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Question 103-1 : Planning an ifr flight from paris charles de gaulle to london .sid is abb 8a assume .variation 3° w .tas 430 kts .w/v 280/40 .distance to top of climb 50 nm .determine the magnetic course ground speed and wind correction angle from top of climb to abb 116 6 . 1503 ? [ Exam pilot ]

Mc 349° gs 414 kts wca 5°

exemple 203 Mc 349°, gs 414 kts, wca -5°.

Question 103-2 : Refer to jeppesen student route manual chart e lo 1 .the minimum en route altitude mea that can be maintained continuously on airway l602 from talla 113 8 tla 55°30 n 003°21 w to newcastle 114 25 new 55°02 n 001°24w is . 1504 ?

Fl200

Img1505 exemple 207 Fl200.

Question 103-3 : 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 6000 kg/h alternate fuel is 4380 kg .contingency should be 5% of trip fuel .what is the minimum required ?

13000 kg

Admin .warning this question indicates contingency should be 5% of trip fuel .normal rules for contingency the greater of 5% of trip or 5 min holding at 1500 ft .we must assume the operator has an exemption .minimum quantity of fuel at take off = trip fuel + alternate + contingency 5% of trip fuel + 30 min final reserve jet aircraft .trip fuel = 5350 kg .alternate = 4380 kg .contingency = 5% of trip fuel .5% x 5350 = 267 kg.30 min final reserve = 6000 /2 = 3000 kg .minimum quantity of fuel at take off = 5350 + 4380 + 267 + 3000 = 12997 kg exemple 211 13000 kg.

Question 103-4 : Using the power setting table for the single engine aeroplane determine the manifold pressure and fuel flow lbs/hr with full throttle and cruise lean mixture in the following conditions .oat +13°c.pressure altitude 8000 ft.rpm 2300 . 2161 ?

22 4 in hg and 69 3 lbs/hr

Admin .first search isa temperature .at 8000 ft oat is +13°c.in standard atmosphere temperature at 8000 ft is 15°c 2°c x 8 = 1°c.we are in isa +14°c.we need now to interpolate between isa and isa +20°c on the table . 1139.isa fuel flow 71 1 pph and man press 22 4 .isa +20°c fuel flow 68 5 pph and man press 22 4 . 71 1 68 5 x 14 / 20 = 1 82. fuel flow = 71 1 1 82 = 69 3 lbs/hr exemple 215 22.4 in.hg and 69.3 lbs/hr.

Question 103-5 : Given the following .head wind component 50 kt.temperature isa +10°c.brake release mass 65000 kg.trip fuel available 18000 kg.what is the maximum possible trip distance . 2363 ?

2740 nm

Admin . 1156 exemple 219 2740 nm.

Question 103-6 : The fuel burn off is 200 kg/h with a relative fuel density of 0 8 .if the relative density is 0 75 the fuel burn will be ?

200 kg/h

Admin .volume changes mass consumption will not change .if they ask for 'litre/hour' instead of 'kg/h' then fuel burn will be 235 l/h exemple 223 200 kg/h.

Question 103-7 : The trip fuel for a jet aeroplane to fly from the departure aerodrome to the destination aerodrome is 5 350 kg fuel consumption in holding mode is 6 000 kg/h .the quantity of fuel which is needed to carry out one go around and land on the alternate airfield is 4 380 kg .the destination aerodrome ?

13 230 kg

Admin .minimum quantity of fuel at take off = trip fuel + alternate + contingency + 30 min final reserve jet aircraft .trip fuel = 5350 kg .alternate = 4380 kg .contingency = the greater of 5% of trip or 5 min holding at 1500 ft .5% of trip = 5% x 5350 = 267 kg.5 min holding at 1500 ft = 6000 x 5/60 = 500 kg .30 min final reserve = 6000 /2 = 3000 kg .minimum quantity of fuel at take off = 5350 + 4380 + 500 + 3000 = 13230 kg exemple 227 13 230 kg.

Question 103-8 : Given .fl 75 oat +10°c lean mixture 2300 rpm .find .fuel flow in gallons per hour gph and tas . 2461 ?

11 6 gph tas 160 kt

Admin .at fl75 in standard atmosphere isa is 15°c 2°c x 7 5 = 0°c .oat is +10°c thus we are at isa +10°c .no need for long interpolations fuel flow is around 11 4 to 12 gph and tas between 158 to 160 kt . 1162 exemple 231 11.6 gph, tas: 160 kt.

