(A22)CPL :00001 :0 :1 B1,:( A ) ( B ) ( C ), :00002 :0 :1 B2, ?( A ), ( B ), ( C ), :00003 :0 :1 B3, ?( A ) ( B ) ( C ) :00005 :0 :1 C4( A ) ( B )/ ( C ) :00006 :0 :1 B5, ( A ) ( B ) ( C ), :00007 :0 :2 A6, ?( A ), , ( B ), , ( C ) , :00008 :0 :1 B7 VA , ?( A ) ( B ) ( C ) :00009 :0 :2 A8 ?( A ), ( B )1

, ( C ), :00010 :0 :1 C9 ?( A ) ( B ) ( C ) :00011 :0 :2 A10( A ), ( B ), ( C ) :00012 :0 :1 A11, ?( A ) ( B ) ( C ) :00013 :0 :1 A12 ?( A ) ( B ) ( C ) :00014 :0 :1 B13, ?( A ), ( B ) ( C ), :00015 :0 :2 C14, , ( A ) , ( B ) ( C ) , :00016 :0 :1 A15, ( A ), ( B ), ( C ), :00017 :0 :2 C16, ? ( A ) ( B ) ( C )

2

:00018 :0 :2 C17, ( A ) ( B ) ( C ) :00019 :0 :1 B18, ?( A ) ( B ) ( C ) :00020 :0 :2 B19, ?( A ) , ( B ), , ( C ) ; , , :00021 :0 :1 C20, 2 , ( A )2 ( B )1/2 ( C )4 :00022 :0 :1 B21, /, ( A ) , ( B ), ( C ), :00023 :0 :1 C22, 2 , ( A ) ( B ) 2 ( C ) 4 :00024 :0 :1 B23( A ), ( B ), ( C ), :00025 :0 :1 A24, , ( A ) ( B ) ( C )3

:00026 :0 :1 B25, ( A ) ( B ) ( C ) :00027 :0 :1 B26, ? ( A ) ( B ) ( C ) :00028 :0 :2 C27, ? ( A ) ( B ) ( C ) :00029 :0 :2 A28, ( A ) , ( B ) , ( C ) :00030 :0 :2 C29, ( A ) ( B ) ( C ) :00031 :0 :2 A30, ? ( A ), ( B ) , ( C ), , :00032 :0 :2 B31, , , ( A ) , ( B ), ( C ) , :00033 :0 :1 A32, ? ( A ) ( B ), ( C )4

:00034 :0 :2 A33, ( A ) ( B ) ( C ) :00035 :0 :1 B34, ( A ) ( B ) ( C ) :00037 :0 :1 B35, ? ( A ) ( B ) ( C ) :00038 :0 :2 B36 VNE ?( A ) ( B ), ( C ) , :00041 :0 :1 A37 ?( A ) ( B )() ( C ) :00042 :0 :2 A38, ? ( A ) ( B ) ( C ) :00044 :0 :2 A39, ?( A ) ( B ) ( C ) 500 ft :00045 :0 :2 B40, ?( A ) ( B ) ( C ) , 5

:00046 :0 :1 A41 1 , , ?( A ) ( B ) VA ( C ) :00047 :0 :1 A42, ?( A ) ( B ) ( C ) 2,000 :00048 :0 :2 A43, ? ( A )/ ( B ) ( C ) VLE :00049 :0 :2 B44, ( A ) ( B ) (VA) ( C ) (VNO) :00050 :0 :2 C45, ? ( A ), ( B ), , ( C ) (VA), , :00051 :0 :1 B46, , ( A ) ( B ) ( C ), :00052 :0 :2 B47, ( A )VS ( B )VS1 ( C )VS0 :00059 :0 :1 B48, , ( A ) , ( B ), ( C )6

:00060 :0 :1 B49, / ?( A ) , ( B ) ( C ) :10001 :0 :2 A50? ( A ) ( B ) ( C ) :10002 :0 :1 A51?( A ) ( B ) ( C ) :10003 :0 :2 A52, ( A ) ( B ) ( C ) :10004 :0 :1 B53, ( A ) ( B ) ( C ) :10005 :0 :2 A54, ( A ) ( B ) ( C ) :10006 :0 :1 B55 2000 , 60( A )3000 ( B )4000 ( C )12000 :10007 :0 :2 B56, , , ( A ) , ( B ), ( C ) , 7

:10008 :0 :2 A57( A ) ( B ) ( C ) :10009 :0 :2 A58, ( A ) , ( B ) ( C ) :10010 :0 :1 C59, 2 , ( A )2 ( B )1/2 ( C )4 :10011 :0 :1 B60, /, ( A ) , ( B ), ( C ), :10012 :0 :2 C61 60 90 135 ( A ), ( B ), ( C ) :10015 :0 :1 B62, ?( A ), ( B ) ( C ), :10018 :0 :1 B63, ?( A ), ( B ), ( C ), :10019 :0 :1 B64,:( A ) ( B ) ( C )8

, :10020 :0 :2 A65, ? ( A ), ( B ) , ( C ), , :10021 :0 :1 A66, ? ( A ) ( B ), ( C ) :10022 :0 :2 B67( A ) ( B ) ( C ) :10023 :0 :1 A68 ?( A ), ( B ), ( C ), :10024 :0 :1 B69, ?( A ) ( B ) ( C ) :10025 :0 :1 A70, ( A ), ( B ), ( C ), :10026 :0 :1 C71( A ) ( B )/ ( C ) :10027 :0 :2 C72( A ) ( B ) ( C )9

:10028 :0 :1 B73( A ) ( B ) ( C ) :10029 :0 :1 A74( A ) ( B ) ( C ) :10030 :0 :1 B75, , ( A ) , ( B ), ( C ) :10031 :0 :1 A76 ?( A ) ( B ) ( C ) :10032 :0 :1 B77, ? ( A ) ( B ) ( C ) :10033 :0 :1 B78( A ), ( B ), ( C ), :10034 :0 :2 C79, ? ( A ) ( B ) ( C ) :10035 :0 :1 C80 ?( A ) ( B ) ( C ) :10036 :0 :110

A81, VF :( A ) ( B ) ( C ) :10037 :0 :1 A82, VNO :( A ) ( B ) ( C ) :10038 :0 :1 A83, VLE :( A ) ( B ) ( C ) :10039 :0 :1 B84, VNE :( A ) ( B ) ( C ) :10040 :0 :1 C85, Vy :( A ) ( B ) ( C ) :10041 :0 :1 B86( A ) ( B ) ( C ) :10042 :0 :1 B87( A ) ( B ) ( C ) :10043 :0 :1 B88 ( A ) ( B ) ( C ) :10044 :0 :1 A89( A ) ( B ) ( C ) :10045 :0 :1 C90 ( A ) ( B )11

( C ) :10046 :0 :1 B91( A ) ( B ) ( C ) :10047 :0 :2 A92( A ) ( B ) ( C ) :10050 :0 :1 C93( A ) ( B ) ( C ) :10051 :0 :2 A94( A ) ( B ) ( C ) :10052 :0 :1 A95( A ) ( B ) ( C ) :10053 :0 :1 A96 ( A ) ( B ) ( C ) :10054 :0 :1 B97( A ) ( B ) ( C ) :10055 :0 :2 C98 ( A ) ( B ) ( C )

12

:10056 :0 :1 A99( A ) ( B ) ( C ) :10057 :0 :2 C100( A ) ( B ) ( C ) :10058 :0 :2 C101( A ) ( B ) ( C ) :10060 :0 :2 B102( A ) ( B ) ( C ) :10061 :0 :1 C103, ?( A ) ( B ) ( C ) :10062 :0 :1 B104 ( A ) ( B ) ( C ) :10063 :0 :1 C105( A ) ( B )1/4 ( C )1/4 :10064 :0 :1 B106( A ) ( B ) ( C )

13

:10065 :0 :1 A107( A ) ( B ) ( C ) :10066 :0 :1 B108( A ) ( B ) ( C ) :10068 :0 :2 C109( A ) ( B ) ( C ) :10069 :0 :2 A110( A ) ( B ) ( C ) :10070 :0 :2 C111 ( A ) ( B ) ( C ) :10071 :0 :2 A112( A ) ( B ) ( C ) :10072 :0 :2 B113 ( A ), ( B ) ( C ), :10073 :0 :1 A114( A ) ( B ) ( C ) :10074 :0 :2 A115(14

A ) ( B ) ( C ) :10076 :0 :2 C116( A ) ( B ) ( C ) :10077 :0 :1 B117( A ) ( B ) ( C ) :10078 :0 :2 B118( A ) ( B ) ( C ) :10079 :0 :2 A119( A ) ( B ) ( C ) :10080 :0 :1 A120P ( A ) ( B ) ( C ) 90 :10081 :0 :1 A121 P ( A ) ( B ) ( C ) :10082 :0 :2 A122( A ) ( B ) ( C ) :10083 :0 :2 A123( A ) ( B ) ( C ) :10084 :0 :215

A124( A ) ( B ) ( C ) :10085 :0 :2 B125 ( A ) ( B ) ( C ) :10086 :0 :1 B126 ( A ) ( B ) ( C ) :10087 :0 :1 A127 ( A ) ( B ) ( C ) :10088 :0 :1 B128(rectangular wing) (wing tips stall)(wing roots stall)( A ) ( B ) ( C ) :10089 :0 :1 B129 (CG) ( A ) ( B ) ( C ) :10090 :0 :1 B130( A ) ( B ) ( C ) :10091 :0 :1 B131(Frost)(Upper Surface of Wing)( A ) ( B ) (Airflow Separation ) (stall during Takeoff) ( C ) :10092 :0 :1 A132( A )16

