Given fuel density of 0 78 kg/l Dry Operating Mass = 33500 kg traffic load = 10600 kg Maximum Take off Mass = 66200 kg Taxi fuel = 200 kg fuel tank capacity = 22500 L ?
Experience > lift > off
An aircraft is to depart at an Take Off Mass of 8220 kg Take off Fuel including Reserve Fuel of 710 kg is 1750 kg The Basic Empty Mass is 4920 kg Considering a total mass of crew and operating items ?
The Take off Mass of an aircraft is 6700 kg Total fuel on board is 800 kg including 200 kg reserve fuel and 19 kg of unusable fuel The traffic load is 900 kg The Zero Fuel Mass is ?
The maximum quantity of fuel that can be loaded into an aircraft's tanks given as 1120 l if fuel density specific gravity given as 0 79 mass of fuel which may be loaded 1120 x 0 79 = 885 kg. 
Given dry operating mass 2800 kg trip fuel 300 kg traffic load 400 kg maximum take off mass 4200 kg maximum landing mass 3700 kgthe maximum fuel load zero fuel mass= 2800 + 400 = 3200 kg useful limitation = lowest value from following two values maximum take off mass 4200 kg maximum landing mass + trip fuel = 3700 + 300 = 4000 kg (this our 'useful limitation') maximum fuel load = 4000 3200 = 800 kg. 
The dry operating mass of an aircraft the sum of basic empty mass + crew + zero fuel mass= 2800 + 400 = 3200 kg useful limitation = lowest value from following two values maximum take off mass 4200 kg maximum landing mass + trip fuel = 3700 + 300 = 4000 kg (this our 'useful limitation') maximum fuel load = 4000 3200 = 800 kg. 
The zero fuel mass the mass of aircraft Excluding usable fuel. zero fuel mass= 2800 + 400 = 3200 kg useful limitation = lowest value from following two values maximum take off mass 4200 kg maximum landing mass + trip fuel = 3700 + 300 = 4000 kg (this our 'useful limitation') maximum fuel load = 4000 3200 = 800 kg. Question 66-8
The baggage compartment of a particular aircraft 1 2 m wide 1 4 m long and has a maximum floor loading of 500 kg per square metre what the maximum capacity of baggage compartment limited maximum floor load only Excluding usable fuel. 1 2 x 1 4 x 500 = 840 kg. Question 66-9
What the reason knowing accurately what your weight during flight So you can fly at optimum cruise altitude. 1 2 x 1 4 x 500 = 840 kg. Question 66-10
Basic empty mass basic mass the mass of an aircraft plus standard items such as So you can fly at optimum cruise altitude. Basic empty mass (basic mass) the mass of an aeroplane plus standard items such as unusable fuel other unusable fluids lubricating oil in engine auxiliary units fire extinguishers pyrotechnics emergency oxygen equipment supplementary electronic equipment. Question 66-11
The following data applies to an aircraft which about to take off maximum structural take off mass 8400 kgperformance limited take off mass 7920 kgdry operating mass 5230 kgcrew and operating items 460 kgtake off fuel 980 kgfrom this data calculate mass of useful load So you can fly at optimum cruise altitude. Useful load = take off mass dry operating mass useful load = 7920 kg 5230 kg useful load = 2690 kg. Question 66-12
1 ton equals approximately So you can fly at optimum cruise altitude. Useful load = take off mass dry operating mass useful load = 7920 kg 5230 kg useful load = 2690 kg. Question 66-13
Given basic empty mass 5300 kgdry operating mass 5500 kgzero fuel mass 5980 kgtake off mass 7980 kgthe useful load So you can fly at optimum cruise altitude. Useful load = take off mass dry operating mass useful load = 7980 kg 5500 kg useful load = 2480 kg. Question 66-14
Based on actual conditions an aeroplane has following performance take off mass limitations flaps 0° 10° 15°runway 4100 4400 4600climb 4700 4500 4200masses are in kg structural limits take off/landing/zero fuel 4 300 kgthe maximum take off mass So you can fly at optimum cruise altitude. You must compare 4300kg structural limit with runway limit climb limit at each flap setting select lowest at flap 0° lowest limit will be 4100 kg at flap 10 lowest limit will be 4300 kg at flap 15 lowest limit 4200 kg now pick highest of three we can safely get airborne at 4300 kg at flap 10°. Question 66-15
Mass individual passengers to be carried on an aeroplane may be determined from a verbal statement or on behalf of passengers if number of Passenger seats available less than . Where number of passenger seats available less than 10 passenger mass may be determined verbal statement. Question 66-16
The regulated take off mass The lower of performance limited take off mass maximum structural take off mass. Regulated take off mass = lower of take off mass subject to departure airfield limitations (performance limited take off mass) and maximum permissible total mass of aircraft at commencement of take off (maximum structural take off mass). Question 66-17
