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Question 82-1 : Considering only structural limitations, on very short legs with minimum take off fuel, the traffic load is normally limited by ? [ Attainment AIM ]

Maximum zero fuel mass.

Maximum zero fuel mass exists to prevent wing bending. if too much weight is concentrated in the fuselage then the wings will flex dramatically in flight. by placing fuel into the wings, the weight is distributed more evenly, there is not a concentration of mass in one area..on very short legs with minimum take off fuel it means very low fuel in the wings and no fuel in center tank , the traffic load will be limited due to this bending moment at the wing roots.

Question 82-2 : Basic empty mass is ?

A component of dry operating mass.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 186 A component of dry operating mass.

Question 82-3 : Allowed traffic load is the difference between ?

Allowed take off mass and operating mass.

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

Question 82-4 : The operating mass of an aeroplane is ?

The dry operating mass plus the take off fuel mass.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 194 The dry operating mass plus the take-off fuel mass.

Question 82-5 : The maximum zero fuel mass is ?

A structural limit listed in the flight manual as a fixed value.

exemple 198 A structural limit listed in the flight manual as a fixed value.

Question 82-6 : The maximum structural take off mass is ?

A limit which may not be exceeded for any take off.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 202 A limit which may not be exceeded for any take-off.

Question 82-7 : To calculate the allowable take off mass, the factors to be taken into account include ?

Maximum landing mass augmented by the fuel burn

Maximum landing mass and the trip fuel.correct, because you can take off at the mlm plus trip fuel because you would land at mlm, in the mlm would be the reserve, contingency and diversion fuel...maximum take off mass minus the trip fuel.this is nonsense the mtom minus trip fuel will not give the allowable tom..maximum landing mass and the fuel on board at take off.it can't be the mlm plus take off fuel because this would mean you would land above the mlm as you would only plan to burn the trip fuel. thus you would be landing at mlm plus reserve, contingency and diversion fuel...maximum zero fuel mass and the trip fuel.this cannot be right because the allowable tom is not the mzfm plus trip fuel but the mzfm plus take off fuel, assuming it doesn't exceed the mtom. exemple 206 Maximum landing mass augmented by the fuel burn

Question 82-8 : The traffic load is defined as the total mass of... ?

Passengers, baggage and cargo, including any non revenue load.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 210 Passengers, baggage and cargo, including any non revenue load.

Question 82-9 : Given..dry operating mass = 38 000 kg.maximum structural take off mass = 72 000 kg.maximum landing mass = 65 000 kg.maximum zero fuel mass = 61 000 kg.trip fuel = 8 000 kg.take off fuel = 10 300 kg..the maximum allowed take off mass and payload are respectively ?

71 300 kg and 23 000 kg.

Zfm is the mass of the aeroplane minus all useable fuel..payload is 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 the maximum structural take off mass..we will be below the maximum landing mass 71300 8000 = 63300 kg. exemple 214 71 300 kg and 23 000 kg.

Question 82-10 : In relation to an aeroplane, the term 'basic empty mass' includes the mass of the aeroplane structure complete with its powerplants, systems, furnishings and other items of equipment considered to be an integral part of the particular aeroplane configuration..its value is ?

Found in the latest version of the weighing schedule as corrected to allow for modifications.

The 'basic empty mass' is recorded in the weighing schedule , not in the flight manual. exemple 218 Found in the latest version of the weighing schedule as corrected to allow for modifications.

Question 82-11 : Prior to departure the medium range twin jet aeroplane is loaded with maximum fuel of 20100 litres at a fuel density specific gravity of 0.78..using the following data..performance limited take off mass 67200 kg.performance limited landing mass 54200 kg.dry operating mass 34930 kg..taxi fuel 250 ?

13090 kg.

Question states 'prior to departure the jet is loaded with maximum fuel'...20100 litres = 15680 kg..traffic load possible at take off.67200 kg 34930 kg + 15680 kg = 16590 kg..at landing, taxi and 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. exemple 222 13090 kg.

Question 82-12 : The operator of an aircraft equipped with 50 seats uses standard masses for passengers and baggage..during the preparation of a scheduled flight a group of passengers present themselves at the check in desk, it is apparent that even the lightest of these exceeds the value of the declared standard ?

The operator should use the individual masses of the passengers or alter the standard masss.

Easa air ops.mass values for passengers and baggage..... g on any flight identified as carrying a significant number of passengers whose masses, including hand baggage, are expected to exceed the standard passenger mass, an operator must determine the actual mass of such passengers by weighing or by adding an adequate mass increment. exemple 226 The operator should use the individual masses of the passengers or alter the standard masss.

