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Question 86-1 : If individual masses are used, the mass of an aircraft must be determined prior to initial entry into service and thereafter ? [ Result topography ]
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.
Question 86-2 : At the maximum landing mass the range of safe cg positions, as determined from the appropriate graph in the loading manual, is. 206 ?
Forward limit 7.4% mac aft limit 27.0% mac.
Img146
Question 86-3 : At a given mass the cg position is at 15% mac. if the leading edge of mac is at a position 625.6 inches aft of the datum and the mac is given as 134.5 inches determine the position of the cg in relation to the datum. ?
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.
Question 86-4 : The aeroplane has a take off mass of 58 000 kg. at this mass the range of safe cg positions, as determined from the appropriate graph in the loading manual, is.. 207 ?
Forward limit 8.0% mac aft limit 26.5% mac.
Img147
Question 86-5 : When preparing to carry out the weighing procedure on an aircraft, which of the following is not required ?
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.
Question 86-6 : An aircraft is weighed prior to entry into service..who is responsible for deriving the dry operational mass from the weighed mass by the addition of the 'operational items' ?
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.
Question 86-7 : An aircraft may be weighed ?
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.
Question 86-8 : A aeroplane has a landing mass of 53000kg. the range of safe cg positions, as determined from the appropriate graph in the loading manual, is.. 208 ?
Forward limit 7.8% mac aft limit 27.0% mac.
Img172
Question 86-9 : The aeroplane has a mass of 61 000 kg in the cruise. the range of safe cg positions, as determined from the appropriate graph in the loading manual, is.. 209 ?
Forward limit 8.3% aft limit 26.3% mac.
Img148
Question 86-10 : An aeroplane must be re weighed at certain intervals. where an operator uses 'fleet masses' and provided that changes have been correctly documented, this interval is ?
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.
Question 86-11 : A flight benefits from a strong tail wind which was not forecast. on arrival at destination a straight in approach and immediate landing clearance is given..the landing mass will be higher than planned and ?
The landing distance required will be longer.
The strong tail wind helps carry the aircraft so less fuel is used. with no delays on arrival and with a straight in approach less time spent on the approach procedure , the plane will land with more fuel on board than expected..approach and landing speeds are increased, the landing distance required is longer.
Question 86-12 : The centre of gravity of an aeroplane is at 25% of the mean aerodynamic chord. this means that the centre of gravity of the aeroplane is situated at 25% of the length of ?
The mean aerodynamic chord in relation to the leading edge.
Longitudinal cg location is normally expressed as a percentage of the mean aerodynamic chord mac from its leading edge.
Question 86-13 : To measure the mass and cg position of an aircraft, it should be weighed with a minimum of ?
3 points of support.
Question 86-14 : An aeroplane has a mean aerodynamic chord mac of 134.5 inches..the leading edge of this chord is at a distance of 625.6 inches aft of the datum..define the location of the centre of gravity of the aeroplane in terms of percentage mac if the mass of the aeroplane is acting vertically through a ?
18,10%.
Leading edge mac is at 625.6 inches aft of the datum...the centre of gravity is at 650 inches aft of the datum 650 625.6 = 24.4 inches from leading edge mac... 24.4 / 134.5 x 100 = 18.10 %.
Question 86-15 : The empty mass of an aircraft is recorded in ?
The weighing schedule and is amended to take account of changes due to modifications of the aircraft.
The empty mass of an aircraft is recorded in the weighing schedule and is amended to take account of changes due to modifications of the aircraft..normally, the aircraft is weighed.. before entering in service.. every 4 years, for individual aircraft.. every 9 years for fleet masses.. every time a modification takes place equipment installed or uninstalled...as the weighing procedure is long and complex, the operator is allowed to adjust the empty mass of an aircraft on the weighing schedule between to weighing procedure.
Question 86-16 : The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 400 us gallons..if the fuel density specific gravity is given as 0.79, the mass of fuel which may be loaded is ?
1196 kg.
1 ug gallons = 3.7854 litres...400 usg x 3.7854 = 1514 litres...1514 x 0.79 = 1196 kg.
