5864317
Description
Quiz by tsampikos pompou, updated more than 1 year ago
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Created by tsampikos pompou
over 8 years ago
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Question 1
Question
231 Calculate the Centre of Gravity and total weight "mass", given the following conditions.
MASS LEVER ARM MOM/1000
BEM 2122 lb 35.76 _
Pilot & Copilot 340 lb 37.0 12.6
Centre row seat _ lb 70.0 23.8
Aft row seat 340 lb _ 34.0
Bagg. Compartment 104 lb 126.9 _
Aft Bagg. Area _ _ _
Fuels (55USG) _ 48.0 17.0
Answer
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O 3600 lb and 49.0 inches aft of datum.
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O 2906 lb and 29.6 inches aft of datum.
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O 3246 lb and 42.1 inches aft of datum.
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O 3600 lb and 24.2 inches aft of datum.
Question 2
Question
232 Four on board. Investigate using tables in Fig. 33, the total moments (/100) and if within limits?
Answer
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O 156.769 cmkp and within limits.
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O 159.868 cmkp and out of limits.
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O 176.681 cmkp and out of limits.
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O 134.583 cmkp and within limits.
Question 3
Question
233 After new equipment installed on aeroplane, as in technical certificate shown in Fig. 34, what's the Basic Empty Mass and total moments(/100)?
Answer
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O 977,9 Kg and 93155 cmkp.
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O 968,0 Kg and 92751 cmkp
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O 975,0 Kg and 93045 cmkp.
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O None of them becomes true, since BEM is not affected by adding or removing any basic equipment from cockpit.
Question 4
Question
239 If air density is increased above ISA conditions, the take-off distance required at full throttle compared with that for standard conditions will be:
Answer
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O less
-
O the same
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O more
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O the same but TORA will be increased because the surface wind will have backed and decreased
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O the same but TORA will be increased because the ground effect helps
Question 5
Question
241 What is the maximum zero fuel mass ?
Answer
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O the maximum permissible mass of an airplane with no useable fuel
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O the dry operating mass excluding traffic load and fuel
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O the dry operating mass excluding fuel, plus traffic load
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O the traffic load, excluding non revenue load but including cargo
Question 6
Question
242 TORA is the:
Answer
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O actual runway available for take-off
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O actual runway available for take-off including stopway and clearway
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O actual runway available required for take-off including the stopway
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O actual runway available minus the stopway
Question 7
Question
248 Which of the following items are included in the Dry Operating Mass?
Answer
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O Crew, crew baggage, food and beverages and passengers service equipment
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O Fuel, Oils and water
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O Passengers, crew, crew and passenger baggage
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O Passenger service equipment, crew and passenger baggage
Question 8
Question
251 The maximum range in a glide path will be achieved by:
Answer
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O a relatively low angle of attack being maintained
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O a negative angle of attack being maintained
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O a relatively high angle of attack being maintained
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O a neutral angle of attack being maintained
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O a more coordinated turn
Question 9
Question
253 If the aircraft C of G is on the forward centre of gravity limit:
Answer
-
O the stalling speed is increased
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O the stalling speed is reduced
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O the stalling speed is unchanged, provided that C of G is between the fore and aft C of limits
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O the stalling angle will be increased
Question 10
Question
254 When gliding for maximum range, the greater the aircraft weight:
Answer
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O the steeper the glide path and higher the airspeed
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O the greater the angle of attack and slower airspeed
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O the shallower the glide path and slower airspeed
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O the slower the airspped and steeper glide path
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O the lower the angle of attack, the better the overall stability
Question 11
Question
255 In comparison to gliding in still air conditions, the rate of descent will be …..(i)….. and the distance llown will be …(ii)…… in a tailwind:
Answer
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O (i) unchanged (ιι) increased
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O (ι) increased (ιι) reduced
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O (i)educed (ιι) unchanged
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O (ι) reduced (ιι) reduced
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O (ι) increased (ιι) increased
Question 12
Question
257 The distance covered when gliding headwind compared with gliding in still air will result in ….. (i)…….. distance traveled over the ground together with ….. (ii)…… descent:
Answer
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O (ι) reduced (ιι) unchanged
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O (ιι) unchanged (ιι) reduced
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O (ι) ncreased (ιι) unchanged
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O (ι) reduced (ιι) reduced
Question 13
Question
262 Flight for the maximum range in a piston engined aircraft is achieved by flying:
Answer
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O at the speed which provides the minimum power / airspeed ratio
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O at just below the minimum drag speed
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O at the lowest density altitude that is safely possible
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O at the same speed for maximum endurance + 10% and the lowest density altitude that is safely possible
Question 14
Question
266 The primary reason for making a take-off into the wind is to: (i) reduce the take-off run available (TORA) (ii) reduce the take-off distance required and (iii) reduce the ground speed at which the aircraft will take off.
Select from he following:
Answer
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O (ii) and (iii) are correct
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O (i) and (ii) are correct
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O (i), (ii) and (iii) are correct
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O (i) and (iii) are correct
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O only (iii) is correct
Question 15
Question
269 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in pounds and moment arm in inches?
Answer
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O 1880 lb 75,000 lb-inches
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O 1980 lb 95,000 lb-inches
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O 2190 lb 77,000 lb-inches
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O 2320 lb 66,000 lb-inches
Question 16
Question
270 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in pounds and moment arm in inches?
