WorksheetsAIRCRAFT GENERAL KNOWLEDGE QUIZ
Total questions: 45
Worksheet time: 23mins
Which of the following correctly describes a semi-monocoque or stressed
skin structure?
Containing no openings, but having internal structural members,
known as longerons, running lengthwise joining the frames
together
Containing openings which are reinforced to maintain the integrity of
the load bearing skin
Containing a load bearing structure that transmits loads
proportionately to the load bearing skin
Containing no openings and no internal support structure, all loads
being carried by the skin
A Fixed Trim Tab Should
Never be adjusted
Be adjusted on the ground by an aircraft technician, to correct
permanent out-of-trim conditions
Be adjusted to achieve laterally level flight
Only be adjusted if the aircraft pitch trim mechanism is found to be
incapable of sufficient movement to trim the aircraft longitudinally
Which stabilising surface provides directional stability?
Fin / Vertical Stabilizer
Rudder
Rudder Trim
Stabilator
Movement about an aircraft’s vertical (normal) axis is known as:
Side Slip
Roll
Yaw
Pitch
Ailerons are control surfaces which control an aircraft in:
Roll
Pitch
Yaw
Stall
The elevator is a control surface which controls an aircraft in:
Roll
Pitch
Yaw
Stall
The rudder is a control surface which controls an aircraft in:
Roll
Pitch
Yaw
Stall
The most common type of modern light aircraft fuselage construction is:
Monocoque
Truss / Framework
Wood
Semi Monocoque / Stressed Skin
Increased lift at lower airspeeds is achieved by deploying:
Elevator
Flaps
Rudder
Ailerons
Rotation of the aircraft about its lateral axis is called:
Side Slip
Roll
Yaw
Pitch
Rotation of the aircraft about its longitudinal axis is known as:
Side Slip
Roll
Yaw
Pitch
A flying control lock:
Locks controls in flight to neutralise aerodynamic loads and ease the
physical load on the pilot
Locks the trim tabs once straight and level flight is established
Locks controls on the ground to prevent damage in windy
conditions.
Locks controls on the ground to prevent the pilot damaging them
while manoeuvring the aircraft
Most nose wheel assemblies on modern light aircraft consist of:
Oleo-Pneumatic Shock Absorber Struts
Spring Steels Struts
Spring Coil Struts
Compressed Rubber Struts
The principal reason why light training aircraft have fixed undercarriages is
that:
Training aircraft need to manoeuvre on the ground
The reduced performance caused by the additional drag of a
fixed undercarriage is offset by its simplicity, low cost and easy
maintenance
Training aircraft need to be supported at a convenient height
Training aircraft need to ensure that kinetic energy on landing is
absorbed
On a light aircraft fitted with a mechanically-steered nose wheel, steering on
the ground is normally effected by:
Cables operated from the aileron control wheel
Use of the differential braking technique, only
Hydraulic jacks which allow self-centreing
Control rods/cables operated by the rudder pedals
The correct working cycle of a four stroke engine is:
exhaust, power, induction, compression
induction, compression, power, exhaust
induction, power, compression, exhaust
exhaust, induction, power, compression
Which of the following actions would help to improve engine cooling during
the climb in an aircraft fitted with an air cooled engine?
Leaning the Fuel / Air Mixture
Closing the cowl flaps
Increasing Power & Reducing Speed
Reducing Power & Increasing Speed
What is a Tensile Load?
A loads that shorten the structural members
A loads that stretches the structural members
A loads that causes one face of material to slide over another
A loads that causes flexes movement during flight
Primary Function of an aircraft's wing?
Store Fuel
Generate Lift
Support Landing Gear
Provide aerodynamic stability
Main advantage of cantilever wing construction
Requires external bracing for strength
Reduce drag and increase structural strength
Only suitable for low speed aircraft
Use fabric covered spars and ribs
Which type of landing gear remains extended at all times?
Retractable
Fixed
Tricycle
Conventional
Main function of aircraft powerplant?
Provide aerodynamic stability
Generate thrust and power electrical system
Fuel storage
Regulate air pressure in the cabin
What does the Pitot-Static System measure?
Fuel Flow & Pressure
Airspeed, Altitude, Vertical Speed
Engine Performance & Temperature
Outside Air Temperature
Function of trim system in an aircraft
Increase lift during takeoff
Reduce pilot workload by maintaining control surface position
Prevent drag increase during high speed
Assist yaw control
What is the primary task of Oil / Lubricating System
Reduce Friction
Improve Engine Performance
Conductor for Electrical System
Source of Hydraulic Liquid
By what activation method does the valve which allows oil to either flow
through or by-pass a serviceable engine oil cooler work?
Temperature Activated
Pressure Activated
Manually
Electrically
Excessive oil pressure can be resolved by using:
Oil pressure relief valve
Thermal Cut Out
Filter-Bypass Valve
Oil Tank Overflow
The prevention of excessive oil pressure in an aircraft engine is assured by:
Ensuring that the engine does not exceed the red-line RPM value.
