The take off path of a helicopter from the start of take off extends to a point ? [ Exam pilot ]

Question 101-1 : 1000 ft 500 ft 1500 ft 100 ft

The todrh is the horizontal distance required between the start of the take off ?

Question 101-2 : 35 ft above the take off surface and a positive climb gradient in case of failure of the critical engine 15 ft above the take off surface and a positive climb gradient in case of failure of the critical engine 35 ft above the take off surface and a positive or zero climb gradient in case of failure of the critical engine 50 ft above the take off surface and a positive or zero climb gradient in case of failure of the critical engine

exemple 205 35 ft above the take off surface and a positive climb gradient in case of failure of the critical engine. — 35 ft above the take off surface and a positive climb gradient in case of failure of the critical engine.

Tlof means ?

Question 101-3 : An area for touch down and lift off the length of an operational runway in feet the person in charge of take offs and landings the speed for translational lift

exemple 209 An area for touch down and lift off. — An area for touch down and lift off.

When calculating the take off performaces of a performance class 2 helicopter ?

Question 101-4 : Maximum 50% of the reported headwind at least 50% of the reported headwind maximum 150% of the reported headwind maximum 60% of the reported headwind

exemple 213 Maximum 50% of the reported headwind. — Cat pol h 105 general . .c when showing compliance with the requirements of this section account shall be taken of the following parameters .1 mass of the helicopter .2 the helicopter configuration .3 the environmental conditions in particular .i pressure altitude and temperature .ii wind . a except as provided in c for take off take off flight path and landing requirements accountability for wind shall be no more than 50% of any reported steady headwind component of 5 kt or more . b where take off and landing with a tailwind component is permitted in the afm and in all cases for the take off flight path not less than 150% of any reported tailwind component shall be taken into account and . c where precise wind measuring equipment enables accurate measurement of wind velocity over the point of take off and landing wind components in excess of 50% may be established by the operator provided that the operator demonstrates to the competent authority that the proximity to the fato and accuracy enhancements of the wind measuring equipment provide an equivalent level of safety .4 the operating techniques and.5 the operation of any systems that have an adverse effect on performance Maximum 50% of the reported headwind.

Vx means the speed for ?

Question 101-5 : Best angle of climb best angle of glide best rate of climb best approach speed

exemple 217 Best angle of climb. — Best angle of climb.

What is the abbreviation for the term 'never exceed speed' ?

Question 101-6 : Vne vno vnx vle

What does the abbreviation 'oei' mean ?

Question 101-7 : One engine inoperative outboard electrical input override electrical inverter out of engine limits

exemple 225 One engine inoperative. — One engine inoperative.

What does the abbreviation 'vle' mean ?

Question 101-8 : Maximum landing gear extended speed maximum landing gear operating speed minimum level speed maximum level speed

exemple 229 Maximum landing gear extended speed. — Maximum landing gear extended speed.

What does the abbreviation 'vlo' mean ?

Question 101-9 : Maximum landing gear operating speed maximum landing gear extended speed minimum landing gear extended speed maximum low level speed

exemple 233 Maximum landing gear operating speed. — Maximum landing gear operating speed.

What effect does temperature have on the performance limited take off mass ?

Question 101-10 : Rising temperatures will lower the performance limited take off mass rising temperatures will permit a higher performance limited take off mass falling temperatures will require a lower performance limited take off mass a change in temperature does not affect the performance limited take off mass

exemple 237 Rising temperatures will lower the performance limited take-off mass. — Rising temperatures will lower the performance limited take-off mass.

What is the abbreviation for the term 'maximum landing gear extended speed' ?

Question 101-11 : Vle vlo vne va

What is the abbreviation for the term 'maximum landing gear operating speed' ?

Question 101-12 : Vlo vle vgo vlg

The main difference between category a and category b helicopters is ?

Question 101-13 : Category a has guaranteed stay up capability category b has not category b has guaranteed stay up capability category a has not that category a is for multi engine helicopters and category b for single engine helicopters that category b is for multi engine helicopters and category a for single engine helicopters

Cat a definition .a multi engined helicopter designed with engine and system isolation features specified in the applicable certification specification and capable of operations using take off and landing data scheduled under a critical engine failure concept that assures adequate designated surface area and adequate performance capability for continued safe flight or safe rejected take off in the event of engine failure . cat b definition .a single engined or multi engined helicopter that does not meet category a standards category b helicopters have no guaranteed capability to continue safe flight in the event of an engine failure and unscheduled landing is assumed

What is the abbreviation for the term 'speed for best rate of climb' ?

