An aircraft Dry Operating Mass is 3000 kg The maximum take off landing and zero fuel mass are identical at 5200 kg Ramp fuel is 650 kg the taxi fuel ?
Mandatory > landing
Given Maximum structural take off mass 8350 kgMaximum structural landing mass 8350 kgZero Fuel Mass 6210 kgTaxi Fuel 10 kgContingency Fuel 90 kgAlternate Fuel 300 kgFinal Reserve Fuel 400 kgTrip Fuel ?
Given Zero Fuel Mass 6660 kgTrip Fuel 990 kgBlock Fuel 1540 kgTaxi Fuel 25 kgThe actual Take Off Mass is equal to ?
Given zero fuel mass 4920 kgtrip fuel 880 kgblock fuel 1330 kgtaxi fuel 25 kgthe actual take off mass equal to Actual take off mass = zero fuel mass + block fuel taxi fuel actual take off mass = 4920 + 1330 25 = 6225 kg. 
Given maximum structural take off mass 8600 kgmaximum structural landing mass 8600 kgzero fuel mass 6500 kgtaxi fuel 15 kgcontingency fuel 110 kgalternate fuel 600 kgfinal reserve fuel 130 kgtrip fuel 970 kgthe expected landing mass at destination will be Fuel on board at landing 110 + 600 + 130 = 840 kg expected landing mass at destination = zero fuel mass + fuel on board at landing expected landing mass at destination = 6500 + 840 = 7340 kg. 
Given maximum structural take off mass 7400 kgmaximum structural landing mass 7400 kgzero fuel mass 5990 kgtaxi fuel 15 kgcontingency fuel 110 kgalternate fuel 275 kgfinal reserve fuel 250 kgtrip fuel 760 kgthe expected landing mass at destination will be Fuel on board at landing 110 + 275 + 250 = 635 kg expected landing mass at destination = zero fuel mass + fuel on board at landing expected landing mass at destination = 5990 + 635 = 6625 kg. 
Given dry operating mass 4920 kgzero fuel mass 5740 kgtrip fuel 670 kgtake off fuel 1050 kgthe traffic load Dry operating mass the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load traffic load the total mass of passengers baggage cargo including any non revenue load 5740 4920 = 820 kg. Question 67-8
Given dry operating mass 5320 kgzero fuel mass 6790 kgtrip fuel 770 kgtake off fuel 1310 kgthe traffic load Dry operating mass the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load traffic load the total mass of passengers baggage cargo including any non revenue load 6790 5320 = 1470 kg. Question 67-9
Given dry operating mass 5210 kgzero fuel mass 6230 kgtrip fuel 990 kgtake off fuel 1590 kgthe traffic load Dry operating mass the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load traffic load the total mass of passengers baggage cargo including any non revenue load 6230 5210 = 1020 kg. Question 67-10
Given zero fuel mass 4770 kgtrip fuel 1040 kgblock fuel 1960 kgtaxi fuel 20 kgthe actual take off mass equal to Actual take off mass = zero fuel mass + block fuel taxi fuel actual take off mass = 4770 + 1960 20 = 6710 kg. Question 67-11
Considering only structural limitations on very short legs with minimum take off fuel traffic load normally limited Maximum zero fuel mass. Maximum zero fuel mass exists to prevent wing bending if too much weight concentrated in fuselage then wings will flex dramatically in flight by placing fuel into wings weight distributed more evenly there not a concentration of mass in one area on very short legs with minimum take off fuel (it means very low fuel in wings no fuel in center tank) traffic load will be limited due to this bending moment at wing roots. Question 67-12
Basic empty mass A component of dry operating mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-13
Allowed traffic load the difference between Allowed take off mass operating mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-14
The operating mass of an aeroplane The dry operating mass plus take off fuel mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-15
The maximum zero fuel mass A structural limit listed in flight manual as a fixed value. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-16
The maximum structural take off mass A limit which may not be exceeded any take off. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-17
To calculate allowable take off mass factors to be taken into account include Maximum landing mass augmented the fuel burn. Maximum landing mass the trip fuel correct because you can take off at mlm plus trip fuel because you would land at mlm in mlm would be reserve contingency diversion fuel maximum take off mass minus trip fuel this nonsense! the mtom minus trip fuel will not give allowable tom! maximum landing mass the fuel on board at take off it can't be mlm plus take off fuel because this would mean you would land above mlm as you would only plan to burn trip fuel thus you would be landing at mlm plus reserve contingency diversion fuel maximum zero fuel mass the trip fuel this cannot be right because allowable tom not mzfm plus trip fuel but mzfm plus take off fuel assuming it doesn't exceed mtom. Question 67-18