Question 103-9 : A public transport aeroplane with reciprocating engines the final reserve should be ?

Fuel to fly for 45 minutes

Eu ops 1 255 fuel policy. . c 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 see eu ops 1 192 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 1 to ops 1 255 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 1 to eu ops 1 255 . . 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 exemple 235 Fuel to fly for 45 minutes.

Question 103-10 : Assuming the following data .ground distance to be covered 1 500 nm.cruise flight level fl 310.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 ?

23 500 kg

Admin .proceed like this .1500 nm / 470kt 40kt = 3 49 h.3 49 x 470 = 1640 nam.on the table to find the corresponding value for 1640 nam you have to interpolate between line 1600 and 1700 nam . 22221 20955 /10 x4 = 506 kg.20955 + 506 = 21461 kg.you must add +1% for pack flow high.and.you have to add +7% for total anti ice on.it means 8% of 21461 = 1717 kg.21461 + 1717 = 23178 kg.we are on isa+15 condition for each degree above isa temperature apply fuel correction 0 010 x 15 x 1640 = 246 kg.23178 + 246 = 23424 kg exemple 239 23 500 kg.

Question 103-11 : For a flight of 2400 ground nautical miles the following apply .tail wind 25 kt.temperature isa 10°c.brake release mass 66000 kg.the a trip fuel and b trip time respectively are . 2463 ?

A 14000 kg b 5h 35 min

Admin . 1169

Question 103-12 : 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 . 1515 ?

1250 kg

Admin . 1173.you have to decrease the fuel by 100 kg as prescribe in the fuel adjustment table exemple 247 1250 kg.

Question 103-13 : 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 ?

34 430 kg

.nam = ngm x tas/gs .nam = 2500 x 470/440 .nam = 2670 nam..212 800 kg is corresponding to 8083 nam in the table . /com en/com033 99 jpg..8083 2670 = 5413 nam..5413 nam is corresponding to 180 329 kg in the table..fuel = 212 800 180 329 = 32 471 kg..fuel consumption with total anti ice 0n = 32 471 x 1 06 = 34 419 kg . renfernandes i still did not understand what do de values on top of the columns 0 2 4 in this case 8 mean i couldn't choose a column unless i knew what they mean .thanks ..mass at brake release is 212 800 kg ==> 212 ton + 0 8 ton .if mass at brake release was 213 600 kg ==> 212 ton + 1 6 ton . miguel .would you be so kind to explain why 5413 are exactly 180 329 kg because i'm trying to calculate it via interpolation but i cannot find a successful result thank you ..180400 180200 = 200 kg.5419 5402 = 17 nam.17 nam for 200 kg.1 nam = 11 8 kg.5419 5413 = 6 nam.6 x 11 8 kg = 71 kg.180400 71 = 180329 kg exemple 251 34 430 kg.

Question 103-14 : The purpose of the decision point procedure is ?

To reduce the minimum required fuel and therefore be able to increase the traffic load

Admin .reduced contingency fuel rcf procedure decision point procedure .this is a technique for increasing the traffic load by reducing the minimum fuel required you reduce the contingency figures by using it only from the decision point to the destination .if an operator's fuel policy includes pre flight planning to a destination 1 aerodrome commercial destination with a reduced contingency fuel procedure using a decision point along the route and a destination 2 aerodrome optional refuel destination the amount of usable fuel on board for departure shall be the greater of 2 1 or 2 2 below .2 1 the sum of . a taxi fuel and. b trip fuel to the destination 1 aerodrome via the decision point and. c contingency fuel equal to not less than 5% of the estimated fuel consumption from the decision point to the destination 1 aerodrome and. d alternate fuel or no alternate fuel if the decision point is at less than six hours from the destination 1 aerodrome are fulfilled and. e final reserve fuel and. f additional fuel and. g extra fuel if required by the commander .2 2 the sum of . a taxi fuel and. b trip fuel to the destination 2 aerodrome via the decision point and. c contingency fuel from departure aerodrome to the destination 2 aerodrome and. d alternate fuel if a destination 2 alternate aerodrome is required and. e final reserve fuel and. f additional fuel and. g extra fuel if required by the commander exemple 255 To reduce the minimum required fuel and therefore be able to increase the traffic load.

