(For this question use annex 033-9562A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) The aeroplane gross mass at top of climb is 61500 kg. The distance to be flown is 385 NM at FL 350 and OAT - 54.3 ° C. The wind component is 40 kt tailwind.Using long range cruise procedure what fuel is required?

Find the distance to the POINT OF SAFE RETURN (PSR). Given: maximum useable fuel 15000 kg, minimum reserve fuel 3500 kg, Outbound: TAS 425 kt, head wind component 30 kt, fuel flow 2150 kg/h, Return: TAS 430 kt, tailwind component 20 kt, fuel flow 2150 kg/h

(For this question use annex 033-9558A) Finish the ENDURANCE/FUEL CALCULATION and determine ATC ENDURANCE for a twin jet aeroplane, with the help of the table provided. Contingency is 5% of the planned trip fuel and fuel flow for extra fuel is 2400 kg/h.

A jet aeroplane is to fly from A to B. The minimum final reserve fuel must allow for :

On an ATC flight plan, to indicate that you will overfly the way-point TANGO at 350 kts at flight level 280, you write:

The quantity of fuel which is calculated to be necessary for a jet aeroplane to fly IFR from departure aerodrome to the destination aerodrome is 5352 kg. Fuel consumption in holding mode is 6 000 kg/h. Alternate fuel is 4380 kg. Contingency should be 5% of trip fuel. What is the minimum required quantity of fuel which should be on board at take-off?

The following fuel consumption figures are given for a jet aeroplane: -standard taxi fuel: 600 kg. -average cruise consumption: 10 000 kg/h. -holding fuel consumption at 1500 ft above alternate airfield elevation: 8000 kg/h. -flight time from departure to destination: 6 hours -fuel for diversion to alternate: 10 200 kg. The minimum ramp fuel load is:

On an ATC flight plan, the letter "Y" is used to indicate that the flight is carried out under the following flight rules.

A jet aeroplane has a cruising fuel consumption of 4060 kg/h, and 3690 kg/h during holding. If the destination is an isolated airfield, the aeroplane must carry, in addition to contingency reserves, additionnal fuel of :

(For this question use annex 033-3318A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Given: long range cruise. outside air temperature (OAT) -45 ° C in FL 350. mass at the beginning of the leg 40 000 kg. mass at the end of the leg 39 000 kg. Find: true airspeed (TAS) at the end of the leg and the distance (NAM).

(For this question use annex 033-9719A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) An aeroplane is flying VFR and approaching position TANGO VORTAC (48° 37"N, 009° 16"E) at FL 055 and magnetic course 090° , distance from VORTAC TANGO 20 NM. Name the frequency of the TANGO VORTAC.

Find the distance from waypoint 3 (WP 3) to the critical point. Given: distance from W P 3 to WP 4 = 750 NM, TAS out 430 kt, TAS return 425 kt, Tailwind component out 30 kt, head wind component return 40 kt

(For this question use annex 033-11717A) The planned flight is over a distance of 440 NM Based on the wind charts at altitude the following components are found. FL50: -30kt. FL100: - 50kt. FL180: -70kt The Operations Manual in appendix details the aircraft"s performances Which of the following flight levels (FL) gives the best range performance:

(For this question use annex 033-3324A or Flight Planning Manual MRJT 1 Figure 4.4) Given: dry operating mass 35 500 kg. estimated load 12 000 kg, contingency approach and landing fuel 2 500 kg. elevation at departure aerodrome 500 ft. elevation at alternate aerodrome 30 ft. Find: final reserve fuel for a jet aeroplane (holding) and give the elevation which is relevant. 1 EAAPS (For this question use 11 400 kg. 04h 12 min 12 400 kg. 04h 12 min 11 400 kg. 03h 55 min 12 400 kg. 03h 55 min 0 0 0 -1 annex 033-3323A or Flight Planning Manual MRJT 1 Figure 4.3.3C) Given: ground distance to destination aerodrome 1 600 NM. headwind component 50 kt. FL 330. cruise 0.78 Mach. ISA + 20 ° C. estimated landing weight 55000 kg . Find: simplified flight planning to determine estimated trip fuel and trip time. 1 EAAPS (For this question use 800 kg. 40 min 1 100 kg. 25 min 1 100 kg. 44 min 800 kg. 24 min 0 -1 0 0 annex 033-3322A or Flight Planning Manual MRJT 1 Figure 4.3.6) Given: estimated dry operation mass 35 500 kg. estimated load 14 500 kg. final reserve fuel 1200 kg. distance to alternate 95 NM. average true track 219° . head wind component 10 kt Find : fuel and time to alternate. 1 EAAPS (For this question use 4 800 kg. 01 : 45 4 400 kg. 02 : 05 4 750 kg. 02 : 00 4 600 kg. 02 : 05 -1 0 0 0 annex 033-3321A or Flight Planning Manual MRJT 1 Figure 4.3.1.B) Given : estimated zero fuel mass 50 t. estimated landing mass at alternate 52 t. final reserve fuel 2 t. alternate fuel 1 t. flight to destination, distance 720 NM, true course (TC) 030, W/V 340/30. cruise: long range FL 330, outside air temperature -30 ° C. Find : estimated trip fuel and time

(For this question use annexes 033-3320A, 033-3320B and 033- 3320C or Flight Planning Manual MRJT 1 Figures 4.2.1, 4.2.2 and 4.5.3.2) Given: estimated take- off mass 57 000 kg. still air distance 150 NAM. outside air temperature (OAT) ISA -10K. cruise at 0.74 Mach. Find : cruise altitude and expected true airspeed

To carry out a VFR flight to an off-shore platform, the minimum fuel quantity on board is:

Flight planning chart for an aeroplane states, that the time to reach the cruising level at a given gross mass is 36 minutes and the distance travelled is 157 NM (zero-wind). What will be the distance travelled with an average tailwind component of 60kt ?

You are flying a constant compass heading of 252° . Variation is 22° E, deviation is 3° W and your INS is showing a drift of 9° right. True track is ?

The purpose of the decision point procedure is ?

(For this question use annex 033-9722A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying from SAULGAU airport (48° 02"N, 009° 31"E) to ALTENSTADT airport (47° 50"N, 010° 53"E). Find magnetic course and the distance.

(For this question use annex 033-9724A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying from Position SIGMARINGEN (48° 05"N, 009° 13"E) to BIBERACH airport (48° 07"N, 009° 46"E). Find magnetic course and the distance.

(For this question use annex 033-9723A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying from ERBACH airport (48° 21"N, 009° 55"E) to POLTRINGEN airport (48° 33"N, 008° 57"E). Find magnetic course and the distance.

