Performance – Quiz 5 – Pilot Interview Handbook

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Question 103

Is based on all engines operative:

Landing climb gradient

Approach climb gradient

Results

All engines operative, maximum go around (TOGA) thrust achieved within 8 seconds, gear down, flaps in landing configuration

Correct

Wrong

Question 104

Class A aircraft wet runway V2 must be achieved by:

35 ft

15 ft

Results

Although screen height must by achieved by 15 ft, V₂ must still be achieved by 35 ft

Correct

Wrong

Question 105

Vmcg is referred to:

IAS

Groundspeed

Results

All V speed refer to IAS. This is because the aerodynamic effectiveness of flight controls (e.g. rudder) is related to the dynamic pressure of airflow (from which IAS is calculated)

Correct

Wrong

Question 106

V1 is the maximum speed to:

Take the first action to reject takeoff

Decide to reject takeoff

Results

Maximum speed to take first action to reject takeoff (i.e. close thrust) and not maximum speed to decide to reject takeoff. If the decision to reject takeoff was made at V₁, then the first action to reject would be taken after V₁ (due to human reaction time), invalidating takeoff performance

Correct

Wrong

Question 107

Tailwind will:

Reduce V1

Increase V1

Results

Due to higher GS and harder deceleration

Correct

Wrong

Question 108

Which is higher:

Vmca

Results

Needs to be higher to ensure adequate directional control

Correct

Wrong

Question 109

Decision to reject takeoff must be made:

At V1

By V1

Results

If the decision to reject takeoff was made at V₁, then the first action to reject would be taken after V₁ (due to human reaction time), invalidating takeoff performance

Correct

Wrong

Question 110

Maximum length of TODA:

1.25 x TORA

1.5 x TORA

Results

Correct

Wrong

Question 111

FMC speeds are based on:

Unbalanced V1

Balanced V1

Results

Do not account for any clearway or stopway available

Correct

Wrong

Question 112

V2 is flown during the:

3rd takeoff segment

2nd takeoff segment

Results

Minimum speed to be flown during 2nd takeoff segment in case of engine failure

Correct

Wrong

Question 113

10% higher speed on touchdown:

10% higher kinetic energy for brakes to absorb

21% higher kinetic energy for brakes to absorb

Results

Kinetic energy = 1/2 x m x V²

Correct

Wrong

Question 114

Standing water:

Runway condition code 3

Runway condition code 2

Results

Correct

Wrong

Question 115

Runway may be more slippery than anticipated:

OAT 10° C or less and dew point spread 5° C or less

OAT 3° C or less and dew point spread 3° C or less

Results

3 Kelvin spread rule

Correct

Wrong

Question 116

Vle is the maximum speed to:

Extend the landing gear

Fly with the landing gear extended

Results

Maximum landing gear extended speed

Correct

Wrong

Question 117

Vlo is the maximum speed to:

Extend or retract the landing gear

Fly with the landing gear extended

Results

Maximum landing gear operating speed

Correct

Wrong

Question 118

Vlo can be higher than Vle:

True

False

Results

Maximum speed to operate (extend or retract the landing gear) cannot be higher than the maximum speed to fly with the landing gear extended

Correct

Wrong

Question 119

Dispatch LDR for a dry runway is:

Actual LDR x 1.67

Actual LDR x 1.92

Results

Correct

Wrong

Question 120

Stopway is designed to be used for:

Landing

Rejected takeoff

All of the above

Results

Correct

Wrong

Question 121

Dispatch LDR for a wet runway is:

Actual LDR x 1.92 (1.67 x 1.15)

Actual LDR x 1.67

Results

Factored by an additional 15%

Correct

Wrong

Question 122

Contaminated runway definition is based on:

Each third of the runway’s surface

Total surface of the runway

Results

Since introduction of GRF (Global Reporting Format)

Correct

Wrong

Question 123

Clearway increases field length limited TOW by:

Increasing V1

Reducing V1

Results

Reduced (unbalanced) V1 allows MTOW to be increased by taking advantage of the higher TODA (increasing TODR without increasing ASDR)

Correct

Wrong

Question 124

Jet engines are designed to spool up from idle to maximum thrust in:

5 seconds

8 seconds

Results

Correct

Wrong

Question 125

Approach path angle 3.6°, GS 140 kt. What is the required rate of descent?

740 ft / min

840 ft / min

Results

Approach gradient* x groundspeed = 6 x 140 = 840 ft / min, *approach gradient = approach path angle / 60 = 3.6 / 60 = 6%

Correct

Wrong

Question 126

Approach gradient 5.8%, GS 130 kt. What is the required rate of descent?

1250 ft / min

750 ft / min

Results

Approach gradient x groundspeed = 5.8 x 130 = 750 ft / min

Correct

Wrong

Question 127

Approach path angle 3°, GS 120 kt. What is the required rate of descent?

600 ft / min

800 ft / min

Results

Approach gradient* x groundspeed = 5 x 120 = 600 ft / min, *approach gradient = approach path angle / 60 = 3 / 60 = 5%

Correct

Wrong

Question 128

Higher pressure altitude:

Lower Vmcg

Higher Vmcg

Results

Less density = less thrust = less thrust asymmetry in case of engine failure = lower Vmcg required

Correct

Wrong

Question 129

Higher temperature:

Higher Vmcg

Lower Vmcg

Results

Less density = less thrust = less thrust asymmetry in case of engine failure = lower Vmcg required

Correct

Wrong

Question 130

Higher pressure altitude:

Lower Vmca

Higher Vmca

Results

Less density = less thrust = less thrust asymmetry in case of engine failure = lower V_mca required

Correct

Wrong

Question 131

Higher temperature:

Lower Vmca

Higher Vmca

Results

Less density = less thrust = less thrust asymmetry in case of engine failure = lower V_mca required

Correct

Wrong

Question 132

Is based on one engine inoperative:

Landing climb gradient

Approach climb gradient

Results

One engine inoperative, TOGA thrust, gear up, flaps in approach configuration

Correct

Wrong

Question 133

Class A aircraft:

All multi-engine jets and turboprops with more than 9 passenger seats or MTOW > 5700 kg

Propeller driven aircraft with 9 passenger seats or less and MTOW of 5700 kg or less

Results

Correct

Wrong

Question 134

Class B aircraft:

Propeller driven aircraft with 9 passenger seats or less and MTOW of 5700 kg or less

All multi-engine jets and turboprops with more than 9 passenger seats or MTOW > 5700 kg