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Title: aircraft mass and balance atpl dat bank
Description: aircraft mass and balance atpl licensE exam sample questions for pilots,flight dispatchers. 100% pass if you study this question data bank well it covers everything you need for your atpl,cpl ppl or flight dispatch caa license exams...you have thousands ways of passing your exams without stress.Thank me later
Description: aircraft mass and balance atpl licensE exam sample questions for pilots,flight dispatchers. 100% pass if you study this question data bank well it covers everything you need for your atpl,cpl ppl or flight dispatch caa license exams...you have thousands ways of passing your exams without stress.Thank me later
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MASS AND BALANCE
INTRODUCTION TO MASS AND BALANCE
Mass Limitations
1
...
For a conventional, nose tricycle gear aircraft configuration, the higher the takeoff mass:
1
...
3
...
Manoeuvrability is reduced
Range will decrease but endurance will increase
Gliding range will reduce
Statement 4 only is correct
A – All statements are correct
B – Statement 3 only is correct
C – Statements 1 and 4 are correct
D – Statement 4 is correct
Ref: AIR: atpl, cpl
Ans: C
3
...
If an aeroplane is at a higher mass than anticipated, for a given airspeed the
angle of attack will:
A – remain constant, drag will decrease and endurance will decrease
B – be decreased, drag will decrease and endurance will increase
C – be greater, drag will increase and endurance will decrease
D – remain constant, drag will increase and endurance will increase
Ref: AIR: atpl, cpl
Ans: C
5
...
This error is not detected by the flight crew but they
will notice that:
A – V1 will be reached sooner than expected
B – speed at un-stick will be higher than expected
C – V1 will be increased
D – the aeroplane will rotate much earlier than expected
Ref: AIR: atpl, cpl
Ans: B
6
...
3 Vs is used
...
If the mass of the aeroplane is increased to 135,000 kg the value of 1
...
At maximum certificated take-off mass an aeroplane departs from an airfield
which is not limiting for either take-off or landing masses
...
An
emergency is declared and the aeroplane returns to departure airfield for an
immediate landing
...
During a violent avoidance manoeuvre, a light twin aircraft, certified to FAR
23 requirements was subjected to an instantaneous load factor of 4
...
The
Flight manual specifies that the aircraft is certified in the normal category for a
load factor of -1
...
8
...
If an extra load is loaded into an aircraft the stall speed is likely to:
A – Stay the same
B – Decrease
C – Increase
D – Change depending on whether the load was placed FWD or AFT of the C
of G
Ref: AIR: atpl, cpl
Ans: C
10
...
Over-loading would result in:
A – a decrease in stalling speed
B – a decrease in fuel consumption
C – an increase in range
D – a reduction of aircraft performance
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
031-01-02 CG limitations
1
...
During take-off you notice that, for a given elevator input, the aeroplane rotates
much more rapidly than expected
...
If the aeroplane is neutrally stable this would suggest that:
A – the CG is forward
B – the CG is in mid range
C – the CG is on the rear limit
D – the CG is behind the rear limit
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
4
...
This
will result in:
A – an increased risk of stalling due to a decrease in tail-plane moment
B – a reduced fuel consumption as a result of reduced drag
C – an increase in longitudinal stability
D – a reduction in power required for a given speed
Ref: AIR: atpl, cpl
Ans: A
5
...
An aeroplane is said to be NEUTRALLY STABLE
...
The mass displacement caused by landing gear extension:
A – does not create a longitudinal moment
B – creates a pitch-up longitudinal moment
C – creates a longitudinal moment in the direction (pitch-up or pitch-down)
determined by the type of landing gear
D – creates a pitch-down longitudinal moment
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
8
...
If the centre of gravity is near the forward limit the aeroplane will:
A – benefit from reduced drag due to the decrease in angle of attack
B – require elevator trim which will result in an increase in fuel consumption
C – require less power for a given airspeed
D – tend to over rotate during take-off
Ref: AIR: atpl, cpl
Ans: B
10
...
Which of the following is most likely to affect the range of centre of gravity
positions on an aeroplane?
A – The need to minimise drag forces and so improve efficiency
B – Location of the undercarriage
C – The need to maintain a low value of stalling speed
D – Elevator and tail-plane (horizontal stabiliser) effectiveness in all flight
conditions
Ref: AIR: atpl, cpl
Ans: D
12
...
Assuming gross mass, altitude and airspeed remain unchanged, movement of
the centre of gravity from the forward to the aft limit will cause:
A – increased cruise range
B – higher stall speed
C – lower optimum cruising speed
D – reduced maximum cruise range
Ref: AIR: atpl, cpl
Ans: A
14
...
The airport has an
exceptionally long runway
...
With the centre of gravity on the forward limit which of the following is to be
expected?
A – A decrease of the stalling speed
B – A decrease in the landing speed
C – A decrease in range
D – A tendency to yaw to the right on take-off
Ref: AIR: atpl, cpl
Ans: C
16
...
A forward C of G would result in:
A – A reduced rate of climb
B – A decrease in cruise range
C – A decrease in both rate of climb and cruise range
D – An increase in both rate of climb and cruise range
Ref: AIR: atpl, cpl
Ans: C
18
...
What effect does the CG on the aft limit have on the fuel consumption of an
aeroplane?
A – Increases
B – Decreases
C – No effect
D – Marginal increase
Ref: AIR: atpl, cpl
Ans: B
20
...
If the CG is aft of the neutral point it results in:
A – increased stability with increased elevator trim
B – Decreased stability with decreased elevator trim
C – Neutral stability
D – Longitudinal instability
Ref: AIR: atpl, cpl
Ans: D
22
...
This is likely to:
A – Be caused by the CG towards the forward limit
B – Be caused by the CG at the aerodynamic centre of the aircraft
C – Be totally unrelated to the position of the CG
D – Cause the CG to move forward
Ref: AIR: atpl, cpl
Ans: B
23
...
The handling and performance problems encountered with a CG too far aft
include:
A – Improvement in nose wheel steering
B – Higher stick forces per G loading with no risk of over-stressing the
airframe in manoeuvres
C – Difficulty or inability to recover from a spin
D – No likelihood of a nose up overbalance (on a bicycle gear aircraft) on the
ground resulting in tail damage
Ref: AIR: atpl, cpl
Ans: C
25
...
In cruise, an extreme aft longitudinal centre of gravity:
A – moves away the cyclic stick from its forward stop and increases the stress
in the rotor head
B – brings the cyclic stick closer to its forward stop and decreases the stress in
the rotor head
C – moves away the cyclic stick from its forward stop and decreases the
stresses in the head rotors
D – brings the cyclic stick closer to its forward stop and increases the stress in
the rotor head
Ref: HELI: atpl, cpl
Ans: D
27
...
A helicopter in the hover that requires an excessive amount of forward and
right cyclic may indicate the centre of gravity is too far:
A – forward and laterally too far to the left
B – forward and laterally too far to the right
C – aft and laterally too far to the left
D – aft and laterally too far to the right
Ref: HELI: atpl, cpl
Ans: C
29
...
Exceeding the forward centre of gravity limit will result in:
A – The helicopter being nose heavy and the pilot may run out of aft cyclic
B – The helicopter being nose heavy and the pilot may run out of forward
cyclic
C – The helicopter being tail heavy and the pilot may run out of forward cyclic
D – The helicopter being tail heavy and the pilot may run out of aft cyclic
Ref: HELI: atpl, cpl
Ans: A
31
...
Who determines the allowable centre-of-gravity range for a helicopter?
A – The licensed engineer carrying out weighing
B – The manufacturer of the helicopter
C – The national aviation authority
D – The pilot in command
Ref: HELI: atpl, cpl
Ans: B
33
...
When must the centre of gravity be computed?
A – After every 400 hrs inspection
B – Prior to every flight
C – At least every four years
D – During every yearly inspection
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
35
...
One effect on an aircraft that is nose-heavy is:
A – a tendency for the nose to pitch up
B – an increase in range
C – a decrease in stability
D – an increase in drag, due to excessive elevator trim
Ref: AIR: atpl, cpl
Ans: D
37
...
Fuel consumption brings the CG forward in flight
...
What is the effect of moving the centre of gravity from the forward limit to the
aft limit?
A – increases stability
B – increases fuel consumption
C – increased range
D – increases stalling speed
Ref: AIR: atpl, cpl
Ans: C
40
...
If the fuel load of a large aircraft was given in litres, but was entered on the
load sheet in kilograms, how would this affect the expected handling of the
aircraft?
A – the stick force required on rotation will be lighter
B – the stick force required on rotation will be heavier
C – the stick force required would be the same in both cases
D – the stick force required would be the same in both cases but the rate of
climb will be less
Ref: AIR: atpl, cpl
Ans: A
031-02
LOADING
031-02-01 Terminology
1
...
A – Traffic load plus dry operating mass
B – Traffic load plus usable fuel mass
C – Dry operating mass plus usable fuel load
D – The part of the traffic load which generates revenue
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
2
...
In mass and balance terms, what is an index?
A – A cut down version of a force
B – A moment divided by a constant
C – A moment divided by a mass
D – A mass divided by a moment
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
4
...
The maximum mass to which an aeroplane may be loaded, prior to engine start,
is:
A – maximum certificated taxi (ramp) mass
B – maximum regulated taxi (ramp) mass
C – maximum certificated take-off mass
D – maximum regulated take-off mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
6
...
By adding to the basic empty mass the following fixed necessary equipment for
a specific flight (catering, safety and rescue equipment, fly away kit, crew), we get:
A – zero fuel mass
B – take-off mass
C – Dry operating mass
D – landing mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
8
...
With respect to aeroplane loading in the planning phase, which of the following
statements is always correct?
LM = Landing Mass
TOM = Take-off Mass
MTOM = Maximum Take-off Mass
ZFM = Zero Fuel Mass
MZFM = Maximum Zero Fuel Mass
DOM = Dry Operating Mass
A – LM = TOM – Trip Fuel
B – MTOM = ZFM + maximum possible fuel mass
C – MZFM = Traffic load + DOM
D – Reserve Fuel = TOM – Trip Fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
10
...
The maximum zero-fuel mass:
1
...
3
...
5
...
is a regulatory limitation
is calculated for a maximum load factor of +3
...
Dry Operating Mass is the mass of the aeroplane less:
A – usable fuel and traffic load
B – usable fuel
C – traffic load, potable water and lavatory chemicals
D – usable fuel, potable water and lavatory chemicals
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
13
...
The actual Zero Fuel Mass is equal to the:
A – Basic Empty Mass plus the fuel loaded
B – Operating Mass plus all the traffic load
C – Dry Operating mass plus the traffic load
D – Actual Landing Mass plus trip fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
15
...
For the purpose of completing the Mass and Balance documentation, the Dry
Operating Mass is defined as:
A – The total mass of the aeroplane ready for a specific type of operation
excluding all usable fuel and traffic load
B – The total mass of the aeroplane ready for a specific type of operation
excluding all usable fuel
C – The total mass of the aeroplane ready for a specific type of operation
excluding all traffic load
D – The total mass of the aeroplane ready for a specific type of operation
excluding crew and crew baggage
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
17
...
Dry operating mass
2
...
The Dry Operating Mass of an aeroplane includes:
A – Fuel and passengers baggage and cargo
B – Unusable fuel and reserve fuel
C – Crew and crew baggage, catering, removable passenger service
equipment, potable water and lavatory chemicals
D – Passengers baggage and cargo
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
19
...
Allowed traffic load is the difference between:
A – operating mass and basic means
B – allowed take off mass and basic mass plus trip fuel
C – allowed take off mass and basic mass
D – allowed take off mass and operating mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
21
...
It is made up of
the aeroplane Dry Operational Mass plus:
A – traffic load and unusable fuel
B – traffic load, unusable fuel and crew standard mass
C – unusable and crew standard mass
D – traffic load and crew standard mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
22
...
The term USEFUL LOAD as applied to an aeroplane includes:
A – traffic load only
B – traffic load plus usable fuel
C – the revenue-earning portion of traffic load only
D – the revenue-earning portion of traffic load plus usable fuel
Ref: AIR: atpl, cpl
Ans: B
24
...
Traffic load is the:
A – Zero Fuel Mass minus Dry Operating Mass
B – Dry Operating Mass minus the disposable load
C – Dry Operating Mass minus the variable load
D – Take-off Mass minus Zero Fuel Mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
26
...
