PERFORMANCE (MATH & CHARTS) Flashcards by Matías Van Hooydonck

An obstacle in the flight path segment requires 2.6 % climb gradient for safe clearance. The gradient is 2.8% at 110 000 kg gross weight.

With the same power settings and the sine of the angle of climb varying inversely with mass, the maximum mass at which the minimum climb gradient can be maintained is:

118 455 kg
108 430 kg
120 310 kg
102 450 kg

118 455 kg

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With the information given, calculate the all-engine-operating (AEO) climb gradient for a twin-engine aeroplane (assume g = 10 m/s²):

Thrust per engine: 120000 N
Take-off Mass: 55000 kg
Lift-to-drag ratio: 8:1

5.35%
9.36%
18.1%
31.1%

31.1%

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With the information given, calculate the all-engine-operating (AEO) climb gradient for a twin-engine aeroplane (assume g = 10 m/s²):

Thrust per engine: 40000 lbs/engine
Take-off Mass: 80000 kg
Lift-to-drag ratio: 7:1

31.1%
10.8%
6.15%
20.9%

31.1%

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Operation Four-engine Turbojet
Mass 150 000 kg
Lift-to-Drag ratio 14
Thrust per engine 75 000 N (all operating)
g 10 m/s²
The Climb Gradient (%) is:

29
1.286
7.94
12.86

12.86

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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) 1.30, (2) 1.15
(1) 1.25, (2) 1.30
(1) 1.15, (2) 1.25
(1) 1.25, (2) 1.15

(1) 1.25, (2) 1.15

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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?

38 kt
19 kt
32 kt
33 kt

32 kt

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For a single-engine aeroplane, calculate the expected obstacle clearance in VMC given the following values:
Climb gradient: 6%
TAS 120 kt
Wind: Tailwind 10kt
Obstacle height: 300 ft at a distance of 1.2 NM from DER (reference zero)

Use 1 NM = 6080 ft, Height Difference = (GD x TAS)/GS x gradient / 100

354 ft
404 ft
104 ft
154 ft

154 ft

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For a single-engine aeroplane, calculate the expected obstacle clearance overhead the trees at extended centerline in VMC given the following values:
Climb gradient: 8%
TAS 180 kt
Wind: Headwind 20kt
Take-off from Runway 02

Use 1 NM = 6080 ft, Height Difference = (GD x TAS)/GS x gradient / 100

320 ft
770 ft
370 ft
220 ft

370 ft

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For a single-engine aeroplane, calculate the expected obstacle clearance overhead the lighted obstacle at extended centerline in VMC given the following values:
Climb gradient: 12%
TAS 145 kt
Wind: Headwind 15 kt
Take-off from Runway 11 with ELEV at MSL

Use 1 NM = 6080 ft, Height Difference = (GD x TAS)/GS x gradient / 100

115 ft
65 ft
315 ft
165 ft

315 ft

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For a single-engine aeroplane, calculate the net glide distance with the following values given:
Altitude: 11000 ft
Terrain elevation: 1500 ft
Gross gradient: 10%
TAS: 250 kt
Headwind: 40 kt

Use 1 NM = 6080 ft
Still air distance = (height difference / net gradient) x 100
Ground distance = Still Air Distance x (GS / TAS)

14.9 NM
12.5 NM
15.6 NM
13.1 NM

12.5 NM

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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:

3600 lbs
2850 lbs
3240 lbs
3450 lbs

3240 lbs

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OAT ISA +10° C
Press. Alt. 5000 ft
Mass 3400 lb
Headwind 5 kt
Flaps Up
Runway surface Tarred
Runway gradient Zero
Runway condition Dry

The [1] Rotation Speed is ___ and the [2] Take-Off Speed is ___.

[1] 69 kt, [2] 80 kt
[1] 71 kt, [2] 82 kt
[1] 74 kt, [2] 85 kt
[1] 67 kt, [2] 82 kt

[1] 71 kt, [2] 82 kt

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OAT 25°C
Press. Alt. 3000 ft
RWY 26L
Wind 310°/20 kt
Take-off Mass 4400 lb
Brakes Heavy Duty
Associated Conditions: As in header of the graph.

The Accelerate-Stop Distance in ft is:

4100
3250
3500
3700

3500

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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:

3500 ft
4550 ft
4250 ft
4870 ft

4250 ft

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OAT 20° C
Press. Alt. 2000 ft
RWY 07R
Wind 120°/ 15 kt
Take-Off Mass 4500 lb
Brakes Heavy Duty
Associated conditions: As in header of the graph.

