Chap 8 Airplane Performance (Predicting/Calculating Performance) - Aiden Auth

B

( Refer to Figure 8. ) Determine the pressure altitude with an indicated altitude of 1,380 feet MSL with an altimeter setting of 28.22 at standard temperature . A - 3,010 foot . B - 2,991 feet . C - 2,913 feet .

A

8-10 PA.LEK1 , K2a ( Refer to Figure 8. ) Determine the pressure altitude at an airport that has a field elevation of 1,386 feet MSL , and an altimeter setting of 29.97 . A - 1,341 feet . B - 1,451 foot . C - 1,562 feet .

C

8-11 PA.I.F.K1 , K2a Refer to Figure 8. ) What is the effect of a temperature decrease and a pressure altitude increase on the density altitude from 90 ° F and 1,250 feet pressure altitude to 55 ° F and 1,750 feet pressure altitude ? A - 1,750 - foot increase . B - 1,350 - foot decrease . C - 1.750 - foot decrease .

B

8-12 PA.L.F.K2c , PA.IV.A.K3 * Which is true about takeoff performance ? A - The use of flaps during takeoff typically increases takeoff distance . B - The takeoff distance determined on performance charts is based on a specific airplane configuration . C - Airplane weight is not a factor in determining takeoff performance .

A

8-13 PA.IV.M.K4 In a forward slip , the power is normally A - reduced to idle and the airplane is pitched down with down elevator . B - reduced to idle and the airplane is pitched up with up elevator . C - increased and airplane is pitched up with up elevator .

B

8-14 PA.I.K.K1 , K2a ( Refer to Figure 36. ) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220 ° at 30 knots ? A - 19 knots . B - 23 knots . C - 26 knots .

C

8-15 PA.I.F.K1 , K2a ( Refer to Figure 36. ) Determine the maximum wind velocity for a 45 ° crosswind if the maximum crosswind component for the airplane is 25 knots . A - 25 knots . B - 29 knots . C - 35 knots .

C

8-16 PA.I.E.K1 , K2a ( Refer to Figure 36. ) What is the maximum wind velocity for a 30 ° crosswind if the maximum crosswind component for the airplane is 12 knots ? A - 16 knots . B - 20 knots . C - 24 knots .

C

8-17 PA.I.EK1 , K2a ( Refer to Figure 36. ) With a reported wind of north at 20 knots , which runway ( 6 , 29 , or 32 ) is acceptable for use for an airplane with a 13 knot maximum crosswind component ? A - Runway 6 . B - Runway 29 . C - Runway 32 .

B

8-18 PA.I.E.K1 , K2a Refer to Figure 36. ) With a reported wind of south at 20 knots , which runway ( 10 , 14 , or 24 ) is appropriate for an airplane with a 13 - knot maximum crosswind component ? A - Runway 10 . B - Runway 14 . C - Runway 24 .

A

8-19 PA.I.F.K1 , K2a ( Refer to Figure 36. ) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220 ° at 30 knots ? A - 19 knots . B - 23 knots . C - 30 knots .

A

8-20 PA.I.E.K1 , K2a , PA.IV.K1 * ( Refer to Figure 40. ) Determine the approximate ground roll distance required for takeoff . OAT ... 32 ° C Pressure altitude ... 2,000 ft Takeoff weight ... 2,500 lb Headwind component ... 20 knots A - 650 feet . B - 800 feet . C - 1,000 feet .

B

8-21 PA.I.EK1 , K2a , PA.IV.K1 ( Refer to Figure 40. ) Determine the total distance required for takeoff to clear a 50 - foot obstacle . OAT ... Std Pressure altitude ... 4,000 ft Takeoff weight ... 2,800 lb Headwind component ... Calm A - 1,500 feet . B - 1,750 feet . C - 2,000 feet .

B

8-22 PA.I.EK1 , K2a , PA.IV.K1 ( Refer to Figure 40. ) Determine the total distance required for takeoff to clear a 50 - foot obstacle . OAT ... Std . Pressure altitude ... Sea level Takeoff weight ... 2,700 lb Headwind component ... Calm A - 1,000 feet . B - 1,400 feet . C - 1,700 feet .

A

8-23 PA.I.F.K1 , K2a , PA.IV.K1 ( Refer to Figure 40. ) Determine the approximate ground roll distance required for takeoff . OAT ... 38 ° C Pressure altitude ... 2,000 ft Takeoff weight ... 2,750 lb Headwind component ... Calm A - 1,150 feet . B - 1,300 feet . C - 1,800 feet .

B

8-24 PA.I.F.K1 , K2a , PA.IV.B.K2 * Refer to Figure 37. ) Determine the approximate total distance required to land over a 50 - foot obstacle . OAT ... 90 ° F Pressure altitude ... 4,000 ft Weight ... 2,800 lb Headwind component ... 10 knots A - 1,525 feet . B - 1,775 feet . C - 1,950 feet .

