Question 117-1 : At reference or see flight planning manual mrjt 1 figure 431c for a flight of 2800 ground nautical miles the following apply head wind component 15 kttemperature isa + 15°ccruise altitude 35000 ftlanding mass 50000 kgthe a trip fuel and b trip time respectively are err a 033 146 ? [ Training professional ]

Question 117-2 : At reference or see flight planning manual mrjt 1 figure 435 for a flight of 3500 ground nautical miles the following apply tail wind component 50 kttemperature isa +10°cbrake release mass 65000kgthe a trip fuel and b trip time respectively are err a 033 150 ?

A 18100 kg b 7hr 20 min.

com encom033 150jpgyou always need to go first to the ref line and then apply the condition mass temperature wind

Question 117-3 : 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

Question 117-4 : An aeroplane has the following masses estimated landing weight 50 000 kgtrip fuel 4 300 kgcontingency fuel 215 kgalternate fuel final reserve included 2 100kgtaxi 500 kgblock fuel 7 115 kg before departure the captain orders to make the block fuel 9 000 kgthe trip fuel in the operational flight ?

4 300 kg.

Trip fuel is trip fuel in the operational flight plan trip fuel is 4300 kg

Question 117-5 : 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 1500 feet above aerodrome b.

Question 117-6 : A jet aeroplane has a cruising fuel consumption of 4060 kgh and 3690 kgh 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

Question 117-7 : Given fuel density = 078 kgl 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 litresthe maximum possible take off fuel is ?

Question 117-8 : Planning an ifr flight from paris to london for the twin jet aeroplaneestimated take off mass tom 52000 kgairport elevation 387 ftfl 280wv 280°40 ktisa deviation 10°caverage true course 340°find fuel to the top of climb toc 2228 ?

1000 kg.

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

Question 117-9 : 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 ?

Question 117-10 : 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 and2 trip fuel and3 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 eg etops and4 extra fuel if required by the commanderappendix 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 117-11 : A flight has to be made with a single engine aeroplane for the fuel calculation allow 10 lbs fuel for start up and taxi3 minutes and 6 lbs of additional fuel to allow for the climb10 minutes and no fuel correction for the descent planned flight time overhead to overhead is 02 hours and 37 minutes ?

276 lbs.

Total flight time 2h37 + 3 min + 10 min = 2h50 283h fuel comsumption at fl50 isa is 694+717 2 = 7055 pph283h x 7055 = 200 pph200 + 6 lbs for the climb + reserve fuel 30% of 200 + 10 for taxi = 276 lbs

Question 117-12 : See flight planning manual mrjt 1 figure 452 and 4531given distance c d 3200 nmlong range cruise at fl 340temperature deviation from isa +12°ctailwind component 50 ktgross mass at c 55 000 kgthe 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 ktnam = ground distance x tasgs nam = 3200 x 443493 = 2875 namat line 55000 the cruise distance nautical air miles is 4151 nautique air miles substract 2875 you find 1276 namwhat is the mass for 1276 nm com encom033 298jpgwe find 40600 kg this is our end mass 55000 40600 = 14400 kglast step we have to increase fuel required by 06 percent per 10 degrees above isa 14400 x 06% = 14486 kgsee section 542 method on caa cap697 flight planning manual for that kind of questions

Question 117-13 : At reference or see flight planning manual mrjt 1 figure 454planning an ifr flight from paris to london for the twin jet aeroplanegiven estimated landing mass 49700 kgfl 280wv 280°40 ktaverage true course 320°procedure for descent 74 m250 kiasthe fuel consumption from the top of descent to london ?

273 kg.

com encom033 317jpgno need for calculation our fuel consumption will be between 270 kg and 275 kgwind has influence on ground distance but not on the descent time 19 min or fuel flow

Question 117-14 : At reference or see flight planning manual mrjt 1 paragraph 21 and figure 41given long range cruisecruise mass 53000 kgfl 310find the fuel mileage penalty fmp for the twin jet aeroplane with regard to the given flight level err a 033 324 ?

