FPL 03

[FPL-PT03 #1] Refer to your Jeppesen GSPRM IFR Chart E(LO)2 and CAP 697, Fig. 4.3.1 (select the correct version).Your planned route is from Shannon Airport, Republic of Ireland (EINN) via SHA VOR/DME - V14 - DUB VOR/DME - L975 - WAL VOR/DME - Y53 - PEDIG - DCT East Midlands Airport, England (EGNX).Forecast conditions are a 25 kt headwind component, a cruising altitude of FL330, a landing weight of 50 000 kg and a temperature of ISA +10°C.What is the trip fuel and time?(Note: Ignore the altitude limitations of the E(LO) chart) A) 2640 kg and 54 min. B) 2280 kg and 54 min. C) 2020 kg and 57 min. D) 2140 kg and 69 min.

[FPL-PT03 #2] Refer to CAP 697, Fig. 4.4.Given a landing weight at destination of 50 000 kg; a destination airport elevation of 2200 ft, a QNH of 1015 hPa, a required landing weight at the alternate airport of 46 000 kg an alternate airport elevation of 3100 ft amsl and a QNH of 998 hPa, calculate the final reserve fuel. A) 1110 kg. B) 2140 kg. C) 1070 kg. D) 2220 kg.

[FPL-PT03 #3] Given the following data, what is the maximum extra fuel that may be uplifted?Maximum Zero Fuel Mass: 155 000 kgMaximum Take-off Mass: 210 000 kgMaximum Landing Mass: 175 000 kgPlanned ZFM: 155 000 kgTake-off Fuel: 48 600 kgTrip Fuel: 42 500 kgFuel tank capacity = 65 000 litres.Jet Fuel A-1 Specific Gravity = 0.82.Each 1000 kg extra in mass incurs fuel penalty values of:TOM: +260 kgLDM: +370 kg. A) 13 900 kg. B) 5720 kg. C) 6400 kg. D) 4700 kg.

[FPL-PT03 #4] Refer to CAP 697, Fig. 4.1 Optimum Altitude.With a brake release weight of 52 000 kg, and using the M 0.74 cruise reference, what is the optimum pressure altitude? A) 34 000 ft B) 37 000 ft. C) 35 000 ft. D) 36 000 ft.

[FPL-PT03 #5] Refer to your Jeppesen GSPRM IFR Chart E(LO)2 and CAP 697, Fig. 4.2.You are tasked with making an urgent freight delivery between Knock Airport, Republic of Ireland (EIKN) and Edinburgh Airport, Scotland (EGPH), routing via the BELFAST VOR/DME (BEL). The Brake Release Weight is 62 500 kg. Outside air temperature is ISA +25°C. What is the short distance cruise altitude? A) 30 000 ft. B) 26 000 ft. C) 28 000 ft. D) 24 000 ft.

[FPL-PT03 #6] Which of the following equations is correct for solving the relationship between nautical air miles and nautical ground miles? A) GS = (TAS x NAM) ÷ NGM B) NGM = (TAS x NAM) ÷ GS C) NAM = (NGM x GS) ÷ TAS D) TAS = GS x (NAM ÷ NGM)

[FPL-PT03 #7] Refer to your Jeppesen GSPRM IFR Chart E(LO)1 and CAP 697, Figure 4.5.1.An aircraft is departing Fagernes airport, Norway (N61°00' E009°15') and climbs to an initial cruising altitude of FL250. OAT = ISA -5°C. QNH = 1003 hPa. Given a brake release weight of 56 000 kg and a 40 kt tailwind component, what is the time, fuel, ground distance and TAS for the climb? A) 10 min, 925 kg, 56 NM, 349 kt. B) 10 min, 1000 kg, 50 NM, 349 kt. C) 9 min, 825 kg, 35 NM, 339 kt. D) 9 min, 900 kg, 39 NM, 339 kt.

[FPL-PT03 #8] Refer to your Jeppesen GSPRM IFR Chart E(LO)4 and CAP 697, Figure 4.5.3.1.An aircraft crosses NANTES ATLANTIQUE VOR/DME (NTS) (N42°10' W001°35') at FL 300 and at LRC speed, with an aircraft mass of 48 600 kg, en-route along A25 to BORDEAUX VOR/DME (BMC). Given a 50 kt tailwind and ISA +10°C, what is the fuel required between NTS and BMC? A) 1280 kg. B) 850 kg. C) 795 kg. D) 705 kg.

[FPL-PT03 #9] Refer to your Jeppesen GSPRM IFR Chart E(HI)11 and CAP 697, Figure 4.5.3.2.An aircraft crosses TORINO VOR/DME (TOP) at FL 350 at M0.74, with an aircraft mass of 52 500 kg, en-route along M730 via GENOA VOR/DME (GEN) (N44°25' E009°05'), FRZ and ANC to SPLIT VOR/DME (SPL). Given a 60 kt headwind and ISA -20°C, what is the fuel required between GEN and SPL? A) 2350 kg. B) 1976 kg. C) 2000 kg. D) 2322 kg.

[FPL-PT03 #10] Refer to your CAP 696 Figure 4.5.4Given: Economy descent profile, TOD at FL 310 descending to an airport 600 ft amsl. QNH = 1033 hPa. Estimated landing weight = 40 000 kg, and a 20kt tailwind component. What is the time, fuel and distance for the descent? A) 20 min, 280 kg, 95 NGM. B) 20 min, 280 kg, 103 NGM. C) 20 min, 280 kg, 88 NGM. D) 20 min, 280 kg, 81 NGM.

