Using the data given at the appendix to this question if the fuel index corrections from ZFM index are as follows 9500 kg 0 96500 kg 6 13500 kg 4 ?
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Using the data given at the appendix determine which of the following correctly gives the values of the Zero Fuel Mass ZFM of the aeroplane and the load index at ZFM 225 ?
For this question use annex ECQB 031 MB 02 v2015 03 From the data given at the appendix and assuming a fuel index shift of 5 7 from the ZFM loaded index determine which of the following is the ?
From data contained in attached appendix maximum allowable take off mass and traffic load respectively 227 6 6 kg2 5kg, 68 38 kg8588 kg, 6677kg732kg, 6 425 kg 975 kg. 
An aeroplane carrying a traffic load of 10320 kg complete necessary sections and determine which of answers given below represents maximum increase in traffic load 228 83kg, 655 kg, 7kg, 8268 kg. 
When has centre of gravity to be computed Prior to every flight, after every 4 hours inspection, at least every 4 years, during every yearly inspection. 
What mass has to be entered in loading chart aviation fuel f 34 if 170 l may be refuelled fuel density = 0 78 kg/l 33 kg,33 dan,7kg, 2 8 kg. 170 litres x 0.78 = 132.6 kg. for information, aviation fuel f 34 a military kerosene type turbine fuel with fuel system icing inhibitor. Question Determination of CG Position 71 Answer 8
An aeroplane with a two wheel nose gear and four main wheels rests on ground with a single nose wheel load of 500 kg and a single main wheel load of 6000 kg the distance between nose wheels and main wheels 10 meter how far the centre of gravity in front of main wheels 4cm, 25 cm, 4 m, 4.6 cm. Total airplane weight = (500 x 2) + (6000 x 4) = 25 000 kg. the center of gravity at this weight located at 1000 kg x 10 m / 25 000 kg = 0.4 m in front of main wheels. Question Determination of CG Position 71 Answer 9
Using reference provided without crew weight and cg position of aircraft are 7 000 kg and 4 70m the mass of pilot 90 kg mass of co pilot 75 kg and mass of flight engineer 90 kg with this crew on board cg position of aircraft will be 231 4.6 5 m,.2 7 m, 4.783 m, 4.455 m. Take moments individually pilot 184 kg.m copilot 153 kg.m flight engineer (column b) 242 kg.m basic empty mass moment 7000 x 4.7 = 32900 kg.m total moment 33479 kg.m total mass 7000 + 90 + 75 + 90 = 7255 kg. cg = moment/mass = 33479/7255 = 4.615 m. Question Determination of CG Position 71 Answer 10
Given that flight time 2 hours and estimated fuel flow will be 1050 l/h and average oil consumption will be 2 25 l/h the specific density of fuel 0 79 the specific density of oil 0 96 the 'freight 2' will be dropped during flight within scope of a rescue action calculate cg position at landing 233 24 cm aft of datum, 25 cm aft of datum, 22 cm aft of datum, 27 cm aft of datum. Take off mass is 19339 kg minus fuel = 2100 x 0.79 = 1659 kg minus oil = 4.5 liter x 0.96 = 4.32 kg minus 'freight 2' = 410 kg our landing mass will be = 17265.68 kg take off moment is 392350 kg.cm fuel moment = 1659 x ( 8 cm) = +13272 kg.cm oil moment = 4.32 x 40 cm = 172.8 kg.cm 'freight 2' moment = 410 x ( 40 cm) = +16400 kg.cm total moment at landing = 421849.2 kg.cm the cg position at landing = 421769.2 kg.cm / 17265.68 kg = 24.42 cm Question Determination of CG Position 71 Answer 11
An aeroplane with a two wheel nose gear and four main wheels rests on ground with a single nose wheel load of 725 kg and a single main wheel load of 6000 kg the distance between nose wheels and main wheels 10 meters how far the centre of gravity in front of main wheels 57 cm, 93 cm, 8 cm,76 cm. Total mass (725 kg x 2) + (6000 kg x 4) = 25450 kg. the distance between nose wheels the main wheels 10 meters. the centre of gravity, in front of main wheels, at centre of gravity = total moment / total mass. centre of gravity = (1450 kg x 10 m) / 25450 kg = 0,5697 m. Question Determination of CG Position 71 Answer 12
