In level flight, in performance class 1 and 2, with one engine failed and the others operating, at 1000 ft above any obstacle along the route, the weight of the helicopter must allow it to climb:

At no definite value by the authority.

In performance class 1, with one engine failed and the others operating normally, the helicopter's weight at the estimated time of landing must be such that a rate of climb of at least 150ft/mn at 1000 ft above the altitude of:

The Destination or alternate/diversion Heliport.

Driftdown is the procedure to be utilised:

After engine Failure, if the helicopter is Above the one-engine-inoperative cruise ceiling.

To conduct an instrument approach at the alternate.

To conduct a visual approach with one engine out.

When en-route in a Performance Class 1 helicopter which has had an engine failure, the mass of the aircraft must be such that a rate of climb may be achieved and maintained. When not visual with the surface, that rate of climb is:

At least 50 ft/min at An altitude of 2000 ft In mountainous areas.

At least 150 ft/min at an altitude of 1000 ft.

50 ft/min at an altitude of 300 ft.

100 ft/min at an altitude of 300 m.

Will be achieved flying with minimum fuel consumption (kg/nm).

Is the same as maximum specific range with wind correction.

Will be achieved By flying with Minimum fuel flow (kg/h).

Is the same as maximum specific range.

In class 1 performance, with one engine failed and the others operating, a helicopter's weight at the estimated landing time must allow it to climb at least at:

150ft/mn at 1000ft above the destination and the alternate heliports.

100 ft/mn at 200ft, above the destination and the alternate heliports.

150ft/mn at 1000ft And 100 ft/mn at 200ft, above the Destination and the alternate heliports.

150ft/mn at 1000ft and 100 ft/mn at 200ft, above the destination heliport.

In performance class 1, when the wind measuring equipment has not received official approval, and there is a headwind component, to determine landing performance an operator may take account of at:

Least, 50% of the reported headwind component.

Most, 80% of the reported headwind component.

Most, 50% of the Reported headwind Component.

Most, 40% of the reported headwind component.

Which of the following correctly defines the flight path and configuration in segment 3 for the TETH Procedure 1?

Level at 200 ft, accelerating from VTOSS to VY, gear up, bleed air off.

Climbing to 200 ft, accelerating from VTOSS to WY, gear up, bleed air off.

Level at 200 ft, Accelerating from VTOSS to VY, Gear down, bleed air off.

Level at 200 ft, accelerating from VTOSS to VY, gear down, air conditioning on.

Please refer to the annex. A helicopter operating in Performance Class 1 commences a short-field take-off, as shown in the annex. Concerning the RTODRH, this...

depends on density altitude, take-off mass, and the selected obstacle clearance height (h).

is equal to distance D1, where the minimum required obstacle clearance (h) is achieved.

reduces With headwind and Shall be less Than the horizontal distance L.

is equal to distance D2, where VTOSS is achieved, with one engine inoperative.

In class 1 performance a multi-engine helicopter with 'D' of 16m is to depart VFR night. For the purpose of obstacle clearance it is not necessary to consider obstacles that are further than:

1.5D or 30m (whichever is greater) + 0.15 DR.

In performance class 1, with one engine failed and the others operating normally, the helicopter's weight at the estimated time of landing must permit a rate of climb of at least 100ft/mn at 200 ft above the altitude of:

The Destination Or alternate/diversion heliport.

In the event of a engine failure in the cruise the minimum pilot reaction time is:

One second or normal Pilot reaction time Whichever is greater.

Where is the maximum range speed found on the fuel flow curve?

Tangent from the power required curve to the fuel flow curve.

From the Tangent of the origin To the fuel flow curve.

In PC1, the take-off flight path is on HDG 300°M, the pilot plans a turn onto 330°M at 200 ft with a transition to IFR after the TDP. The obstacle clearance requirement is:

35 ft +1.5D +0.01DR + an adequate margin.

35 ft + 0.01DR + An adequate Margin.

In Class 1 performance, for a multi-engine helicopter of a length less than 15 metres, it is not necessary to take into account obstacles whose lateral margin relative to the helicopter's flight path in IFR with standard course guidance, with the critical engine failed is greater than a certain distance.

This distance in IFR flight is: 22.5 metres + 0.15 DR.

This distance in visual flight is: 22.5metres + 0.30 DR.

This distance In IFR flight is 30 Metres + 0.15 DR.

This distance in visual flight is: 30 metres + 0.30 DR.

Which of the following statements is correct with regard to limited power operations?

With limited Power turning Increases the power required and may lead to loss of height.

Turning reduces the total rotor thrust required and increases power available.

With limited power an increase in bank angle decreases the power required due to the decrease in effective weight.

With limited power turning decreases the power required and may lead to loss of height.

In the event of a balked landing in PC1 the correct configuration at 1000 ft is:

Critical engine inoperative, Remaining engines at MCP, Gear retracted, Speed VY, minimum ROC 150 fpm.

Critical engine inoperative, remaining engines at MCP, gear retracted, speed VMIN, minimum ROC 150 fpm.

Critical engine inoperative, remaining engines at MCP, gear down, speed VTOSS, minimum ROC 100 fpm.

Critical engine inoperative, remaining engines at take-off power, gear down, speed VTOSS, minimum ROC 150 fpm.

In Performance Class 1 helicopter operations, at the beginning of which segment in the Category A take-off flight path must the best rate of climb speed (Vy) be achieved?