(Density altitude)(Angel of attack)( B ) ( C ) (bank angel) :10093 :0 :1 B133( A ) ( B ) ( C ) :10094 :0 :1 B134( load factor )( A ) ( B ) ( C ) :10095 :0 :1 A135 1500 (Angle of Bank) 60 ( A )3,000 ( B )4,000 ( C ) 12,000 :10096 :0 :1 C136(Angle of Bank) 45 110 knots 150 knots( load factor)( A ) ( B ) ( C )(radius) :10097 :0 :1 B137 70 100 Positive Load Factor 3.0G( A )315 ( B )210 ( C )350 :10099 :0 :1 B138 VA ( A )(High density altitude)(stall speed) ( B )(Turbulence) ( C )(Turbulence) :10100 :0 :117

C139constant-speed propeller ( A ) ( prop governor )(pitch angle of the propeller blades ) ( B ) ( C ) :10101 :0 :1 A140(Stalling Speed) (minimum steady flight speed)( A )VS ( B )VS1 ( C )VSo. :10102 :0 :1 A141(Ground Effect)( A ) (induced drag) ( B )(Angel of attack) ( C )(ground friction)

:10103 :0 :1 C142( A ) ( B ) ( C ) :10104 :0 :1 B143 ( A ) ( B ) ( C ) :10105 :0 :1 A144, ? ( A )( B )( C ) 2000 :10106 :0 :1 C145 ( A ) ( B ) ( C ) :10107 :0 :1 A146( A )( B ) ( C )(laminar flow) 18

:10108 :0 :1 B147( A ) ( B ) ( maximum distance glide ) ( C ) :10109 :0 :1 B148(Wingtip vortex) ( A )(takeoff roll) ( B ) ( C )"""" :10110 :0 :1 B149VNO ( A )(normal operating speed) ( B )(maximum structural cruising speed) ( C ) (maximum operating speed) :10111 :0 :1 C150""( A )(Center of Gravity) ( B )(Elevator Trim) ( C ) :10112 :0 :1 B151( A ) ( B )( C ) :10113 :0 :1 A152 1 miles (Wingtip vortex)( A ) ( B ) VA ( C ) :10114 :0 :1 A153 ( A )(cabin area) ( B )(cabin area)19

( C ) :10115 :0 :1 B154 (manifold pressure )( A ) (propeller blade angle)(RPM) ( B ) (propeller blade angle)(RPM) ( C ) (propeller blade angle)(RPM) :10116 :0 :1 C155(fixed-pitch propeller) (efficiency)?( A )(RPM) ( B ) ( C )(RPM) :10117 :0 :1 A156(Propeller efficiency) ( A )(thrust horsepower) ( brake horsepower ) ( B ) ( C ) :10118 :0 :1 A157 ( electric turn coordinator )( A ) ( electric turn coordinator ) ( B )( C ) :10119 :0 :1 C158 "land and hold short" (LAHSO) ( A ) ( B ) ( C ) :10121 :0 :1 C159( A ) VNE ( B ) ( C )VA :10123 :0 :1 A160 ?( A ) ( B )20

( C ), :10124 :0 :1 C161, ?( A ) , ( B ) ( C ) :10125 :0 :1 B162, ?( A ) ( B ) ( C ) :10126 :0 :1 B163 ?( A ) ( B ) ( C ) :10127 :0 :1 A164, , ?( A ) ( B ) ( C ) :10128 :0 :1 A165 ?( A ) ( B ) ( C ) :10129 :0 :1 C166, ( A ), ( B ), ( C ), :10130 :0 :1 C167, ?( A ) () ( B ) ( C ) :10131 :0 :1 A168( A ), ( B ), ( C ),

21

:10132 :0 :1 C169( A ) ( B ) ( C ) :10133 :0 :1 A170, , ( A ) ( B ), ( C ) , :10134 :0 :1 C171, , ( A ) ( B ) ( C ) :10135 :0 :1 B172,, ( A ), ( B ), ( C ), :10136 :0 :1 C173, . ( A ) ( B ) ( C ) :10137 :0 :1 B174 ( A ), ( B ), ( C ), :10138 :0 :1 C175, ( A ) ( B ) ( C ) :10139 :0 :1 A176( A ) ( B ) ( C ) :10140 :0 :122

C177 ( A ) ( B ) ( C ) :10141 :0 :1 B178( A ) , , ( B ) , ( C ) ,

:10142 :0 :1 B179, , ( A ) ( B ) ( C ) :10143 :0 :1 C180, ( A ) ( B ) ( C ) :10145 :0 :1 B181, , ( A ) ( B ) ( C ) :10149 :0 :1 B182( A ) , ( B ), ( C ) :10150 :0 :1 B183, ( A ) ( B ) ( C ) :10151 :0 :1 A184( A ), ( B ), ( C )

23

:10152 :0 :1 B185( A ) ( B ) ( C ) :10153 :0 :2 B186, ,( A ) ( B ) ( C ) :10154 :0 :1 A187, , ( A ) ( B ) ( C ) :10155 :0 :1 B188( A ) ( B ) ( C ) :10156 :0 :1 A189, , ( A ), ( B ), ( C ), :10157 :0 :1 A190? ( A ) ( B ) ( C ) :10158 :0 :1 B191, ( A ) ( B ) ( C ) :10159 :0 :1 C192, , ( A ) ( B ) ( C )24

:10160 :0 :2 A193, ( A ) ( B ) ( C ) :10161 :0 :1 B194, ( A ) ( B ) ( C ) :10162 :0 :1 C195 60 , 90 135 , ( A ), ( B ), ( C ), :10164 :0 :1 A196,?( A ) 60 , , 10 ( B ), 60 , , 25 ( C ) 45 , 10 :10166 :0 :1 C197, ( A ) ( B ) ( C ) :10167 :0 :1 A198, ( A ) ( B ) ( C ) :10168 :0 :1 B199, , ( A ) ( B ) ( C )

25

:10169 :0 :1 A200( A ), ( B ), ( C ), :10170 :0 :1 A201( A ) ( B ) ( C ) :10171 :0 :1 A202, ( A ) ( B ) ( C ) :10172 :0 :1 B203 2,000 , 60 , ( A )3,000 ( B )4,000 ( C )12,000 :10173 :0 :1 B204, ( A ) ( B ) ( C ) :10174 :0 :1 A205, , ( A ), ( B ) ( C ) :10176 :0 :1 A206( A ), ( B ) , ( C ), :10177 :0 :1 C207?( A ) ( B ) ( C ) :10178 :0 :1 A208 ( A ) ( B ) ( C )26

:10179 :0 :1 B209 VA ( A ) , ( B ), ( C ), :10180 :0 :1 A210, ( A ), , ( B ), , ( C ), :10181 :0 :1 B211( A ) ( B ) ( C ) , :10183 :0 :1 A212( A ) ( B ) ( C ) :10184 :0 :1 B213, ( A ), ( B ), ( C ) , :10185 :0 :1 B214, , ,( A ), ( B ), ( C ), :10186 :0 :1 B215( A ), ( B ), ( C ) :10187 :0 :1 A216, , 27

( A ) ( B ) ( C ) :10188 :0 :1 A217, , ( A ), ( B ), ( C ), :10189 :0 :1 B218, ( A ) ( B ) ( C ) ,, :10190 :0 :1 A219, ( A ), ( B ) ( C ) :10191 :0 :1 A220, ( A ) , ( B ) VA , ( C ), :10192 :0 :1 A221, , ( A ) ( B ) ( C ) 500 :10193 :0 :1 A222, ( A ), ( B ), ( C ) , 2,000 :10194 :0 :128

B223( A ), ( B ), ( C ), :10195 :0 :1 A224( A ) ( B ) ( C ) :10196 :0 :1 C225, ( A ) ( B ), ( C ) :10197 :0 :1 B226 45 90 , ( A ) 2 ( B ) 4 ( C ) 6 :10198 :0 :1 C227 90 45 , ( A ) 4 ( B ) 2 ( C ) 4 :10207 :0 :1 C228, , , ( A ) ( B ) ( C ) :10013 :3 :2 C229( Fig1)( A ) ( B ) ( C ) :10013 :4 :2 C230( Fig1) A , , ( A ) ( B ) ( C ) :10013 :5 :2 B231( Fig1) B , ( A ) ( B ) ( C )29

:10013 :6 :2 C232( Fig1)( A ) ( B ) ( C ) :10016 :1 :2 C233( Fig2) ( A ) ( B ) 60 ( C ) :10016 :2 :2 A234( Fig2) ( A ) 60 10 / ( B ) 60 35 / ( C ) 45 10 / :10048 :1 :2 B235( Fig3) 4500 45 ( A )4563 ( B )6363 ( C )9063 :10048 :2 :2 B236( Fig3) 2300 60 ( A )4600 ( B )4600 ( C )3450 :10048 :3 :2 B237( Fig3) 3300 30 ( A )3810 ( B )3810 ( C )6600 :10163 :1 :2 C238( 2) ,?( A ) , ( B ) 60 , ( C ),

30

:10165 :1 :2 C239( 4) , 60 , 2G , ?( A )66 ( B )74 ( C )84 :10175 :1 :2 C240( 4) 60 80 , ( A )3 Gs ( B )3.5 Gs ( C )3.7 Gs :10199 :1 :2 B241( 5) C E ( A ) ( B ) ( C )