Given container size length x width x height 0 8 x 0 8 x 0 8 mcontainer has 2 supports 0 2 m each in longitudinal direction maximum running load 1915 kg/mcalculate maximum total mass of loaded container without exceeding maximum permissible running load The lower of performance limited take off mass maximum structural take off mass. If maximum running load 1915 kg (1915 kg per 1 m in longitudinal direction) we need to convert this value down to both ground supports 2 x ( 0 2) m = 0 4 m the total length of both ground supports 0 4 m (= total load pressing down on a running load length of 0 4 m) 1915 kg x 0 4m = 766 kg. Question 66-18
From pilot's flight manual determine maximum total volume of fuel which can be loaded into standard tank version 1064 The lower of performance limited take off mass maximum structural take off mass. Read question carefully if it asking mass or volume total volume of fuel 487 + 405 + 236 + 324 + 246 + 423 + 246 = 2367 litres total mass of fuel 2367 x 0 79 = 1870 kg. Question 66-19
The basic advantage of standard size containers Standard size containers are designed to fit lock into cargo compartment maximum space efficiency. Read question carefully if it asking mass or volume total volume of fuel 487 + 405 + 236 + 324 + 246 + 423 + 246 = 2367 litres total mass of fuel 2367 x 0 79 = 1870 kg. Question 66-20
From pilot's flight manual determine maximum total mass of fuel which can be loaded into standard tank version 1064 Standard size containers are designed to fit lock into cargo compartment maximum space efficiency. Read question carefully if it asking mass or volume total volume of fuel 487 + 405 + 236 + 324 + 246 + 423 + 246 = 2367 litres total mass of fuel 2367 x 0 79 = 1870 kg. Question 66-21
The maximum floor loading of cargo compartment specified to be 732 kg/m² which the smallest given pallet size acceptable to load a box of 826 kg Standard size containers are designed to fit lock into cargo compartment maximum space efficiency. Floor loading limit 732 kg/m² ==> you can put maximum 732 kg to 1 m² that's limit you have 826 kg to load so yo need more than 1 m² space it's ==> 826/732= 1 13 m² if you put 826 kg evenly on 1 13 m² it will be ok so minimum pallet size should be 1 13 m² pallets 1 25 m x 1 25 m ==> 1 56 m² ==> acceptable 1 3 m x 1 3 m ==> 1 69 m²==> acceptable 1 2 m x 1 2 m ==> 1 44 m²==> acceptable 1 05 m x 1 05 m ==> 1 10 m²==> not acceptable question asks smallest pallet smallest one among acceptable pallets ==> 1 2 m x 1 2 m ==> 1 44 m². Question 66-22
The term 'landing mas at destination defined as Final reserve fuel alternate fuel contingency fuel plus zero fuel mass. Floor loading limit 732 kg/m² ==> you can put maximum 732 kg to 1 m² that's limit you have 826 kg to load so yo need more than 1 m² space it's ==> 826/732= 1 13 m² if you put 826 kg evenly on 1 13 m² it will be ok so minimum pallet size should be 1 13 m² pallets 1 25 m x 1 25 m ==> 1 56 m² ==> acceptable 1 3 m x 1 3 m ==> 1 69 m²==> acceptable 1 2 m x 1 2 m ==> 1 44 m²==> acceptable 1 05 m x 1 05 m ==> 1 10 m²==> not acceptable question asks smallest pallet smallest one among acceptable pallets ==> 1 2 m x 1 2 m ==> 1 44 m². Question 66-23
Determine take off mass tom the following single engine aeroplane standard empty mass 1764 lbsoptional equipment 35 lbspilot + front seat passenger 300 lbscargo mass 350 lbsfuel quantity at brakes release 60 gal trip fuel 35 gal fuel density 6 lbs/gal Final reserve fuel alternate fuel contingency fuel plus zero fuel mass. Take off mass = 1764 + 35 + 300 + 350 + (6 x 60) take off mass = 2809 lbs. Question 66-24
Refer to figure 031 15 calculate maximum fuel mass the centre tank in pounds Final reserve fuel alternate fuel contingency fuel plus zero fuel mass. The maximum mass of fuel in centre tank 7008 kg convert this value into pounds to get 15450 lbs (1kg = 2 2 lbs). Question 66-25
What the reason cargo loads to be tied down Preventing such loads from moving to remain within cg limits of aircraft. The maximum mass of fuel in centre tank 7008 kg convert this value into pounds to get 15450 lbs (1kg = 2 2 lbs). Question 66-26
The structural limitation of a baggage compartment 50 lb/ft a load has a mass of 320 kg and has to be distributed over an area of at least Preventing such loads from moving to remain within cg limits of aircraft. 1 m = 3 28 ft therefore 1 m² = 10 76 ft² convert limitation of 50 lb/ft² to kg m² 50 lb = 22 68 kg 10 76 ft² x 22 68 kg = 244 kg/10 76 ft² or 244 kg/m² the mass given the question 320 kg to find distribution we need to use rule of proportion to find aera a mass of 320 kg 1m² / 244 kg x 320 kg = 1 31 m². Question 66-27
