Dash 1 Section 6

Question 1

What does a reversible flight control system mean?

Answer 1

Aerodynamic forces are fed back to the pilot from each control surface through a system of push rods, cables and pulleys.

Question 2

What do the bobweight and downspring do?

Answer 2

They increase force in the pitch axis. The bob weight increases pitch force as G forces increase (maneuvering flight) and the downspring increases pitch force about the trim speed in steady state conditions.

Question 3

What is pitch force during maneuvering flight conditions?

Answer 3

9 lbs/G for aft centers of gravity and 12 lbs/G for fwd centers of gravity

Question 4

As airspeed increases, trim appears to become more/less effective?

Answer 4

More effective. This is noticeable in the roll and yaw axes.

Question 5

At forward centers of gravity near _________trim will be required at final approach speed.

Answer 5

Full pitch up

Question 6

At forward centers of gravity how much pull force will be required to maintain approach speed with power at IDLE?

Answer 6

8 lbs

Question 7

At approach speeds or below with flaps in the LDG position and 100% torque, how much rudder trim is needed?

Answer 7

Full nose-right rudder trim

Question 8

Directional trim is a function of what four things?

Answer 8

Torque, indicated airspeed, pressure altitude, and pitch rate

Question 9

During what two situations is the pilot most likely to encounter TAD-induced rudder feedback?

Answer 9

Over-the-top aerobatic maneuvers and large power changes at low airspeeds

Question 10

Lowering the flaps to LDG does what to the aircraft?

Answer 10

Induces buffeting and a slight pitch up.

Question 11

Extending the speed brake does what to the aircraft?

Answer 11

Produces a slight pitch up which is countered by an elevator trim interconnect.

Question 12

What prevents use of the speed brake with flaps extended?

Answer 12

A flap/speed brake interconnect (lockout)

Question 13

What exacerbated light longitudinal forces?

Answer 13

Slipstream effects caused by power

Question 14

This aircraft has a yawning tendency at high roll rates which is greatest for what?

Answer 14

Uncoordinated rolling pullouts greater than 2 G

Question 15

How can you minimize yaw in asymmetric maneuvers?

Answer 15

1) maintain coordinated roll and yaw control inputs
2) If rolling pullouts are greater than +2G uncoordinated, limit roll to one half lateral stick
3) if uncoordinated rolling at -1G, max bank angle change is 180 degrees

Question 16

What factors affect glide performance?

Answer 16

Airspeed, configuration, angle of bank, and coordination of flight (rudder ball centered)

Question 17

What are the best glide speeds configured and unconfigured?

Answer 17

125 KIAS, feathered prop, wings level

105 KIAS, gear and flaps down

Question 18

True/False. With the engine out, the flaps cannot be deployed.

Answer 18

False. The flaps can be deployed, but it must be after the landing gear is extended through the emergency hydraulic accumulator.

Question 19

Is use if the speed brake possible in a power-off (engine out) glide?

Answer 19

No. There’s no normal hydraulic pressure.

Question 20

The stick shaker and natural buffet occur how many knots above stall speed?

Answer 20

5-10 knots for stick shaker

3 knots for natural buffet

Question 21

With power at 100% a pitch attitude of what is possible for a wings level stall

Answer 21

45 deg nose up

Question 22

What characterizes a stall?

Answer 22

An uncommanded nose or wing drop/roll off

Question 23

With power off stalls there tends to be a roll off to the __________ and with power on stalls there tends to be a roll off to the __________.

Answer 23

Right. Left.

Question 24

Full right rudder and full right aileron may not prevent a left roll-off at stall above what torque?

Answer 24

60%

Question 25

What effect do the landing gear, flaps, speed brake and fuel imbalance have on the stall characteristics?

Answer 25

Flaps aggravate the roll-off tendency.

The other three have little or negligible effect.

Question 26

How can you recognize an inverted stall?

Answer 26

Lighter aileron forces, nose wandering tendency, little buffet, airspeed will suddenly decrease to zero.
Power-off: slow nose drop with full forward stick
Power-on (100% torque): pitch attitude 30 deg above horizon with full forward stick

Question 27

What characterizes an accelerated (turning) stall?

Answer 27

More pronounced buffet, abrupt lateral roll off towards or away from the turn

Question 28

Sustained heavy buffet above how many Gs in an accelerated stall can damage the fuselage/empennage?

Answer 28

3.0

Question 29

Altitude lost during a recovery from a wings level stall is usually less than what?

Answer 29

100 feet

Question 30

What is the definition of OCF?

Answer 30

A situation in which the aircraft does not respond immediately and in a normal sense to application of flight controls.

Question 31

What are the three categories of OCF?

Answer 31

Poststall gyrations, incipient spins, steady-state spins.

Question 32

What are post-stall gyrations?

Answer 32

Uncommanded and rapid aircraft motions about any axis, stalled or near stalled AOA, random turn needle deflections, erratic airspeed

Question 33

What is an incipient spin?

Answer 33

A spin like motion before the OCF progresses to steady state. Sustained yaw, oscillations in pitch, roll and yaw, fully deflected turn needle, stalled AOA, and airspeed moving towards a steady state value.

Question 34

How long is the incipient spin phase?

Answer 34

Approximately 2 turns.

Question 35

How much altitude does a steady state spin lose?

Answer 35

4500 feet in 6 turns

Question 36

What is a spiral?

Answer 36

A rolling/yawing motion where the airspeed increases through 160 KIAS

Question 37

What two things must occur for a spin to happen?

Answer 37

Stalled wings and sustained yaw.

Question 38

Spin entry attitudes greater then how many degrees nose high may result in low oil pressure and engine damage?

Answer 38

50 degrees NH

Question 39

Spins below ______ are prohibited due to high stresses on the propeller which occur when propeller RPM is below ________.

Answer 39

10,000’ MSL; 80%

Question 40

What are some characterizations of an erect spin?

Answer 40

Initial 60 deg NL pitch, after 3 turns near steady state, 2-3 s/turn, 400-500’ altitude lost/turn, AOA 18+, 120-135 KIAS airspeed, turn needle fully deflected

Question 41

How do ailerons affect spins?

Answer 41

If in same direction, more oscillations. If in opposite direction, more damped out spin.

Question 42

What is a progressive spin?

Answer 42

Reversing rudder direction and thus reversing spin direction. Aircraft will rotate 1.5-2 more turns then reverse direction. Airspeed will increase through 175 KIAS in reversal

Question 43

What is an aggravated spin?

Answer 43

Maintaining pro-spin rudder with control stick forward which will lead to 70 deg NL pitch down and 280 deg/S roll rate.

Question 44

What is the main cause for inverted spins?

Answer 44

High torque

Question 45

What characterizes inverted spins?

Answer 45

Flatter spins, about 30 deg NL, 40 knots of airspeed, AOA of 0, and -1.5 G

Question 46

If control stick remains at full aft for more than 4 turns in a spin what may occur?

Answer 46

It may be impossible to recover the aircraft from the spin. Approximately 2000’ altitude will be lost.

Question 47

If an inverted or power-on departure/spin is encountered what should the pilot assume?

Answer 47

Engine damage, low oil pressure and CHIP light

Question 48

What four factors determine altitude loss in a dive recovery?

Answer 48

Altitude, airspeed, dive angle, and acceleration (G-loading).