An aeroplane has a planned take off mass of 200 000 kg its cg located at 15 38 m of reference point representing a cg location at 30% mac mean aerodynamic cord moment arm of forward cargo 15 mmoment arm of aft cargo 25 mfor performance purposes value of centre of gravity location need to be move aft to 35% mac what mass of cargo must be shifted from front cargo hold to aft hold 234 46 kg, 56 kg, 36 kg, it impossible to move cg at requested value. Length of mean aerodynamic chord = (14 + 4.6) 14 = 4.6 m change in cg = 30% vers 35% = 5% 5% of mac lenght = 5% 4.6 = 0.23 m change in mass / total mass = change in cg / total distance moved change in mass = change in cg x total mass / total distance moved change in mass = 0.23 m x 200000 kg / 10 m change in mass = 4600 kg. Question Determination of CG Position 71 Answer 13
The index method in mass and balance calculations used Reducing magnitude of moment, reducing magnitude of useful load, increasing magnitude of useful load, increasing magnitude of moment. In mass balance calculations 'index' a figure without unit of measurement which represents a moment. the value of index the moment divided a constant, usually 1000. it used to simplify calculations decreasing values. Question Determination of CG Position 71 Answer 14
What are advantages of using index method to determine moments it Reduces magnitude of moments, making it less time consuming to compute, digitalised can be automatically uploaded to aircraft fmc to determine stabiliser trim setting, directly produces position of cg the stabiliser trim setting, enabled pilots to calculate position of cg mental arithmetic thereby expedites mass balance calculations. Question Determination of CG Position 71 Answer 15
What the principle of index method To divide high magnitude moments a constant make result more easier to use, to refer every item of aircraft to a position called ba (balance arm), to compute cg position stabiliser trim setting without completing a load sheet, to round all values easier much faster calculation. Ecqb03 july 2016 Question Determination of CG Position 71 Answer 16
Define 'under loa Allowed tom dom useful load, actual tom dom useful load, allowed tl tom, actual tl tom Question Determination of CG Position 71 Answer 17
for this question use annex ecqb 031 046 v2015 01 the aircraft loaded as shown in table calculate new total moment if mass of crew increased 240 3kg.mm, 3 kg.mm, 348 kg.mm, 348kg.mm Ecqb03 july 2016 sorry, we haven't yet recovered annex. we get only question the correct answer (this nice, isn't it?) !!! Question Determination of CG Position 71 Answer 18
The planned take off mass of a turbojet aeroplane 180 000 kg with its centre of gravity located at 26 % mac mean aerodynamic cord shortly prior to engine start local staff informs flight crew that 4 000 kg must be unloaded from cargo 4 after handling operation new centre of gravity location in % mac will be 244 22.%, 3.%, 2.%, 24.2 %. Img /com_en/com031 291.jpg Question Determination of CG Position 71 Answer 19
A turbojet aeroplane has a planned take off mass of 190 000 kg following cargo loading crew informed that centre of gravity at take off located at 38 % mac mean aerodynamic cord which beyond limits the captain decides then to redistribute part of cargo load between cargo 1 and cargo 4 in order to obtain a new centre of gravity location at 31 % mac he asks a transfer of 244 3kg from cargo 4 to cargo, 2kg from cargo 4 to cargo,kg from cargo 4 to cargo, it not possible to obtain required centre of gravity. Img /com_en/com031 292.jpg Question Determination of CG Position 71 Answer 20
The planned take off mass of an aeroplane 190 000 kg with its centre of gravity located at 29 % mac mean aerodynamic cord shortly prior to engine start local staff informs flight crew that an additional load of 4 000 kg must be loaded in cargo 4 after loading this cargo new centre of gravity location will be 245 32,2 %, 3%, 27 %, 25 %. Question Determination of CG Position 71 Answer 21
The planned take off mass of an aeroplane 180 000 kg with its centre of gravity located at 31 % mac mean aerodynamic cord shortly prior to engine start local staff informs crew that an additional load of 4 000 kg must be loaded in cargo 1 after loading this cargo new centre of gravity location will be 246 Question Determination of CG Position 71 Answer 22
