landing ]

Question 85-2 : Given the following information what will be the expected landing mass at the destination maximum structural take off mass 8600 kg maximum structural landing mass 8600 kg zero fuel mass 6500 kg taxi fuel 15 kg contingency fuel 110 kg alternate fuel 600 kg final reserve fuel 130 kg trip fuel 970 kg ?

Question 85-3 : The total mass limit of a light twin is equal to 3200 lb the pilot weighs 200 lb and the combined mass of the passengers and their baggages is 650 lb assuming a dry operating mass of 1742 lb how much fuel can be loaded ?

367 kg.

Dry operating mass dom is the sum of the basic empty mass bem and the variable load crew crew baggage food beverages water etc excluding both usable fuel and payload so the pilot's mass is included in the domthus the fuel that can be loaded is total mass limit dom passengers & baggage = 3200 lb 1742 lb 650 lb = 808 lbconvert lb into kg 808 lb 22 lb per kg = 367 kgnote be careful with the units of measurement apply the unit conversions where necessary

Question 85-4 : You are flying in a twin engine piston aeroplane with a maximum structural landing mass of 4700 kg on a very hot and humid summer day your performance limited landing mass on this particular flight is equal to 4300 kg assuming that you did not burn the 30 kg of contingency fuel that you had loaded ?

4300 kg.

The maximum structural landing mass 4700 kg is the maximum permissible total aeroplane mass upon landing under normal circumstancesthe performance limited landing mass 4300 kg is the landing mass limited by similar destination airfield considerations and derived from performance calculationsthe regulated landing mass is the lower between the performance limited landing mass and the maximum structural landing mass 4300 kgnote the contingency fuel consumption is irrelevant to the question

Question 85-5 : Given the following information what is the underloadoverload allowed take off mass 4300 kg operating mass 3296 kg total fuel mass 650 kg mass of the crew and their baggage 187 kg traffic load 1014 kg ?

An overload of 10 kg.

Traffic load tl is is the total mass of passengers baggage and cargo including any ’non revenue’ loaddry operating mass dom is the total mass of the aeroplane ready for a specific type of operation excluding usable fuel and traffic load the mass includes items such as crew and crew baggage catering and removable passenger service equipment potable water and lavatory chemicals food and beveragesoperating mass om is the dom plus fuel but without traffic loadfor this question we will only consider the take off situation ignoring the landing and the zero fuel situation since the given data do not permit so subtracting from the allowed take off mass structural limit the om and the traffic load to figure out if the aircraft is overloaded or underloaded allowed tom om traffic load = 4300 kg 3296 kg 1014 kg = 10 kgthe ' ' sign indicates that it is overloaded by 10 kgnote be careful to avoid any double mass calculations due to the fact that some masses are already included in other masses eg fuel mass is included in om crew and crew baggage mass is included in dom dom is included in om and so on

Question 85-6 : In a turn flight which scenario will cause the most bending moment at the wing root ?

High zfm low fuel.

Maximum zero fuel mass mzfm is the maximum permissible mass of an aeroplane with no usable fuel the mzfm is a structural limit based on the bending moments of the wing rootall extra weight above the mzfm must comprise fuel only the added fuel which is invariably carried in the wing increases its stiffness and reduces its bending and torsion twisting fuel being stored in the wings is a useful feature as the weight of the fuel counteracts the lift generated and gives relief to the roots of the cantilever wing however with no fuel the wings are light and the fuselage is heavy which causes a large moment at the root of the wing therefore the maximum zero fuel weight implies a protection to the wing root against being overstressed as long as it is not exceeded lack of large amounts of fuel in the wings will not cause failure at the wing roots because of bending

Question 85-7 : According to the aircraft flight manual the maximum structural mass of your aircraft is 3650 lb which may be increased by 30 lb for taxiing it's a hot day and the performance charts restrict the performance limiting take off mass to 3540 lb what is the value of the regulated take off mass rtom ?

3540 lb.

