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A platform is a heliport situated ? [ Exam pilot ]

Question 105-1 : At least 3 m above the surrounding surface at least 35 ft above the surrounding surface 3 m above the surface on a fixed structure at sea on a floating or fixed structure at sea

Air operations.def.'elevated final approach and take off area elevated fato ' means a fato that is at least 3 m above the .surrounding surface exemple 205 At least 3 m above the surrounding surfaceAt least 3 m above the surrounding surface

A safe forced landing is a landing ?

Question 105-2 : Unavoidable landing or ditching with a reasonable expectancy of no injuries to persons in the aircraft or on the surface unavoidable landing on ground with a reasonable expectancy of no injuries to persons in the aircraft or on the surface a forced landing in which it can be reasonably hoped that there will be no injuries a landing or ditching which is unavoidable and in which it can be reasonably hoped that there will be no injuries to the occupants of the helicopter

exemple 209 Unavoidable landing or ditching with a reasonable expectancy of no injuries to persons in the aircraft or on the surface.Unavoidable landing or ditching with a reasonable expectancy of no injuries to persons in the aircraft or on the surface.

Aeo means ?

Question 105-3 : All engines operating all engines inoperative all exits open aft electrical bay overcharged

exemple 213 All engines operating.All engines operating.

An elevated heliport or helideck is defined as one which is above the ?

Question 105-4 : 3 m 10 m 3 ft 13 m

Air operations.def.'elevated final approach and take off area elevated fato ' means a fato that is at least 3 m above the .surrounding surface exemple 217 3 m.3 m.

An increase in ambient temperature ?

Question 105-5 : 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

exemple 221 Generally reduces performance in performance class 1 and especially the take-off weight.Generally reduces performance in performance class 1 and especially the take-off weight.

An increase in density altitude ?

Question 105-6 : Generally reduces performance in performance class 1 and decreases 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 dependingon the aircraft type

exemple 225 Generally reduces performance in performance class 1 and decreases especially the take-off weight.Generally reduces performance in performance class 1 and decreases especially the take-off weight.

An increase in pressure altitude ?

Question 105-7 : Generally reduces performance in class 1 and especially the take off weight increases performance in class 1 and especially the take off weight does not influence performance in class 1 and especially not on the take off weight increases or does not influence take off weight depending to aircraft type

exemple 229 Generally reduces performance in class 1 and especially the take-off weight.Generally reduces performance in class 1 and especially the take-off weight.

Assuming an engine failure has occurred during take off a performance class 1 ?

Question 105-8 : There is no additional margin to apply 35 ft 7r 3 m

Cat pol h 205 take off. .b the take off mass shall be such that .1 it is possible to reject the take off and land on the fato in case of the critical engine failure being recognised at or before the take off decision point tdp .2 the rejected take off distance required rtodrh does not exceed the rejected take off distance available rtodah and.3 the todrh does not exceed the take off distance available todah .4 notwithstanding b 3 the todrh may exceed the todah if the helicopter with the critical engine failure recognised at tdp can when continuing the take off clear all obstacles to the end of the todrh by a vertical margin of not less than 10 7 m 35 ft .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 only obstacles as specified in cat pol h 110 have to be considered .2 where a change of direction of more than 15° is made adequate allowance shall be made for the effect of bank angle on the ability to comply with the obstacle clearance requirements this turn is not to be initiated before reaching a height of 61 m 200 ft above the take off surface unless it is part of an approved procedure in the afm exemple 233 There is no additional margin to apply.There is no additional margin to apply.

Assuming one engine inoperative in a helicopter with performance class 1 during ?

Question 105-9 : 100 ft/min at 61 m 300 ft/min at 150 ft 60 m/sec at 200 ft 1000 ft/min at 150 ft

Cs 29 67 climb one engine inoperative . oei . a for category a rotorcraft in the critical take off configuration existing along the take off path the following apply . 1 the steady rate of climb without ground effect 61 m 200 ft above the take off surface must be at least 30 m 100 ft per minute for each weight altitude and temperature for which take off data are to be scheduled with exemple 237 100 ft/min at 61 m.100 ft/min at 61 m.

Assuming that an engine fails at some point during take off a helicopter of ?