Question 101-14 : Vy vx vlo v2

What is the abbreviation for the term 'take off safety speed' ?

Question 101-15 : Vtoss vx vy vto

What is the effect of tail wind on the time to climb to a given altitude ?

Question 101-16 : The time to climb does not change the time to climb increases the time to climb decreases the effect on the time to climb will depend on the helicopter type

exemple 261 The time to climb does not change. — The time to climb does not change.

When allowing a helicopter to descend to a level which can be maintained on the ?

Question 101-17 : Drift down self levelling controlled descent auto level

When calculating the landing weight of a performance class 2 helicopter with ?

Question 101-18 : 50% of the forecast headwind the headwind the tailwind the passengers and freight to be uplifted

exemple 269 50% of the forecast headwind. — Cat pol h 105 general . .c when showing compliance with the requirements of this section account shall be taken of the following parameters .1 mass of the helicopter .2 the helicopter configuration .3 the environmental conditions in particular .i pressure altitude and temperature .ii wind . a except as provided in c for take off take off flight path and landing requirements accountability for wind shall be no more than 50% of any reported steady headwind component of 5 kt or more . b where take off and landing with a tailwind component is permitted in the afm and in all cases for the take off flight path not less than 150% of any reported tailwind component shall be taken into account and . c where precise wind measuring equipment enables accurate measurement of wind velocity over the point of take off and landing wind components in excess of 50% may be established by the operator provided that the operator demonstrates to the competent authority that the proximity to the fato and accuracy enhancements of the wind measuring equipment provide an equivalent level of safety .4 the operating techniques and.5 the operation of any systems that have an adverse effect on performance 50% of the forecast headwind.

When calculating the performance of a class 2 helicopter with one engine ?

Question 101-19 : The pressure altitude the eta the surface of the landing site the height of obstructions on the go round

exemple 273 The pressure altitude. — Annex 6 operation of aircraft helicopter .to determine the performance of the helicopter account should be taken of at least the following factors .a mass of the helicopter .b elevation or pressure altitude and temperature and.c wind for take off and landing accountability for wind should be no more than 50 per cent of any reported steady headwind component of 5 knots or more where take off and landing with a tailwind component is permitted in the flight manual not less than 150 per cent of any reported tailwind component should be allowed where precise wind measuring equipment enables accurate measurement of wind velocity over the point of take off and landing these values may be varied The pressure altitude.

When considering the take off path for a helicopter with performance class 2 ?

Question 101-20 : 35 ft in vfr 35 ft + 0 001 dr in ifr 10 7 m + 0 01 dr in vfr 35 ft in ifr

exemple 277 35 ft in vfr. — Cat pol h 210 take off flight path .a from the end of the todrh with the critical engine failure recognised at the tdp.1 the take off mass shall be such that the take off flight path provides a vertical clearance above all obstacles located in the climb path 'of not less than 10 7 m 35 ft for operations under vfr' and 10 7 m 35 ft + 0 01 x distance dr for operations under ifr ..todrh take off distance required .tdp take off decision point . 702.cows are moving obstacles 35 ft in vfr.

When en route in a performance class 1 helicopter which has had an engine ?

Question 101-21 : 50 ft/min at an altitude of 2000 ft in mountainous areas 100 ft/min at an altitude of 300 m 150 ft/min at an altitude of 1000 ft 50 ft/min at an altitude of 300 ft

exemple 281 50 ft/min at an altitude of 2000 ft in mountainous areas. — 50 ft/min at an altitude of 2000 ft in mountainous areas.

When landing a performance class 2 helicopter with one engine inoperative the ?

Question 101-22 : 35 ft 35 m 15 ft a safe margin

exemple 285 35 ft. — Cat pol h 325 pc2 to cat pol h 220 landing .a the landing mass of the helicopter at the estimated time of landing shall not exceed the maximum mass specified in the afm for the procedure to be used .b in the event of the critical engine failure being recognised at any point at or before the landing decision point ldp it is possible either to land and stop within the fato or to perform a balked landing and clear all obstacles in the flight path by a vertical margin of 10 7 m 35 ft . 694 35 ft.

