In Performance Class 1 (PC1) operation of a large helicopter, the drift-down technique is used to perform a...

controlled emergency landing in case of a failure of the tail rotor or fixed pedal controls.

controlled recovery procedure, in case of encountering a vortex ring state during the landing phase.

fuel-saving descent from the assigned en-route altitude to the initial approach fix (IAF) at destination.

descent when Encountering a Critical engine failure at an Altitude above the OEI service ceiling.

Consider the alternative take-off profile for a PC1 helicopter certified in accordance with CS- 29...

HIGE power is required as a minimum.

Using HIGE power will allow a steeper flight path.

A steeper flight path will be allowed using HOGE power.

With reference to CAP 758 figure 3.17. The TETH has suffered an engine failure at 12000 ft PA and commenced the drift down. Start of drift down mass 7000 kg. Calculate the distance flown and the stabilising height.

Distance 9 NM Stabilising PA 10000 ft.

Distance 9 km stabilising PA 9800 ft.

Distance 12 NM stabilising PA 10000 ft.

Distance 11 NM stabilising PA 9800 ft.

When planning for OEI in the cruise in IMC a helicopter in PC2 must be able to maintain a rate of climb of at least:

50 fpm but PC2 must maintain VMC and remain above MSA.

50 fpm at 2000 ft Above all Mountainous terrain.

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 and not over a mountainous area, that rate of climb should be a minimum of:

150 ft/min at an altitude of 2000 ft.

100 ft/min at an altitude of 1000 ft.

50 ft/min at An altitude of 1000 ft.

50 ft/min at an altitude of 2000 ft.

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

120% of the reported tail wind component.

50% of the reported tail wind component.

80% of the reported tail wind component.

D150% of the Reported tail Wind component.

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

1.5 x length of the helicopter +.15 DR for VFR.

When planning for one engine inoperative in the cruise, a helicopter operating in Performance Class 1 or 2 must be able to maintain a rate of climb of at least:

50 ft/min at 2000 ft In mountainous Areas.

Which of the following statements is correct?

An engine failure at high cruising altitude will always result in a drift down, because it is not permitted to fly the same altitude as with all engines operating.

The drift down regulations require a minimum descent angle after an engine failure at cruising altitude.

When determining the Obstacle clearance During driftdown fuel dumping may be Taken into account.

The drift down procedure requires a minimum obstacle clearance of 35 ft.

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.

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

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

When calculating the landing weight of a Performance Class 2 helicopter with one engine inoperative, the following must be considered:

The passengers and freight to be uplifted.

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

More than 150% of the reported headwind component.

Less than 50% of the reported headwind component.

More than 80% of the reported headwind component.

More than 50% of the reported headwind Component.

Obstacles beyond 10R may be disregarded in PC1:

For day operations with visual navigation clues.

For night Operations with suitable visual Navigation clues.

For night operations with accurate course guidance.

For a Performance Class 1 helicopter en-route with OEI in VFR and with the surface not in sight the minimum ROC required is?

50 fpm at 2000 ft Over all obstacles and Terrain in a mountainous area.

50 fpm at 2000 ft in a mountainous area.

When flying for endurance minimum drag speed is not used. This is because thrust is:

Not directly related to fuel flow mass.

Not directly related to fuel mass.

Which of the following criteria must be established at the landing decision point LDP on a clear airfield?

Height 100 ft, VY 40 kt, ROD 300-500 fpm.

Height 50 ft, V1 40 kt, ROD 300-500 fpm.

Height 100 ft, VI 40 kt, ROD 300-400 fpm.

Height 100 Ft, VI 40 kt, ROD 300-500 Fpm.

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

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

A pilot operating a helicopter in Performance Class 1 intends to land but experiences a critical power-unit failure before reaching the LDP. Which option is correct?

A safe forced landing is NOT assured because the failure occurred before reaching the LDP.

A balked landing may be conducted, but only if the helicopter is in sight of the surface.

The pilot is committed to land because in PC1 a balked landing is NOT possible.

The pilot can Continue the landing and Stop within the FATO, or Execute a balked landing.

An increase in density altitude:

Generally reduces performance in Performance class 1 and Decreases especially the take-off weight.

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

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

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

Increasing the mass (and, therefore, weight) of the aircraft will:

Decrease the Rate and angle of climb.

Increase the rate and angle of climb.

Increase the rate of climb and decrease the angle of climb.

Decrease the rate of climb and increase the angle of climb.

Climbing at Vx will achieve:

The greatest increase in altitude in a given period of time.

The maximum horizontal distance for a given vertical distance.

Who is responsible before a flight that the load is safely distributed and secured?

