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Question 117-1 : At reference or see flight planning manual mrjt 1 figure 4.3.5. for a flight of 3500 ground nautical miles, the following apply. tail wind component 50 kt.temperature isa +10°c.brake release mass 65000kg.the a trip fuel and b trip time respectively are .. err a 033 150 ? [ Training professional ]

A 18100 kg b 7hr 20 min

. /com en/com033 150.jpg..you always need to go first to the ref line, and then, apply the condition mass, temperature, wind. exemple 217 (a) 18100 kg (b) 7hr 20 min

Question 117-2 : Mark the correct statement.if a decision point procedure is applied for flight planning ?

The trip fuel to the destination aerodrome is to be calculated via the decision point.

.the decision point procedure permits aircraft to carry less contingency fuel than in the standard case. operators select a point called the decision point along the planned route. at this point, the pilot has two possibilities. reach a suitable proximate diversion airport, taking into account the maximum landing weight limitation,. continue the flight to the destination airport, when the remaining fuel is sufficient. exemple 221 The trip fuel to the destination aerodrome is to be calculated via the decision point.

Question 117-3 : An aeroplane has the following masses.estimated landing weight 50 000 kg.trip fuel 4 300 kg.contingency fuel 215 kg.alternate fuel final reserve included 2 100kg.taxi 500 kg.block fuel 7 115 kg.before departure the captain orders to make the block fuel 9 000 kg..the trip fuel in the operational ?

4 300 kg.

.trip fuel is... trip fuel in the operational flight plan, trip fuel is 4300 kg. exemple 225 4 300 kg.

Question 117-4 : In a flight plan when the destination aerodrome is a and the alternate aerodrome is b, the final reserve fuel for a turbojet engine aeroplane corresponds to ?

30 minutes holding 1,500 feet above aerodrome b

exemple 229 30 minutes holding 1,500 feet above aerodrome b

Question 117-5 : 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, additional fuel of ?

8120 kg.

.isolated aerodrome. if acceptable to the authority, the destination aerodrome can be considered as an isolated aerodrome, if the fuel required diversion plus final to the nearest adequate destination alternate aerodrome is more than..for aeroplanes with reciprocating engines, fuel to fly for 45 minutes plus 15 % of the flight time planned to be spent at cruising level or two hours, whichever is less or.. for aeroplanes with turbine engines, fuel to fly for two hours at normal cruise consumption above the destination aerodrome, including final reserve fuel...2 x 4060 kg = 8120 kg. exemple 233 8120 kg.

Question 117-6 : Given.fuel density = 0,78 kg/l.dry operating mass = 33500 kg.traffic load = 10 600 kg.maximum allowable take off mass = 66200 kg.taxi fuel = 200 kg.tank capacity = 22 500 litres..the maximum possible take off fuel is ?

17 350 kg.

.22500 x 0,78 = 17550 kg..minus 200 kg for taxi, we obtain 17350 kg...we also need to check if our maximum allowable take off mass is not exceeded.mtow > dry operating mass + traffic load + fuel.mtow > 33500 + 10600 + 17550.mtow > 61650 kg..that's ok, maximum possible take off fuel is 17350 kg. exemple 237 17 350 kg.

Question 117-7 : Planning an ifr flight from paris to london for the twin jet aeroplane..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. 2228 ?

1000 kg.

. 1224.wind has influence on ground distance but not on the time to reach the top of climb 11 min or fuel flow.

Question 117-8 : Provided that flight conditions on the leg gamma to delta remain unchanged and fuel consumption remains unchanged, what fuel remaining should be expected at waypoint delta . 2244 ?

4475 kg.

.actual flight time between beta and gamma 35 minutes..actual fuel used 5285 4970 = 315 kg.fuel flow from beta to gamma 315 / 35 = 9 kg/min.fuel used from gamma to delta 55 min x 9 kg = 495 kg..on arrival overhead delta, fuel on board will be.4970 495 = 4475 kg. exemple 245 4475 kg.

Question 117-9 : The required time for final reserve fuel for turbojet aeroplane is ?

30 minutes.