====================English Version====================

Question:00001 Group:0 Difficult:1 B1One of the main functions of flaps during the approach and landing is to ( A )decraese the angle of descent without increasing the airspeed ( B ) provide the same amount of lift at a slower airsped ( C )decrease lift, thus enabling a steeper-than-normal approach to be made Question:00002 Group:0 Difficult:1 B2Which is true regarding the use of flaps during level turns ?( A ) The lowering of flaps incraeses the stall speed ( B )The rasing of flaps increases the stall speed ( C )Rasing flaps will require added forward pressure on the yoke or stick Question:00003 Group:0 Difficult:1 B3A rectangular wing, as compared to other wing planforms, has a tendency to stall at the( A )wingtip, with the stall progression toward the wing root ( B )wing root, with the stall progression toward the wingtip ( C )center trailing edge, with the stall progression outward toward the wing root and tip Question:00005 Group:0 Difficult:1 C4The angle of attack of a wing directly controls the( A )angle of incidence of the wing ( B )amount of airflow above and below the wing ( C )31

distribution of pressure acting on the wing Question:00006 Group:0 Difficult:1 B5Frost covering the upper surface of an airplane wing usually will cause ( A )the airplane to stall at an H13that is higher than normal ( B )the airplane to stall at an angle of attack that is lower than normal ( C )drag factors so large that sufficient speed can not be obtained for takeoff Question:00007 Group:0 Difficult:2 A6The angle of attak at which a wing stalls remains constant regardless of ( A )weight, dynamic pressure, bank angle, or pitch attitude ( B )dynamic pressure, but varies with weight, bank angle, and pitch attitude ( C )weight and pitch attitude, but varies with dynamic pressure and bank angle Question:00008 Group:0 Difficult:1 B7The need to slow an aircraft below VA is brought about by the following weather phenomenon( A )high density altitude which increases the indicated stall speed ( B )turbulence which causes an increase in stall speed ( C )turbulence which causes an decrease in stall speed Question:00009 Group:0 Difficult:2 A8Stall speed is affected by( A )weight, load factor, and power ( B ) load factor, angle of attack, and power ( C )angle of attack, weight, and air density Question:00010 Group:0 Difficult:1 C9The staling speed of an airplane is most affected by( A )changes in air density ( B )variations in flight attitude ( C )variations in airplane loading Question:00011 Group:0 Difficult:2 A10An airplane will stall at the same( A )angle of attack regardless of the attitude with relation to the horizon ( B )airspeed regardless of the attitude with relation to the horizon ( C )angle of attack and attitude with relation to the horizon

Question:00012 Group:0 Difficult:1 A11In a rapid recovery from a dive, the effects of load factor would cause the32

stall speed to( A )increase ( B )decrease ( C )not vary Question:00013 Group:0 Difficult:1 A12Recovery from a stall in any airplane becomes more difficult when its ( A )C.G. moves aft ( B )C.G. moves forward ( C )elevator trim is adjusted noseddown Question:00014 Group:0 Difficult:1 B13Which statement is true relative to changing angle of attack( A )a decraese in angle of attack will increase pressure below the wing, and decrease drag ( B )an increase in angle of attack will increase drag ( C )an increase in angle of attack will decrease pressure below the wing, and increase drag Question:00015 Group:0 Difficult:2 C14To generate the same amount of lift as altitude is increased, an airplane must be flown at( A )the same true airspeed regardless of angle of attack ( B )a lower true airspeed and a greater angle of attack ( C )a higher true airspeed for any given angle of attack Question:00016 Group:0 Difficult:1 A15As the angle of bank is increased, the vertical component of lift ( A )decreases and the horizontal component of lift increases ( B )increases and the horizontal component of lift decreases ( C )decreases and the horizontal component of lift remains constant Question:00017 Group:0 Difficult:2 C16Which is true regarding the forces acting on an aircraft in a steady-state descent ? The sum of all( A )upward forces is less than the sum of all downward forces ( B )rearword forces is greater than the sum of all forward forces ( C )forward forces is equal to the sum of all rearward forces Question:00018 Group:0 Difficult:2 C17During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift( A )is momentarily decreased ( B ) remains the same ( C )is momentarily increased Question:00019 Group:0 Difficult:133

B18What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased ?( A )increase the angle of attack to produce more lift than drag ( B )increase the angle of attack to compensate for the decreasing lift ( C )decrease the angle of attack to compenstae for the increasing drag Question:00020 Group:0 Difficult:2 B19Which is true regarding the force of lift in steady, unaccelerated flight ? ( A )at lower airspeeds the angle of attack must be less to generate sufficient lift to maintain altitude ( B )there is a corresponding indicated airspeed required to every angle of attack to generate sufficient lift to maintain altitude ( C )an airfoil will always stall at the same indicated airspeed; therefore, an increase in weight will require an increase in speed to generate sufficient lift to maintain altitude Question:00021 Group:0 Difficult:1 C20In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become( A )twice as great ( B )half as great ( C ) four times greater Question:00022 Group:0 Difficult:1 B21As airspeed decreases in level flight below that speed for max lift/drag ratio, total drag of an airplane( A )decreases because of lower parasite drag ( B )increases because of increased induced drag ( C )increases because of increased parasite drag Question:00023 Group:0 Difficult:1 C22In theory, if the angle of attack and other factors remain constant and the airspeed is doubled, the lift produced at the higher speed will be ( A )the same as at the lower speed ( B )two times greater than at the lower speed ( C )four times greater than at the lower speed Question:00024 Group:0 Difficult:1 B23An airplane leaving ground effect will( A )experience a reduction in ground friction and require a slight power reduction ( B )experience an increase in induced drag and require more thrust ( C )require a lower angle of attack to maintain the same lift coefficient

34

Question:00025 Group:0 Difficult:1 A24To produce the same lift while in ground effect as when out of ground effect, the airplane requires( A )a lower angle of attack ( B )the same angle of attack ( C )a greater angle of attack Question:00026 Group:0 Difficult:1 B25longitudinal stability involves the motion of the airplane controlled by its ( A )rudder ( B )elevator ( C )ailerons Question:00027 Group:0 Difficult:1 B26If an airplane is loaded to the rear of the its C.G. range, it will tend to be unstable about its( A )vertical axis ( B )lateral axis ( C )longitudinal axis Question:00028 Group:0 Difficult:2 C27If airspeed is increased during a level turn, what action would be necessary to maintain altitude ? The angle of attack( A )and angle of bank must be decreased ( B )must be increased or angle of bank decreased ( C ) must be decreased or angle of bank increased Question:00029 Group:0 Difficult:2 A28While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would( A )remain constant regardless of air density and the resultant lift vector ( B )very depending upon speed and air density provided the resultant lift vector varies proportationately ( C )vary depending upon the resultant lift vector Question:00030 Group:0 Difficult:2 C29To increase the rate of turn and at the same time decrease the radius, a pilot should( A )maintain the bank and decrease airspeed ( B )increase the bank and increase airspeed ( C )increase the bank and decrease airspeed Question:00031 Group:0 Difficult:2 A30Which is corect with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude ?( A )for a specific angle of bank and airspeed, the rate and radius of turn will not vary ( B )to maintain a steady rate of turn, the angle of bank must be increased as the airspeed is decreased ( C )the faster the true airspeed, the faster the rate and larger the35

radius of turn regardless of the angle of bank Question:00032 Group:0 Difficult:2 B31While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will( A )decrease the rate of turn resulting in a decreased load factor ( B )decrease the rate of turn resulting in no change in load factor ( C )increase the rate of turn resulting in no change in load factor Question:00033 Group:0 Difficult:1 A32Why is it necessary to increase back elevator pressure to maintain altitude during a turn ? To compensate for the( A )loss of the vertical component of lift ( B )loss of the horizontal component of lift and the increase in centrifugal force ( C )rudder deflection and slight opposite aileron throughout the turn Question:00034 Group:0 Difficult:2 A33For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn( A )is constant and the stall speed increases ( B )varies with the rate of turn ( C )is constant and the stall speed decreases Question:00035 Group:0 Difficult:1 B34Airplane wing loading during a level coordinated turn in smooth air depending upon the( A )rate of turn ( B )angle of bank ( C )true airspeed Question:00037 Group:0 Difficult:1 B35Max structural cruising speed is the max speed at which an airplane can be operated during( A )abrupt maneuvers ( B )normal operations ( C ) flight in smooth air Question:00038 Group:0 Difficult:2 B36Why should flight speeds above VNE be avoided ?( A )excessive induced drag will result in structural failure ( B )design limit load factors may be exceeded, if gusts are encountered ( C )control effectiveness is so impaired that the aircraft becomes uncontrollable

36

Question:00041 Group:0 Difficult:1 A37Calibrated airspeed is best described as indicated aiespeed corrected for ( A )installation and instrument error ( B )the power-off stall speed ( C )the maneuvering speed Question:00042 Group:0 Difficult:2 A38What is an advantage of an electric turn coordinator if the airplane has a vacuum system for other gyroscopic instruments ?( A )it is a backup in case of vacuum system failure ( B )it is more reliable than the vacuum-driven indicators ( C )it will not tumble as will vacuum-driven turn indicators Question:00044 Group:0 Difficult:2 A39To avoid possible wake turbulence from a large jet aircraft that has just landed prior to your takeoff, at which point on the runway should you plan to become airborne ?( A )past the point where the jet touched down ( B )at the point where the jet touched down, or just prior to this point ( C ) approximately 500 ft prior to the point where the jet touched down Question:00045 Group:0 Difficult:2 B40Choose the correct statement regarding wake turbulence( A ) vortex generation begins with the initiation of the takeoff roll ( B )the primary hazard is loss of control because of induced roll ( C )the greatest vortex strength is produced when the generating airplane is heavy, clean, and fast Question:00046 Group:0 Difficult:1 A41Which procedure should you follow to avoid wake turbulence if a large jet crosses your course from left to right approximately 1 mile ahead and at your altitude ?( A )make sure you are slightly above the path of the jet ( B )slow your airspeed to VA and maintain altitude and course ( C )make sure you are slightly below the path of the jet and perpendicular to the course Question:00047 Group:0 Difficult:1 A42When landing behind a large aircraft, which procedure should be followed for vortex avoidance ?( A )stay above its final approach flightpath all the way to touchdown ( B )stay below and to one side of its final approach flightpath ( C )stay well below its final approach flightpath and land at least 2,000 ft behind37

