Performance Easa repaso

With regard to Regulation (EU) No 965/2012 Part CAT (performance class B aeroplanes), the unfactored take-off distance, specified in the AFM, shall not exceed: - when multiplied by a factor of (1) ___ the take-off run available (TORA) - or, when stop way and/or clearway is available, when multiplied by a factor of (2) ___, the take-off distance available (TODA). (1) 1.25, (2) 1.15. (1) 1.15, (2) 1.25. (1) 1.30, (2) 1.15. (1) 1.25, (2) 1.30.

According AMC1 CAT.POL.A.330, unless otherwise specified in the AFM, or other performance or operating manuals from the manufacturers, the variable affecting the landing performance and the associated factor that should be applied to the AFM data on a dry short-grass runway is: 1.15. 1.20. 1.25. 1.30.

For this question, use attachment IC-032-018 or a suitable calculation method) Given the maximum allowed crosswind component of 25 kt for take-off on runway direction 220(M) and wind from 270(M), what is the maximum allowed reported wind speed to NOT exceed maximum crosswind component?. 32 kt. 33 kt. 38 kt.

If aerodrome pressure altitude decreases, the.. take-Off Distance Required decreases. take-Off Distance Required increase. accelerate-Stop Distance increases. take-Off Ground Run increases.

On the Power versus TAS graph for level flight, a tangent from the origin touches the power required curve where the... Lift to Drag ratio is a maximum. Drag coefficient is a minimum. Lift to Drag ratio is a minimum. Maximum Drag Speed is reached.

In straight horizontal steady flight, at speeds below that for minimum drag... lower speed requires higher thrust. higher speed, but still below that for minimum drag, requires higher thrust. the aeroplane cannot be flown manually. the aeroplane can only be controlled in level flight.

To achieve maximum range with a headwind, the airspeed should be... higher than the maximum range cruise speed with no wind. equal to the maximum range cruise speed with no wind. lower than the maximum range cruise speed with no wind. reduced to the maximum speed for gust penetration.

With regard to jet-engines, "Specific Fuel Consumption (SFC)" can be understood as: Fuel flow (kg/h) for unit of producible thrust (N). Fuel mass (kg) for unit of producible thrust (N). Fuel mass (kg) for unit of producible thrust (N). Unit of producible thrust (N) per fuel consumption (kg).

With regard to a turbojet aeroplane, speed for maximum endurance corresponds to.. the speed for minimum drag. the speed for minimum ratio between drag and speed. the speed for minimum power. the speed for minimum power.

With regard to propeller-driven aeroplanes, which of the following statements is correct? 1. A piston-engine aeroplane will reach its highest endurance at MSL level. 2. Speed for maximum endurance decreases with increasing altitude. 1 is correct, 2 is incorrect. 1 is incorrect, 2 is incorrect. 1 is incorrect, 2 is correct. 1 is correct, 2 is correct.

The best rate of climb at a constant gross mass.. Decreases with increasing altitude as the thrust available decreases due to lower air density. Increases with increasing altitude as the drag decreases due to lower air density. Increases with increasing altitude due to higher TAS. Is not affected by changes in altitude.

When compared to a descent with a given mass at the speed for Minimum Angle of Descent, how will a higher mass affect the Minimum Descent Angle and the corresponding speed?. The Minimum Angle of descent will remain constant at a higher speed. The Minimum Angle of descent will remain constant at the same speed. The Minimum Angle of descent will increase with a lower speed. The Minimum Angle of descent will decrease at the same speed.

With regard to Minimum Angle of Descent during glide, which of the following statements is correct? 1. A higher mass results in a higher Minimum Angle of Descent. 2. A higher mass allows a higher speed for the same Minimum Angle of Descent. 1 is incorrect, 2 is correct. 1 is incorrect, 2 is incorrect. 1 is correct, 2 is correct. 1 is correct, 2 is incorrect.