[FPL-PT03 #11] Refer to your Jeppesen GSPRM IFR Chart E(HI)2.Routing from London Gatwick Airport, England to Paris Charles de Gaulle Airport, France via, GWC and DVL along route UN859 at FL250, what frequency would you contact, in the vicinity of DVL? A) 128.870 MHz B) 134.410 MHz C) 129.005 MHz D) 132.185 MHz

[FPL-PT03 #12] Refer to Jeppesen GSPRM IFR Chart E(LO)2 and the image below.You are due to fly a VVIP flight from Doncaster Sheffield Airport, England (EGCN) - N53 28 W001 00' - to Dublin Airport, Ireland ((EIDW), departing EGCN at 21.05 UTC and routing via UPTON, L975, L70, V14 and DUB. Planned ETO at UPTON is 21.10 UTC and average planned GS is 296 kt. Approach to landing from DUB to touchdown is 8 minutes.METAR W/V at EIDW = 290/40 (no forecast changes)Aircraft maximum crosswind component = 25 ktA take-off delay means your ETO at UPTON is 21.15.What is your best course of action (from the following options)? A) Land on runway 28 (no distance limitations). B) Increase average GS to 325 kt. C) Land on runway 34 (no distance limitations). D) Cancel the flight.

[FPL-PT03 #13] Refer to Jeppesen GSPRM IFR Chart E(LO)1.A route is planned between FLESLAND VOR/DME (N60 20' E005 20') and MYGEGENAES NDB (N62 03' W007 16') along N623 and G3.TAS = 390 kt.ETO at FLS is 09.24 UTC, with a planned ETO at MY of 10.36 UTC.Reporting at VALDI at 09.52, what is the revised ETO at MY? A) 10.35 UTC B) 10.43 UTC C) 10.26 UTC D) 10.30 UTC

[FPL-PT03 #14] Refer to Jeppesen GSPRM IFR Chart E(LO)1.A route is planned between MYGEGENAES NDB (N62 03' W007 16') and FLESLAND VOR/DME (N60 20' E005 20') along N623 and G3.Mach No = 0.73Pressure Altitude = FL 250OAT = ISA-10°CForecast W/V = 220°/80Fuel flow is 1250 kg/hrFuel SG = 0.82Fuel cost = £0.85 per litreWhat is the fuel cost difference, which results from accepting a higher flight level at FL290 (OAT = ISA -5°C) with a reported wind of 250/120? A) -£127.00 B) -£85.00 C) +£127.00 D) +£85.00

[FPL-PT03 #15] Referring to your Jeppesen GSPRM IFR Chart E(HI)2 and any other relevant data, answer the following questions for an approach to land at Stuttgart Airport, Germany (EDDS):What is the appropriate frequency for obtaining local weather information for the BADSO 2A arrival? A) 126.125 Hz B) 126.125 GHz C) 126.125 MHz D) 126.125 KHz

[FPL-PT03 #16] Referring to your Jeppesen GSPRM IFR Chart E(HI)2 and any other relevant data, answer the following questions for an approach to land at Stuttgart Airport, Germany (EDDS):Using BADSO 2A arrival, what is the frequency of the navaid to which you should proceed in case of communications failure? A) 109.2 GHz B) 109.2 Hz C) 109.2 MHz D) 109.2 KHz

[FPL-PT03 #17] Referring to your Jeppesen GSPRM IFR Chart E(HI)2 and any other relevant data, answer the following questions for an approach to land at Stuttgart Airport, Germany (EDDS):For a straight-in landing on RWY 07, what is the CAT II ILS DH? A) 50 ft B) 100 ft C) 1367 ft D) 91 ft

[FPL-PT03 #18] Referring to your Jeppesen GSPRM IFR Chart E(HI)2 and any other relevant data, answer the following questions for an approach to land at Stuttgart Airport, Germany (EDDS):For the RNP RWY 07 approach. what is the minimum ground visibility for aircraft greater than 5.7 mt MTOW? A) 1500 m B) 5000 ft C) 2400 m D) 4000 m

[FPL-PT03 #19] You are due to fly an MEP freight aircraft from X to Y. The aircraft requires each wing tank to be refuelled individually. Total fuel required is 148 US Gallons of Avgas. There is already 120 lb in the port wing tank and 140 lb in the starboard wing tank. What total fuel uplift must the crew request from the fueller? Avgas specific gravity = 0.72. A) 328 litres B) 86.5 US Gals C) 395 litres D) 104 Imp Gals

[FPL-PT03 #20] You are due to fly an METP freight aircraft from A to B. The aircraft requires each wing tank to be refuelled individually. Total usable fuel = 800 litres of JET-A1 in each wing tank. The aircraft fuel gauges are calibrated in US Gallons and show that there is already 45 US Gal in the port wing tank and 60 US Gal in the starboard wing tank. The moment arm in the aircraft mass & balance documentation is stated in lbs/in and the fuel bowser is calibrated in litres. What total fuel uplift must the crew request from the fueller and what mass of fuel must be entered into the mass & balance calculation? JET-A1 specific gravity = 0.80. A) 1125 ltr & 900 lb B) 1200 ltr & 960 lb C) 1200 ltr & 2120 lb D) 1125 ltr & 2040 lb

[FPL-PT03 #21] Refer to your Jeppesen GSPRM IFR Chart E(LO)2An aircraft crosses CRK VOR/DME at FL80 at 15.42 UTC, en-route along route P2 to STU VOR/DME, at a GS of 260 kt. The aircraft's ETO at NEXAT is 15.59 UTC. What is the revised GS to maintain the ETO overhead STU? A) 302 kt B) 260 kt C) 285 kt D) 249 kt