.an operator shall ensure that the pre flight calculation of usable fuel required for a flight includes.1. taxi fuel and.2. trip fuel and.3. reserve fuel consisting of.. i contingency fuel and.. ii alternate fuel, if a destination alternate aerodrome is required. this does not preclude selection of the departure aerodrome as the destination alternate aerodrome and.. iii final reserve fuel see appendix below and.. iv additional fuel, if required by the type of operation e.g. etops and..4. extra fuel if required by the commander....appendix. final reserve fuel, which shall be.. a for aeroplanes with reciprocating engines, fuel to fly for 45 minutes or.. b for aeroplanes with turbine engines, fuel to fly for 30 minutes at holding speed at 1 500 ft 450 m above aerodrome elevation in standard conditions, calculated with the estimated mass on arrival at the destination alternate aerodrome or the destination aerodrome, when no destination alternate aerodrome is required.

Question 117-10 : A flight has to be made with a single engine aeroplane..for the fuel calculation allow 10 lbs fuel for start up and taxi.3 minutes and 6 lbs of additional fuel to allow for the climb.10 minutes and no fuel correction for the descent..planned flight time overhead to overhead is 02 hours and 37 ?

276 lbs.

.total flight time.2h37 + 3 min + 10 min = 2h50 2.83h..fuel comsumption at fl50 isa is. 69.4+71.7 /2 = 70.55 pph..2.83h x 70.55 = 200 pph..200 + 6 lbs for the climb + reserve fuel 30% of 200 + 10 for taxi = 276 lbs. exemple 253 276 lbs.

Question 117-11 : See flight planning manual mrjt 1 figure 4.5.2 and 4.5.3.1.given.distance c d 3200 nm.long range cruise at fl 340.temperature deviation from isa +12°c.tailwind component 50 kt.gross mass at c 55 000 kg.the fuel required from c d is .. err a 033 298 ?

14 500 kg.

For 55000 kg we have a tas of 431 kt, temperature is isa +12, we have to increase tas by 1 kt per degrees above isa, so tas = 431 + 12 = 443 kt...nam = ground distance x tas/gs.nam = 3200 x 443/493 = 2875 nam...at line 55000, the cruise distance nautical air miles is 4151 nautique air miles. substract 2875, you find 1276 nam...what is the mass for 1276 nm. /com en/com033 298.jpg..we find 40600 kg this is our end mass..55000 40600 = 14400 kg...last step, we have to increase fuel required by 0.6 percent per 10 degrees above isa.14400 x 0.6% = 14486 kg....see section 5.4.2 method on caa cap697 flight planning manual, for that kind of questions. exemple 257 14 500 kg.

Question 117-12 : At reference or see flight planning manual mrjt 1 figure 4.5.4.planning an ifr flight from paris to london for the twin jet aeroplane..given.estimated landing mass 49700 kg.fl 280.w/v 280°/40 kt.average true course 320°.procedure for descent.74 m/250 kias.the fuel consumption from the top of descent ?

273 kg.

. /com en/com033 317.jpg..no need for calculation, our fuel consumption will be between 270 kg and 275 kg..wind has influence on ground distance but not on the descent time 19 min or fuel flow. exemple 261 273 kg.

Question 117-13 : At reference or see flight planning manual mrjt 1 paragraph 2.1 and figure 4.1.given.long range cruise.cruise mass 53000 kg.fl 310.find the fuel mileage penalty fmp for the twin jet aeroplane with regard to the given flight level.. err a 033 324 ?

Fmp 4%

. /com en/com033 324.jpg.. exemple 265 Fmp 4%

Question 117-14 : The final reserve fuel for aeroplanes with turbine engines is ?

Fuel to fly for 30 minutes at holding speed at 1500 ft 450 m above aerodrome elevation in standard conditions.

exemple 269 Fuel to fly for 30 minutes at holding speed at 1500 ft (450 m) above aerodrome elevation in standard conditions.

Question 117-15 : The fuel burn of an aircraft turbine engine is 220 l/h with a fuel density of 0.80..if the density is 0.75, the fuel burn will be ?

235 l/h.

.volume changes if temperature changes, mass consumption will not change...the fuel burn is 220 l/h, in mass it is 176 kg/h. it will remain the same mass if temperature increases, but the volume will be higher...220 x 0.8 / 0.75 = 235 l/h. exemple 273 235 l/h.

