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Which is true of the aircraft basic empty mass ? [ Attainment AIM ]

Question 82-1 : It is a component of dry operating mass it is the actual take off mass less traffic load it is dry operating mass minus fuel load it is dry operating mass minus traffic load

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

The maximum quantity of fuel that can be loaded into an aircraft's tanks is ?

Question 82-2 : 11364 kg 18206 kg 14383 kg 13647 kg

1 us gallon = 3 78 litres 3 785411784 litres .3800 x 3 785411784 x 0 79 = 11363 8 kg exemple 186 11364 kg.11364 kg.

Determine the landing mass for the following single engine aeroplane .given . ?

Question 82-3 : 2599 lbs 2799 lbs 2659 lbs 2449 lbs

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

Given .maximum allowable take off mass 64400 kg.maximum landing mass 56200 ?

Question 82-4 : 3000 kg 7000 kg 4000 kg 5600 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 194 3000 kg.3000 kg.

The traffic load is a part of the ?

Question 82-5 : Zero fuel mass basic empty mass operating mass dry operating mass

Please download the following document used as a reference at the exam ./pdf/031 mass definitions pdf exemple 198 Zero fuel mass.Zero fuel mass.

The si units of running or linear load are ?

Question 82-6 : N/m kg/m kg/m³ n kg/m² kg n/m² lb/ft

exemple 202 N/m, kg/m.N/m, kg/m.

Given .fuel density of 0 78 kg/l dry operating mass = 33500 kg traffic load = ?

Question 82-7 : 17350 kg 21900 kg 17550 kg 22100 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 206 17350 kg.17350 kg.

An aircraft is to depart at an take off mass of 8220 kg .take off fuel ?

Question 82-8 : 1130 kg 1550 kg 1040 kg 2590 kg

8220 1750 4920 420 = 1130 kg exemple 210 1130 kg.1130 kg.

The take off mass of an aircraft is 6700 kg .total fuel on board is 800 kg ?

Question 82-9 : 5919 kg 5900 kg 5681 kg 5000 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 214 5919 kg.5919 kg.

The maximum quantity of fuel that can be loaded into an aircraft's tanks is ?

Question 82-10 : 885 kg 1418 kg 858 kg 1011 kg

1120 x 0 79 = 885 kg exemple 218 885 kg.885 kg.

Given . dry operating mass 2800 kg. trip fuel 300 kg. traffic load 400 kg. ?

Question 82-11 : 800 kg 1000 kg 500 kg 700 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 222 800 kg.800 kg.

The dry operating mass of an aircraft is the sum of the basic empty mass + crew ?

Question 82-12 : Operating items traffic load taxi fuel traffic load + usable fuel

exemple 226 Operating items.Operating items.

The zero fuel mass is the mass of the aircraft ?

Question 82-13 : Excluding usable fuel excluding usable and unusable fuel including unusable and reserve fuel when weighed for issue or renewal of its weight schedule and excludes crew traffic load usable and unusable fuel

exemple 230 Excluding usable fuel.Excluding usable fuel.

The baggage compartment of a particular aircraft is 1 2 m wide by 1 4 m long ?

Question 82-14 : 840 kg 298 kg 1300 kg 192 kg

1 2 x 1 4 x 500 = 840 kg exemple 234 840 kg.840 kg.

What is the reason for knowing accurately what your weight is during flight ?

Question 82-15 : So you can fly at the optimum cruise altitude so the operator can choose the appropriate routes to fly it is unimportant you only need to know your weight for take off and landing

exemple 238 So you can fly at the optimum cruise altitude.So you can fly at the optimum cruise altitude.

Basic empty mass basic mass is the mass of an aircraft plus standard items such ?

Question 82-16 : Pyrotechnics fuel passengers crew

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

The following data applies to an aircraft which is about to take off .maximum ?

Question 82-17 : 2690 kg 1710 kg 3630 kg 3150 kg

Useful load = take off mass dry operating mass.useful load = 7920 kg 5230 kg.useful load = 2690 kg exemple 246 2690 kg.2690 kg.

1 ton equals approximately ?

Question 82-18 : 2200 lb 2000 lb 1200 lb 220 lb

exemple 250 2200 lb.2200 lb.