The regulated take off mass rtom is the lowest of the performance limited take off mass pltom andmaximum structural take off mass mstom and it is the maximum mass at which the aircraft is able to depart from an airport in the given ambient conditionstherefore the rtom is 3540 lbnote ignore the taxi fuel of 30 lbs it is not a factor when considering take off masses as it is already burnt at that stage

Question 85-8 : The aircraft's fuel gauge is calibrated into litres and the required fuel that must be loaded is 1250 lb for the next flight if the fuel truck supplies fuel in litres how many litres are required with a specific gravity of 079 according to the operations manual ?

718 litres.

A relationship exists between litres and kilograms one litre of water weighs one kilograma similar relationship exists between pounds and imperial gallons ig one ig of water weighs ten poundsalso it is known that 1 kilogram is equal to 2205 libres or poundsto convert from volumes to mass or mass to volumes you need the specific gravity of the fuelthe specific gravity sg shows the relationship between litres and kilograms or between pounds and imperial gallonsspecific gravity 079 means that a volume of fuel weighs 79% of the equivalent volume of waterfor this question 1250 lb of fuel has a fuel volume of 1250 lb 2205 079 = 718 litres rounded

Question 85-9 : What is the definition of the maximum take off mass of an aeroplane ?

It is the maximum permissible total aeroplane mass at the start of the take off run.

The maximum take off mass mtom often referred to as maximum take off weight mtow of an aircraft is a fixed value defined by the aircraft manufacturerit is the maximum permissible total aeroplane mass at the start of the take off run due to structural or other limitsthe mtom is usually specified in units of kilograms or pounds and does not vary with environmental factors such as changes in temperature wind component runway etc

Question 85-10 : Given the following information calculate the actual zero fuel mass of the aircraftperformance limited take off mass 1860 lb basic empty mass 1130 lb take off fuel 312 lb unusable fuel 4 lb pilot's mass 180 lb passengers' mass 205 lb ?

1515 lb.

Bem1130 lb+ pilot180 lb+ passenger205 lb= zero fuel mass1515 lb remember the unusable fuel is already included in the bemthe question is asking for the actual zfm not the maximum zfm

Question 85-11 : You have just finished planning a flight and you require 3643 lb of fuel the fuel tanker supplies fuel in us gallon with the specific gravity of 084 how many us gallons do you require ?

520.

We first must convert 3643 lb into kg kilograms into litres using the specific gravity given thereafter litres l into us gallons usg 1 pounds lb to kilograms kg => lb × 0454 3643 lb x 0454 = 16539 kg 2 conversion between fuel volume and mass fuel mass in kg specific gravity density = fuel volume in l 16539 kg 084 = 1969 l 3 litres l to us gallons => litres 3785 1969 l 3785 = 520 usg

Question 85-12 : Given the following information what will be the expected landing mass at the destination maximum structural take off mass 7400 kg maximum structural landing mass 7400 kg zero fuel mass 5990 kg taxi fuel 15 kg contingency fuel 110 kg alternate fuel 275 kg final reserve fuel 250 kg trip fuel 760 kg ?

6625 kg.

Landing mass lm is the mass of the aircraft as it crosses the threshold on landing and equal to the zero fuel mass plus all the fuel amount remaining in the aircraft's tanks until landing the only fuel amount that is expected to be burnt is the trip fuelso the expected landing mass at the destination will be zero fuel mass 5990 kg + contingency fuel 110 kg + alternate fuel 275 kg + final reserve fuel 250 kg = 6625 kg

Question 85-13 : Given the following information calculate the maximum traffic load that can be carried maximum structural take off mass 4200 kg performance limited take off mass 4200 kg performance limited landing mass 3610 kg dry operating mass 2230 kg block fuel 865 kg trip fuel 440 kg taxi fuel 15 kg ?

970 kg.

Step 1 no mzfm information has been given so we can calculate the allowed take off mass as follows rtom rlm + trip fuel 3610 kg + 440 kg 4200 kg 4050 kg step 2 calculate the traffic load allowedtake off mass dom take off fuel = allowed traffic load4050 2230 850 block fuel 865 kg taxi fuel 15 kg = 970 kg

Question 85-14 : During the pre flight mass and balance calculations a fuel amount of 1850 kg has been decided to be carried for tankering purposes while the refuelling procedure was about to start the load controller informs the commander about a last minute change lmc of +285 kg given the following information ?