Question 117-16 : At reference or see flight planning manual mep1 figure 3.1.a flight is to be made from one airport elevation 3000 ft to another in a multi engine piston aireroplane mep1..the cruising level will be fl 110..the temperature at fl 110 is isa 10° c..the temperature at the departure aerodrome is 1° ?

6 us gallon.

Isa temperature at fl110 is.15°c 2°c x 11 = 7°c..outside air temperature at fl110 is 10°c + 7°c = 17°c... /com en/com033 358.jpg..fuel to climb from 3000 ft to 11000 ft = 9.5 3.5 = 6 us gallon. exemple 277 6 us gallon.

Question 117-17 : When using decision point procedure, you reduce the ?

Contingency fuel by adding contingency only from the burnoff between decision point and destination.

.the decision point procedure is a specific set of fuel planning rules which you apply in the pre flight planning phase. it makes use of an en route alternate, and it tells you to calculate the fuel requirement in two different ways, and take the higher of those two fuel figures....you will need approval from the authority to use this procedure, and the overall result in this method of planning will be a reduction of the minimum fuel requirement through a reduction of contingency fuel. exemple 281 Contingency fuel by adding contingency only from the burnoff between decision point and destination.

Question 117-18 : A jet aeroplane is to fly from a to b. the minimum final reserve fuel must allow for ?

30 minutes hold at 1500 ft above destination aerodrome elevation, when no alternate is required.

Caestudent06.if no alternate is required, 15 minutes extra reserve fuel must be taken, above the 30 minutes... .you are right, final reserve fuel for a jet is always 30 minutes at 1500 ft above the aerodrome elevation at holding speed..15 minutes extra reserve fuel additional fuel is mandatory if there is no alternate at destination, above the final reserve fuel of 30 minutes. exemple 285 30 minutes hold at 1500 ft above destination aerodrome elevation, when no alternate is required.

Question 117-19 : At reference or see 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.. err a 033 411 ?

1138 kg

. /com en/com033 411.jpg..extrapolate fuel for a mass of 57000 kg. 1150 + 1100 / 2 = 1125 kg..extrapolate fuel for a mass of 57500 kg. 1150 + 1125 / 2 = 1137.5 kg..wind has an effect on ground distance only, not for fuel consumption. exemple 289 1138 kg

Question 117-20 : At reference or see flight planning manual sep 1 figure 2.2 table 2.2.3.using the power setting table, for the single engine aeroplane, determine the cruise tas and fuel flow lbs/h with full throttle and cruise lean mixture in the following conditions.given.oat 13°c.pressure altitude 8000 ft.rpm ?

160 kt and 69.3 lbs/h.

.first step, search for isa temperature.oat is +13°c, isa at 8000 ft = 15°c 2 x 8 = 1°c.we are in isa +14°c...for standard day isa and isa +20°c, ktas is the same 160 kt...seconde step, search for fuel flow.for standard day isa , fuel flow is 71.1 pph.for isa +20°c, fuel flow is 68.5 pph..interpolation for isa +14°c is. 71.1 68.5 x 6/20 = 0.8.fuel flow is 68.5 + 0.8 = 69.3 pph. exemple 293 160 kt and 69.3 lbs/h.

Question 117-21 : At reference or see flight planning manual mep 1 figure 3.3.a flight has to be made with a multi engine piston aeroplane mep 1..for the fuel calculations take 5 us gallons for the taxi, and an additional 13 minutes at cruise condition to account for climb and descent..calculated time overhead to ?

91 us gallons.

.from the table, fuel flow in us gallons per hour is 23.3 gph..2h37 + 13min = 2h50 = 2.83 hours...23.3 x 2.83 = 65.93 usg...reserve fuel is 30% of the trip fuel..65.93 x 1.30 = 85.7 usg....minimum block fuel 85.7 + 5 usg for taxi = 90.7 usg... moonen .i found 118 us gallons, the power setting is 65% and if i read the table 23.3 gph is for 45% and this is the good response, can you explain to me. thank you....we are looking for fuel flow, not manifold pressure... /com en/com033 456.jpg.. exemple 297 91 us gallons.

Question 117-22 : Integrated range' curves or tables are presented in the aeroplane operations manuals. their purpose is ?

To determine the fuel consumption for a certain still air distance considering the decreasing fuel flow with decreasing mass.

exemple 301 To determine the fuel consumption for a certain still air distance considering the decreasing fuel flow with decreasing mass.