The traffic load defined as total mass of Passengers baggage cargo including any non revenue load. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-19
Given dry operating mass = 38 000 kgmaximum structural take off mass = 72 000 kgmaximum landing mass = 65 000 kgmaximum zero fuel mass = 61 000 kgtrip fuel = 8 000 kgtake off fuel = 10 300 kgthe maximum allowed take off mass and payload are respectively Passengers baggage cargo including any non revenue load. Zfm the mass of aeroplane minus all useable fuel payload the load we are carrying that earns revenue payload = maximum zero fuel mass dom 61000 38000 = 23000 kg maximum allowed take off mass = payload + dom + fuel 23000 + 38000 + 10300 = 71300 kg we are below maximum structural take off mass we will be below maximum landing mass (71300 8000 = 63300 kg). Question 67-20
In relation to an aeroplane term 'basic empty mas includes mass of aeroplane structure complete with its powerplants systems furnishings and other items of equipment considered to be an integral part of particular aeroplane configuration its value Found in latest version of weighing schedule as corrected to allow modifications. The 'basic empty mas recorded in weighing schedule not in flight manual. Question 67-21
Prior to departure medium range twin jet aeroplane loaded with maximum fuel of 20100 litres at a fuel density specific gravity of 0 78 using following data performance limited take off mass 67200 kgperformance limited landing mass 54200 kgdry operating mass 34930 kgtaxi fuel 250 kgtrip fuel 9250 kgcontingency and holding fuel 850 kgalternate fuel 700 kgthe maximum permissible traffic load Found in latest version of weighing schedule as corrected to allow modifications. Question states 'prior to departure jet loaded with maximum fue 20100 litres = 15680 kg traffic load possible at take off 67200 kg (34930 kg + 15680 kg) = 16590 kg at landing taxi trip fuel have been burnt 15680 (250 + 9250) = 6180 kg of fuel remains in our aeroplane traffic load possible at landing 54200 (34930 kg + 6180 kg) = 13090 kg. Question 67-22
The operator of an aircraft equipped with 50 seats uses standard masses passengers and baggage during preparation of a scheduled flight a group of passengers present themselves at check in desk it apparent that even lightest of these exceeds value of declared standard mass The operator should use individual masses of passengers or alter standard masss. Easa air ops mass values passengers baggage (g) on any flight identified as carrying a significant number of passengers whose masses including hand baggage are expected to exceed standard passenger mass an operator must determine actual mass of such passengers weighing or adding an adequate mass increment. Question 67-23
The following data extracted from an aeroplane's loading manifest performance limited take off mass 93500 kgexpected landing mass at destination 81700 kgmaximum certificated landing mass 86300 kgfuel on board 16500 kgduring flight a diversion made to an en route alternate which not 'performance limite landing fuel remaining at landing 10300 kg the landing mass Is 873 kg excess structural stress could result. Fuel on board fuel remaining at landing = 16500 kg 10300 kg = 6200 kg we only have one mass givent take off performance limited take off mass thus landing mass will be 93500 kg 6200 kg = 87300 kg structural stress could result (maximum certificated landing mass 86300 kg). Question 67-24
The following data relates to a planned flight of an aeroplane dry operational mass 60 520 kgperformance limited take off mass 92 750 kgstructural limited take off mass 88 750 kgperformance limited landing mass 72 250 kgstructural limited landing mass 73 500 kgmaximum zero fuel mass 67 530 kgfuel on board at take off trip fuel 12500 kg contingency and final reserve fuel 2300 kg alternate fuel 1700 kgusing this data as appropriate calculate maximum traffic load that can be carried Is 873 kg excess structural stress could result. Fuel on board fuel remaining at landing = 16500 kg 10300 kg = 6200 kg we only have one mass givent take off performance limited take off mass thus landing mass will be 93500 kg 6200 kg = 87300 kg structural stress could result (maximum certificated landing mass 86300 kg). Question 67-25
