Performance And Limitations Flashcards

Question

Oil capacity and minimum requirement - double check with instructor

Answer 1

Sump: 7 quarts Total: 8 quarts one quart is contained in the filter

Answer 2

Takeoff — Headwind increases performance. Tailwind decreases aircraft performance Landing — Same as takeoff Cruise flight — Winds aloft have somewhat an opposite effect on airplane performance. A headwind will decrease performance by. A tailwind will increase performance by increasing the ground speed

Answer 3

a. Because of the obviously dangerous overload that it is possible for a pilot to impose on the aircraft structure. b. Because an increased load factor increases the stalling speed and makes stalls possible at seemingly safe flight speeds.

Answer 4

As load factor increases, stalling speed increases.

Answer 5

VY is 74 kts

Answer 6

Exceeding the critical angle of attack. Each airplane has a particular angle of attack where the airflow separates from the upper surface of the wing and the stall occurs.

Answer 7

10 degrees = below 110 kts 20-30 degrees = below 85 kts

Answer 8

Centrifugal force is the “equal and opposite reaction” of the airplane to the change in direction, and it acts “equal and opposite” to the horizontal component of lift.

Answer 9

ask instructor

Answer 10

Takeoff Normal - 2550 Takeoff Utility - 2100 Landing Normal - 2550 Landing Utility - 2100

Answer 11

Remember: W A M (Weight x Arm = Moment)

Answer 12

Lower stall speed — less wing loading. Higher cruise speed — reduced drag; smaller angle of attack is required to maintain altitude. Less stable — stall and spin recovery more difficult; the center of gravity is closer to the center of pressure, causing longitudinal instability.

Answer 13

WASUR Weight Air density (density altitude) Surface wind Upslope or downslope of runway Runway surface

Answer 14

LHAND L ycoming H orizontally Opposed A ir cooled N ormally aspirated D irect drive 280hp 2700 rpm

Answer 15

The takeoff distance chart should be consulted keeping in mind that the distances shown are based on the short field technique

Answer 16

Dual ignition system - engine ignition is provided by two engine driven magnetos and two spark plugs in each cylinder. Starter - Flywheel - Crankshaft - Magnetos - Spark Plugs - Cylinder

Answer 17

Occurs when an airplane banks its wings for a turn. The increased lift of the raised wing is associated with increased drag, which causes the airplane to yaw toward the side of the raised wing Defined as the tendency of an airplane to yaw in the opposite direction of the turn

Answer 18

Takeoff charts — takeoff distance of the airplane with no flaps or with a specific flap configuration. You can also compute distances for a no flap or flap takeoff over a 50-foot obstacle Fuel, time, and distance-to-climb chart — The fuel amount used during the climb, the time it will take to accomplish the climb, and the ground distance that will be covered during the climb. Cruise and range performance chart — True airspeed, fuel consumption, endurance in hours, and range in miles at specific cruise configurations. Crosswind and headwind component chart — The headwind and crosswind component for any given wind direction and velocity. Landing charts — Normal landing distance as well as landing distance over a 50-foot obstacle. Stall speed performance charts — Give an understanding of the speed at which the airplane will stall in a given configuration.

Answer 19

As the internal engine parts and the propeller are revolving in one direction, an equal force is trying to rotate the airplane in the opposite direction. It is greatest when at low airspeeds with high power settings and a high angle of attack

Answer 20

· Remember, maneuvering speed is defined as the highest speed at which full deflection of the controls about any one axis are guaranteed not to overstress the airframe.

Answer 21

a. Takeoff and landing distance b. Rate of climb c. Ceiling d. Payload e. Range f. Speed g. Fuel economy h. Maneuverability i. Stability

Answer 22

two blade, fixed pitch, one piece forged aluminum alloy propeller which is anodized to retard corrosion. 75" diameter

Answer 23

Remember: P A R E P ower—reduce to idle A ilerons—position to neutral R udder—apply full opposite against rotation E levator—apply positive, forward of neutral, movement to break stall Once the spin rotation stops, neutralize the rudder and begin applying back pressure to return to level flight.

Answer 24

Longer takeoff run Longer landing roll Reduced maximum altitude Reduced cruising speed Reduced maneuverability Reduced rate and angle of climb Higher stalling speed Higher landing speed Higher takeoff speed Excessive weight on the nosewheel Shorter range

Answer 25

In steady-state, straight-and-level, unaccelerated flight, the sum of the opposing forces is equal to zero. extra: There can be no unbalanced forces in steady, straight flight (Newton’s Third Law). This is true whether flying level or when climbing or descending. It does not mean the four forces are equal. It means the opposing forces are equal to, and thereby cancel the effects of each other.

Answer 26

Vne = 163 kias

Answer 27

Center of gravity — The point about which an aircraft would balance if it were possible to suspend it at that point. Expressed in inches from datum.