Question 117-23 : At reference or see flight planning manual sep 1 figure 2.4..using the range profile diagramm, for the single engine aeroplane, determine the range, with 45 minutes reserve, in the following conditions.given.oat isa +16°c.pressure altitude 4000 ft.power full throttle / 25.0 in/hg/ 2100 rpm.. err a ?

865 nm.

. /com en/com033 491.jpg.. exemple 305 865 nm.

Question 117-24 : At reference or see 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.. err a 033 493 ?

Pressure altitude, aeroplane mass and flaps up with minimum drag airspeed

exemple 309 Pressure altitude, aeroplane mass and flaps up with minimum drag airspeed

Question 117-25 : 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... err a 033 509 ?

Atc endurance 04 07

. /com en/com033 509.jpg..contingency is 5% of the planned trip fuel = 290 kg.final reserve for a jet aeroplane is 30 minutes...minimum take off fuel = 5800 + 290 + 1800 + 1325 = 9215 kg..fuel flow for extra fuel is 2400 kg/h, so 585 kg gives 14 minutes 38 seconds. exemple 313 Atc endurance: 04:07

Question 117-26 : Given.oat +5°c.during climb average head wind component 20 kt.take off from msl with the initial mass of 3 650 lbs.find time and fuel to climb to fl75. 2464 ?

9 min. 3,3 usg

. 2465 exemple 317 9 min. 3,3 usg

Question 117-27 : Maximum allowable take off mass 64 400 kg.maximum landing mass 56 200 kg.maximum zero fuel mass 53 000 kg.dry operating mass 35 500 kg.estimated load 14 500 kg.estimated trip fuel 4 900kg.minimum take off fuel 7 400 kg.find the maximum allowable take off fuel ?

11 100 kg.

.in order to find the maximum allowable take off fuel, we must consider the mtow maximum take off weight and the mlw maximum landing weight....mtow = dry operating mass + estimated load + maximum take off fuel..64400 = 35500 + 14500 + maximum take off fuel..maximum take off fuel = 14400 kg..mlw = dry operating mass + estimated load + maximum landing fuel..56200 = 35500 + 14500 + maximum landing fuel..maximum landing fuel = 6200 kg..4900 kg trip fuel + 6200 kg = 11100 kg..11100 kg is the lower limitation. exemple 321 11 100 kg.

Question 117-28 : At reference or use flight planning manual sep 1 table 2.2.3..given.fl 70.oat 19°c.lean mixture 2300 rpm..find fuel flow in gallons per hour gph and tas .. err a 033 536 ?

12.35 gph, tas 159 kt.

.no need for calculation.. /com en/com033 536.jpg.. exemple 325 12.35 gph, tas: 159 kt.

Question 117-29 : At reference or see 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 ?

345 nam. 2000 kg

56000 1100 = 54900 kg on table, tas is 437 kt...adjustments for operation at non standard temperatures states to decrease tas by 1 knot per degree celsius below isa..isa 5°c > tas = 432 kt...tas x 48/60 = 345.6 nam...on table, 54900 > 3736 346 = 3390..we can read for 3390 by interpolation 52900 kg..54900 52900 = 2000 kg...see section 5.4.2 method on caa cap697 flight planning manual, for that kind of questions. exemple 329 345 namxsx 2000 kg

Question 117-30 : 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 ?

51 629 kg.

Take off mass = dry operating mass + traffic load + fuel trip + contingency + alternate + final reserve..contingency fuel is the higher of 5% of trip or 5 minutes holding at 1500ft..5% of trip = 90 kg..5 minutes holding at 1500 ft = 204 kg..the question states holding fuel final reserve 1 225 kg.holding fuel for a jet aircraft is 30 minutes at holding speed at 1500 ft above aerodrome elevation..contingency = 1225/30 x 5 = 204 kg...34000 + 13000 + 1800 + 204 + 1400 + 1225 = 51629 kg.... fuel policy.contingency fuel, which shall be the higher of i or ii below.. i either..5% of the planned trip fuel or, in the event of in flight replanning, 5% of the trip fuel for the remainder of the flight... ii an amount to fly for 5 minutes at holding speed at 1 500 ft 450 m , above the destination aerodrome in standard conditions...note baggage mass is already included in traffic load..traffic load is the total mass of passengers, baggage and cargo, including any non revenue load. exemple 333 51 629 kg.

