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Question 112-1 : Using attached graphic according to the flight manual diagram the never exceed speed vne at pressure altitude 10 000 ft with an outside air temperature oat of +10°c and an inflight mass of 2050 kg is . 687 ? [ Training professional ]

115 kt

Vne at 10000 ft oat +10°c and 2300 kg is 115 kt ias .the graphic states at any gross mass above 2300 kg decrease vne by 10 kias .since the inflight mass is below 2300 kg we do not change the value exemple 212 115 kt.

Question 112-2 : According to the flight manual diagram the never exceed speed vne at pressure altitude 10 000 ft with an outside air temperature oat of +10° c and an inflight mass of 2400 kg is . 662 ?

105 kt

You must removed 10 kias at any gross mass above 2300 kg exemple 216 105 kt.

Question 112-3 : Using attached graphic which letter indicates the speed for maximum endurance . 688 ?

B

Power required curve power versus airspeed chart . 690.a power required to hover outside ground effect.b power required to hover inside ground effect.c translational lift area.d adjustment of power required to counteract sinking.e minimum power for level flight/maximum rate of climb speed/ speed for maximum endurance exemple 220 B

Question 112-4 : Using attached graphic which letter indicates the speed for the best rate of climb . 688 ?

B

Power required curve power versus airspeed chart . 690.a power required to hover outside ground effect.b power required to hover inside ground effect.c translational lift area.d adjustment of power required to counteract sinking.e minimum power for level flight/ maximum rate of climb speed / speed for maximum endurance exemple 224 B

Question 112-5 : Using attached graphic which letter indicates the speed for best range . 688 ?

C

The best range will be reach at the minimum total drag speed .power required curve power versus airspeed chart . 690.a power required to hover outside ground effect.b power required to hover inside ground effect.c translational lift area.d adjustment of power required to counteract sinking.e minimum power for level flight/maximum rate of climb speed/ speed for maximum endurance exemple 228 C

Question 112-6 : A head wind will ?

Increase the climb flight path angle

exemple 232 Increase the climb flight path angle.

Question 112-7 : A helicopter which has no guaranteed 'stay up' ability in the event of an engine failure is certified in ?

Category b

No guaranteed stay up ability means that the helicopter cannot maintain level flight in case of an engine failure .category b helicopters single engine or a multi engine helicopter that does not meet category a standards have no guaranteed ability to continue safe flight in the event of an engine failure and a forced landing is assumed exemple 236 Category b.

Question 112-8 : A helicopter will obtain a maximum flight distance at the speed ?

For maximum range

exemple 240 For maximum range.

Question 112-9 : A hostile sea area is defined as being ?

South of 45°s

exemple 244 South of 45°s.

Question 112-10 : A platform is a heliport situated ?

At least 3 m above the surrounding surface

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 248 At least 3 m above the surrounding surface

Question 112-11 : A safe forced landing is a landing ?

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

exemple 252 Unavoidable landing or ditching with a reasonable expectancy of no injuries to persons in the aircraft or on the surface.

Question 112-12 : Aeo means ?

All engines operating

exemple 256 All engines operating.

Question 112-13 : An elevated heliport or helideck is defined as one which is above the surrounding level by ?

3 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 260 3 m.

Question 112-14 : An increase in ambient temperature ?

Generally reduces performance in performance class 1 and especially the take off weight

exemple 264 Generally reduces performance in performance class 1 and especially the take-off weight.

Question 112-15 : An increase in density altitude ?

Generally reduces performance in performance class 1 and decreases especially the take off weight

exemple 268 Generally reduces performance in performance class 1 and decreases especially the take-off weight.

Question 112-16 : An increase in pressure altitude ?

Generally reduces performance in class 1 and especially the take off weight

exemple 272 Generally reduces performance in class 1 and especially the take-off weight.

Question 112-17 : Assuming an engine failure has occurred during take off a performance class 1 helicopter which plans a turn in the climb of more than 15° must be capable of clearing vertical obstructions by an extra ?

There is no additional margin to apply

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 276 There is no additional margin to apply.

Question 112-18 : Assuming one engine inoperative in a helicopter with performance class 1 during an approach to land the following minimum rate of climb must be achievable ?

100 ft/min at 61 m

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 280 100 ft/min at 61 m.

Question 112-19 : Assuming that an engine fails at some point during take off a helicopter of performance class 1 must be able to clear all obstacles vertically by ?

10 7 m + 0 01 dr in ifr

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 284 10.7 m + 0.01 dr in ifr.

Question 112-20 : The 'climb gradient' is defined as the ratio of ?

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' exemple 288 The increase of altitude to horizontal air distance expressed as a percentage.

Question 112-21 : 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

exemple 292 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 112-22 : Density altitude is ?

Pressure altitude corrected for 'non standard' temperature

exemple 296 Pressure altitude corrected for 'non standard' temperature.

Question 112-23 : Flying in a straight line at constant airspeed a head wind ?

Increases the climb gradient

exemple 300 Increases the climb gradient.

Question 112-24 : 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 exemple 304 The horizontal distance travelled from the end of the available runway length.

Question 112-25 : 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

exemple 308 150 ft/min.

Question 112-26 : 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 exemple 312 150% of the reported tail wind component.

Question 112-27 : 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 exemple 316 150%.

Question 112-28 : Helicopters operated in performance class 2 are certified in ?

Category a

exemple 320 Category a.

Question 112-29 : 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 exemple 324 Both decrease.

Question 112-30 : 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

exemple 328 Its speed has to be maintained in a small range (vmin is close to vmax).

Question 112-31 : 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 exemple 332 A safe drift-down procedure.

Question 112-32 : 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 exemple 336 300 m.

Question 112-33 : In a given configuration mass and fuel on board the endurance of a helicopter ?

Depends on altitude and true air speed

exemple 340 Depends on altitude and true air speed.

Question 112-34 : 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

exemple 344 At a speed close to the best range speed and with minimum rotor speed without exceeding the vne power-off.

Question 112-35 : 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

exemple 348 At a speed close to the vy and with minimum rotor speed.

Question 112-36 : 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 exemple 352 At least 50 ft/mn

Question 112-37 : 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 exemple 356 More than 50% of the headwind component if a precise wind measuring equipment enables accurate measurement.

Question 112-38 : 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 ' exemple 360 At least 35 ft vertically.

Question 112-39 : 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

exemple 364 The destination or alternate/diversion heliport.

Question 112-40 : 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

exemple 368 The destination or alternate/diversion heliport.


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