New Aero Test

General Information
The new Aero course consists of four class days, each 4 hours long, and the test must be started on the fifth day between around 1015 (check your sked!). You have 2 hours to complete it. The initial failure rate after the first two classes has been 16% (4:25). Failure rates have come down since then, but still take the test seriously. There are 5 CBT's, the first two need to be completed prior to class #1, and the rest have to be completed prior to class #2. These take appx 4 hours to complete. In addition, NATOPS part XI should be read as well as chapters 1-2 end of chapter review completed prior to class #1. According to a reputable source some of the questions in the ICW (CBT's) and workbook are the same as questions on the test, and many of the previous gouge questions were incorporated into the workbook.


 * Example Class Sked
 * Old Question Bank

Enabling Objective/Study Gouge
Below are the instructor-reviewed ELO's from the draft version of Aero (dated 01MAR07) Bravo Zulu to classes 4407 and 4507
 * Aero ELO's (21MAR07)
 * Aero CBT Questions thanks Barraza, Alamo, Scarcella

(NEED GOUGE!)

Aero Test

 * @@@Test changed December 2009@@@
 * Always use 10% rule for humidity on the test, verified by Aero Instructor 5/2008 (2 questions)
 * Know components of generator system (1)
 * Vibration Causes (2 questions)
 * Vne is set by structural limitations (1)
 * Causes and effects of feathering (5-6 questions)
 * Virtual Axes is perp. to TPP and thrust acts through it (2)
 * Components of In-Plane Drag (1)
 * Geometric twist limited by high-speed performance (1)
 * questions that are on the test:
 * 34 on p. 1-26
 * 43 on p. 1-28
 * 28 on p. 3-32
 * 12 on p. 6-25
 * know all questions in ch.7 & ch.8 review
 * Compressibility causes damage to dynamic components because of TORSIONAL (twisting force) on the blades.
 * Transverse flow results in slight RIGHT ROLL and airframe VIBRATIONS. Occurs between 10-20 kias.

Aero Review
Atmosphere: -Composition: 78% Nitrogen, 21% Oxygen, 1% Other Gasses. If RH=100% Approx 4% Water

DA Conversion Chart w/ RH correction using 10% rule for every 10% in relative humidity, add 100 ft. (ALWAYS USE THE 10% rule)

-40% rule(Not used on the test): 0 – 40% RH =no humidity correction. Every 10% over 40%, add 100 ft to Dry DA i.e. 50% RH = +100’ DA

Symmetric- Non-cambered, produces 0 Net lift at 0 AOA, so no twisting moment

Non Symmetric- Cambered, produces lift at 0 AOA, but as a result also produces a twisting/torsion moment and stalls at lower AOA.

Geometric Twist- Provides even distribution of AOA down rotor blades to account for increased speed toward tips. TH-57 has 5 degree reduction from root to tip.

Flapping- Result of differing aerodynamic forces on the blades. Occurs on horizontal hinge and corrects for dissymmetry of lift.

Dissymmetry of Lift- ADV blade has more airspeed due to forward flight. As a result more lift is produced and blade flaps up increasing I.V. and thereby reducing AOA and overall producing less lift. The RET blade flaps down due to the deceased overall velocity causing less lift. Downward flapping decreases I.V. therefore increasing lift which balances out the lift produced by the rotor system.

Blowback occurs during acceleration to forward flight. It is the nose up/slowing acceleration tendency caused by upward flapping of the Advancing Blade in the 90 position translated to the nose (the 360) because of Phase Lag.

Phase Lag- In a two bladed rotor system the effect of an applied force is not felt until 90 degrees from the point it is applied

Geometric Imbalance- Occurs when flapping causes the blade CG to shift. Eliminated in the TH-57 with underslung mounting.

Coriolis Effect- Ice skater’s arms: in spins faster, out spins slower. Lead and Lag about a vertical hinge. TH-57’s underslung mounts on the teetering head eliminate this. Fully articulated have dampeners to restrict movement on vertical hinge. Rigid use flexible mounts.

Torque Effect- Mast and transmission spin left therefore causing the fuselage to want to spin right. This is countered by the tail rotor providing anti torque force. Tail Rotor though causes Translating Tendency.

Translating Tendency- In a hover the tail rotor’s force tends to cause the helicopter to slide to the right. Counter with left cyclic.