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 :

When using decision point procedure, you reduce the

(For this question use annex 033 11702 A) The measured course 042° T. The variation in the area is 6° W and the wind is calm. The deviation card is reproduced in the annex. In order to follow this course, the pilot must fly a compass heading of:

When calculating the fuel required to carry out a given flight, one must take into account : 1 - the wind 2 - foreseeable airborne delays 3 - other weather forecasts 4 - any foreseeable conditions which may delay landing The combination which provides the correct statement is :

For a flight to an off- shore platform, an alternate aerodrome is compulsory, except if : 1 - flight duration does not exceed two hours 2 - during the period from two hours before to two hours after the estimated landing time, the forecast conditions of ceiling and visibility are not less than one and a half times the applicable minima 3 - the platform is available and no other flight either from or to the platform is expected between the estimated time of departure and one half hour after the estimated landing time The combination which regroups all of the correct statements is :

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 :

Given the following: D = flight distance X = distance to Point of Equal Time GSo = groundspeed out GSr = groundspeed return The correct formula to find distance to Point of Equal Time is :

On a ATC flight plan, to indicate that you will overfly the way-point ROMEO at 120 kt at flight level 085, you will write :

(For this question use annex 033-3305A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Given: long range cruise: temp. -63° C at FL 330 initial gross mass enroute 54 100 kg. leg flight time 29 min Find: fuel consumption for this leg

(For this question use annex 033-9556A or Flight Planning Manual MRJT 1 Figure 4.14) Find the SPECIFIC RANGE for the twin jet aeroplane flying below the optimum altitude (range loss = 6%) and using the following data. Given: MACH .74 CRUISE, Flight level = 310, Gross mass = 50000 kg, ISA conditions

Which of the following statements is relevant for forming route portions in integrated range flight planning?

(For this question use annex 033-9550A or Flight Planning Manual MRJT 1 Figure 4.2.2) Find the SHORT DISTANCE CRUISE ALTITUDE for the twin jet aeroplane. Given: Brake release mass=45000 kg, Temperature=ISA + 20° C, Trip distance=50 Nautical Air Miles (NAM)

(For this question use annex 033-9551A or Flight Planning Manual MRJT 1 Figure 4.2.2) Find the SHORT DISTANCE CRUISE ALTITUDE for the twin jet aeroplane. Given: Brake release mass=40000 kg, Temperature=ISA + 20° C, Trip distance=150 Nautical Air Miles (NAM)

(For this question use annexes 033-11226A and 033-11226B) In standard atmosphere, assuming a mass of 197 000 kg, in order to fly at FL 370 and to be at the optimum altitude, your Mach number should be:

(For this question use annex 033-11254A, 033-11254B, 033- 11254C and 033- 11254D) Knowing that: . Mass at brake release: 190 000 kg . Selected cruise speed: 0.82 Mach . Flight leg distance: 1 500 NM . Cruise level: optimum . Air conditioning: standard . Anti-icing: OFF . Temperature: ISA . CG: 37% Assuming zero wind, the planned landing mass at destination will be:

(For this question use annex 033-11253A, 033-11253B, 033- 11253C and 033- 11253D) Knowing that: . Mass at brake release: 190 000 kg . Selected cruise speed: 0.82 Mach . Flight leg distance: 1 500 NM . Cruise level: optimum . Air conditioning: standard . Anti-icing: OFF . Temperature: ISA . CG: 37% Assuming zero wind, the planned flight time from take-off to landing needed to complete this flight will be: subject/sec aragraph wording Domanda rispostaA rispostaB rispostaC rispostaD ck1 ck2 ck3 ck4 1 FRANCE (For this question use 394 minutes 389 minutes 400 minutes 383 minutes 0 0 -1 0 annex 033-11252A,033- 11252B and 033- 11252C) Knowing that: . Mass at brake release: 210 000 kg . Selected cruise speed: 0.82 Mach . Air distance: 3 000 NM . Cruise level: optimum . Air conditioning: standard . Anti-icing: OFF . Temperature: ISA . CG: 37% Assuming zero wind, the planned flight time from take-off to landing needed to complete this flight will be:

(For this question use annex 031-11231A) For a long distance flight at FL 370, "Long Range" regime, divided into four flight legs with the following specifications: - segment AB - Ground distance: 2 000 NM. headwind component: 50 kt - segment BC - Ground distance: 1 000 NM. headwind component: 30 kt - segment CD - Ground distance: 500 NM. tailwind component: 70 kt - segment DE - Ground distance: 1 000 NM. headwind component: 20 kt The total air distance is approximately:

(For this question use annex 031-11229A ) For a turbojet aeroplane flying with a mass of 190 000 kg, at Mach 0.82, and knowing that the temperature at flight level FL 370 is - 35° C, the optimum flight altitude calculated using the annex is:

(For this question use annex 033-11261A) Prior to an IFR flight, when filling in the ICAO flight plan, the time information which should be entered in box 13: "Time" is:

(For this question use annex 033-11271A) The flight crew of a turbojet aeroplane prepares a flight using the following data: . Take-off mass: 210 500 kg . Flight leg ground distance: 2 500 NM . Flight level FL 330. "Long Range" flight regime . Tailwind component at this level: 70 kt . Total anti-ice set on "ON" . Fixed taxi fuel: 500 kg. final reserve: 2 400 kg . Ignore alternate fuel. The effects of climb and descent are not corrected for consumption. The quantity of fuel that must be loaded at the parking area is:

(For this question use annex 033-11270A) A turbojet aeroplane flies using the following data: . flight level: FL 330, flight regime: "Long Range" (LR), mass: 156 500 kg . tailwind component at this level: 40 kt With a remaining flight time of 1 h 10 min the ground distance that can be covered by the aeroplane at cruising speed is:

(For this question use annex 033-11262A) Prior to an IFR flight, when filling in the ICAO flight plan, the time information which should be entered in box 16: "Total estimated time" is the time elapsed from:

For flight planning purposes the landing mass at alternate is taken as:

The final reserve fuel for aeroplanes with turbine engines is

(For this question use annex 033-11260A and 033-11260B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg air distance: 2 700 NM - Flight level FL 310, true airspeed: 470 kt - Tailwind component at this level: 35 kt - Initially planned take- off mass (without extra fuel on board): 195 000 kg - Fuel price: 0.28 Euro/l at departure. 0.26 Euro/l at destination To maximize savings, the commander chooses to carry extra fuel in addition to that which is necessary. The optimum quantity of fuel which should be carried in addition to the prescribed quantity is:

(For this question use annex 033-11259A and 033-11259B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg air distance: 2 700 NM - Flight level FL 310, true airspeed: 470 kt - Tailwind component at this level: 35 kt - Initially planned take- off mass (without extra fuel on board): 180 000 kg - Fuel price: 0.28 Euro/l at departure. 0.26 Euro/l at destination To maximize savings, the commander chooses to carry extra fuel in addition to that which is necessary. The optimum quantity of fuel which should be carried in addition to the prescribed quantity is:

