The centre of gravity of an aircraft ?
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Which statement regarding the relationship between traffic load and range is correct ?
The term 'useful load' as applied to an aircraft includes ?
If other factors are unchanged fuel mileage nautical miles per kg Lower with a forward centre of gravity position. With a forward cg aircraft 'nose heavy' it has a nose down moment thus downforce on tail on a steady flight must be increased the total aircraft weight increases therefore more weight = more drag = more power the fuel mileage (nautical miles per kg) lower with a forward centre of gravity position example with a aft cg fuel mileage = 10 nm 100 kg with a forward cg fuel mileage = only 8 nm 100 kg. 
The stalling speed of an aeroplane will be highest when it loaded with a High gross mass forward centre of gravity. A forward cg requires more lift generates more drag stalling speed will be greater than with an aft cg also a higher gross mass it mandatory to generates more lift which generates more induced drag stalling speed increases. 
With centre of gravity on forward limit which of following to be expected High gross mass forward centre of gravity. The most forward cg is more down force tail needs to generate to compensate keep airplane from pitching down this increased down force must be counteracted increased lift from wing that of course means an increase in angle of attack or airspeed = stall speed increases = consumption increases = range decreases. 
If centre of gravity of an aeroplane moves forward during flight elevator control will become Heavier making aeroplane more difficult to manoeuvre in pitch. When centre of gravity moves forward during flight aeroplane will be more stable but requires more forces to change pitch (elevator control will become heavier). Question 63-8
The determination of centre of gravity in relation to mean aerodynamic chord consists of defining centre of gravity longitudinally in relation to Length of mean aerodynamic chord the leading edge. Longitudinal cg location normally expressed as a percentage of mean aerodynamic chord (mac) from its leading edge. Question 63-9
The maximum zero fuel mass Is calculated a maximum load factor of +2 5 g. Longitudinal cg location normally expressed as a percentage of mean aerodynamic chord (mac) from its leading edge. Question 63-10
When has centre of gravity to be computed Prior to every flight. Longitudinal cg location normally expressed as a percentage of mean aerodynamic chord (mac) from its leading edge. Question 63-11
The operating mass om The take off mass minus traffic load. The operating mass the dry operating mass plus take off fuel mass or/also the operating mass the take off mass minus traffic load /pdf/031_mass_definitions pdf. Question 63-12
The 'regulated landing mas the Lowest of structural limited landing mass the performance limited landing mass. The operating mass the dry operating mass plus take off fuel mass or/also the operating mass the take off mass minus traffic load /pdf/031_mass_definitions pdf. Question 63-13
Given dry operating mass= 29 800 kgmaximum take off mass= 52 400 kgmaximum zero fuel mass= 43 100 kgmaximum landing mass= 46 700 kgtrip fuel= 4 000 kgfuel quantity at brakes release= 8 000 kgthe maximum traffic load Lowest of structural limited landing mass the performance limited landing mass. Traffic load the total mass of passengers baggage cargo including any non revenue load the lowest mass our limitation. Question 63-14
The take off mass of an aircraft 117 000 kg comprising a traffic load of 18 000 kg and fuel of 46 000 kg what the dry operating mass Lowest of structural limited landing mass the performance limited landing mass. Dry operating mass = the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load this mass includes items such as + crew crew baggage + catering removable passenger service equipment (food beverages potable water lavatory chemicals etc ) + special operational equipment (e g stretchers rescue hoist cargo sling) dry operating mass = take off mass traffic load fuel dry operating mass = 117000 18000 46000 = 53000 kg. Question 63-15
The dry operating mass includes Crew crew baggage catering removable passenger service equipment potable water lavatory chemicals. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-16
The maximum load per running metre of an aircraft 350 kg/m the width of floor area 2 metres the floor strength limitation 300 kg per square metre which one of following crates length x width x height can be loaded directly on floor A load of 4 kg in a crate with dimensions 2 m x 2 m x 2 m. Maximum load per running metre 400 / 1 2 = 333 kg/m floor strength limitation 400 / (1 2 x 1 2) = 277 77 kg/m² both limitations are respected. Question 63-17
