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10 FLIG. PER. EXAM. PREP.
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Preguntas del test (25)
1267 When an aircraft is in flight, to achieve a greater climb angle:
- AO The amount by which thrust exceeds drag must be increased
- BO The amount by which lift exceeds weight must be increased
- CO The amount by which thrust exceeds lift must be reduced
- DO The ratio between lift and drag will remain the same
- EO The ratio between lift and drag is improved
2268 The definition of gross weight is:
- AO the maximum permitted total weight, "mass" at any time
- BO the maxim zero fuel weight, or "mass".
- CO the maximum ramp weight, or "mass".
- DO the weight, or "mass" of pilots and of passengers
- EO the minimum zero fuel weight, or"mass".
3269 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?
- AO 1880 lb 75,000 lb-inches
- BO 1980 lb 95,000 lb-inches
- CO 2190 lb 77,000 lb-inches
- DO 2320 lb 66,000 lb-inches
4270 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?
- AO 1750 lb 66,000 lb-inches
- BO 1650 lb 80,000 lb-inches
- CO 2000 lb 95,000 lb-inches
- DO 2350 lb 110,000 lb-inches
5271 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)
- AO 905 Kg 860 Kg-mm
- BO 835 Kg 1050 Kg-mm
- CO 1020 Kg 950 Kg-mm
- DO 790 Kg 1000 Kg-mm
6272 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:
- AO have an increased range
- BO require extra weight in the forward baggage compartment to bring the C of G forward
- CO have an decreased range
- DO have an increased pitch altitude during the cruise and requite little or no flare on landing
7273 An aircraft with a C of G out of its forward limit may experience that:
- AO the elevator may be ineffective, particularly during take-off and landing
- BO the elevator may be ineffective during the flare
- CO the elevator may be ineffective during rotation
- DO all the above are incorrect
8274 If the angle of attack is increased from 4° to 8°:
- AO the lift / drag ratio will reduce
- BO the lift / drag ratio will remain the same
- CO the lift / drag ratio will increase
- DO the stalling angle will be reduced
9275 Taking off from a strip where the field length is critical and limits the take-off weight:
- AO a large flap angle should be selected
- BO a small angle of flap should be selected
- CO zero flap should be used
- DO none of the above apply
- EO V2 should be maintained high
10276 (Fig.3) Calculate the rate of climb (VY) for an aircraft operating at 9000 ft with ΟΑΤ 0°.
- AO 310 fpm
- BO 580 fpm
- CO 365 fpm
- DO 650 fpm
11277 (Fig.3). Calculate the rate of climb (VY) for an aircraft operating at 7000 ft με ΟΑΤ 20° C.
- AO 360 fpm
- BO 415 fpm
- CO 305 fpm
- DO 420 fpm
12278 The length of a runway available plus the addition of the clearway is named:
- AO TODA
- BO TORA
- CO TDA
- DO TLOF
- EO ASDA
13279 In a banked turn:
- AO the stalling speed increases
- BO the stalling angle reduces
- CO the stalling speed reduces
- DO the stalling angle increases
- EO VG remains the same
14280 One effect during the cruise of operating with partial flap extension would be:
- AO a reduction in rate of climb capability
- BO decreased coefficient of lift
- CO decreased coefficient of drag
- DO an increase in rate of climb capability
- EO an increase in angle of climb capability
15281 Lift being produced by the wing of an aircraft maintaining a constant true air speed(TAS) will:
- AO decrease as altitude is increased
- BO increase as altitude is increased
- CO remain constant with change in altitude
- DO decrease as altitude is reduced
16282 The speed at which the aircraft wheels leave the ground during take off is:
- AO VLOF
- BO V2
- CO VR
- DO V4
- EO VG
17283 The selection of take-off flap prior to an aircraft departure will:
- AO decrease the ground run
- BO increase the rate of climb
- CO increase the maneuvering speed
- DO increase VG
18284 A wing evenly contaminated with only a small amount of ice will produce:
- AO an increase in weight and drag and a significant lift reduction
- BO an increase in weight and decrease in drag
- CO an increase in both drag and lift coefficients due to a weight increase
- DO an increase in weight and reduced rate of descent for any given engine power setting.
19285 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
- AO 45°
- BO 30°
- CO 60°
- DO 75°
20286 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)
- AO 60°
- BO 20°
- CO 40°
- DO 80°
21287 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.
- AO TOM 3642 lb, LM 3402 lb and both C.G.s within limits.
- BO TOM 3655 lb, LM 3402 lb and both C.G.s within limits
- CO TOM 3642 lb, LM 3402 lb and take-off C.G. out of limits but landing C.G. within.
- DO TOM and all C.G.s out of envelope.
22288 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.
- AO TOM 3822 lb and take-off C.G. out of limits.
LM 3558 lb and landing C.G. out of limits. - BO TOM 3835 lb and take-off C.G. within limits.
LM 3558 lb and landing C.G. out of limits. - CO TOM 3535 lb and take-off C.G. within limits.
LM 3558 lb and landing C.G. within limits. - DO Within limits, since cargo does not interfere the graph.
- AO TOM 3822 lb and take-off C.G. out of limits.
23291 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 -
- AO 3592 lb 160.4 (lb-in)
- BO 3592 lb 150.0 (lb-in)
- CO 3592 lb 180.0 (lb-in)
- DO 3592 lb 140.6 (lb-in)
24292 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
- AO Not allowed.
- BO It is on the discretion of the operator.
- CO Γ Allowed.
25293 Ice accretion in a piston engine induction system is produced by:
- AO low power settings, high humidity and warm weather.
- BO high power settings, moderate humidity and cold air.
- CO low power settings, low humidity and very cold air.
- DO high power settings, high relative humidity and lean fuel mixture.
Información
- Descripción
- 10 FLIG. PER. EXAM. PREP.
- Autor
- tsampikos pompou
- Idioma
- English
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