The Zero Fuel Mass is the mass of the aircraft ?
Result > topography
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 ?
What is the reason for knowing accurately what your weight is during flight ?
Basic empty mass basic mass the mass of an aircraft plus standard items such as Pyrotechnics, fuel, passengers, crew Basic empty mass (basic mass) the mass of an aeroplane plus standard items such as unusable fuel other unusable fluids lubricating oil in engine auxiliary units fire extinguishers pyrotechnics emergency oxygen equipment supplementary electronic equipment... 
The following data applies to an aircraft which about to take off maximum structural take off mass 8400 kgperformance limited take off mass 7920 kgdry operating mass 5230 kgcrew and operating items 460 kgtake off fuel 980 kgfrom this data calculate mass of useful load 269kg,7 kg, 363kg, 3 5kg. Useful load = take off mass dry operating mass useful load = 7920 kg 5230 kg useful load = 2690 kg 
1 ton equals approximately 22 lb, 2lb,2 lb, 22lb. 
Given basic empty mass 5300 kgdry operating mass 5500 kgzero fuel mass 5980 kgtake off mass 7980 kgthe useful load 248kg, 268kg, 2kg, 48kg. Useful load = take off mass dry operating mass useful load = 7980 kg 5500 kg useful load = 2480 kg Question Mass and Balance Details of Aircraft 68 Answer 8
Based on actual conditions an aeroplane has following performance take off mass limitations flaps 0° 10° 15°runway 4100 4400 4600climb 4700 4500 4200masses are in kg structural limits take off/landing/zero fuel 4 300 kgthe maximum take off mass 43 kg, 47 kg, 4kg, 42 kg. You must compare 4300kg structural limit with runway limit climb limit at each flap setting select lowest at flap 0°, lowest limit will be 4100 kg. at flap 10, lowest limit will be 4300 kg. at flap 15, lowest limit 4200 kg. now pick highest of three we can safely get airborne at 4300 kg at flap 10°. Question Mass and Balance Details of Aircraft 68 Answer 9
Mass individual passengers to be carried on an aeroplane may be determined from a verbal statement or on behalf of passengers if number of Passenger seats available less than , passengers carried less than , passenger seats available less than 2 , passengers carried less than 2. Where number of passenger seats available less than 10 passenger mass may be determined verbal statement. Question Mass and Balance Details of Aircraft 68 Answer 10
The regulated take off mass The lower of performance limited take off mass maximum structural take off mass, take off mass subject to departure airfield limitations, higher of performance limited take off mass maximum structural landing mass, maximum permissible total mass of aircraft at commencement of take off. Regulated take off mass = lower of take off mass subject to departure airfield limitations (performance limited take off mass) and maximum permissible total mass of aircraft at commencement of take off (maximum structural take off mass). Question Mass and Balance Details of Aircraft 68 Answer 11
Given container size length x width x height 0 8 x 0 8 x 0 8 mcontainer has 2 supports 0 2 m each in longitudinal direction maximum running load 1915 kg/mcalculate maximum total mass of loaded container without exceeding maximum permissible running load 766 kg, 383 kg,532 kg, 2393 kg. If maximum running load 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 0.4 m (= total load pressing down on a running load length of 0.4 m). 1915 kg x 0.4m = 766 kg. Question Mass and Balance Details of Aircraft 68 Answer 12
From pilot's flight manual determine maximum total volume of fuel which can be loaded into standard tank version 1064 2367 l,868 l, 824l, 2 2l. Read question carefully if it asking 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. Question Mass and Balance Details of Aircraft 68 Answer 13
The basic advantage of standard size containers Standard size containers are designed to fit lock into cargo compartment maximum space efficiency, maximum mass of cargo loaded in containers always limited the mtom, with cargo loaded in containers one does not have to observe maximum floor loading limit, maximum mass of cargo loaded in containers often limited the g forces in flight. Question Mass and Balance Details of Aircraft 68 Answer 14
From pilot's flight manual determine maximum total mass of fuel which can be loaded into standard tank version 1064 87kg, 2367 kg, 2996 kg, 824kg. Read question carefully if it asking 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. Question Mass and Balance Details of Aircraft 68 Answer 15
The maximum floor loading of cargo compartment specified to be 732 kg/m² which the smallest given pallet size acceptable to load a box of 826 kg.2 m x.2 m,.25 m x.25 m,.3 m x.3 m,. 5 m x. 5 m. Floor loading limit 732 kg/m² ==> you can put maximum 732 kg to 1 m². that's limit. you have 826 kg to load. so yo need more than 1 m² space 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 ==> 1.2 m x 1.2 m ==> 1.44 m² Question Mass and Balance Details of Aircraft 68 Answer 16
The term 'landing mas at destination defined as 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. Question Mass and Balance Details of Aircraft 68 Answer 17
