For the medium range transport aeroplane from the loading manual determine the maximum total volume of fuel which can be loaded into the main wing tanks Fuel density ?
Students > VFR
The flight preparation of a turbojet aeroplane provides the following data Take off runway limitation 185 000 kgLanding runway limitation 180 000 kgPlanned fuel consumption 11 500 kgFuel already ?
The crew of a transport aeroplane prepares a flight using the following data Block fuel 40 000 kg Trip fuel 29 000 kg Taxi fuel 800 kg Maximum take off mass 170 000 kg Maximum landing mass 148 500 ?
The dry operating mass of an aircraft 2000 kg the maximum take off mass landing and zero fuel mass are identical at 3500 kg the block fuel mass 550 kg and taxi fuel mass 50 kg the available mass of traffic load Traffic load the total mass of passengers baggage cargo including any non revenue load it means usable fuel not a part of 'traffic loa traffic load = maximum take off mass (dry operating mass + fuel on board at take off) traffic load = 3500 (2000 + 500) = 1000 kg. 
The basic empty mass of an aircraft 30000 kg the masses of following items are catering 300 kg safety and rescue material nil fly away kit nil crew inclusive crew baggage 365 kg fuel at take off 3000 kg unusable fuel 120 kg passengers baggage cargo 8000 kgthe dry operating mass The dry operating mass = basic empty mass + standard items the basic empty mass includes unuseable fuel dry operating mass = 30000 + 300 + 365 = 30665 kg the dom includes unusable fuel since unusable fuel a part of basic empty mass dry operating mass = the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load this mass includes items such as + crew crew baggage + catering removable passenger service equipment (food beverages potable water lavatory chemicals etc ) + special operational equipment (e g stretchers rescue hoist cargo sling). 
By adding to basic empty mass following fixed necessary equipment a specific flight catering safety and rescue equipment fly away kit crew we get Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. 
An aircraft dry operating mass 3000 kg the maximum take off landing and zero fuel mass are identical at 5200 kg ramp fuel 650 kg taxi fuel 50 kg the maximum traffic load Maximum traffic load = 5200 kg 600 kg (at take off) 3000 kg = 1600 kg. Question 65-8
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 780 kgthe expected landing mass at destination will be Fuel on board at landing 90 + 300 + 400 = 790 kg expected landing mass at destination = zero fuel mass + fuel on board at landing expected landing mass at destination = 6210 + 790 = 7000 kg. Question 65-9
Given zero fuel mass 6660 kgtrip fuel 990 kgblock fuel 1540 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 = 6660 + 1540 25 = 8175 kg. Question 65-10
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. Question 65-11
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. Question 65-12
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. Question 65-13
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 65-14
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 65-15
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 65-16
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 65-17
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 65-18
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 65-19
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 65-20
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 65-21
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 65-22
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 65-23
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 65-24
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 65-25
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 65-26
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 65-27
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 65-28
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 65-29
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 65-30
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 65-31
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 65-32
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 65-33
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 65-34
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 65-35
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 65-36
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 65-37
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 65-38
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 65-39
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 65-40
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.
Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.
2559 Free Training Exam