Answer 28

Density altitude is pressure altitude corrected for nonstandard temperature.

Answer 29

100 LL aviation grade fuel blue 100 aviation grade fuel green

Answer 30

VS is 48 Kias

Answer 31

max 120 lbs combined for baggage 1 and 2

Answer 32

It is the load supported by the wings divided by the total weight of the airplane.

Answer 33

1) Fuel flows by gravity from the two wing tanks 2) then the fue selector valve 3) Then it flows through a strainer 4) flows to the carburetor 5) the mixed fuel and air then flows to the cylinders through intake manifold tubes 6) The manual primer draws its fuel from the fuel strainer and injects it into the cylinder intake ports

Answer 34

During landing, any excess speed during the landing phase may result in a significant float distance. In such cases, if care is not exercised by the pilot, he/she may run out of runway and options at the same time. During takeoff, due to the reduced drag in ground effect, the aircraft may seem capable of takeoff well below the recommended speed and will settle back down to the runway

Answer 35

The product of the weight of an item multiplied by its arm. Moments are expressed in pound-inches (lb-in). Total moment is the weight of the airplane multiplied by the distance between the datum and the CG.

Answer 36

It’s the cross sectional shape of a wing, blade, or sail. Wings, horizontal tail surfaces, vertical tail surfaces, and propellers are examples of airfoils.

Answer 37

SOG Stretching your glide Overshooting Final Go-around

Answer 38

ask instructor, I tried looking at POH Limitations

Answer 39

Increased takeoff distance (greater takeoff TAS required) Reduced rate of climb (decreased thrust and reduced acceleration Increased true airspeed on approach and landing (same IAS) Increased landing roll distance.

Answer 40

The maximum allowable weight of both the airplane and its contents.

Answer 41

Crew and passengers 190 lbs each Gasoline 6 lbs/U.S. gal Oil 7.5 lbs/U.S. gal Water 8.35 lbs/U.S. gal

Answer 42

Carburetor: up-draft, float type, fixed jet carburetor mounted on the bottom of the engine. Fuel is delivered by gravity flow from the fuel system. Fuel is mixed with air and delivered to the cylinders through intake manifold tubes. The manual primer draws its fuel from the fuel strainer and injects it into the cylinder intake ports

Answer 43

28 volt Direct Current system 24 volt lead acid battery 60 amp alternator

Answer 44

Ground effect is a condition of improved performance the airplane experiences when it is operating near the ground.

Answer 45

TTS Turns — The load factor increases after a bank has reached 45° or 50°. Turbulence — Severe vertical gusts cause a sudden increase in angle of attack, resulting in large loads which are resisted by the inertia of the airplane. Speed — The amount of excess load that can be imposed upon the wing depends on how fast the airplane is flying.

Answer 46

Vno- Structural Cruising speed: 129K Vy - best rate of climb- 74K Va- Maneuvering Speed - at 1990 lbs= 90K at 2550 = 105K Vx - best angle of climb - 62 K Vfe - 10 degrees = 110K 20-30 degrees = 85k Vso - Stall Speed landing configuration = 40K Vr - Rotation speed = 55 K Vg -Glide speed = 68k Vs - Stall speed clean configuration = 48 K Vne - 163 K

Answer 47

The angle of attack is the angle between the wing chord line and the direction of the relative wind

Answer 48

three one on each wing and one from the fuel strainer drain under an access door on the aft right side of the top of the engine cowling

Answer 49

Pressure Altitude — the altitude indicated when the altimeter setting window (barometric scale) is adjusted to 29.92 HG (inches of mercury)

Answer 50

See attached

Answer 51

Lift — the upward acting force Weight, the downward acting force Thrust — the forward acting force Drag — the backward acting force

Answer 52

single disk, hydraulically-actuated break on each main landing gear wheel. breaks are operated by applying pressure to the top of the rudder pedal each break is connected by a hydraulic line to a master cylinder attached to each of the pilots rudder pedals

Answer 53

Higher stall speed — stalling angle of attack is reached at a higher speed due to increased wing loading. Slower cruise speed — increased drag; greater angle of attack is required to maintain altitude. More stable — the center of gravity is farther forward from the center of pressure which increases longitudinal stability.

Answer 54

WAVAS Wing area — Angle of attack — Velocity of the air — Air density — Shape of the airfoil —

Answer 55

TGCA Torque reaction of the engine and propeller Gyroscopic effect of the propeller. Corkscrewing effect of the propeller slipstream. Asymmetrical loading of the propeller (P-Factor)

Answer 56

In flight — torque reaction is acting around the longitudinal axis, tending to make the airplane roll. On the ground — As the left side of the airplane is being forced down by torque reaction, more weight is being placed on the left main landing gear. This results in more ground friction, or drag, on the left tire than on the right, causing a further turning moment to the left.

Answer 57

Intake Compression Power Exhaust