Determine take off mass tom the following single engine aeroplane standard empty mass 1764 lbsoptional equipment 35 lbspilot + front seat passenger 300 lbscargo mass 350 lbsfuel quantity at brakes release 60 gal trip fuel 35 gal fuel density 6 lbs/gal 28 9 lbs, 2764 lbs, 2799 lbs, 2659 lbs. Take off mass = 1764 + 35 + 300 + 350 + (6 x 60) take off mass = 2809 lbs Question Mass and Balance Details of Aircraft 68 Answer 18
Refer to figure 031 15 calculate maximum fuel mass the centre tank in pounds 545lbs, 3 78 lbs,568lbs, 864lbs. The maximum mass of fuel in centre tank 7008 kg. convert this value into pounds to get 15450 lbs (1kg = 2.2 lbs). Question Mass and Balance Details of Aircraft 68 Answer 19
What the reason cargo loads to be tied down Preventing such loads from moving to remain within cg limits of aircraft, maximising space increasing maximum payload of aircraft, maximising performance of aircraft during take off landing procedures, maintaining enough space in compartment hold in case of evacuation. Question Mass and Balance Details of Aircraft 68 Answer 20
The structural limitation of a baggage compartment 50 lb/ft a load has a mass of 320 kg and has to be distributed over an area of at least.3m², 6.4 m²,.76 m²,4. m². 1 m = 3.28 ft therefore 1 m² = 10.76 ft² convert limitation of 50 lb/ft² to kg 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 the question 320 kg. to find distribution we need to use rule of proportion to find aera a mass of 320 kg 1m² / 244 kg x 320 kg = 1.31 m² Question Mass and Balance Details of Aircraft 68 Answer 21
The loaded centre of gravity cg of an aeroplane 713 mm aft of datum the mean aerodynamic chord lies between station 524 mm aft and 1706 mm aft the cg expressed as % mac mean aerodynamic chord 100 x distance between leading edge cg / mac length 100 x (713 524)/ (1706 524) 100 x 189 / 1182 = 15,99%. Question Mass and Balance Details of Aircraft 68 Answer 22
The centre of gravity location of aeroplane normally computed along Longitudinal axis, lateral axis, vertical axis, horizontal axis. Question Mass and Balance Details of Aircraft 68 Answer 23
In mass and balance calculations which of following describes datum It the point on aircraft designated the manufacturer from which all centre of gravity measurements calculations are made, it the most forward position of centre of gravity, it the most aft position of centre of gravity, it the distance from centre of gravity to point through which weight of component acts. To be correct, this not necessarily a point 'on' aircraft... the datum an imaginary vertical line chosen on longitudinal axis of aeroplane, specified the designer, from which all horizontal c of g measurements are made. in most cases, datum located in vicinity of aircraft nose, usually firewall. Question Mass and Balance Details of Aircraft 68 Answer 24
An aircraft has its centre of gravity located 7 metres from datum line and it has a weight of 49000 n the moment about datum 343nm,.43 nm, 7nm, 34n/m. Arm = moment / force 7 = x / 49000 7 x 49 000 = 343000 nm. nm = newton multiplied meter. Question Mass and Balance Details of Aircraft 68 Answer 25
Which one of following correct Arm = moment / force, arm = force x moment, arm = force / moment, moment = force / arm Question Mass and Balance Details of Aircraft 68 Answer 26
Which of following statements correct A rear centered aircraft less stable stalls at a slower speed than a forward centered aircraft, if actual centre of gravity located behind aft limit of centre of gravity it possible that aeroplane will be unstable, making it necessary to increase elevator forces, if actual centre of gravity close to forward limit of centre of gravity aeroplane may be unstable, making it necessary to increase elevator forces, lowest stalling speed obtained if actual centre of gravity located in middle between aft forward limit of centre of gravity. Question Mass and Balance Details of Aircraft 68 Answer 27
In mass and balance calculations 'index' Is a figure without unit of measurement which represents a moment, a location in aircraft identified a number, an imaginary vertical plane or line from which all measurements are taken, range of moments centre of gravity (cg) can have without making aircraft unsafe to fly. Index the moment divided a constant, usually 1000. it used to simplify calculations decreasing values. 'a location in aircraft identified a number' a position. and 'an imaginary vertical plane or line from which all measurements are taken' the datum. Question Mass and Balance Details of Aircraft 68 Answer 28
Which of following are exact propositions 1 an aircraft belonging to a fleet must be weighed systematically every 48 months2 an aircraft not belonging to a fleet must be weighed systematically every 9 years Incorrect, 2 incorrect, correct, 2 correct, correct, 2 incorrect, incorrect, 2 correct. An aeroplane must be re weighed at certain intervals at intervals of 4 years if individual aeroplane masses are used 9 years if fleet masses are used. Question Mass and Balance Details of Aircraft 68 Answer 29