Answer
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O 1750 lb 66,000 lb-inches
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O 1650 lb 80,000 lb-inches
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O 2000 lb 95,000 lb-inches
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O 2350 lb 110,000 lb-inches
Question 17
Question
271 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in Kilograms and moment arm in millimeters .Conversion formula: (lb-in) x 11.5 = (Kgr-mm)
Answer
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O 905 Kg 860 Kg-mm
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O 835 Kg 1050 Kg-mm
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O 1020 Kg 950 Kg-mm
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O 790 Kg 1000 Kg-mm
Question 18
Question
272 If an aircraft at maximum Take-off Weight (MTOW) is loaded in a manner that positions its C of G at or beyond its aft limit it will:
Answer
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O have an increased range
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O require extra weight in the forward baggage compartment to bring the C of G forward
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O have an decreased range
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O have an increased pitch altitude during the cruise and requite little or no flare on landing
Question 19
Question
273 An aircraft with a C of G out of its forward limit may experience that:
Answer
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O the elevator may be ineffective, particularly during take-off and landing
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O the elevator may be ineffective during the flare
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O the elevator may be ineffective during rotation
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O all the above are incorrect
Question 20
Question
274 If the angle of attack is increased from 4° to 8°:
Answer
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O the lift / drag ratio will reduce
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O the lift / drag ratio will remain the same
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O the lift / drag ratio will increase
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O the stalling angle will be reduced
Question 21
Question
278 The length of a runway available plus the addition of the clearway is named:
Answer
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O TODA
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O TORA
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O TDA
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O TLOF
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O ASDA
Question 22
Question
280 One effect during the cruise of operating with partial flap extension would be:
Answer
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O a reduction in rate of climb capability
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O decreased coefficient of lift
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O decreased coefficient of drag
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O an increase in rate of climb capability
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O an increase in angle of climb capability
Question 23
Question
281 Lift being produced by the wing of an aircraft maintaining a constant true air speed(TAS) will:
Answer
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O decrease as altitude is increased
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O increase as altitude is increased
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O remain constant with change in altitude
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O decrease as altitude is reduced
Question 24
Question
282 The speed at which the aircraft wheels leave the ground during take off is:
Answer
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O VLOF
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O V2
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O VR
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O V4
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O VG
Question 25
Question
285 The maximum demonstrated cross wind component for the aircraft is 11kt.Given a 16kt wind speed, by how many degrees can a runway heading differ from the wind direction before the surface cross wind component equals 11kt? See.Fig.9
Answer
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O 45°
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O 30°
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O 60°
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O 75°
Question 26
Question
286 The maximum demonstrated cross wind component for your aircraft is 15kts. Given a 19kts wind speed, by how many degrees can a runway heading differ from the wind direction before the surface cross wind component equals 15kts. (Use CRP-1 or consult Fig. 9)
Answer
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O 60°
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O 20°
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O 40°
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O 80°
Question 27
Question
287 Loading manifest sheet and C.G. envelope graph for Class "B" aircraft in passenger configuration, is given in Fig.6.
Front occupants……………………………..340 lb
Middle row occupants ………………….340 lb
Baggage comp. Zone "B"……………….200 lb
Fuel Loaded ...............................................58 USG
Trip Fuel ......................................................40 USG
Determine if take-off, landing mass and associated C.G.s are within limits and choose the correct answer.
Answer
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O TOM 3642 lb, LM 3402 lb and both C.G.s within limits.
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O TOM 3655 lb, LM 3402 lb and both C.G.s within limits
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O TOM 3642 lb, LM 3402 lb and take-off C.G. out of limits but landing C.G. within.
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O TOM and all C.G.s out of envelope.
Question 28
Question
288 Loading manifest sheet and C.G. envelope graph for Class "B" aircraft in cargo configuration, is given in Fig.6.
Front occupants……………………………..200 lb
3rd & 4th seats pax…………………….missing
Baggage comp. Zone "A"……………… 520 lb
Baggage comp. Zone "B"……………… 300 lb
Baggage comp. Zone "C"……………… 100 lb
Fuel loaded.....................................................48 USG
Trip fuel ...........................................................44USG
Determine if take-off, landing mass and associated C.G.s are within limits and choose the correct answer.
Answer
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O TOM 3822 lb and take-off C.G. out of limits. LM 3558 lb and landing C.G. out of limits.
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O TOM 3835 lb and take-off C.G. within limits. LM 3558 lb and landing C.G. out of limits.
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O TOM 3535 lb and take-off C.G. within limits. LM 3558 lb and landing C.G. within limits.
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O Within limits, since cargo does not interfere the graph.
Question 29
Question
291 Determine from the "loading graph" in Fig.35, if aircraft's total moments are within envelope? (Max. MTOW 3600 Lb)
ITEM MASS (lb) TOTAL MOMENTS/1000 (lb-in)
BEM 2122 75.9
Pilot 270 -
Cargo "A" 300 -
Cargo "B" 340 -
Cargo "C" 320 -
Fuels[40USG] 240 -
Answer
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O 3592 lb 160.4 (lb-in)
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O 3592 lb 150.0 (lb-in)
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O 3592 lb 180.0 (lb-in)
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O 3592 lb 140.6 (lb-in)
Question 30
Question
292 Determine from the "loading graph" in Fig.35, if aircraft can be allowed to take-off for max. MTOW of3600 lb?
ITEM MASS (lb) TOTAL MOMENTS/1000 (lb-in)
BEM 2122 75.9
Pilot 270 -
Cargo "A" 350 -
Cargo "B" 380 -
Cargo "C" 320 -
Fuels[40USG] 240
Answer
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O Not allowed.
-
O It is on the discretion of the operator.
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O Γ Allowed.
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