Question:00048 Group:0 Difficult:2 A43If necessary to takeoff from a slushy runway, the freezing of landing gear mechanisms can be minimized by ?( A )recycling the gear ( B ) delaying gear retraction ( C )increasing the airspeed to VLE before retraction Question:00049 Group:0 Difficult:2 B44if severe turbulence is encountered during flight, the pilot should reduce the airspeed to( A )minimum control speed ( B )design-maneuvering speed (VA) ( C )max structural cruising speed (VNO) Question:00050 Group:0 Difficult:2 C45Which is the best technique for minimizing the wing-load factor when flying in severe turbulence ?( A )change power settings, as necessary, to maintain constant airspeed ( B )control airspeed with power, maintain wings level, and accept variations of altitude ( C )set power and trim to obtain an airspeed at or below maneuvering speed, maintain wings level, and accept variations of airspeed and altitude Question:00051 Group:0 Difficult:1 B46A pilot is encountering an area where significant clear air turbulence has been reported. Which action is appropriate upon encountering the first ripple ( A )maintain altitude and airspeed ( B )adjust airspeed to that recommended for rough air ( C )enter a shallow climb or descent at maneuvering speed Question:00052 Group:0 Difficult:2 B47Which is the correct symbol for the stalling speed or the minimum steady flight speed in a specified configuration ?( A )VS ( B )VS1 ( C ) VS0 Question:00059 Group:0 Difficult:1 B48In small aircraft, normal recovery from spins may become difficult if the ( A )C.G. is too far rearward, and rotation is around the longitudinal axis ( B ) C.G. is too far rearward, and rotation is around the C.G. ( C )spin is entered before the stall is fully developed Question:00060 Group:0 Difficult:1 B49What performance is a characteristic of flight at max lift/drag ratio in a38

propeller-driven airplane ? Maximum( A )gain altitude over a given distance ( B )range and max glide distance ( C )coefficient of lift and max coefficient of drag Question:10001 Group:0 Difficult:2 A50The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flight is known as( A )load factor and directly affects stall speed. ( B )aspect load and directly affects stall speed. ( C )load factor and has no relation with stall speed. Question:10002 Group:0 Difficult:1 A51Load factor is the lift generated by the wings of an aircraft at any given time ( A )divided by the total weight of the aircraft. ( B )multiplied by the total weight of the aircraft. ( C )divided by the basic empty weight of the aircraft. Question:10003 Group:0 Difficult:2 A52For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn( A )is constant and the stall speed increases. ( B )varies with the rate of turn. ( C )is constant and the stall speed decreases. Question:10004 Group:0 Difficult:1 B53Airplane wing loading during a level coordinated turn in smooth air depends upon the( A )rate of turn. ( B )angle of bank. ( C )true airspeed. Question:10005 Group:0 Difficult:2 A54In a rapid recovery from a dive, the effects of load factor would cause the stall speed to( A )increase. ( B )decrease. ( C )not vary. Question:10006 Group:0 Difficult:1 B55If an aircraft with a gross weight of 2,000 pounds was subjected to a 60constant-altitude bank, the total load would be( A )3,000 pounds. ( B )4,000 pounds. ( C )12,000 pounds. Question:10007 Group:0 Difficult:2 B56While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will( A )decrease the rate of turn39

resulting in a decreased load factor. ( B )decrease the rate of turn resulting in no change in load factor. ( C )increase the rate of turn resulting in no change in load factor. Question:10008 Group:0 Difficult:2 A57Lift on a wing is most properly defined as the( A )force acting perpendicular to the relative wind. ( B )differential pressure acting perpendicular to the chord of the wing. ( C )reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber. Question:10009 Group:0 Difficult:2 A58While holding the angle of bank constant, if the rate of turn is varied the load factor would( A )remain constant regardless of air density and the resultant lift vector. ( B )vary depending upon speed and air density. ( C ) vary depending upon the resultant lift vector. Question:10010 Group:0 Difficult:1 C59In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become( A )twice as great ( B )half as great ( C ) four times greater Question:10011 Group:0 Difficult:1 B60As airspeed decreases in level flight below that speed for max lift/drag ratio, total drag of an airplane( A )decreases because of lower parasite drag ( B )increases because of increased induced drag ( C )increases because of increased parasite drag Question:10012 Group:0 Difficult:2 C61If the airspeed is increased from 90 knots to 135 knots during a level 60banked turn, the load factor will( A )increase as well as the stall speed. ( B )decrease and the stall speed will increase. ( C )remain the same but the radius of turn will increase. Question:10015 Group:0 Difficult:1 B62Which statement is true relative to changing angle of attack?( A ) A decrease in angle of attack will increase pressure below the wing, and decrease drag. ( B )An increase in angle of attack will increase drag. ( C )An40

increase in angle of attack will decrease pressure below the wing, and increase drag. Question:10018 Group:0 Difficult:1 B63Which is true regarding the use of flaps during level turns?( A ) The lowering of flaps increases the stall speed. ( B )The raising of flaps increases the stall speed. ( C )Raising flaps will require added forward pressure on the yoke or stick.

Question:10019 Group:0 Difficult:1 B64One of the main functions of flaps during the approach and landing is to ( A )decrease the angle of descent without increasing the airspeed. ( B ) provide the same amount of lift at a slower airspeed. ( C )decrease lift, thus enabling a steeper-than-normal approach to be made. Question:10020 Group:0 Difficult:2 A65Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?( A )For a specific angle of bank and airspeed, the rate and radius of turn will not vary. ( B )To maintain a steady rate of turn, the angle of bank must be increased as the airspeed is decreased. ( C )The faster the true airspeed, the faster the rate and larger the radius of turn regardless of the angle of bank. Question:10021 Group:0 Difficult:1 A66Why is it necessary to increase back elevator pressure to maintain altitude during a turn? To compensate for the( A )loss of the vertical component of lift. ( B )loss of the horizontal component of lift and the increase in centrifugal force. ( C )rudder deflection and slight opposite aileron throughout the turn. Question:10022 Group:0 Difficult:2 B67To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the( A )forces opposing the resultant component of drag. ( B )vertical component of lift. ( C )horizontal component of lift. Question:10023 Group:0 Difficult:141

A68Stall speed is affected by( A )weight, load factor, and power. ( B ) load factor, angle of attack, and power. ( C )angle of attack, weight, and air density. Question:10024 Group:0 Difficult:1 B69A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the( A )wingtip, with the stall progression toward the wing root. ( B )wing root, with the stall progression toward the wing tip. ( C ) center trailing edge, with the stall progression outward toward the wing root and tip. Question:10025 Group:0 Difficult:1 A70By changing the angle of attack of a wing, the pilot can control the airplane( A )lift, airspeed, and drag. ( B )lift, airspeed, and CG. ( C )lift and airspeed, but not drag. Question:10026 Group:0 Difficult:1 C71The angle of attack of a wing directly controls the( A )angle of incidence of the wing. ( B )amount of airflow above and below the wing. ( C )distribution of pressures acting on the wing. Question:10027 Group:0 Difficult:2 C72An aircraft wing is designed to produce lift resulting from a difference in the( A )negative air pressure below and a vacuum above the wing surface. ( B )vacuum below the wing surface and greater air pressure above the wing surface. ( C )higher air pressure below the wing surface and lower air pressure above the wing surface. Question:10028 Group:0 Difficult:1 B73On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the( A )chord line. ( B )flightpath. ( C )longitudinal axis. Question:10029 Group:0 Difficult:1 A74Which statement is true, regarding the opposing forces acting on an airplane in steady-state level flight?( A )These forces are equal. ( B )Thrust is greater than drag and weight and lift are equal. ( C )Thrust is greater than drag and lift is greater than weight.

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Question:10030 Group:0 Difficult:1 B75In small airplanes, normal recovery from spins may become difficult if the ( A )CG is too far rearward and rotation is around the longitudinal axis. ( B ) CG is too far rearward and rotation is around the CG. ( C )spin is entered before the stall is fully developed. Question:10031 Group:0 Difficult:1 A76Recovery from a stall in any airplane becomes more difficult when its ( A )center of gravity moves aft. ( B )center of gravity moves forward. ( C ) elevator trim is adjusted nosedown. Question:10032 Group:0 Difficult:1 B77If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its( A )vertical axis. ( B )lateral axis. ( C )longitudinal axis. Question:10033 Group:0 Difficult:1 B78An airplane leaving ground effect will( A )experience a reduction in ground friction and require a slight power reduction. ( B )experience an increase in induced drag and require more thrust. ( C )require a lower angle of attack to maintain the same lift coefficient. Question:10034 Group:0 Difficult:2 C79If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack( A )and angle of bank must be decreased. ( B )must be increased or angle of bank decreased. ( C ) must be decreased or angle of bank increased. Question:10035 Group:0 Difficult:1 C80The stalling speed of an airplane is most affected by( A )changes in air density. ( B )variations in flight altitude. ( C )variations in airplane loading. Question:10036 Group:0 Difficult:1 A81Defines VF as :( A )design flap speed ( B )flap operating speed ( C )max flap extended speed Question:10037 Group:0 Difficult:1 A82Defines VNO as :( A )max structural cruising speed ( B )normal43

operating speed ( C )max operating speed Question:10038 Group:0 Difficult:1 A83Defines VLE as :( A )max landing gear extended speed ( B )max landing gear operating speed ( C )max leading edge flaps extended speed Question:10039 Group:0 Difficult:1 B84Defines VNE as :( A )max nose wheel extended speed ( B )neverexceed speed ( C )max landing gear extended speed Question:10040 Group:0 Difficult:1 C85Defines Vy as :( A )speed for best rate of descent ( B )speed for best angle of climb ( C )speed for best rate of climb Question:10041 Group:0 Difficult:1 B86Which of the following is considered a primary flight control? ( A )Leading-edge flap ( B )Elevator ( C )Dorsal fin Question:10042 Group:0 Difficult:1 B87The four forces acting on an airplane in flight are ( A )lift, weight, thrust, and gravity. ( B )lift, weight, thrust, and drag ( C )lift, gravity, power, and friction. Question:10043 Group:0 Difficult:1 B88When are the four forces that act on an airplane in equilibrium?