Given following maximum structural take off mass 48 000 kg maximum structural landing mass 44 000 kg maximum zero fuel mass 36 000 kg taxi fuel 600 kg contingency fuel 900 kg alternate fuel 800 kg final reserve fuel 1 100 kg trip fuel 9 000 kg the actual tom can never be higher than A load of 4 kg in a crate with dimensions 2 m x 2 m x 2 m. the actual take off mass the lowest of three it can never be higher if we don't want structural troubles. Question 63-18
The maximum zero fuel mass 1 a regulatory limitation2 calculated a maximum load factor of +3 5 g3 based on maximum permissible bending moment at wing root4 defined on assumption that fuel consumed from outer wings tank first5 defined on assumption that fuel consumed from centre wing tank firstthe combination of correct statements A load of 4 kg in a crate with dimensions 2 m x 2 m x 2 m. The maximum zero fuel mass a regulatory limitation (cs23 cs25) it a design limitation to prevent wing bending it defined on assumption that fuel consumed from centre wing tank first. Question 63-19
At flight preparation stage following parameters in particular are available determining mass of aircraft 1 dry operating mass2 operating masswhich statement correct The dry operating mass includes fixed equipment needed to carry out a specific flight. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-20
Which of following corresponds to zero fuel mass The take off mass of an aeroplane minus all usable fuel. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-21
Given that maximum structural take off mass 146000 kg maximum structural landing mass 93900 kg maximum zero fuel mass 86300 kg trip fuel 27000 kg taxi fuel 1000 kg contingency fuel 1350 kg alternate fuel 2650 kg final reserve fuel 3000 kgdetermine actual take off mass The take off mass of an aeroplane minus all usable fuel. Without dry operating mass our traffic load will depend on maximum zero fuel mass or a maximum structural mass we have two possibility lowest will be our answer actual take off mass = maximum structural landing mass + trip fuel actual take off mass = 93900 + 27000 = 120 900 kg or actual take off mass = maximum zero fuel mass + trip fuel + contingency + alternate + final reserve actual take off mass = 86300 + 27 000 + 1350 + 2650 + 3000 = 120 300 kg. Question 63-22
Given maximum structural take off mass 72 000 kg maximum structural landing mass 56 000 kg maximum zero fuel mass 48 000 kg taxi fuel 800 kg trip fuel 18 000 kg contingency fuel 900 kg alternate fuel 700 kg final reserve fuel 2 000 kg determine actual take off mass The take off mass of an aeroplane minus all usable fuel. the actual take off mass the lowest of three it can never be higher if we don't want structural troubles. Question 63-23
The actual take off mass equal to 41 545 kg catering 300 kg safety and rescue material nil fly away kit nil crew inclusive crew baggage 365 kg fuel at take off 3 000 kg unusable fuel 120 kg passengers baggage cargo 8 000 kgthe basic empty mass The take off mass of an aeroplane minus all usable fuel. The basic empty mass includes unusable fuel 41 545 kg (8000 kg + 3000 kg) + 120 kg = 30 665 kg. Question 63-24
The zero fuel mass of an aeroplane always The take off mass minus mass of take off fuel. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-25
Given maximum structural take off mass 146 900 kgmaximum structural landing mass 93 800 kgmaximum zero fuel mass 86 400 kgtrip fuel 27 500 kgblock fuel 35 500 kgengine starting and taxi fuel 1 000 kgthe maximum take off mass equal to The take off mass minus mass of take off fuel. We are looking the maximum take off mass maximum take off mass = maximum zero fuel mass + fuel at take off maximum take off mass = 86 400 + (35 500 1 000) = 120 900 kg the maximum zero fuel mass a structural limiting mass it made up of aeroplane dry operational mass + traffic load unuseable fuel. Question 63-26
Traffic load the Zero fuel mass minus dry operating mass. We are looking the maximum take off mass maximum take off mass = maximum zero fuel mass + fuel at take off maximum take off mass = 86 400 + (35 500 1 000) = 120 900 kg the maximum zero fuel mass a structural limiting mass it made up of aeroplane dry operational mass + traffic load unuseable fuel. Question 63-27
While making mass and balance calculation a particular aircraft term 'basic empty mas applies to sum of airframe engine s fixed ballast plus Unusable fuel full operating fluids. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-28
The term 'maximum zero fuel mas consist of The maximum permissible mass of an aeroplane with no usable fuel. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-29
The actual 'zero fuel mas equal to Dry operating mass plus traffic load. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-30
The actual 'take off mas equivalent to Dry operating mass plus take off fuel the traffic load. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-31