The engine’s high capacity pressure pump.
The engine’s oil pressure relief valve.
The engine’s filter by-pass valve.
Where is the sensor of the engine oil temperature gauge located?
Within the exhaust sections of the engine
Before the oil cooler
After passing through the oil cooler, but before reaching the hot
sections of the engine
In the same position as the pressure sensor for the oil pressure
gauge
When a magneto is selected OFF, the switch located in the primary circuit:
Is closed and the circuit is earthed
Is opened, breaking circuit continuity
Is opened and the circuit is earthed
Is closed, earthing the plug leads
The high tension supply connected to the spark plugs comes from:
The magneto’s primary and secondary self-generation and
distribution system
The battery during start up and low idle
The battery, and is transformed by the magneto
The battery and the high tension coil
The high tension supply to the spark plugs is supplied from:
Alternator
The magneto and is independent of the aircraft electrical system
The magneto, supplied from the aircraft electrical system
The battery on engine start-up and low idle, and the magneto once
the engine is running at fast idle
How does the venturi throat of a carburettor change the characteristic of the
air?
A dynamic pressure increase and a velocity decrease
A dynamic pressure decrease and a velocity increase
A drop in local static pressure and velocity increase
A dynamic pressure increase and a temperature increase
Detonation could result from:
Weak mixtures and high cylinder head temperatures
A designed interrupted ignition sequence during start-up when
backfiring occurs
Rich mixtures and low cylinder head temperatures
High engine RPM when using high octane fuel
During preflight checks, water in the fuel system is monitored. This is because
water will cause:
Icing
Fuel to Freeze
Fuel System Contamination resulting in loss of engine power
Emulsification of the fuel in the fuel lines which could cause them to
become blocked
A fuel priming pump normally delivers fuel directly to:
The induction manifold or inlet valve port
The carburettor float chamber
The combustion chamber
The accelerator pump outlet
In the aircraft tanks, fuel is most likely to be contaminated by water from:
Poorly fitting fuel caps
Contamination during refuelling
Leaks in the tanks that have let in rain
Atmospheric air remaining in partially-filled tanks
The engine driven vacuum pump is designed to produce and direct
sufficient airflow:
Across a turbine that, in turn, drives the gyros
Through a helical impeller which drives the gyros
Onto gyro rotors to drive them round
Over the instrument case to move the gyro
The instruments usually powered by a vacuum pump system are:
(i) Direction Indicator
(ii) Turn Coordinator
(iii) Attitude Indicator or Artificial Horizon
(iv) Altimeter
(v) Magnetic Compass
(i) & (ii)
(i) & (iii)
(i), (ii), & (iv)
(i), (iii), & (v)
If, while an aircraft is descending, the static vent leading to the Vertical Speed
Indicator becomes blocked, the indicator will:
continue to show the same reading
indicate a climb
indicate a descend
show a zero reading, after a short delay
When an aircraft is in flight, the pressure sensed by the forward facing hole
in the pitot tube is:
Static Pressure Only
Total Pressure + Dynamic Pressure
Dynamic Pressure + Static Pressure
Dynamic Pressure Only
The principle of operation of the Vertical Speed Indicator (VSI) is that it:
compares static pressure in a capsule, sensed through a direct
static vent, with that in the instrument’s case, sensed though a
metered vent. The VSI is, thus, able to detect the rate of change of
static pressure with height
compares total pressure from the pitot tube with static pressure
from the static vents. The VSI is calibrated to show the difference
between the two as a vertical speed in feet per minute
compares dynamic pressure from the pitot tube with static
pressure from the static vents. The VSI is calibrated to show the
difference between the two as a vertical speed in feet per minute or
metres per second
senses total pressure only, from the pitot tube, and converts the
change in total pressure with height into a rate of climb or descent,
measured either in feet per minute or metres per second
An Altimeter:
contains a barometric capsule, connected to a total pressure source,
that contracts during a descent
contains an aneroid capsule connected to a static pressure source.
The capsule contracts during a descent
contains a barometric capsule that expands during a descent
contains a partially evacuated capsule that expands during a
descent
If the power supply to the pitot heater failed during flight in icing conditions
and the aircraft subsequently descended, the readings on the Altimeter, the
VSI and the ASI would, if ice had blocked the pitot (total pressure) tube:
Altimeter : Correct, VSI : Under-read, ASI : Over-read
Altimeter : Under-read, VSI : Correct, ASI : Over-read
Altimeter : Correct, VSI : Correct, ASI : Over-read
Altimeter : Correct, VSI : Correct, ASI : Under-read
What is the purpose of the ball in the Turn and Slip Indicator or Turn
Coordinator?
The ball indicates rate of turn
The ball indicates angle of bank
The ball indicates slip and skid
The ball indicates rate of descent in a turn