( A )when the aircraft is accelerating ( B )During unaccelerated flight ( C ) When the aircraft is at rest on the ground. Question:10044 Group:0 Difficult:1 A89When are inboard ailerons normally used? ( A )Low-speed and High-speed flight ( B )High-speed flight only. ( C )Lowspeed flight only.44

Question:10045 Group:0 Difficult:1 C90When departing behind a heavy aircraft, the pilot should avoid wake turbulence by maneuvering the aircraft ( A )below and downwind from the heavy aircraft. ( B )below and upwind from the heavy aircraft. ( C )above and upwind from the heavy aircraft Question:10046 Group:0 Difficult:1 B91What force makes an airplane turn? ( A )The vertical component of lift ( B )The horizontal component of lift. ( C ) Centrifugal Question:10047 Group:0 Difficult:2 A92An airplane said to be inherently stable will ( A )require less effort to control ( B )be difficult to stall. ( C )not spin Question:10050 Group:0 Difficult:1 C93The angle of attack at which an airplane wing stalls will ( A )increase if the CG is moved forward ( B )change with an increase in gross weight ( C )remain the same regardless of gross weight Question:10051 Group:0 Difficult:2 A94What determines the longitudinal stability of an airplane? ( A )The location of the CG with respect to the center of lift ( B )The effectiveness of the horizontal stabilizer, rudder, and rudder trim tab. ( C ) The relationship of thrust and lift to weight and drag Question:10052 Group:0 Difficult:1 A95What is one purpose of wing flaps? ( A )To enable the pilot to make steeper approaches to a landing without increasing the airspeed ( B )To relieve the pilot of maintaining continuous pressure on the controls ( C )To decrease wing area to vary the lift45

Question:10053 Group:0 Difficult:1 A96What is the relationship of lift, drag, thrust, and weight when the airplane is in straight-and-level flight? ( A )Lift equals weight and thrust equals drag ( B )lift, drag, and weight equal thrust. ( C )Lift and weight equal thrust and drag. Question:10054 Group:0 Difficult:1 B97What is the purpose of the rudder on an airplane? ( A )To control overbanking tendency ( B )To control yaw ( C )To control roll Question:10055 Group:0 Difficult:2 C98Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at . ( A )twice the length of the wingspan above the surface. ( B )a higher-thannormal angle of attack. ( C )less than the length of the wingspan above the surface Question:10056 Group:0 Difficult:1 A99One of the main functions of flaps during approach and landing is to ( A )increase the angle of descent without increasing the airspeed. ( B ) decrease the angle of descent without increasing the airspeed ( C )permit a touchdown at a higher indicated airspeed. Question:10057 Group:0 Difficult:2 C100The amount of excess load that can be imposed on the wing of an airplane depends upon the ( A )position of the CG. ( B )abruptness at which the load is applied. ( C ) speed of the airplane. Question:10058 Group:0 Difficult:2 C101Wingtip vortices created by large aircraft tend to

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( A )rise into the traffic pattern. ( B )rise into the takeoff or landing path of a crossing runway. ( C )sink below the aircraft generating turbulence Question:10060 Group:0 Difficult:2 B102In what flight condition must an aircraft be placed in order to spin? ( A )Partially stalled with one wing low. ( B )Stalled. ( C )In a steep diving spiral. Question:10061 Group:0 Difficult:1 C103When landing behind a large aircraft, the pilot should avoid wake turbulence by staying ( A )below the large aircraft's final approach path and landing before the large aircraft's touchdown point. ( B )above the large aircraft's final approach path and landing before the large aircraft's touchdown point ( C )above the large aircraft's final approach path and landing beyond the large aircraft's touchdown point Question:10062 Group:0 Difficult:1 B104An airplane has been loaded in such a manner that the CG is located aft of the aft CG limit. One undesirable flight characteristic a pilot might experience with this airplane would be ( A )a longer takeoff run ( B )difficulty in recovering from a stalled condition ( C )stalling at higher-than-normal airspeed. Question:10063 Group:0 Difficult:1 C105The wind condition that requires maximum caution when avoiding wake turbulence on landing is a ( A )strong headwind. ( B )light, quartering headwind ( C )light, quartering tailwind Question:10064 Group:0 Difficult:1 B106Loading an airplane to the most aft CG will cause the airplane to be ( A )less stable at slow speeds, but more stable at high speeds. ( B )less stable47

at all speeds. ( C )less stable at high speeds, but more stable at low speeds. Question:10065 Group:0 Difficult:1 A107Wingtip vortices are created only when an aircraft is ( A )developing lift. ( B )operating at high airspeeds. ( C )heavily loaded Question:10066 Group:0 Difficult:1 B108The greatest vortex strength occurs when the generating aircraft is ( A )heavy, dirty, and fast. ( B )heavy, clean, and slow. ( C )light, dirty, and fast Question:10068 Group:0 Difficult:2 C109The term "angle of attack"?is defined as the angle( A )formed by the longitudinal axis of the airplane and the chord line of the wing. ( B ) between the airplane's climb angle and the horizon. ( C )between the wing chord line and the relative wind. Question:10069 Group:0 Difficult:2 A110Ground effect is most likely to result in which problem?( A ) Becoming airborne before reaching recommended takeoff speed. ( B )Settling to the surface abruptly during landing. ( C )Inability to get airborne even though airspeed is sufficient for normal takeoff needs. Question:10070 Group:0 Difficult:2 C111What causes an airplane (except a T-tail) to pitch nosedown when power is reduced and controls are not adjusted? ( A )The CG shifts forward when thrust and drag are reduced ( B )When thrust is reduced to less than weight, lift is also reduced and the wings can no longer support the weight. ( C )The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced. Question:10071 Group:0 Difficult:2 A112During a spin to the left, which wing(s) is/are stalled? ( A )Both wings are stalled ( B )left wings is stalled ( C )right wings is stalled48

Question:10072 Group:0 Difficult:2 B113When taking off or landing at an airport where heavy aircraft are operating, one should be particularly alert to the hazards of wingtip vortices because this turbulence tends to ( A )rise from a crossing runway into the takeoff or landing path ( B )sink into the flightpath of aircraft operating below the aircraft generating the turbulence. ( C )rise into the traffic pattern area surrounding the airport. Question:10073 Group:0 Difficult:1 A114During an approach to a stall, an increased load factor will cause the airplane to ( A )stall at a higher airspeed ( B )have a teendency to spin. ( C )be more difficult to control. Question:10074 Group:0 Difficult:2 A115Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight? ( A )Turns ( B )Climbs. ( C )Stalls Question:10076 Group:0 Difficult:2 C116As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will ( A )decrease as the true airspeed decreases ( B )decrease as the true airspeed increase ( C )remain the same regardless of altitude. Question:10077 Group:0 Difficult:1 B117What is ground effect? ( A )The result of an alteration in airflow patterns increasing induced drag about the wings of an airplane. ( B )The result of the interference of the surface of the Earth with the airflow patterns about an airplane ( C )The result of the disruption of the airflow patterns about the wings of an airplane to the point where the wings will no longer support the airplane in flight.49

Question:10078 Group:0 Difficult:2 B118How will frost on the wings of an airplane affect takeoff performance? ( A )Frost will change the camber of the wing, increasing its lifting capability. ( B )Frost will disrupt the smooth flow of air over the wing, adversely affecting its lifting capability. ( C )Frost will cause the airplane to become airborne with a higher angle of attack, decreasing the stall speed. Question:10079 Group:0 Difficult:2 A119In what flight condition is torque effectthe greatest in a single-engine airplane?( A )Low airspeed, high power, high angle of attack. ( B ) Low airspeed, low power, low angle of attack. ( C )high airspeed, high power, high angle of attack. Question:10080 Group:0 Difficult:1 A120The left turning tendency of an airplane cause by P-factor is the result of the( A )propeller blade descending on the right, producing more thrust than the ascending blade on the left. ( B )clockwise rotation of the engine and propeller turning the airplane counterclockwise. ( C )gyroscopic forces applied to the rotating propeller blades acting 90' in advance of the point the force was applied. Question:10081 Group:0 Difficult:1 A121When does P-factor cause the airplane to yaw to the left?( A ) When at high angles of attack. ( B )When at low angles of attack. ( C )When at high airspeed. Question:10082 Group:0 Difficult:2 A122The primary purpose of high-lift devices is to increase the ( A )lift at low speeds. ( B )L/D max. ( C )drag and reduce airspeed. Question:10083 Group:0 Difficult:2 A123What is a purpose of flight spoilers? ( A )Reduce lift without increasing airspeed. ( B )Increase the camber of the wing. ( C )Direct airflow over the top of the wing at high angles of attack.

