Under what condition does pressure altitude has the same value as density altitude ?
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What is true about a clearway ?
The effect an increase of weight has on the value of stalling speed lAS is that Vs ?
An aircraft has a stall speed of 83 kt on short final its speed will be A clearway can be water or land must be under control of aerodrome authority. on (short) final you are supposed to be at 1 3 x vs. 
The parameters taken into account take off performance calculations are Outside temperature pressure altitude wind mass. on (short) final you are supposed to be at 1 3 x vs. 
For a piston engine aeroplane speed maximum range That which gives maximum lift to drag ratio. if you want to stay in flight longest time possible (maximum endurance) you need to fly at minimum power required speed (vmp velocity minimum power)) if you want to travel maximum distance possible (maximum range) you need to fly at speed that wich gives maximum lift to drag ratio (vmd velocity minimum drag) . 
Maximum endurance a piston engine aeroplane achieved at The speed that approximately corresponds to maximum rate of climb speed. maximum endurance in a piston engine aeroplane will occur at vmp (minimum power speed) you want to use as little fuel as possible in order to stay airborne as longer as possible you are not concerned with distance the best rate of climb will occur where you have excess power available that vy (best rate of climb speed) in a piston engine aeroplane that definitely slower than speed minimum drag (vmd) thus maximum endurance a piston engine aeroplane achieved at a speed that approximates best rate of climb speed (vmp) a common mistake done between trhust required curve (showing drags) power required curve (showing required power) for propeller driven aircraft curve lowest point of curve the tas at wich least power needed (as opposed to producing least drag) is therefore best endurance in level flight it also maximum rate of climb speed because gap between power required power available greatest (more power needed above below minimum power speed). Question 77-8
The maximum indicated air speed of a piston engine aeroplane without turbo charger in level flight reached At lowest possible altitude. maximum ias will always be achieved at sea level because this where density highest dynamic pressure 1/2 rho v² which sensed the pitot system. Question 77-9
At reference or see performance manual sep1 1 figure 2 4 with regard to graph landing performance what the minimum headwind component required in order to land at helgoland airport given runway length 1300 ftrunway elevation mslweather assume isa conditionsmass 3200 lbsobstacle height 50 ft 2104 At lowest possible altitude. please find hereafter full completed graph be aware that we must assume a factored runway (a piston engine airplane has to land in 70% of runway length) 1300 ft x 0 7 = 910 ft with this distance none of answers are correct. Question 77-10
How does thrust of a propeller vary during take off r assuming unstalled flow conditions at propeller blades the thrust Decreases while aeroplane speed builds up. the angle of attack as in case of a aircraft wing defined as angle between chord line relative airflow with a propeller however relative airflow the resultant of airflow due to rotation forward speed change either of these values the angle of attack will change the angle of attack decreases similar to a decreases of angle of attack an aircraft wing less lift will be produce a propeller it results in less thrust. Question 77-11
In a given configuration endurance of a piston engine aeroplane only depends on Altitude speed mass fuel on board. oszklarska the fuel on board weight contained in airplane mass it not ? therefore 'altitude speed mas answer equivalent to 'altitude speed mass fue no you need to know quantity of fuel on board to be able to calculate endurance (to stay airborne as longer as possible). Question 77-12
At a higher gross mass on a piston engined aeroplane in order to maintain a given angle of attack configuration and altitude The airspeed must be increased the drag will also increase. at a higher gross mass we need to increase lift (if we consider to maintain same altitude) lift = cl x 1/2 rho v² x s cl = lift coefficient rho = density v = tas (in m/s) s = surface since density surface lift coefficient (e g change in angle of attack) do not change only speed can changed therefore airspeed must be increased the drag will also increase. Question 77-13
On a reciprocating engine aeroplane to maintain a given angle of attack configuration and altitude at higher gross mass An increase in airspeed power required. at a higher gross mass we need to increase lift (if we consider to maintain same altitude) lift = cl x 1/2 rho v² x s cl = lift coefficient rho = density v = tas (in m/s) s = surface since density surface lift coefficient (e g change in angle of attack) do not change only speed can changed therefore power required increases airspeed will increased the drag will also increase notice whatever propulsion system (prop or jet) it doesn't play a role (as seen its absence in lift formula). Question 77-14