1618 kg.

The only limiting factor is the allowed take off mass 7205 kg because we are looking for the max block fuel the maximum zero fuel mass does not assume any fuel amountso the max additional fuel that can be carried is allowed tom dom tl before lmc lmc to fuel block taxi fuel = 7205 kg 4135 kg 1200 kg 285 kg 1430 kg 33 kg = 188 kgthus the maximum block fuel that can be carried is minimum required block fuel + max additional fuel = 1430 kg + 188 kg = 1618 kg which means that the initially desired block fuel of 1850 kg cannot be carried after the lmcorthe max allowable take off fuel that can be carried is allowed tom dom tl before lmc lmc = 7205 kg 4135 kg 1200 kg 285 kg = 1585 kgthus the maximum block fuel that can be carried is max allowable take off fuel + taxi fuel = 1585 kg + 33 kg = 1618 kg

Question 85-15 : Given the following information what is the underloadoverload maximum structural take off mass 6400 kg performance limited take off mass 6400 kg performance limited landing mass 5430 kg operating mass 4480 kg take off fuel 1440 kg trip fuel 1090 kg mass of the crew and their baggage 235 kg traffic ?

Question 85-16 : The maximum load specified in the loading sheet is exceeded by 10% which action should be taken ?

Reduce useful load.

The maximum load consists of the variable load and useful or disposable load it is a limit either structural or extracted after applying performance calculations and should never be exceededvariable load or operational items consists of the crew their baggage and any removable equipment required for the flight catering service equipment food water lavatory chemicals useful load or disposable load is made up of traffic load passengers baggage freight usable fuel usable oil where appropriatethe variable load cannot be reduced since it is necessary for the flight thus the only load that can be reduced is the useful load or disposable load so as not to exceed the maximum load

Question 85-17 : Determine the traffic load on board given basic empty mass 11 758 lb dry operating mass 12 470 lb zero fuel mass 12 912 lb ramp mass 16 512 lb ?

Question 85-18 : Given the following information calculate the traffic loadoperating mass 5720 kg zero fuel mass 5160 kg mzfm 5978 kg take off fuel 1735 kg block fuel 1770 kg ?

1175 kg.

Operating mass om this is the dry operating mass dom plus fuel but without any passengers and freightom = dom + take off fuel dom = om take off fuel dom = 5720 kg 1735 kg = 3985 kgzero fuel mass zfm this is the dry operating mass plus the traffic load but excluding all usable fuelzfm = dom + tl tl = zfm dom tl = 5160 kg 3985 kg = 1175 kg

Question 85-19 : What is the allowed traffic load mtom 6100 kg performance limited tom 6000 kg performance limited lm 5250 kg dom 3450 kg block fuel 950 kg trip fuel 530 kg taxi fuel 20 kg ?

1400 kg.

Traffic load tl is the difference between the actual take off mass and the operating mass om operating mass om = dom + fuel but without the traffic load 1 the actual take off mass is the lowest of mtom = 6100 kgperformance limited tom = 6000 kgperformance limited lm + trip fuel = 5250 kg + 530 kg = 5780 kg 2 allowed traffic load = tom om om = dom + block fuel taxi fuel om = 3450 kg + 950 kg 20 kg = 4380 kgallowed traffic load = tom om allowed traffic load = 5780 kg 4380 kg = 1400 kg

Question 85-20 : For the upcoming commercial flight from london to rome the aircraft has a crew of 7 members and 115 passengers to calculate the traffic load as part of the pre flight calculations we have the following information flight crew 4 male & 3 femalemale passengers 70female passengers 35children 10baggage ?

10 266 kg.

