Result > topography : The zero fuel mass is the mass of the aircraft ?

Question 68-1 : 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 168 excluding usable fuel. — excluding usable fuel.

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

Question 68-2 : 840 kg 298 kg 1300 kg 192 kg

exemple 172 840 kg. — 1 2 x 1 4 x 500 = 840 kg 840 kg.

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

Question 68-3 : 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 176 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 68-4 : 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 68-5 : 2690 kg 1710 kg 3630 kg 3150 kg

exemple 184 2690 kg. — Useful load = take off mass dry operating mass..useful load = 7920 kg 5230 kg..useful load = 2690 kg 2690 kg.

1 ton equals approximately ?

Question 68-6 : 2200 lb 2000 lb 1200 lb 220 lb

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

Question 68-7 : 2480 kg 2680 kg 2000 kg 480 kg

exemple 192 2480 kg. — Useful load = take off mass dry operating mass..useful load = 7980 kg 5500 kg..useful load = 2480 kg 2480 kg.

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

Question 68-8 : 4300 kg 4700 kg 4100 kg 4200 kg

exemple 196 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° 4300 kg.

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

Question 68-9 : 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

exemple 200 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 passenger seats available is less than 10.

The regulated take off mass is ?

Question 68-10 : 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

exemple 204 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 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 68-11 : 766 kg 383 kg 1532 kg 2393 kg

exemple 208 766 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 766 kg.

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

Question 68-12 : 2367 l 1868 l 8240 l 2121 l

exemple 212 2367 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 2367 l.

The basic advantage of standard size containers ?

Question 68-13 : 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 216 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 68-14 : 1870 kg 2367 kg 2996 kg 8240 kg

exemple 220 1870 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 1870 kg.

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

Question 68-15 : 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

exemple 224 1.2 m x 1.2 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 1.2 m x 1.2 m.

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

Question 68-16 : 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 228 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 ?

Question 68-17 : 2809 lbs 2764 lbs 2799 lbs 2659 lbs

exemple 232 2809 lbs. — Take off mass = 1764 + 35 + 300 + 350 + 6 x 60.take off mass = 2809 lbs 2809 lbs.

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

Question 68-18 : 15450 lbs 3178 lbs 15680 lbs 8640 lbs

exemple 236 15450 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 15450 lbs.

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

Question 68-19 : 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 240 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 68-20 : 1 31 m² 6 4 m² 0 76 m² 14 11 m²

exemple 244 1.31 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 1.31 m².

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

Question 68-21 : 16% 41% 60% 10%

exemple 248 16%. — 100 x distance between leading edge and cg / mac length..100 x 713 524 / 1706 524.100 x 189 / 1182 = 15 99% 16%.

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

Question 68-22 : Longitudinal axis lateral axis vertical axis horizontal axis

exemple 252 longitudinal axis. — longitudinal axis.

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

Question 68-23 : 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

exemple 256 it is the point on the aircraft designated by the manufacturer from which all centre of gravity measurements and calculations are made. — 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 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 68-24 : 343000 nm 1 43 nm 7000 nm 34000 n/m

exemple 260 343000 nm. — Arm = moment / force..7 = x / 49000..7 x 49 000 = 343000 nm.nm = newton multiplied by meter 343000 nm.

Which one of the following is correct ?

Question 68-25 : Arm = moment / force arm = force x moment arm = force / moment moment = force / arm

exemple 264 arm = moment / force — arm = moment / force

Which of the following statements is correct ?

Question 68-26 : 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 268 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 68-27 : 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

exemple 272 is a figure without unit of measurement which represents a moment. — 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 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 68-28 : 1 is incorrect 2 is incorrect 1 is correct 2 is correct 1 is correct 2 is incorrect 1 is incorrect 2 is correct

exemple 276 1 is incorrect, 2 is incorrect. — 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 1 is incorrect, 2 is incorrect.

At what mass is an aircraft weighed ?

Question 68-29 : The basic empty mass the basic mass the empty mass the dry operating mass

exemple 280 the basic empty mass. — Basic empty 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 basic empty mass.

An aircraft is weighed and the following recordings are made .nose wheel ?

Question 68-30 : 30180 kg 28400 kg 31960 kg 32505 kg

exemple 284 30180 kg. — The 'fixed items' are parts of the aircraft when it is weighed you don't have to add them again to find the empty mass.5330 + 12370 + 12480 = 30180 kg 30180 kg.

If individual masses are used the mass of an aircraft must be determined prior ?

Question 68-31 : At intervals of 4 years if no modifications have taken place at regular annual intervals only if major modifications have taken place at intervals of 9 years