An aeroplane with reciprocating engines flying at a constant angle of attack mass and configuration with increasing altitude drag Remains unchanged but tas increases. with increasing altitude density (rho) decreases angle of attack mass configuration remain constant to maintain lift tas has to increase drag = cd x 1/2 x rho x v² (velocity = tas) v increases while rho decreases drag remains constant. Question 77-15
On a reciprocating engine aeroplane with increasing altitude at constant gross mass angle of attack and configuration power required Increases the tas increases the same percentage. this question compares an aircraft at a certain weight angle of attack a first altitude then in same configuration at a second altitude you have to understand that aircraft in straight level flight (it not climbing) our aircraft has to produce same lift lift (l) = 1/2 rho cl s v² for a higher altitude density reduces cl s remain unchanged thus only tas (v) can (and must) increase for that reason power required must increase. Question 77-16
At reference or see performance manual sep 1 figure 2 4 with regard to landing chart the single engine aeroplane determine landing distance from a height of 50 ft given o a t 27 °cpressure altitude 3000 ftaeroplane mass 2900 lbstailwind component 5 ktflaps landing position down runway tarred and dry 2146 Approximately 85 feet. . Question 77-17
performance manual sep 1 figure 2 4 with regard to landing chart the single engine aeroplane determine landing distance from a height of 50 ftgiven o a t isa +15°cpressure altitude 0 ftaeroplane mass 2940 lbtailwind component 10 ktflaps landing position down runway tarred and dry 2145 Approximately 93 feet. . Question 77-18
for this question use annex 032 005 or performance manual sep 1 figure 2 4 with regard to landing chart the single engine aeroplane determine landing distance from a height of 50 ft given oat isa +15°cpressure altitude 0 ftaeroplane mass 2940 lbheadwind component 10 ktflaps landing position down runway short and wet grass firm soil err _a_032 295 Approximately 8 feet. Img /com_en/com032 295 jpg oat isa +15°c so oat +30°c at 0 ft pressure altitude runway wet grass landing factor short grass 1 15 landing factor wet runway 1 15 1275 ft x 1 15 = 1466 ft 1466 ft x 1 15 = 1686 ft approximately 1800 feet our answer. Question 77-19
With regard to take off performance chart the single engine aeroplane determine maximum allowable take off mass given o a t isapressure altitude 4000 ftheadwind component 5 ktflaps uprunway tarred and dryfactored runway length 2000 ftobstacle height 50 ft 2143 Approximately 8 feet. complete graph with data you will find 3200 lbs. Question 77-20
At reference or see performance manual sep 1 figure 2 2 with regard to take off performance chart the single engine aeroplane determine take off distance to a height of 50 ft given oat 7°cpressure altitude 7000 ftaeroplane mass 2950 lbsheadwind component 5 ktflaps approach settingrunway tarred and dry err _a_032 297 Approximately 2 5 ft. Complete graph with data img /com_en/com032 297 jpg you find 1900 ft closest answer 2050 ft. Question 77-21
At reference or see performance manual sep 1 figure 2 1 with regard to take off performance chart the single engine aeroplane determine take off speed 1 rotation and 2 at a height of 50 ft given o a t isa+10°cpressure altitude 5000 ftaeroplane mass 3400 lbsheadwind component 5 ktflaps uprunway tarred and dry err _a_032 298 Approximately 2 5 ft. Img /com_en/com032 298 jpg . Question 77-22
At reference or see performance manual sep 1 figure 2 2 with regard to take off performance chart the single engine aeroplane determine take off distance to a height of 50 ft given o a t 38°cpressure altitude 4000 ftaeroplane mass 3400 lbstailwind component 5 ktflaps approach settingrunway dry grasscorrection factor 1 2 err _a_032 299 Approximately 396 ft. Img /com_en/com032 299 jpg do not forget to apply 'grass correction factor' 3300 ft x 1 2 = 3960 ft. Question 77-23
With regard to climb performance chart the single engine aeroplane determine climb speed ft/min o a t isa + 15°cpressure altitude 0 ftaeroplane mass 3400 lbsflaps upspeed 100 kias 2139 Approximately 396 ft. youssef92 for me i find that answer 1370ft/min if you start at 15°c instead of 30°c you will find around 1350 1370 ft but question states o a t isa + 15°c it means an outside temperature of 30°c at sea level. Question 77-24
At reference or see performance manual sep 1 figure 2 2 with regard to take off performance chart the single engine aeroplane determine take off distance over a 50 ft obstacle height given o a t 30°cpressure altitude 1000 ftaeroplane mass 2950 lbstailwind component 5 ktflaps approach settingrunway short wet grass firm subsoil if runway surface wet grass a 1 3 factor must beused err _a_032 301 Approximately 396 ft. Img /com_en/com032 3587 jpg 1750 ft x surface factor 1 3 = 2275 ft. Question 77-25
Using landing diagram single engine aeroplane determine landing distance from a screen height of 50 ft in following conditions given pressure altitude 4000 fto a t 5°caeroplane mass 3530 lbsheadwind component 15 ktflaps downrunway tarred and drylanding gear down 2135 Approximately 396 ft. 1320 ft (close to 1350 ft). Question 77-26
The pilot of a single engine aircraft has established climb performance the carriage of an additional passenger will cause climb performance to be Approximately 396 ft. 1320 ft (close to 1350 ft). Question 77-27