The Accelerate-Stop Distance is:

3300 ft
3450 ft
3750 ft
3600 ft

3450 ft

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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

2450 ft
1650 ft
2050 ft
1350 ft

1650 ft

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With the information given below, determine the gross take-off distance over 50 ft:

Temperature: 24° C
Pressure altitude: 5000 ft
Take-off mass: 3400 lb
Headwind component: 20 kt
Runway surface: dry grass
Correction factor: 1.2 for runway surface/condition

1440 ft
1960 ft
2820 ft
2350 ft

2820 ft

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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:

1370 ft
1550 ft
1740 ft
1280 ft

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1550 ft

OAT 24° C
Press. Alt. 3000 ft
RWY 30R
Wind 060°/4 kt
Take-Off Mass 3800 lb
Associated conditions As in the header of the graph.

The Ground Roll Distance is:

2100 ft
1540 ft
1670 ft
2270 ft

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1670 ft

OAT +18° C
Aerodrome Press. Altitude 1500 ft
Mass 1270 kg
Tailwind 4 kt
Runway surface Hard
Runway condition Dry
Runway slope Zero

The Take-Off Distance to 50 ft height is:

580 m
375 m
610 m
465 m

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465 m

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:

1150 ft
2350 ft
1350 ft
1800 ft

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2350 ft

OAT 38°C
Press. Alt. 4000 ft
Aeroplane Mass 3400 lb
Tailwind 5 kt
Flaps Approach setting
Runway surface Grass
Runway condition Dry
Runway slope Zero
Correction factor 1.2 for runway condition

The Take-off Distance, rounded to the nearest 50 ft, is:

3400 ft
3850 ft
5000 ft
4050 ft

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3850 ft

Take-off distance in ISA with zero wind and zero ft pressure-altitude: 600 m.

Corrections:
+/- 20 m / 1 000 ft field elevation
- 5 m / kt headwind
+ 10 m / kt tail wind
+/- 15 m / % runway slope
+/- 5 m / °C deviation from standard temp.

Calculate take-off distance at 1000 ft elevation, 17°C, QNH 1013.25 hPa, 1% up-slope, and 10 kt tailwind.

575 m
725 m
645 m
755 m

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755 m

With the information given below, determine the engine-out Rate Of Climb (ROC):

OAT: 15° C
Pressure Altitude: 3000 ft
Mass: 4400 lb
Headwind: 35 kt

1900 ft/min
230 ft/min
320 ft/min
1650 ft/min

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320 ft/min

Determine the the minimum TODA for a multi-engine piston aeroplane in commercial operation, given the information below: Take-Off Distance Required (from AFM, defactored): 2800 ft Runway slope: 1.5 % UP Runway conditions: paved, wet (no stopway / clearway available) 2270 ft 3770 ft 3640 ft 3010 ft

3770 ft

Determine the the maximum take-off distance required (unfactored, from AFM) for a multi-engine piston aeroplane in commercial operation, given the information below: Take-Off Distance Available (no stop/clearway): 3500 ft Runway slope: 1.0 % UP Runway conditions: Grass (firm soil 10cm long), wet 2230 ft 2890 ft 2560 ft 2050 ft

2050 ft

OAT 0° C Press. Alt. 18000 ft Gross mass 3750 lb Mixture 25° F rich of Peak EGT Determine the Two-Engine Rate of Climb in ft/min: 1050 450 1250 750

1050

OAT -20° C Press. Alt. 14000 ft Gross mass 4000 lb Determine the One-Engine Inoperate Rate of Climb in ft/min: 175 325 1025 650

175

OAT -20° C Press. Alt. 18000 ft Gross mass 4000 lb Mixture Leaned to 25° F rich of peak EGT Determine the Two-Engine Rate of Climb in ft/min: 570 850 1050 1270

1050

OAT 10°C Press. Alt, 2000 ft Gross Mass 3750 lb Determine the One-engine Inoperative Rate of Climb in ft/min: 430 480 210 860

430

With regard to a twin-engine piston aeroplane with all engines operating (AEO) and the information given below, calculate the clearance over the obstacle, assuming minimum prescribed climb gradient: Airport elevation: 700 ft Obstacle elevation: 950 ft Distance of the obstacle from DER: 2500 m Departure procedure: initially on runway track, no specific climb reuqirements in SID 78 ft 128 ft 1078 ft 1028 ft

128 ft

With regard to a performance class B aeroplane with all engines operating (AEO) and the information given below, calculate for the purpose of obstacle clearance the distance from DER to reach 1500 ft above reference zero: Cloud base: 200 ft above reference zero, no wind, TAS: 110 kt All Engines Rate of Climb (ROC) at Take-Off Power: 2000 ft/min Single Engine Rate of Climb (ROC) at Take-Off Power: 500 ft/min (assume Take-Off Power throughout the complete climb segment) 4.73 NM 4.91 NM 4.77 NM 4.86 NM