(For this question use annex 033-9579A, B,C,D or Flight Planning Manual MRJT 1 Figure 4.2.2 and Figure 4.5.3.2) Given: Estimated take- off mass 57000 kg, Ground distance 150 NM, Temperature ISA - 10° C, Cruise at .74 Mach Find: Cruise altitude and expected true air speed

(For this question use annex 033-4616A or Flight Planning Manual MRJT 1 Figure 4.3.6) In order to get alternate fuel and time, the twin - jet aeroplane operations manual graph shall be entered with:

(For this question use annexes 033-11224A, 033-11224B and 033- 11224C) Given: . Take-off mass: 150 000 kg . Planned cruise at FL . Long range MACH . Standard Atmosphere (ISA) . CG: 37 % You have to cover an air distance of 2 000 NM. Your flight time will be:

(For this question use annex 033-9546A or Flight Planning Manual MRJT 1 Figure 4.3.6) In order to find ALTERNATE FUEL and TIME TO ALTERNATE, the AEROPLANE OPERATING MANUAL shall be entered with:

(For this question use annex 033-11186A) Which best describes be maximum intensity of icing, if any, at FL150 in the vicinity of BUCHAREST (45° N 026° E) ?

(For this question use annex 033-11194A) The wind direction and velocity (° /kt) at 40° N 040° E is

(For this question use annex 033-11192A) The approximate mean wind component (kt) at Mach 0.78 along true course 270° at 50°N from 000° to 010° W is

(For this question use annex 033-11191A) The wind direction and velocity (° /kt) at 60° N 015° W is

(For this question use annex 033-11190A) The wind direction and velocity (° /kt) at 50° N 040° E is:

(For this question use annex 033-11189A) The wind velocity over ITALY is

(For this question use annex 033-11228A) For a long distance flight at FL 390, "Long Range" regime, divided into four flight legs with the following characteristics: - segment AB - Ground distance: 2 000 NM. head wind component: 50 kt - segment BC - Ground distance: 1 000 NM. head wind component: 30 kt - segment CD - Ground distance: 500 NM. tail wind component: 100 kt - segment DE - Ground distance: 1 000 NM. head wind component: 70 kt The air distance of the entire flight is approximately:

(For this question use annex 033-11187A) Which best describes the maximum intensity of CAT, if any, forecast for FL330 over BENGHAZI (32° N 020° E) ?

(For this question use annex 033-11197A) Which affects the visibility forecast for 0000 UTC at LAHORE (OPLA) ?

(For this question use annex 033-11185A) Which best describes the significant cloud, if any, forecast for the area southwest of BODO (67° N 014° E)

(For this question use annex 033-11184A) Which describes the maximum intensity of icing, if any, at FL180 in the vicinity of CASABLANCA (33° N 008° W) ?

(For this question use annex 033-11183A) In the vicinity of PARIS (49° N 003° E) the tropopause is at about

(For this question use annex 033-11182A) The surface weather system over England (53° N 002° W) is

(For this question use annex 033-11181A) Which describes the worst hazard, if any, that could be associated with the type of feature at 38°N 015° E ?

(For this question use annexes 033-11074A, 033-11074B, 033- 11074C and 033- 11074D) Planning a MACH 0,82 cruise at FL 390, the estimated landing mass is 160 000 kg. The ground distance is 2 800 NM and the mean wind is equal to zero. ISA conditions. Fuel consumption will be:

(For this question use annexes 033-11073A, 033-11073B, 033- 11073C and 033- 11073D) Planning a MACH 0,82 cruise at FL 390, the estimated landing mass is 160 000 kg. the ground distance is 2 800 NM and the mean tailwind is 100 kt. ISA conditions. Fuel consumption will be:

(For this question use annex 033-11188A) The maximum wind velocity (° /kt) shown in the vicinity of MUNICH (48° N 012° E) is :

(For this question use annex 033-11208A) A turbojet aeroplane, weighing 200 000 kg, initiates its cruise at the optimum level at M 0.84 (ISA, CG=37%, Total Anti Ice ON). A head wind of 30 kt is experienced and, after a distance of 500 NM, severe icing is encountered and this requires an immediate descent. The aeroplane mass at start of descent is:

(For this question use annexes 033-11223A, 033-11223B and 033- 11223C) Given: . Take-off mass: 150 000 kg . Planned cruise at FL . Long range MACH . Standard Atmosphere (ISA) . CG: 37 % Covering an air distance of 2 000 NM, your trip fuel from take- off to landing will be:

(For this question use annex 033-11216A) A turbojet aeroplane is flying using the following data: . flight level FL 250, Long Range (LR) cruise, mass of 150 000 kg . temperature: ISA . head wind component: 100 kt . remaining flight time: 1 h 40 min The ground distance that can be covered during the cruise flight is:

(For this question use annex 033-11215A) A turbojet aeroplane is flying using the following data: . optimum flight level, Mach 0.80, mass of 190 000 kg . temperature: ISA . tailwind component: 100 kt The fuel mileage and the fuel consumption per hour are:

(For this question use annex 033-11214A) Assuming the following data: . Ground distance to be covered: 2 600 NM . Cruise flight level: FL . Cruising speed: Mach 0.82 (true airspeed: 470 kt) . Wind: zero wind during flight . Planned destination landing mass: 140 000 kg . Temperature: ISA + 15° C . CG: 37 % . Total anti-ice: ON . Air conditioning: normal Fuel consumption for such a flight is:

(For this question use annex 033-11213A and 033-11213B) Assuming the following data: . Ground distance to be covered: 2 500 NM . Cruise flight level: FL . Cruising speed: Mach 0.82 (true airspeed: 470 kt) . Tailwind component: 40 kt . Planned destination landing mass: 150 000 kg . Temperature: ISA . CG: 37% . Total anti-ice: OFF . Air conditioning: normal Fuel consumption for such a flight is:

(For this question use annex 033-11212A and 033-11212B) Assuming the following data: . Ground distance to be covered: 1 500 NM . Cruise flight level: FL . Cruising speed: Mach 0.82 (true airspeed: 470 kt) . Head wind component: 40 kt . Planned destination landing mass: 140 000 kg . Temperature: ISA + 15° C . CG: 37 % . Total anti-ice: ON . Pack flow: HI Fuel consumption for such a flight is:

(For this question use annex 033-11211A and 033-11211B ) Assuming the following data: . Ground distance to be covered: 2 000 NM . Cruise flight level: FL . Cruising speed: Mach 0.82 (true airspeed: 470 kt) . Head wind component: 30 kt . Planned destination landing mass: 160 000 kg . Temperature: ISA . CG: 37% . Total anti-ice: ON . Pack flow: HI Time needed to carry out such a flight is:

(For this question use annex 033-11195A) What lowest cloud conditions (oktas/ft) are forecast for 1900 UTC at HAMBURG (EDDH) ?