Question 86-17 : The maximum quantity of fuel that can be loaded into an aircraft's tanks is given as 2200 l..if the fuel density specific gravity is given as 0.79, the mass of fuel which may be loaded is ?
1738 kg.
2200 x 0.79 = 1738 kg.
Question 86-18 : The basic empty mass is 4960 kg, the dry operating mass is 5220 kg and the zero fuel mass is 6040 kg..if the take off mass is 7630 kg the useful load is ?
2410 kg.
Useful load = maximum take off mass dry operating mass..useful load = 7630 kg 5220 kg = 2410 kg.
Question 86-19 : The basic empty mass is 4800 kg, the dry operating mass is 5050 kg and the zero fuel mass is 6210 kg..if the take off mass is 8010 kg the useful load is ?
2960 kg.
Useful load = the mass of the aircraft including everything and everyone contained within it at the commencement of take off the total mass of an aircraft ready for a specific type of operation excluding all usable fuel and traffic load...useful load = take off mass dry operating mass..useful load = 8010 kg 5050 kg = 2960 kg.
Question 86-20 : Longitudinal cg location is normally expressed ?
As a percentage of the mac from its leading edge.
Question 86-21 : Given.basic empty mass bem 1 200 kg.balance arm of bem 3.0 m.centre of gravity at bem 25% of mac..length of mac 2.0 m...in the mass and balance section of the flight manual the following information is given.position arm..front seats 2.5 m.rear seats 3.5 m.rear hold 4.5 m.fuel tanks 3.0 m..the ?
22 % of mac.
Com en/annexe.php annexe=com031 226.jpg..basic mass cg was at 25% of the mean aerodynamic chord mac with an arm of 3 m...the length of mac is 2m so the cg is at 0.5 m from leading edge mac....take off mass cg = moment/mass = 4300 / 1460 = 2.945 m..with a cg located at 2.945 m for take off, it is at 0.445 m from the leading edge mac..0.445/2 x 100 = 22.25% mac...hwoarangitf.please, how do you found the '0.445'm from the leading edge mac thank you.....at basic mass, the cg is at 25% of the mac, for a chord length of 2m, and 3m aft of the datum. 25% of 2m is 50 cm, thus the leading edge of the mac is at 2.5m aft of datum...cg location at take off will be at 2.945 2.5m = 0.445m aft of leading edge of the mac...com en/annexe.php annexe=com031 226b.jpg
Question 86-22 : Given the following data.distance from datum to centre of gravity 12.53 m.distance from datum to leading edge 9.63 m.length of mac 8.00 m.calculate the centre of gravity in % mac mean aerodynamic chord ?
36.3% mac.
Position of the cg on the mac = distance from datum to centre of gravity distance from datum to leading edge..position of the cg on the mac = 12.53 9.63 = 2.9 m...8 m is the lenght of the mac and center of gravity is located on the mac at 2.9 m...8 m is 100% of the length, 2.9m is at..2.9 x 100 / 8 = 36.25 %.
Question 86-23 : At reference to determine the dry operating index doi for a dom of 35000kg and a %mac of 14%.. 229 ?
Doi 40.
Img169
Question 86-24 : Which of the following combinations of compartment centroid and maximum load is correct.. 230 ?
835.5 in and 3062 kg.
Img171.take care, we are talking in inches and in kilograms.
Question 86-25 : Given the following data, calculate the cg as a %mac mean aerodynamic cord when 12000 n of last minute cargo is added to a hold 10 m from the datum..aum all up mass 460000 n.lemac leading edge mac 14 m from datum.mac 4.6 m.current cg 15.4 m from datum ?
27.5%.
Admin .mass x arm = moment.460000 n x 15.4 m = 7084000 nm..12000 n of last minute cargo is added to a hold 10 m from the datum.12000 n x 10 m = 120000 nm..new mass is 472000 n.new moment is 7204000 nm..cg position is now 7204000 / 472000 = 15.26 m..in percentage of mean aerodynamic chord it is.lemac is at 14 m therefore cg is 1.26m from lemac.1.26 / 4.6 x 100 = 27.5% mac.
