Class A Landing – Air – DGCA Question Bank For Politics

#1. The approach climb requirement has been established to ensure:

minimum climb gradient in case of a go-around with one engine inoperative.

obstacle clearance in the approach area.

manoeuvrability in case of landing with one engine inoperative.

manoeuvrability during approach with full flaps and gear down, all engines operating.

#2. The maximum mass for landing could be limited by:

the climb requirements with all engines in the landing configuration but with gear up.

the climb requirements with one engine inoperative in the approach configuration.

the climb requirements with one engine inoperative in the landing configuration.

the climb requirements with all engines in the approach configuration.

#3. Which of the following is true according to JAA regulations for turbo propeller powered aeroplanes not performing a steep approach?

Maximum Take-off Run is 0.5 x runway length.

Maximum use of clearway is 1.5 x runway length.

Maximum Landing Distance at the destination aerodrome and at any alternate aerodrome is 0.7 x LDA (Landing Distance Available).

Maximum Landing Distance at destination is 0.95 x LDA (Landing Distance Available).

#4. For a turboprop powered aeroplane, a 2,200 m long runway at the destination aerodrome is expected to be “wet”. To ensure the wet landing distance meets the requirement, the “dry runway” landing distance should not exceed:

1,540 m

1,147 m.

1,339 m.

1,771 m.

#5. A flight is planned with a turbojet aeroplane to an aerodrome with a landing distance available of 2,400 m. Which of the following is the maximum landing distance for a dry runway?

1 437 m.

1 250 m.

1 090 m

1 655 m.

#6. The maximum mass for landing could be limited by:

the climb requirements with all engines in the landing configuration but with gear up.

the climb requirements with one engine inoperative in the approach configuration.

the climb requirements with one engine inoperative in the landing configuration.

the climb requirements with all engines in the approach configuration.

#7. According to JAR-OPS 1, which one of the following statements concerning the landing distance for a turbojet aeroplane is correct?

The landing distance is the distance from 35 ft above the surface of the runway to the full stop.

When determining the maximum allowable landing mass at destination, 60% of the available landing runway length should be taken into account

Reverse thrust is one of the factors always taken into account when determining the landing distance required.

Malfunctioning of an anti-skid system has no effect on the required runway length.

#8. By what factor must the landing distance available (dry runway) for a turbojet powered aeroplane be multiplied to find the maximum landing distance?

1.15

1.67

60/115

0.60

#9. The landing field length required for jet aeroplanes at the alternate in wet conditions is the demonstrated landing distance plus:

92%

43%

70%

67%

#10. The landing field length required for turbojet aeroplanes at the destination in wet condition is the demonstrated landing distance plus:

67%

70%

43%

#11. For a turbojet aeroplane, what is the maximum landing distance for wet runways when the landing distance available at an aerodrome is 3,000 m?

2 070 m.

1,562 m.

1,800 m

2,609 m.

#12. If the airworthiness documents do not specify a correction for landing on a wet runway; the landing distance must be increased by:

10%

20%

15%

5%

#13. Required runway length at destination airport for turboprop aeroplanes:

is the same as at an alternate airport.

is less then at an alternate airport.

is more than at an alternate airport.

is 60% longer than at an alternate airport

#14. For this question use Figure 4.28 in CAP 698 Section 4. What is the minimum field length required for the worst wind situation, landing a twin jet aeroplane with the anti-skid inoperative? Elevation: 2000 ft QNH: 1013 hPa Landing mass: 50,000 kg Flaps: as required for minimum landing distance Runway condition: dry Wind: Maximum allowable tailwind: 15 kt Maximum allowable headwind: 50 kt

2600 m.

2700 m.

2900 m.

3100 m.

#15. Compared to the landing distance available, the maximum landing distance for a turbo-propeller and turbojet aircraft are:

60%, 60%

70%, 70%

70%, 60%

60%, 70%

#16. The landing climb gradient limit mass is determined by:

A gradient of 3.2% with one engine inoperative, the other engines at take off power in the landing configuration.

A gradient of 3.2% with all engines operating at take off power, in the landing configuration.

A gradient of 2.1% with all engines operating at take off power, with landing gear retracted, and approach flap.

A gradient of 3.2% with all engines operating at take off power, with landing gear retracted and approach flap.

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