Question 82-13 : The following data is extracted from an aeroplane's loading manifest..performance limited take off mass 93500 kg.expected landing mass at destination 81700 kg.maximum certificated landing mass 86300 kg.fuel on board 16500 kg..during the flight a diversion is made to an en route alternate which is ?

Is 87300 kg and excess structural stress could result.

Fuel on board fuel remaining at landing = 16500 kg 10300 kg = 6200 kg...we only have one mass givent for take off, the performance limited take off mass, thus, the landing mass will be.93500 kg 6200 kg = 87300 kg and structural stress could result maximum certificated landing mass is 86300 kg. exemple 230 Is 87300 kg and excess structural stress could result.

Question 82-14 : The following data relates to a planned flight of an aeroplane.dry operational mass 60 520 kg.performance limited take off mass 92 750 kg.structural limited take off mass 88 750 kg.performance limited landing mass 72 250 kg.structural limited landing mass 73 500 kg.maximum zero fuel mass 67 530 ?

7010 kg.

Img168 exemple 234 7010 kg.

Question 82-15 : Maximum allowed take off mass limit 37 200kg.dry operating mass 21 600 kg.take off fuel 8 500 kg.passengers on board male 33, female 32, children 5.baggage 880 kg..the company uses the standard passenger mass systems allowed by regulations. the flight is not a holiday charter. in these conditions, ?

585 kg.

Adults = 33 males + 32 females x 84 kg = 5460 kg.children = 5 x 35 kg = 175 kg.passenger load is 5460 kg + 175 kg = 5635 kg...mtom dom + fuel + passenger + baggage.37200 kg 21600 + 8500 + 5635 + 880 = 585 kg. exemple 238 585 kg.

Question 82-16 : The take off mass of an aircraft is 8470 kg..total fuel on board is 1600 kg including 450 kg reserve fuel and 29 kg of unusable fuel..the traffic load is 770 kg...what is the zero fuel mass ?

6899 kg.

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 the zero fuel mass = 6870 + 29 = 6899 kg.

Question 82-17 : Traffic load is the difference between ?

The take off mass and the operating mass.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 246 The take-off mass and the operating mass.

Question 82-18 : The basic empty mass of an aircraft is 30000 kg..given the following data calculate the dom dry operating mass. catering 300 kg. crew 600 kg. trip fuel 1200 kg. unusable fuel 30 kg. traffic load 2500 kg ?

30900 kg.

Dry operating mass = basic empty mass + variable load..dry operating mass = 30000 kg + 300 kg + 600 kg = 30900 kg.. unusable fuel is already included in the basic empty mass. exemple 250 30900 kg.

Question 82-19 : Which is true of the aircraft basic empty mass ?

It is a component of dry operating mass.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 254 It is a component of dry operating mass.

Question 82-20 : The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 3800 us gallons..if the fuel density specific gravity is given as 0.79 the mass of fuel which may be loaded is ?

11364 kg.

1 us gallon = 3.78 litres 3,785411784 litres...3800 x 3.785411784 x 0.79 = 11363.8 kg. exemple 258 11364 kg.

Question 82-21 : Determine the landing mass for 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 ?

2599 lbs.

Take off mass = 1764 + 35 + 300 + 350 + 6 x 60 = 2809 lbs..expected landing mass = 2809 6 x 35 = 2599 lbs. exemple 262 2599 lbs.

Question 82-22 : Given..maximum allowable take off mass 64400 kg.maximum landing mass 56200 kg.maximum zero fuel mass 53000 kg.dry operating mass 35500 kg.traffic load 14500 kg.trip fuel 4900 kg.take off fuel 7400 kg..find maximum additional load ?

3000 kg.

Take off mass will be 35500 + 14500 + 7400 = 57400 kg...landing mass will be 57400 4900 = 52500 kg..maximum landing mass is 56200 kg, so we can add 56200 52500 kg = 3700 kg...last check, the maximum zero fuel mass of 53000 kg.35500 + 14500 + 3700 = 53700 kg... we are exceeding this limit, we need to reduce the additional load by 700 kg...3700 700 = 3000 kg. exemple 266 3000 kg.

Question 82-23 : The traffic load is a part of the ?

Zero fuel mass.

Please download the following document used as a reference at the exam../pdf/031 mass definitions.pdf exemple 270 Zero fuel mass.

Question 82-24 : The si units of running or linear load are ?

N/m, kg/m.

exemple 274 N/m, kg/m.

Question 82-25 : 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 is ?

17350 kg.

