Q2 CASA ATPL Systems and Aerody
The primary purpose of a supercritical wing section is to:
Increase the critical drag rise number
Prevent tip stalling on swept wing aircraft
Shorten the take off roll of an aircraft
Provide greater lift at a given angle of attack
Decrease the critical drag rise number
Coffin Corner is best described, as the situation where an aircraft is operating at such high altitude
that the difference between high and low speed buffet is only a few knots. Which statement is
correct?
It is effected by aircraft weight and load factors
It is not effected by aircraft weight or G load factors
It is not effected by aircraft weight
Which answer best describes the purpose of the Transformer Rectifier Unit (TRU)?
It converts DC power to AC power and steps up the voltage
It converts AC power to DC power and steps down the voltage
It converts DC power to AC power and steps down the voltage
It converts AC power to DC power and steps up the voltage
The term ‘Fail Passive’ of the autopilot system is used to describe:
An autopilot system comprising 2 autopilots and should one fail both will be disconnected
leaving the aircraft in a passive state of trim. The aircraft must then be flown manually.
An autopilot system comprising 2 autopilots and should one fail it will be isolated and the remaining autopilot will automatically begin a missed approached procedure
An autopilot system that comprises 3 autopilots and should one fail it will be isolated the other two continuing to fly the landing approach in a “Fail Passive” mode
Which description best describes Spiral Stability:
Opposes oscillatory stability and gets better with increased altitude
Works in conjunction with oscillatory stability and gets better with altitude
Opposes oscillatory stability and gets worse with increased altitude
Which answer is most correct when describing the Diffuser in the exhaust section of a gas turbine
engine:
It is a divergent duct increasing gas stream pressure and decreasing gas stream velocity
It is a convergent duct increasing gas stream pressure and decreasing gas stream velocity
It is a divergent duct decreasing gas stream pressure and increasing gas stream velocity
It is a convergent duct decreasing gas stream pressure and increasing gas stream velocity
Which statement is correct about turbine blade creep stress values with time in service?
Initially during the primary stage and finally in the tertiary stage, blade stretching is
significant, being less so between these stages
Initially the blade stretches considerably during the primary stage then at a linear rate during the tertiary stage
Initially the blade stretches very little but creep values increase at linear rate up to blade failure
The function of the positive pressure relief valves in the pressurisation system of a transport category
aircraft is to:
Limit the maximum positive pressure differential
Prevent ambient pressure being greater than cabin pressure upon landing
Limit the cabin pressure to a value above the outside ambient pressure at all times
Limit cabin altitude to a value below or equal to the aircraft altitude
What is the purpose of the Shuttle Valve in the hydraulic system of a transport category aircraft?
To allow hydraulic pressure from the alternate system to automatically pressurise the lines in
the event of a failure of the normal system
To vent excess hydraulic system pressure back to the reservoir during period of low demand
To allow two separate hydraulic systems to simultaneously supply pressure to required services
To allow for the correct operating sequence of components when extending or retracting landing gear
In which component of the air cycle machine in the air-conditioning system of a transport category
aircraft is the coldest air found?
The expansion turbine
The condenser
The secondary heat exchanger
The primary heat exchanger
Which of the following components of a hydraulic system in a transport category aircraft acts as a
surge suppressor:
The accumulator
The pressure relief valve
The reservoir
The check valve
The pressure regulator
The highest temperature in a gas turbine engine is:
In the primary zone of the combustion chamber
In the dilution zone of the combustion chamber
At the first stage turbine nozzle guide vanes
At the jet propelling nozzle
In a pure turbojet, compared to a high by pass turbofan of the same thrust output, the rear (LP)
turbine wheels are -
smaller and rotate faster
larger and rotate slower
larger and rotate faster
smaller and rotate slower
Regarding factors that effect VMCA which statement is most correct?
High density altitude, dihedral, and skid induced blanketing of the live engine wing all
reduce VMCA
Low density altitude, anhedral and rearward CoG reduce Vmca values
Dihedral, banking toward the failed engine and a large tail fin increase Vmca values
A method of reducing the engine air bleed load in an air cycle air conditioning system of a jet
transport aircraft is to
recirculate the air
increase the vapour pressure
lower the cabin temperature
lower the cabin altitude
Which statement is most correct regarding crew alert messages:
Warnings are colour coded red, cautions and advisories are amber
Over-speed and altitude alerts are both cautions and are colour coded amber
Warnings, cautions and advisories all have associated aural warnings
Engine fire and antiskid malfunctions are both displayed in amber
Which of the answers listed below best represents the display of active waypoints and active routes?