[FPL-PT03 #22] Refer to Jeppesen GSPRM IFR Chart E(LO)14. Your charter holiday aircraft is routing from UK over Italy via ARA (Araxos) VOR/DME (N38° 10’ E021° 26’) along L612, via TRL (Tripolis) VOR/DME (N37° 25’ E022° 20’), along J65 via SUD (Souda) VOR/DME (N35° 32’ E024° 10’) to IRA (Iraklion) VOR/DME (N35° 21’ E025° 12’), to land at Nikos Kazantzakis International Airport, Crete. On approaching ARA along N604, Athens Control clears you “direct own navigation from TRL to IRA, maintain FL80 until advised”. Given a CAS of 210 kt, and W/V of 260°/30 at FL80 (OAT ISA +30°C) calculate the revised magnetic heading, groundspeed and ETE from TRL to IRA. A) 132°M, 269 kt, 41 min B) 136°M, 231 kt, 42 min C) 140°M, 250 kt, 40 min D) 132°M, 231 kt, 41 min

[FPL-PT03 #23] Refer to IFR Chart E(HI)1.Your aircraft is routing from Newcastle, England (EGNT) to Keflavik, Iceland via route L602 - TLA VOR/DME - route UL613 - BAMRA - UP61.ETO TLA VOR/DME = 11.25 UTCETO BAMRA = 12.15 UTC5 nm before VADNO (N57° 27’ W003° 38’), ATC instructs a speed change: “Reduce speed, cross BAMRA not before 12.17 UTC”. What is the required reduction in groundspeed? A) 20 kt B) 25 kt C) 15 kt D) 10 kt

[FPL-PT03 #24] Refer to CAP 697 Figure 4.6.1.Given a trip distance of 500 miles, 50 kt tailwind, max cruising level of FL160, standard day and an estimated landing weight of 50 000 kg, what is the trip fuel and time for a gear-down ferry flight? A) 5250 kg - 1hr 26 min B) 8900 kg - 2hr 24 min C) 5350 kg - 1hr 39 min D) 5900 kg - 1hr 26 min

[FPL-PT03 #25] "Refer to Cap 697 Figure 4.6.1Given a trip distance of 500 miles 50 kf tailwind, max cruising level of FL160, standard day and an estimated landing weight of 50 000 kg, what is the trip fuel and time for a gear-down ferry flight?" A) 5900 kg - 1hr 26 min B) 5350 kg - 1hr 26 min C) 5250 kg - 1hr 36 min D) 8900 kg - 2hr 24 min

[FPL-PT03 #26] An MRJT aircraft is flying with its landing gear down. Complete the following:The _____ performance has a _____ effect on routes and altitudes. A) reduced; negative B) reduced; positive C) improved; negative D) improved; positive

[FPL-PT03 #27] An MRJT aircraft is flying with its landing gear down. Complete the following:There will be _____ drag. A) none B) significant C) minor

[FPL-PT03 #28] An MRJT aircraft is flying with its landing gear down. Complete the following:The aircraft's speed is limited to a ______ of 220 KIAS. A) threshold B) Minimum C) Maximum

[FPL-PT03 #29] Refer to CAP 697 Figure 4.6.1.Given a trip distance of 300 miles, 100 kt headwind, max cruising level of FL200, standard day and an estimated landing weight of 55 000 kg, what is the trip fuel and time for a gear-down ferry flight? A) 6250 kg - 1 hr 45 min B) 4100 kg - 1 hr 45 min C) 2500 kg - 0 hr 51 min D) 5600 kg - 1 hr 45 min

[FPL-PT03 #30] An MRJT aircraft is flying with its landing gear down. How will the aircraft's performance be affected? A) There will be a medium reduction on performance owing to a limited increase in both lift and drag which has a medium effect on routes and altitudes. B) There will be a large reduction in performance owing to a significant increase in drag which has a negative effect on routes and altitudes. C) There will be a small reduction on performance owing to a limited increase in drag which has a negligible effect on routes and altitudes. D) There will be no effect on performance as modern engines and airframes are designed to accommodate such events.

[FPL-PT03 #31] Refer to CAP 697 Figure 4.7.2Given an ETOPS approval time of 120 minutes, long range cruise (LRC) technique and a weight of 55 000 kg at time of diversion; what is your permissible radius of operation on one engine? A) 752 NM. B) 380 NM. C) 803 NM. D) 743 NM.

[FPL-PT03 #32] Refer to CAP 697 Figure 4.7.3Given, a distance of 800 nm from the diversion point to the alternate, a 50 kt headwind, a weight of 40 000 kg at the point of diversion, a stabilisation level of FL 260 and ISA+20°C conditions; what is the fuel required and the time to arrive at the diversion? A) 6500 kg & 2 hr 39 min B) 6500 kg & 2 hr 30 min C) 4500 kg & 2 hr 30 min D) 5400 kg & 2 hr 39 min

[FPL-PT03 #33] Refer to CAP 697 Figures 4.7.1a & 4.7.1bGiven a distance of 800 nm to the diversion from the critical point, a 50 kt headwind, a weight of 50 000 kg at the critical point, ISA conditions and no icing; calculate the critical fuel reserve required. A) 6300 kg B) 7800 kg C) 6000 kg D) 8100 kg

[FPL-PT03 #34] Refer to the LRJT 1 Integrated Cruise table.A turbojet aeroplane is flying using the following data:Flight level FL 330, Long Range (LR) cruise, Mass of 160 000 kg, Temperature: ISA, Head wind component: 120 kt, Remaining flight time: 4h 30 minReferring to the image below. Which of the following correctly indicates the ground distance remaining? A) 1328 NGM B) 1447 NGM C) 1868 NGM D) 2408 NGM

[FPL-PT03 #35] Refer to the LRJT 1 Integrated Cruise table.For a long distance flight at FL 370, "Long Range" regime, divided into 4 flight legs with the following specifications:Segment AB - Ground distance: 1000 NM. headwind component: 100 ktSegment BC - Ground distance: 2000 NM. headwind component: 50 ktSegment CD - Ground distance: 500 NM. tailwind component:50 ktSegment DE - Ground distance: 1500 NM. tailwind component: 100 ktThe total air distance is approximately: A) 5200 NAM B) 4517 NAM C) 4800 NAM D) 5000 NAM