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 is more than what the fuel tanks can contains...therefore, we can fill them full, and we will have to remove 200 kg for taxi, to know our maximum possible fuel at take off.2500 x 0,78 = 17550 kg..17550 200 = 17350 kg. exemple 278 17350 kg.

Question 82-26 : 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 of 420 kg, the permissible traffic load will be ?

1130 kg.

8220 1750 4920 420 = 1130 kg. exemple 282 1130 kg.

Question 82-27 : 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 ?

5919 kg.

The total fuel includes 19 kg of unuseable fuel...this unuseable fuel is part of the basic empty mass and therefore part of the dom..tom useable fuel = zfm..6700 800 19 = 5919 kg. exemple 286 5919 kg.

Question 82-28 : The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 1120 l..if the fuel density specific gravity is given as 0.79, the mass of fuel which may be loaded is ?

885 kg.

1120 x 0.79 = 885 kg. exemple 290 885 kg.

Question 82-29 : Given. dry operating mass 2800 kg. trip fuel 300 kg. traffic load 400 kg. maximum take off mass 4200 kg. maximum landing mass 3700 kg..the maximum fuel load is ?

800 kg.

Zero fuel mass= 2800 + 400 = 3200 kg...useful limitation = the lowest value from the following two values.. maximum take off mass 4200 kg... maximum landing mass + trip fuel = 3700 + 300 = 4000 kg this is our 'useful limitation'... maximum fuel load = 4000 3200 = 800 kg. exemple 294 800 kg.

Question 82-30 : The dry operating mass of an aircraft is the sum of the basic empty mass + crew + ?

Operating items.

exemple 298 Operating items.

Question 82-31 : The zero fuel mass is the mass of the aircraft ?

Excluding usable fuel.

exemple 302 Excluding usable fuel.

Question 82-32 : The baggage compartment of a particular aircraft is 1,2 m wide by 1,4 m long and has a maximum floor loading of 500 kg per square metre..what is the maximum capacity of the baggage compartment limited by maximum floor load only ?

840 kg.

1.2 x 1.4 x 500 = 840 kg. exemple 306 840 kg.

Question 82-33 : What is the reason for knowing accurately what your weight is during flight ?

So you can fly at the optimum cruise altitude.

exemple 310 So you can fly at the optimum cruise altitude.

Question 82-34 : Basic empty mass basic mass is the mass of an aircraft plus standard items such as ?

Pyrotechnics.

Basic empty mass basic 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 314 Pyrotechnics.

Question 82-35 : The following data applies to an aircraft which is about to take off..maximum structural take off mass 8400 kg.performance limited take off mass 7920 kg.dry operating mass 5230 kg.crew and operating items 460 kg.take off fuel 980 kg..from this data calculate the mass of the useful load ?

2690 kg.

Useful load = take off mass dry operating mass..useful load = 7920 kg 5230 kg..useful load = 2690 kg exemple 318 2690 kg.

Question 82-36 : 1 ton equals approximately ?

2200 lb.

exemple 322 2200 lb.

Question 82-37 : Given.basic empty mass 5300 kg.dry operating mass 5500 kg.zero fuel mass 5980 kg.take off mass 7980 kg..the useful load is ?

2480 kg.

Useful load = take off mass dry operating mass..useful load = 7980 kg 5500 kg..useful load = 2480 kg exemple 326 2480 kg.

Question 82-38 : Based on actual conditions, an aeroplane has the following performance take off mass limitations..flaps 0° 10° 15°.runway 4100 4400 4600.climb 4700 4500 4200..masses are in kg.. structural limits take off/landing/zero fuel 4 300 kg..the maximum take off mass is ?

4300 kg.

You must compare the 4300kg structural limit with the runway limit and climb limit at each flap setting and select the lowest..at flap 0°, the lowest limit will be 4100 kg..at flap 10, the lowest limit will be 4300 kg..at flap 15, the lowest limit is 4200 kg...now pick the highest of the three and we can safely get airborne at 4300 kg at flap 10°. exemple 330 4300 kg.

Question 82-39 : Mass for individual passengers to be carried on an aeroplane may be determined from a verbal statement by or on behalf of the passengers if the number of ?

Passenger seats available is less than 10.

Where the number of passenger seats available is less than 10 passenger mass may be determined by verbal statement. exemple 334 Passenger seats available is less than 10.

Question 82-40 : The regulated take off mass is ?

The lower of performance limited take off mass and maximum structural take off mass.

Regulated take off mass = lower of.. the take off mass subject to departure airfield limitations performance limited take off mass..and.. the maximum permissible total mass of the aircraft at commencement of take off maximum structural take off mass. exemple 338 The lower of performance limited take-off mass and maximum structural take-off mass.


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