The term Maximum Zero Fuel Mass consists of:
A – The maximum mass authorised for a certain aeroplane not including the
fuel load and operations items
B – The maximum mass authorised for a certain aeroplane not including
traffic load and fuel load
C – The maximum permissible mass of an aeroplane with no usable fuel
D – The maximum mass for some aeroplanes including the fuel load and the
traffic load
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
28
...
In calculations with respect to the position of the centre of gravity a reference is
made to a datum
...
Its
position is given in the aeroplane Flight or Loading Manual
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
30
...
32
...
Its precise position is given in the control and loading manual and it is located:
A – at or near the focal point of the aeroplane axis system
B – at or near the forward limit of the centre of gravity
C – at a convenient point which may not physically be on the aeroplane
D – at or near the natural balance point of the empty aeroplane
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
33
...
This datum point is:
A – a point near the centre of the aeroplane
...
It may be located
anywhere on the aeroplane’s longitudinal axis or on the extensions to that
axis
D – a point from which all balance arms are measured
...
Which is true of the aeroplane empty mass?
A – it is dry operating mass minus fuel load
B – It is a component of dry operating mass
C – It is dry operating mass minus traffic load
D – it is the actual take-off mass, less traffic load
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
35
...
The Traffic Load is defined as:
A – The total mass of flight crew, passengers, baggage, cargo and usable fuel
B – The total mass of crew and passengers excluding any baggage or cargo
C – The total mass of passengers, baggage and cargo, including any nonrevenue load
D – The total mass of passengers, baggage, cargo and usable fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
37
...
With regard to the maximum Zero-Fuel Weight (MZFW)
...
When establishing the mass breakdown of an aeroplane, the empty mass is
defined as the sum of the:
A – basic mass plus variable equipment mass
B – basic mass, plus special equipment mass
C – standard empty mass plus specific equipment mass plus trapped fluids
plus unusable fuel mass
D – empty mass dry plus variable equipment mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
40
...
Take-off mass is described as:
A – The take-off mass subject to departure airfield limitations
B – The mass of an aeroplane including everything and everyone contained
within it at the start of the take-off run
C – DOM fuel but without traffic load
D – The lowest of performance limited and structural limited T
...
M
Ref: AIR: atpl, cpl
Ans: B
42
...
The chemical fluids used to charge the aircraft toilets are counted as:
A – part of the basic empty mass
B – part of the dry operating mass
C – part of the payload
D – part of the under load
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
44
...
The aircraft datum is a (i) reference point that is defined on or relative to the
aircraft about which the (ii) of any load locations are known
A – (i) movable (ii) moments
B – (i) variable (ii) moments
C – (i) fixed (ii) arms
D – (i) forward (ii) arms
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
46
...
The chemical fluids used to charge the aircraft toilets are counted as?
A – part of the basic empty mass
B – part of the variable load
C – part of the payload
D – part of the under load
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
48
...
The Basic Empty Mass of a helicopter is the mass of the helicopter without
crew …:
A – without specific equipments for the mission, without payload, with fuel on
board
B – without specific equipment for the mission, without payload, with the
unusable fuel and standard equipment
C – without payload, with specific equipment for the mission, without the
unusable fuel
D – without specific equipment for the mission, without payload, without
unusable fuel
Ref: HELI: atpl, cpl
Ans: B
50
...
In centre of gravity calculations the moment arm is:
A – The vertical distance from the datum to the centre of gravity of the
helicopter or of an items placed in the helicopter
B – The horizontal distance between the fully loaded helicopter’s centre of
gravity and the centre of gravity of an individual item in the helicopter
C – The vertical distance between the fully loaded helicopter’s centre of
gravity and the centre of gravity of an individual item in the helicopter
D – The horizontal distance from the datum to the centre of gravity of the
helicopter, or to an item placed in the helicopter
Ref: HELI: atpl, cpl
Ans: D
52
...
The Dry Operating Mass of a helicopter:
A – includes fuel and passengers baggage and cargo
B – includes passengers and cargo
C – is the total mass of the helicopter ready for a specific type of operation
D – includes unusable fuel and reserve fuel
Ref: HELI: atpl, cpl
Ans: C
54
...
The Dry Operating Mass of a helicopter is the sum of the following:
A – Basic Empty Mass + crew + traffic load + taxi fuel
B – Basic Empty Mass + crew + taxi fuel
C – Basic Empty Mass + crew + traffic load
D – Basic Empty mass = crew + operating items
Ref: HELI: atpl, cpl
Ans: D
56
...
The maximum mass to which a helicopter may be loaded, prior to engine start,
is:
A – maximum structural taxi mass
B – maximum regulated taxi mass
C – maximum structural take-off mass
D – maximum regulated take-off mass
Ref: HELI: atpl, cpl
Ans: A
58
...
It is tabulated in the flight
manual
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
59
...
The maximum zero-fuel mass:
1
...
3
...
is a regulatory limitation
is calculated for a maximum load factor of +3
...
is defined on the assumption that fuel is consumed from the inner wing
tanks first
A – 1, 2, 3
B – 2, 3, 5
C – 1, 3, 5
D – 2, 3, 4
Ref: AIR: atpl, cpl
Ans: C
61
...
The reference about which centre of gravity moments are taken is the:
A – Chord line
B – Centre of mass
C – Centre of pressure
D – Datum
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
63
...
The Traffic Load is defined as:
A – The total mass of passengers and their baggage plus any cargo
B – The total mass of the helicopter prior to take-off
C – The total mass of the helicopter prior to take-off minus usable fuel
D – The total mass of flight crew, passengers and usable fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
65
...
Which of the following corresponds to Zero Fuel Mass?
A – Operating mass plus luggage of passengers and cargo
B – Operating mass plus passengers and cargo
C – The take-off mass of an aircraft minus all usable fuel
D – Take-off mass minus fuel to destination and alternate
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
67
...
The Zero Fuel Mass is the mass of the helicopter:
A – Excluding usable and unusable fuel
B – Including unusable and reserve fuel
C – When weighed for issue or renewal of its weight schedule and excludes
crew, traffic load, usable and unusable fuel
D – Excluding usable fuel
Ref: HELI: atpl, cpl
Ans: D
69
...
To calculate the allowable take-off mass, the factors to be taken into account
include:
A – the sum of the Maximum Landing Mass and the trip fuel
B – the sum of the Maximum Landing Mass and the fuel on board at take-off
C – the sum of the Maximum Zero Fuel Mass and the trip fuel
D – the Maximum Take-off Mass minus the trip fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
71
...
Variable load includes:
A – mass of all persons and items of load, including fuel and other
consumable fluids
B – mass of all passengers, crew and their baggage, less fuel and consumable
fluids
C – mass of crew, their baggage, plus removable units of equipment
D – mass of passengers, crew and their baggage, plus removable equipment
and consumable fuel and fluids
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
73
...
The take-off fuel of an aircraft is:
A – the ZFM minus the traffic load
B – DOM minus variable load
C – TOM minus ZFM
D – Traffic load plus take-off fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
031-02-02 Mass Limits
1
...
9)
...
(Refer to CAP 696 – Figure 4
...
Referring to the loading manual for the
transport aeroplane, the maximum running load for the aft section of the forward
lower deck cargo compartment is:
A – 13
...
12 kg per inch
C – 14
...
18 kg per inch
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
3
...
9)
...
5 inches is 2059 Lbs
B – 835
...
5 inches is 4541 kg
D – 835
...
Considering only structural limitation, on long distance flights (at the aeroplane
maximum range), the traffic load is normally limited by:
A – The maximum zero fuel mass plus the take-off mass
B – The maximum zero fuel mass
C – The maximum take-off mass
D – The maximum landing mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
5
...
Which of the following statements is correct?
A – The Maximum Zero Fuel Mass ensures that the centre of gravity remains
within limits after the uplift of fuel
B – The Maximum Landing Mass of an aeroplane is restricted by structural
limitations, performance limitations and the strength of the runway
C – The Maximum Take-off Mass is equal to the maximum mass when
leaving the ramp
D – The Basic Empty Mass is equal to the mass of the aeroplane excluding
traffic load and usable fuel but including the crew
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
7
...
If the maximum structural landing mass is exceeded:
A – the aircraft will be unable to get airborne
B – the undercarriage could collapse on landing
C – no damage will occur providing the aircraft is within the regulated landing
mass
D – no damage will occur providing the aircraft is within the performance
limited landing mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
9
...
9)
...
Considering only structural limitations, on very short legs with minimum takeoff fuel, the traffic load is normally limited by:
A – Maximum landing mass
B – Maximum zero fuel mass
C – Maximum take-off mass
D – Actual landing mass
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
11
...
The take off mass
is likely to be limited by:
A – MZFM
B – Obstacle limited mass
C – Maximum certified take-off mass
D – Climb limited mass
Ref: AIR: atpl, cpl
Ans: D
12
...
It is tabulated in the
Flight Manual
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
13
...
(For this Question use CAP 696 – Figure 4
...
10)
...
A) for the forward hold centroid is:
A – 257 inches
B – 367
...
5 inches
D – 421
...
(Refer to figure 031_9
...
Referring to the Pilot’s Flight Manual for the
transport helicopter TETH-1, the maximum load for the aft-cargo bay in
section C is:
A – 400 daN/m2
B – 250 daN
C – 115 daN
D – 75 lbs/ft2
Ref: HELI: atpl, cpl
Ans: B
16
...
(Refer to figure 031_9
...
Referring to the Pilot’s Flight Manual for the
transport helicopter TETH1, the maximum load for the aft cargo bay in section
A is:
A – 115 daN
B – 195 daN/m2
C – 55 daN
D – 120 lb
Ref: HELI: atpl, cpl
Ans: A
17
...
(Refer to figure 031_9
...
From the Pilot’s Flight Manual of the
transport
helicopter TETH1, the cabin floor has a maximum load carrying capacity
(maximum floor load) of:
A – 115 daN
B – 1500 daN
C – 195 daN/m2
D – 1500 daN/m2
Ref: HELI: atpl, cpl
Ans: D
18
...
(Refer to figure 031_9
...
Referring to the Pilot’s Flight Manual for the
transport helicopter TETH1, the maximum load for the aft cargo bay in section
B is:
A – 550 lb
B – 55 daN
C – 75 daN/m2
D – 115 daN
Ref: HELI: atpl, cpl
Ans: B
19
...
What are the criteria for correct loading of a helicopter?
A – Adherence to the maximum mass limitations
B – Correct distribution of the useful load and adherence to the maximum
mass limitations
C – Maximum allowable baggage mass in the aft cargo compartment
D – Correct distribution of the useful load
Ref: HELI: atpl, cpl
Ans: B
21
...
9878
...
9)
...
(Refer to CAP 696 – Figure 4
...
Referring to the loading manual for the
890
...
9)
...
Considering only structural limitation, on long distance flights (at the aeroplane
910
...
Which of the following statements is correct?
914
...
If the maximum structural landing mass is exceeded:
921
...
9)
...
Considering only structural limitations, on very short legs with minimum take936
...
The maximum certificated take-off mass is:
950
...
(For this Question use CAP 696 – Figure 4
...
10)
...
(Refer to figure 031_9
...
Referring to the Pilot’s Flight Manual for the
18085
...
6)
...
(Refer to figure 031_9
...
From the Pilot’s Flight Manual of the transport
18087
...
6)
...
Considering only structural limitations, on long distance flights (at the
18177
...
Using the data for the MRJT, what is the maximum
compartment load for the area between BA 286 and 343:
A – 762 lbs
B – 314
...
47 kg
Ref: AIR: atpl, cpl
Ans: C
031-02-03 Mass calculations
1
...
When determining the mass of fuel/oil and the value of the SG is not known, the
value to use is:
A – determined by the operator
B – set out in JAR OPS – 1 Section 1
C – determined by the aviation authority
D – determined by the pilot
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
3
...
An aeroplane is performance limited to a landing mass of 54230 kg
...
If the take-off mass is
64280 kg the useful load is:
A – 12200 kg
B – 17080 kg
C – 29280 kg
D – 10080 kg
The useful load=tarfic load+ take of fuel
Take of fuel=ZFM-TOM
Take of fuel= 64280-52080=12200
Traffic load=ZFM-DOM
Traffic load=52080-35000= 17080
Useful load=17080+12200=29280Ans
Ref: AIR: atpl, cpl
Ans: C
5
...
On arrival at
destination a straight in approach and immediate landing clearance is given
...
A revenue flight is to be made by a jet transport
...
e
...
