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Question 126-1 : The 'climb gradient' is defined as the ratio of ? [ Preparation civilian ]
The increase of altitude to horizontal air distance expressed as a percentage.
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'.
Question 126-2 : Define the term 'performance class 3'. ?
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.
Question 126-3 : Density altitude is ?
Pressure altitude corrected for 'non standard' temperature.
Question 126-4 : Flying in a straight line at constant airspeed, a head wind ?
Increases the climb gradient.
Question 126-5 : For a helicopter the distance dr is ?
The horizontal distance travelled from the end of the available runway length.
Distance dr dr is the horizontal distance that the helicopter has travelled from the end of the take off distance available... 698
Question 126-6 : For a performance class 2 helicopter with one engine inoperative, on take off, the rate of climb at 1000 ft above the heliport must be at least ?
150 ft/min.
Question 126-7 : For take off with a tail wind component in class 1 performance an operator must take account of at least ?
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.
Question 126-8 : For the calculation of mtow for a performance class 1 helicopter, the following factoring of reported tail wind is used ?
150%.
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.
Question 126-9 : Helicopters operated in performance class 2 are certified in ?
Category a.
Question 126-10 : How do the best angle of climb speed and best rate of climb speed vary with increasing altitude ?
Both decrease.
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.
Question 126-11 : If a helicopter is flying horizontally at its service ceiling ?
Its speed has to be maintained in a small range vmin is close to vmax.
Question 126-12 : 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 safe drift down procedure.
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.
Question 126-13 : In a descent, with one engine inoperative, a helicopter with performance class 1 must follow a flight path which clears all obstacles vertically by ?
300 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.
Question 126-14 : In a given configuration, mass and fuel on board, the endurance of a helicopter ?
Depends on altitude and true air speed.
Question 126-15 : In a power off autorotation in still air, to obtain the maximum glide range, the helicopter should be flown ?
At a speed close to the best range speed and with minimum rotor speed without exceeding the vne power off.
Question 126-16 : In a power off autorotation in still air, to obtain the minimum rate of descent, the helicopter should be flown ?
At a speed close to the vy and with minimum rotor speed.
Question 126-17 : In flight level, in class 2 performance, with one engine failed and the others operating, at 1000 ft above any obstacle along his road, the weight of the helicopter must allow it to climb ?
At least 50 ft/mn
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.
Question 126-18 : In performance class 1 when there is a head wind component, an operator, when calculating take off performance may take into account... ?
More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.
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.
Question 126-19 : In performance class 1, having cleared the elevated heliport or heliplatform's edge, in case of an engine failure after the take off decision point, the helicopter can clear any obstacle until the end of the take off required distance with a margin of ?
At least 35 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...'.
Question 126-20 : 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 100ft/mn at 200 ft above the altitude of ?
The destination or alternate/diversion heliport.
Question 126-21 : 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.
Question 126-22 : In performance class 2 when there is a head wind component, an operator, when calculating take off performance may take into account... ?
More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.
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.
Question 126-23 : 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 ?
Most, 50% 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.
Question 126-24 : In performance class 2, 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 ?
Most, 50% 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.
Question 126-25 : In straight and level flight at constant indicated airspeed, a reduction in pressure altitude ?
Reduces the power required.
Question 126-26 : In the context of performance planning, dr means ?
The horizontal distance travelled from the end of the take off distance available.
Distance dr dr is the horizontal distance that the helicopter has travelled from the end of the take off distance available... 698
Question 126-27 : In the cruise, a helicopter with performance class 3, must be able to fly at ?
The minimum flight altitude.
Question 126-28 : In which document is an official 'power required chart' to be found ?
In the 'helicopter flight manual'.
Question 126-29 : Landing distance required means ?
The distance from a specified point on the approach until the helicopter comes to rest.
Question 126-30 : Large rotorcraft are those of maximum weight of ?
9072 kg 20000 lbs or more.
Large rotorcraft are classified in.accordance of cs 29.
Question 126-31 : Ldrh is the horizontal distance required to land ?
And stop completely from a point 50 ft above the landing surface.
Annex 6 operation of aircraft helicopter part 3 ..landing distance required ldrh the horizontal distance required to land and come to a full stop from a point 15 m 50 ft above the landing surface.
Question 126-32 : Maximum endurance... ?
Will be achieved by flying with minimum fuel flow kg/h.
Question 126-33 : Maximum range for a helicopter ?
Will be obtained at the optimum altitude.
Question 126-34 : Minimum weather limits are applied to helicopter class 3 operations. these are ?
Cloud ceiling is less than 600 ft above local surface.
Cat.pol.h.400 general.....d operations shall not be conducted..1 out of sight of the surface.2 at night.3 when the ceiling is less than 600 ft or.4 when the visibility is less than 800 m.
Question 126-35 : On the take off of a performance class 2 helicopter from an elevated heliport, the take off weight must be such that if one engine becomes inoperative at or after dpato ?
The helicopter may continue its flight.
Dpato defined point after take off.
Question 126-36 : Performance class 3 helicopters are certified in ?
Category a or b.
Question 126-37 : Performance class 3 may be defined, for a single engined helicopter such that, if an engine becomes inoperative ?
A forced landing will result.
Question 126-38 : Performance class 3 operations to or from helidecks are ?
Never made.
Question 126-39 : Performance planning is required to ensure that ?
The space required for a manoeuvre is less than the space available.
Performance planning refers to weight calculation in order to safely manoeuvring the helicopter. if the space required for a manoeuvre the clearance path for take off or landing is equal or greater than the space available you will not be able to perform the manoeuvre.
Question 126-40 : Performance such that, in the event of failure of a critical power unit, enables a helicopter to land within the rejected take off distance available is ?
Performance class 1.
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