The loaded centre of gravity cg of an aeroplane 713 mm aft of datum the mean aerodynamic chord lies between station 524 mm aft and 1706 mm aft the cg expressed as % mac mean aerodynamic chord Preventing such loads from moving to remain within cg limits of aircraft. 100 x distance between leading edge cg / mac length 100 x (713 524)/ (1706 524) 100 x 189 / 1182 = 15 99%. Question 66-28
The centre of gravity location of aeroplane normally computed along Preventing such loads from moving to remain within cg limits of aircraft. 100 x distance between leading edge cg / mac length 100 x (713 524)/ (1706 524) 100 x 189 / 1182 = 15 99%. Question 66-29
In mass and balance calculations which of following describes datum It the point on aircraft designated the manufacturer from which all centre of gravity measurements calculations are made. To be correct this not necessarily a point 'on' aircraft the datum an imaginary vertical line chosen on longitudinal axis of aeroplane specified the designer from which all horizontal c of g measurements are made in most cases datum located in vicinity of aircraft nose usually firewall . Question 66-30
An aircraft has its centre of gravity located 7 metres from datum line and it has a weight of 49000 n the moment about datum It the point on aircraft designated the manufacturer from which all centre of gravity measurements calculations are made. Arm = moment / force 7 = x / 49000 7 x 49 000 = 343000 nm nm = newton multiplied meter. Question 66-31
Which one of following correct It the point on aircraft designated the manufacturer from which all centre of gravity measurements calculations are made. Arm = moment / force 7 = x / 49000 7 x 49 000 = 343000 nm nm = newton multiplied meter. Question 66-32
Which of following statements correct A rear centered aircraft less stable stalls at a slower speed than a forward centered aircraft. Arm = moment / force 7 = x / 49000 7 x 49 000 = 343000 nm nm = newton multiplied meter. Question 66-33
In mass and balance calculations 'index' Is a figure without unit of measurement which represents a moment. Index the moment divided a constant usually 1000 it used to simplify calculations decreasing values 'a location in aircraft identified a number' a position and 'an imaginary vertical plane or line from which all measurements are taken' the datum. Question 66-34
Which of following are 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 incorrect 2 incorrect. An aeroplane must be re weighed at certain intervals at intervals of 4 years if individual aeroplane masses are used 9 years if fleet masses are used. Question 66-35
At what mass an aircraft weighed The basic empty mass. Basic empty mass the mass of an aeroplane plus standard items such as unusable fuel other unusable fluids lubricating oil in engine auxiliary units fire extinguishers pyrotechnics emergency oxygen equipment supplementary electronic equipment. Question 66-36
An aircraft weighed and following recordings are made nose wheel assembly scale 5330 kgleft main wheel assembly scale 12370 kgright main wheel assembly scale 12480 kgif 'fixed item amount to a mass of 1780 kg with a crew mass of 545 kg empty mass as entered in weight schedule The basic empty mass. The 'fixed item are parts of aircraft when it weighed you don't have to add them again to find empty mass 5330 + 12370 + 12480 = 30180 kg. Question 66-37
If individual masses are used mass of an aircraft must be determined prior to initial entry into service and thereafter At intervals of 4 years if no modifications have taken place. Easa air ops regulation (eu) no 965/2012 cat pol mab 100 mass balance loading (a) during any phase of operation loading mass centre of gravity (cg) of aircraft shall comply with limitations specified in afm or operations manual if more restrictive (b) the operator shall establish mass the cg of any aircraft actual weighing prior to initial entry into service thereafter at intervals of four years if individual aircraft masses are used or nine years if fleet masses are used the accumulated effects of modifications repairs on mass balance shall be accounted and properly documented aircraft shall be reweighed if effect of modifications on mass balance not accurately known (c) the weighing shall be accomplished the manufacturer of aircraft or an approved maintenance organisation (d) the operator shall determine mass of all operating items crew members included in aircraft dry operating mass weighing or using standard masses the influence of their position on aircraft's cg shall be