B

8-25 PA.L.F.K1 , K2a , PA.IV.B.K2 * ( Refer to Figure 38. ) Determine the approximate landing ground roll distance Pressure altitude ... Sea level Headwind ... 4 knots Temperature ... Std A - 356 feet . B - 401 feet . C - 490 feet .

A

8-26 PA.I.E.K1 , K2a , K2d , PA.IV.B.K2 * Refer to Figure 38. ) Determine the total distance required to land over a 50 - foot obstacle Pressure altitude ... 7,500 ft Headwind ... 8 knots : Temperature ... 32 ° F Runway ... Hard surface A - 1,004 feet . B - 1,205 feet . C - 1,506 feet .

B

8-27 PA.L.FK1 , K2a , 2d , PA.IV.B.K2 ( Refer to Figure 38. ) Determine the total distance required to land over a 50 - foot obstacle . Pressure altitude ... 5,000 ft Headwind ... 8 knots , Temperature ... 41 " P Runway ... Hard surface A - 837 foot . B - 956 feet . C - 1,076 feet .

B

8-28 PA.I.EK1 , K2a , PA.IV.B.K2 ( Refer to Figure 38. ) Determine the approximate landing ground roll distance . Pressure altitude ... 5,000 ft Headwind ... Calm Temperature ... 101 ° F A - 445 feet . B - 545 feet . C - 495 feet .

C

8-29 PA.L.FK1 , K2a , PA.IV.B.K2 ( Refer to Figure 38. ) Determine the total distance required to land over a 50 - foot obstacle . Pressure altitude ... 3,750 ft Headwind ... 12 knots Temperature ... Std A - 794 feet . B - 836 feet . C - 816 feet .

B

8-30 PA.I.F.K1 , K2a , PA.IV.B.K2 ( Refer to Figure 38. ) Determine the approximate landing ground roll distance . Pressure altitude ... 1,250 ft Headwind ... 8 knots Temperature ... Std A - 275 feet . B - 366 feet . C - 470 feet .

B

8-31 PA.IX.B.K1 , K2c , PA.I.F.K2b , PA.IV.B.K2 * If an emergency situation requires a downwind landing , pilots should expect a faster A - airspeed at touchdown , a longer ground roll , and better control throughout the landing roll . B - groundspeed at touchdown , a longer ground roll , and the likelihood of desired touchdown point . overshooting the C - groundspeed at touchdown , a shorter ground roll , and the likelihood of undershooting the desired touchdown point .

C

8-32 PA.IV.A.K2 * Which would provide the greatest altitude in the shortest distance during climb after takeoff ? A - Vy . B - VA C - Vx

A

8-33 PA.IV.A.K2 * After takeoff , which airspeed would the pilot use to gain the most altitude in a given time ? A - Vy B - Vx C - VA

A

8-34 PA.LEK1 , K2a [ Refer to Figure 35. ) Approximately what true airspeed should a pilot expect with 65 percent maximum continuous power at 9,500 feet with a temperature of 36 ° F below standard ? A - 158 knots . B - 161 knots C - 163 knots .

B

8-35 PA.LEK1 , K2a ( Refer to Figure 35. ) What is the expected fuel consumption for a 1.000 - nautical mile flight under the following conditions ? Pressure altitude ... 8,000 ft Temperature ... 22 ° C Manifold pressure ... 20.8 inches Hg Wind ... Calm A - 60.2 gallons . B - 70.1 gallons . C - 73.2 gallons .

B

8-36 PA.L.F.K1 , K2a ( Refer to Figure 35. ) What fuel flow should a pilot expect at 11,000 feet on a standard day with 65 percent maximum continuous power ? A - 10.6 gallons per hour . B - 11.2 gallons per hour . C - 11.8 gallons per hour .

C

8-37 PA.I.F.K1 , K2a ( Refer to Figure 35. ) Determine the approximate manifold pressure setting with 2,450 RPM to achieve 65 percent maximum continuous power at 6,500 feet with a temperature of 36 ° F higher than standard . A - 19.8 inches Hg B - 20.8 inches Hg . C - 21.0 inches Hg .

B

8-38 PA.I.E.K2c , PA.IV.E.K3 When performing a short - field takeoff , you should operate the airplane to obtain maximum takeoff performance by A - using full power , full flaps and accelerating to Vy . B - consulting and following the performance section of the AFM / POH to obtain the power setting , flap setting , airspeed , and procedures prescribed by the manufacturer . C - rotating at Vx and then climbing to clear the 50 - foot obstacle at Vy .