[FPL-PT03 #36] Refer to the LRJT 1 Integrated Cruise table.A turbojet aircraft is flying using the following data: TOM: 155 400 kg; Planned cruise at FL 330; LRC; Standard Atmosphere (ISA); CG: 37 %. What flight time will be required to cover an air distance of 2350 NM? A) 7 hr 23 min B) 8 hr 51 min C) 5 hr 58 min D) 1 hr 28 min

[FPL-PT03 #37] A turbojet has the following data: Take-off mass: 169 800 kg; Planned cruise at FL 330; Long range Mach; Standard Atmosphere (ISA); CG: 37 %. Covering an air distance of 3800 nm, what is the approximate trip fuel from take-off to landing? A) 169 800 kg B) 43 000 kg C) 40 100 kg D) 129 700 kg

[FPL-PT03 #38] 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:

[FPL-PT03 #39] During the pre flight preparation, the pilot calculates an amount of 27.5 US gallons for refuelling, which equals to:

[FPL-PT03 #40] 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 Traffic load: 14 500 kg Trip fuel: 4900 kg Minimum Take-off Fuel: 7400 kg. Find maximum allowable take-off fuel:

[FPL-PT03 #41] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. MTOM 233 000 kg MLM 182 000 kg MZFM 170 000 kg DOM 122 550 kg Traffic Load 41 936 kg Trip Fuel 52 139 kg Planned T/O Fuel 57 143 kg Taxi Fuel 300 kg Fuel burn correction per 1000 kg of Extra Fuel based upon: TOM: + 394 kg and LDM: + 650 kg Fuel tank capacity 110 000 kg

[FPL-PT03 #42] Find the remaining fuel in litres : ETO ATO Planned Fuel (L) Actual 1. 10:02 10:00 133 137 2. 10:10 10:08 126 130 3. 10:32

[FPL-PT03 #43] Refer to CAP697 MRJT Figure 4.3.1c. Trip distance 1900 nm, 50 kt tailwind, estimated landing weight 50 000 kg, cruise at FL220, ISA -10°C. What is the trip fuel and time?

[FPL-PT03 #44] Given the following information, calculate the minimum required fuel for a Commercial Air Transport flight in accordance with the Reduced Contingency Fuel Procedure. Taxi Fuel: 230 kg Trip Fuel to the Decision Point: 8355 kg Trip Fuel from the Decision Point to the commercial destination: 2120 kg Trip Fuel from the Decision Point to the optional refuel destination: 1860 kg Final Reserve Fuel: 1200 kg No Additional Fuel is required No Extra Fuel is required An en-route alternate for the optional refuel destination is available No destination alternate requirements exist for both destination aerodromes.

[FPL-PT03 #45] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel to be uplifted, if the Commander wants to climb directly to the optimum altitude of 37 000 ft. Maximum Take-off Mass (MTOM) to climb at FL370: 68 000 kg Maximum Zero Fuel Mass (MZFM): 62 731 kg Actual Zero Fuel Mass (AZFM): 59 031 kg Regulated Take-Off Mass (RTOM): 76 000 kg Maximum Landing Mass (MLM): 66 360 kg Fuel Tank Capacity: 16 000 kg Taxi Fuel: 240 kg Trip Fuel: 4761 kg Minimum Block Fuel: 8000 kg

[FPL-PT03 #46] Use Flight Planning Manual MRJT 1 Figure 4.5.1 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:

[FPL-PT03 #47] The Trip Fuel for a jet aeroplane to fly from the departure aerodrome to the destination aerodrome is 5350 kg. Fuel consumption in holding mode is 6000 kg/hr The quantity of fuel which is needed to carry out one go-around and land on the alternate airfield is 4380 kg. The destination aerodrome has a single runway. What is the minimum quantity of fuel which should be on board at take-off?

[FPL-PT03 #48] Flight Planning Manual MRJT 1 Figure 4.3.5. What is the Trip Fuel? Given: Temperature ISA +15°C Brake release mass 62 000 kg Trip time 5 hrs 20 min

[FPL-PT03 #49] Flight Planning Manual MRJT 1 Figure 4.3.5. For a flight of 2400 ground nautical miles, the following apply: Tailwind 25 kt Temperature ISA -10°C Brake release mass 66 000 kg The Trip Fuel and trip time respectively are:

[FPL-PT03 #50] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. MTOM 233 000 kg MLM 182 000 kg MZFM 170 000 kg DOM 122 550 kg Traffic Load 43 217 kg Trip Fuel 45 854 kg Planned T/O Fuel 51 616 kg Taxi Fuel 300 kg Fuel burn correction per 1000 kg of Extra Fuel based upon: TOM: + 394 kg and LDM: + 650 kg Fuel tank capacity 110 000 kg

[FPL-PT03 #51] Use 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/hr) with full throttle and cruise lean mixture in the following conditions: Given: OAT: 13°C Pressure altitude: 8000 ft RPM: 2300

[FPL-PT03 #52] Given the following planning data, calculate the maximum possible extra fuel in kg, including any fuel penalty, that can be uplifted. Max Ramp Mass 77 500 kg MTOM 73 000 kg MLM 66 360 kg MZFM 62 720 kg DOM 42 845 kg Traffic Load 17 460 kg Planned T/O fuel 10 365 kg Trip Fuel 7890 kg Taxi Fuel 195 kg Fuel Penalty: 135 kg / 1000 kg extra fuel Max Fuel tank capacity 21 000 kg

[FPL-PT03 #53] Refer to GSPRM Jeppesen Plate AMSTERDAM (Schipol) 10-2B. You recover via MOLIX, LUTEX and ROBVI and then hold for 20 mins. Expected fuel state at SUGOL after 20 mins holding? Usable Fuel at MOLIX 380 lbs GS = 103 kts Fuel flow at SUGOL 215 lbs/h Holding fuel flow 140 lbs/h

[FPL-PT03 #54] During a VFR flight at a navigational checkpoint the remaining usable fuel in tanks is 60 US gallons. The reserve fuel is 12 US gallons. According to the flight plan the remaining flight time is 1h35min. Calculate the highest acceptable rate of consumption possible for the rest of the trip.