This is the only traffic load that will not exceed either the
MTOW, MLW or the MZFW limitations
Ref: AIR: atpl, cpl; HELI: atpl, cpl
7
...
14)
Aeroplane Dry Operating mass
85000 kg
Performance limited take-off mass 127000 kg
Performance limited landing mass 98500 kg
Maximum zero fuel mass
89800 kg
Fuel requirements for flight:
Trip fuel 29300 kg
Contingency and final reserve fuel 3600 kg
Alternate fuel 2800 kg
The maximum traffic load that can be carried on this flight is:
MTOM
Less DOM
Less Fuel
127000
(85000)
(35700)
6300
MLM
MZFM
98500
(85000)
(6400)
7100
89800
(85000)
4800
Maximum traffic load is the lower of the three calculated values i
...
4800 kg
...
Given:
Maximum structural take-off mass = 146900 kg
Maximum structural landing mass = 93800 kg
Maximum zero fuel mass = 86400 kg
Trip fuel = 27500 kg
Block fuel = 35500 kg
Engine starting and taxi fuel = 1000 kg
The maximum take-off mass is equal to:
A – 120300 kg
B – 121300 kg
C – 113900 kg
D – 120900 kg
MTOM= ZFM +TAKE OF FUEL
MTOM=
86400+34500=120900 ANS
MTOM
Less DOM
Less Fuel
127000
(85000)
(35700)
6300
MLM
MZFM
98500
(85000)
(6400)
7100
89800
(85000)
4800
Maximum traffic load is the lower of the three calculated values i
...
4800 kg
...
Given:
Dry operating mass = 38000 kg
Maximum structural take-off mass = 72000 kg
Maximum landing mass = 65000 kg
Maximum zero fuel mass = 61000 kg
Fuel burn = 8000 kg
Take-off Fuel = 10300 kg
The maximum allowed take-off mass and payload are respectively:
A – 73000 kg and 27000 kg
B – 71300 kg and 25300 kg
C – 73000 kg and 24700 kg
D – 71300 kg and 23000 kg
Allowed take-off mass=ZFM+TAKE OFF FUEL
=61000+10300=71300 Ans
MTOM
Less DOM
Less Fuel
72000
(38000)
(10300)
23700
MLM
65000
(38000)
(2300)
24700
MZFM
61000
(38000)
23000 Ans
Maximum traffic load is the lower of the three calculated values i
...
23000 kg
...
The empty mass of an aeroplane, as given in the weighing schedule, is 61300
kg
...
If the takeoff mass is 132000 kg (including a usable fuel quantity of 43800 kg) the useful load is:
A – 26900 kg
B – 70700 kg
C – 29600 kg
D – 68400 kg
Useful load= TOM-DOM
DOM= basic empty mass+crew
61300+2300=63600
Useful load=132000-63600=68400 Ans
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
11
...
e
...
This is the only traffic load that will not exceed either the
MTOW, MLW or the MZFW limitations
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
12
...
If the flight is not a
holiday charter, the mass value which may be used for an adult is:
A – 88 kg (male) 74 kg (female)
B – 76 kg
C – 84 kg (male) 76 kg (female)
D – 84 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
13
...
964
...
5 and 4
...
(Fuel density value 0
...
An aircraft basic empty mass is 3000 kg
...
Ramp fuel is 650 kg, the taxi fuel is 50 kg
...
e
...
This is the only traffic load that will not exceed either the
MTOW, MLW or the MZFW limitations
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
16
...
The basic empty mass of an aircraft is 30000 kg
...
A revenue flight is to be made by a jet transport
...
e
...
This is the only traffic load that will not exceed either the
MTOW, MLW or the MZFW limitations
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
19
...
4)
The medium range jet transport aeroplane is to operate a flight carrying the
maximum possible fuel load
...
Departure airfield performance limited take-off mass:
60400 kg
Landing airfield:
not performance limited
Dry Operating Mass:
34930 kg
Fuel required for flight:
Taxi fuel:
715 kg
Trip fuel:
Contingency and final reserve fuel:
Alternate fuel:
Additional reserve:
Traffic load for flight:
8600 kg
1700 kg
1500 kg
400 kg
11000 kg
A – 16080 kg
B – 15815 kg
C – 13650 kg
D – 14470 kg
Mass on fuel at start of take off=( DOM+TRAFFIC LOAD)-LIMITED TAKE
OFF MASS
Ref: AIR: atpl, cpl
Ans: D
20
...
During the preparation of a scheduled flight a group of
passengers present themselves at the check-in desk, it is apparent that even the lightest
of these exceeds the value of the declared standard mass
...
An aeroplane is to depart from an airfield where the performance limited takeoff mass is 89200 kg
...
e
...
This is the only traffic load that will not exceed either the
MTOW, MLW or the MZFW limitations
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
22
...
A twin-engine aeroplane is certified for a Max Structural TOM and a Max LM
of 58000 kg and 55000 kg respectively
...
(For this question use CAP 696 – Figure 4
...
The destination
airfield has a performance limited landing mass of 54500 kg
...
Loading data is as follows:
Taxi fuel:
350 kg
Trip fuel:
9250 kg
Contingency and final reserve fuel 1100 kg
Alternate fuel:
1000 kg
Traffic load:
18600 kg
Check the load and ensure that the flight may be operated without exceeding
any of the aeroplane limits
...
A – The flight may be safely operated with the stated traffic and fuel load
B – The flight is ‘zero fuel mass’ limited and the traffic load must be reduced
to 14170 kg
C – The flight is ‘landing mass’ limited and the traffic load must be reduced to
17500 kg
D – The flight may be safely operated with an additional 200 kg of traffic load
Ref: AIR: atpl, cpl
Ans: C
25
...
The maximum take-off mass
landing and zero fuel mass are identical at 3500 kg
...
The available mass of payload is:
A – 1500 kg
B – 950 kg
C – 1000 kg
D – 1450 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
26
...
9)
The centroid of the forward hold is:
A – halfway between stations 228 and station 500
B – 314
...
9 inches from the datum
D – 367
...
An aeroplane is to depart from an airfield at a take-off mass of 302550 kg
...
The Dry Operating Mass is 161450 kg
...
(Refer to CAP 696 – Figure 4
...
The flight is not a holiday charter
...
Given that:
Maximum structural take-off mass:
Maximum structural landing mass:
Actual zero fuel mass:
Trip fuel:
Taxi fuel:
Contingency fuel:
Alternate fuel:
Final reserve fuel:
146000 kg
93900 kg
86300 kg
27000 kg
1000 kg
1350 kg
2650 kg
3000 kg
Determine the actual take-off mass:
ZFM
Trip fuel
Contingency fuel:
Alternate fuel
Final reserve fuel
86300
27000
1350
2650
3000
120300 Ans
A – 120900 kg
B – 146000 kg
C – 120300 kg
D – 121300 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
30
...
9)
What is the balance arm, the maximum compartment load and the running
load for the most aft compartment of the forward cargo hold?
A – 421
...
12 kg per inch
B – 1046
...
18 kg per inch
C – 421
...
12 kg per inch
D – 1046
...
18 kg per inch
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
31
...
The nominal Dry Operating Mass is 60120 kg and the Maximum Zero Fuel Mass is
given as 72100 kg
...
The take-off mass of an aeroplane is 141000 kg
...
The traffic load is
12800 kg
...
Given are:
Maximum structural take-off mass:
Maximum structural landing mass:
Maximum zero fuel mass:
Taxi fuel:
Trip fuel:
72000 kg
56000 kg
48000 kg
800 kg
18000 kg
Contingency fuel:
Alternate fuel:
Final reserve fuel:
Determine the actual take-off mass:
ZFM
48000
Trip fuel
18000
Contingency
900
Alternate
700
Final reserve 2000
69600 Ans
A – 74000 kg
B – 69600 kg
C – 72000 kg
D – 70400 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
900 kg
700 kg
2000 kg
34
...
The following are the
aeroplane structural limits:
Maximum Ramp Mass:
69500 kg
Maximum Take Off Mass:
69300 kg
Maximum Landing Mass:
58900 kg
Maximum Zero Fuel Mass:
52740 kg
Take off and Landing mass are not performance limited
Dry Operating Mass:
34930 kg
Trip Fuel:
11500 kg
Taxi Fuel:
250 kg
Contingency & final reserve fuel:
1450 kg
Alternate Fuel:
1350 kg
The maximum traffic load that can be carried is:
Solve like page # 55 Q # 26
...
The crew of a transport aeroplane prepares a flight using the following data:
Block fuel:
Trip fuel:
Taxi fuel:
Maximum take-off mass:
Maximum landing mass:
Maximum zero fuel mass:
Dry operating mass:
40000 kg
29000 kg
800 kg
170000 kg
148500 kg
112500 kg
80400 kg
The maximum traffic load for this flight is:
Solve like page # 55 Q # 26
...
The following data applies to an aeroplane which is about to take off:
Certified maximum take-off mass: 141500 kg
Performance limited take-off mass: 137300 kg
Dry Operating Mass:
58400 kg
Crew and crew hand baggage mass:
640 kg
Crew baggage in hold:
110 kg
Fuel on board:
60700 kg
From this data calculate the mass of the useful load
...
(For this question use CAP 696 – Figure 4
...
Take-off mass is not
airfield limited
...
Determine the
maximum cargo load that may be carried without exceeding the limiting
aeroplane landing mass
...
The following data applies to a planned flight:
Dry Operating Mass:
Performance limited Take-off Mass:
Performance limited Landing Mass:
Maximum Zero Fuel Mass:
Fuel required at ramp:
Taxi fuel:
Trip fuel:
Contingency fuel:
Alternate fuel:
Holding fuel:
34900 kg
66300 kg
55200 kg
53070 kg
400 kg
8600 kg
430 kg
970 kg
900 kg
Traffic load:
16600 kg
Fuel costs at the departure airfield are such that it is decided to load the
maximum fuel quantity possible
...
Given:
Dry Operating Mass:
Maximum Take-off Mass:
Maximum Zero-Fuel Mass:
Maximum Landing Mass:
Trip Fuel:
Fuel quantity at brakes release:
The maximum traffic load is:
29800 kg
52400 kg
43100 kg
46700 kg
4000 kg
8000 kg
Solve like page # 55 Q # 26
...
The standard mass for a child is:
A – 38 kg for all flights
B – 35 kg for holiday charters and 38 kg for all other flights
C – 35 kg for all flights
D – 30 kg for holiday charters and 35 kg for all other flights
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
41
...
Operational items
(including crew standard mass of 1060 kg) are 2300 kg
...
The take-off mass of an aeroplane is 117000 kg, comprising a traffic load of
18000 kg and fuel of 46000 kg
...
A flight has been made from London to Valencia carrying minimum fuel and
maximum traffic load
...
79 kg/l
...
Dry Operating Mass:
34930 kg
Trip Fuel (Valencia to London)
5990 kg
Taxi Fuel:
250 kg
The maximum traffic load that can be carried from Valencia will be:
A – 14331 kg
B – 13240 kg
C – 16770 kg
D – 9830 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
44
...
If the standard mass for the crew is 545
kg the Dry Operating Mass is:
DOM= TOM-TARFFIC LOAD-FUEL
66700-14200-10500=42000 ANS
CREW IS ADDED IN DOM
...
Determine the Landing Mass for the following single engine aeroplane
...
Determine the Zero Fuel Mass for the following single engine aeroplane
...
(Refer to CAP 696 – Figure 3
...
5 inches
160 lbs
200 lbs
290 lbs
110 lbs
100 lbs
50 lbs
100 US Gal
55 US Gal
3 US Gal
6 lbs/US Gal
A – 4720
B – 4120
C – 4390
D – 4372
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
48
...
In determining the Dry Operating Mass of an aeroplane it is common practice
to use standard mass values for crew
...
These do not include a hand
baggage allowance
B – flight crew 85 kg, cabin crew 75 kg each
...
These
include an allowance for hand baggage
D – flight crew (male) 88 kg (female) 75 kg, cabin crew 75 kg each
...
To calculate a usable take-off mass, the factors to be taken into account include:
A – Maximum landing mass augmented by fuel on board at take-off
B – Maximum landing mass augmented by the fuel burn
C – Maximum zero fuel mass augmented by the fuel burn
D – Maximum take-off mass decreased by the fuel burn
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
51
...
Fuel remaining at landing is 10300 kg
...
