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At reference 033 345 .a twin jet aeroplane gross mass 200000 kg begin his ? [ Exam pilot ]

Question 102-1 : 192 500 kg 193 400 kg 193 800 kg 193 000 kg

On the reference for 200000 kg we have 6778 nm and 844 min .tas = 484 kt headwind = 30 kt.gs = 454 kt.time = 500/454 = 1 10h = 66 min.66 min + 7% = 71 min.844 min 71 min = 773 min.on the reference 773 minutes is corresponding to a value of 192 500 kg . ninorr .where did you take 7% from ..on the reference .total anti ice on .fuel= +7% exemple 202 192 500 kg.192 500 kg.

Planned and actual data as shown in the flight log excerpt 033 145 .actual ?

Question 102-2 : 2000 kg 2062 kg 2310 kg 2160 kg

Cqb15 january 2012 ..between alpha to beta actual consumption was 2470 2330 = 140 kg.140 kg for 20 minutes column 'ate' so 140x3 = 420 kg/heure .distance between beta and gamma is 85 nm column 'leg dist' at a ground speed of 110 kt .it will take .85 /110 = 0 773 h .0 773 x 420 = 325 kg of fuel burned .the fuel remaining over gamma should be .2330 325 = 2005 kg .closest answer 2000 kg exemple 206 2000 kg.2000 kg.

The trip fuel for a jet aeroplane to fly from the departure aerodrome to the ?

Question 102-3 : 14548 kg 14363 kg 14130 kg 15948 kg

Cqb15 january 2012 ..minimum quantity of fuel at take off = trip fuel + alternate + contingency + 30 min final reserve jet aircraft .trip fuel = 8350 kg .alternate = 4380 kg .contingency = the greater of 5% of trip or 5 min holding at 1500 ft .5% of trip = 5% x 8350 = 418 kg.5 min holding at 1500 ft = 2800 x 5/60 = 233 kg .30 min final reserve = 2800 /2 = 1400 kg .minimum quantity of fuel at take off = 8350 + 418 + 4380 + 1400 = 14548 kg exemple 210 14548 kg.14548 kg.

Use reference 033 046 .a turbojet aeroplane flies using the following data ?

Question 102-4 : 105 nm/1000 kg.5330 kg/h 105 nm/1000 kg.6515 kg/h 86 nm/1000 kg.6515 kg/h 71 nm/1000 kg.5330 kg/h

From reference for 190000 kg we get 6515 nam and tas 459 kt .6515 459 = 6056 nam > 184 600 kg.190 000 184 600 = 5400 kg/h.distance accomplished in one hour with the wind is 559 nm 459 + 100 .thus fuel consumption for 1000kg is 559/5 4 = 103 5 nm/1000kg exemple 214 105 nm/1000 kgxsx5330 kg/h.105 nm/1000 kgxsx5330 kg/h.

See reference 033 068 .given .distance between c to d 540 nm.cruise speed 300 ?

Question 102-5 : 4240 kg 4620 kg 3680 kg 3350 kg

Cqb15 january 2012 ..nam = ground distance x tas/gs .nam = 540 x 406/356 = 616 nm.from reference 033 068 at line 60000 the cruise distance nautical air miles is 3898 nautique air miles substract 616 you find 3282 nam .back to reference 033 068 what is the mass for 3282 nm we get 55800 kg.60000 55800=4200kg.last step we have to increase fuel required by 0 5 percent per 10 degrees above isa we are in isa+20°c so 1 percent more .4200x1%= 4242 kg ..see section 5 4 2 method page 24 on caa cap697 flight planning manual for that kind of questions .notice you must use the tas given for cruise 406 kt as state in the pdf document exemple 218 4240 kg.4240 kg.

Use route manual chart e hi 2.what is the meaning of the chart information for ?

Question 102-6 : Ndb only ident oe ndb ident oe and vor ident vey vor only ident vey vor/dme ident sup and ndb ident oe

. /com fr/com033 340 jpg. exemple 222 Ndb only, ident oe.Ndb only, ident oe.

Given .planned and actual data as shown in the flight log excerpt provided that ?

Question 102-7 : 4940 kg 5090 kg 4690 kg 5010 kg

Buhoraptor .hello my answer is 4990 kg .please can you tell me why there are difference thank you and congratulations for your website ..thank you .beta to gamma 10 minutes .fuel used 5440 5340 = 100 kg.fuel flow from beta to gamma 100 / 10 = 10 kg/min.planned time from gamma to delta 1 53 to 2 33 = 40 minutes .planned fuel from gamma to delta 40 min x 10 kg = 400 kg.on arrival overhead delta fuel on board will be .5340 400 = 4940 kg exemple 226 4940 kg.4940 kg.