[FPL-PT03 #55] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. Maximum Ramp Mass 77 500 kg MTOM 77000 kg MLM 66 360 kg MZFM 62720 kg DOM 42 845 kg Traffic Load 17460 kg Planned T/O Fuel 10 365 kg Trip Fuel 7890 kg Taxi Fuel 195 kg Fuel burn correction per 1000 kg of Extra Fuel based upon: TOM: + 135 kg and LDM: + 156 kg Fuel tank capacity 21 000 kg

[FPL-PT03 #56] Given the following information, what is the total fuel required for a VFR Commercial Air Transport flight with a multi-engine piston aircraft? Start up and Taxi Fuel: 2 gal Climb Fuel: 6 gal Cruise Fuel: 21 gal Alternate Fuel: 3 gal Fuel flow for Final Reserve Fuel: 16 gal/h

[FPL-PT03 #57] Find the time and distance given: FF 9.6 USG TAS 100 Wind 15 kts tail Actual fuel 50 USG

[FPL-PT03 #58] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. MTOM: 87 5000 lbs MLM: 65 2000 lbs MZFM: 55 5100 lbs DOM: 39 4100 lbs Traffic Load: 10 9350 lbs Trip Fuel: 28 9750 lbs Planned T/O Fuel: 31 5315 lbs Taxi Fuel: 1600 lbs Fuel burn correction per 1000lb of Extra Fuel based upon: TOM: + 470lb and LDM: + 887lb Tank capacity: 37 7750 lbs

[FPL-PT03 #59] For pre-flight planning purposes, what is the minimum Fuel required for the Commercial Air Transport flight in a Jet aircraft aeroplane, given the following information? Assume the Basic Fuel Scheme WITHOUT variations applies. Trip Fuel: 3740 kg Fuel to alternate: 936 kg Taxi Fuel: 140 kg Fuel flow at 1500 ft above destination aerodrome: 2132 kg/h Extra Fuel: 0 kg Discretionary Fuel: 0 kg

[FPL-PT03 #60] Determine the required fuel for an aircraft on a commercial VFR flight with reciprocating engines, given: Fuel Flow: 120 kg/h Trip Time: 4 h 39 min No alternate selected and good weather expected.

[FPL-PT03 #61] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. MTOM 233 000 kg MLM 182 000 kg MZFM 170 000 kg DOM 122 550 kg Traffic Load 35 367 kg Trip Fuel 62 332 kg Planned T/O Fuel 67 885 kg Taxi Fuel 300 kg Fuel burn correction per 1000 kg of Extra Fuel based upon: TOM: + 394 kg and LDM: + 650 kg Fuel tank capacity 110 000 kg

[FPL-PT03 #62] Using 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 40 000 kg at the most critical point, the maximum air distance to the relevant alternate is:

[FPL-PT03 #63] A jet aeroplane equipped with old engines has a specific fuel consumption of 0.06 kg per Newton of thrust and per hour and, in a given flying condition, a fuel mileage of 14 kg per Nautical Miles. In the same flying conditions, the same aeroplane equipped with modern engines with a specific fuel consumption of 0.035 kg per Newton of thrust and per hour, has a fuel mileage of:

[FPL-PT03 #64] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. Maximum Ramp Mass 63 060 kg MTOM 62 800 kg MLM 54 900 kg MZFM 51 300 kg DOM 33 200 kg Traffic Load 12 375 kg T/O Fuel 3575 kg Trip Fuel 2100 kg Taxi Fuel 195 kg Fuel burn correction per 1000 kg of Extra Fuel based upon: TOM: + 40 kg and LDM: + 42kg Fuel tank capacity 16 145 kg

[FPL-PT03 #65] An aeroplane with reciprocating engines is planning to depart for an isolated destination Aerodrome as a Commercial Air Transport operation. Calculate the minimum amount of fuel required (to the nearest 10 kg), when overhead the isolated aerodrome, considering the following details. Flight time: 2 hours and 30 minutes Top of climb to top of descent time: 2 hours Normal fuel consumption cruise: 780 kg per hour

[FPL-PT03 #66] How much useable fuel should be on board at start-up given the following planning information: APU fuel flow 150 kg/h Taxi fuel flow 11 kg / minute APU time 38 minutes Taxi. 13 minutes Trip fuel (including contingency) 4250 kg Alternate and Final Reserve fuel 3730 kg

[FPL-PT03 #67] How much useable fuel should be on board at start-up given the following planning information: APU fuel flow 150 kg/h Taxi fuel flow 11 kg / minute APU time 38 minutes Taxi. 13 minutes Trip fuel (including contingency) 4250 kg Alternate and Final Reserve fuel 3730 kg

[FPL-PT03 #68] Given the following Information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel to be uplifted. Maximum Zero Fuel Mass MZFM: 2000 kg Actual Zero Fuel Mass AZFM: 2000 kg Regulated Take-Off Mass RTOM: 3000 kg Maximum Landing Mass MLM: 2200 kg Fuel Tank Capacity: 550 kg Trip Fuel TF: 190 kg Minimum Block Fuel (BF): 300 kg

[FPL-PT03 #69] Given : Taxi Fuel = 150 kg Trip time = 2hrs Alternate = 1200 kg Extra Fuel = 350 kg Holding Fuel Flow = 2500 kg/hr Trip Fuel flow = 3100 kg/hr Find the Block Fuel.