When landing at an elevated heliport a helicopter with performance class 1 and ?

Question 101-23 : 4 5 m 15 m 35 ft 35 m

exemple 289 4.5 m. — Img692.the balked landing at an elevated heliport may be accomplished using drop down techniques in order to accelerate to vtoss as the drop down is carried out beyond the dimensions of the heliport an obstacle clearance margin of at least 15 ft is required .15 ft = 4 5 m.vtoss take off safety speed 4.5 m.

When planning for landing a performance class 1 helicopter the following ?

Question 101-24 : Any expected change in mass during flight take off technique not more than 75% of forecast headwind the expected ambient pressure at the heliport

exemple 293 Any expected change in mass during flight. — The mass of a helicopter will change when lifting carrying cargo dropping off or picking up passengers in addition to the decrease in mass due to fuel consumption Any expected change in mass during flight.

When planning obstacle avoidance on the take off path of a performance class 1 ?

Question 101-25 : 7 x rotor radius r for day operations 30 ft 2 x length of helicopter 1 5 x length of the helicopter + 15 dr for ifr

exemple 297 7 x rotor radius (r) for day operations. — Cat pol h 110 obstacle accountability . .c obstacles may be disregarded if they are situated beyond .1 7 x rotor radius r for day operations if it is assured that navigational accuracy can be achieved by reference to suitable visual cues during the climb .2 10 x r for night operations if it is assured that navigational accuracy can be achieved by reference to suitable visual cues during the climb .3 300 m if navigational accuracy can be achieved by appropriate navigation aids or.4 900 m in all other cases 7 x rotor radius (r) for day operations.

Where is an official 'fuel flow chart' found ?

Question 101-26 : In the 'helicopter flight manual' in the 'maintenance manual' in the 'operators manual' in the 'type certificate'

exemple 301 In the 'helicopter flight manual'. — In the 'helicopter flight manual'.

Which of the following factors has the greatest effect on take off power ?

Question 101-27 : Density altitude light precipitation humidity airfield elevation

exemple 305 Density altitude. — Density altitude.

Which of the following groups of conditions are the most favourable for take off ?

Question 101-28 : Low airfield elevation low humidity low temperature high atmospheric pressure high airfield elevation low temperature high atmospheric pressure low airfield elevation high temperature low air density high airfield elevation low humidity high temperature low atmospheric pressure

exemple 309 Low airfield elevation, low humidity, low temperature, high atmospheric pressure. — Low airfield elevation, low humidity, low temperature, high atmospheric pressure.

Why is vne stated as an operating limitation .1 aerodynamic limitation.2 ?

Question 101-29 : 1 and 4 2 only 3 and 5 2 and 4

With one engine inoperative a helicopter with performance class 1 when landing ?

Question 101-30 : 35 ft 15 m 4 5 m a safe margin

exemple 317 35 ft. — Cat pol h 220 landing . .b in the event of the critical engine failure being recognised at any point at or before the landing decision point ldp it is possible either to land and stop within the fato or to perform a balked landing and clear all obstacles in the flight path by a vertical margin of 10 7 m 35 ft . 692 35 ft.

The height/velocity diagram or unsafe area ?

Question 101-31 : Is independent of the altitude at which the helicopter is operating does not exist for multi engine helicopters is independent of the type of landing gear or skid the helicopter is equipped with depends on the mass of the helicopter

exemple 321 Is independent of the altitude at which the helicopter is operating. — Is independent of the altitude at which the helicopter is operating.

Maximum endurance for a helicopter depends on ?

Question 101-32 : True airpseed indicated airspeed wind speed true airpseed or indicated airspeed

exemple 325 True airpseed. — Maximum endurance is achieved in unaccelerated level flight with minimum fuel flow .the speed to fly for maximum endurance is the speed at the lowest fuel flow per unit of time True airpseed.

A helicopter in performance class 3 must be certified in ?

Question 101-33 : Category a or b category a category b no category

exemple 329 Category a or b. — Category a or b.

At night operations in performance class 3 helicopters are ?