Question 105-10 : 10 7 m + 0 01 dr in ifr 10 7 ft in vfr 35 m in ifr 35 m 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 only obstacles as specified in cat pol h 110 have to be considered .2 where a change of direction of more than 15° is made adequate allowance shall be made for the effect of bank angle on the ability to comply with the obstacle clearance requirements this turn is not to be initiated before reaching a height of 61 m 200 ft above the take off surface unless it is part of an approved procedure in the afm

The 'climb gradient' is defined as the ratio of ?

Question 105-11 : The increase of altitude to horizontal air distance expressed as a percentage the increase of altitude to distance over ground expressed as a percentage true airspeed to rate of climb rate of climb to true airspeed

The 'climb gradient' is defined as the ratio expressed as a percentage of the change in geometric height divided by the horizontal distance traveled .gradient = change in height/horizontal distance x 100%.for small angles of climb you can use rate of climb / true airspeed but this is not the exact definition of the 'climb gradient' exemple 245 The increase of altitude to horizontal air distance expressed as a percentage.The increase of altitude to horizontal air distance expressed as a percentage.

Define the term 'performance class 3' ?

Question 105-12 : Performance class 3 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 performance class 3 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 3 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 3 helicopters means single engine or multi engine helicopters which do not fully meet all class 2 standards class 3 helicopters have no guaranteed stay up ability in the event of engine failure and unscheduled landing is assumed

Density altitude is ?

Question 105-13 : Pressure altitude corrected for 'non standard' temperature altitude referenced to the standard datum altitude read directly from the altimeter height above the surface

exemple 253 Pressure altitude corrected for 'non standard' temperature.Pressure altitude corrected for 'non standard' temperature.

Flying in a straight line at constant airspeed a head wind ?

Question 105-14 : Increases the climb gradient decreases the climb gradient increases the distance required to descent 100 m has no effect on the climb gradient

exemple 257 Increases the climb gradient.Increases the climb gradient.

For a helicopter the distance dr is ?

Question 105-15 : The horizontal distance travelled from the end of the available runway length the rotor's diameter the horizontal distance travelled from the beginning of the take off the horizontal distance travelled since entering hovering flight

Distance dr dr is the horizontal distance that the helicopter has travelled from the end of the take off distance available . 698 exemple 261 The horizontal distance travelled from the end of the available runway length.The horizontal distance travelled from the end of the available runway length.

For a performance class 2 helicopter with one engine inoperative on take off ?

Question 105-16 : 150 ft/min 100 ft/min 50 ft/min 300 ft/min

exemple 265 150 ft/min.150 ft/min.

For take off with a tail wind component in class 1 performance an operator must ?

Question 105-17 : 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

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 exemple 269 150% of the reported tail wind component.150% of the reported tail wind component.

For the calculation of mtow for a performance class 1 helicopter the following ?

Question 105-18 : 150% 50% 100% 75%

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 exemple 273 150%.150%.

Helicopters operated in performance class 2 are certified in ?

Question 105-19 : Category a category b any of category a b or c category c

exemple 277 Category a.Category a.

How do the best angle of climb speed and best rate of climb speed vary with ?

Question 105-20 : Both decrease both increase best angle of climb increases while best rate of climb decreases best angle of climb decreases while best rate of climb increases

The higher you go the less power you will have .you can increase the angle of climb only if you have an excess of thrust or a rate of climb excess power .eventually the helicopter will not be able to climb if the helicopter has reached its absolute ceiling exemple 281 Both decrease.Both decrease.

If a helicopter is flying horizontally at its service ceiling ?

Question 105-21 : Its speed has to be maintained in a small range vmin is close to vmax the helicopter must be flown at vmax the helicopter must be flown at vmin vmin will coincide with vmax

exemple 285 Its speed has to be maintained in a small range (vmin is close to vmax).Its speed has to be maintained in a small range (vmin is close to vmax).

If during descent in a performance class 1 helicopter which has one engine ?

Question 105-22 : A safe drift down procedure a safe forced landing a diversion a hold