With respect to aeroplane loading in planning phase which of following statements always correct lm = landing masstom = take off massmtom = maximum take off masszfm = zero fuel massmzfm = maximum zero fuel massdom = dry operating mass Lm = tom trip fuel. Landing mass = take off mass trip fuel 'mzfm = traffic load + dom' not correct to be correct it would have to say 'mzfm = dom + maximum traffic loa. Question 63-32
Given an aeroplane with maximum structural landing mass 125000 kgmaximum zero fuel mass 108500 kgmaximum structural take off mass 155000 kgdry operating mass 82000 kgscheduled trip fuel 17000 kg and reserve fuel 5000 kg assuming performance limitations are not restricting maximum permitted take off mass and maximum traffic load are respectively Lm = tom trip fuel. the lowest value our maximum traffic load (26500 kg) now our maximum permitted take off mass is maximum zero fuel mass + fuel at take off = 108500 + 22000 = 130500 kg. Question 63-33
For purpose of completing mass and balance documentation traffic load considered to be equal to take off mass Lm = tom trip fuel. Take off mass = operating mass + traffic load (operating mass 'dom + fuel at take off') therefore you can say that traffic load = tom operating mass. Question 63-34
For purpose of completing mass and balance documentation operating mass considered to be dry operating mass plus Lm = tom trip fuel. /pdf/031_mass_definitions pdf. Question 63-35
When establishing mass breakdown of an aeroplane empty mass defined as sum of Standard empty mass plus specific equipment mass plus trapped fluids plus unusable fuel 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 63-36
For purpose of completing mass and balance documentation dry operating mass defined as The total mass of aircraft ready a specific type of operation excluding all usable fuel traffic load. Please download following document used as a reference at exam /pdf/031_mass_definitions pdf. Question 63-37
An aircraft's weighing schedule indicates that empty mass 57320 kg the nominal dry operating mass 60120 kg and maximum zero fuel mass given as 72100 kg which of following a correct statement in relation to this aeroplane Operational items have a mass of 28 kg the maximum traffic load this aeroplane 98 kg. Operational items are difference between dry operating mass empty mass 60120 57320 = 2800 kg the traffic load the difference between mzfm dom 72100 60120 = 11980 kg. Question 63-38
An aeroplane to depart from an airfield where performance limited take off mass 89200 kg certificated maximum masses are as follows ramp taxi mass 89930 kgmaximum take off mass 89430 kgmaximum landing mass 71520 kgmaximum zero fuel mass 62050 kgfuel on board at ramp taxi fuel 600 kgtrip fuel 17830 kgcontingency final reserve and alternate 9030 kg if dry operating mass 40970 kg traffic load that can be carried on this flight Operational items have a mass of 28 kg the maximum traffic load this aeroplane 98 kg. lowest limitation 21080 kg. Question 63-39
The empty mass of an aircraft as given in weighing schedule 61300 kg the operational items including crew given as a mass of 2300 kg if take off mass 132000 kg including a useable fuel quantity of 43800 kg useful load Operational items have a mass of 28 kg the maximum traffic load this aeroplane 98 kg. Useful load = the mass of aircraft including everything everyone contained within it at commencement of take off the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load useful load = take off mass dry operating mass = 132000 kg 63600 kg = 68400kg for information dry operating mass includes items such as crew crew baggage catering removable passenger service equipment (food beverages potable water lavatory chemicals etc ) special operational equipment (e g stretchers rescue hoist cargo sling). Question 63-40
The following data applies to an aeroplane which about to take off certified maximum take off mass 141500 kgperformance limited take off mass 137300 kgdry operating mass 58400 kgcrew and crew hand baggage mass 640 kgcrew baggage in hold 110 kgfuel on board 60700 kgfrom this data calculate mass of useful load Operational items have a mass of 28 kg the maximum traffic load this aeroplane 98 kg. Useful load = the mass of aircraft including everything everyone contained within it at commencement of take off the total mass of an aircraft ready a specific type of operation excluding all usable fuel traffic load useful load = take off mass dry operating mass = 137300 kg 58400 kg = 78900 kg for information dry operating mass includes items such as crew crew baggage catering removable passenger service equipment (food beverages potable water lavatory chemicals etc ) special operational equipment (e g stretchers rescue hoist cargo sling).
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