[FPL-PT03 #70] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. MTOM 875 000 lbs MLM 652 000 lbs MZFM 555 100 lbs DOM 394 100 lbs Traffic Load 155 215 lbs Trip Fuel 198 620 lbs Planned T/O Fuel 226 195 lbs Taxi Fuel 1600 lbs Fuel burn correction per 1000 lb of Extra Fuel based upon: TOM: + 470 lb and LDM: + 887 lbs

[FPL-PT03 #71] For pre-flight planning purposes what is the block fuel required? Assume the Basic Fuel Scheme WITHOUT variations applies. Taxi fuel: 350 kg Trip fuel: 85 000 kg Contingency fuel: 5% of the Trip fuel Final reserve fuel: 3000 kg Alternate fuel: 5500 kg Discretionary fuel: 1500 kg Extra fuel: 0 kg

[FPL-PT03 #72] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel, including any fuel penalty, that can be uplifted. MTOM 85 000 kg MLM 75 500 kg MZFM 71 420 kg DOM 48 000 kg Traffic Load 15 464 kg Trip Fuel 2561 kg Planned T/O Fuel 5167 kg Taxi Fuel 200 kg Fuel tank capacity 23 500 kg Fuel burn correction per 1000 kg of Extra Fuel based upon: TOM: + 54 kg and LDM: + 57kg

[FPL-PT03 #73] Refer to figure or CAP 697 Figure 4.5.3.2 for Pressure Altitude 35 000. What will be the change in air range available from 1000 kg of fuel for the following situation if the OAT increases from -55° to -45°C? Aircraft mass at start of cruise leg: 50 000 kg Cruise level: FL350 Cruise speed: Mach 0.74 Forecast OAT at FL350: -55°C Wind component at FL350: -25 kt

[FPL-PT03 #74] Refer to CAP 697 Figure 4.5.3.2 for Pressure Altitude 35 000 ft. What will be the approximate change in ground distance available from 1000 kg of fuel for the following situation if the headwind increases from 25 kt to 35 kt? Aircraft mass at start of cruise leg: 65 000 kg Cruise level: FL350 Cruise speed: Mach 0.74 Forecast OAT at FL350: -65°C Headwind at FL350: 25 kt

[FPL-PT03 #75] The flight crew has 1 hour flight time remaining of a 4 hours flight towards the destination aerodrome. The FMS displays the message DEST EFOB BELOW MIN and the Commander looks at the FMS data to see that there is an estimated 0.3 tonnes less fuel than required when arriving at the destination. Under NORMAL circumstances for commercial air transport flight with one destination alternate nominated, what is the minimum fuel to be expected on board when arriving at the destination aerodrome?

[FPL-PT03 #76] The following data is extracted from an aeroplane loading manifest. Take-off Mass (Performance Limited) 93 500 kg Expected Landing Mass at destination 81 700 kg Maximum Certificated Landing Mass 86 300 kg Take-off Fuel on board 16 500 kg During the flight a diversion is made to an en-route alternate which is not performance limited for landing. Fuel remaining at landing is 10 300 kg The Landing Mass:

[FPL-PT03 #77] Given the following information for a Commercial Air Transport operation, calculate the maximum possible Extra Fuel to be uplifted. Maximum Zero Fuel Mass: 62731 kg Actual Zero Fuel Mass: 55031 kg Regulated Take-Off Mass: 76000 kg Maximum Landing Mass: 66360 kg Fuel Tank Capacity: 16000 kg Taxi Fuel: 240 kg Trip Fuel: 7931 kg Minimum Block Fuel: 16000 kg

[FPL-PT03 #78] The commander decides to increase the Block Fuel by 1200 kg due to an expected holding at the destination aerodrome as this equates to approximately 30 minutes of holding. After take-off, the FMS indicates that there is only 27 minutes of extra holding fuel despite the payload being as originally planned. What is the reason for this?

[FPL-PT03 #79] According to the following NOTAM, what is the safe distance for a civilian aircraft? Q) EUAD/QSPLT/IV/BO/AE/000/021/5212N00011E003 A) EUAD B) FROM 16/02/09 0830C) TO 16/02/09 1430 E) E BAND HIGH INTENSITY RADAR TRANSMISSION AREA (HIRTA) IN D304 RADIUS 1NMMAX HEIGHT 472FT AGLSAFE DISTANCES CIVILIAN ACFT 0.011NM 11FT AGL MIL ACFT VERY LOW 0.011NM 11FT AGL LOW 0.053NM 157FT AGL MEDIUM 0.077NM 242FT AGL HIGH 0.143NM 472FT AGL

[FPL-PT03 #80] Given the following NOTAM information, when can the aerodrome be expected to be operating on Tuesday? >>> LKPD PARDUBICE > END OF BULLETIN

[FPL-PT03 #81] Given the following NOTAM information, when can the aerodrome be expected to be operating on Tuesday? >>> LKPD (PARDUBICE) > END-OF-BULLETIN

[FPL-PT03 #82] Given the following NOTAM information, what operating hours can be expected for BRISTOL RADAR during the summer? ATS SURVEILLANCE SERVICES AND PROCEDURES BRISTOL LOWER AIRSPACE RADAR SERHR CHANGED TO 1000- 1800 WINTER (SUMMER 1HR EARLIER) ENR 1.6 PARAGRAPH 4.1.6 REFERS NOTAM EG/B0056/16 >>> END-OF-BULLETIN

[FPL-PT03 #83] Given A to B: 2050 NM Mean ground speed there 440 kt Mean ground speed back 540 kt The distance to the point of equal time PET between A & B is:

[FPL-PT03 #84] Given: Track 355° (T) Wind velocity 340/30 kt TAS 140 kt Total distance A to B 350 NM What is the time and the distance to the point of equal time between A and B?