Given .basic empty mass 5300 kg.dry operating mass 5500 kg.zero fuel mass 5980 ?

Question 82-19 : 2480 kg 2680 kg 2000 kg 480 kg

Useful load = take off mass dry operating mass.useful load = 7980 kg 5500 kg.useful load = 2480 kg exemple 254 2480 kg.2480 kg.

Based on actual conditions an aeroplane has the following performance take off ?

Question 82-20 : 4300 kg 4700 kg 4100 kg 4200 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 258 4300 kg.4300 kg.

Mass for individual passengers to be carried on an aeroplane may be determined ?

Question 82-21 : Passenger seats available is less than 10 passengers carried is less than 10 passenger seats available is less than 20 passengers carried is less than 20

Where the number of passenger seats available is less than 10 passenger mass may be determined by verbal statement exemple 262 Passenger seats available is less than 10.Passenger seats available is less than 10.

The regulated take off mass is ?

Question 82-22 : The lower of performance limited take off mass and maximum structural take off mass the take off mass subject to departure airfield limitations the higher of performance limited take off mass and maximum structural landing mass the maximum permissible total mass of the aircraft at commencement of take off

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

Given .container size length x width x height 0 8 x 0 8 x 0 8 m.container has ?

Question 82-23 : 766 kg 383 kg 1532 kg 2393 kg

If the maximum running load is 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 is 0 4 m = the total load is pressing down on a running load length of 0 4 m .1915 kg x 0 4m = 766 kg exemple 270 766 kg.766 kg.

From the pilot's flight manual determine the maximum total volume of fuel which ?

Question 82-24 : 2367 l 1868 l 8240 l 2121 l

Read the question carefully if it is asking for 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 exemple 274 2367 l.2367 l.

The basic advantage of standard size containers ?

Question 82-25 : Standard size containers are designed to fit and lock into the cargo compartment for maximum space efficiency maximum mass of cargo loaded in the containers is always limited by the mtom with the cargo loaded in containers one does not have to observe the maximum floor loading limit maximum mass of cargo loaded in the containers is often limited by the g forces in flight

exemple 278 Standard size containers are designed to fit and lock into the cargo compartment for maximum space efficiency.Standard size containers are designed to fit and lock into the cargo compartment for maximum space efficiency.

From the pilot's flight manual determine the maximum total mass of fuel which ?

Question 82-26 : 1870 kg 2367 kg 2996 kg 8240 kg

Read the question carefully if it is asking for 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 exemple 282 1870 kg.1870 kg.

The maximum floor loading of the cargo compartment is specified to be 732 ?

Question 82-27 : 1 2 m x 1 2 m 1 25 m x 1 25 m 1 3 m x 1 3 m 1 05 m x 1 05 m

Floor loading limit 732 kg/m² ==> you can put maximum 732 kg to 1 m² that's the limit .you have 826 kg to load so yo need more than 1 m² space and 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 is ==> 1 2 m x 1 2 m ==> 1 44 m² exemple 286 1.2 m x 1.2 m.1.2 m x 1.2 m.

The term 'landing mass' at destination is defined as ?

Question 82-28 : Final reserve fuel alternate fuel contingency fuel plus zero fuel mass final reserve fuel trip fuel plus zero fuel mass final reserve fuel alternate fuel contingency fuel plus landing mass at alternate final reserve fuel trip fuel contingency fuel plus zero fuel mass

exemple 290 Final reserve fuel, alternate fuel, contingency fuel plus zero fuel mass.Final reserve fuel, alternate fuel, contingency fuel plus zero fuel mass.

Determine the take off mass tom for the following single engine aeroplane ?

Question 82-29 : 2809 lbs 2764 lbs 2799 lbs 2659 lbs

Take off mass = 1764 + 35 + 300 + 350 + 6 x 60 .take off mass = 2809 lbs exemple 294 2809 lbs.2809 lbs.

Refer to figure 031 15 .calculate the maximum fuel mass for the centre tank in ?

Question 82-30 : 15450 lbs 3178 lbs 15680 lbs 8640 lbs

The maximum mass of fuel in the centre tank is 7008 kg convert this value into pounds to get 15450 lbs 1kg = 2 2 lbs exemple 298 15450 lbs.15450 lbs.