Question 86-26 : What are the standard masses used for crew ?
85 kg for flight crew, 75 kg cabin crew, including hand baggage.
Eu ops 1.615 mass values for crew. a an operator shall use the following mass values to determine the dry operating mass.1. actual masses including any crew baggage or.2. standard masses, including hand baggage, of 85 kg for flight crew members and 75 kg for cabin crew members or.3. other standard masses acceptable to the authority...b an operator must correct the dry operating mass to account for any additional baggage. the position of this additional baggage must be accounted for when establishing the centre of gravity of the aeroplane.
Question 86-27 : For the medium range twin jet the datum point is located.. 235 ?
540 inches forward of the front spar.
In bottom of the appendix, you can read.' 2.1 datum point 540inches forward of front spar fs '.
Question 86-28 : The chemical fluids used to charge the aircraft toilets are counted as ?
Part of the variable load.
Question 86-29 : For this question use annex ecqb 031 054 v2015 01.calculate the basic empty mass and the centre of gravity.. 240 ?
968.4 kg and 179.7 cm
Ecqb03 july 2016...sorry, we haven't yet recovered the annex. we get only the question and the correct answer this is nice, isn't it
Question 86-30 : For this question use annex ecqb 031 057 v2015 05.using the loading manifest in the annex, determine the basic empty mass... 240 ?
Question 86-31 : The bem of an aircraft is the basic empty weight of an aircraft without crew and items of removable equipment. it is found in the... ?
Weighing schedule at the last date of weighing.
Question 86-32 : The mass of an aircraft is 2000 kg and 400 kg of freight is added to a hold 2 m aft of the present cg position, the movement of the cg is ?
0.33 m aft.
Change of cg = mass added x distance from hold to cg / new total mass..change of cg = 400 x 2 / 2000 + 400 = 0.33 m...we add cargo aft, thus the cg will move aft.
Question 86-33 : Once the mass and balance documentation has been signed prior to flight ?
Acceptable last minute change to the load must be documented.
See easa air ops regulation no 965/2012..cat.pol.mab.105 mass and balance data and documentation.
Question 86-34 : Using the loadsheet on the annex, determine the underload and the difference between the maximum allowed tom and the actual tom. the underload is..... 248 ?
3770 kg and the difference is 7170 kg.
Underload = allowed tl total tl.underload = 15000 kg 11230 kg = 3770 kg...difference mtom and actual tom.actual tom = om + tl.actual tom = 44400 kg + 11230 kg = 55630 kg...difference = mtom actual tom.difference = 62800 kg 55630 kg = 7170 kg.
Question 86-35 : A location in the aircraft which is identified by a number designating its distance from the datum is known as ?
Station.
Station is a location in the aircraft which is identified by a number designating its distance from the datum.
Question 86-36 : The centre of gravity of a body is that point ?
Through which the sum of the forces of all masses of the body is considered to act.
Question 86-37 : Assuming gross mass, altitude and airspeed remain unchanged, movement of the centre of gravity from the forward to the aft limit will cause ?
Increased cruise range.
With a forward cg, the aircraft is 'nose heavy', he has a nose down moment, thus, the downforce on the tail on a steady flight, must increase...the total aircraft weight increases and therefore more weight = more drag = more power = reduced maximum cruise range..with an aft cg, downforce on the tail on a steady flight is decreased.less weight = less drag = less power = increased cruise range.
Question 86-38 : Moment balance arms are measured from a specific point to the body station at which the mass is located. that point is known as ?
The datum.
The datum is an imaginary vertical line chosen on the longitudinal axis of the aircraft, specified by the designer, from which all horizontal cg measurements are made.. 159.in most cases, the datum is located in the vicinity of the aircraft nose, usually the firewall.
Question 86-39 : The centre of gravity of an aircraft is that point through which the total mass of the aircraft is said to act..the weight acts in a direction ?
Parallel to the gravity vector.
Img145.the sum of the aircraft weight acts through the center of gravity towards the earth's center.
Question 86-40 : When an aircraft is stationary on the ground, its total weight will act vertically ?
Through its centre of gravity.
Centre of gravity cg is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector.
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