Performance class 1. cat pol h 215 en route critical engine inoperative .a the mass of the helicopter and flight path at all points along the route with the critical engine inoperative and the meteorological conditions expected for the flight shall permit compliance with 1 2 or 3 .1 when it is intended that the flight will be conducted at any time out of sight of the surface the mass of the helicopter permits a rate of climb of at least 50 ft/minute with the critical engine inoperative at an altitude of at least 300 m 1000 ft or 600 m 2000 ft in areas of mountainous terrain above all terrain and obstacles along the route within 9 3 km 5 nm on either side of the intended track .2 when it is intended that the flight will be conducted without the surface in sight the flight path permits the helicopter to continue flight from the cruising altitude to a height of 300 m 1000 ft above a landing site where a landing can be made in accordance with cat pol h 220 the flight path clears vertically by at least 300 m 1000 ft or 600 m 2000 ft in areas of mountainous terrain all terrain and obstacles along the route within 9 3 km 5 nm on either side of the intended track drift down techniques may be used .3 when it is intended that the flight will be conducted in vmc with the surface in sight the flight path permits the helicopter to continue flight from the cruising altitude to a height of 300 m 1000 ft above a landing site where a landing can be made in accordance with cat pol h 220 without flying at any time below the appropriate minimum flight altitude obstacles within 900 m on either side of the route need to be considered .b when showing compliance with a 2 or a 3 .1 the critical engine is assumed to fail at the most critical point along the route .2 account is taken of the effects of winds on the flight path .3 fuel jettisoning is planned to take place only to an extent consistent with reaching the aerodrome or operating site with the required fuel reserves and using a safe procedure and.4 fuel jettisoning is not planned below 1000 ft above terrain .c the width margins of a 1 and a 2 shall be increased to 18 5 km 10 nm if the navigational accuracy cannot be met for 95% of the total flight time exemple 289 A safe drift-down procedure.A safe drift-down procedure.

In a descent with one engine inoperative a helicopter with performance class 1 ?

Question 105-23 : 300 m 1000 m 600 m 10 m

Performance class 1. cat pol h 215 en route critical engine inoperative .a the mass of the helicopter and flight path at all points along the route with the critical engine inoperative and the meteorological conditions expected for the flight shall permit compliance with 1 2 or 3 .1 when it is intended that the flight will be conducted at any time out of sight of the surface the mass of the helicopter permits a rate of climb of at least 50 ft/minute with the critical engine inoperative at an altitude of at least 300 m 1000 ft or 600 m 2000 ft in areas of mountainous terrain above all terrain and obstacles along the route within 9 3 km 5 nm on either side of the intended track .2 when it is intended that the flight will be conducted without the surface in sight the flight path permits the helicopter to continue flight from the cruising altitude to a height of 300 m 1000 ft above a landing site where a landing can be made in accordance with cat pol h 220 the flight path clears vertically by at least 300 m 1000 ft or 600 m 2000 ft in areas of mountainous terrain all terrain and obstacles along the route within 9 3 km 5 nm on either side of the intended track drift down techniques may be used .3 when it is intended that the flight will be conducted in vmc with the surface in sight the flight path permits the helicopter to continue flight from the cruising altitude to a height of 300 m 1000 ft above a landing site where a landing can be made in accordance with cat pol h 220 without flying at any time below the appropriate minimum flight altitude obstacles within 900 m on either side of the route need to be considered .b when showing compliance with a 2 or a 3 .1 the critical engine is assumed to fail at the most critical point along the route .2 account is taken of the effects of winds on the flight path .3 fuel jettisoning is planned to take place only to an extent consistent with reaching the aerodrome or operating site with the required fuel reserves and using a safe procedure and.4 fuel jettisoning is not planned below 1000 ft above terrain .c the width margins of a 1 and a 2 shall be increased to 18 5 km 10 nm if the navigational accuracy cannot be met for 95% of the total flight time exemple 293 300 m.300 m.

In a given configuration mass and fuel on board the endurance of a helicopter ?

Question 105-24 : Depends on altitude and true air speed depends on altitude and wind conditions depends on groundspeed and altitude depends on altitude only

exemple 297 Depends on altitude and true air speed.Depends on altitude and true air speed.

In a power off autorotation in still air to obtain the maximum glide range the ?

Question 105-25 : At a speed close to the best range speed and with minimum rotor speed without exceeding the vne power off at a speed close to the vne at a speed close to the vne power on at a speed close to maximum endurance speed

exemple 301 At a speed close to the best range speed and with minimum rotor speed without exceeding the vne power-off.At a speed close to the best range speed and with minimum rotor speed without exceeding the vne power-off.

In a power off autorotation in still air to obtain the minimum rate of descent ?

Question 105-26 : At a speed close to the vy and with minimum rotor speed at a speed close to zero at a speed close to the vne at a speed close to maximum range speed

exemple 305 At a speed close to the vy and with minimum rotor speed.At a speed close to the vy and with minimum rotor speed.

In flight level in class 2 performance with one engine failed and the others ?