[FPL-PT03 #85] Given: Track 355° (T) Wind velocity 340/30 kt TAS 140 kt Total distance A to B 350 NM What is the time and the distance to the point of equal time between A and B?

[FPL-PT03 #86] According to the following NOTAM, what time does the Tower close on Saturdays in winter? AMEND AD HR WINTER MON-FRI 0815-1215, 1315-1730 SAT 0815-1230 SUMMER MON-SAT 0700-1730APP/TWR WINTER MON-FRI 0815-1215, 1315-1730 SAT 0815-1215 SUMMER MON-SAT 0700-1800.

[FPL-PT03 #87] Given the following NOTAM information, what RADAR and TOWER frequency should be used by departing aircraft at 2100 UTC? >>> EGLF (FARNBOROUGH)

[FPL-PT03 #88] Given: Distance from departure to destination 150 NM Safe Endurance 2.4 h True Track 250 W/V 280/15 TAS 120 kt What is the distance of the PSR from the departure point??

[FPL-PT03 #89] With 3.5 hours total endurance on board, and a wind velocity of 270°/20 kt, a pilot has to travel over a distance of 200 NM on a track of 270°T. If the TAS is 100 kt and the pilot must land with 30 minutes worth of fuel on board, what is the distance to the Point of Safe Return PSR, and how long will it take to get there?

[FPL-PT03 #90] According to the following NOTAM, when can you expect the HENTON DVOR to come back into service? Q) EUAD/QNVAS/IV/BO/E/000/999/5221N00140W025 B) FROM 16/02/09 1130 C) TO 16/02/09 1530 E) HENTON DVOR/DME HEN FREQ 113.65 MHZ/CH 083Y, DVOR U/S

[FPL-PT03 #91] An aircraft was over A at 1435 hours flying direct to B. Given: Distance A to B 2900 NM True airspeed 470 kt Mean wind component OUT +55 kt Mean wind component BACK -75 kt The ETA for reaching the point of equal time (PET) between A and B is:

[FPL-PT03 #92] Given: Distance from departure to destination 260 NM Safe Endurance 4.1 h True Track 150 W/V 100/30 TAS 110 kt What is the distance of the PSR from the departure point?

[FPL-PT03 #93] Given: Distance A to B 2346 NM Ground speed OUT 365 kt Ground speed BACK 480 kt The time from A to the point of equal time (PET) between A and B is:

[FPL-PT03 #94] Given: Distance from departure to destination 2450 NM Safe Endurance 7.5 h TAS 410 kt Ground Speed Out 360 kt Ground Speed Home 460 kt What is the time of the PSR from the departure point in minutes?

[FPL-PT03 #95] According to the following NOTAM, what is the maximum height of the balloon involved? Q) EUAD/QWCLW/IV/M/W/000/004/5339N00135W001 A) EUAD B) FROM 15/12/14 1348C) TO 16/03/06 1830 E) UNMANNED CAPTIVE BALLOON IN LOW FLYING AREA AVOIDANCE AREA WI 1NM RADIUSMAX HEIGHT 200FT AGL/324FT AMSL15/12/06/OPSLFLOWER Surface, UPPER 324 Feet AMSL SCHEDULE DEC 14 1348-1600, DEC 15-31 0700-1600, JAN 01-31 0700-1630, FEB 01-29 0700- 1730, MAR 01-06 0600-1830

[FPL-PT03 #96] According to the following NOTAM, what is the maximum height of the balloon involved? Q) EUAD/QWCLW/IV/M/W/000/004/5339N00135W001 A) EUAD B) FROM: 15/12/14 13:48C) TO: 16/03/06 18:30 E) UNMANNED CAPTIVE BALLOON IN LOW FLYING AREA AVOIDANCE AREA WI 1 NM RADIUS. MAX HEIGHT 200FT AGL/324FT AMSL. 15/12/06/0PSLF. LOWER: Surface, UPPER: 324 Feet AMSL SCHEDULE: DEC 14 1348-1600, DEC 15-31 0700-1600, JAN 01-31 0700-1630, FEB 01- 29 0700-1730, MAR 01-06 0600-1830

[FPL-PT03 #97] Given: Distance from departure to destination 165 NM True track 055° W/V 360/20 TAS 105 kt What is the distance of the PET from the departure point?

[FPL-PT03 #98] Given the following NOTAM information, when can RWY 07R/25L be expected to be in operation? >>> EDDF FRANKFURT MAIN> END OF BULLETIN

[FPL-PT03 #99] Given: Distance from departure to destination: 950 NM Safe Endurance: 3.5 h TAS: 360 kt Ground Speed Out: 320 kt Ground Speed Home: 400 kt What is the distance and time of the PSR from the departure point?

[FPL-PT03 #100] Prior to an IFR flight, when filling in the ICAO flight plan, the time information which should be entered in Box 13 (time) is:

[FPL-PT03 #101] Given the following NOTAM information, what changes apply to NDB CF? NEW TODAY TIL 1603312359 NDB REMAINS CF 367KHZ FROM 0000 TO 0900 NDB CF 367KHZ BECOMES ASM 367KHZ FROM 0900 TO 2359 REF TRIGGER NOTAM PERM AIRAC AIP AMDT 04/16 : NOTAM LF/F0403/16 >>> END OF BULLETIN

[FPL-PT03 #102] Given: Distance from departure to destination 220 NM True track 175° W/V 220/10 TAS 135 kts What is the distance of the PET from the departure point?