Active waypoints are displayed in magenta and tracks as solid magenta lines
Active waypoints are displayed in green and tracks as solid magenta lines
Active waypoints are displayed in magenta and tracks as dashed magenta lines
Active waypoints are displayed in white and tracks as dashed white lines
Which of the following combinations of flight director/autopilot modes are not selectable together:
HDG SEL and HDG HOLD
HDG HOLD and LOC
HDG SEL and ALT HOLD
HDG SEL and V/S
In a gas turbine engine, how does thrust produced at engine design RPM vary?
An OAT increase will lead to a thrust decrease
A humidity increase will lead to a thrust increase
An OAT increase will lead to a thrust increase
An OAT decrease will lead to a thrust decrease
In a turboprop powered aircraft the power lever is used to control
Pitch and torque in the Beta range
Pitch only in the reverse thrust range
Pitch and torque in the normal (Alpha) flight range
Pitch and torque in all operating ranges
The EPR of a gas turbine engine may be defined as:
The ratio between the engine inlet pressure and the exhaust duct pressure
The ratio between the gas temperature and gas pressure of the engine
The ratio between the Fan N1 RPM and N2 RPM
The ratio between the static pressure and dynamic pressure in the compressor
The EGT of a gas turbine engine may be defined as:
The temperature at the exit from the last stage of the turbine
The temperature of the gas flow at the exit of the compressor
The temperature of the gas flow at the entry to the turbine
The temperature of the gas flow at the exit from the combustion chamber
As a flight progresses and weight decreases as fuel is burnt in a transport category aircraft:
Optimum speed decreases, maximum altitude increases and buffet boundaries increase
Optimum speed increases, maximum altitude decreases and buffet boundaries decrease
Optimum speed increases, maximum altitude decreases and buffet boundaries increase
Optimum speed decreases, maximum altitude decreases and buffet boundaries increase
The freezing point of Jet-A1 fuel is closest to:
-50 C
-40 C
-30 C
-20 C
What is the purpose of the bogie wheel landing gear configuration compared to a single wheel on a
main gear leg?
Reduced tyre pressure and lower ACN’s
Cost effectiveness
Reduced tyre surface area contact
Softer main gear landings
Which of the following statements is correct concerning the operation of the Ground Proximity
Warning System:
A hard warning is not always preceded by a soft warning
A soft warning is always followed by a hard warning
All modes provide both hard and soft warnings
All modes provide hard warnings
On a turboprop aircraft the purpose of the safety coupling is to:
Disconnect the engine from the gearbox in the event of excessive negative torque
Disconnect the propeller from the gearbox in the event of excessive negative torque
Disconnect the propeller from the gearbox in the event of excessive engine RPM
Disconnect the engine from the gearbox in the event of excessive torque
The measurement of temperature in a gas turbine engine is one of the most critical items of
information the pilot needs for safe operation of the engine. The type of thermocouple used in
measurement of turbine temperature varies with engine type and design. From the following list
select the statement which correctly describes the usual application of various thermocouple probe
types:
Rapid response probes are used primarily in turboprop installations while stagnation type
probes are used mainly in turbojet and turbofan installations
Rapid response probes are used primarily in turbojet and turbofan installations while stagnation type probes are used mainly in turboprop installations
Surface probes measure gas temperature while immersion probes measure engine temperature
With differential spoilers fitted to an aircraft a left bank will require:
The left spoiler to extend if both were retracted
The left spoiler to retract if both were extended
Both spoilers to remain extended if both were extended
The left spoiler to remain retracted if both were retracted
The auto-brake selector has eight positions: DISARM, OFF, 1, 2, 3, 4, MAX and RTO. Which
statement regarding the retardation rates of various settings is true?
RTO is greater than MAX
RTO and MAX provide the same level of braking
RTO is less than MAX
Manual braking is greater than both RTO & MAX
While in cruise at a constant Flight Level at M0.82 an increase in ambient temperature will result in:
A higher TAS and a higher SFC
A higher TAS and a lower SFC
A lower TAS and a higher SFC
A lower TAS and a lower SFC
What indicates that self-sustaining speed has been achieved during the start cycle of a gas turbine
turbofan engine?