4.91 NM

To maintain obstacle clearance, a departure route initially requires a climb gradient of 5.4%. With the information given below, determine the corresponding Rate of Climb (ROC): TAS: 150 kt Tailwind component: 15 kt 1560 ft/min 730 ft/min 810 ft/min 890 ft/min

890 ft/min

The Climb Gradient after take-off, in ISA conditions and still-air, at 0 ft pressure altitude, is 6%. Calculate the Climb Gradient with Wing- and Engine Anti-Ice ON at the given conditions: Aerodrome Press. Alt. 1000 ft OAT +17° C Atmospheric Pressure 1013.25 hPa Corrections: Aerodrome Elevation +/- 0.2 % per 1000 ft ISA Deviation +/- 0.1 % per °C Effect of Wing Anti-ice ON - 1.0 % Effect of Engine Anti-ice ON - 0.5 % 4.8 % 4.4 % 3.6 % 3.9 %

3.9 %

With the information given below, determine the all-engine-operative (AEO) still-air climb gradient: Take-Off Mass: 4750 lb Airport elevation: 3000 ft OAT: +9°C Tailwind: 10 kt Climb speed: 92 kt IAS, 100 kt TAS Flaps / Gear: Up Power: Take-off 14.0 % 15.2 % 19.0 % 12.7 %

12.7 %

With the information given below, determine the one-engine-inoperative (OEI) flight path gradient: Take-Off Mass: 4000 lb Airport elevation: 3000 ft OAT: +9°C Tailwind: 10 kt Climb speed: 92 kt IAS, 100 kt TAS Flaps / Gear: Up Power: Take-off 4.3 % 4.0 % 2.1 % 4.7 %

4.0 %

For a performance class B aeroplane with the information given below, determine the field-length-limited landing mass and 50 ft barrier speed: Pressure altitude: 4000 ft OAT: ISA Headwind component: 10 kt Landing distance (defactored): 1900 ft 4100 lbs, 78 kt 4500 lbs, 82 kt 3000 lbs, 68 kt 3450 lbs, 71 kt

4100 lbs, 78 kt

For a performance class B aeroplane with the information given below, determine the field-length-limited landing mass and 50 ft barrier speed: Pressure altitude: 4000 ft OAT: -2°C Tailwind component: 5 kt Landing distance (defactored): 3050 ft 4500 lbs, 90 kt 3000 lbs, 76 kt 3650 lbs, 82 kt 3850 lbs, 84 kt

3850 lbs, 84 kt

For a performance class B aeroplane with the information given below, determine the balked landing climb gradient (assume still air conditions): Pressure altitude: 4000 ft OAT: +30°C Landing mass: 4513 lbs 9.9 % 9.2 % 8.5 % 7.8 %

8.5 %

OAT 27° C Press. Alt. 3000 ft Aeroplane Mass 2900 lb Tailwind 5 kt Flaps Landing (Down) Runway surface Tarred Runway condition Dry The Landing Distance from 50 ft height is: 1350 ft 1850 ft 1720 ft 1280 ft

1850 ft

OAT: ISA +15° C Press. Alt. 0 ft Aeroplane Mass: 2940 lb Tailwind: 10 kt Flaps: Landing (Down) Runway surface: Tarred Runway condition: Dry The Landing Distance from 50 ft height is: 1600 ft 1750 ft 950 ft 1900 ft

1900 ft

According the factors given in CAT.POL.A 330 and 335 and AMC, for a performance class B aeroplane in commercial operation, with the information given below, determine the defactored landing distance (rounded to the nearest 10 ft): Landing distance available (LDA): 4400 ft Runway surface: Grass (firm soil 10 cm long) Runway condition: Wet Runway slope: 1.0 % upslope Increase landing distance by 5 % for each 1 % downslope 3080 ft 2330 ft 3330 ft 2450 ft

2330 ft

According the factors given in CAT.POL.A 330 and 335 and AMC, for a performance class B aeroplane in commercial operation, with the information given below, determine the minimum landing distance available (rounded to the nearest 10 ft): Landing distance defactored: 2200 ft Runway surface: Grass (firm soil, 5 cm long) Runway condition: Wet Runway slope: 0.5 % downslope Increase landing distance by 5 % for each 1 % downslope 2980 ft 4160 ft 1820 ft 4260 ft

4260 ft

According the factors given in CAL.POL.A 330 and 335 and AMC, for a performance class B aeroplane in commercial operation, with the information given below, determine the minimum landing distance available (rounded to the nearest 10 ft): Landing distance defactored: 2400 ft Runway surface: Tarred Runway condition: Wet Runway slope: 0.5 % upslope Increase landing distance by 5 % for each 1 % downslope 3940 ft 3430 ft 2760 ft 4040 ft

3940 ft

PERFORMANCE (MATH & CHARTS) Flashcards

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