Fmp 4%.

com encom033 324jpg

Question 117-15 : 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.

Question 117-16 : The fuel burn of an aircraft turbine engine is 220 lh with a fuel density of 080 if the density is 075 the fuel burn will be ?

235 lh.

Volume changes if temperature changes mass consumption will not changethe fuel burn is 220 lh in mass it is 176 kgh it will remain the same mass if temperature increases but the volume will be higher220 x 08 075 = 235 lh

Question 117-17 : At reference or see flight planning manual mep1 figure 31a 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 110the temperature at fl 110 is isa 10° c the temperature at the departure aerodrome is 1° ccalculate ?

6 us gallon.

Isa temperature at fl110 is 15°c 2°c x 11 = 7°coutside air temperature at fl110 is 10°c + 7°c = 17°c com encom033 358jpgfuel to climb from 3000 ft to 11000 ft = 95 35 = 6 us gallon

Question 117-18 : 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 figuresyou 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

Question 117-19 : 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

Question 117-20 : At reference or see flight planning manual mrjt 1 figure 451 given brake release mass 57500 kgtemperature isa 10°c average headwind component 16 ktinitial fl 280find climb fuel for enroute climb 28074 err a 033 411 ?

1138 kg.

com encom033 411jpgextrapolate fuel for a mass of 57000 kg 1150 + 1100 2 = 1125 kgextrapolate fuel for a mass of 57500 kg 1150 + 1125 2 = 11375 kgwind has an effect on ground distance only not for fuel consumption

Question 117-21 : At reference or see flight planning manual sep 1 figure 22 table 223using the power setting table for the single engine aeroplane determine the cruise tas and fuel flow lbsh with full throttle and cruise lean mixture in the following conditions given oat 13°cpressure altitude 8000 ftrpm 2300 err a ?

160 kt and 693 lbsh.

First step search for isa temperature oat is +13°c isa at 8000 ft = 15°c 2 x 8 = 1°cwe are in isa +14°cfor 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 711 pphfor isa +20°c fuel flow is 685 pphinterpolation for isa +14°c is 711 685 x 620 = 08fuel flow is 685 + 08 = 693 pph

Question 117-22 : At reference or see flight planning manual mep 1 figure 33a 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 descentcalculated time overhead to overhead ?

91 us gallons.

From the table fuel flow in us gallons per hour is 233 gph2h37 + 13min = 2h50 = 283 hours233 x 283 = 6593 usgreserve fuel is 30% of the trip fuel 6593 x 130 = 857 usgminimum block fuel 857 + 5 usg for taxi = 907 usg moonen i found 118 us gallons the power setting is 65% and if i read the table 233 gph is for 45% and this is the good response can you explain to me thank youwe are looking for fuel flow not manifold pressure com encom033 456jpg

Question 117-23 : 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.

Question 117-24 : At reference or see flight planning manual sep 1 figure 24using the range profile diagramm for the single engine aeroplane determine the range with 45 minutes reserve in the following conditions given oat isa +16°cpressure altitude 4000 ftpower full throttle 250 inhg 2100 rpm err a 033 491 ?

865 nm.

com encom033 491jpg

Question 117-25 : At reference or see flight planning manual mrjt 1 figure 44 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.

Question 117-26 : Finish the endurancefuel 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 kgh err a 033 509 ?

Atc endurance 04 07.

com encom033 509jpgcontingency is 5% of the planned trip fuel = 290 kgfinal reserve for a jet aeroplane is 30 minutesminimum take off fuel = 5800 + 290 + 1800 + 1325 = 9215 kgfuel flow for extra fuel is 2400 kgh so 585 kg gives 14 minutes 38 seconds

Question 117-27 : Given oat +5°cduring climb average head wind component 20 kttake off from msl with the initial mass of 3 650 lbsfind time and fuel to climb to fl75 2464 ?