Question 117-31 : You are to determine the maximum fuel load which can be carried in the following conditions. dry operating mass 2800 kg. trip fuel 300 kg. payload 400 kg. maximum take off mass 4200 kg. maximum landing mass 3700 kg ?

800 kg.

. /com en/com033 548.jpg..we can take off with 1000 kg, but we can land only after having burn 500 kg... if not, we will be over weight..the question states that trip fuel is 300 kg, it means that we can take off with 800 kg 500 kg + 300 kg and then, we will land at our maximum landing mass. exemple 337 800 kg.

Question 117-32 : At reference or see flight planning manual mrjt 1 figure 4.5.1.given.brake release mass 62000 kg.temperature isa +15°c.the fuel required for a climb from sea level to fl330 is.. err a 033 549 ?

1700 kg.

. /com en/com033 549.jpg.. exemple 341 1700 kg.

Question 117-33 : At reference or see flight planning manual sep 1 figure 2.1. given.take off mass 3500 lbs.departure aerodrome pressure altitude 2500 ft.oat +10°c.first cruising level fl 140.oat 5°c.find the time, fuel and still air distance to climb... err a 033 557 ?

22 min, 6.7 gal, 45 nam

. /com en/com033 557.jpg.. exemple 345 22 min, 6.7 gal, 45 nam

Question 117-34 : At reference or see flight planning manual sep1 figure 2.2 table 2.2.3.a flight has to be made with the single engine sample aeroplane.for the fuel calculation allow 10 lbs fuel for start up and taxi..3 minutes and 10 lbs of additional fuel to allow for the climb..10 minutes and no fuel correction ?

325 lbs.

..total flight time..3h32 + 3 min + 10 min = 3h45 3.42h...fuel comsumption at fl70 isa +20°c is.. 68.5+69 /2 = 68.75 pph....3.42h x 68.75 = 235 pph....235 + 10 lbs for the climb + reserve fuel 30% of 235 + 10 for taxi = 325 lbs. exemple 349 325 lbs.

Question 117-35 : A flight has to be made with a multi engine piston aeroplane mep 1. for the fuel calculations take 5 us gallons for the taxi, and an additional 13 min at cruise condition to account for climb and descent. calculated time from overhead.to overhead is 1h 47 min..powersetting is 45%, 2600 ?

47 us gallons.

exemple 353 47 us gallons.

Question 117-36 : A flight has to be made with the sep. for the fuel calculation.allow. 10 lbs fuel for start up and taxi. 3 min additional fuel for the climb. 10 min additional fuel for the descent. planned flight time overhead to overhead is 3h 12 min. reserve fuel 30% of the trip fuel. power setting is 25 inch hg ?

359 lbs.

exemple 357 359 lbs.

Question 117-37 : A flight has to be made with the sep1. for the fuel calculation allow. 10 lbs fuel for start up and taxi. 3 min and 1 gallon of additional fuel to allow for the climb. 10 min and no fuel correction for the descent. planned flight time overhead to overhead is 3h 12. reserve fuel 30% of the trip fuel. ?

297 lbs.

exemple 361 297 lbs.

Question 117-38 : Given.dry operating mass 33500 kg.traffic load 7600 kg.maximum allowable takeoff mass 66200 kg.taxi fuel 200 kg.tank capacity 16100 kg.the maximum possible takeoff fuel is ?

15900 kg.

exemple 365 15900 kg.

Question 117-39 : Given.brake release mass 58 000 kg.temperature isa 15.the fuel required to climb from an aerodrome at elevation 4000 ft to fl300 is. 1514 ?

1150 kg.

exemple 369 1150 kg.

Question 117-40 : Given.distance from departure to destination 500 nm.true track 090°.wind 090°/20kt.tas 150 kt.what is the distance and time of the pet from the departure point ?

Distance 283 nm, time 131 min.

Ground speed out 130 kt.ground speed home 170 kt..pet = d x gsh / gso + gsh.pet = 500 x 170 / 130 + 170 = 283 nm. exemple 373 Distance: 283 nm, time: 131 min.


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