Traffic load is the total mass of passengers baggage cargo or freight including any non revenue load flight crew members are not part of the traffic load for this question the traffic load consists of 115 passengers their baggage 62 items and non revenue load 500 kg as stated in the question the standardized mass values for passengers and their baggage are as follows males 88 kg females 70 kg children 35 kg baggage 13 kgtherefore the traffic load will be 105 adults 70 male passengers + 35 female passengers + 10 children + 62 baggage items + non revenue load traffic load = 70 x 88 kg + 35 x 70 + 10 x 35 kg + 62 x 13 kg + 500 kg = 10 266 kg

Question 85-21 : Determine the underloadoverload given allowed take off mass 4300 kg operating mass 3169 kg total fuel mass 680 kg mass of the crew and their baggage 183 kg traffic load 1104 kg ?

An underload of 27 kg.

Traffic load tl is is the total mass of passengers baggage and cargo including any ’non revenue’ loaddry operating mass dom is the total mass of the aircraft ready for a specific type of operation excluding usable fuel and traffic load the mass includes items such as crew and crew baggage catering and removable passenger service equipment potable water and lavatory chemicals food and beveragesoperating mass om is the dom plus fuel but without traffic loadfor this question we will only consider the take off situation ignoring the landing and the zero fuel situation since the given data do not permit so subtracting from the allowed take off mass structural limit the om and the traffic load to figure out if the aircraft is overloaded or underloaded allowed tom om traffic load = 4300 kg 3169 kg 1104 = + 27 kgthe '+' sign indicates that it is underloaded by 27 kgnote be careful to avoid any double mass calculations due to the fact that some masses are already included in other masses eg fuel mass is included in om crew and crew baggage mass is included in dom dom is included in om and so on

Question 85-22 : Among the masses calculated for mass and balance calculations is also the regulated landing mass which of the following statements best describes the regulated landing mass ?

The lowest of the performance limited landing mass and the maximum structural landing mass.

The take off and landing weight will be constrained by either a structural limit or a performance limit influenced by environmental conditions on the given dayregulated landing mass the regulated landing mass rlm is the is the lowest of the performance limited landing mass and maximum structural limited landing mass the actual landing mass must not exceed this limitperformance limited landing mass the performance limited landing mass pllm is the maximum permissible total aircraft mass subject to the landing aerodrome or site limitations also taking the current metereological conditions into account this limit is not a set figure and needs to be calculated for each sector if the pllm is exceeded the aircraft may overrun the landing distance available and a go around might not be achievable

Question 85-23 : The maximum structural landing mass is… ?

A fixed value which is listed in the flight manual.

Maximum structural landing mass mslm is the maximum permissible total aircraft mass on landing in normal circumstances it generally depends on the landing gear strength or the landing impact loads on certain parts of the structure this limitation is listed in the aircraft flight manual andor the operational manualmaximum structural take off mass mstom is the maximum permissible total aircraft mass at the start of the take offmaximum structural taxi mass is the structural limitation of the mass of the aircraft at commencement of taximaximum zero fuel mass mzfm is the maximum permissible mass of an aircraft with no usable fuel

Question 85-24 : Given the following data for a flight what is the usable take off fuel mass loaded on board actual take off mass 62 800 kg dry operating mass 34 200 kg crew and its baggage mass 500 kg passengers and their baggage mass 13 300 kg cargo mass 5700 kg ?

9600 kg.

The take off mass tom is the actual mass of the aeroplane at the start of the takeoff run including everything and everyone contained within itthe dry operating mass dom is the total mass of the aeroplane ready for a specific type of operation excluding usable fuel and traffic load it is the bem plus the variable load the variable load includes crew and crew baggage the usable take off mass is calculated by deducting the dry operating mass dom and the combined mass of passengers their baggage and cargo traffic load from the total take off mass it's important to note that the dom already accounts for the crew and their baggageusable take off fuel = actual take off mass dom passengers and their baggage mass cargo massusable take off fuel = 62 800 kg 34 200 kg 13 300 kg 5700 kg = 9600 kg

Question 85-25 : During the planning of a flight the flight crew decides to start with a block fuel of 3130 lb in order to take off with the maximum structural take off mass on shut down from the previous flight the fuel of the aircraft was 850 lb the bowser calibrates fuel in litres if the specific gravity of the ?

