1
The maximum zero-fuel mass: 1- is a regulatory limitation 2- is calculated for a maximum load factor of +3.5 g 3- is based on the maximum permissible bending moment at the wing root 4- is defined on the assumption that fuel is consumed from the outer wings tank first 5- is defined on the assumption that fuel is consumed from the centre wing tank first 6- can be increased by stiffening the wing The combination of correct statements is:
2, 3, 4, 6
2, 3, 6
1, 2, 3
1, 3, 5
2
If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity (cg) on the aircraft?
It will cause the cg to move aft.
It will cause the cg to move forward.
The cg location will change, but the direction cannot be told the information given.
It will not affect the cg location.
3
At the flight preparation stage, the following parameters in particular are available for determining the mass of the aircraft: Dry operating mass , Operating mass Which statement is correct:
The Dry Operating Mass includes take-off fuel.
The Dry Operating Mass includes fixed equipment needed to carry out a specific flight
The Operating Mass includes the traffic load.
The Operating Mass is the mass of the aircraft without take-off fuel.
4
Which of the following corresponds to zero fuel mass?
Operating mass plus luggage of passengers and cargo.
Take-off mass minus fuel to destination and alternate.
Operating mass plus passengers and cargo.
The take-off mass of an aeroplane minus all usable fuel.
5
Given that: - Maximum structural take-off mass: 146 000 kg, - Maximum structural landing mass: 93 900 kg, - Maximum zero fuel mass: 86 300 kg, - Trip fuel: 27 000 kg, - Taxi fuel: 1 000 kg, - Contingency fuel: 1350 kg, - Alternate fuel: 2650 kg, - Final reserve fuel: 3000 kg, Determine the actual take-off mass:
120 900 kg.
146 000 kg.
121 300 kg.
120 300 kg.
6
On an aeroplane without central fuel tank, the maximum Zero Fuel Mass is related to:
wing loaded trip fuel.
Maximum Structural Take-Off Mass.
the bending moment at the wing root.
variable equipment for the flight
7
Considering only structural limitations, on long distance flights (at the aeroplane's maximum range), the traffic load is normally limited by:
The Maximum Zero Fuel Mass plus the Take-off Mass.
The Maximum Take-off Mass.
The Maximum Zero Fuel Mass.
The Maximum Landing Mass.
8
The Zero Fuel Mass of an aeroplane is always:
the Maximum Take-off Mass minus the take-off fuel mass.
the Take-off Mass minus the mass of take-off fuel
the Take-off Mass minus the fuselage fuel mass.
the Take-off Mass minus the wing fuel mass.
9
Given: Maximum structural take-off mass= 146 900 kg, Maximum structural landing mass= 93 800 kg, Maximum zero fuel mass= 86 400 kg, Trip fuel= 27 500 kg, Block fuel= 35 500 kg Engine starting and taxi fuel = 1 000 kg. The maximum take-off mass is equal to:
113 900 kg
120 300 kg
120 900 kg
121 300 kg
10
The centre of gravity location of the aeroplane is normally computed along the:
lateral axis.
horizontal axis.
vertical axis.
longitudinal axis.
11
In mass and balance calculations the "index" is:
is a figure without unit of measurement which represents a moment.
a location in the aeroplane identified by a number
the range of moments the centre of gravity (cg) can have without making the aeroplane unsafe to fly
an imaginary vertical plane or line from which all measurements are taken.
12
Loads must be adequately secured in order to:
allow steep turns.
avoid any centre of gravity (cg) movement during flight.
prevent excessive 'g'-loading during the landing flare
avoid unplanned centre of gravity (cg) movement and aircraft damage.
13
Traffic load is the:
Zero Fuel Mass minus Dry Operating Mass.
Take-off Mass minus Zero Fuel Mass.
Dry Operating Mass minus the disposable load.
Dry Operating Mass minus the variable load.
14
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
LM = TOM - Trip Fuel
Reserve Fuel = TOM - Trip Fuel
MTOM = ZFM + full tank fuel mass
MZFM = Traffic load + DOM
15
When establishing the mass breakdown of an aeroplane, the empty mass is defined as the sum of the:
standard empty mass plus specific equipment mass plus trapped fluids plus unusable fuel mass
empty mass dry plus variable equipment mass
basic mass plus special equipment mass
basic mass plus variable equipment mass
16
For the purpose of completing the Mass and Balance documentation, the Dry Operating Mass is defined as:
The total mass of the aircraft ready for a specific type of operation excluding all traffic load
The total mass of the aircraft ready for a specific type of operation excluding all usable fuel and traffic
load.
The total mass of the aircraft ready for a specific type of operation excluding crew and crew baggage.
The total mass of the aircraft ready for a specific type of operation excluding all usable fuel.