Given the following:
Maximum structural take-off mass:
Maximum structural landing mass:
Maximum zero fuel mass:
Taxi fuel:
Contingency fuel:
Alternate fuel:
Final reserve fuel:
Trip fuel:
48000 kg
44000 kg
36000 kg
600 kg
900 kg
800 kg
1100 kg
9000 kg
Determine the actual take-off mass:
A – 48000 kg
B – 47800 kg
C – 48400 kg
D – 53000 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
53
...
An aeroplane develops a serious technical problem shortly after take-off and
has to return to its departure airfield
...
How much fuel must be dumped?
A – Sufficient to reduce the mass to the zero fuel mass
B – The pilot calculates the amount of fuel to jettison to reduce the mass to a
safe level at, or below the Regulated Landing Mass
C – The fuel system automatically stops the jettison at the Regulated Landing
Mass
D – As much as the pilot feels is just insufficient to land safely
Ref: AIR: atpl, cpl
Ans: B
55
...
If the standard mass for the crew is 190 kg
the dry operating mass is?
A – 5290 kg
B – 5480 kg
C – 8410 kg
D – 6710 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
56
...
The responsibility for determination of the mass of OPERATING MASSES
and CREW MEMBERS included within the Dry Operating Mass lies with:
A – the commander
B – the authority of the state of registration
C – the person compiling the weighing schedule
D – the operator
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
58
...
(Refer to CAP 696 figure 4-14)
The following data relates to a planned flight of an aeroplane:
Dry Operational mass:
60520 kg
Performance limited take-off mass: 72250 kg
Performance limited landing mass: 72230 kg
Maximum Zero Fuel mass:
67530 kg
Fuel on board at take-off
Trip fuel:
Contingency and final reserve fuel
Alternate fuel:
12500 kg
2300 kg
1700 kg
Using this data, as appropriate, calculate the maximum traffic load that can be
carried
...
(Refer to figure 031_L401)
From the data contained in the attached appendix, the maximum allowable
take-off mass and traffic load is respectively:
A – 66770 kg and 17320 kg
B – 60425 kg and 10975 kg
C – 61600 kg and 12150 kg
D – 68038 kg and 18588 kg
Ref: AIR: atpl, cpl
Ans: C
61
...
Complete the necessary
sections of the attached appendix and determine which of the answers given
below represents the maximum increase in the traffic load:
A – 7000 kg
B – 8268 kg
C – 650 kg
D – 1830 kg
Ref: AIR: atpl, cpl
Ans: D
62
...
A – 64200 kg
B – 63800 kg
C – 62650 kg
D – 54900 kg
Ref: AIR: atpl, cpl
Ans: C
63
...
A – 52900 kg with an underload of 4200 kg
B – 57100 kg with an underload of 3770 kg
C – 58500 kg with an overload of 3770 kg
D – 62000 kg with an underload of 3770 kg
Ref: AIR: atpl, cpl
Ans: B
64
...
A – 52000 kg with an underload of 1830 kg
B – 66770 kg with an overload of 1830 kg
C – 61600 kg with an underload of 1830 kg
D – 68038 kg with an overload of 1830 kg
Ref: AIR: atpl, cpl
Ans: C
65
...
45359237 lb
B – kg x 2
...
20462262 lb
D – None of the above
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
66
...
205
B – US gall x 4
...
264
D – US gall x 3
...
To convert 1 US gallon of AVGAS (100 LL) to lbs:
A – 1 USG
B – 1 USG
C – 1 USG
D – 1 USG
= 3
...
8 lbs
= 4 lbs
= 6 lbs
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
68
...
55 kg
B – 55
...
45 kg
D – 57
...
2588 USG of fuel has been loaded into an aircraft, what is the volume in
litres?
A – 979
...
66 L
C – 9796
...
58 L
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
70
...
When standard mass values are being used, infants occupying separate
passenger seats must be considered as:
A – adults
B – children
C – infants after being weighed
D – the same if below 2 years of age
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
72
...
Choose the correct statement as related to infants travel in aircraft:
A – An infant is a person between the ages of 0 years to 2 years
B – An infant is a person between the ages of 0 years to 3 years
C – An infant seated on an adults lap increases the pax mass by 35 kg
D – An infant must always be seated in its own seat and accounted for as 35
kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
74
...
An aircraft has an average fuel consumption of 7500 kg per hour at 480 kts
...
8, the start, run up + taxi allowance is 1200 kg and a minimum
reserve fuel of 10000 kg
...
2 nm & Endurance 7
...
0 hr
C – Range 3379
...
0 hr
D – Range 3360 nm & Endurance 7
...
The mass of 729 US Gallons of fuel at SG 0
...
The weight of 867 US Gallons of fuel (SG 0
...
If 1250 lbs of fuel at SG 0
...
The weight of 1292 litres of fuel (SG 0
...
If 567 kgs of fuel at SG 0
...
The mass of 16858 kg in lbs is?
A – 7822 lbs
B – 7645 lbs
C – 36330 lbs
D – 37166 lbs
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
81
...
5600 USG is equivalent to how many imperial gallons?
A – 6338 imp
B – 4366 imp
C – 4663 imp
D – 4848 imp
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
83
...
A helicopter is performance limited to a landing mass of 6=7550 kg
...
If the take-off mass is 7980 kg the useful load is:
A – 2780 kg
B – 2480 kg
C – 2000 kg
D – 480 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
85
...
Take-off fuel
(including Reserve Fuel of 680 kg) is 1750 kg
...
Considering a total mass of crew and operating items of 510 kg, the
permissible Traffic Load will be:
A – 730 kg
B – 1300 kg
C – 2310 kg
D – 1010 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
86
...
Take off Fuel
(including Reserve Fuel of 710 kg) is 1750 kg
...
Considering a total mass of crew and operating items of 420 kg, the
permissible Traffic Load will be:
A – 2590 kg
B – 1040 kg
C – 1130 kg
D – 1550 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
87
...
Take off Fuel
(including Reserve Fuel of 920 kg) is 1840 kg
...
Considering a total mass of crew and operating items of 440 kg, the
permissible Traffic Load will be:
A – 1820 kg
B – 1380 kg
C – 2740 kg
D – 920 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
88
...
Given:
-
The take-off mass of an aircraft is 8470 kg
Total fuel on board is 1600 kg including 450 kg reserve fuel and 29 kg of
unusable fuel
The traffic load is 770 kg
What is the Zero Fuel Mass?
A – 6420 kg
B – 6129 kg
C – 6899 kg
D – 6870 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
90
...
Given:
Dry Operating Mass:
5320 kg
Zero Fuel Mass:
6790 kg
Trip Fuel:
770 kg
Take-Off Fuel:
1310 kg
The Traffic Load is:
A – 1470 kg
B – 3080 kg
C – 1610 kg
D – 2940 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
92
...
Given:
Zero Fuel Mass:
Trip Fuel:
Block Fuel:
Taxi Fuel:
4770 kg
1040 kg
1960 kg
20 kg
The actual Take-Off Mass is equal to:
A – 5890 kg
B – 4970 kg
C – 6710 kg
D – 6730 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
94
...
Given:
Zero Fuel Mass:
Trip Fuel:
Block Fuel:
Taxi Fuel:
6660 kg
990 kg
1540 kg
25 kg
The actual Take-Off Mass is equal to:
A – 8175 kg
B – 8200 kg
C – 7210 kg
D – 8110 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
96
...
If the take-off mass is 8010 kg the useful load is:
A – 2960 kg
B – 1800 kg
C – 1160 kg
D – 3210 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
97
...
If the take-off mass is 7630 kg the useful load is:
A – 2670 kg
B – 2410 kg
C – 1590 kg
D – 820 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
98
...
The operational items
(including crew) is given as a mass of 320 kg
...
The basic empty mass of a helicopter is 5200 kg
...
If the take-off mass is 7840 kg
(including a usable fuel quantity of 1220 kg) the useful load is:
A – 2370 kg
B – 1150 kg
C – 1490 kg
D – 2640 kg
Ref: HELI: atpl, cpl
Ans: D
100
...
The operational items (including crew) is given as a mass of 530 kg
...
The maximum quantity of fuel that can be loaded into a helicopter’s tanks is
given as 1120 litres
...
79 the
mass of fuel which may be loaded is:
A – 1418 kg
B – 858 kg
C – 1011 kg
D – 885 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
102
...
If the fuel density (specific gravity) is given as 0
...
The maximum quantity of fuel that can be loaded into a helicopter’s tanks is
given as 600 US Gallons
...
79
the mass of fuel which may be loaded is:
A – 1794 kg
B – 2875 kg
C – 2155 kg
D – 3453 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
104
...
If the fuel density (specific gravity) is given as 0
...
The maximum quantity of fuel that can be loaded into an aircraft’s tanks is
given as 2200 litres
...
79 the
mass of fuel which may be loaded is:
A – 2785 kg
B – 2098 kg
C – 1798 kg
D – 1738 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
106
...
If the fuel density (specific gravity) is given as 0
...
The Take-Off Mass of a helicopter is 6700 kg
...
The traffic load is
900 kg
...
The take-off mass of a helicopter is 7840 kg which includes a traffic load of
870 kg and a usable fuel load of 960 kg
...
The Take-Off Mass of a helicopter is 8150 kg, comprising a Traffic Load of
990 kg and Take-Off Fuel of 2400 kg
...
What is the
Dry Operating Mass?
A – 6390 kg
B – 7160 kg
C – 4760 kg
D – 3130 kg
Ref: HELI: atpl, cpl
Ans: C
110
...
If the standard mass for the crew is
300 kg the Dry Operating Mass is:
A – 4580 kg
B – 6490 kg
C – 7910 kg
D – 4880 kg
Ref: HELI: atpl, cpl
Ans: D
111
...
The Trip Fuel is 980 kg
...
The Take-Off Mass of a helicopter is 8400 kg, comprising a traffic load of
1590 kg and take off fuel of 1840 kg
...
What is the
Dry Operating Mass?
A – 4970 kg
B – 3970 kg
C – 5970 kg
D – 6810 kg
Ref: HELI: atpl, cpl
Ans: A
113
...
If the standard mass for the crew is
270 kg the Dry Operating Mass is:
A – 5900 kg
B – 7050 kg
C – 7270 kg
D – 5630 kg
Ref: HELI: atpl, cpl
Ans: D
114
...
If the standard mass for the crew is
190 kg the Dry Operating Mass is:
A – 8410 kg
B – 5480 kg
C – 5290 kg
D – 6710 kg
Ref: HELI: atpl, cpl
Ans: B
115
...
Total fuel on board is 1900 kg
including 300 kg reserve fuel and 20 kg of unusable fuel
...
The zero fuel mass is:
A – 6780 kg
B – 6100 kg
C – 7120 kg
D – 7100 kg
Ref: HELI: atpl, cpl
Ans: C
116
...
What is the Dry Operating Mass?
A – 53000 kg
B – 64000 kg
C – 71000 kg
D – 99000 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
117
...
Total fuel on board is 63000
kg including 14000 kg reserve fuel and 1000 kg of unusable fuel
...
The Zero Fuel Mass is:
A – 65200 kg
B – 79000 kg
C – 78000 kg
D – 93000 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
118
...
If the standard mass for the
crew is 545 kg the Dry Operating Mass is:
A – 56200 kg
B – 41455 kg
C – 42545 kg
D – 42000 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
119
...
78 kg/l)
A – 133 kg
B – 133 daN
C – 170 kg
D – 218 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
120
...
81
...
Using the following, calculate the traffic mass:
PLTOM:
Taxi mass:
DOM:
Landing mass:
Operating mass:
Trip fuel:
PLLM:
MZFM:
68000 kg
67640 kg
38600 kg
60500 kg
50000 kg
7000 kg
64800 kg
59000 kg
A – 19260 kg
B – 17500 kg
C – 17460 kg
D – 28500 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
122
...
A MRJT is about to make a scheduled European flight, using the following
information calculate the most limiting TOM for the aircraft:
MZFM:
MLM:
MTOM:
PLLM:
PLTOM:
Take off fuel:
Trip fuel:
56000 kg
58600 kg
66800 kg
59000 kg
65000 kg
13400 kg
8100 kg
A – 65000 kg
B – 69400 kg
C – 66700 kg
D – 64100 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
124
...
Given the following information:
Basic Empty Mass:
Dry Operating Mass:
Zero Fuel Mass:
Traffic load:
Fuel:
The All Up Mass is:
A – 50900 kg
B – 53000 kg
C – 44700 kg
D – 61300 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
30400 kg
32500 kg
40800 kg
8300 kg
12200 kg
126
...