What dry operating index doi The index the position of centre of gravity at dry operating mass, distance from datum to centre of gravity of a mass, point through which force of gravity said to act on a mass, product of mass balance arm. Dry operating index (doi) the index the position of centre of gravity at dry operating mass. dry operation mass (dom) the total mass of aeroplane ready a specific type of operation excluding usable fuel traffic load. the mass includes items such as i) crew crew baggage. ii) catering removable passenger service equipment. iii) potable water lavatory chemicals. iv) food beverages. balance arm (ba) the distance from datum to centre of gravity of a mass. centre of gravity (cg) that point through which force of gravity said to act on a mass. moment the product of mass balance arm. Question Determination of CG Position 71 Answer 23
A 3 m long plank on a pivot halfway along its length a 1 kg mass suspended on left end and a 2 kg mass from other end how far and in which direction should plank be moved in order the plank to be in balance.5m to left,.5m to right,m to left,m to right. Moment = mass x balance arm 1 kg x 1.5 m = 1.5 kgm 2 kg x 1.5 m = 3 kgm the 1 kg mass must have same moment than 2 kg mass the plank to be in balance 1 kg x 2 m = 2 kg x 1 m 2 kg.m = 2 kg.m. Question Determination of CG Position 71 Answer 24
For following see saw to be in balance with a mass of 35 kg suspended on left end 14m left of pivot and 75 kg suspended on right end mass required at position 5m left of pivot must be 247 22 kg,36 kg, 57 kg,4 kg. 14m x 35 kg + 5m x ? = 8m x 75 kg ? = (8 x 75 14 x 35) / 5 ? = (600 490) / 5 ? = 22 kg. Question Determination of CG Position 71 Answer 25
Refer to figure 031 13 for a medium range twin jet aircraft with a cg located at 18% mac at 62000 kg gross mass determine stabilizer trim units required a take off flap setting of 15° Question Determination of CG Position 71 Answer 26
Consider a conventional aircraft with three wheels the nose jack located 161 inches aft of datum the main wheel jacks are located 775 inches aft of datum after weighing following results are reported nose jack 2300 lbeach main wheel jack 19300 lbwhat the basic empty mass of aircraft and centre of gravity from datum Bem 4 9 lb, cg 74.5 in, bem 2 6 lb, cg 722.3 in, bem 4 9 lb, cg 722.3 in, bem 2 6 lb, cg 7 9.6 in. Question Determination of CG Position 71 Answer 27
Refer to figure 031 57 calculate cg position and moment the basic empty mass using data given from attached table 5.7 in aft of datum the moment 365 74 in.lb,.4 in aft of datum the moment 489666 in.lb, 95.3 in aft of datum the moment 38 373 in.lb, 3.6 in aft of datum the moment 43 998 in.lb Question Determination of CG Position 71 Answer 28
The mass and cg of an aircraft must be established actual weighing the Operator prior to initial entry into service, owner operator before first flight of day, pilot on entry of aircraft into service, engineers before commencing service. Easa air ops regulation (eu) no 965/2012 cat.pol.mab.100 mass balance, loading (a) during any phase of operation, loading, mass centre of gravity (cg) of aircraft shall comply with limitations specified in afm, or operations manual if more restrictive. (b) the operator shall establish mass the cg of any aircraft actual weighing prior to initial entry into service 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 repairs on mass balance shall be accounted and properly documented. aircraft shall be reweighed if effect of modifications on mass balance not accurately known. (c) the weighing shall be accomplished the manufacturer of aircraft or an approved maintenance organisation. (d) the operator shall determine mass of all operating items crew members included in aircraft dry operating mass weighing or using standard masses. the influence of their position on aircraft's cg shall be determined. (e) the operator shall establish mass of traffic load, including any ballast, actual weighing or determining mass of traffic load in accordance with standard passenger baggage masses. (f) in addition to standard masses passengers checked baggage, operator can use standard masses other load items, if it demonstrates to competent authority that these items have same mass or that their masses are within specified tolerances. (g) the operator shall determine mass of fuel load using actual density or, if not known, density calculated in accordance with a method specified in operations