(For this question use annex 033-11209A and 033-11209B) Assuming a departure/destination fuel price ratio of 0.91, the commander decides to optimize fuel tankering by using the following data: . Cruise flight level: FL . Air distance to be covered: 2 500 NM . Planned take-off mass: 200 000 kg (with the minimum prescribed fuel quantity of 38 000 kg that includes a trip fuel of 29 000 kg) . Maximum landing mass: 180 000 kg . Maximum take-off mass: 205 000 kg . Maximum tank capacity: 40 000 kg The additional fuel quantity will be:

(For this question use annex 033-11196A) What minimum visibility (m) is forecast for 0600 UTC at LONDON LHR (EGLL) ?

(For this question use annex 033-11207A and 033-11207B) A turbojet aeroplane is prepared for a 1300 NM flight at FL 350, with a true airspeed of 460 kt and a head wind of 160 kt. The take-off runway limitation is 174 000 kg, the planned departure mass is 160 000 kg. The departure fuel price is equal to 0.92 times the arrival fuel price (fuel price ratio = 0.92). In order for the airline to optimize its savings, the additional fuel quantity that must be loaded on board is:

(For this question use annexes 033-11204A, 033-11204B and 033- 11204C) The flight crew of a turbojet aeroplane prepares a flight using the following data: Flight leg ground distance: 4 000 NM Flight level FL 370. "Long range" flight regime Effective wind at this level: head wind of 50 kt Temperature: ISA Centre of gravity (CG): 37 % Pack flow : LOW (LO) Anti ice: OFF Reference landing mass: 140 000 kg Taxi fuel: 500 kg Final reserve fuel: 2 400 kg The fuel quantity which must be loaded on board the aircraft is:

(For this question use annex 033-11202A) Which of the following flight levels, if any, is forecast to be clear of significant cloud, icing and CAT along the marked route from SHANNON (53° N 10° W) to BERLIN (53° N 13° E) ?

(For this question use annex 033-11201A) What mean temperature (° C) is likely on a course of 360° (T) from 40° N to 50° N at 040° E ?

A METAR reads : SA1430 35002KY 7000 SKC 21/03 QI024 = Which of the following information is contained in this METAR ?

(For this question use annex 033-11198A) What is the earliest time (UTC), if any, that thunderstorms are forecast for DOHA (OTBD) ?

(For this question use annex 033-11210A and 033-11210B) Assuming a departure/destination fuel price ratio of 0.92, the commander decides to optimize fuel tankering by using the following data: . Cruise flight level: FL . Air distance to be covered: 1 830 NM . Planned take-off mass: 190 000 kg (with a minimum prescribed fuel quantity of 30 000 kg that includes a trip fuel of 22 000 kg) . Maximum landing mass: 180 000 kg . Maximum take-off mass: 205 000 kg . Maximum tank capacity: 40 000 kg The additional fuel quantity will be:

(For this question use annex 033-9576A or Route Manual chart E(HI)5 CAA-Edition) Given: Leg Moulins(N46 24.4 E003 38.0)/Dijon(N47 16.3 E005 05.9). Find: Route designator and total distance

Given: True course (TC) 017° , W/V 340° /30 kt, True air speed (TAS) 420 kt Find: Wind correction angle (WCA) and ground speed (GS)

(For this question use annex 033-9578A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Given: Long range cruise, OAT -45° C at FL 350, Gross mass at the beginning of the leg 40000 kg, Gross mass at the end of the leg 39000 kg Find: True air speed (TAS) and cruise distance (NAM) for a twin jet aeroplane

(For this question use annex 033-9573A or Flight Planning Manual MRJT 1 Figure 4.5.1) Given: Brake release mass 57500 kg, Initial FL 280, average temperature during climb ISA -10° C, average head wind component 18 kt Find: Climb time for enroute climb 280/.74

(For this question use annexes 033-3911A and 033-3911B) or (Route Manual chart E(HI)4 CAA-Edition and Flight planning manual Figure 4.3.6) Planning a flight from Paris Charles de Gaulle (N49 00.9 E002 36.9) to London Heathrow (N51 29.2 W 000 27.9) for a twin - jet aeroplane. The alternate airport is Manchester (N53 21.4 W 002 15.7) Preplanning: The wind from London to Manchester is 250° /30 kt The distance from London to Manchester is 160 NM. Assume the Estimated Landing Mass at alternate is about 50 000 kg. Find the alternate fuel and the according time.

On a VFR flight plan, the total estimated time is: 15 minutes

A helicopter is on a 150 NM leg to an off-shore oil rig. Its TAS is 130 kt with a 20 kt tailwind, its endurance is 3h30min without reserve. Upon reaching destination, it is asked to proceed outbound to locate a ship in distress, on a track which gives a 15 kt tailwind. Maintaining zero reserve on return to the oil rig, the helicopter can fly outbound for distance of:

On an ATC flight plan, an aircraft indicated as "H" for "Heavy" certified take-off mass

(For this question use annex 033-9575A or Flight Planning Manual MRJT 1 Figure 4.5.1) Given: Brake release mass 57500 kg, Temperature ISA - 10° C, Average headwind component 16 kt, Initial FL 280 Find: Climb fuel for enroute climb 280/.74

(For this question use annex 033-3910A or Flight Planning Manual MRJT 1 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 kg Traffic Load: 13 000 kg The holding is planned at 1 500 ft above alternate elevation. The alternate elevation is 256 ft. The holding is planned for 30 minutes with no reductions. Determine the Estimated Landing Mass at alternate Manchester.

(For this question use annex 033-9574A or Flight Planning Manual MRJT 1 Figure 4.5.1) Given: Brake release mass 57500 kg, Temperature ISA - 10° C, Headwind component 16 kt, Initial FL 280 Find: Still air distance (NAM) and ground distance (NM) for the enroute climb 280/.74

(For this question use annexes 033-3912A and 033-3912B or Route Manual chart E(HI)4 CAA-Edition and Flight planning manual 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: Powersetting: Mach= 0.74 Planned flight level FL The Landing Mass in the fuel graph is 50 000 kg The trip distance used for calculation is 200 NM The wind from Paris to London is 280° /40 kt Find the estimated trip fuel.