exemple 288 at intervals of 4 years if no modifications have taken place. — Easa air ops.regulation eu no 965/2012.cat pol mab 100 mass and balance loading.. a during any phase of operation the loading mass and centre of gravity cg of the aircraft shall comply with the limitations specified in the afm or the operations manual if more restrictive. b the operator shall establish the mass and the cg of any aircraft by actual weighing prior to initial entry into service and 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 and repairs on the mass and balance shall be accounted for and properly documented aircraft shall be reweighed if the effect of modifications on the mass and balance is not accurately known. c the weighing shall be accomplished by the manufacturer of the aircraft or by an approved maintenance organisation. d the operator shall determine the mass of all operating items and crew members included in the aircraft dry operating mass by weighing or by using standard masses the influence of their position on the aircraft's cg shall be determined. e the operator shall establish the mass of the traffic load including any ballast by actual weighing or by determining the mass of the traffic load in accordance with standard passenger and baggage masses. f in addition to standard masses for passengers and checked baggage the operator can use standard masses for other load items if it demonstrates to the competent authority that these items have the same mass or that their masses are within specified tolerances. g the operator shall determine the mass of the fuel load by using the actual density or if not known the density calculated in accordance with a method specified in the operations manual. h the operator shall ensure that the loading of. 1 its aircraft is performed under the supervision of qualified personnel and.. 2 traffic load is consistent with the data used for the calculation of the aircraft mass and balance. i the operator shall comply with additional structural limits such as the floor strength limitations the maximum load per running metre the maximum mass per cargo compartment and the maximum seating limit for helicopters in addition the operator shall take account of in flight changes in loading. j the operator shall specify in the operations manual the principles and methods involved in the loading and in the mass and balance system that meet the requirements contained in a to i this system shall cover all types of intended operations at intervals of 4 years if no modifications have taken place.

At the maximum landing mass the range of safe cg positions as determined from ?

Question 68-32 : Forward limit 7 4% mac aft limit 27 0% mac forward limit 8 0% mac aft limit 27 2% mac forward limit 8 6% mac aft limit 27 0% mac forward limit 8 0% mac aft limit 26 8% mac

exemple 292 forward limit 7.4% mac aft limit 27.0% mac. — 146 forward limit 7.4% mac aft limit 27.0% mac.

At a given mass the cg position is at 15% mac if the leading edge of mac is at ?

Question 68-33 : 645 78 inches aft of datum 605 43 inches aft of datum 20 18 inches aft of datum 228 34 inches aft of datum

exemple 296 645.78 inches aft of datum. — The mac lenght is 134 5 inches and the cg is at 15% of this distance back from the leading edge .15% of 134 5 inches is 20 175 inches.if the leading edge of the mac is at 625 6 inches aft of the datum the cg will be at 625 6 + 20 175 = 645 775 inches aft of the datum 645.78 inches aft of datum.

The aeroplane has a take off mass of 58 000 kg at this mass the range of safe ?

Question 68-34 : Forward limit 8 0% mac aft limit 26 5% mac forward limit 8 5% mac aft limit 26 1% mac forward limit 8 2% mac aft limit 26 2% mac forward limit 9 5% mac aft limit 26 1% mac

exemple 300 forward limit 8.0% mac aft limit 26.5% mac. — 147 forward limit 8.0% mac aft limit 26.5% mac.

When preparing to carry out the weighing procedure on an aircraft which of the ?

Question 68-35 : Drain all engine tank oil drain all useable fuel drain all chemical toilet fluid tanks removable passenger services equipment to be off loaded

exemple 304 drain all engine tank oil. — Basic empty 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.engine oil is included in the basic empty mass drain all engine tank oil.

An aircraft is weighed prior to entry into service .who is responsible for ?

Question 68-36 : The operator the appropriate aviation authority the aircraft manufacturer or supplier the commander of the aircraft

exemple 308 the operator. — The operator is responsible for deriving the dry operational mass from the weighed mass by the addition of the 'operational items' prior the aircraft enter into service the operator.

An aircraft may be weighed ?

Question 68-37 : In an enclosed non air conditioned hangar in a quiet parking area clear of the normal manoeuvring area in an area of the airfield set aside for maintenance at a specified 'weighing location' on the airfield

exemple 312 in an enclosed, non-air conditioned, hangar. — Weighing procedures normal precautions consistent with good practices in the weighing procedures such as checking for completeness of the aircraft and equipment determining that fluids are properly accounted for and the weighing is accomplished in an enclosed building preventing the effect of the wind should be provided in an enclosed, non-air conditioned, hangar.

A aeroplane has a landing mass of 53000kg the range of safe cg positions as ?

Question 68-38 : Forward limit 7 8% mac aft limit 27 0% mac forward limit 8 2% mac aft limit 27 0% mac forward limit 7 3% mac aft limit 26 8% mac forward limit 8 7% mac aft limit 26 8% mac

exemple 316 forward limit 7.8% mac aft limit 27.0% mac. — 172 forward limit 7.8% mac aft limit 27.0% mac.

The aeroplane has a mass of 61 000 kg in the cruise the range of safe cg ?

Question 68-39 : Forward limit 8 3% aft limit 26 3% mac forward limit 7 7% aft limit 25 2% mac forward limit 7 6% aft limit 26 9% mac forward limit 8 0% aft limit 27 2% mac

exemple 320 forward limit 8.3% aft limit 26.3% mac. — 148 forward limit 8.3% aft limit 26.3% mac.

An aeroplane must be re weighed at certain intervals where an operator uses ?

Question 68-40 : 9 years for each aeroplane 4 years for each aeroplane whenever the certificate of airworthiness is renewed whenever a major modification is carried out

exemple 324 9 years for each aeroplane. — Easa air ops.regulation eu no 965/2012.cat pol mab 100 mass and balance loading.. a during any phase of operation the loading mass and centre of gravity cg of the aircraft shall comply with the limitations specified in the afm or the operations manual if more restrictive. b the operator shall establish the mass and the cg of any aircraft by actual weighing prior to initial entry into service and 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 and repairs on the mass and balance shall be accounted for and properly documented aircraft shall be reweighed if the effect of modifications on the mass and balance is not accurately known. c the weighing shall be accomplished by the manufacturer of the aircraft or by an approved maintenance organisation 9 years for each aeroplane.

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