[FPL-PT03 #103] Given the following NOTAM, are you able to fly passengers into EUAD on a charter flight? Q) EGTT/QAZCA/IV/NBO/AE/000/022/5334N00021W003 A) EUAD B) FROM 15/12/08 0942 C) TO PERM E) AERODROME ATZ ACTIVE 0620-2115 DAILYAD OPEN, ATS AVBL, USE OF THE AD IS PRIOR PERMISSION REQUIRED 0620-0630 UTC FOR NON SKED MOVEMENTSEUAD AD 2.3 AND AD 2.17 REFER

[FPL-PT03 #104] A ground distance of 135 NM shall be covered with a planned TAS of 450 kt; the fuel consumption is 5 kg/NM. The original fuel planning was made considering the forecast wind component of -25 kt. Before departure, the forecast is revised to a wind component of +25 kt. How much fuel is required in addition to the original calculation?

[FPL-PT03 #105] Due to a drive failure, the slats of a transport category aircraft do not retract properly after take-off. Based on the flight planning data given below, calculate the time penalty in per cent for the flight, based on endurance. Usable fuel 8540 kg Fuel consumption 2600 kg/h Final reserve fuel 1100 kg (Note: consider 60% fuel penalty for flap/slat failure and 180% for gear retraction failure)

[FPL-PT03 #106] An aircraft is flying at Mach .84 at FL330. The static air temperature is -48 degrees Celsius and the headwind component 52 kt. At 13.38 UTC the controller requests the pilot to cross the meridian of 030W at 1500 UTC. The distance to go is 570 NM. What should be the reduced Mach number?

[FPL-PT03 #107] Given the following information, what is the ground speed? TAS: 150 kt Track: 090° Wind: 050°/46 kt

[FPL-PT03 #108] During a flight the fuel indicators show that the remaining amount of fuel is 100 lb after 38 minutes. The total amount of fuel at take off was 160 lb. For the alternate fuel, 30 lb is necessary. The planned fuel for taxi is 13 lb. Final reserve fuel is estimated at 50 lb. If the fuel flow remains the same, how many minutes can be flown to the destination with the remaining fuel?

[FPL-PT03 #109] Given the following information, assuming conditions stay the same, what is the ETA at DELTA? BETA to GAMMA distance: 60 NM Actual time en-route: 30 min Actual lime of arrival at GAMMA: 1240 UTC GAMMA to DELTA distance: 34 NM

[FPL-PT03 #110] Refer to GSPRM Jeppesen Plate AMSTERDAM (Schipol) 10-2B. You recover via MOLIX, LUTEX and ROBVI and then hold for 20 mins. TAS 250 kt Nil Wind Fuel flow in cruise 3000 kg /h Holding fuel flow 2400 kg / h How much fuel do you burn between MOLIX and leaving the hold to commence the procedure?

[FPL-PT03 #111] Given: True Air Speed: 135 kt True course: 270° Wind: 340° /20 kt Distance: 53 NM Determine ground speed (GS) and flight time for covering the given distance:

[FPL-PT03 #112] An aircraft at FL 120, IAS 200 kt, OAT -5°C and wind component +30 kt, is required to reduce speed in order to cross a reporting point 5 MIN later than planned. Assuming flight conditions do not change, when 100 NM from the reporting point IAS should be reduced to:

[FPL-PT03 #113] The planned flight time between two waypoints is 25 minutes, and the distance is 30 NM. During the actual flight, the flight time between these waypoints is found to be 32 minutes. How much lower is the actual groundspeed compared to the one that has been used for planning?

[FPL-PT03 #114] After flying for 16 min at 100 kt TAS with a 20 kt tailwind component, you have to return to the airfield of departure. You will arrive after (Note include a standard rate turn of 3° /sec in your calculations):

[FPL-PT03 #115] An aircraft flying at 7500 ft is cleared to descend to be level at 1 000 ft, 6 NM before reaching a beacon. If ground speed is 156 kt and Rate of Descent is 800 ft/min, how many miles before the beacon should descent begin?

[FPL-PT03 #116] An aircraft flies from airport A to airport B, covering a total distance of 460 NM. After 1 h 11 min, it has covered a distance of 183 NM, and its remaining fuel is equal to 780 lb plus reserves. Determine the remaining fuel at airport B, assuming conditions remain the same and given: TAS: 185 kt Headwind: 30 kt Trip fuel: 1098 lb Fuel flow: 370 lb/h

[FPL-PT03 #117] Given the following information, what is the ground speed of the aircraft? TAS: 300 kt Heading: 090° Wind: 330°/46 kt

[FPL-PT03 #118] An aircraft is in cruising flight at FL095, GS 155 kt. The pilot intends to descend at 500 ft/min to arrive overhead the MAN VOR at 2000 FT (QNH 1030 hPa). The TAS remains constant in the descent, wind is negligible, temperature standard. At what distance from MAN should the pilot commence the descent?

[FPL-PT03 #119] Distance from A to B is 1000 NM, All engine TAS is 400 kt, Engine failure TAS is 350 kt, Wind component between A and PET is a 50 kt tailwind and wind component between PET to B is a 30 kt tailwind. What is the distance and time to the engine failure PET from A?

[FPL-PT03 #120] An aircraft takes 14 minutes to climb to FL290 covering 71 NAM, what is the ground distanced covered in a 30 kt headwind?

[FPL-PT03 #121] An aircraft takes-off from an airport 2 hours before sunset. The pilot flies a track of 090° (T), W/V 130° /20 kt, TAS 100 kt. In order to return to the point of departure before sunset, the furthest distance which may be travelled is:

[FPL-PT03 #122] With respect to the optimum altitude, which of the following statements is correct?

[FPL-PT03 #123] A pilot is calculating the Take-Off Distance for a Performance Class B multi- engined aeroplane. Specific factors must be applied to the AFM data to take into account variables that affect the takeoff performance. These factors have NOT been provided in the AFM and other performance and operating manuals from the manufacturer. For which variables must the pilot apply a factor greater than 1.0?