The take-off safety speed V2min for turbo-propeller aeroplanes with more than three engines should not be less than... 1.08 VSR. 1.3 VSR. 1.13 VSR. 1.15 VSR.

The correct relationship between the reference landing speed (VREF) and the reference stalling speed in the landing configuration (VSR0) is... VREF > 1.23 VSR0. VREF > VSRO. VREF > 1.15 VSR0. VREF > 1.32 VSR0.

V2 must exceed VMC by. 10 %. 15 %. 5 %. 25 %.

When using Take-Off Flaps 20° instead of 10°.. V2 decreases if not restricted by VMCA. the value of V2 does not change.

V1 will be decreased by... inoperative anti-skid. increased take-off mass. increased outside air temperature.

An uphill slope... increases the take-off distance more than the accelerate stop distance. decreases the accelerate stop distance only. decreases the take-off distance only. ncreases the allowed take-off mass.

With inoperative antiskid the... Accelerate-Stop Distance increases. Accelerate-Stop Distance decreases. Accelerate-Stop Distance is not affected.

In case of contaminated runways, "wet" conditions the runway appearance is (1) ___, whereas in "damp" conditions the runway (2). (1) reflective, (2) has no shiny appearance. 1) not shiny, (2) has a shiny appearance. (1) flooded with water, (2) has a shiny appearance.

See attachment IC-032-029 or CAP698 Figure 4.5 Take-Off Performance - Climb Limit) Using the following conditions for take-off, determine the Climb Limit Brake Release Mass: Airport Elevation: 2000 ft Airport temperature: +25°C Configuration: Flap position 15, PACKS OFF. 57100 kg. 56200 kg. 55300 kg. 60800 kg.

With regard to a runway contaminated with compacted snow, when compared to dry conditions, which of the following statements is correct? 1. Accelerate-Stop-Distance (ASD) increases. 2. Take-Off Distance (TOD) is NOT affected. 1 is correct, 2 is correc. 1 is correct, 2 is incorrect. 1 is incorrect, 2 is correct. 1 is incorrect, 2 is incorrect.

See attachment IC-032-031) According the the values shown in the annex, the optimum flap/slat setting and maximum Performance Limited Take-Off Mass (PLTOM) in accordance with the requirements for commercial air transport is: Annex: ic-032-031.png. 25°, 57700 kg. 25°, 63200 kg. 5°, 64000 kg.

Max. Brake Release Mass values in Zero Wind of a CS-25 certified aeroplane are: Flap Setting 5° 15° 25° Runway Limitation (kg) 66000 69500 71500 2nd Segment Climb Limitation (kg) 72200 69000 61800 Wind correction: Headwind +120 kg / kt Tailwind - 360 kg / kt With 5 kt tailwind, the Max. Brake Release Mass and corresponding Flap Settings are: 67200 kg, 15°. 67200 kg, 15°. 72200 kg, 25°.

If the take-off mass of an aeroplane is tyre speed limited, a downhill slope will... not affect the maximum take-off mass. decrease the maximum take-off mass. increase the maximum take-off mass. ncrease the take-off distance required.

Higher Pressure Altitude in ISA conditions.. decreases the field length limited take-off mass. decreases the take-off distance required. increases the climb limited take-off mass.

For a Class A aeroplane, to avoid obstacles during the driftdown after an engine failure (whenever a measurably positive climb cannot be achieved), a vertical clearance of ___ must be ensured. 2000 ft. 1000 ft. 2500 ft. 50 ft.

In a glide at constant Mach Number, the Lift Coefficient decreases because... IAS increases. Aircraft Mass decreases. TAS decreases. Glide Angle increases.

When descending at constant Mach Number, the margin to low speed buffet... increases, because the lift coefficient decreases. remains constant, because the Mach number does not change. increases, because the lift coefficient increases. decreases, because the lift coefficient decreases.

In a Turbojet the Wet Landing Distance is the Demonstrated Landing Distance plus... 92 %. 67 %. 78 %.