Given .planning data as shown in the flight log excerpt fuel planning section ?

Question 102-8 : 5669 kg 5320 kg 6175 kg 6749 kg

.1h40 = 1 33 h.720 x 1 33 = 960 kg.estimated mass at destination est ldg mass at dest 6629 kg .6629 960 = 5669 kg exemple 230 5669 kg.5669 kg.

Given .planned and actual data as shown in the flight log excerpt .provided ?

Question 102-9 : 4550 kg 4740 kg 4140 kg 4640 kg

.beta to gamma 10 minutes .fuel used 5270 5150 = 120 kg.fuel flow from beta to gamma 120 / 10 = 12 kg/min.fuel used from gamma to delta 50 min x 12 kg = 600 kg.on arrival overhead delta fuel on board will be .5150 600 = 4550 kg exemple 234 4550 kg.4550 kg.

Given .planned and actual data as shown in the flight log excerpt.provided that ?

Question 102-10 : 4690 kg 4440 kg 4160 kg 4510 kg

.beta to gamma 65 minutes .fuel used 5490 4970 = 520 kg.fuel flow from beta to gamma 520 / 65 = 8 kg/min.fuel used from gamma to delta 35 min x 8 kg = 280 kg..on arrival overhead delta fuel on board will be .4970 280 = 4690 kg exemple 238 4690 kg.4690 kg.

Vtoss is the take off safety speed for ?

Question 102-11 : Category a helicopters class 2 helicopters single engine and multi engine helicopters single engine helicopters

Using attached graphic according to the flight manual diagram the never exceed ?

Question 102-12 : 115 kt 110 kt 120 kt 105 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 246 115 kt.115 kt.

According to the flight manual diagram the never exceed speed vne at pressure ?

Question 102-13 : 105 kt 110 kt 115 kt 125 kt

You must removed 10 kias at any gross mass above 2300 kg exemple 250 105 kt.105 kt.

Using attached graphic which letter indicates the speed for maximum endurance . ?

Question 102-14 : B c d a

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 254 BB

Using attached graphic which letter indicates the speed for the best rate of ?

Question 102-15 : B a c d

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 258 BB

Using attached graphic which letter indicates the speed for best range . 688 ?

Question 102-16 : C a b d

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 262 CC

A head wind will ?

Question 102-17 : Increase the climb flight path angle increase the angle of climb increase the rate of climb shorten the time to a given altitude

exemple 266 Increase the climb flight path angle.Increase the climb flight path angle.

A helicopter which has no guaranteed 'stay up' ability in the event of an ?

Question 102-18 : Category b category a category c category d

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 270 Category b.Category b.

A helicopter will obtain a maximum flight distance at the speed ?

Question 102-19 : For maximum range for minimum ho y fuel flow for maximum endurance the speed for minimum power required

exemple 274 For maximum range.For maximum range.

A hostile sea area is defined as being ?

Question 102-20 : South of 45°s south of 45°n where search and rescue response is too quick where there are few shipping lanes

exemple 278 South of 45°s.South of 45°s.

A platform is a heliport situated ?

Question 102-21 : 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 282 At least 3 m above the surrounding surfaceAt least 3 m above the surrounding surface

A safe forced landing is a landing ?

Question 102-22 : 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 286 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 102-23 : All engines operating all engines inoperative all exits open aft electrical bay overcharged

exemple 290 All engines operating.All engines operating.

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

Question 102-24 : 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 294 3 m.3 m.

An increase in ambient temperature ?

Question 102-25 : 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 298 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 102-26 : 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 302 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 102-27 : 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 306 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 102-28 : 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 310 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 102-29 : 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 314 100 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 102-30 : 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 exemple 318 10.7 m + 0.01 dr in ifr.10.7 m + 0.01 dr in ifr.

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

Question 102-31 : 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 322 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 102-32 : 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

exemple 326 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 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.

Density altitude is ?

Question 102-33 : Pressure altitude corrected for 'non standard' temperature altitude referenced to the standard datum altitude read directly from the altimeter height above the surface

exemple 330 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 102-34 : Increases the climb gradient decreases the climb gradient increases the distance required to descent 100 m has no effect on the climb gradient

exemple 334 Increases the climb gradient.Increases the climb gradient.

For a helicopter the distance dr is ?

Question 102-35 : 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 338 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 102-36 : 150 ft/min 100 ft/min 50 ft/min 300 ft/min

exemple 342 150 ft/min.150 ft/min.

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

Question 102-37 : 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 346 150% 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 102-38 : 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 350 150%.150%.

Helicopters operated in performance class 2 are certified in ?

Question 102-39 : Category a category b any of category a b or c category c

exemple 354 Category a.Category a.

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

Question 102-40 : 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 358 Both decrease.Both decrease.

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