The segment between 35 feet and 200 feet.

The segment After Acceleration.

The segment between the hover and 35 feet.

How much of the tailwind should be considered for a performance class 1 helicopter?

Not less than 150 % of Any reported tailwind Component.

Less than 150 % tailwind if precise wind-measuring equipment is available at the take-off area.

Less than 100 % tailwind if precise wind-measuring equipment is available at the take-off area.

In Performance Class 1, for a multi-engine helicopter of a total length with the rotors turning of less than 15 metres, it is not necessary to take into account obstacles whose lateral margin relative to the helicopter's flight path with the critical engine failed is greater than a certain distance.

This distance is 30 metres + 0.15 DR For IFR operations with standard Course guidance.

This distance i s 22.5 metres + 0.10 DR for VFR operations with accurate course guidance.

This distance i s 22.5 metres + 0.10 DR for IFR operations with accurate course guidance.

This distance is 15 metres + 0.15 DR for IFR operations with standard course guidance.

For take-off with a tailwind component in class 1 performance an operator must take account of at least:

150% of the Reported Tailwind component.

120% of the reported tailwind component.

50% of the reported tailwind component.

80% of the reported tailwind component.

When planning obstacle avoidance on the take-off path of a Performance Class 1 helicopter which has suffered an engine failure, consideration need not be given to obstacles which are further than:

1.5 x Length of the Helicopter (or 30 m) + 0.15 DR for IFR.

An increase in ambient temperature:

generally reduces Performance in Performance Class 1 and especially the take-off weight.

increases performance in performance class 1 and especially the take-off weight.

does not influence performance in performance class 1 and especially the take-off weight.

increases or does not influence take-off weight depending on the aircraft type.

In performance class 1 when there is a headwind component, an operator, when calculating take-off performance may take into account not:

more than 50% of the Reported headwind component.

less than 50% of the reported headwind component.

more than 80% of the reported headwind component.

more than 150% of the reported headwind component.

Helicopter Performance Quiz

Authored by Ha Trang Dao

English

University

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MULTIPLE CHOICE QUESTION

30 sec • 1 pt

In cruise, an extreme aft longitudinal centre of gravity:

Brings the cyclic stick closer To its forward stop And increases the stress in the rotor head.

Moves away the cyclic stick from its forward stop and increases the stress in the rotor head.

Brings the cyclic stick closer to its forward stop and decreases the stress in the rotor head.

Moves away the cyclic stick from its forward stop and decreases the stresses in the head rotors.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

A helicopter in the hover that requires an excessive amount of aft and right cyclic may indicate the centre of gravity is too far:

Forward and laterally too far To the left.

Aft and laterally too far to the left.

Aft and laterally too far to the right.

Forward and laterally too far to the right.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

Following an engine failure en-route when not visual with the surface, the helicopter must clear obstacles within a 5nm domain either side of intended track. The flight conditions improve to VMC and the surface is in sight. What are the dimensions of the obstacle domain?

900m Semi-width.

600m semi-width.

10R.

300m semi-width.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

Please refer to the annex. Given a gross mass of 6300 kg and an OAT of -5° C, at what pressure altitude can the helicopter maintain a hover IGE with one engine inoperative?

7500 ft.

6250ft.

5250 ft.

5500 ft.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

ATC request that a descent from 6500 ft to 4000 ft in 8.3 NM. TAS is 154 kt. The rate of descent needed is

618 ft/min.

802 ft/min.

642 ft/min.

773 Ft/min.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

If carrying out a balked landing the minimum ROC at 200ft is:

Minimum ROC does not apply until 1000 ft.

150 ft/min.

100ft/min.

50 ft/min.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

With reference to CAP758 figure 3.44. Determine the distance D4 and the gradient required for the TETH to climb from 200 ft to 1000 ft given: PA 8000 ft OAT 0°C Mass 7000 kg Wind 20 kts HW

180 m/600 ft/8%.

1000 m/3000 ft/6%.

3000m/10000 ft/8%.

250 m/750 ft/12%.

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Helicopter Performance Quiz

In cruise, an extreme aft longitudinal centre of gravity:

A helicopter in the hover that requires an excessive amount of aft and right cyclic may indicate the centre of gravity is too far:

Following an engine failure en-route when not visual with the surface, the helicopter must clear obstacles within a 5nm domain either side of intended track. The flight conditions improve to VMC and the surface is in sight. What are the dimensions of the obstacle domain?

Please refer to the annex. Given a gross mass of 6300 kg and an OAT of -5° C, at what pressure altitude can the helicopter maintain a hover IGE with one engine inoperative?

ATC request that a descent from 6500 ft to 4000 ft in 8.3 NM. TAS is 154 kt. The rate of descent needed is

If carrying out a balked landing the minimum ROC at 200ft is:

With reference to CAP758 figure 3.44. Determine the distance D4 and the gradient required for the TETH to climb from 200 ft to 1000 ft given: PA 8000 ft OAT 0°C Mass 7000 kg Wind 20 kts HW

In level flight, in performance class 1 and 2, with one engine failed and the others operating, at 1000 ft above any obstacle along the route, the weight of the helicopter must allow it to climb:

In performance class 1, with one engine failed and the others operating normally, the helicopter's weight at the estimated time of landing must be such that a rate of climb of at least 150ft/mn at 1000 ft above the altitude of:

The "take-off path" is the horizontal and vertical profile calculated:

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