An extract of flight manual of a single engine propeller aircraft reproduced in annex airport characteristics hard dry and zero slope runwayactual conditions are pressure altitude 1 500 ftoutside temperature +18°cwind component 4 knots tailwindfor a take off mass of 1 270 kg take off distance will be 2137 Approximately 396 ft. 1270 kg = 2800 lbs convert 1520 ft to meters 1520 x 0 3048 = 463 m. Question 77-28
With regard to landing chart the single engine aeroplane determine landing distance from a height of 50 ft given o a t isapressure altitude 1000 ftaeroplane mass 3500 lbstailwind component 5 ktflaps landing position down runway tarred and dry 2136 Approximately 7 feet. you will find 1760 ft (close enough to 1700 feet). Question 77-29
With regard to take off performance chart the single engine aeroplane determine take off distance to a height of 50 ft given o a t 30°cpressure altitude 1000 ftaeroplane mass 3450 lbstailwind component 2 5 ktflaps uprunway tarred and dry 2134 Approximately 247 feet. . Question 77-30
For this question use reference or performance manual sep 1 figure 2 1with regard to take off performance chart the single engine aeroplane determine maximum allowable take off mass given oat isapressure altitude 4000 ftheadwind component 5 ktflaps uprunway tarred and dryfactored runway length 2000 ftobstacle height 50 ft err _a_032 359 Approximately 247 feet. Complete graph with data img /com_en/com032 359 jpg you will find 3240 lbs. Question 77-31
Consider graphic representation of power required versus true air speed tas a piston engined aeroplane with a given mass when drawing tangent from origin point of contact a determines speed of 2133 Maximum specific range. maximum specific range reached at minimum drag speed (vmd) a piston engined aeroplane vmd the speed maximum range in a prop aircraft vmd the speed maximum endurance in a jet aircraft. Question 77-32
For this question use reference sep 1 figure 2 3 using climb performance chart the single engine aeroplane determine ground distance to reach a height of 1500 ft above reference zero in following conditions given o a t at take off isaairport pressure altitude 5000 ftaeroplane mass 3300 lbsspeed 100 kiaswind component 5 kt tailwind err _a_032 362 Maximum specific range. At 5000 ft isa t° 5°c 1500/1080= 1 39 minute ground speed 100 + 5 = 105 kt (105/60) x 1 39 = 2 43 nm 2 43 = 4 5 km = 14722 ft img /com_en/com032 362 jpg closest answer 15640 ft normally we should use climb gradient since question gives a speed in ias but rate of climb can also lead closely to correct answer ebbr1000 tas= 108 kt height difference x 100/ climb gradient= (1500 x 100)/ 9 9 = 15151 ft (15151 x gs)/ tas= (15151 x 113)/ 108 = 15852 ft. Question 77-33
For this question use reference using climb performance chart the single engine aeroplane determine rate of climb and gradient of climb in following conditions given o a t at take off isaairport pressure altitude 3000 ftaeroplane mass 3450 lbsspeed 100 kias err _a_032 363 Maximum specific range. Isa at 3000 ft 15° (2° x 3) = +9°c for a given ias true airspeed about 2% higher than ias per 1000ft of altitude above sea level img /com_en/com032 363 jpg rate of climb 1140 ft/min gradient of climb 10 6% atplea figure cap698 figure 2 3. Question 77-34
At reference or use performance manual sep 1 figure 2 1airport characteristics hard dry and runway slope zeroactual conditions are pressure altitude 1500 ftoutside temperature +18°cwind component 4 kt tailwindfor a take off mass of 2800 lbs take off distance will be err _a_032 405 Maximum specific range. Img /com_en/com032 405 png . Question 77-35
Unless otherwise specified in afm a performance class b aeroplane landing on a downhill runway what factor must be applied each 1% of downslope Maximum specific range. Ecqb04 october 2017 the factor to be applied each 1% of downslope 5% (or 1 05). Question 77-36
Unless otherwise specified in afm a performance class b aeroplane taking off on a uphill runway what factor must be applied each 1% of uphill slope Maximum specific range. Ecqb04 october 2017 the factor to be applied each 1% of uphill slope 5% (or 1 05). Question 77-37
The following conditions are observed at an airport runway 13 wind 140° 30 kt a pilot can determine a crosswind component of Maximum specific range. vt = sin 10° x 30 = 5 kt. Question 77-38
Maximum crosswind demonstrated equal to 0 2 vs0 and following conditions are observed at an airport vs0 70kt landing runway 35 wind 300° 20 kt Maximum specific range. 350 300=50° crosswind sin50x20=15 3kt demonstrated crosswind 70x0 2=14kt. Question 77-39
Which margin above stall speed provided the landing speed reference vref Maximum specific range. 350 300=50° crosswind sin50x20=15 3kt demonstrated crosswind 70x0 2=14kt. Question 77-40
With regard to graph the light twin aeroplane will accelerate and stop distance be achieved in a take off where brakes are released before take off power set 2147 No performance will be worse than in chart. on associated condtions you can read 'full power before brake release' if you release brake before engine in full power your acceleration will be slower a longer runway distance required to accelerate until v1.
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