9 min 33 usg.

2465

Question 117-28 : Maximum allowable take off mass 64 400 kgmaximum landing mass 56 200 kgmaximum zero fuel mass 53 000 kgdry operating mass 35 500 kgestimated load 14 500 kgestimated trip fuel 4 900kgminimum take off fuel 7 400 kgfind 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 fuel64400 = 35500 + 14500 + maximum take off fuelmaximum take off fuel = 14400 kgmlw = dry operating mass + estimated load + maximum landing fuel56200 = 35500 + 14500 + maximum landing fuelmaximum landing fuel = 6200 kg4900 kg trip fuel + 6200 kg = 11100 kg11100 kg is the lower limitation

Question 117-29 : At reference or use flight planning manual sep 1 table 223given fl 70oat 19°clean mixture 2300 rpmfind fuel flow in gallons per hour gph and tas err a 033 536 ?

1235 gph tas 159 kt.

No need for calculation com encom033 536jpg

Question 117-30 : At reference or see flight planning manual mrjt 1 figure 4531 given flight time from top of climb to the enroute point in fl280 is 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 ?

345 nam 2000 kg.

56000 1100 = 54900 kg on table tas is 437 ktadjustments for operation at non standard temperatures states to decrease tas by 1 knot per degree celsius below isa isa 5°c > tas = 432 kttas x 4860 = 3456 namon table 54900 > 3736 346 = 3390we can read for 3390 by interpolation 52900 kg54900 52900 = 2000 kgsee section 542 method on caa cap697 flight planning manual for that kind of questions

Question 117-31 : Planning a flight from paris charles de gaulle to london heathrow for a twin jet aeroplanepreplanning maximum take off mass 62 800 kgmaximum zero fuel mass 51 250 kgmaximum landing mass 54 900 kgmaximum taxi mass 63 050 kgassume the following preplanning results trip fuel 1 800 kgalternate fuel 1 ?

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 kg5 minutes holding at 1500 ft = 204 kgthe 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 elevationcontingency = 122530 x 5 = 204 kg34000 + 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 conditionsnote baggage mass is already included in traffic loadtraffic load is the total mass of passengers baggage and cargo including any non revenue load

Question 117-32 : 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 encom033 548jpgwe can take off with 1000 kg but we can land only after having burn 500 kg if not we will be over weightthe 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

Question 117-33 : At reference or see flight planning manual mrjt 1 figure 451given brake release mass 62000 kgtemperature isa +15°cthe fuel required for a climb from sea level to fl330 is err a 033 549 ?

1700 kg.

com encom033 549jpg

Question 117-34 : At reference or see flight planning manual sep 1 figure 21 given take off mass 3500 lbsdeparture aerodrome pressure altitude 2500 ftoat +10°cfirst cruising level fl 140oat 5°cfind the time fuel and still air distance to climb err a 033 557 ?

22 min 67 gal 45 nam.

com encom033 557jpg

Question 117-35 : At reference or see flight planning manual sep1 figure 22 table 223a flight has to be made with the single engine sample aeroplanefor the fuel calculation allow 10 lbs fuel for start up and taxi3 minutes and 10 lbs of additional fuel to allow for the climb10 minutes and no fuel correction for the ?

325 lbs.

Total flight time 3h12 + 3 min + 10 min = 3h25 342h fuel comsumption at fl70 isa +20°c is 685+69 2 = 6875 pph342h x 6875 = 235 pph235 + 10 lbs for the climb + reserve fuel 30% of 235 + 10 for taxi = 325 lbs

Question 117-36 : 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 minpowersetting is 45% 2600 rpmcalculated ?

47 us gallons.

Question 117-37 : 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 or ?

359 lbs.

Question 117-38 : 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.

Question 117-39 : 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.

Question 117-40 : Given brake release mass 58 000 kgtemperature isa 15the fuel required to climb from an aerodrome at elevation 4000 ft to fl300 is 1514 ?

1150 kg.