What is the reason for cargo loads to be tied down ?

Question 82-31 : Preventing such loads from moving and to remain within the cg limits of the aircraft maximising the space and increasing the maximum payload of the aircraft maximising the performance of the aircraft during take off and landing procedures maintaining enough space in the compartment hold in case of evacuation

exemple 302 Preventing such loads from moving and to remain within the cg limits of the aircraft.Preventing such loads from moving and to remain within the cg limits of the aircraft.

The structural limitation of a baggage compartment is 50 lb/ft a load has a ?

Question 82-32 : 1 31 m² 6 4 m² 0 76 m² 14 11 m²

1 m = 3 28 ft therefore 1 m² = 10 76 ft².convert the limitation of 50 lb/ft² to kg and 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 by the question is 320 kg to find the distribution we need to use the rule of proportion to find the aera for a mass of 320 kg .1m² / 244 kg x 320 kg = 1 31 m² exemple 306 1.31 m².1.31 m².

The loaded centre of gravity cg of an aeroplane is 713 mm aft of datum .the ?

Question 82-33 : 16% 41% 60% 10%

100 x distance between leading edge and cg / mac length.100 x 713 524 / 1706 524 .100 x 189 / 1182 = 15 99% exemple 310 16%.16%.

The centre of gravity location of the aeroplane is normally computed along the ?

Question 82-34 : Longitudinal axis lateral axis vertical axis horizontal axis

exemple 314 Longitudinal axis.Longitudinal axis.

In mass and balance calculations which of the following describes the datum ?

Question 82-35 : It is the point on the aircraft designated by the manufacturer from which all centre of gravity measurements and calculations are made it is the most forward position of the centre of gravity it is the most aft position of the centre of gravity it is the distance from the centre of gravity to the point through which the weight of the component acts

To be correct this is not necessarily a point 'on' the aircraft .the 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 . 159.in most cases the datum is located in the vicinity of the aircraft nose usually the firewall . 1065 exemple 318 It is the point on the aircraft designated by the manufacturer from which all centre of gravity measurements and calculations are made.It is the point on the aircraft designated by the manufacturer from which all centre of gravity measurements and calculations are made.

An aircraft has its centre of gravity located 7 metres from the datum line and ?

Question 82-36 : 343000 nm 1 43 nm 7000 nm 34000 n/m

Arm = moment / force.7 = x / 49000.7 x 49 000 = 343000 nm .nm = newton multiplied by meter exemple 322 343000 nm.343000 nm.

Which one of the following is correct ?

Question 82-37 : Arm = moment / force arm = force x moment arm = force / moment moment = force / arm

exemple 326 Arm = moment / forceArm = moment / force

Which of the following statements is correct ?

Question 82-38 : A rear centered aircraft is less stable and stalls at a slower speed than a forward centered aircraft if the actual centre of gravity is located behind the aft limit of centre of gravity it is possible that the aeroplane will be unstable making it necessary to increase elevator forces if the actual centre of gravity is close to the forward limit of the centre of gravity the aeroplane may be unstable making it necessary to increase elevator forces the lowest stalling speed is obtained if the actual centre of gravity is located in the middle between the aft and forward limit of centre of gravity

exemple 330 A rear-centered aircraft is less stable and stalls at a slower speed than a forward-centered aircraft.A rear-centered aircraft is less stable and stalls at a slower speed than a forward-centered aircraft.

In mass and balance calculations the 'index' is ?

Question 82-39 : Is a figure without unit of measurement which represents a moment a location in the aircraft identified by a number an imaginary vertical plane or line from which all measurements are taken the range of moments the centre of gravity cg can have without making the aircraft unsafe to fly

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 position .and 'an imaginary vertical plane or line from which all measurements are taken' is the datum exemple 334 Is a figure without unit of measurement which represents a moment.Is a figure without unit of measurement which represents a moment.

Which of the following are the exact propositions .1 an aircraft belonging to ?

Question 82-40 : 1 is incorrect 2 is incorrect 1 is correct 2 is correct 1 is correct 2 is incorrect 1 is incorrect 2 is correct

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 exemple 338 1 is incorrect, 2 is incorrect.1 is incorrect, 2 is incorrect.

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