Maximum allowed take off mass limit 37 200kgdry operating mass 21 600 kgtake off fuel 8 500 kgpassengers on board male 33 female 32 children 5baggage 880 kgthe company uses standard passenger mass systems allowed regulations the flight not a holiday charter in these conditions maximum cargo that may be loaded Is 873 kg excess structural stress could result. Adults = (33 males + 32 females) x 84 kg = 5460 kg children = 5 x 35 kg = 175 kg passenger load 5460 kg + 175 kg = 5635 kg mtom (dom + fuel + passenger + baggage) 37200 kg (21600 + 8500 + 5635 + 880) = 585 kg. Question 67-26
The take off mass of an aircraft 8470 kg total fuel on board 1600 kg including 450 kg reserve fuel and 29 kg of unusable fuel the traffic load 770 kg what the zero fuel mass Is 873 kg excess structural stress could result. Total fuel on board (including unusable fuel) = 1600 kg take off mass minus total fuel on board = 8470 1600 = 6870 kg unusable fuel is included within zero fuel mass = 6870 + 29 = 6899 kg. Question 67-27
Traffic load the difference between The take off mass the operating mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-28
The basic empty mass of an aircraft 30000 kg given following data calculate dom dry operating mass catering 300 kg crew 600 kg trip fuel 1200 kg unusable fuel 30 kg traffic load 2500 kg The take off mass the operating mass. Dry operating mass = basic empty mass + variable load dry operating mass = 30000 kg + 300 kg + 600 kg = 30900 kg (unusable fuel already included in basic empty mass). Question 67-29
Which true of aircraft basic empty mass It a component of dry operating mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-30
The maximum quantity of fuel that can be loaded into an aircraft's tanks given as 3800 us gallons if fuel density specific gravity given as 0 79 mass of fuel which may be loaded It a component of dry operating mass. 1 us gallon = 3 78 litres (3 785411784 litres) 3800 x 3 785411784 x 0 79 = 11363 8 kg. Question 67-31
Determine landing mass the following single engine aeroplane given standard empty mass 1764 lbs optional equipment 35 lbs pilot + front seat passenger 300 lbs cargo mass 350 lbs fuel quantity at brakes release 60 gal trip fuel 35 gal fuel density 6 lbs/gal It a component of dry operating mass. Take off mass = 1764 + 35 + 300 + 350 + (6 x 60)= 2809 lbs expected landing mass = 2809 (6 x 35) = 2599 lbs. Question 67-32
Given maximum allowable take off mass 64400 kgmaximum landing mass 56200 kgmaximum zero fuel mass 53000 kgdry operating mass 35500 kgtraffic load 14500 kgtrip fuel 4900 kgtake off fuel 7400 kgfind maximum additional load It a component of dry operating mass. Take off mass will be 35500 + 14500 + 7400 = 57400 kg landing mass will be 57400 4900 = 52500 kg maximum landing mass 56200 kg so we can add 56200 52500 kg = 3700 kg last check maximum zero fuel mass of 53000 kg 35500 + 14500 + 3700 = 53700 kg we are exceeding this limit we need to reduce additional load 700 kg 3700 700 = 3000 kg. Question 67-33
The traffic load a part of the It a component of dry operating mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-34
The si units of running or linear load are It a component of dry operating mass. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 67-35
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 the maximum fuel that can be carried at take off It a component of dry operating mass. Maximum fuel at take off = maximum take off mass (dry operating mass + traffic load) maximum fuel at take off = 66200 (33500 + 10600) = 22100 kg this more than what fuel tanks can contains therefore we can fill them full we will have to remove 200 kg taxi to know our maximum possible fuel at take off 2500 x 0 78 = 17550 kg 17550 200 = 17350 kg. Question 67-36
An aircraft to depart at an take off mass of 8220 kg take off fuel including reserve fuel of 710 kg 1750 kg the basic empty mass 4920 kg considering a total mass of crew and operating items of 420 kg permissible traffic load will be It a component of dry operating mass. 8220 1750 4920 420 = 1130 kg. Question 67-37
The take off mass of an aircraft 6700 kg total fuel on board 800 kg including 200 kg reserve fuel and 19 kg of unusable fuel the traffic load 900 kg the zero fuel mass It a component of dry operating mass. The total fuel includes 19 kg of unuseable fuel this unuseable fuel part of basic empty mass therefore part of dom tom useable fuel = zfm 6700 (800 19) = 5919 kg. Question 67-38
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 It a component of dry operating mass. 1120 x 0 79 = 885 kg. Question 67-39
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 It a component of dry operating mass. 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 67-40
The dry operating mass of an aircraft the sum of basic empty mass + crew + It a component of dry operating mass. 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.
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