Question 103-15 : At reference or see 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 ?

M/kias 74/330

. /com en/com033 120 jpg. exemple 259 M/kias .74/330

Question 103-16 : 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 . oat 3°c. pressure altitude 6000 ft. power 21 in/hg / 2100 rpm . 2155 ?

134 kt and 55 7 lbs/h

Admin .first step search for isa temperature .oat is +3°c isa at 6000 ft = 15°c 2 x 6 = +3°c.we are in standard condition isa .for standard day isa ktas is the same 134 kt .step two search for fuel flow .for standard condition isa fuel flow is 55 7 pph pound per hour or lbs/h exemple 263 134 kt and 55.7 lbs/h.

Question 103-17 : For turbojet engine driven aeroplane given .taxi fuel 600 kg.fuel flow for cruise 10 000 kg/h.fuel flow for holding 8 000 kg/h.alternate fuel 10 200 kg.planned flight time to destination 6 h.forecast visibility at destination 2000 m.the minimum ramp fuel required is ?

77 800 kg

Admin .fuel flow for cruise 6h x 10000 kg = 60000 kg.contingency fuel 5% x 60000 = 3000 kg.taxi fuel 600 kg.alternate fuel 10200 kg.30 minutes fuel for holding at 8000kg/h = 4000 kg.total = 60000 + 3000 + 600 + 10200 + 4000.total = 77800 kg exemple 267 77 800 kg.

Question 103-18 : The following apply .temperature isa +15°c.brake release mass 62000 kg.trip time 5h 20 min .what is the trip fuel . 2180 ?

13500 kg

Admin . 1194.enter the graph at 5 33 5h40 exemple 271 13500 kg.

Question 103-19 : At reference or see flight planning manual mrjt 1 figure 4 3 1c. for a flight of 2800 ground nautical miles the following apply .head wind component 15 kt.temperature isa + 15°c.cruise altitude 35000 ft.landing mass 50000 kg.the a trip fuel and b trip time respectively are . err a 033 146 ?

A 17600 kg b 6 hr 50 min

.first set the red lines on the graph . /com en/com033 146 jpg.reach the ref lines first and after join the red lines .above landing mass on the right part of the graph you have to use the dashed line it is for high pressure alitude flights exemple 275 (a) 17600 kg (b) 6 hr 50 min.

Question 103-20 : 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 ?

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 279 (a) 18100 kg (b) 7hr 20 min

Question 103-21 : 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 283 The trip fuel to the destination aerodrome is to be calculated via the decision point.

Question 103-22 : 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

Admin .trip fuel is trip fuel in the operational flight plan trip fuel is 4300 kg exemple 287 4 300 kg.

Question 103-23 : 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 291 30 minutes holding 1,500 feet above aerodrome b

Question 103-24 : 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

Admin .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 295 8120 kg.

Question 103-25 : 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

Admin .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 299 17 350 kg.

Question 103-26 : 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

Admin . 1224.wind has influence on ground distance but not on the time to reach the top of climb 11 min or fuel flow exemple 303 1000 kg.

Question 103-27 : 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

Admin .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 307 4475 kg.

Question 103-28 : The required time for final reserve fuel for turbojet aeroplane is ?

30 minutes

Admin .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 exemple 311 30 minutes.

Question 103-29 : 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

Admin .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 315 276 lbs.

Question 103-30 : 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 319 14 500 kg.

Question 103-31 : 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 ?

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 323 273 kg.

Question 103-32 : 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 327 Fmp 4%

Question 103-33 : 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 331 Fuel to fly for 30 minutes at holding speed at 1500 ft (450 m) above aerodrome elevation in standard conditions.

Question 103-34 : 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

Admin .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 335 235 l/h.

Question 103-35 : 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° c ?

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 339 6 us gallon.

Question 103-36 : 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 343 Contingency fuel by adding contingency only from the burnoff between decision point and destination.

Question 103-37 : 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 347 30 minutes hold at 1500 ft above destination aerodrome elevation, when no alternate is required.

Question 103-38 : 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 351 1138 kg

Question 103-39 : 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 355 160 kt and 69.3 lbs/h.

Question 103-40 : 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 359 91 us gallons.


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