The starter disengages
The pressure starts to rise in the compressor
The turbine first starts to drive the compressor
The EGT rises first
In the event of a failure of the active sources of 115Volts AC in a transport category aircraft, which
component of the electrical system supplies the AC power?
The Static Inverter
The Generator
The Transistor
A TRU
As a turbofan powered aircraft climbs through the tropopause, thrust will:
Reduce at a greater rate compared to below the tropopause
Reduce at the same rate as below the tropopause
Remain constant
Increase
TCAS-2 TA ONLY mode is selected by the crew. Which statement is correct regarding advising of
threat levels to the crew?
RA will not be displayed aurally nor visually
RA will not be displayed visually only aurally
RA will not be announced aurally only visually
RA will continue to be announced aurally and visually
An aircraft flies above its mach trim speed, the mach trim system will:
Deflect the leading edge of the horizontal stabilator downwards
Deflect the trim tab downwards
Deflect the trim tab upwards
Deflect the elevator upwards
What is the difference between the de-ice system and the anti-ice system?
Anti-ice is selected on prior to entering an area of ice and de-ice after entering it
De-ice is selected on prior to entering an area of ice and anti-ice on after entering it
Anti-ice uses pneumatic pressure to remove formed ice and de-ice uses thermal means
There is no difference between them
In aircraft fitted with Series Type Yaw Dampers:
They are normally turned on during all phase of flight. The pilot rudder pedals will not move
in response to yaw damper movements
They cannot be turned on when on the takeoff roll whereas parallel types can
The pilot’s rudder pedals move in conjunction with the yaw damper inputs
Regarding the gas flow in the combustion section of a gas turbine engine:
Pressure is said to be constant and temperature increases
Pressure increases and temperature decreases
Pressure and temperature decrease
Pressure and temperature increase
The effect of a centre of gravity (CoG) position on the cruise speed of an aircraft for a given thrust
setting and weight in level flight is:
A rearward CoG (within limits) results in a higher cruise speed
A forward CoG (within limits) results in a higher cruise speed
No effect if trimmed correctly
A forward CP (within limits) results in a lower cruise speed
A rearward CP (within limits) results in a higher cruise speed
In an aircraft equipped with a Flight Management Computer (FMC), a holding pattern programmed
into the FMC LNAV active route will command the holding pattern track taking account of -
the actual wind
nil wind
the forecast wind
the wind in the CASA wind model
Gas turbine engine mass air flow is governed primarily by -
the RPM, the airspeed and the air density
the turbine inlet temperature, the RPM and the number of combustion chambers
the RPM, the number of compressor stages and the turbine inlet temperature
the number of combustion chambers, the number of compressor stages and the turbine inlet temperature
The correct procedure to follow in the event of a hot start to prevent torching in a gas turbine engine
is to -
motor the engine with the fuel supply cut off
close the bleed valves to decrease mass flow through the compressor
open the bleed valves to increase the mass air flow through the compressor
gradually open the throttle to en-richen the mixture and cool the combustion temperatures
An advantage of NICAD batteries in an aircraft installation compared to lead acid batteries is -
faster recharge cycle
greater load carrying capabilities
no need for ventilation
no dangerous gases
Regarding the forces acting on an aircraft in a steady climb
lift is less than weight and thrust is greater than drag
lift is less than weight and thrust is less than drag
lift is greater than weight and thrust is greater than drag
lift equals weight and thrust equals drag
The component of the autopilot system which safeguards against a servomotor runaway is -
the torque limiter
the comparator
the trim system
the artificial feel
An aircraft landing gear tyre replacement should be considered essential with
a bulge in the tyre
worn tread
a deep cut in the tread
a metal object imbedded in the tread
The fuel boost pumps in a jet transport category aircraft fuel system are located
in the fuel tanks
in the fuel manifold
in the nacelle
in the fuel control unit
The function of the follow up linkage in the nose wheel landing gear system of a jet transport
category aircraft is
to hold the nose wheel steering at the correct angle
to prevent nose wheel shimmy
to stop tyre scuffing
to permit the tiller to turn the nose wheel
The nose-wheel centering system of large jet aircraft operates to straighten the nose wheel -
prior to gear retraction
during gear retraction
after gear retraction
prior to gear extension