Planning a flight from Paris (Charles de Gaulle) to London (Heathrow) for a twin - jet aeroplane. Preplanning: Maximum Take-off Mass: 62 800 kg Maximum Zero Fuel Mass: 51 250 kg Maximum Landing Mass: 54 900 kg Maximum Taxi Mass: 63 050 kg Assume the following preplanning results: Trip fuel: 1 800 kg Alternate fuel: 1 400 kg Holding fuel (final reserve): 1 225 kg Dry Operating Mass: 34 000 kg Traffic Load: 13 000 kg Catering: 750 kg Baggage: 3 500 kg Find the Take-off Mass (TOM):

(For this question use annex 033-9564A or Flight Planning Manual MRJT 1 Figure 4.5.1) Find: Time, Fuel, Still Air Distance and TAS for an enroute climb 280/.74 to FL 350. Given: Brake release mass 64000 kg, ISA +10° C, airport elevation 3000 ft

Find the time to the Point of Safe Return (PSR). Given: Maximum useable fuel 15000 kg, Minimum reserve fuel 3500 kg, TAS out 425 kt, Head wind component out 30 kt, TAS return 430 kt, Tailwind component return 20 kt, Average fuel flow 2150 kg/h

(For this question use annex 033-9571A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Find: Final fuel consumption for this leg Given: Long range cruise, Temperature - 63° C, FL 330, Initial gross mass enroute 54100 kg, Leg flight time 29 min

(For this question use annex 033-9572A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Find: Air distance in Nautical Air Miles (NAM) for this leg and fuel consumption Given: Flight time from top of climb at FL 280 to the enroute point is 48 minutes. Cruise procedure is long range cruise. Temperature is ISA -5° C. The take-off mass is 56000 kg and climb fuel 1100 kg.

Given : Distance A to B 3060 NM Mean groundspeed "out" 440 kt Mean groundspeed "back" 540 kt Safe Endurance 10 hours The time to the Point of Safe Return (PSR) is:

(For this question use annex 033-9543A Flight Planning Manual MRJT 1 Figure 4.4) The final reserve fuel taken from the HOLDING PLANNING table for the twin jet aeroplane is based on the following parameters:

Integrated range curves or tables are presented in the Aeroplane Operations Manuals. Their purpose is

Given : Distance A to B 2050 NM Mean groundspeed 440 kt Mean groundspeed "back" 540 kt The distance to the point of equal time (PET) between A and B is :

Given : Distance X to Y 2700 NM Mach Number 0.75 Temperature -45° C Mean wind component 10 kt tailwind Mean wind compontent "back" 35 kt tailwind The distance from X to the point of equal time (PET) between X and Y is : 3 UNITED KI (For this question use (i) 2000 ft (ii) 160° (i) 200 ft (ii) 223° (i) 3000 ft (ii) 160° (i) 3000 ft (ii) 223° -1 0 0 0 annex 033- 11059A or Route Manual chart AMSTERDAM SCHIPHOL ILS DME Rwy 22 (11-6)) The Missed Approach procedure is to climb to an alitude of (i)------------ on a track of (ii) ----------

Given : X = Distance A to point of equal time (PET) between A and B E = Endurance D = Distance A to B O = Groundspeed "on" H = Groundspeed "back" The formula for calculating the distance X to point of equal time (PET) is:

Given : Course A to B 088° (T) distance 1250 NM Mean TAS 330 kt Mean W/V 340° /60 kt The time from A to the PET between A and B is :

For a repetitive flight plan (RPL) to be used, flights must take place on a regular basis on at least :

In the ATS flight plan Item 15 (Cruising speed), when not expressed as a Mach number, cruising speed is expressed as :

In the ATS flight plan Item 13, in a flight plan submitted before departure, the departure time entered is the :

In the ATS flight plan Item 15, a cruising speed of 470 knots will be entered as :

When an ATS flight plan is submitted for a flight outside designated ATS routes, points included in Item 15 (route) should not normally be at intervals of more than :

In an ATS flight plan, Item 15 (route), a cruising pressure altitude of 32000 feet would be entered as :

In an ATS flight plan Item 15 (route), in terms of latitude and longitude, a significant point at 41° 35" north 4° 15" east should be entered as :

An aircraft plans to depart London at 1000 UTC and arrive at Munich (EDDM) at 1215 UTC. In the ATS flight plan Item 16 (destination/EET) should be entered with :

In the ATS flight plan Item 19, if the number of passengers to be carried is not when the plan is ready for filing :

(For this question use annex 033-12289A) In the ATS flight plan Item 19, emergency and survival equipment carried on the flight should be indicated by :

According to the chart the minimum obstruction clearance altitude (MOCA) is 8500 ft. The meteorological data gives an outside air temperature of -20°C at FL 85. The QNH, given by a met. station at an elevation of 4000ft, is 1003 hPa. What is the minimum pressure altitude which should be flown according to the given MOCA?

A "current flight plan" is a :

In an ATS flight plan Item 15, in order to define a position as a bearing and distance from a VOR, the group of figures should consist of :

(For this question use annex 033-12372A or Route Manual chart NAP) The distance (NM) from A (64° N006° E) to C (62° N020° W) is

(For this question use annex 033-12374A or Route Manual chart NAP) The average true course from A (64° N006° E) to C (62° N020° W) is

(For this question use annex 033-12376A or Route Manual chart NAP) The initial true course from A (64° N006° E) to C (62° N020° W) is

(For this question use annex 033-12377A or Route Manual chart NAP) The distance (NM) from C (62° N020° W) to B (58° N004° E) is

When completing an ATS flight plan, an elapsed time (Item 16) of 1 hour 55 minutes should be entered as :

Which of the following statements filing a flight plan is correct? time of departure.

(For this question use annex 033-3311A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Given :FL 330. long range cruise. OAT - 63° C. gross mass 50 500 kg. Find: true airspeed (TAS)

In the ATS flight plan item 15, when entering a route for which standard departure (SID) and standard arrival (STAR) procedures exist :

In the ATS flight plan item 15, it is necessary to enter any point at which a change of cruising speed takes place. For this purpose a "change of speed" is defined as :

(For this question use annex 033-12285A) In the ATS flight plan item 7, for a radio equipped aircraft, the identifier must always :

(For this question use annex 033-3309A or Flight Planning Manual MRJT 1 Figure 4.5.1) Given : mass at brake release 57 500 kg. temperature ISA -10° C. average head wind component 16 kt initial cruise FL 280 Find: climb fuel

When completing an ATS flight plan for a European destination, clock times are to be expressed in :

(For this question use annexes 033-3308A or Flight Planning Manual MRJT 1 Figure 4.5.1) Given : brake release mass 57 500 kg temperature ISA -10° C. head wind component 16 kt initial FL 280 Find: still air distance (NAM) and ground distance (NM) for the climb

(For this question use annex 033-12364A or Flight Planning Manual MRJT 1 Figure 4.7.2) For the purpose of planning an extended range flight it is required that with a start of diversion mass of 55000kg a diversion of 600 nautical miles should be achieved in 90 minutes. Using the above table, the only listed cruise technique to meet that requirement is :

(For this question use annex 033-12281A) Item 9 of the ATS flight plan includes "NUMBER AND TYPE OF AIRCRAFT". In this case "NUMBER" means :

(For this question use annex 033-12280A) When completing Item 9 of the ATS flight plan, if there is no appropriate aircraft designator, the following should be entered :

For the purposes of Item 9 (Wake turbulence category) of the ATS flight plan, an aircraft with a maximum certificated take-off mass of 62000 kg is :

An aircraft has a maximum certificated take-off mass of 137000 kg but is operating at take-off mass 135000 kg. In Item 9 of the ATS flight plan its wake turbulence category is :

(For this question use annex 033-12277A) In the event that SELCAL, is prescribed by an appropriate authority, in which section of the ATS flight plan will the SELCAL code be entered ?