The Commander of the Intended flight.

A pilot wishes to fly at a speed which will give him maximum range. He knows that he is flying with a tailwind. How will the speed selected by the pilot compare with the maximum range speed for still air?

It will be increased by a margin slightly less than the amount of tailwind.

It will be decreased By a margin slightly less Than the amount of tailwind.

It will be the same as for still air.

It will be decreased by a margin slightly more than the amount of tailwind.

Which of the next cases will result in worsening of performance and possibility of exceeding structural limitations of helicopter?

Helicopter is loaded Over maximal Allowed weight.

Helicopter climbing at Vbroc with maximal allowed weight.

Helicopter flying over maximal landing weight.

Helicopter with higher weight at take off than landing.

Performance Class 1 Helicopter Quiz

Authored by Ha Trang Dao

English

University

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MULTIPLE CHOICE QUESTION

30 sec • 1 pt

If, during descent in a Performance Class 1 helicopter which has one engine inoperative, fuel is to be jettisoned, the fuel contents should be kept to a figure which enables the aircraft to carry out:

A hold.

A safe forced landing.

A safe let-down Procedure.

A diversion.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

When planning for landing a Performance Class 1 helicopter, the following information must be considered:

Take-off technique.

The ambient Pressure at the destination Heliport.

Not less than 175% of forecast tailwind.

Not more than 75% of forecast headwind.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

With reference to CAP 758 figure 3.11. Find the ROC, given AUM 7750kg, OAT 0°C, PA 11000ft, all engines operating at max continuous rating.

980 fpm.

1080fpm.

800 fpm.

1300 fpm.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

Reference annex or CAP 758 Figure 3.12.For the TETH operating in Performance Class 1 determine the Maximum Take-off Mass (MTOM) that will give minimum obstacle clearance within 5nm of track and a minimum ROC of 50 fpm over a mountainous area of 8000ft OAT +10°C at that altitude.

8000 kgs.

7300kgs.

7700 kgs.

7000 kgs.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

At annex or CAP 758 fig 3.39.For the TETH determine the gradient of climb at 200 ft agl. Given: Mass 6900 kg, PA 11000 ft, OAT -10°C. Speed VTOSS. OEI.

1.89 %.

6.44%.

2.01%.

5.74%.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

An aircraft must be capable of the following OEI performance when en-route in the cruise?:

35 ft/min rate of climb at 1000 ft above mountainous terrain, clear of obstacles within 900m either side of track, when VFR.

35 ft/min rate of climb at 1000 ft above mountainous terrain, clear of obstacles within 900m either side of track, when IFR.

50 ft/min rate of Climb at 2000 ft above Mountainous terrain, clear of obstacles Within 5 nm either side of track, when IFR.

50 ft/min rate of climb at 2000 ft above mountainous terrain, clear of obstacles within 5 nm either side of track, when VFR.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

In Performance Class 1 operations, unless otherwise approved by the competent authority, in order to ensure that climb gradients can be maintained, turning by more than 15° to comply with a procedure is only allowed after what height above the take-off surface?

10 m (35 ft).

61 m(200 ft).

152 m (500 ft).

300 m (1000 ft).

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Performance Class 1 Helicopter Quiz

If, during descent in a Performance Class 1 helicopter which has one engine inoperative, fuel is to be jettisoned, the fuel contents should be kept to a figure which enables the aircraft to carry out:

When planning for landing a Performance Class 1 helicopter, the following information must be considered:

With reference to CAP 758 figure 3.11. Find the ROC, given AUM 7750kg, OAT 0°C, PA 11000ft, all engines operating at max continuous rating.

Reference annex or CAP 758 Figure 3.12.For the TETH operating in Performance Class 1 determine the Maximum Take-off Mass (MTOM) that will give minimum obstacle clearance within 5nm of track and a minimum ROC of 50 fpm over a mountainous area of 8000ft OAT +10°C at that altitude.

At annex or CAP 758 fig 3.39.For the TETH determine the gradient of climb at 200 ft agl. Given: Mass 6900 kg, PA 11000 ft, OAT -10°C. Speed VTOSS. OEI.

An aircraft must be capable of the following OEI performance when en-route in the cruise?:

In Performance Class 1 operations, unless otherwise approved by the competent authority, in order to ensure that climb gradients can be maintained, turning by more than 15° to comply with a procedure is only allowed after what height above the take-off surface?

For the calculation of MTOW for a Performance Class 1 helicopter, the following factoring of reported tail-wind is used:

With one engine inoperative, a helicopter with Performance Class 1, when landing at an elevated heliport, must be able to clear all obstructions vertically by:

What is the ROC OEI service ceiling for the TETH

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