Question 105-27 : At least 50 ft/mn at least 100 ft/mn at least 150 ft/mn at a no definit value by the autority

Cat pol h 320 en route critical engine inoperative.the mass of the helicopter and flight path at all points along the route with the critical engine inoperative and the meteorological conditions expected for the flight shall permit compliance with 1 2 or 3 .1 when it is intended that the flight will be conducted at any time out of sight of the surface the mass of the helicopter permits a rate of climb of at least 50 ft/minute with the critical engine inoperative at an altitude of at least 300 m 1 000 ft or 600 m 2 000 ft in areas of mountainous terrain above all terrain and obstacles along the route within 9 3 km 5 nm on either side of the intended track exemple 309 At least 50 ft/mnAt least 50 ft/mn

In performance class 1 when there is a head wind component an operator when ?

Question 105-28 : More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement less than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement not more than 50% of the reported headwind not more than 150% of the reported headwind 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 exemple 313 More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.

In performance class 1 having cleared the elevated heliport or heliplatform's ?

Question 105-29 : At least 35 ft vertically 35 ft at least 35 ft at least 15 ft vertically

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 only obstacles as specified in cat pol h 110 have to be considered . 695.be aware that the question specifically states ' having cleared the elevated heliport or heliplatform's edge ' exemple 317 At least 35 ft vertically.At least 35 ft vertically.

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

Question 105-30 : The destination or alternate/diversion heliport the destination heliport the alternate heliport the take off heliport

exemple 321 The destination or alternate/diversion heliport.The destination or alternate/diversion heliport.

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

Question 105-31 : The destination or alternate/diversion heliport the alternate heliport the destination heliport the take off heliport

exemple 325 The destination or alternate/diversion heliport.The destination or alternate/diversion heliport.

In performance class 2 when there is a head wind component an operator when ?

Question 105-32 : More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement less than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement not more than 50% of the reported headwind not more than 150% of the reported headwind 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 exemple 329 More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.

In performance class 1 when the wind measuring equipment has not received ?

Question 105-33 : Most 50% of the reported headwind component least 50% of the reported headwind component most 80% of the reported headwind component most 40% of the reported headwind 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 exemple 333 Most, 50% of the reported headwind component.Most, 50% of the reported headwind component.

In performance class 2 when the wind measuring equipment has not received ?

Question 105-34 : Most 50% of the reported headwind component least 50% of the reported headwind component most 80% of the reported headwind component most 40% of the reported headwind 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 exemple 337 Most, 50% of the reported headwind component.Most, 50% of the reported headwind component.

In straight and level flight at constant indicated airspeed a reduction in ?

Question 105-35 : Reduces the power required increases the power required increases or reduces the power required depending on the airspeed does not affect the power required

exemple 341 Reduces the power required.Reduces the power required.

In the context of performance planning dr means ?

Question 105-36 : The horizontal distance travelled from the end of the take off distance available the horizontal distance remaining to the end of the todah the horizontal distance to the first significant obstacle the range to the first waypoint

Distance dr dr is the horizontal distance that the helicopter has travelled from the end of the take off distance available . 698 exemple 345 The horizontal distance travelled from the end of the take-off distance available.The horizontal distance travelled from the end of the take-off distance available.

In the cruise a helicopter with performance class 3 must be able to fly at ?

Question 105-37 : The minimum flight altitude the normal range speed vne minimum power speed

exemple 349 The minimum flight altitude.The minimum flight altitude.

In which document is an official 'power required chart' to be found ?

Question 105-38 : In the 'helicopter flight manual' in the 'maintenance manual' in the 'operators manual' in the 'type certificate'

exemple 353 In the 'helicopter flight manual'.In the 'helicopter flight manual'.

Landing distance required means ?

Question 105-39 : The distance from a specified point on the approach until the helicopter comes to rest the distance required for a running landing the distanced required to accelerate to vtoss the distance required to accelerate from rest to a specified point on the take off path

exemple 357 The distance from a specified point on the approach until the helicopter comes to rest.The distance from a specified point on the approach until the helicopter comes to rest.

Large rotorcraft are those of maximum weight of ?

Question 105-40 : 9072 kg 20000 lbs or more 9072 lbs 20000 kg or more 9072 lbs or more 9071 kg or more

Large rotorcraft are classified in .accordance of cs 29 exemple 361 9072 kg (20000 lbs or more).9072 kg (20000 lbs or more).

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