ATPL Systems III

50問 • 2年前

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During flight planning, the pilot enters a holding pattern into the FMC flight plan for approach at an airport. Upong arrival at the holding fix with LNAV engaged, the FMC will command an entry to be holding pattern based on the -

actual aircraft track at the fix

In an aircraft EFIS with three symbol generators, the failure of the captains SG would require

the captain to manually switch to the standby SG

During a flight over continental Australia in a high capacity RPT aircraft equipped with EFIS and FMS, the reference for the MAP mode of the EHSI would be ?

magnetic track

For the park brake to work effectively following the shutdown of all hydraulic systems, at the time of shutdown the brake accumulator pressure must be -

above minimum brake operating pressure

Items monitored by take off configuration warning system in a high capacity jet aircraft include -

L/E flap position, T/E flap position, stabiliser trim position, spoiler lever position and the park brake valve position

During the ROLLOUT submode of an autoland, the IDLE mode of the autothrottle will be -

diss engaged when selecting reverse thrust

Conditional waypoints are entered into FMC via the -

arrivals or departures pages

Subsonic flow through a divergent duct will experience-

constant density, an increase in pressure and a decrease in velocity

Supersonic flow through a divergent duct will experience -

a decrease in density and pressure, and increased velocity

In a free power turbine type engine (turboprop), the free power turbine is -

not connected to any other turbine shaft

During a CAT III ILS multi autopilot approach , the rollout thrust setting will be -

flight idle for 5 seconds after touchdown then ground idle

The gas turbine engine design feature which decreases the occurrence of compressor stall is

variable inlet guide vanes

In terms of SFC, a turboprop would be more efficient than a turbojet during -

low speed flight

Pressing the CANCEL switch on the EICAS control panel will -

select the next page

in an aircraft with two separate independent hydraulic systems

some systems are powered by both systems simultaneously

on a aircraft equipped with both outboard and inboard ailerons, the inboard ailerons operate

at all times

During TCAS operations in TA mode, RAs are -

shown as TA’s

in a gas turbine engine combustion system, the hottest gas temperature is found in -

the primary zone of the combustion chamber

a benefit of a split bus electrical system is

there’s a reduced need for frequency matching

engine bleed air, may be used for -

reverse thrust actuation, anti icing, air conditioning and pressurisation

Inflight, engine bleed air for anti icing the wing leading edges in known icing conditions is -

used continuously

the radio altimeter display on the EADU is blank when -

above 2500ft

when climbing at a constant Mach no. TAS will -

decrease in the troposphere then remain constant in the isothermal layer above the troposphere

the reference for the heading display on the EFIS MAP and FMC is -

either true or magnetic as selected by the pilot or determined by latitude

On an aircraft with a converntional flight instrument panel with two compass systems, the captains HSI displays a HDG flag. In this situation another expected indication would be -

a HDG flag on the first officers RMI

An aircraft with a TAS of 300ft had a fuel burn of 3000kg/hr. The specific air range as a ratio distance travelled per tonne of fuel used would be most correctly expressed as a ratio of -

100nm/tonne

The EPR of a gas turbine engine may be defined as ?

the ratio between the total jet pipe pressure and the total engine inlet pressure

windscreen rain repellent fluid is used in some installations to assist visibility. A limitation on its use is -

it should not be used on a dry windscreen as it could smear and reduce vision

the first indication of a successful light off (light-up) in a gas turbine engine is -

increasing TOT

as a flight progresss and weight reduces as fuel is burnt in a large jet transport aircraft

optimum speed decreases, max altitude increases and buffet boundaries increase

a pressurised aircraft on climb maintains cabin altitude at that of the departure aero drone until it reaches its max pressure differential. If the climb is continued?

the cabin altitude will climb as the system maintain maximum pressure differential

In level flight an AP/FDS mode control panel shows a selected IAS of 280kts in altitude hold mode. The flight director, autopilot and autothrottle are then all turned off. In this case the 280 IAS indication will -

remain displayed in the window and as the command airspeed bug on the speed tape

reverse thrust is most useful on large transport turbine aircraft -

at high forward speed in the landing roll

In a gas turbine engine, compressor surge can be recognised by ?

fluctuating RPM

If a reduced thrust take off is programmed into the FMC using the assumed temperature method

the reduced thrust output from the remaining engines will be sufficient to provide the required climb gradients for obstacle clearance without needing to increase thrust output

The use of sweepback as a design feature of a jet transport aircraft wing will result in -

an increase in MCDR

On a conventional ASI/Mach meter the Mach Readout is covered by a red flag indicating loss of altitude sensing. This means that the Mach display is unreliable and ?

the VMO pointer is also probably unreliable

an IVSI differs from a conventional VSI in that it has ?

accelerometers or dash lots to give an immediate indication of climb or descent

an autopilot “hardcover” means -

full servomotor deflection

the purpose of a propeller brake in a turboprop installation is to -

stop the propeller from windmilling when in feather on the ground

in normal operation of an aircraft electrical system with a bus tie, the generators are operated

in parallel

in an aircraft electrical system with two engine driven generators and an APU generator, non of which and be synchronised -

in normal operation, the system operates as a split bus system

an advantage of an axial compressor in a gas turbine engine is -

axial thrust

when the residual voltage of a large aircraft AC generator decrease to zero and no batter power is available -

it can be restarted if it is a PMG

when an integrated drive generator (IDG or CSD) suffers an internal failure of the unit -

if manually disconnected it cannot be reconnected in flight

with multiple battery installation in an aircraft, the batteries are usually connected in ?

parallel, to give increased current at a constant voltage

the combustion chamber design which is most cost effective and efficient is the ?

annular design

The perecentsge of the mass airflow through a gas turbine entering the combustion chamber through the swirl vanes is

12%

when the “Throttle Hold” THR HLD mode of the autothrottle is active and annunciater on the autothrottle flight mod annunciator on tbr EADI 1

the autothrottle is de energised

the EGT of a gas turbine engine can be defined as ?

the temperature of the gas flow at the exit of the last turbine stage

ATPL Systems

Will Erwin · 50問 · 2年前

ATPL Systems