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WorksheetsCPD222 Mid 2/65
Total questions: 40
Worksheet time: 50mins
The region of speed instability is:
(a) the same as the region of reversed command
(b) the region in which manual control is not possible
(c) at speeds below the low buffet speed
(d) the region above the thrust available and drag curve intersection
In which of the following conditions is thrust available equal to drag?
(a) in a descent at constant IAS
(b) in level flight at constant IAS
(c) in level flight accelerating
(d) in a climb at constant IAS
Maximum horizontal speed occurs when:
(a) thrust = minimum drag
(b) thrust does not increase with increasing speed
(c) maximum thrust = total drag
(d) thrust = maximum drag
If a piston-engined aeroplane is to maintain a given angle of attack, configuration and altitude at an increased gross mass it will require:
(a) an increased airspeed and constant power
(b) an increased power and a decreased airspeed
(c) an increased airspeed and increased power
(d) a higher coefficient of drag
If the thrust available exceeds the thrust required in level flight the aeroplane:
(a) will accelerate
(b) will descend if the airspeed remains constant
(c) decelerates if it is in the region of reversed command
(d) will decelerate
The critical engine inoperative:
(a) does not affect the aeroplane performance since it is independent of the power plant
(b) decreases the power required because of the lower drag caused by the windmilling engine
(c) increases the power required and decreases the total drag due to the windmilling engine
(d) increases the power required because of the greater drag caused by the windmilling engineand the compensation for the yaw effect
Which of the following sets are examples of aerodynamic balancing of control surfaces?
(a) balance tab, horn balance and mass balance
(b) control surface leading-edge mass, horn balance and mass balance
(c) spring tab, servo-tab and power-assisted control
(d) servo-tab, a seal between the wing trailing edge and the control surface leading edge
When power-assisted controls are used for pitch control, this:
(a) makes trimming unnecessary
(b) makes aerodynamic balancing of the controls difficult
(c) can only function as an elevator trim tab
(d) ensures that partial aerodynamic forces is still felt on the control column
During entry and roll out of a turn adverse yaw is compensated by:
(a) servo-tabs
(b) differential aileron deflection
(c) horn-balanced controls
(d) antibalanced controls
For an aeroplane that is flying straight and level in trim, the position of the power-assisted elevator relative to the trimmable horizontal stabiliser is:
(a) dependent on the speed, the position of the slats, flaps and CG
(b) the elevator deflection is always zero compared to the stabiliser position
(c) with a forward CG position the elevator is deflected upward and vice versa
(d) the elevator is always deflected downward to ensure that sufficient authority remains for
the flare on landing
If the elevator trim tab is deflected up, the cockpit trim indicator shows:
(a) nose-up
(b) nose-left
(c) nose-down
(d) neutral
The purpose of a trim system on power-assisted flying controls is to:
(a) reduce the stick force to zero
(b) decrease the stress imposed on the trim tab
(c) decrease the stress imposed on the hydraulic actuators
(d) to facilitate manual control of the aeroplane in the event of a complete hydraulic failure
One of the factors that limits the maximum aft position of the CG is:
(a) minimum value of the stick force per ‘g.’
(b) maximum longitudinal stability of the aeroplane
(c) maximum elevator deflection
(d) too small an effect of the controls of an aeroplane
How does the exterior appearance of an aeroplane change when it is trimmed for a speed increase?
(a) The elevator is deflected further upward by a downward deflection of the trim tab.
(b) The elevator is deflected further downward by a movable horizontal stabiliser.
(c) The exterior appearance of the aeroplane will not change.
(d) Elevator deflection is increased further downward by the upward deflection of the trim tab.
