ATPL Flight Planning and Monitoring
test bank contains questions pertaining to
033-06-01 Extraction of data
. The following list contains only a relatively small percentage of the pertinent
questions. Our software, which you are free to download now at no cost, will
generally contain a much more complete set of questions associated with this
test bank. This list is intended only to familiarize you in a general way with
the questions of the
Flight Planning and Monitoring
Flight Planning and Monitoring
EASA ATPL Theory Test Prep Software
Sorry, file temporarily unavailable. Please check back soon.
That said, while the following questions are intended
as a general familiarization tool, this list may not be up-to-date nor accurate.
We do not update this website as often as we update our software, which will
contain at any moment all questions that we have for a given test / topic. Therefore,
if you need to actually study for your test, instead of using the list below,
we strongly, strongly encourage you to download our GroundSchool
Written Test Prep Software and Apps. Not only is it more complete and up-to-date, but is also considerably faster and more efficient as a study tool.
from the EASA ATPL
Flight Planning and Monitoring
- (Refer to figure 4.3.1C)For a flight of 2000 ground nautical miles, cruising at 30000 ft, within the limits of the data given, a headwind component of 25 kt will affect the trip time by approximately:
- (Refer to CAP 697 figure 4.4)Given for the twin jet aeroplane:Estimated mass on arrival at the alternate: 50 000 kgElevation at destination aerodrome: 3 500 ftElevation at alternate aerodrome: 30 ftFind: Final reserve fuel.
- (Refer to Jeppesen Manual MUNICH ILS Rwy 26R (11-4) or figure AP-01)The ILS frequency and identifier are:
- (Refer to CAP 697 - figure 3.2)Cruising Level: 15 000 ftOutside Air Temperature: -20° CPower: High SpeedWhat is the range with 45 minutes reserve fuel at 45% power?
- Given:Distance X to Y: 2700 NMMach Number: 0.75Temperature: -45° CMean wind component ON: 10 ktTailwind Mean wind component BACK: 35 kt tailwindThe distance from X to the point of equal time (PET) between X and Y is:
- (Refer to CAP 697 figure 188.8.131.52)The aeroplane gross mass at top of climb: 61 500 kgThe distance to be flown: 385 NM at FL 350OAT: -54° CWind component: 40 kt tailwindUsing long range cruise procedure what fuel is required?
- (Refer to CAP 697 figure 4.2.1)Given:Cruise mass: 54 000 kgLong Range Cruise or 0.74 MachFind the OPTIMUM ALTITUDE for the twin - jet aeroplane.
- (Refer to Jeppesen Manual - LONDON HEATHROW ILS DME Rwy 09R (11-1) or figure AP-12)The Minimum Descent Altitude (MDA) for an ILS approach, glide slope out, is:
- Given the following:D = flight distanceX = distance to Point of Equal TimeGSo = groundspeed outGSr = groundspeed returnThe correct formula to find distance to Point of Equal Time is:
- (Refer to Route Manual chart E(HI)4 or figure HI-11 and CAP 697 figure 4.3.2A)Planning a flight from Paris Charles de Gaulle (N49 00.9 E002 36.9) to London Heathrow (N51 29.2 W000 27.9) for a twin-jet aeroplane. Preplanning:Power setting: Mach= 0.74Planned flight level: FL 280Landing Mass in the fuel graph: 50 000 kgTrip distance used for calculation: 200 NMWind from Paris to London: 280° /40 ktFind the estimated trip fuel.
- (Refer to figure 4.4)Planning a flight from Paris Charles de Gaulle to London Heathrow for a twin-jet aeroplane.Preplanning:Dry Operating Mass (DOM): 34 000 kgTraffic Load: 13 000 kgThe holding is planned at 1 500 ft above alternate elevation (256 ft)The holding is planned for 30 minutes with no reductionsDetermine the Estimated Landing Mass at alternate Manchester:
- (Refer to CAP 697 figure 4.5.1C)Find: Time, Fuel, Still Air Distance and TAS for an enroute climb 280/.74 to FL 350.Given:Brake release mass: 64 000 kgISA +10° CAirport elevation 3 000 ft
- Given the following data find the distance and time to the PSR:Leg Distance: 1190 NMTAS Out: 210 knotsWind Component Out: - 30 knotsFuel Flow Out: 2400 kg/hrTAS Home: 210 knotsWind Component: + 30 knotsFuel Flow Home: 2000 kg/hrFlight Plan Fuel: 20 500 kgReserves: 6000 kg
- If CAS is 190 kts, Altitude 9000 ft. Temp. ISA - 10° C, True Course (TC) 350° , W/V 320/40, distance from departure to destination is 350 NM, endurance 3 hours, and actual time of departure is 1105 UTC. The Point of Equal Time (PET) is reached at:
- (Refer to CAP 697 - figure 3.4)Given:Cruise altitude: 19 000 ftOAT: -14° CPower setting: 45%Find TAS:
- (Refer to CAP 697 figure 4.2.1 and table 4.2.1)Given:Cruise weight: 53 000 kgLRC/ M0.74Cruise at FL310What is the fuel penalty?