(For this question use annex 033-12276A) In the ATS flight plan Item 15, for a flight along a designated route, where the departure aerodrome is not on or connected to that route :

An operator (turbojet engine) shall ensure that calculation up of usable fuel for a flight for which no destination alternate is required includes, taxi fuel, trip fuel, contingency fuel and fuel to fly for:

(For this question use annex 033-9739A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying VFR from PEITING (47° 48.0"N, 010° 55.5"E) to IMMENSTADT (47° 33.5"N, 010° 13.0"E).Determine the minimum altitude within a corridor 5NM left and 5 NM right of the courseline in order to stay 1000 ft clear of obstacles.

(For this question use annex 033-9738A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying VFR from PEITING (47° 48.0"N, 010° 55.5"E) to IMMENSTADT (47° 33.5"N, 010° 13.0"E) determine the distance.

(For this question use annex 033-12373A or Route Manual chart NAP) The average magnetic course from A (64° N006° E) to C (62° N020° W) is

Mark the correct statement: If a decision point procedure is applied for flight planning,

(For this question use annex 033-3306A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Given: flight time from top of climb to the enroute point in FL280 is 48 min. Cruise procedure is long range cruise (LRC). Temp. ISA -5° C Take-off mass 56 000 kg Climb fuel 1 100 kg Find: distance in nautical air miles (NAM) for this leg and fuel consumption:

(For this question use annex 033-3307A or Flight Planning Manual MRJT 1 Figure 4.5.1) Given: estimated take- off mass 57 500 kg. initial cruise FL 280. average temperature during climb ISA -10° C. average head wind component 18 kt Find: climb time

(For this question use annex 033-9708A or Flight Planning Manual MRJT 1 Figure 4.5.3.2) Planning an IFR-flight from Paris to London for the twin jet aeroplane. Given: Gross mass 50000 kg, FL 280, ISA Deviation -10° C, Cruise procedure Mach 0.74 Determine the TAS

Given : true track 017. W /V 340/30. TAS 420 kt Find : wind correction angle (WCA) and ground speed (GS)

(For this question use annex 033-9701A or Flight Planning Manual MRJT 1 Figure 4.5.1) Planning an IFR-flight from Paris to London for the twin jet aeroplane. Given: Estimated Take- off Mass (TOM) 52000 kg, Airport elevation 387 ft, FL 280, W/V 280° /40 kt, ISA Deviation -10° C, Average True Course 340° Find: Fuel to the top of climb (TOC)

(For this question use annex 033-9700A or Flight Planning Manual MRJT 1 Figure 4.5.1) Planning an IFR-flight from Paris (Charles de Gaulle) to London (Heathrow) for the twin jet aeroplane. Given: Estimated Take- off Mass (TOM) 52000 kg, Airport elevation 387 ft, FL 280, W/V 280° /40 kt, ISA Deviation -10° C, Average True Course 340° Find: Time to the top of climb (TOC)

(For this question use annex 033-9699A and 033-9699B or Flight Planning Manual MRJT 1 Paragraph 5.1 and Figure 4.5.1) Planning an IFR-flight from Paris to London for a twin jet aeroplane. Given: Estimated Take- off Mass (TOM) 52000 kg, Airport elevation 387 ft, FL 280, W/V 280° /40 kt, ISA- Deviation -10° C, Average True Course 340° Find: Ground distance to the top of climb (TOC)

(For this question use annex 033-9698A or Flight Planning Manual MRJT 1 Figure 4.4) Given: twin jet aeroplane, Estimated mass on arrival at the alternate 50000 kg, Elevation at destination aerodrome 3500 ft, Elevation at alternate aerodrome 30 ft Find: Final reserve fuel

(For this question use annex 033-9697A or Flight Planning Manual MRJT 1 Figure 4.4) Given: twin jet aeroplane, Estimated mass on arrival at the alternate 50000 kg, Estimated mass on arrival at the destination 52525 kg, Alternate elevation MSL, Destination elevation 1500 ft Find: Final reserve fuel and corresponding time

(For this question use annex 033-9696A or Flight Planning Manual MRJT 1 Figure 4.3.6) Given: twin jet aeroplane, Dry operating mass 35500 kg, Traffic load 14500 kg, Final reserve fuel 1200 kg, Distance to alternate 95 NM, Tailwind component 10 kt Find: Fuel required and trip time to alternate with simplified flight planning (ALTERNATE PLANNING)

(For this question use annex 033-9695A or Flight Planning Manual MRJT 1 Figure 4.3.3C) Given: Twin jet aeroplane, Ground distance to destination aerodrome is 1600 NM, Headwind component 50 kt, FL 330, Cruise .78 Mach, ISA Deviation +20° C and Landing mass 55000 kg Find: Fuel required and trip time with simplified flight planning

(For this question use annexes 033-9494A and 033-9694B or Flight Planning Manual MRJT 1 Figure 4.5.3.1 and Figure 4.3.1B) Given: twin jet aeroplane, Zero fuel mass 50000 kg, Landing mass at alternate 52000 kg, Final reserve fuel 2000 kg, Alternate fuel 1000 kg, Flight to destination: Distance 720 NM, True course 030° , W/V 340° /30 kt, Long range cruise, FL 330, Outside air temperature -30° C Find: Estimated trip fuel and time with simplified flight planning

Given: Maximum allowable take-off mass 64400 kg, Maximum landing mass 56200 kg, Maximum zero fuel mass 53000 kg, Dry operating mass 35500 kg, Traffic load 14500 kg, Trip fuel 4900 kg, Take-off fuel 7400 kg Find: Maximum additional load

Given: Maximum allowable take-off mass 64400 kg, Maximum landing mass 56200 kg, Maximum zero fuel mass 53000 kg, Dry operating mass 35500 kg, Traffic load 14500 kg, Trip fuel 4900 kg, Minimum Take-off Fuel 7400 kg Find: Maximum allowable take-off fuel

(For this question use annex 033-9691A or Flight Planning Manual MRJT 1 Figure 4.5.3.1) Given: twin jet aeroplane, FL 330, Long range cruise, Outside air temperature -63° C, Gross mass 50500 kg Find: True air speed (TAS)

(For this question use annex 033-12367A or Flight Planning Manual MRJT 1 Figure 4.5.4) A descent is planned at .74/250KIAS from 35000ft to 5000ft. How much fuel will be consumed during this descent?