The fuel load on take-off is 380 kg and the
traffic load is 1150 kg
...
An aircraft has a Dry Operating Mass of 37400 kg
...
The Certificate of Airworthiness Maximum Structural Take-Off
Mass is 66000 kg, the Maximum Structural Landing Mass is 54000 kg and the
Maximum Zero Fuel Mass is 52000 kg
...
Allowing 500 kg for start, taxi and take-off and 12400 kg for trip fuel the
maximum allowed traffic load is:
A – 12300 kg
B – 13500 kg
C – 14600 kg
D – 13100 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
128
...
80 SG
...
78 SG, the volume of fuel
that can be loaded is:
A – 1840 litres
B – 2243 litres
C – 2359 litres
D – 2875 litres
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
129
...
The
Basic Empty Mass is 3210 lb and the flight is to be conducted with two pilots
whose masses are 180 lb and 210 lb respectively
...
The maximum Allowed Traffic Load is:
A – 680 lb
B – 514 lb
C – 870 lb
D – 565 lb
Ref: AIR: atpl, cpl
Ans: B
031-02-04 Effects of overloading
No questions in this sub-chapter
031-04
CENTRE OF GRAVITY (CG)
031-03-01 Definition of Centre of Gravity
1
...
The centre of gravity of a body is that point:
A – which is always used as datum when computing moments
B – where the sum of the moments from the external forces acting on the body
is equal to zero
C – where the sum of the external forces is equal to zero
D – through which the sum of the forces of all masses of the body is
considered to act
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
3
...
The centre of gravity of an aeroplane is at 25% of the Mean Aerodynamic
Chord
...
The datum for determining the CG has to be along the longitudinal axis:
A – between the nose and the tail
B – between the leading and trailing edge of the MAC
C – but does not have to be between the nose and the tail
D – at the fire wall
Ref: AIR: atpl, cpl
Ans: C
6
...
That point is known as:
A – the centre of gravity of the aeroplane
B – the focal point
C – the axis
D – the datum
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
7
...
The CG position is:
A – set by the pilot
B – set by the manufacturer
C – able to exist within a range
D – fixed
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
9
...
The centre of gravity of an aircraft:
A – is in a fixed position and is unaffected by aircraft loading
B – must be maintained in a fixed position by careful distribution of the load
C – can be allowed to move between defined limits
D – may only be moved if permitted by the regulating authority and endorsed
in the aircraft’s certificate of airworthiness
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
11
...
4” FWD of the wing leading edge at the inboard edge of the inboard
fuel tank
C – On the nose of the aeroplane
D – 78
...
(Refer to CAP 696 figure 2-1)
For the single engine piston/propeller aeroplane the FWD C of G limits are:
A – 74
...
00” – 80
...
4”
D – 37
...
The centre of gravity is that (i) on an aircraft through which the total (ii) is
considered to act vertically (iii)
...
In centre of gravity calculations the datum is:
A – The fixed reference about which moments are taken to calculate the
position of the centre of pressure
B – The fixed reference about which moments are taken to calculate the
position of the centre of gravity
C – The point through which the centre of gravity acts
D – The horizontal reference used to calculate the helicopter’s empty centre of
gravity
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
15
...
The true definition of the datum point is:
A – the centre of gravity related to the nose of the aircraft
B – a reference point for calculating the centre of pressure
C – a point in the fuselage which all the axes pass through
D – a reference point from where all measurements are taken for centre of
gravity calculation
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
031-03-02 Balance of forces and moments
1
...
The centre of gravity of an aeroplane is that point through which the total mass
of the aeroplane is said to act
...
The weight of an aeroplane, which is in level non-accelerated flight, is said to
act:
A – always along the vertical axis of the aeroplane
B – vertically through the centre of pressure
C – vertically through the datum point
D – vertically through the centre of gravity
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
4
...
Which of the following is unlikely to have any effect on the position of the
centre of gravity on an aeroplane in flight?
A – Lowering the landing gear
B – Changing the tailplane (horizontal stabiliser) incidence angle
C – Movement of cabin attendants going about their normal duties
D – Normal consumption of fuel for a swept wing aeroplane
Ref: AIR: atpl, cpl
Ans: B
6
...
13 units
B – It moves AFT by 0
...
3 units
D – It moves AFT by 0
...
A loaded aircraft weighs 4200 lb with a C of G of 9 inches AFT of the datum
...
The
new C of G position is:
A – 6
...
0 inches AFT
C – 6
...
0 inches FWD
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
8
...
Does this affect the CG?
A – No, the position of the CG would remain the same
B – Yes, but the CG movement could not be calculated
C – Yes, the CG would move aft
D – Yes, the CG would move forward
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
9
...
(Refer to figure 031_8-5)
For the following see-saw to be in balance:
A – Fb = A x Fa/B
B – Fb = A + Fa/B
C – Fb = A x B/Fa
D – Fb = B x Fa/A
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
11
...
(refer to figure 031_8-7)
For the following boom to be in balance:
A – B + Fa x A/Fb
B – B + Fb x A/Fa
C – B + -(Fa x A/Fb)
D – B + Fb + A/Fa
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
13
...
What centre of gravity movement may be expected on gear retraction?
A – CG moves forward
B – CG moves rearward
C – no significant change to CG position
D – CG moves far rearward
Ref: AIR: atpl, cpl
Ans: D
031-03-03 Basic calculations of CG
1
...
The moment about the datum is:
A – 343000 Nm
B – 1
...
Which one of the following is correct?
A – Arm = Force/Moment
B – Arm = Moment/Force
C – Moment = Force/Arm
D – Arm = Force x Moment
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
3
...
If all the moments are positive when calculating mass (weight) and balance,
the position of the datum would be at the:
A – trailing edge of the wing
B – main wheels centreline
C – nose, or forward of the aircraft
D – centre line of the nose or tail wheel depending on the aircraft type
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
5
...
(Refer to CAP 696 figure 3-2)
From data sheet attached select the volume of the fuel allowance for start, run
up and taxi as per the worked example
A – 3
...
8 Imp gallons
C – 3
...
8 US pints
Ref: AIR: atpl, cpl
Ans: A
7
...
A load placed forward of the datum:
A – Has a negative arm and therefore generates a negative moment
B – Has a negative arm and therefore generates a negative mass and moment
C – Has a positive arm and therefore generates a positive mass and moment
D – Has a positive arm and therefore generates a positive moment
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
9
...
Max floor loading = 750 kg per m2
...
What is the minimum pallet size?
A – 30 cm x 200 cm
B – 40 cm x 300 cm
C – 40 cm x 200 cm
D – 30 cm x 300 cm
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
2
...
(For this question use CAP 696 – Figure 4
...
0% MAC aft limit 26
...
0% MAC aft limit 27
...
6% MAC aft limit 27
...
4% MAC aft limit 27
...
(For this question use CAP 696 – Figure 4
...
The range of safe CG
positions, as determined from the appropriate graph in the loading manual, is:
A – Forward limit 8
...
0% MAC
B – Forward limit 7
...
0% MAC
C – Forward limit 7
...
8% MAC
D – Forward limit 8
...
8% MAC
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
3
...
11)
The aeroplane has a mass of 61000 kg in the cruise
...
7% aft limit 25
...
0% aft limit 27
...
6% aft limit 26
...
3% aft limit 26
...
(For this question use CAP 696 – Figure 4
...
At this mass the range of
safe CG positions, as determined from the appropriate graph in the loading
manual, is:
A – Forward limit 9
...
1% MAC
B – Forward limit 8
...
2% MAC
C – Forward limit 8
...
5% MAC
D – Forward limit 8
...
1% MAC
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
5
...
The datum used for balance calculations is:
A – chosen on the longitudinal axis of the aeroplane, and necessarily situated
between the nose and the tail of the aircraft
B – chosen on the longitudinal axis of the aeroplane, but not necessarily
between the nose and the tail of the aircraft
C – chosen on the longitudinal axis of the aircraft and necessarily situated
between the leading edge and trailing edge of the wing
D – chosen on the longitudinal axis of the aircraft, and always at the fire-wall
level
Ref: AIR: atpl, cpl
Ans: B
7
...
6 m
C – 625
...
6 in
Ref: AIR: atpl, cpl
Ans: C
8
...
0 inches
B - +79
...
5 inches
D - +80
...
(Refer to CAP 696 Figures 4-7 & 4-8)
From the data sheet for a medium range twinjet determine the moment effect
of 20 passengers without hand baggage located in zon E:
A – 108780 kg force inches
B – 1181040 kg force inches
C – 1305360 force inches
D – 1212120 kg force inches
Ref: AIR: atpl, cpl
Ans: D
10
...
52m, aft limit 4
...
40m, aft limit 4
...
47m, aft limit 4
...
50m, aft limit 4
...
(Refer to figure 031_9-5)
The helicopter has a mass of 8000 kg in the cruise
...
52 m, aft limit 4
...
52 m, aft limit 4
...
47 m, aft limit 4
...
44 m, aft limit 4
...
(Refer to figure 031_9-5)
The helicopter has a landing mass of 7500 kg
...
40m, aft limit 4
...
50m, aft limit 4
...
40m, aft limit 4
...
44m, aft limit 4
...
(Refer to figure 031_9-5)
The helicopter has a Take-Off Mass of 7000 kg
...
40m, aft limit 4
...
52m, aft limit 4
...
40m, aft limit 4
...
52m, aft limit 4
...
(Refer to figure 031_9-8)
Where has the longitudinal reference (datum line) been defined on the single
engine piston helicopter SEPH1?
A – 100 inches forward of main rotor centreline
B – At the centreline of the helicopter through the main rotor
C – The longitudinal reference has not been defined
D – At the centre of gravity
Ref: HELI: atpl, cpl
Ans: A
15
...
147 inches
C – at 100
...
1 inches
Ref: HELI: atpl, cpl
Ans: C
16
...
67m forward of the main rotor centre
Ref: HELI: atpl, cpl
Ans: D
17
...
The longitudinal centre of gravity datum (helicopter):
A – Must be located aft of the main rotor mast
B – Must be located in line with the main rotor mast
C – Can be located anywhere
D – Must be located forward of the main rotor mast
Ref: HELI: atpl, cpl
Ans: C
19
...
The longitudinal reference (datum line) for determining the moment arm is
defined:
A – by the manufacturer of the helicopter
B – by the operator of the helicopter
C – by the National Aviation Authority
D – by the pilot in command of the helicopter
Ref: HELI: atpl, cpl
Ans: A
21
...
The BEM of an aircraft is the basic/empty weight of an aircraft without crew
and items of removable equipment, it is:
A – Found in the aircraft manual and includes unusable fuel and liquids in
closed systems
B – Found in the weighing schedule at the last date of weighing
C – Found in the loading manual and includes unusable fuel
D – Found in the Operations Manual and includes engine oil
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
23
...
(Refer to figure 031_4-11)
With reference to the MRJT, what are the limits for the CG as a percentage of
the aircraft’s MAC at TOM of 57500 kg?
A – 88
...
5%
B – 9% to 25%
C – 8% to 26
...
(Refer to figure 031_4-11)
What are the limits for the CG as a percentage of the aircraft’s MAC at its
maximum taxi mass?
A – 88
...
5%
B – 9
...
5% to 27%
D – 12% to 20%
Ref: AIR: atpl, cpl
Ans: B
031-04-02 Aircraft weighing
1
...
Who is responsible for
deriving the Dry Operational Mass from the weighed mass by the addition of the
‘operational items’?
A – The Operator
B – The appropriate Aviation Authority
C – The aeroplane manufacturer or supplier
D – The commander of the aeroplane
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
2
...
An aeroplane may be weighed:
A – in an area of the airfield set aside for maintenance
B – in a quiet parking area clear of the normal manoeuvring area
C – in an enclosed, non-air conditioned, hangar
D – at a specified ‘weighing location’ on the airfield
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
4
...
Where an operator uses
fleet masses and provided that changes have been correctly documented, this interval
is:
A – 4 years for each aeroplane
B – 9 years for each aeroplane
C – whenever a major modification is carried out
D – whenever the Certificate of Airworthiness is renewed
Ref: AIR: atpl, cpl
Ans: B
5
...
An aeroplane with a two wheel nose gear and four main wheels rests on the
ground with a single nose wheel load of 500 kg and a single main wheel load of 6000
kg
...
How far
is the centre of gravity in front of the main wheels?