At what mass an aircraft weighed The basic empty mass, basic mass, empty mass, dry operating mass. Basic empty mass the mass of an aeroplane plus standard items such as unusable fuel other unusable fluids lubricating oil in engine auxiliary units fire extinguishers pyrotechnics emergency oxygen equipment supplementary electronic equipment. Question Mass and Balance Details of Aircraft 68 Answer 30
An aircraft weighed and following recordings are made nose wheel assembly scale 5330 kgleft main wheel assembly scale 12370 kgright main wheel assembly scale 12480 kgif 'fixed item amount to a mass of 1780 kg with a crew mass of 545 kg empty mass as entered in weight schedule 38kg, 284 kg, 3 96kg, 325 5 kg. The 'fixed item are parts of aircraft when it weighed, you don't have to add them again to find empty mass 5330 + 12370 + 12480 = 30180 kg. Question Mass and Balance Details of Aircraft 68 Answer 31
If individual masses are used mass of an aircraft must be determined prior to initial entry into service and thereafter 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. 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 Mass and Balance Details of Aircraft 68 Answer 32
At maximum landing mass range of safe cg positions as determined from appropriate graph in loading manual 206 Forward limit 7.4% mac aft limit 27. % mac, forward limit 8. % mac aft limit 27.2% mac, forward limit 8.6% mac aft limit 27. % mac, forward limit 8. % mac aft limit 26.8% mac. Question Mass and Balance Details of Aircraft 68 Answer 33
At a given mass cg position at 15% mac if leading edge of mac at a position 625 6 inches aft of datum and mac given as 134 5 inches determine position of cg in relation to datum 645.78 inches aft of datum, 6 5.43 inches aft of datum, 2. 8 inches aft of datum, 228.34 inches aft of datum. The mac lenght 134.5 inches the cg at 15% of this distance back from leading edge 15% of 134.5 inches 20.175 inches. if leading edge of mac at 625.6 inches aft of datum, cg will be at 625.6 + 20.175 = 645.775 inches aft of datum. Question Mass and Balance Details of Aircraft 68 Answer 34
The aeroplane has a take off mass of 58 000 kg at this mass range of safe cg positions as determined from appropriate graph in loading manual 207 Forward limit 8. % mac aft limit 26.5% mac, forward limit 8.5% mac aft limit 26. % mac, forward limit 8.2% mac aft limit 26.2% mac, forward limit 9.5% mac aft limit 26. % mac. Question Mass and Balance Details of Aircraft 68 Answer 35
When preparing to carry out weighing procedure on an aircraft which of following not required Drain all engine tank oil, drain all useable fuel, drain all chemical toilet fluid tanks, removable passenger services equipment to be off loaded. Basic empty mass the mass of an aeroplane plus standard items such as unusable fuel other unusable fluids lubricating oil in engine auxiliary units fire extinguishers pyrotechnics emergency oxygen equipment supplementary electronic equipment. engine oil included in basic empty mass. Question Mass and Balance Details of Aircraft 68 Answer 36
An aircraft weighed prior to entry into service who responsible deriving dry operational mass from weighed mass the addition of 'operational item The operator, the appropriate aviation authority, the aircraft manufacturer or supplier, the commander of aircraft. The operator responsible deriving dry operational mass from weighed mass the addition of 'operational item, prior aircraft enter into service. Question Mass and Balance Details of Aircraft 68 Answer 37
An aircraft may be weighed In an enclosed, non air conditioned, hangar, in a quiet parking area clear of normal manoeuvring area, in an area of airfield set aside maintenance, at a specified 'weighing location' on airfield. Weighing procedures normal precautions consistent with good practices in weighing procedures, such as checking completeness of aircraft equipment, determining that fluids are properly accounted for, the weighing accomplished in an enclosed building preventing effect of wind should be provided. Question Mass and Balance Details of Aircraft 68 Answer 38
A aeroplane has a landing mass of 53000kg the range of safe cg positions as determined from appropriate graph in loading manual 208 Forward limit 7.8% mac aft limit 27. % mac, forward limit 8.2% mac aft limit 27. % mac, forward limit 7.3% mac aft limit 26.8% mac, forward limit 8.7% mac aft limit 26.8% mac. Question Mass and Balance Details of Aircraft 68 Answer 39
The aeroplane has a mass of 61 000 kg in cruise the range of safe cg positions as determined from appropriate graph in loading manual 209 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. % aft limit 27.2% mac. Question Mass and Balance Details of Aircraft 68 Answer 40
An aeroplane must be re weighed at certain intervals where an operator uses 'fleet masse and provided that changes have been correctly documented this interval 9 years each aeroplane, 4 years each aeroplane, whenever certificate of airworthiness renewed, whenever a major modification carried out. 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.
Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.
2679 Free Training Exam