- Given flight details:Distance: 1825 NMAll engines TAS: 300 ktOne engine inoperative TAS: 250 ktW/C outbound: 10 kt headW/C Inbound: 20 kt headWhat is the time and distance to the one engine inoperative PET?
- (Refer to figure 4.7.3)Given:Diversion distance: 720 NMTail wind component: 25 ktMass at point of diversion: 55 000 kgTemperature: ISADiversion fuel available: 4 250 kgWhat is the minimum pressure altitude at which the above conditions may be met?
- (Refer to Route Manual chart SID PARIS Charles-De-Gaulle (20-3) or figure AP-03)Planning a IFR flight from Paris (Charles de Gaulle) to London (Heathrow).Find the elevation of the departure aerodrome.
- (Refer to CAP 697 - pages 26 & 27 - or figure 10-12)The Simplified Planning graphs require a fuel of 6000 kg. Given:Estimated taxi time: 20 minutesAPU running time: 60 minutesEngine and wing anti-icing: 40 minutesThe total fuel required is:
- (Refer to CAP 697 - figure 3.3)At 65%, 2400 rpm power what is the fuel flow and MAP at 9000 ft?
- (Refer to CAP 697 figure 4.3.1)Trip distance: 1900 NMFuel on board: 15 000 kgLanding weight: 50 000kgWhat is the minimum pressure altitude for this flight?
- (Refer to Jeppesen Manual LONDON HEATHROW ILS DME Rwy 09L (11-2) or figure AP-05).The decision altitude for an ILS straight-in landing is:
- (Refer to figure 184.108.40.206)Given:Flight time from top of climb to the enroute point in FL280: 48 minCruise procedure is long range cruise (LRC)Temp: ISA -5° CTake-off mass: 56 000 kgClimb fuel: 1 100 kgFind: distance in nautical air miles (NAM) for this leg and fuel consumption:
- (Refer to CAP697 figure 220.127.116.11)Given:FL330OAT -63° CWeight 50 500 kgWhat is TAS?
- (Refer to figure 2-1)Given:FL 75OAT: +5° CDuring climb: average head wind component 20 ktTake-off from MSL with the initial mass of 3 650 lbsFind the still air distance (NAM) and ground distance (NM) using the graph TIME, FUEL, DISTANCE TO CLIMB:
- (Refer to figure 4.5.1C)Given:Brake release mass: 62 000 kgTemperature: ISA + 15° CThe fuel required for a climb from Sea Level to FL330 is:
- (Refer to CAP 697 - figure 3.5)Calculate the Endurance with and without reserves, given:Cruise Pressure Altitude: 14 000 ft65% power
- (Refer to CAP 697 figure 4.5.4)Planning an IFR-flight from Paris to London for the twin jet aeroplane.Given:Estimated Landing Mass: 49 700 kgFL 280W/V 280° /40 ktAverage True Course: 320° Procedure for descent: .74 M/250 KIASDetermine the distance from the top of descent to London (elevation 80 ft).
- (Refer to CAP 697 - figures 3.3 & 3.4)Calculate the fuel used in lbs, the Manifold Pressure and the time taken in the cruise, given:55% power set at 2200 rpmCruise Pressure Altitude: 12 000 ftAmbient Temperature: -6° CLeg Distance: 287 NMWind Component: – 16 kts
- If CAS is 190 kts, Altitude 9000 ft, Temp. ISA - 10° C, True Course (TC) 350° , W/V 320/40, distance from departure to destination is 350 NM, endurance 3 hours and actual time of departure is 1105 UTC.The distance from departure to Point of Equal Time (PET) is:
- (Refer to CAP697 figure 4.2.1)Given:Cruise mass 54 000 kgLRC / 0.74MFind Optimum Altitude.
- (Refer to figure 4.2.2)Find the SHORT DISTANCE CRUISE ALTITUDE for the twin jet aeroplane.Given:Brake release mass: 40 000 kgTemperature: ISA +20° CTrip distance: 150 Nautical Air Miles (NAM)
- (Refer to figure 2-2-3)Given:FL 75OAT +10° CLean mixture @ 2300 RPMFind the Fuel flow in gallons per hour (GPH) and TAS.
- (Refer to CAP 697 - figure 3.4)For the MEP, if the OAT is -20° C at 19 000 ft the TAS at 45% power is:
list above contains 1/4 or less of the actual number of questions
and may not be up to date! Download the software today to get
access to all available questions.
more information about the EASA ATPL
Flight Planning and Monitoring
test bank, click here.
Content, and Accuracy Notice: . Dauntless Software grants visitors
permission to use the contents of this page for personal use - commercial or
public use, including collecting (or harvesting) of any data or material on
this page is strictly prohibited. This material is presented for informational
purposes only and may be in error. Dauntless Software works hard to maintain
our EASA ATPL question banks. If you see an error on this web page, it
is likely NOT an error that is repeated in our software, as our software (unlike
this web page) is connected to our editorial mechanism whose mission is to quickly
identify and correct errors. If you see what you believe to be an error, please
download and try our software to see if the error is repeated there. If you
believe it is, you can use the issue-reporting mechanisms within the software
to contact our editors about any concern you may have and we will be happy to
look into it promptly.