A – 40 cm
B – 25 cm
C – 4 meters
D – 41
...
When preparing to carry out the weighing procedure on an aeroplane, which of
the following is not required?
A – drain all usable fuel
B – drain all engine tank oil
C – drain all chemical toilet fluid tanks
D – removable passenger services equipment to be offloaded
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
8
...
57 cm aft of datum
B – 32
...
57 cm forward of datum
D – 32
...
An operator has a fleet of 43 aircraft, how many aircraft must be weighed at
the same time to maintain the fleet value?
A–6
B–7
C–8
D–9
Ref: AIR: atpl, cpl
Ans: D
10
...
The interval between 2 fleet mass evaluations must not exceed:
A – 48 months
B – 36 months
C – 24 months
D – 12 months
Ref: AIR: atpl, cpl
Ans: A
12
...
The distance between the nose wheels and the main wheels is 10
meters
...
The weights measured at the landing gear of an aircraft are as follows:
Nose wheel
(55 inches aft of datum):
Right main wheel
(121 inches aft of datum):
Left main wheel
(121 inches aft of datum):
475 lbs
1046 lbs
1040 lbs
The C of G of the aircraft is:
A – 104
...
4 in
C – 108
...
The following results were obtained after weighing a helicopter:
Front point:
Right rear point:
Left rear point:
220 kg
500 kg
480 kg
The helicopter datum is 3
...
The front point is
located 2
...
50 m
aft of the rotor axis
...
36 m
B – 0
...
44 m
D – 1
...
The following results were obtained after weighing a helicopter:
Mass at front point:
300 kg
Mass at right rear point:
1100 kg
Mass at left rear point: 950 kg
It is given that the front point is located 0
...
20m from this axis
...
After weighing a helicopter the following values are noted:
Forward point:
Aft right point:
Aft left point:
350 kg
995 kg
1205 kg
What is the longitudinal CG-position in relation to the datum situated 4m in
front of the rotor axis, knowing that the forward point is at 2
...
52 m
B – 4
...
21m
D – 4
...
An aeroplane is weighed and the following recordings are made:
Nose wheel assembly scale:
Left main wheel assembly scale:
Right main wheel assembly scale:
5330 kg
12370 kg
12480 kg
If the OPERATIONAL ITEMS amount to a mass of 1780 kg with a crew mass
of 545 kg, the empty mass, as entered in the weight schedule, is:
A – 32505 kg
B – 30180 kg
C – 28400 kg
D – 31950 kg
Ref: AIR: atpl, cpl
Ans: B
18
...
At the re-weighing of an aircraft, who is responsible for establishing the
DOM?
A – operator
B – commander
C – manufacturer
D – the Authority
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
20
...
(Refer to figure 031_8-10)
What is the centre of gravity position of the aeroplane in the diagram, given:
Left main:
Right main:
Nose:
1620 kg
1632 kg
640 kg
A – 24
...
1” FWD of the Datum
C – 24
...
1” AFT of the Datum
Ref: AIR: atpl, cpl
Ans: A
22
...
31 m aft of datum
B – 2
...
2m aft of datum
D – 3
...
The maximum aircraft mass excluding all usable fuel is:
A – fixed and listed in the Aircraft Operating Manual
B – variable and is set by the payload for the trip
C – fixed by the physical size of the fuselage and cargo holds
D – variable and depends on the actual fuel load for the trip
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
2
...
The maximum certificated taxi (or ramp) mass is that mass to which an
aeroplane may be loaded prior to engine start, it is:
A – a fixed value which is listed in the Flight Manual
B – a value which varies with airfield temperature and altitude
...
Standard corrections are
listed in the Flight Manual
D – a value which is only affected by the outside air temperature
...
The Maximum Zero Fuel Mass is the mass of the aeroplane with no usable fuel
on board
...
It is a structural limit
B – governed by the requirements of the centre of gravity limits and the
structural limits of the aeroplane
C – tabulated in the Flight Manual against arguments of airfield elevation and
temperature
D – governed by the traffic load to be carried
...
In relation to an aeroplane, the term BASIC EMPTY MASS includes the mass
of the aeroplane structure complete with its power plants, systems, furnishings and
other items of equipment considered to be an integral part of the particular aeroplane
configuration
...
It is entered in the loading manifest
B – found in the latest version of the weighing schedule as corrected to allow
for modifications
C – found in the flight manual and is inclusive of unusable fuel plus fluids
contained in closed systems
D – printed in the loading manual and includes unusable fuel
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
6
...
(For this Question use CAP 696 – Figures 4
...
2)
For the medium range twin jet the datum point is located:
A – on the nose of the aeroplane
B – 540 cm forward on the front spar
C – 540 inches forward of the front spar
D – at the leading edge of the Mean Aerodynamic Chord (MAC)
Ref: AIR: atpl, cpl
Ans: C
8
...
It differs from Dry Operating Mass by the value of
the “useful load”
B – the loading manifest
...
If changes occur, due to modifications, the
aeroplane must be re-weighed always
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
9
...
8 inches aft of the datum
B – 85
...
4 inches aft of the datum
D – 25
...
(Refer to CAP 696 figure 4-6)
From the data sheet for a medium range twin jet determine the amount of
unusable fuel in the aircraft:
A – 17
...
1 US gallons at 52 kg
C – 17
...
0 US gallons at 52 kg
Ref: AIR: atpl, cpl
Ans: B
11
...
(Refer to CAP 696 figures 4-1 & 4-2)
From the medium range twin jet data sheet give the distance of body station
727F from the front spar:
A - +540 inches
B - +313 inches
C - +287 inches
D - +187 inches
Ref: AIR: atpl, cpl
Ans: B
13
...
(Refer to figure 031_9-7)
For the transport helicopter TETH1, from the Pilot’s Flight Manual, determine
the maximum total volume of fuel which can be loaded into the Standard tank
version:
A – 8240 1
B – 2121 1
C – 2367 1
D – 1868 1
Ref: HELI: atpl, cpl
Ans: C
15
...
95m
...
Is it allowed to fly under otherwise identical conditions
if a pilot is weighing 10 kg less as given?
A – No, the new centre of gravity is located 1 cm aft of the aft limit (thus
outside the allowable range)
B – Yes, the reduced mass can only have a positive effect
C – Yes, the new centre of gravity is located 1 cm forward of the aft limit
(thus within the allowable range)
D – Yes, the new centre of gravity is now located more forward within the
allowable range
Ref: HELI: atpl, cpl
Ans: A
16
...
97m
...
Is it allowed to fly under otherwise identical conditions
if a pilot is weighing 10 kg less as given?
A – Yes, the new centre of gravity is located 1 cm forward of the aft limit,
thus still within the allowable range
B – No, the new centre of gravity is located 1 cm aft of the aft limit, thus
outside the allowable range
C – Yes, the reduced mass can only have a positive effect
D – Yes, the new centre of gravity is now located more forward within the
allowable range
Ref: HELI: atpl, cpl
Ans: A
17
...
945 m
...
Is it allowed to fly under otherwise identical conditions
if a pilot is weighing 10 kg more as given?
A – Yes, the increased mass can only have a positive effect
B – Yes, the new centre of gravity is now located more backward within the
allowable range
C – Yes, the new centre of gravity is located 1 cm forward of the aft limit, thus
within the allowable range
D – No, the new centre of gravity is located 1 cm aft of the aft limit, thus
outside the allowable range
Ref: HELI: atpl, cpl
Ans: C
18
...
It differs from Dry Operating Mass by the value of
the useful load
D – the loading manifest
...
The forward centre-of-gravity limit of a helicopter is located at 2
...
The
maximum allowable mass has been reached
...
53m
...
What must be done before the flight?
A – Shift something of load items to a more rear position and compute again
B – Load something aft of the centre-of-gravity so that the helicopter regains
the allowable centre-of-gravity range
C – Take off
D – Unload something aft of the centre of gravity and compute again
Ref: HELI: atpl, cpl
Ans: A
20
...
Its value is:
A – found in the latest version of the weighing schedule as corrected to allow
for modifications
B – inclusive of an allowance for crew, crew baggage and other operating
items, it is entered in the loading manifest
C – found in the flight manual and is inclusive of usable fuel plus fluids
contained in closed systems
D – printed in the loading manual and includes usable fuel
Ref: HELI: atpl, cpl
Ans: A
21
...
1
B - -7
...
8
D - -8
...
At a given mass the CG position is at 15% MAC
...
6 inches aft of the datum and the MAC is given as 134
...
78 inches aft of datum
B – 20
...
43 inches aft of datum
D – 228
...
(For this question use CAP 696 – Figure 3
...
in) at landing in the following conditions:
Basic empty mass:
3210 lbs
One pilot:
160 lbs
Front seat passenger:
200 lbs
Centre seat passengers:
290 lbs (total)
One passenger rear seat:
110 lbs
Baggage in zone 1:
100 lbs
Baggage in zone 4:
50 lbs
Block fuel:
100 US Gal
Trip fuel:
55 US Gal
Fuel for start up and taxi (included in block fuel): 3
US Gal
Fuel density: 6 lbs/US Gal
Total moment at take-off: 432226 lbs
...
What is the CG as a percentage MAC of the fully loaded aircraft below?
BEM
Arm
CG
MAC
Item Balance arm:
Front seats
Rear seats
Fuel SG
Fuel
Fuel arm
Rear seats Empty
Pilot
Passenger
12000 kg
3m
25% MAC
2m
2
...
74
410 litres
2
...
The loaded centre of gravity (cg) of an aeroplane is 713 mm aft of datum
...
The cg
expressed as % MAC (mean aerodynamic chord) is:
A – 16%
B – 41%
C – 60%
D – 10%
Ref: AIR: atpl, cpl
Ans: A
5
...
4)
With respect to multi-engine piston powered aeroplane, determine the block
fuel moment (lbs
...
5 inch
160 lbs
200 lbs
290 lbs (total)
110 lbs
100 lbs
50 lbs
100 US Gal
55 US Gal
3 US Gal
6 lbs/US Gal
A – 433 906
B – 56 160
C – 30 886
D – 9 360
Ref: AIR: atpl, cpl
Ans: B
6
...
35 cm aft datum
B – 56
...
16 cm aft datum
D – 53
...
Calculate the centre of gravity in % MAC (mean aerodynamic chord) with
following data:
Distance datum – centre of gravity:
Distance datum – leading edge:
Length of MAC:
12
...
63m
8m
A – 23
...
4% MAC
C – 47
...
3% MAC
Ref: AIR: atpl, cpl
Ans: D
8
...
1 – 2
...
in/100) in the following conditions:
Basic Empty Mass:
2415 lbs
Arm at Basic Empty Mass:
77
...
8
C – 2496
...
8
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
9
...
03%
B – 18
...
25%
D – 20
...
The mass and balance information gives:
Basic mass:
Basic balance arm:
1200 kg
3
...
The length of MAC is 2m
...
5m
3
...
5m
3
...
Fuel tanks contain
140 litres of petrol with a density of 0
...
The rear seats are not occupied
...
The position of the centre of gravity at take-off (as % MAC) is:
A – 29%
B – 22%
C – 34%
D – 17%
Ref: AIR: atpl, cpl
Ans: B
11
...
5 inches
...
6 inches aft of the datum
...
A – 85
...
6%
C – 18
...
5%
Ref: AIR: atpl, cpl
Ans: C
12
...
Given are the following information at take-off
STATION MASS (kg) / ARM (cm) / MOMENT (kgcm)
Basic Empty Condition
Crew
Freight 1
Freight 2
Fuel
Oil
12045
145
5455
410
6045
124
+30
-160
+200
-40
-8
+40
+361350
-23200
+1091000
-16400
-48360
+4960
Given that the flight time is 2 hours and the estimated fuel flow will be 1050
litres per hour and the average oil consumption will be 2
...
79 and the specific density of oil is 0
...
Calculate
the landing centre of gravity
...
26 cm aft of datum
B – 61
...
27 cm aft of datum
D – 61
...
Determine the position of the CG as a percentage of the MAC given that the
balance arm of the CTG is 724 inches and the MAC extends from a balance arm of
517 inch to 1706 inch
...
2%
B – 15
...
3%
D – 17
...
(For this Question use CAP 696 – Figure 3
...
92 inches aft of datum
B – 91
...
60 inches aft of datum
D – 91
...
5 in
160 lbs
200 lbs
290 lbs (total)
110 lbs
100 lbs
50 lbs
4210 lbs
377751 lbs
...