determined (e) the operator shall establish mass of traffic load including any ballast actual weighing or determining mass of traffic load in accordance with standard passenger baggage masses (f) in addition to standard masses passengers checked baggage operator can use standard masses other load items if it demonstrates to competent authority that these items have same mass or that their masses are within specified tolerances (g) the operator shall determine mass of fuel load using actual density or if not known density calculated in accordance with a method specified in operations manual (h) the operator shall ensure that loading of (1) its aircraft performed under supervision of qualified personnel and (2) traffic load consistent with data used the calculation of aircraft mass balance (i)the operator shall comply with additional structural limits such as floor strength limitations maximum load per running metre maximum mass per cargo compartment the maximum seating limit for helicopters in addition operator shall take account of in flight changes in loading (j) the operator shall specify in operations manual principles methods involved in loading in mass balance system that meet requirements contained in (a) to (i) this system shall cover all types of intended operations. Question 66-38
At maximum landing mass range of safe cg positions as determined from appropriate graph in loading manual 206 Forward limit 7 4% mac aft limit 27 % mac. Easa air ops regulation (eu) no 965/2012 cat pol mab 100 mass balance loading (a) during any phase of operation loading mass centre of gravity (cg) of aircraft shall comply with limitations specified in afm or operations manual if more restrictive (b) the operator shall establish mass the cg of any aircraft actual weighing prior to initial entry into service thereafter at intervals of four years if individual aircraft masses are used or nine years if fleet masses are used the accumulated effects of modifications repairs on mass balance shall be accounted and properly documented aircraft shall be reweighed if effect of modifications on mass balance not accurately known (c) the weighing shall be accomplished the manufacturer of aircraft or an approved maintenance organisation (d) the operator shall determine mass of all operating items crew members included in aircraft dry operating mass weighing or using standard masses the influence of their position on aircraft's cg shall be determined (e) the operator shall establish mass of traffic load including any ballast actual weighing or determining mass of traffic load in accordance with standard passenger baggage masses (f) in addition to standard masses passengers checked baggage operator can use standard masses other load items if it demonstrates to competent authority that these items have same mass or that their masses are within specified tolerances (g) the operator shall determine mass of fuel load using actual density or if not known density calculated in accordance with a method specified in operations manual (h) the operator shall ensure that loading of (1) its aircraft performed under supervision of qualified personnel and (2) traffic load consistent with data used the calculation of aircraft mass balance (i)the operator shall comply with additional structural limits such as floor strength limitations maximum load per running metre maximum mass per cargo compartment the maximum seating limit for helicopters in addition operator shall take account of in flight changes in loading (j) the operator shall specify in operations manual principles methods involved in loading in mass balance system that meet requirements contained in (a) to (i) this system shall cover all types of intended operations. Question 66-39
At a given mass cg position at 15% mac if leading edge of mac at a position 625 6 inches aft of datum and mac given as 134 5 inches determine position of cg in relation to datum 645 78 inches aft of datum. The mac lenght 134 5 inches the cg at 15% of this distance back from leading edge 15% of 134 5 inches 20 175 inches if leading edge of mac at 625 6 inches aft of datum cg will be at 625 6 + 20 175 = 645 775 inches aft of datum. Question 66-40
The aeroplane has a take off mass of 58 000 kg at this mass range of safe cg positions as determined from appropriate graph in loading manual 207 Forward limit 8 % mac aft limit 26 5% mac. The mac lenght 134 5 inches the cg at 15% of this distance back from leading edge 15% of 134 5 inches 20 175 inches if leading edge of mac at 625 6 inches aft of datum cg will be at 625 6 + 20 175 = 645 775 inches aft of datum.
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