5863486
Description
Quiz by tsampikos pompou, updated more than 1 year ago
|
Created by tsampikos pompou
almost 8 years ago
|
|
Question 1
Question
175 An aeroplane operating from a flat runway in the same wind conditions as when operating from an up-sloping runway will require a ....(i).... take-off distance and a ....(ii).... landing distance.
Answer
-
O (i) shorter (ii) longer
-
O (i) longer (ii) longer
-
O (i) longer (ii) shorter
-
O (i) shorter (ii) shorter
Question 2
Question
179 Pressure altitude is frequently employed as the datum for measuring aircraft performance. Given an aerodrome elevation as 1010ft amsl and a QFE of 990hPa.
What is the aerodrome pressure altitude? [1mb = 30ft]
Answer
-
O 1700ft
-
O 1500ft
-
O 1244ft
-
O 1623ft.
Question 3
Question
181 Flight for maximum range in a piston engined normally aspirated aircraft is achieved by flying:
Answer
-
O at just above the minimum drag speed.
-
O at the lowest density altitude that is safely possible.
-
O just below that speed which provides the maximum power/airspeed ratio.
-
O at the same speed, where minimum difference between power required and power available exist.
Question 4
Question
183 The remaining fuel weight available for computing mass and balance, is 285 Kgs AVGAS of specific gravity 0.70. Determine how many litres the pump will indicate to be within limits.
Answer
-
O 407 lts.
-
O 1995 lts.
-
O 355 lts.
-
O 500 lts.
Question 5
Question
184 In a constant IAS climb in the troposphere?
Answer
-
O TAS increases.
-
O TAS decreases.
-
O TAS increases, then remains constant.
-
O TAS decreases, then remains constant.
Question 6
Question
186 The relationship between Vx and Vy?
Answer
-
O Vx is always less than or equal to Vy.
-
O Vx is always less than Vy.
-
O Vx is always greater than Vy,
-
O There's no between them.
Question 7
Question
188 Loading icreases, then……………………
Answer
-
O Vx and Vy increase.
-
O Vx increases and Vy decreases.
-
O Vx decreases and Vy increases.
-
O both Vx and Vy decrease.
Question 8
Question
199 If the aeroplane in Fig. 27 quits engine at 8.000 ft, the distance will cover in still air conditions, is:
Answer
-
O 12 nm
-
O 10 nm
-
O 14 nm
-
O 13 nm.
Question 9
Question
200 An aircraft with full tanks has 500 litres on board. Given that the fuel specific gravity is 0.750, the weight of the fuel will be:
Answer
-
O 825 lbs or 375 Kgrs.
-
O 800 lbs. or 362 Kgrs
-
O 820 lbs or 372 Kgrs.
-
O 900 lbs or 407 Kgrs.
Question 10
Question
203 What effect has a centre of gravity close to the forward limit?
Answer
-
O A reduce rate of climb
-
O A better rate of climb capability
-
O A reduction in the specific fuel consumption
-
O A decreased induced drag
Question 11
Question
206 Consult Fig.30 that's in accordance with CAP 696
Where is the reference datum?
Answer
-
O 39 inches forward of the firewall
-
O 74 inches aft of the fwd CG position
-
O 80.4 inches aft of the rear CG position
-
O 87.7 inches aft of the rear CG position
Question 12
Question
207 Consult Fig.30 that's in accordance with CAP 696
What are the CG limits?
Answer
-
O fwd limit = 74 inches to 80.4 inches and aft limit = 87.7 inches
-
O fwd limit = 74 inches to 80.4 inches
-
O fwd limit = 74 inches, aft limit = 80.4 inches
-
O fwd limit = 74 inches, aft limit = 87.7 inches
Question 13
Question
208 Consult Fig.30 that's in accordance with CAP 696
What is the CG at the BEM?
Answer
-
O 77.7 inches
-
O 77 inches
-
O 87 inches
-
O 77.7 centimetres
Question 14
Question
209 Consult Fig.30 that's in accordance with CAP 696
What is the distance of the main undercarriage from the firewall?
Answer
-
O 58 inches
-
O 97 inches
-
O 87.7 inches
-
O 39 inches
Question 15
Question
210 Consult Fig.30 that's in accordance with CAP 696
The aircraft has six seats. Assuming no other cargo or baggage, what is the maximum fuel (in 74USG capacity version), that can be carried if all six seats are occupied and the mass of each occupant is 180 lb?
Answer
-
O 155 lbs but the CG would be dangerously out of limits
-
O 296 lbs but the CG would be dangerously out of limits
-
O 444 lbs and the CG would be dangerously out of limits
-
O 1551bs and the CG would be in limits since tank fuel capacity is 74USG.
Question 16
Question
211 Consult Fig.30 that's in accordance with CAP 696
If the landing mass is 3075 lb and the trip fuel was 40 USG, what was the ZFM if the fuel tanks held 60 gallons of fuel prior to take-off?
Answer
-
O 3000 lb
-
O 3035lb
-
O 3590 lb
-
O 3055lb
Question 17
Question
212 Fig.30 that's in accordance with CAP 696
What is the maximum ramp mass (MRM), out of hangar?
Answer
-
O 3663 lbs
-
O 3650 lbs
-
O 3780 lbs
-
O 3880 lbs
Question 18
Question
213 Consult Fig.30 that's in accordance with CAP 696
How far is the main wheel from the aft CG limit?
Answer
-
O 9.3 inches aft of the rear datum
-
O 0.7 inches behind the rear datum
-
O 0.7 inches forward of the rear datum
-
O 6.6 inches forward of the rear datum
Question 19
Question
216 The Take-off mass is:
Answer
-
O the mass of the aeroplane including everyone and everything contained within it at the start of the take-off run.