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Question:10084 Group:0 Difficult:2 A124Which is a purpose of ground spoilers? ( A )Reduce the wings lift upon landing. ( B )Aid in rolling an airplane into a turn. ( C )Increase the rate of descent without gaining airspeed. Question:10085 Group:0 Difficult:2 B125How can turbulent air cause an increase in stalling speed of an airfoil? ( A )A decrease in angle of attack. ( B )An abrupt change in relative wind. ( C )Sudden decrease in load factor. Question:10086 Group:0 Difficult:1 B126The main compartment providing the same amount of lift at slower airspeed during the approach and landing is( A )Aileron ( B )Flaps ( C )Elevator Question:10087 Group:0 Difficult:1 A127The raising of flaps increases the stall speed during level turns? ( A )Correct ( B )incorrect ( C )There is no change in the stall speed whether using the flap or no Question:10088 Group:0 Difficult:1 B128The rectangular wing has a tendency to stall first at the wing tips with the stall pattern progressing inward to the wing roots.( A )Correct ( B ) incorrect ( C )There is no difference between wing roots and wing tips during stall pattern. Question:10089 Group:0 Difficult:1 B129The pilot can control the airplanes lift, airspeed, and CG by changing the angle of attack of a wing.( A )Correct ( B )incorrect ( C )There is no change in airplanes lift, airspeed, and CG Question:10090 Group:0 Difficult:1 B130The angel of attack of a wing directly controls the( A )angle of incidence of the wing. ( B )distribution of pressures below and above wing. ( C )amount of airflow above and below the wing.

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Question:10091 Group:0 Difficult:1 B131Frost covering the upper surface of an airplane wing usually will cause ( A )the airplane to stall at an angle of attack that is higher than normal. ( B ) airflow separation at a lower angel of attack, resulting in a tendency to stall during Takeoff ( C )drag factors so large that sufficient speed cannot be obtained for takeoff. Question:10092 Group:0 Difficult:1 A132There are no effect on the indicated stalling speed since( A ) Change in density altitude and angel of attack ( B )As the weight is increased ( C )A-?? As the bank angel increases Question:10093 Group:0 Difficult:1 B133An aircraft wing is designed to produce lift resulting from a difference in the( A )negative air pressure below and a vacuum above the wings surface. ( B )higher air pressure below the wings surface and lower air pressure above the wings surface. ( C )higher air flow above and below the wings surface . Question:10094 Group:0 Difficult:1 B134Airplane wing loading during a level coordinated turn in smooth air depends upon the( A )rate of turn ( B )angle of bank ( C )Ground speed Question:10095 Group:0 Difficult:1 A135If an aircraft with a gross weight of 1,500 pounds was subjected to a 60 constant-altitude bank, the total load would be( A )3,000 pounds ( B )4,000 pounds. ( C )12,000 pounds Question:10096 Group:0 Difficult:1 C136If the airspeed is increased from 110 knots to 150 knots during a level 45 banked turn, the load factor will( A )increase as well as the stall speed. ( B )decrease and the stall speed will increase. ( C )remain the same but the radius turn will increase. Question:10097 Group:0 Difficult:1 B137Baggage weighing 70 pounds is placed in a normal category airplanes baggage compartment which is placarded at 100 pounds. If this airplane is52

subjected to a positive load factor of 3.0Gs, the total load of the baggage would be( A )315 pounds and would be excessive. ( B )210 pounds and would not be excessive. ( C )350 pounds and would not be excessive. Question:10099 Group:0 Difficult:1 B138The need to slow an aircraft below VA is brought about by the following weather phenomenon:( A )High density altitude which increases the indicated stall speed ( B )Turbulence which causes an increase in stall speed ( C )Turbulence which causes a decrease in stall speed Question:10100 Group:0 Difficult:1 C139Which statement best describes the operating principle of a constant-speed propeller?( A )As throttle setting is changed by the pilot, the prop governor causes pitch angle of the propeller blades to remain unchanged ( B ) A high blade angle, or increased pitch, reduces the propeller drag and allows more engine power for takeoffs. ( C )The propeller control regulates the engine RPM, and in turn, the propeller RPM. Question:10101 Group:0 Difficult:1 A140Which is the correct symbol for the stalling speed or the minimum steady flight speed at which the airplane is controllable?( A )VS ( B )VS1 ( C )VSo. Question:10102 Group:0 Difficult:1 A141An airplane leaving ground effect will( A )experience an increase in induced drag and require more thrust ( B )require a lower angle of attack to maintain the same lift coefficient ( C )experience a reduction in ground friction and require a slight power reduction. Question:10103 Group:0 Difficult:1 C142True airspeed is best described as calibrated airspeed corrected for ( A )installation or instrument error ( B )non-standard temperature ( C ) altitude and non-standard temperature Question:10104 Group:0 Difficult:1 B143As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane( A )decreases because of lower parasite drag. ( B )increases because of increased induced drag. ( C )53

increases because of increased parasite drag. Question:10105 Group:0 Difficult:1 A144When landing behind a large aircraft, which procedure should be followed for vortex avoidance?( A )Stay above its final approach flightpath all the way to touchdown. ( B )Stay below and to one side of its final approach flightpath ( C )Stay well below its final approach flightpath and land at least 2,000 feet behind. Question:10106 Group:0 Difficult:1 C145During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift( A )is momentarily decreased ( B ) remains the same. ( C )is momentarily increased. Question:10107 Group:0 Difficult:1 A146Lift on a wing is most properly defined as the( A )force acting perpendicular to the relative wind ( B )differential pressure acting perpendicular to the chord of the wing. ( C )reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber Question:10108 Group:0 Difficult:1 B147What performance is characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? Maximum( A )gain in altitude over a given distance. ( B )range and maximum distance glide. ( C )coefficient of lift and minimum coefficient of drag. Question:10109 Group:0 Difficult:1 B148During a takeoff made behind a departing large jet airplane, the pilot can minimize the hazard of wingtip vortices by( A )extending the takeoff roll and not rotating until well beyond the jet's rotation point. ( B ) being airborne prior to reaching the jet's flightpath until able to turn clear of its wake. ( C )maintaining extra speed on takeoff and climbout. Question:10110 Group:0 Difficult:1 B149Defines VNO as( A )normal operating speed ( B )maximum structural cruising speed ( C )maximum operating speed.

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Question:10111 Group:0 Difficult:1 C150Recovery from a stall in any airplane becomes more difficult when its ( A )center of gravity moves forward. ( B )elevator trim is adjusted nosedown. ( C )center of gravity moves aft. Question:10112 Group:0 Difficult:1 B151When should pilots decline a 'land and hold short' (LAHSO) clearance? ( A )If runway surface is contaminated ( B )When it will compromise safety. ( C )Only when the tower controller concurs. Question:10113 Group:0 Difficult:1 A152Which procedure should you follow to avoid wake turbulence if a large jet crosses your course from left to right approximately 1 mile ahead and at your altitude?( A )Make sure you are slightly above the path of the jet. ( B )Slow your airspeed to VA and maintain altitude and course. ( C )Make sure you are slightly below the path of the jet and perpendicular to the course. Question:10114 Group:0 Difficult:1 A153Which is true regarding preheating an aircraft during cold weather operations?( A )The cabin area as well as the engine should be preheated. ( B )The cabin area should not be preheated with portable heaters. ( C )Hot air should be blown directly at the engine through the air intakes. Question:10115 Group:0 Difficult:1 B154To eastablish a climb after takeoff in an aircraft equipped with a constantspeed propeller,the output of the engine is reduced to climb power by decreasing manifold pressure and( A )increasing RPM by decreasing propeller blade angle ( B )decreasing RPM by increasing propeller blade angle ( C )decreasing RPM by decreasing propeller blade angle Question:10116 Group:0 Difficult:1 C155A fixed-pitch propeller is designed for best efficiency only at a given combination of( A )altitude and RPM ( B )airspeed and altitude ( C )airspeed and RPM Question:10117 Group:0 Difficult:1 A156Propeller efficiency is the( A )ratio of thrust horsepower to brake horsepower ( B )actual distance a propeller advances in one revolution ( C )55

ratio of geometric pitch to effective pitch Question:10118 Group:0 Difficult:1 A157What is an advantage of an electric turn coordinator if the airplane has a vacuum system for other gyroscopic instruments?( A )It's more reliable than the vacuum-driven indicators ( B )It will not tumble as will vacuum-driven turn indicators ( C )It's backup in case of vacuum system failure Question:10119 Group:0 Difficult:1 C158Who has the final authority to accept or decline any 'land and hold short' (LAHSO) clearance?( A )Airplane owner/operator ( B )ATC tower controller ( C )Pilot-in-command Question:10121 Group:0 Difficult:1 C159Which airspeed would a pilot be unable to identify by the color coding of an airspeed indicator?( A )The never-exceed speed ( B )The poweroff stall speed ( C )The maneuvering speed Question:10123 Group:0 Difficult:1 A160What procedure is recommended for an engine-out approach and landing ? ( A )the flightpath and procedures should be almost identical to a normal approach and landing ( B )the altitude and airspeed should be considerably higher than normal throughout the approach ( C )a normal approach, except do not extend the landing gear or flaps until over the runway threshould Question:10124 Group:0 Difficult:1 C161What effect, if any, will landing at a higer-than-recommended touchdown speed have on hydroplaning ?( A )no effect on hydroplaning, but increases landing roll ( B )reduces hydroplaning potential if heavy braking is applied ( C )increases hydroplaning potential regardless of braking Question:10125 Group:0 Difficult:1 B162At which speed will increasing the pitch attitude cause an airplane to climb ?( A )low speed ( B )high speed ( C )any speed Question:10126 Group:0 Difficult:1 B163How can the pilot increase the rate of turn and decrease the radius at the56