A repetitive flight plan (RPL) is filed for a scheduled flight: Paris- Orly to Angouleme, Paris Orly as alternate. Following heavy snow falls, Angouleme airport will be closed at the expected time of arrival. The airline decides before departure to plan a re-routing of that flight to Limoges.

An aeroplane flies at an airspeed of 380 kt. lt flies from A to B and back to A. Distance AB = 480 NM. When going from A to B, it experiences a headwind component = 60 kt. The wind remains constant. The duration of the flight will be:

(For this question use annex 033-12366A or Flight Planning Manual MRJT 1 Figure 4.7.2) An aircraft on an extended range operation is required never to be more than 120 minutes from an alternate, based on 1 engine inoperative LRC conditions in ISA. Using the above table and a given mass of 40000 kg at the most critical point, the maximum air distance to the relevant alternate is :

(For this question use annex 033-12368A or Route Manual chart NAP) The average magnetic course from C (62° N020° W) to B (58° N004° E) is

(For this question use annex 033-12369A or Route Manual chart NAP) The average true course from C (62° N020° W) to B (58° N004° E) is

(For this question use annex 033-12370A or Route Manual chart NAP) The initial magnetic course from C (62° N020° W) to B (58° N004° E) is

(For this question use annex 033-12371A or Route Manual chart NAP) The initial true course from C (62° N020° W) to B (58° N004° E) is

(For this question use annex 033-12375A or Route Manual chart NAP) The initial magnetic course from A (64° N006° E) to C (62° N020° W) is

(For this question use annex 033-12365A or Flight Planning Manual MRJT 1 Figure 4.7.2) Using the above table, in ISA conditions and at a speed of M.70/280KIAS, in an elapsed time of 90 minutes an aircraft with mass at point of diversion 48000 kg could divert a distance of :

(For this question use annex 033-12356A or Route Manual chart 5 AT(HI)) The initial great circle course from position A (80° 00"N 170° 00"E) to position B (75° 00"N 011° E) is 177° (G). The final grid course at position B will be :

(For this question use annex 033-9734A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying VFR from VILLINGEN (48° 03.5"N, 008° 27.0"E) to FREUDENSTADT (48° 28.0"N, 008° 24.0"E) determine the magnetic course.

(For this question use annex 033-9735A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying VFR from VILLINGEN (48° 03.5"N, 008° 27.0"E) to FREUDENSTADT (48° 28.0"N, 008° 24.0"E) determine the distance.

(For this question use annex 033-9736A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying VFR from VILLINGEN (48° 03.5"N, 008° 27.0"E) to FREUDENSTADT (48° 28.0"N, 008° 24.0"E).Determine the minimum altitude within a corridor 5NM left and 5 NM right of the courseline in order to stay 1000 ft clear of obstacles.

Given: Dry operating mass (DOM)= 33500 kg Load= 7600 kg Maximum allowable take-off mass= 66200 kg Standard taxi fuel= 200 kg Tank capacity= 16 100 kg The maximum possible take-off fuel is:

The required time for final reserve fuel for turbojet aeroplane is:

How many feet you have to climb to reach FL 75? Given: FL 75. departure aerodrome elevation 1500 ft. QNH = 1023 hPa. temperature = ISA. 1 hPa = 30 ft

VFR flights shall not be flown over the congested areas of cities at a height less than

(For this question use annex 033-12361A or Flight Planning Manual MRJT 1 Figure 4.7.3) Given: Distance to alternate 950 NM Head wind component 20 kt Mass at point of diversion 50000kg Diversion fuel available 5800kg The minimum pressure altitude at which the above conditions may be met is :

(For this question use annex 033-12360A or Flight Planning Manual MRJT 1 Figure 4.7.3) Given: Diversion distance 650 NM Diversion pressure altitude 16 000 ft Mass at point of diversion 57 000 kg Head wind component 20 kt Temperature ISA + 15° C The diversion (a) fuel required and (b) time, are approximately :

(For this question use annex 033-12358A or Flight Planning Manual MRJT 1 Figure 4.7.3) Given: Diversion fuel available 8500kg Diversion cruise altitude 10000ft Mass at point of diversion 62500kg Head wind component 50kt Temperature ISA -5° C The (a) maximum diversion distance, and (b) elapsed time alternate, are approximately :

(For this question use annex 033-12355A or Route Manual chart 5 AT(HI)) The initial great circle true course from Keflavik (64° 00"N 022° 36" W) to Vigra (62° 33"N 006° 02"E) measures 084° . On a polar enroute chart where the grid is aligned with the 000° meridian the initial grid course will be :

(For this question use annex 033-12354A or Route Manual chart NAP) On a direct great circle course from Shannon (52° 43" N 008° 53"W) to Gander (48° 54"N054° 32"W), the (a) average true course, and (b) distance, are :

(For this question use annex 033-12353A or Route Manual chart 5 AT(HI)) On airway PTS P from Vigra (62° 334N 006° 02"E), the initial great circle grid course is :

An aircraft is flying at MACH 0.84 at FL 330. The static air temperature is -48° C and the headwind component 52 Kt. At 1338 UTC the controller requests the pilot to cross the meridian of 030W at 1500 UTC. Given the distance to go is 570 NM, the reduced MACH No. should be:

On a given path, it is possible to chose between four flight levels (FL), each associated with a mandatory flight Mach Number (M). The flight conditions, static air temperature (SAT) and headwind component (HWC) are given below: FL 370 - M = 0.80 Ts = -60° C HWC = - 15 kt FL 330 - M = 0.78 Ts = -60° C HWC= - 5 kt FL 290 - M = 0.80 Ts = -55° C HWC = - 15 kt FL 270 - M = 0.76 Ts = -43° C HWC = The flight level allowing the highest ground speed is:

A twin-jet aeroplane carries out the W ASHINGTON- PARIS flight. When it reaches point K (35° N - 048° W) a non- mechanical event makes the Captain consider rerouting to one of the three following fields. The flight conditions are: - from K to BERMUDAS (distance 847NM, headwind component=18 kt) - from K to SANTA MARIA (distance 1112 NM, tailwind component=120 kt) - from K to GANDER (distance 883 NM, wind component=0). With an aeroplane true airspeed of 460 kt, the field selected will be that more rapidly reached:

(For this question use annex 033-9557A or Flight Planning Manual MRJT 1 Figure 4.5.3.2) Find the FUEL FLOW for the twin jet aeroplane with regard to the following data. Given: MACH .74 cruise, Flight level 310, Gross mass 50000 kg, ISA conditions

(For this question use annex 033-12359A or Flight Planning Manual MRJT 1 Figure 4.7.3) Given: Diversion distance 720NM Tail wind component 25kt Mass at point of diversion 55000kg Temperature ISA Diversion fuel available 4250kg What is the minimum pressure altitude at which the above conditions may be met ?