-
O the maximum permissible total aeroplane mass on completion of the refuelling operation.
-
O the maximum permissible total aeroplane mass for take-off but excluding fuel.
-
O the maximum permissible total aeroplane mass at the start of the take-off run.
Question 20
Question
218 If an aeroplane is at elevation of 660ft and QFE is 1003 hPa, the approximate Pressure Altitude is:
Answer
-
O 300ft
-
O 660ft
-
O 350ft
-
O 365ft
Question 21
Question
219 The Basic Empty Mass is the:
Answer
-
O Operating mass minus the crew and fuel load
-
O MZFM minus both traffic load and the fuel load
-
O Take-off mass minus the traffic load and the fuel load
-
O Landing mass less traffic load
Question 22
Question
220 (Refer to Fig.7) What is the maxi¬mum amount of baggage that may be loaded aboard the airplane for the CG to remain within the moment envelope?
MASS (LB) MOM/1000
Basic Empty Mass 1,350 51.5
Pilot and front passenger 250 -
Rear passengers 400 -
Baggage - -
Fuel, 27 USG _ _
Oil, 8qt - -0.2
Answer
-
O 165 pounds.
-
O 110 pounds.
-
O 120 pounds.
-
O 150 pounds
Question 23
Question
221 (Refer to Fig.7) Calculate the moment of the airplane and determine which category is applicable.
MASS (LB) MOM/1000
Basic Empty Mass 1,350 51.5
Pilot and front pass 380 -
Rear passengers 96 -
Fuel, 38 gal - _
Oil, 8 qt - -0.2
Answer
-
O 80.3 (lb-in), utility category.
-
O 69.2 (lb-in), utility category.
-
O 81.2 (lb-in), normal category
-
O 83.0 (lb-in) normal category
Question 24
Question
222 (Refer to Fig.7) What is the maxi¬mum amount of fuel that may be aboard the airplane on takeoff if loaded as follows?
MASS (LB) MOM/1000
Basic Empty Mass 1,350 51.5
Pilot and front passenger 340 -
Rear passengers 310 _
Baggage 45 _
Oil, 8 qt _ _
Answer
-
O 150 litres.
-
O 90 litres.
-
O 120 litres.
-
O 200 litres.
Question 25
Question
223 18 (Refer to Fig.7) Determine the moment/1000 with the following data:
MASS (LB) MOM/1000
Basic Empty Mass 1,350 51.5
Pilot and front passenger 340 -
Fuel (std. tanks) Capacity -
Oil, 8 qt - -
Answer
-
O 74.9 pound-inches.
-
O 69.9 pound-inches.
-
O 77.6 pound-inches.
-
O 81.0 pound-inches.
Question 26
Question
224 (Refer to figure 7). Determine the aircraft loaded moment /1000 and the aircraft category.
MASS (LB) MOM/1000
Basic Empty mass 1,350 51.5.
Pilot and front pass 345 -
Fuel 48 gal. 288 -
Oil, 8 qt - -
Answer
-
O 80.0 utility category.
-
O 78.2, normal category.
-
O 79.2, normal category.
-
O 80.4, utility category.
Question 27
Question
225 Refer to the graph in Fig. 32. Which combination of aircraft gross weight in pounds and C of G position in inches aft of the datum results in safe configuration?
Answer
-
O 2700 lbs and 35.0 inches.
-
O 3040 lbs and 50.4 inches.
-
O 3620 lbs and 45.0 inches.
-
O 2800 lbs and 50.0 inches.
Question 28
Question
226 Refer to the graph in Fig. 32. Which combination of aircraft gross weight in pounds and C of G position in inches aft of the datum results in safe configuration?
Answer
-
O 2540 lbs and 33.5 inches.
-
O 3600 lbs and 42.0 inches.
-
O 3650 lbs and 45.0 inches.
-
O 2750 lbs and 49.8 inches.
Question 29
Question
227 Refer to the graph in Fig. 31. What's the maximum amount of fuel with long range tanks that may be aboard the aeroplane on take off, if loaded as follows:
MASS MOM/1000
BEM 1800 lb 63.3
Pilot 290 lb 12.6
2nd row seat 260 lb 25.2
Fuels _ _
Bagg. Compartment 100 lb 11.6
Aft Bagg. Area _ 1.6
Answer
-
O 450 lt or 75 USG.
-
O 500 lt or 83 USG.
-
O 336 lt or 56 USG.
-
O 336 lt or 50 USG.
Question 30
Question
228 Refer to the graph in Fig. 31. Fill her up with std tanks and determine, if the total moments are within envelope.
MASS MOM/1000
BEM 1800 lb 63.3
1st row seat 340 lb 12.6
2nd row seat 340 lb 25.2
Fuels Full capacity _
Bagg. Compartment 104 lb 10.5
Answer
-
O 127.7 lb-in and 43.7 inches aft of datum.
-
O 111.6 lb-in and 38.2 inches aft of datum.
-
O 127.7 lb-in and 38.2 inches aft of datum.
-
O 116.6 lb-in and 43.7 inches fore of datum.
Question 31
Question
229 Use the C of G envelope graph in Fig.2 in order to answer the following question.
The combination of weight "mass" and moment arm shown, which is acceptable for flight in the Utility Category is:
Answer
-
O 2000lb 80.0
-
O 2100lb 75.3
-
O 2115lb 100.2
-
O 2117lb 100.2
Question 32
Question
230 Pressure Altitude is?
Answer
-
O The altimeter indication when 1013.25 hPa, is set on the sub-scale.
-
O The altitude above sea level.
-
O The altimeter indication when QFE, is set on the sub-scale.
-
O The altimeter indication when QNH, is set on the sub-scale.
Want to create your own Quizzes for free with GoConqr? Learn more.