manual. (h) the operator shall ensure that loading of (1) its aircraft performed under supervision of qualified personnel and (2) traffic load consistent with data used the calculation of aircraft mass balance. (i)the operator shall comply with additional structural limits such as floor strength limitations, maximum load per running metre, maximum mass per cargo compartment the maximum seating limit. for helicopters, in addition, operator shall take account of in flight changes in loading. (j) the operator shall specify, in operations manual, principles methods involved in loading in mass balance system that meet requirements contained in (a) to (i). this system shall cover all types of intended operations. Question Determination of CG Position 71 Answer 29
Refer to figure 031 59 the see saw in a state of equilibrium calculate distance between a and c 3 ,49 m, 37,m, 29,49 m, 22,49 m. left side must be equal to right side = moment on left side must be equal to moment on right side (520kg x 8m) = ((48kg x 7m) + 170 kg x x) x the distance between pivot to mass c x = ((520kg x 8m) (48kg x 7m)) / 170 x = (4160 336) / 170 = 22,49 m. distance between a c 8 m + 22,49 m = 30,49 m. Question Determination of CG Position 71 Answer 30
Given length of mac 114 inchesforward gc limit 12% macaft cg limit 38% maccalculate distance of cg at 10m mac with reference to forward limit 2.28 inches, 8.77 inches, 25. 8 inches,.53 inches. Question Determination of CG Position 71 Answer 31
Consider a conventional aircraft with three wheels the nose jack located 161 inches aft of datum the main wheel jacks are located 775 inches aft of datum after weighing following results are reported nose jack 6488 lbeach main wheel jack 17783 lbwhat the basic empty mass of aircraft and centre of gravity from datum Bem 42 54 lb, cg 68.3 in, bem 2427lb, cg 6.9 in, bem 42 54 lb, cg 57.3 in, bem 2427lb, cg 936 in. Question Determination of CG Position 71 Answer 32
Refer to figure 031 61 originally there has been 225 l of fuel in tank of aircraft but pilot decides do add 200 kg of additional fuel what will happen to centre of gravity The cg will move towards nose of aircraft, the cg will move towards tail of aircraft, the cg will move towards bottom of aircraft, the cg will remain same. Question Determination of CG Position 71 Answer 33
Refer to figure 031 05 given force fa 100 ndistance a 6 mdistance b 3 mcalculate force fb to obtain equilibrium Question Determination of CG Position 71 Answer 34
Refer to figure 031 34 givenbem 1200 kgbem cg 3 00pilot and front pax 200 kgcargo on pax floor 50 kgfuel 250 kgfind loaded centre of gravity cg using attached graph 2.96 m, 2.99 m, 3. 3 m, 3. m. Question Determination of CG Position 71 Answer 35
Refer to figure 031 04 given force fa 100 ndistance a 6 mdistance b 3 mcalculate force fa to obtain equilibrium Question Determination of CG Position 71 Answer 36
Select correct statement the cg safe range The safe range falls between front rear cg limits includes both limits, the safe range falls between front rear cg limits but does not include them, the safe range falls between front rear cg limits but only includes aft limit, the safe range falls between front rear cg limits but only includes forward limit. Question Determination of CG Position 71 Answer 37
The fuel index Used to calculate correct position of cg due to different locations of fuel tanks, difference between zero fuel mass index the doi, a standard value given easa can be used different types of aircraft, only used aeroplanes with wing tip tanks. Question Determination of CG Position 71 Answer 38
Refer to figure 031 03 given force fa 300 nforce fb 150 ndistance a 3 mcalculate distance b to obtain equilibrium Question Determination of CG Position 71 Answer 39
Refer to figure 031 60 given weight 110800 kgmac 31 6%from given values and information given the attached sheet find dry operating index if an additional pilot 85 kg will join flight in zone e 2.4,22. ,22.2,2.7. note moi this question also exists at examination with weight 112600 kg, mac 30.7% an additional pilot of 75 kg in zone g, answer 119.3. Question Determination of CG Position 71 Answer 40
Refer to figure 031 55 find cg position as %mac the take off
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