1261 i.

Block fuel needed = 3130 lb fuel on shut down = 850 lb extra fuel needed = block fuel needed fuel on shut down = 3130 lb 850 lb = 2280 lb 1 covert 2280 lb into kg 1 kilogram is equal to 2205 libres or pounds1 kg = 2205 lb2280 lb 2205 = 1034 kg 2 covert 1034 kg into litres to convert from volumes to mass or mass to volumes you need the specific gravity of the fuel the specific gravity sg shows the relationship between litres and kilograms or between pounds and imperial gallonsspecific gravity 082 means that a volume of fuel weighs 82% of the equivalent volume of watermass kg specific gravity = volume l 1034 kg 082 = 1261 litres2280 lb of fuel has a fuel volume of 2280 lb 2205 082 = 1261 litres

Question 85-26 : The maximum structural take off mass of an aircraft is 242 000 kg its maximum taxi mass is 252 000 kg the taxi time is 32 minutes while the aircraft consumes fuel at 1350 kgh which of the following is the maximum take off mass that should be taken into account ?

242 000 kg.

Taxi fuel fuel consumption 1350 kg h taxi time 32 min taxi fuel = 1350 x 32 60 = 720 kgthe take off mass will be the lowest of maximum structural take off mass 242 000 kgmaximum taxi mass minus the taxi fuel 252 000 kg 720 kg = 251 280 kgtherefore the take off mass that respects both maximum structural take off mass limitation and maximum taxi mass limitation is 242 000 kg

Question 85-27 : The total mass limit of a light twin is equal to 3200 lb the pilot weighs 200 lb and the combined mass of the passengers and their baggages is 850 lb assuming a dry operating mass of 1742 lb how much fuel can be loaded ?

276 kg.

Dry operating mass dom is the sum of the basic empty mass bem and the variable load crew crew baggage food beverages water etc excluding both usable fuel and payload so the pilot's mass is included in the domthus the fuel that can be loaded is total mass limit dom passengers & baggage = 3200 lb 1742 lb 850 lb = 608 lbconvert lb into kg 608 lb 22 lb per kg = 276 kgnote be careful with the units of measurement apply the unit conversions where necessary

Question 85-28 : Based on the given data calculate the actual zero fuel mass operating mass 45 430 kg actual traffic load 14 730 kg useful load traffic load + take off fuel 25 280 kg ?

49 610 kg.

The useful load of 25 280 kg includes the traffic load and the take off fuel the traffic load is given as 14 730 kg and the take off fuel can be calculated useful load = traffic load + take off fuel take off fuel = usable load traffic load = 25 280 kg 14 730 kg = 10 550 kgdry operating mass dom is the total mass of the aeroplane ready for a specific type of operation excluding usable fuel and traffic load dom = om take off fuel = 45 430 kg 10 550 kg = 34 880 kgzero fuel mass zfm is the total mass of the aircraft not considering the usable fuel it is dry operating mass plus the traffic load zfm = dom + tl = 34 880 kg + 14 730 kg = 49 610 kg

Question 85-29 : The maximum structural take off mass of an aircraft is 442 235 kg its maximum taxi mass is 443 613 kg the taxi time is 32 minutes while the aircraft consumes fuel at 4320 kgh which of the following is the maximum take off mass that should be taken into account ?

441 309 kg.

Taxi fuel fuel consumption 4320 kg h taxi time 32 min taxi fuel = 4320 x 32 60 = 2304 kgthe take off mass will be the lowest of maximum structural take off mass 442 235 kgmaximum taxi mass minus the taxi fuel 443 613 kg 2304 kg = 441 309 kgtherefore the take off mass that respects both maximum structural take off mass limitation and maximum taxi mass limitation is 441 309 kg

Question 85-30 : An aircraft has the following weight limitations maximum take off mass mtom 61 200 kg maximum zero fuel mass mzfm 55 000 kg maximum landing mass mlm 56 500 kgthe following fuel quantities have been planned dry operating mass dom 29 900 kg taxi fuel 800 kg trip fuel 2800 kg alternate fuel ?