Aircraft Performance Class A Turboprop Runway Length at Destination 2200 m Runway condition Wet The landing distance required from the Aircraft Flight Manual (AFM) for a dry runway should be at maximum: 1339 m. 1247 m. 1540 m. 1247 m.

With regard to climb with constant Mach number below the tropopause in ISA conditions, which of the following statements is correct? 1. EAS decreases. 2. CAS decreases. 3. TAS increases. 1 and 2. 1, 2 and 3. 2 and 3. 1 and 3.

See attachment IC-032-001 or CAP698 Figure 4.4 Take-Off Performance) Operation Twin Turbojet Certificated Take-Off Flap Settings 5° and 15° Field length available 2400 m OAT -10° C Pressure Alt. 7000 ft PMC ON A/C Auto Packs ON Anti-ice OFF Wind Zero Runway Gradient Zero The Max. Take-off Mass is: 56000 kg. 54000 kg. 51000 kg.

(See attachment IC-032-036) With the numbers from the annex showing a Regulated Take-Off Mass (RTOM) Table for runway 05L from position VB, and with the information given below, find the Regulated Take-Off Mass (RTOM) for departure: OAT +3°C, Wind 050/15, QNH 993 hPa Anti-Ice (ENG only) ON, Packs OFF Quick line-up, Runway WET (Do NOT interpolate, instead, use the most conservative numbers). 78430 kg. 79400 kg. 78590 kg. 79560 kg.

(See attachment IC-032-038 or CAP698 Figure 4.23) With the information given below, determine the maximum permissible net mass allowing clearance from highest relevant obstacles: Min. off-route pressure altitude: 16400 ft Temperature: ISA + 5 ANTI-ICE ALL OFF A/C AUTO (HIGH). 53500 kg. 56000 kg.

See attachment IC-032-016 or CAP 698 Figure 2.1) OAT ISA Press. altitude 4000 ft Headwind comp. 5 kt Flaps Zero Runway length 2000 ft Runway surface Tarred Runway radient Zero Runway condition Dry The maximum Take-off Mass (TOM) is: 3240 lbs. 3600 lbs. 2850 lbs. 3450 lbs.

(See attachment IC-032-020 or CAP 698 Figure 3.2) OAT 20° C Press. Alt. 2000 ft RWY 24L Wind 120°/ 8 kt Take-Off Mass 4500 lb Brakes Heavy Duty Associated conditions: As in the header of graph. The Accelerate-Stop Distance is: 4250 ft. 4550 ft. 4870 ft. 3500 ft.

(See attachment IC-032-021 or CAP 698 Figure 2.2) With the information given below, determine the take-off distance over 50 ft: Temperature: +9° C Pressure altitude: 3000 ft Headwind component: 5 kt Take-Off Mass: 3250 lb. 1650 ft. 1350 ft. 2050 ft. 2450 ft.

See attachment IC-032-005) OAT -15° C Press. Alt. 4000 ft RWY 12R Wind 080°/12 kt Take-Off Mass 4000 lb Associated conditions As in the header of the graph. The Take-Off Distance is: 1550 ft. 1370 ft. 1280 ft. 1740 ft.

(See attachment IC-032-008) OAT 30°C Press. Alt. 1000 ft Aeroplane Mass 2950 lb Tailwind 5 kt Flaps Approach setting Runway Short wet grass, firm subsoil Correction Factor 1.3 (for runway conditions) The Take-Off Distance, rounded to the nearest 50 ft, is: 2350 ft. 1800 ft. 1350 ft. 1150 ft.

(See attachment IC-032-040 or CAP698 Figure 4.29) With the information given below, determine the Climb-Limited Landing Mass: Airport: Elevation 3000 ft, QNH 1013 hPa, Temperature +20°C, Configuration: Flaps 30, A/C AUTO, ENGINE and WING ANTI-ICE ON. 57450 kg. 62800 kg. 58760 kg. 68150 kg.