Question 101-34 : Never carried out only allowed in good moonlight only allowed with a good power margin routinely carried out

exemple 333 Never carried out. — Never carried out.

For take off with a tail wind component in class 2 performance an operator must ?

Question 101-35 : 150% of the reported tail wind component 50% of the reported tail wind component 80% of the reported tail wind component 120% of the reported tail wind component

exemple 337 150% of the reported tail wind component. — Cat pol h 105 general . .c when showing compliance with the requirements of this section account shall be taken of the following parameters .1 mass of the helicopter .2 the helicopter configuration .3 the environmental conditions in particular .i pressure altitude and temperature .ii wind . a except as provided in c for take off take off flight path and landing requirements accountability for wind shall be no more than 50% of any reported steady headwind component of 5 kt or more . b where take off and landing with a tailwind component is permitted in the afm and in all cases for the take off flight path not less than 150% of any reported tailwind component shall be taken into account and . c where precise wind measuring equipment enables accurate measurement of wind velocity over the point of take off and landing wind components in excess of 50% may be established by the operator provided that the operator demonstrates to the competent authority that the proximity to the fato and accuracy enhancements of the wind measuring equipment provide an equivalent level of safety .4 the operating techniques and.5 the operation of any systems that have an adverse effect on performance 150% of the reported tail wind component.

When planning for one engine inoperative in the cruise a helicopter of ?

Question 101-36 : 50 ft/min at 2000 ft in mountainous areas 100 ft/min 100 ft/min at 1000 ft 300 ft/min at 300 m

exemple 341 50 ft/min at 2000 ft in mountainous areas. — 50 ft/min at 2000 ft in mountainous areas.

Define the term 'performance class 2' ?

Question 101-37 : Performance class 2 operations are those operations such that in the event of critical power unit failure performance is available to enable the helicopter to safely continue the flight except when the failure occurs early during the take off manoeuvre or late in the landing manoeuvre in which cases a forced landing may be required performance class 2 operations are those with performance such that in the event of failure of the critical power unit the helicopter is able to land within the rejected take off distance available or safely continue the flight to an appropriate landing area depending on when the failure occurs performance class 2 helicopters means multi engine helicopters based on a critical engine failure concept which assures performance capability for continued safe flight in the event of an engine failure performance class 2 operations are those operations such that in the event of a power unit failure at any time during the flight a forced landing may be required in a multi engine helicopter but will be required in a single engine helicopter

exemple 345 Performance class 2 operations are those operations such that, in the event of critical power unit failure, performance is available to enable the helicopter to safely continue the flight, except when the failure occurs early during the take-off manoeuvre or late in the landing manoeuvre, in which cases a forced landing may be required. — Performance class 2 operations are those operations such that, in the event of critical power unit failure, performance is available to enable the helicopter to safely continue the flight, except when the failure occurs early during the take-off manoeuvre or late in the landing manoeuvre, in which cases a forced landing may be required.

In class 2 performance with one engine failed and the others operating a ?

Question 101-38 : 150 ft/min at 1000 ft above the destination and the alternate heliports 150 ft/min at 1000 ft above the destination heliport 150 ft/min at 200 ft above the destination heliport 150 ft/min at 200 ft above the destination and the alternate heliports

exemple 349 150 ft/min at 1000 ft above the destination and the alternate heliports. — 150 ft/min at 1000 ft above the destination and the alternate heliports.

Performance class 2 helicopters shall have a maximum approved seating ?

Question 101-39 : 19 or less but more than 9 19 or more 29 or more more than 19

exemple 353 19 or less but more than 9. — 19 or less but more than 9.

In class 1 performance with one engine failed and the others operating a ?

Question 101-40 : 150 ft/min at 1000ft and 100 ft/min at 200 ft above the destination and the alternate heliports 150 ft/min at 1000 ft above the destination and the alternate heliports 100 ft/min at 200 ft above the destination and the alternate heliports 150 ft/min at 1000 ft and 100 ft/min at 200ft above the destination heliport

exemple 357 150 ft/min at 1000ft and 100 ft/min at 200 ft, above the destination and the alternate heliports. — 150 ft/min at 1000ft and 100 ft/min at 200 ft, above the destination and the alternate heliports.

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