same time ?( A )steepen the bank and increase airspeed ( B )steepen the bank and decrease airspeed ( C )shallow the bank and increase airspeed Question:10127 Group:0 Difficult:1 A164What effect does landing at high elevation airports have on ground speed with comparable conditions relative to temperature, wind and airplane weight ?( A )higher than at low elevation ( B )lower than at low elevation ( C )the same as at low elevation Question:10128 Group:0 Difficult:1 A165What effect does an uphill runway slope have upon takeoff performance ? ( A )increases takeoff distance ( B )decreases takeoff speed ( C )decreases takeoff distance Question:10129 Group:0 Difficult:1 C166As outside air pressure decreases, thrust output will( A )increase due to greater efficiency of jet aircraft in thin air ( B )remain the same since compression of inlet air will compensate for any decrease in air pressure ( C ) decrease due to higher density altitude Question:10130 Group:0 Difficult:1 C167What is the best method of speed reduction if hydroplaning is experienced on landing ?( A )apply full main wheel braking only ( B )apply nosewheel and main wheel braking alternately and abruptly ( C )apply aerodynamic braking to the fullest advantage Question:10131 Group:0 Difficult:1 A168By changing the angle of attack of a wing, the pilot can control the airplanes( A )lift, airspeed, and drag. ( B )lift, airspeed, and CG. ( C )lift and airspeed, but not drag. Question:10132 Group:0 Difficult:1 C169The angle of attack of a wing directly controls the( A )angle of incidence of the wing. ( B )amount of airflow above and below the wing. ( C )distribution of pressures acting on the wing. Question:10133 Group:0 Difficult:1 A170Which statement is true, regarding the opposing forces acting on an57

airplane in steady-state level flight?( A )These forces are equal. ( B )Thrust is greater than drag and weight and lift are equal. ( C )Thrust is greater than drag and lift is greater than weight. Question:10134 Group:0 Difficult:1 C171To generate the same amount of lift as altitude is increased, an airplane must be flown at( A )the same true airspeed regardless of angle of attack. ( B )a lower true airspeed and a greater angle of attack. ( C )a higher true airspeed for any given angle of attack. Question:10135 Group:0 Difficult:1 B172What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased?( A )Increase the angle of attack to produce more lift than drag. ( B )Increase the angle of attack to compensate for the decreasing lift. ( C )Decrease the angle of attack to compensate for the increase drag. Question:10136 Group:0 Difficult:1 C173In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become( A )twice as great. ( B )half as great. ( C ) four times greater. Question:10137 Group:0 Difficult:1 B174As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane( A )decreases because of lower parasite drag. ( B )increases because of increased induced drag. ( C ) increases because of increased parasite drag. Question:10138 Group:0 Difficult:1 C175During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift( A )is momentarily decreased. ( B ) remains the same. ( C )is momentarily increased. Question:10139 Group:0 Difficult:1 A176Lift on a wing is most properly defined as the( A )force acting perpendicular to the relative wind. ( B )vary depending upon speed and air density. ( C )reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber.58

Question:10140 Group:0 Difficult:1 C177An aircraft wing is designed to produce lift resulting from a difference in the( A )negative air pressure below and a vacuum above the wings surface. ( B )vacuum below the wings surface and greater air pressure above the wings surface. ( C )higher air pressure below the wings surface and lower air pressure above the wings surface. Question:10141 Group:0 Difficult:1 B178Which is true regarding the force of lift in steady, unaccelerated flight? ( A )At lower airspeeds the angle of attack must be less to generate sufficient lift to maintain altitude. ( B )There is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude. ( C )An airfoil will always stall at the same indicated airspeed; therefore, an increase in weight will require an increase in speed to generate sufficient lift to maintain altitude. Question:10142 Group:0 Difficult:1 B179On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the( A )chord line. ( B )flightpath. ( C )longitudinal axis. Question:10143 Group:0 Difficult:1 C180Which is true regarding the forces acting on an aircraft in a steady-state descent? The sum of all( A )upward forces is less than the sum of all downward forces. ( B )rearward forces is greater than the sum of all forward forces. ( C )forward forces is equal to the sum of all rearward forces. Question:10145 Group:0 Difficult:1 B181Which maximum range factor decreases as weight decreases?( A )Altitude. ( B )Airspeed. ( C )Angle of attack. Question:10149 Group:0 Difficult:1 B182in small airplanes, normal recovery from spins may become difficult if the ( A )CG is too far rearward and rotation is around the longitudinal axis. ( B ) CG is too far rearward and rotation is around the CG. ( C )spin is entered before the stall is fully developed. Question:10150 Group:0 Difficult:159

B183If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its( A )vertical axis. ( B )lateral axis. ( C ) longitudinal axis. Question:10151 Group:0 Difficult:1 A184An airplane will stall at the same( A )angle of attack regardless of the attitude with relation to the horizon. ( B )airspeed regardless of the attitude with relation to the horizon. ( C )angle of attack and attitude with relation to the horizon. Question:10152 Group:0 Difficult:1 B185Longitudinal stability involves the motion of the airplane controlled by its ?( A )rudder. ( B )elevator. ( C )ailerons. Question:10153 Group:0 Difficult:2 B186If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays ( A )positive dynamic stability. ( B )positive static stability. ( C )Neutral dynamic stability. Question:10154 Group:0 Difficult:1 A187If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays( A )neutral longitudinal static stability. ( B )positive longitudinal static stability. ( C ) Neutral longitudinal dynamic stability. Question:10155 Group:0 Difficult:1 B188Longitudinal dynamic instability in an airplane can be identified by ( A )bank oscillations becoming progressively steeper. ( B )pitch oscillations becoming progressively steeper. ( C )Trilatitudinal roll oscillations becoming progressively steeper. Question:10156 Group:0 Difficult:1 A189Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?( A )For a specific angle of bank and airspeed, the rate and radius of turn will not vary. ( B )To maintain a steady rate of turn, the angle of bank must be increased as the airspeed is decreased. ( C )The faster the true airspeed, the faster the rate and60

larger the radius of turn regardless of the angle of bank. Question:10157 Group:0 Difficult:1 A190Why is it necessary to increase back elevator pressure to maintain altitude during a turn? To compensate for the( A )loss of the vertical component of lift. ( B )loss of the horizontal component of lift and the increase in centrifugal force. ( C )rudder deflection and slight opposite aileron throughout the turn. Question:10158 Group:0 Difficult:1 B191To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the( A )forces opposing the resultant component of drag. ( B )vertical component of lift. ( C )horizontal component of lift. Question:10159 Group:0 Difficult:1 C192If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack( A )and angle of bank must be decreased. ( B )must be increased or angle of bank decreased. ( C ) must be decreased or angle of bank increased. Question:10160 Group:0 Difficult:2 A193For a give angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn( A )is constant and the stall speed increases. ( B )varies with the rate of turn. ( C )is constant and the stall speed decreases. Question:10161 Group:0 Difficult:1 B194Airplane wing loading during a level coordinated turn in smooth air depends upon the( A )rate of turn. ( B )angle of bank. ( C )true airspeed. Question:10162 Group:0 Difficult:1 C195If the airspeed is increased from 90 knots to 135 knots during a level 60 banked turn, the load factor will( A )increase as well as the stall speed. ( B )decrease and the stall speed will increase. ( C )remain the same but the radius of turn will increase.

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Question:10164 Group:0 Difficult:1 A196(Refer to Figure 2.) Select the correct statement regarding stall speeds. The airplane will stall( A )10 knots higher in a power-on 60 bank with gear and flaps up than with gear and flaps down. ( B )25 knots lower in a power-off, flaps-up, 60 bank, than in a power-off, flaps-down, wings-level configuration. ( C )10 knots higher in a 45 bank, power-on stall than in a wings-level stall with flaps down. Question:10166 Group:0 Difficult:1 C197To increase the rate of turn and at the same time decrease the radius, a pilot should( A )maintain the bank and decrease airspeed. ( B )increases the bank and increase airspeed. ( C )increase the bank and decrease airspeed. Question:10167 Group:0 Difficult:1 A198As the angle of bank is increased, the vertical component of lift ( A )decreases and the horizontal component of lift increase. ( B )increases and the horizontal component of lift decreases. ( C )decreases and the horizontal component of lift remains constant. Question:10168 Group:0 Difficult:1 B199Which is true regarding the use of flaps during level turns?( A ) The lowering of flaps increases the stall speed. ( B )The raising of flaps increases the stall speed. ( C )Raising flaps will require added forward pressure on the yoke or stick. Question:10169 Group:0 Difficult:1 A200The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flight is known as?( A )load factor and directly affects stall speed. ( B )aspect load and directly affects stall speed. ( C )load factor and has no relation with stall speed. Question:10170 Group:0 Difficult:1 A201Load factor is the lift generated by the wing of an aircraft at any given time( A )divided by the total weight of the aircraft. ( B )multiplied by the total weight of the aircraft. ( C )divided by the basic empty weight of the aircraft. Question:10171 Group:0 Difficult:162