B

8-39 PA.I.F.K2c , PA.IV.B.K3 * Which is a proper technique to perform an approach and landing in a crosswind ? A - After correcting for drift during final approach , neutralize the ailerons and rudder in the landing flare and during rollout . B - Correct for drift by lowering the upwind wing and apply opposite rudder to keep the longitudinal axis aligned with the runway . C - Correct for drift by lowering the downwind wing and apply opposite rudder to keep the longitudinal axis aligned with the runway .

A

8-40 PA.IV.F.K2 * , PA.IV.F.K3 , PA.IV.N.K3 For a crosswind from the right during a short- field landing , A - a sideslip with the right wing low and left rudder as needed will help to maintain the desired ground track for the airplane and keep the longitudinal axis aligned with the runway centerline . B - a sideslip with the left wing low and right rudder as needed will help to maintain the desired ground track for the airplane and keep the longitudinal axis aligned with the runway centerline . C - a forward slip with left wing low and right rudder as needed will help to maintain the desired ground track for the airplane and keep the longitudinal axis aligned with the runway centerline .

A

8-41 PA.V.B.K1 , K2 , K4 ( Refer to Figure 62. ) In flying the rectangular course , when would the aircraft be turned less than 90 ° ? A - Corners 1 and 4 . B - Corners 1 and 2 . C - Corners 2 and 4 .

B

8-42 PA.V.B.K1 , K2 , K3 Refer to Figure 66. ) While practicing S - turns , a consistently smaller half - circle is made on one side of the road than on the other , and this turn is not completed before crossing the road or reference line . This would most likely occur in turn A - 1-2-3 because the bank is decreased too rapidly during the latter part of the turn . B - 4-5-6 because the bank is increased too rapidly during the early part of the turn . C - 4-5-6 because the bank is increased too slowly during the latter part of the turn .

C

8-7 PA.LEK1 K2a ( Refer to Figure 8. ) Determine the density altitude for these conditions : Altimeter setting ... 29.25 Runway temperature ... + 81 ° F Airport elevation ... 5,250 ft MSL A - 4,600 feet MSL B - 5.877 feet MSI C - 8,500 feet MSI

A

8-8 PA.LEK1 , K2a ( Refer to Figure 8. ) Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96 . A - 3,527 feet MSL B - 3,556 feet MSL C - 3,639 feet MSL

A

8-9 PA.I.EK1 , K2a ( Refer to Figure 8. ) What is the effect of a temperature increase from 35 ° F to 50 ° F on the density altitude if the pressure altitude remains at 3,000 feet MSL ? A - 1,000 - foot increase . B - 1,100 - foot decrease . C - 1.300 - foot Increase .

C

Altimeter setting is the value to which barometric pressure scale of the altimeter is set so the altimeter indicates. A - calibrated altitude at field elevation B - absolute altitude at field elevation C - true altitude at field elevation

C

If a flight is made from an area of low pressure into an area of high pressure without the altimeter setting being adjusted, the altimeter will indicate A - the actual altitude above sea level B - higher than the actual altitude above sea level C - lower than the actual altitude above sea level

C

If a pilot changes the altimeter setting from 30.11 to 29.96. What is the approximate change in indication? A - Altimeter will indicate .15" Hg higher B - Altimeter will indicate 150 feet higher C - Altimeter will indicate 150 feet lower

C

If the outside air temperature (OAT) at a given altitude is warmer than standard, the density altitude is A - equal to pressure altitude B - lower than pressure altitude C - higher than pressure altitude

C

Under what condition is pressure altitude and density altitude the same value? A - At sea level, when the temperature is 0 degrees Fahrenheit B - When the altimeter has no installation error C - At standard temperature

B

What effect , if any , does high humidity have on aircraft performance ? A - It increases performance . B - It decreases performance . C - It has no effect on performance .

B

What effect does high density altitude have on aircraft performance ? A - It increases engine performance . B - It reduces climb performance . C - It increases takeoff performance .

B

What effect does high density altitude, as compared to low density altitude, have on propeller efficiency and why? A - Efficiency is increased due to less friction on the propeller blades. B - Efficiency is reduced because the propeller exerts less force at high density altitudes than at low density altitudes. C - Efficiency is reduced due to the increased force of the propeller in the thinner air.

B

What is density altitude? A - The height above the standard datum plane B - The pressure altitude corrected for nonstandard temperature C - The altitude read directly from the altimeter

A

What is true altitude? A - The vertical distance of the aircraft above sea level B - The vertical distance of the aircraft above the surface C - The height above the standard datum plane

C

Which combination of atmospheric conditions reduces aircraft takeoff and climb performance ? A - Low temperature , low relative humidity , and low density altitude . B - High temperature , low relative humidity , and low density altitude . C - High temperature , high relative humidity ,and high density altitude .

C

[ Refer to Figure 8. ) What is the effect of a temperature increase from 25 ° F to 50 ° F on the density altitude if the pressure altitude remains at 5,000 feet ? A - 1,200 - foot increase . B - 1,400 - foot increase . C - 1,650 - foot increase .