(Refer to figure 7-1)
The loading for a flight is shown in the attached load sheet, with the following
data applying to the aeroplane:
Maximum take-off mass:
Maximum landing mass:
Centre of gravity (CG):
Limit forward:
Aft:
Estimated trip fuel:
150,000 kg
140,000 kg
10
...
0m aft of datum
55,000 kg
A – Take-off CG is out of limits at 12
...
97m aft of datum
C – Landing CG is out of limits at 10
...
17m aft of datum
Ref: AIR: atpl, cpl
Ans: C
17
...
70m
...
796m
B – 6270 kg and 5
...
61m
D – 6270 kg and 4
...
The planned take-off mass of an aeroplane is 180000 kg, with its centre of
gravity located at 31% MAC (Mean Aerodynamic Chord)
...
Length of MAC = 4
...
Shortly prior
to engine start, the local staff informs the crew that an additional load of 4000
kg must be loaded in cargo 1 (located at 2
...
After loading this cargo, the new centre of gravity location will be:
A – 34%
B – 25%
C – 28%
D – 37%
Ref: AIR: atpl, cpl
Ans: B
19
...
6
200 000 kg
32% MAC
14 m
4
...
73 m from reference point)
Cargo 2 = 2000 kg (8
...
49 m from reference point)
Cargo 4 = empty (21
...
After loading, the new load distribution
between cargo 1 and cargo 4 is:
A – 2000 kg in cargo 1;
2000 kg in cargo 4
B – 1000 kg in cargo 1;
3000 kg in cargo 4
C – 2500 kg in cargo 1;
1500 kg in cargo 4
D – 3000 kg in cargo 1
1000 kg in cargo 4
Ref: AIR: atpl, cpl
Ans: C
20
...
6
200000 kg
32% MAC (Mean Aerodynamic Chord)
Distance from reference point to leading edge: 14m
Length of MAC = 4
...
73m from reference point)
Cargo 2 = 2000 kg (8
...
49m from reference point)
Cargo 4 = empty (21
...
He asks for a transfer of:
A – 1000 kg from cargo 1 to cargo 4
B – 500 kg from cargo 1 to cargo 3
C – 1000 kg from cargo 3 to cargo 1
D – 1500 kg from cargo 3 to cargo 1
Ref: AIR: atpl, cpl
Ans: A
21
...
70m
-
the mass of the pilot is 90 kg
the mass of the co-pilot is 75 kg
the mass of the flight engineer is 90 kg
With this crew on board, the CG position of the aircraft will be:
A – 4,455 m
B – 4,615 m
C – 0,217 m
D – 4,783 m
Ref: AIR: atpl, cpl
Ans: B
22
...
The MAC is 90 inches and LEMAC is located 321 inches aft of the
datum
...
(Refer to Figure 8-14)
Without the man on the winch, the mass and the lateral G position of the
helicopter are 6000 kg and 0
...
The mass of the wet man on
the winch is 180 kg
...
059 m to the right
C – 6,180 kg and 0
...
041 m to the right
Ref: HELI: atpl, cpl
Ans: A
24
...
04 m to the right
...
With the man on the winch, the lateral CG position of the aircraft will be:
A – 0
...
016m to the left
C – beyond the limits
D – 0
...
At a mass of 1800 kg, a helicopter equipped with a winch has a lateral CGposition of 5 cm to the left
...
With a winch load of 200 kg the lateral CG
position of the helicopter will be:
A – 10
...
5 cm to the left
C – 1
...
5 cm to the left
Ref: HELI: atpl, cpl
Ans: C
26
...
10m
...
97m
B – 2
...
91m
D – 2
...
(Refer to figure 031_9-11)
Calculate the position of the centre of gravity for the following loaded
helicopter:
A – 1
...
80
C – 2
...
24
Ref: HELI: atpl, cpl
Ans: A
28
...
5 to 3
...
25 aft + 4500
500
3
...
75 fwd
562
...
6m aft; landing 2
...
85m aft; landing 2
...
9m aft; landing 2
...
1m aft; landing 3
...
The loaded centre of gravity of an aircraft is 23
...
If the
length of the MAC is 8 feet, and the distance of the leading edge of the MAC
is 20 feet aft of the Datum, the position of the centre of gravity as a % MAC
is:
A – 8%
B – 23
...
62%
Ref: AIR: atpl, cpl
Ans: D
30
...
If the centre of gravity
position is 14
...
66”
B – 118
...
6”
D – 115
...
(Refer to figures L235, 5-3 & 4-4)
Using the load and trim sheet attached, calculate the G at take-off mass and
the stabiliser trim setting for 5 degrees of flap
A – 15
...
3 trim units
B – 14
...
75 trim units
D – 16
...
5 trim units
Ref: AIR: atpl, cpl
Ans: A
2
...
12)
Using the load and trim sheet, which of the following is the correct value for
the index at a Dry Operating Mass (DOM) of 35000 kg with a CG at 14%
MAC?
A – 35
...
0
C – 41
...
0
Ref: AIR: atpl
Ans: B
3
...
A – 16
...
4% MAC
C – 13
...
7% MAC
Ref: AIR: atpl
Ans: A
4
...
(Refer to figure 031_L400)
Using the data given in the Load & Trim sheet, determine which of the
following gives the correct values for the Zero Fuel Mass and position of the
centre of gravity (% MAC) at that mass
...
48%
B – 46130 kg and 24
...
8%
D – 41310 kg and 17
...
(Refer to figures 031_L500 and 031_L502
Contrary to the forecast given in the LOAD and TRIM sheet, cargo
compartment 1 is empty
...
5%
B – 36%
C – 26%
D – 31%
Ref: AIR: atpl
Ans: D
6
...
5%
B – 31
...
5%
D – 32
...
(Refer to figures 031_L500 and 031_L502)
Just prior to departure, you accept 10 passengers additional on board who will
be seated in compartment OC and you have 750 kg unloaded from cargo
compartment 5
...
8%
B – 30
...
5%
D – 23
...
(Refer to figure L_303)
The weight and balance sheet is available and contrary to the forecast, cargo
compartment 1 is empty
The zero fuel weight centre of gravity in MAC % (Mean Aerodynamic Chord)
is located at:
A – 26
...
5%
C – 33
...
(Refer to figure 031_L400)
Using the data given in the Load & Trim sheet, determine from the following
the correct values for the take off mass and the position of the centre of gravity
at that mass if the fuel index correction to be applied is given as 0
...
A – 20
...
3%
C – 22
...
5%
Ref: AIR: atpl
Ans: D
10
...
9
6500 kg – 6
...
7
3000 kg – 4
...
6%
C – 49130 kg and 21
...
(Refer to figure 031_L403)
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:
A – 35100 kg and 20
...
0
C – 51300 kg and 57
...
5
Ref: AIR: atpl
Ans: B
12
...
7
from the ZFM loaded index, determine which of the following is the correct
value (percentage MAC) for the position of the centre of gravity at Take Off
Mass:
A – 18%
B – 19%
C – 15%
D – 14%
Ref: AIR: atpl
Ans: A
13
...
The loading manifest shows the following details…
Passengers loaded:
Males:
40
Females:
65
Children:
8
Infants: 5
Baggage in hold number 4: 120 pieces
Using the standard mass values given and the data in the appendix, select from
the following the correct value for the mass of freight (all loaded in hold No
...
(Refer to CAP 696 figures 4-13 and 4-14)
For an aircraft with a DOI of 50, a DOM of 34100 kg and a bulk fuel load of
11900 kg, choose the correct statement for its mass and CG as a % MAC
...
75% MAC
B – 46000 kg at 15
...
5% MAC
D – 46000 kg at 17
...
(Refer to CAP 696 figure 4-14)
From the Load & Trim sheet attached – for an aircraft with a BEM of 34100
kg and CG at 15% MAC, select the correct statement after 2000 kg of cargo is
loaded into the rear hold
...
(Refer to figures 031_L500, 031_L503 and 031_L504)
Knowing that:
Dry operating mass:
110000 kg
Basic index:
119
...
3%
B – 28
...
5%
D – 32
...
(Refer to figures 031_L500, 031_L503 and 031_L505)
Knowing that:
Dry operating mass:
110000 kg
Basic index
119
...
5%
B – 27
...
3%
D – 28
...
(Refer to figures 031_L500, 031_L503 and 031_L505)
Knowing that:
Dry operating mass:
110000 kg
Basic index:
119
...
5%
B – 28
...
3%
D – 27
...
(Refer to figures 031_L500, 031_L503 and 031_L504)
Knowing that:
Dry operating mass:
110000 kg
Basic index:
119
...
5%
B – 32
...
0%
D – 31
...
(Refer to figure 031_9-1)
The empty mass of your helicopter is 1100 kg with a CG-position at 3
...
The load is as follows:
- Total mass of pilot and co-pilot:
- Total mass of passengers at rear:
150 kg
200 kg
In order not to exceed the limitations the minimum remaining fuel on board
should be:
A – 450 kg
B – 350 kg
C – 250 kg
D – 125 kg
Ref: HELI: atpl, cpl
Ans: D
21
...
What action must be taken?
A – None, since a 10 percent greater load is still within the specified safety
margin
B – Increase rotor speed by 10 percent
C – Reduce useful load
D – Take off carefully
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
22
...
During the flight 12,800 kg of fuel is consumed
...
8% MAC
B – 24
...
1% MAC
D – 23
...
(Refer to figure 031_4-14)
What would be the DOM index for a DOM of 45,000 kg and a CG at 15%
MAC?
A – 41
B – 44
C – 38
D – 45
Ref: AIR: atpl
Ans: A
031-05-03 Intentional re-positioning of CG
1
...
The aeroplane will be heavier than expected
and calculated take-off safety speeds:
A – are unaffected but V1 will be increased
B – will not be achieved
C – will be greater than required
D – will give reduced safety margins
Ref: AIR: atpl, cpl
Ans: D
2
...
5
Aft cg limit station:
79
...
8 kg
B – 62
...
9 kg
D – 73
...
A mass of 500 kg is loaded at a station which is located 10 metres behind the
present Centre of Gravity and 16 metres behind the datum
...
Given:
Aeroplane mass = 36000 kg
Centre of gravity (cg) is located at station 17m
What is the effect on cg location if you move 20 passengers (total mass = 1600
kg) from station 16 to station 23?
A – It moves aft by 3
...
157 m
C – It moves aft by 0
...
157 m
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
5
...
8
What will be the new position of the centre of gravity if 100 kg is moved from
the station 30 to station 120?
A – Station 118
...
33
C – Station 120
...
69
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
6
...
0
116
...
0 is:
A – 140 kg
B – 317 kg
C – 207 kg
D – 14 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
7
...
If 450 kg is added to a cargo hold 1
...
The loaded cg will move:
A – 40 cm
B – 33 cm
C – 30 cm
D – 34 cm
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
8
...
The total mass of an aeroplane is 9000 kg
...
0m from the datum line
...
1m from the datum line
...
8m from
the datum) to the aft hold (at 3
...
0 kg
B – 900 kg
C – 300 kg
D – 196 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
10
...
62m aft of the datum
...
How much mass must be removed from the rear hold (30m aft of the datum) to
move the centre of gravity to the middle of the limits:
A – 43120 kt
B – 16529 kg
C – 8680 kg
D – 29344 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
11
...
0
285
...
5
A – 463
...
3
C – 436
...
3
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
12
...
7m and 6
...
The loaded centre of gravity position
is 4
...
How much mass must be transferred from the front to the rear hold
in order to bring the out of limit centre of gravity position to the foremost limit?
A – 3500 kg
B – 35000 kg
C – 62500 kg
D – 7500 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
13
...
40m from the zero reference point
...
The final location
of the centre of gravity, calculated in percentage of mean aerodynamic chord
AB (from point A), is equal to:
A – 30
...
5%
C – 27
...
9%
Ref: AIR: atpl, cpl
Ans: C
14
...
38m
rearward of the reference point, representing a CG location at 30% MAC
(Mean Aerodynamic Chord)
...
The front and
rear cargo compartments are located at a distance of 15m and 25m from the
reference point respectively, the cargo load mass which needs to be transferred
from the front to the rear cargo compartment is:
A – 5600 kg
B – 3600 kg
C – It is not possible to establish the required centre of gravity location
D – 4600 kg
Ref: AIR: atpl, cpl
Ans: D
15
...
Shortly prior to engine start, the local staff informs the flight crew that an
additional load of 4000 kg must be loaded in cargo 4
...