The aircraft has a 550 kg overload and the captain must reduce the traffic load by 550 kg.

There is no need to calculate any masses in this question we are being asked only what our solution is to the aircraft being over weightlooking at the answers 'the aircraft has a 550 kg overload and the captain must reduce the traffic load by 550 kg' > correct although this will cost the operator money the fuel that has been decided can be considered essential there is captain's fuel of 500 kg andextra fuel of 550 kgbut both of these are required for the safe operation of this flight'the aircraft is within limits and the flight can proceed without adjustments' > incorrect the question clearly states that the aircraft is 550 kg over weight the flight can simply not proceed in this condition'the aircraft has a 550 kg overload and the captain must remove 550 kg of extra fuel' > incorrect the extra fuel is required to compensate for the long taxi although we are dipping in to the flight planning syllabus if that extra fuel is required then it must be carried for the safe operation of the flight'the aircraft cannot depart because the mtom mlm or mzfm limits are exceeded' > incorrect at first look this seems a fine answer however the aircraft can depart if some of the weight is removed and the limits respected this answer perhaps indicates that the flight is grounded

Question 85-31 : Which is the correct formula for calculating taxiramp mass ?

Operating mass + traffic load tl + taxi fuel.

The taxi mass is the heaviest that the aircraft will be with all the fuel passengers bags cargo etc on board but with the engines yet to be started it is limited to a maximum structural limit maximum certificated taxi ramp mass this is the structural limit on the ramp and includes the total block fuel this is the heaviest an aircraft can ever bethis question is testing your knowledge of the various mass definitions and their relationship with one another as can be seen in the figure operating mass + traffic load tl = take off mass take off mass + taxi fuel = taxi mass

Question 85-32 : The loaded centre of gravity cg of an aeroplane is 713 mm aft of datumthe mean aerodynamic chord lies between station 524 mm aft and 1706 mm aftthe cg expressed as % mac mean aerodynamic chord is ?

16%.

100 x distance between leading edge and cg mac length100 x 713 524 1706 524 100 x 189 1182 = 1599%

Question 85-33 : The centre of gravity location of the aeroplane is normally computed along the ?

Longitudinal axis.

Question 85-34 : In mass and balance calculations which of the following describes the datum ?

It is the point on the aircraft designated by the manufacturer from which all centre of gravity measurements and calculations are made.

To be correct this is not necessarily a point 'on' the aircraftthe datum is an imaginary vertical line chosen on the longitudinal axis of the aeroplane specified by the designer from which all horizontal c of g measurements are made 159in most cases the datum is located in the vicinity of the aircraft nose usually the firewall 1065

Question 85-35 : An aircraft has its centre of gravity located 7 metres from the datum line and it has a weight of 49000 nthe moment about the datum is ?

343000 nm.

Arm = moment force7 = x 490007 x 49 000 = 343000 nmnm = newton multiplied by meter

Question 85-36 : Which one of the following is correct ?

Arm = moment force.

Question 85-37 : Which of the following statements is correct ?

A rear centered aircraft is less stable and stalls at a slower speed than a forward centered aircraft.

Question 85-38 : In mass and balance calculations the 'index' is ?

Is a figure without unit of measurement which represents a moment.

Index is the moment divided by a constant usually 1000 it is used to simplify the calculations by decreasing the values'a location in the aircraft identified by a number' is a positionand 'an imaginary vertical plane or line from which all measurements are taken' is the datum

Question 85-39 : Which of the following are the exact propositions 1 an aircraft belonging to a fleet must be weighed systematically every 48 months2 an aircraft not belonging to a fleet must be weighed systematically every 9 years ?

1 is incorrect 2 is incorrect.

An aeroplane must be re weighed at certain intervals at intervals of 4 years if individual aeroplane masses are used and 9 years if fleet masses are used

Question 85-40 : At what mass is an aircraft weighed ?

The basic empty 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