Sensitivity for a spiral dive will occur when:
(a) the Dutch-roll tendency is too strongly suppressed by the yaw damper
(b) the static directional stability is positive and the static lateral stability is relatively weak
(c) the static directional stability is negative and the static lateral stability is positive
(d) the static lateral and directional stability are both negative
The CG of a stable aeroplane is located:
(a) at the neutral point
(b) between the aft limit and the neutral point
(c) ahead of the neutral point by a sufficient margin
(d) aft of the neutral point
Static longitudinal stability is created by:
(a) the wing surface area being greater than the horizontal tail surface area
(b) a large trim-speed range
(c) the CG being located ahead of the neutral point
(d) the CG being located ahead of the wing leading edge
The lateral static stability is decreased by:
(a) increased wing span
(b) anhedral
(c) dihedral
(d) a high wing
The most forward allowable position of the CG is limited by:
(a) engine thrust and location
(b) trim system and trim-tab surface area
(c) wing surface area and stabilise surface area
(d) elevator capability and elevator control forces
If the CG is located in a forward position then the elevator deflection for a manoeuvre with a load factor greater than 1 will be:
(a) dependent on the trim position
(b) larger
(c) smaller
(d) unchanged
The manoeuvrability of an aeroplane is best when the:
(a) flaps are extended
(b) CG is on the aft limit of the CG envelope
(c) speed is low
(d) CG is on the forward limit of the CG envelope
When the CG is at the aft limit of the CG envelope its relationship to the neutral point is:
(a) forward of the neutral point
(b) aft of the neutral point
(c) at the neutral point
(d) above the neutral point
Rearward movement of the CG:
(a) increase spiral instability
(b) creates a tendency to ‘Dutch roll
(c) increase the elevator stick-force gradient
(d) increase the value of the minimum control speed
For take-off if the CG is towards the forward limit the effect is:
(a) the stick force required at rotation is increased
(b) Vmcg is decreased
(c) the stick force required at rotation is decreased
(d) the stick force at rotation is unaffected
A swept wing causes:
(a) adverse dihedral effect
(b) increased yaw effect
(c) positive dihedral effect
(d) adverse yaw effect
The aerodynamic centre (AC) is the point at which:
(a) Cl is the same for all angles of attack
(b) all aerodynamic forces are the same for any angle of attack
(c) the lift for any angle of attack is the same
(d) the pitching moment is constant for all normal angles of attack
Which motions interact in a Dutch roll?
(a) pitch and adverse yaw
(b) roll and yaw
(c) pitch and yaw
(d) pitch and roll
An aeroplane that is longitudinally statically unstable is simultaneously dynamically:
(a) stable
(b) neutral
(c) unstable
(d) positively stable
Which of the following conditions make an aircraft prone to spiral divergence?
(a) Positive lateral stability, positive directional stability.
(b) Overactive yaw damper.
(c) Positive longitudinal stability.
(d) Positive directional stability, weak lateral stability.
The effect that a swept wing has on lateral stability with increased altitude is (i) static (ii) dynamic:
(a) (i) increased; (ii) decreased
(b) (i) decreased; (ii) decreased
(c) (i) unchanged; (ii) decreased
(d) (i) increased; (ii) unchanged
The data that may be obtained from a buffet-onset boundary chart is:
(a) Mmo for various masses and altitudes
(b) Mcrit for various masses and altitudes
(c) the low-speed and the high-speed stall Mach numbers for various masses and altitudes
(d) the low-speed and the high-speed buffet Mach numbers for various masses and altitudes
The buffet margin:
(a) is always greatest after a step climb
(b) decreases during a constant Mach number descent
(c) is always positive below Mmo
(d) increases during a constant IAS descent
The turn indicator shows a right turn and the slip indicator is left of the neutral position. The action required to coordinate the turn is:
(a) decrease the right bank
(b) increase the rate of turn
(c) increase the right bank
(d) increase the right rudder
The bank angle to be used in a rate one turn depends on the:
(a) TAS
(b) mass
(c) load factor
(d) wind
Is it permissible for a transport aeroplane to exceed the ‘buffet-onset Mach number?
(a) Yes, during the approach.
(b) Yes, to fly faster at extremely high altitudes.
(c) No.
(d) Yes.
The following device is used to ensure the correct response when a jet aeroplane enters or leaves a turn:
(a) a yaw damper
(b) vortex generators
(c) a dorsal fin
(d) roll-control spoilers
A heavy aeroplane and a light aeroplane enter a turn at the same TAS and with the same bank angle. The radius of turn of the heavy aeroplane is . . .. . ... that of the light aeroplane.
(a) the same as
(b) greater than
(c) less than
(d) double
The effect that mass has on the radius of turn for the same bank angle is that:
(a) it increases proportionately as mass increases
(b) it decreases proportionately as mass increases
(c) mass does not affect the radius of turn
(d) it increases proportionately as mass decreases
In a minimum radius turn if the flap is lowered:
(a) the aeroplane will stall
(b) increase the turn radius provided that there is sufficient thrust to prevent the aeroplane from
stalling and that Vle is not a factor
(c) decrease the turn radius provided that there is sufficient excess thrust to maintain a safe
speed and the Vfe is not a factor
(d) increase the rate of turn but not affect the turn radius
To produce a coordinated turn when the turn and slip needle shows right and the ball is to the left it is necessary to:
(a) increase the bank angle to the right
(b) increase the rudder input to the right
(c) decrease the bank angle to the right
(d) increase the radius of turn