(For this question use annex 033-12316A ) The W/V (° /kt) at 40° N 020° W is

(For this question use annex 033-12315A) What mean temperature (° C) is likely on a true course of 270° from 025° E to 010° E at 45° N ?

(For this question use annex 033-12314A ) The W/V (° /kt) at 50° N015° W is:

(For this question use annex 033-12318A) The W/V (° /kt) at 60° N015° W is

(For this question use annex 033-11245A and 033-11245B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg distance: 3 500 NM - Flight level FL 310, true airspeed: 450 kt - Headwind component at this level: 5 kt - Initially planned take- off mass (without extra fuel on board): 180 000 kg - Fuel price: 0.35 $/l at departure. 0.315 $/l at destination To maximize savings, the commander chooses to carry extra fuel in addition to that which is necessary. Using the appended annex, the optimum quantity of fuel which should be carried in addition to the prescribed quantity is:

(For this question use annex 033-11244A and 033-11244B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg distance: 4 000 NM - Flight level FL 310, true airspeed: 450 kt - Headwind component at this level: 50 kt - Initially planned take- off mass (without extra fuel on board): 170 000 kg - Fuel price: 0.27 Euro/l at departure. 0.30 Euro/l at destination To maximize savings, the commander chooses to carry extra fuel in addition to that which is necessary. Using the appended annex, the optimum quantity of fuel which should be carried in addition to the prescribed quantity is:

(For this question use annex 033-11243A and 033-11243B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg distance: 3 500 NM - Flight level FL 310, true airspeed: 450 kt - Headwind component at this level: - 55 kt - Initially planned take- off mass (without extra fuel on board): 180 000 kg - Fuel price: 0.30 Euro/l at departure. 0.27 Euro/l at destination To maximize savings, the commander decides to carry extra fuel in addition to that which is necessary. Using the appended annex, the optimum quantity of fuel which should be carried in addition to the prescribed quantity is:

(For this question use annex 033-11241A) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight level FL 370 at "Long Range" (LR) cruise regime - Mass at brake release: 212 800 kg - Flight leg ground distance: 2 500 NM - Temperatures: ISA - CG: 37% - Headwind component: 30 kt - "Total anti-ice" set on "ON" for the entire flight - No requested climb and descent correction of the fuel consumption The fuel consumption (from take-off to landing) is: 1 FRANCE (For this question use 0.29 $/l 0.30 $/l 0.24 $/l 0.28 $/l 0 -1 0 0 annex 033-11240A and 033-11240B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg distance: 3 500 NM - Flight level FL 310, true airspeed: 450 kt - Headwind component at this level: 55 kt - Initially planned take- off mass (without extra fuel on board): 180 000 kg - Fuel price: 0.27 $/l at destination The commander may carry on board 8 000 kg more fuel than that which is necessary. For this fuel transport operation to be cost effective, the maximum fuel price at departure must be: 1 FRANCE (For this question use 0.27 $/l 0.26 $/l 0.28 $/l 0.33 $/l -1 0 0 0 annex 033-11239A and 031-11239B) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight leg distance: 3 500 NM - Flight level FL 310, true airspeed: 450 kt - Headwind component at this level: 55 kt - Initially planned take- off mass (without extra fuel on board): 180 000 kg - Fuel price: 0.30 $/l at departure The commander may carry a fuel quantity of 8 000 kg in addition to that which is necessary. For this fuel transport operation to be cost effective, the maximum fuel price at arrival must be:

(For this question use annex 033-11238A) The flight crew of a turbojet aeroplane prepares a flight using the following data: - Flight level FL 370 at "Long Range" (LR) cruise regime - (Prescribed) mass at brake release: 204 500 kg - Flight leg ground distance: 2 000 NM - Temperatures: ISA - Headwind component: 70 kt - "Total anti-ice" set on "ON" for the entire flight - no requested climb and descent correction of the fuel consumption The fuel required from take-off to landing is:

(For this question use annex 033-12334A ) What is the earliest time (UTC), if any, that thunderstorms are forecast for TUNIS/CARTHAGE ?

(For this question use annex 033-12333A ) Which best describes the weather, if any, at LYON/SATOLAS at 1330 UTC ?

(For this question use annex 033-12332A) The surface wind velocity (° /kt) at PARIS/CHARLES-DE- GAULLE at 1330 UTC was

(For this question use annex 033-12331A ) The lowest cloud conditions (oktas/ft) at BORDEAUX/MERIGNA C at 1330 UTC were

(For this question use annex 033-12335A ) Which is the heaviest type of precipitation, if any, forecast for BORDEAUX/MERIGNA C at 1000 UTC ?

(For this question use annex 033-12319A) The approximate mean wind component (kt) along true course 180° from 50° N to 40° N at 005° W is

(For this question use annex 033-12337A ) What minimum visibility is forecast for PARIS/CHARLES-DE- GAULLE at 2100 UTC ?

(For this question use annex 033-12329A ) What lowest cloud conditions (oktas/ft) are forecast for JOHANNESBURG/JA N SMUTS at 0300 UTC?

(For this question use annex 033-9737A, AERONAUTICAL CHART ICAO 1:500 000 STUTTGART (NO 47/6) or Route Manual VFR+GPS chart ED-6) Flying VFR from PEITING (47° 48.0"N, 010° 55.5"E) to IMMENSTADT (47° 33.5"N, 010° 13.0"E) determine the magnetic course.

(For this question use annex 033-12338A ) Which best describes the weather, if any, forecast for JOHANNESBURG/JA N SMUTS at 0400 UTC?

(For this question use annex 033-12328A ) Over LONDON (51° N000° E/W), the lowest FL listed which is unaffected by CAT is:

(For this question use annex 033-12327A ) The maximum wind velocity (° /kt) immediately north of TUNIS (36° N010° E) is

(For this question use annex 033-12326A ) Which describes the maximum intensity of turbulence, if any, forecast for FL260 over TOULOUSE (44° N001° E) ?

(For this question use annex 033-12325A ) Which best describes the significant cloud forecast over TOULOUSE (44° N001° E) ?

(For this question use annex 033-12324A ) In the vicinity of SHANNON (52° N009° W) the tropopause is at about FL

(For this question use annex 033-12323A ) The surface system over VIENNA (48° N016° E) is a

(For this question use annex 033-12322A ) Which describes the intensity of icing, if any, at FL 150 in the vicinity of TOULOUSE (44° N 01° E) ?

(For this question use annex.033-12321A ) Which best describes the maximum intensity of icing, if any, at FL160 in the vicinity of BERLIN (53° N013° E) ?