A202In a rapid recovery from a dive, the effects of load factor would cause the stall speed to( A )increase. ( B )decrease. ( C )not vary. Question:10172 Group:0 Difficult:1 B203If an aircraft with gross weight of 2,000 pounds was subjected to a 60 constant-altitude bank, the total load would be( A )3,000 pounds. ( B )4,000 pounds. ( C )12,000 pounds. Question:10173 Group:0 Difficult:1 B204While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will( A )decrease the rate of turn resulting in a decreased load factor. ( B )decrease the rate of turn resulting in no change in load factor. ( C )increase the rate of turn resulting in no change in load factor. Question:10174 Group:0 Difficult:1 A205While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would( A )remain constant regardless of air density and the resultant life vector. ( B )vary depending upon speed and air density provided the resultant lift vector varies proportionately. ( C )vary depending upon the resultant lift vector. Question:10176 Group:0 Difficult:1 A206Stall speed is affected by ( A )weight, load factor, and power. ( B )load factor, angle of attack, and power. ( C )angle of attack, weight, and air density. Question:10177 Group:0 Difficult:1 C207The stalling speed of an airplane is most affected by ( A )changes in air density. ( B )variations in flight altitude. ( C )variations in airplane loading Question:10178 Group:0 Difficult:1 A208Recovery from a stall in any airplane becomes more difficult when its ( A )center of gravity moves aft. ( B )center of gravity moves forward. ( C )63

elevator trim is adjusted nose down. Question:10179 Group:0 Difficult:1 B209The need to slow an aircraft below VA is brought about by the following weather phenomenon: ( A )High density altitude which increases the indicated stall speed. ( B ) Turbulence which causes an increase in stall speed. ( C )Turbulence which causes a decrease in stall speed. Question:10180 Group:0 Difficult:1 A210The angle of attack at which a wing stalls remains constant regardless of ( A )weight, dynamic pressure, bank angle, or pitch attitude. ( B )dynamic pressure, but varies with weight, bank angle, and pitch attitude. ( C )weight and pitch attitude, but varies with dynamic pressure and bank angle. Question:10181 Group:0 Difficult:1 B211One of the main functions of flaps during the approach and landing is to ( A )decrease the angle of descent without increasing the airspeed. ( B ) provide the same amount of lift at a slower airspeed. ( C )decrease lift, thus enabling a steeper-than-normal approach to be made. Question:10183 Group:0 Difficult:1 A212Both lift and drag would be increased when which of these devices are extended?( A )Flaps. ( B )Spoilers. ( C )Slats. Question:10184 Group:0 Difficult:1 B213A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the ( A )wingtip, with the stall progression toward the wing root. ( B )wing root, with the stall progression toward the wing tip. ( C )center trailing edge, with the stall progression outward toward the wing root and tip. Question:10185 Group:0 Difficult:1 B214A propeller rotating clockwise as seen from the rear, creates a spiraling slipstream. The spiraling slipstream, along with torque effect, tends to rotate the airplane to the ( A )right around the vertical axis, and to the left around the longitudinal axis.64

( B )left around the vertical axis, and to the right around the longitudinal axis. ( C )Left around the vertical axis, and to the left around the longitudinal axis. Question:10186 Group:0 Difficult:1 B215An airplane leaving ground effect will ( A )experience a reduction in ground friction and require a slight power reduction. ( B )experience an increase in induced drag and require more thrust. ( C )require a lower angle of attack to maintain the same lift coefficient. Question:10187 Group:0 Difficult:1 A216To produce the same lift while in ground effect as when out of ground effect, the airplane requires ( A )a lower angle of attack. ( B )the same angle of attack. ( C )a greater angle of attack. Question:10188 Group:0 Difficult:1 A217If the same angle of attack is maintained in maintained in ground effect as when out of ground effect, lift will ( A )increase, and induced drag will decrease. ( B )decrease, and parasite drag will increases. ( C )increase, and induced drag will increase. Question:10189 Group:0 Difficult:1 B218Choose the correct statement regarding wake turbulence. . ( A )Vortex generation begins with the initiation of the takeoff roll. ( B )The primary hazard is loss of control because of induced roll. ( C )The greatest vortex strength is produced when the generating airplane is heavy, clean, and fast. Question:10190 Group:0 Difficult:1 A219During a takeoff made behind a departing large jet airplane, the pilot can minimize the hazard of wingtip vortices by ( A )being airborne prior to reaching the jets flight path until able to turn clear of its wake. ( B )maintaining extra speed on takeoff and climb out. ( C ) extending the takeoff roll and not rotating until well beyond the jets rotation point.

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Question:10191 Group:0 Difficult:1 A220Which procedure should you follow to avoid wake turbulence if a large jet crosses your course from left to right approximately 1 mile ahead and at your altitude?( A )Make sure you are slightly above the path of the jet. ( B )Slow your airspeed to VA and maintain altitude and course. ( C )Make sure you are slightly below the path of the jet and perpendicular to the course. Question:10192 Group:0 Difficult:1 A221To avoid possible wake turbulence from a large jet aircraft that has just landed prior to your takeoff, at which point on the runway should you plan to become airborne? ( A )Past the point where the jet touched down. ( B )At the point where the jet touched down, or just prior to this point. ( C )Approximately 500 feet prior to the point where the jet touched down. Question:10193 Group:0 Difficult:1 A222When landing behind a large aircraft, which procedure should be followed for vortex avoidance?( A )Stay above its final approach flight path all the way to touchdown. ( B )Stay below and to one side of its final approach flight path. ( C )Stay well below its final approach flight path and land at least 2,000 feet behind. Question:10194 Group:0 Difficult:1 B223That portion of the gliders total drag created by the production of lift is called.( A )induced drag, and is not affected by changes in airspeed. ( B )induced drag, and is greatly affected by changes in airspeed. ( C )parasite drag, and is greatly affected by changes in airspeed. Question:10195 Group:0 Difficult:1 A224The best L/D ratio of a glider occurs when parasite drag is ( A )equal to induced drag. ( B )less than induced drag. ( C )greater than induced drag. Question:10196 Group:0 Difficult:1 C225At a give airspeed, what effect will an increase in air density have on lift and drag of a glider?( A )Lift and drag will decrease. ( B )Lift will increase but drag will decrease. ( C )Lift and drag will increase.66

Question:10197 Group:0 Difficult:1 B226If the airspeed of a glider is increased from 45 MPH to 90 MPH, the parasite drag will be?( A )two times greater. ( B )four times greater. ( C )six times greater. Question:10198 Group:0 Difficult:1 C227If the indicated airspeed of a glider is decreased from 90 MPH to 45 MPH, the induced drag will be ( A )four times less. ( B )two times greater. ( C )four times greater. Question:10207 Group:0 Difficult:1 C228In theory, if the angle of attack and other factors remain constant and the airspeed is double, the lift produced at the higher speed will be( A ) the same as at the lower speed. ( B )two times greater than at the lower speed. ( C )four times greater than at the lower speed. Question:10013 Group:3 Difficult:2 C229(Refer to Figure 1.)Which is true regarding aerodynamic drag? ( A )Induced drag is created entirely by air resistance. ( B )All aerodynamic drag is created entirely by the production of lift. ( C )Induced drag is a byproduct of lift and is greatly affected by changes in airspeed. Question:10013 Group:4 Difficult:2 C230(Refer to Figure 1.) At the airspeed represented by point A, in steady flight, the airplane will( A )have its maximum L/D ratio. ( B )have its minimum L/D ratio. ( C )be developing its maximum coefficient of lift. Question:10013 Group:5 Difficult:2 B231(Refer to Figure 1.) At the airspeed represented by point B, in steady flight, the pilot can expect to obtain the airplanes maximum( A ) endurance. ( B )glide range. ( C )coefficient of lift. Question:10013 Group:6 Difficult:2 C232(Refer to Figure 1.)The primary purpose of wing spoilers is to decrease ( A )the drag. ( B )landing speed. ( C )the lift of the wing. Question:10016 Group:1 Difficult:267

C233(Refer to Figure 2.) Select the correct statement regarding stall speeds. ( A )Power-off stalls occur at higher airspeeds with the gear and flaps down. ( B )In a 60 bank the airplane stalls at a lower airspeed with the gear up. ( C )Power-on stalls occur at lower airspeeds in shallower banks. Question:10016 Group:2 Difficult:2 A234(Refer to Figure 2.) Select the correct statement regarding stall speeds. The airplane will stall( A )10 knots higher in a power-on 60 bank with gear and flaps up than with gear and flaps down. ( B )35 knots lower in a power-off, flaps-up, 60 bank, than in a power-off, flaps-down, wings-level configuration. ( C )10 knots higher in a 45 bank, power-on stall, with gear and flaps down, than in a wings-level stall. Question:10048 Group:1 Difficult:2 B235(Refer to Figure 3.) If an airplane weighs 4,500 pounds, what approximate weight would the airplane structure be required to support during a 45' banked turn while maintaining altitude? ( A )4,563 pounds ( B )6750 pounds ( C )9063 pounds Question:10048 Group:2 Difficult:2 B236(Refer to Figure 3.) If an airplane weighs 2,300 pounds, what approximate weight would the airplane structure be required to support during a 60' banked turn while maintaining altitude? ( A )4600 kilogram ( B )4600 pounds. ( C )3450 pounds Question:10048 Group:3 Difficult:2 B237(Refer to Figure 3.) If an airplane weighs 3,300 pounds, what approximate weight would the airplane structure be required to support during a 30'banked turn while maintaining altitude?( A )3810kilogram ( B )3810 pounds ( C )6600 pounds Question:10163 Group:1 Difficult:2 C238(Refer to Figure 2.) Select the correct statement regarding stall speeds. ( A )Power-off stalls occur at higher airspeeds with the gear and flaps down. ( B )In a 60 bank the airplane stalls at a lower airspeed with the gear up. ( C )Power-on stalls occur at lower airspeeds in shallower banks. Question:10165 Group:1 Difficult:268

C239(Refer to Figure 4.) What is the stall speed of an airplane under a load factor of 2 Gs if the unaccelerated stall speed is 60 knots?( A )66 knots. ( B )74 knots. ( C )84 knots. Question:10175 Group:1 Difficult:2 C240(Refer to Figure 4.) What increase in load factor would take place if the angle of bank were increased from 60 to 80?( A )3 Gs. ( B )3.5 Gs. ( C )3.7 Gs Question:10199 Group:1 Difficult:2 B241(Refer to Figure 5.) The horizontal dashed line from point C to point E represents the( A )ultimate load factor. ( B )positive limit load factor. ( C )airspeed range for normal operations.

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