(Refer to figure 031_8-4)
An aeroplane has a planned take-off mass of 200000 kg, with its centre of
gravity (CG) located at 15
...
The current cargo
load distribution is:
FRONT cargo:6500 kg
REAR cargo:
4000 kg
For performance purposes, the captain decides to reset the value of the centre
of gravity location to 33% MAC
...
After the transfer operation, the new cargo load distribution is:
A – front cargo: 9260 kg: rear cargo: 1240 kg
B – front cargo: 3740 kg: rear cargo: 6760 kg
C – front cargo: 6760 kg: rear cargo: 3750 kg
D – front cargo: 4540 kg: rear cargo: 5950 kg
Ref: AIR: atpl, cpl
Ans: B
17
...
Shortly prior to engine
start, the local staff informs the flight crew that 4000 kg must be unloaded from cargo 4
(23
...
Given:
Distance from reference point to leading edge: 14m
Length ofo MAC = 4
...
The planned take-off mass of a turbojet aeroplane is 180000 kg with its centre
of gravity located at 26% MAC (Mean Aerodynamic Chord)
...
69 m aft of reference point)
...
6m
After the handling operation, the new centre of gravity location in % MAC
will be:
A – 23
...
8%
C – 20
...
2%
Ref: AIR: atpl, cpl
Ans: B
19
...
Following
cargo l loading, the crew is informed that the centre of gravity at take-off is
located at 38% MAC (Mean Aerodynamic Chord) which is beyond limits
...
5m
from reference point) and cargo 4 (20
...
Given:
Distance from reference point to leading edge: 14m
Length of MAC = 4
...
A turbojet aeroplane has a planned take-off mass of 190000 kg
...
50m from reference point)
Cargo 4: 7000 kg (20
...
6m
Once the cargo loading is completed, the crew is informed that the centre of
gravity at take-off is located at 38% MAC (Mean Aerodynamic Chord) which
is beyond the limits
...
Following the transfer operation, the new load
distribution is:
A – cargo 1: 5000 kg
cargo 4: 4000 kg
B – cargo 1: 4000 kg
cargo 4: 5000 kg
C – cargo 1: 6000 kg
cargo 4: 4000 kg
D – cargo 1: 4000 kg
cargo 4: 6000 kg
Ref: AIR: atpl, cpl
Ans: C
21
...
0 – 94
...
5 inches
Arm from datum to baggage zone 4 = 178
...
6 inches
Total weight of loaded aircraft = 3400 lb
Freight equally distributed between baggage zones 1 and 4
The weight of freight to be moved between baggage zones to bring the aircraft
into balance is:
A – 44 lbs from zone 4 to zone 1
B – 83 lbs from zone 1 to zone 4
C – 44 lbs from zone 1 to zone 4
D – 83 lbs from zone 4 to zone 1
Ref: AIR: atpl
Ans: A
22
...
If 800 lbs of baggage is moved from FS 1130 to FS 430 the new C of G will be:
A – 975
...
72 in
C – 979
...
62 in
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: B
23
...
Shortly prior to
engine start, the local staff informs the crew that an additional load of 4000 kg
must be loaded in cargo 1
...
(Refer to figures 031_L500 and 031_L502)
A turbojet aeroplane is parked with the following data:
Corrected Dry Operating Mass:
Basic corrected index:
110100 kg
118
...
4000 kg
2000 kg
2000 kg
Take-off mass:
Centre of gravity location:
200,000 kg
32% MAC
To maximise performance, the captain decides to re-distribute part of the
cargo load between cargo 1 and cargo 4, in order to take off with a new centre
of gravity location at 35% MAC
...
(Refer to figures 031_L500 and 031_L502)
A turbojet aeroplane is parked with the following data:
Corrected dry operating mass: 110,100 kg
Basic corrected index: 118
...
He asks for a transfer of:
A – 1000 kg from cargo 1 to cargo 4
B – 500 kg from cargo 1 to cargo 3
C – 1000 kg from cargo 3 to cargo 1
D – 500 kg from cargo 3 to cargo 1
Ref: AIR: atpl
Ans: A
26
...
The zero fuel weight centre of gravity in MAC% (Mean Aerodynamic Chord)
is located at:
A – 31
...
5%
D – 32%
Ref: AIR: atpl
Ans: C
27
...
Shortly prior to
engine start, the local staff informs the flight crew that an additional load of
4000 kg must be loaded in cargo 4
...
(Refer to figures 031_L500 and 031_L501)
A turbojet aeroplane has a planned take-off mass of 190000 kg
...
The captain decides then to re-distribute part of the cargo
load between cargo 1 and cargo 4 in order to obtain a new centre of gravity
location at 31% MAC
...
(Refer to figures 031_L500 and 031_L501)
A turbojet aeroplane has a planned take-off mass of 180,000 kg
...
The
captain decides then to re-distribute part of the cargo load between cargo 1 and cargo
4 in order to obtain a new centre of gravity location at 31% MAC
...
(Refer to figures 031_L500 and 031_L502)
The planned take-off mass of a turbojet aeroplane is 180,000 kg with its centre
of gravity located at 26% MAC (Mean Aerodynamic Chord)
...
After the handling operation, the new centre of
gravity location in % MAC will be:
A – 23
...
8%
C – 20
...
2%
Ref: AIR: atpl
Ans: B
31
...
Shortly
prior to engine start, the local staff informs the flight crew that 4000 kg must
be unloaded from cargo 4
...
(Refer to figure 031_8-4)
An aeroplane, whose specific data is shown in the annex, has a planned takeoff mass of 200,000 kg, with its centre of gravity (CG) located at 15
...
The current cargo load distribution is:
Front cargo:
Rear cargo:
6500 kg
4000 kg
For performance purposes, the captain decides to reset the value of the centre
of gravity location to 33% MAC
...
After the transfer operation, the new cargo load distribution is:
A – front cargo: 9260 kg: rear cargo: 1240 kg
B – front cargo: 3740 kg: rear cargo: 6760 kg
C – front cargo: 6760 kg: rear cargo: 3740 kg
D – front cargo: 4550 kg: rear cargo: 5950 kg
Ref: AIR: atpl, cpl
Ans: B
33
...
6
200,000 kg
32% MAC
Initial cargo distribution:
Cargo 1:
Cargo 2:
Cargo 3:
Cargo 4:
Cargo 5:
4000 kg
2000 kg
2000 kg
Empty
Empty
To maximise performance, the captain decides to re-distribute part of the
cargo load between cargo 1 and cargo 4, in order to take off with a new centre
of gravity location at 35% MAC
...
An aircraft’s mass is 22,000 kg and the centre of gravity is 1
...
What would be the new centre of gravity if 1500 kg were transferred from the
rear hold 15m aft of datum to the forward hold 12m forward of datum?
A – 0
...
14m fwd of datum
C – 1
...
84m fwd of datum
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
35
...
ft
Centre of gravity range from 0
...
0 ft fwd of datum
A – 50 lbs
B – 112 lbs
C – 1120 lbs
D – 500 lbs
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
36
...
69m aft
of datum
...
69m
B – 22
...
78m
D – 21
...
The loaded mass of an aircraft is 33,000 lbs, and the centre of gravity is 3 feet
aft of the Datum
...
If the loaded mass is 28,220 kg how much load should be transferred 9
...
2 hold to the No
...
6 metres aft?
A – 590 kg
B – 1790 kg
C – 2980 kg
D – 4160 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
39
...
A passenger weighing 150 lb
moves back 10 seat rows, a distance of 330 inches
...
5” rearward
B – 2
...
00” rearward
D – 2
...
Assuming that an aircraft CG has to remain within limits, what is the
maximum weight which could be added to a cargo hold located at station 125,
if the CG is at station 85 and the aft limit is positioned at station 100
...
A – 3000 lbs
B – 1687
...
7 lbs
D – 1945 lbs
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
41
...
If 90 kg of electrical equipment installed at a position 600 cm aft of datum
and 90 kg of electrical equipment installed 600 cm forward to datum, what will
be the new G location?
A – 220 cm aft of datum
B – remain at 200 cm aft of datum
C – 199 cm aft of datum
D – move to the datum
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: C
42
...
The take-off mass of the aircraft
is 60000 kg and the CG is located at 2m aft of datum
...
92m aft of the datum
B – 2
...
08m aft of the datum
D – 1
...
The CG of an aircraft is at 25% MAC and MAC is 1m
...
If the
aircraft mass is 38000 kg, what load must be transferred from hold 1 to hold 2
to move the CG to 40% MAC?
A – 1520 kg
B – 259 kg
C – 480 kg
D – 380 kg
Ref: AIR: atpl, cpl
Ans: D
44
...
A load weighing 1000 kg is moved from the forward
section of the aft cargo compartment to the aft section of the forward cargo
compartment
...
(Refer to figure 031_8-12)
The loaded mass of the aircraft represented below is 5250 lbs and the centre of
gravity is 21” aft of the datum
...
The new centre of gravity position will be:
A – 21
...
52” aft of the datum
C – 20
...
84” aft of the datum
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
031-06
CARGO HANDLING
031-06-01 Types of Cargo
No questions in this sub-chapter
031-06-02 Floor load and running load limits
1
...
The width
of the floor area is 2 metres
...
Which one of the following crates (length x width x height) can be loaded directly on
the floor?
A – A load of 700 kg in a crate with dimensions:
1
...
4m x 0
...
5m x 1m x 1m
C – A load of 400 kg in a crate with dimensions:
1
...
8m x 0
...
2m x 1
...
2m
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
2
...
What is the maximum mass of a package which
can be safely supported on a pallet with dimensions of 80 cm by 80 cm?
A – 4160
...
6 kg
C – 41
...
6 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
3
...
It is planned to load a
cubic container each side of which measures 0
...
Its maximum gross mass must not
exceed: (assume g=10m/s2):
A – 5000 kg
B – 1000 kg
C – 500 kg
D – 100 kg
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
4
...
9)
A pallet having a freight platform which measures 200 cm x 250 cm has a
total mass of 300 kg
...
Using the loading manual for the transport aeroplane, calculate how much
mass may be added to, or must be off loaded from the pallet in order for the
load intensity to match the maximum permitted distribution load intensity for
lower deck forward cargo compartment
...
5 kg must be off-loaded
B – 285
...
5 kg may be added
D – 158
...
The floor limit of an aircraft cargo hold is 5000 N/m2
...
4m of side
...
The maximum floor loading for a cargo compartment in an aeroplane is given as
750 kg per square metre
...
Assuming the pallet base is entirely in contact with the floor, which of the
following is the minimum size pallet that can be used?
A – 40 cm by 200 cm
B – 30 cm by 300 cm
C – 30 cm by 200 cm
D – 40 cm by 300 cm
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: A
7
...
2 metres by 0
...
Using
the information on CAP 696 Figure 4
...
If a compartment takes a maximum load of 500 kg, with a running load of 350
kg/m and a distribution load of 300 kg/m2 max
...
2
...
4
...
The maximum floor loading on a baggage compartment floor is 120 lb per
square foot
...
The maximum floor loading on a baggage compartment floor is 120 lb per
square foot
...
The baggage compartment of a particular helicopter is 1
...
4m
long and has a maximum floor loading of 300 kg per square metre
...
The baggage compartment of a particular helicopter is 1
...
4m
long and has a maximum floor loading of 500 kg per square metre
...
The baggage compartment of a particular helicopter is 1
...
4m long
and has a maximum floor loading of 520 kg per square metre
...
The baggage compartment of a particular helicopter is 2
...
4m
long and has a maximum floor loading of 480 kg per square metre
...
Loads must be adequately secured in order to:
A – allow steep turns
B – avoid any centre of gravity (cg) movement during flight
C – prevent excessive ‘g’-loading during the landing flare
D – avoid unplanned centre of gravity (cg) movement and aircraft damage
Ref: AIR: atpl, cpl; HELI: atpl, cpl
Ans: D
2
Title: aircraft mass and balance atpl dat bank
Description: aircraft mass and balance atpl licensE exam sample questions for pilots,flight dispatchers. 100% pass if you study this question data bank well it covers everything you need for your atpl,cpl ppl or flight dispatch caa license exams...you have thousands ways of passing your exams without stress.Thank me later
Description: aircraft mass and balance atpl licensE exam sample questions for pilots,flight dispatchers. 100% pass if you study this question data bank well it covers everything you need for your atpl,cpl ppl or flight dispatch caa license exams...you have thousands ways of passing your exams without stress.Thank me later