Virtual Axis- Axis perpendicular to the TPP or Rotor Disk’s tilt

Mechanical Axis- Also called Physical/Actual Axis on which the rotor actually spins- should be in-line with the CG

Control Axis- Axis perpendicular to the swash plates.

Coning- The upward angle of rotor system under load. Is the balance of aerodynamic force (lift) and centrifugal force.

Vortices- The result of high pressure below an airfoil moving to the low above and the associated turbulence.

Ground Effect- The reduction in vortices as well as the reduction in I.V. when operating within one rotor diameter of the ground, measured from the rotors.

Translational Lift- Horizontal mass flow through the system decreases I.V. therefore increasing lift and making the system more efficient. Rotors are able to essentially outrun their own vortices and expose the leading edges to clean air. Occurs any time horizontal air velocity is present but is considered EFFECTIVE at 13-24 kts. This deals with momentum theory b/c of mass flow.

Pendulum Effect- Pulling collective in the flare causes the nose to want to swing up.

Transverse Flow Effect- Occurs at 10-20kts and is a result of higher I.F. at the back of rotor disk causing decrease in AOA. Phase lag causes this to be felt at the 90 position and causes a drooping right roll tendency.

Autorotation- Has three phases: Entry- Immediate airflow reversal (down collective), Steady State Descent- Managing Nr and Airspeed (90-107 Nr, Optimal 94-95, & 50 or 72kts), Deceleration and Touchdown- 100’ start flare 20- 15’ Collective and level nose. ~Stall Region- Close to the hub/mast actual AOA is greater than stall AOA due to slow rotational speed ~Autorotative/Driving Region- AOA causes more thrust than drag providing lift/thrust to the rotor ~Propeller/Driven Region- AOA causes more drag tending to slow the blade/resist autorotation ~Reverse Flow Region- Caused in forward flight autos- Horizontal speed over takes rotational velocity near the center of the stalled region.

Retreating Blade Stall- Severe case of dissymmetry of lift, results in a up pitch. left roll. Caused when linear speed increases to the point where retreating blade flap causes increases past critical AOA. Increases in weight, DA, G-Load, and Collective increase the probability.

Compressibility- Loss of lift and buffeting that occur when advancing blade approaches the local speed of sound.

Vortex Ring State- at 40kts or less with decent rates of 800 fpm or greater. This causes the aircraft to settle into its own dirty air and become enveloped in its own vortex.

Ground Resonance- Caused by an imbalance in the rotor head and contact with the ground. Fully articulated systems are most susceptible due to their ability to lead and lag.

Dynamic Rollover- Requires a pivot point, Thrust = Weight, and a rolling moment or inertia. Collective full down is the best response.

Mast Bumping- Low G, rapid cyclic inputs, flight near CG limits and steep slope landings can cause the Rotor head to bang against mast. Recovery varies for condition: Start- center cyclic Slope LDG- return to hover and center cyclic, and then find somewhere else to land Engine Failure- cyclic to maintain G, keep Nr Low G- cyclic pull aft, collective pull up Nose High- collective up, cyclic neutral

Vibrations- Three Categories: Low Frequency: 1-1 Lateral = Main Rotor out of Balance 1-1 Vertical = Main Rotor out of Track Medium Frequency: Loose component or cargo High Frequency KA Flex shaft, engine, tail rotor, or transmission failure or fault- i.e. anything that 	rotates.

Know: Blade Element Diagram, Pr/Pa Diagram, & HV Diagram

Example Test Questions
NEW AERO TEST GOUGE

READ THE QUESTIONS. THE TESTS USE A LOT OF QUESTIONS FROM THE OLD AERO EXAM QUESTION BANK (STRAIGHT FROM THE COURSE WRITER). HOWEVER, THE WORDING HAS BEEN CHANGED ON SOME TO MAKE IT TRICKIER, SO READ THE QUESTIONS CLOSELY BEFORE ANSWERING!!!!

1. What aggravates compressibility
 * Decrease in air temp

2. What are the main forces on rotor blades
 * Centrifugal and aerodynamic

3. If you input a cyclic control to lower blade pitch at 90 degrees to your left what happens?
 * TPP Pitches back (aft)

4. What aggravates dynamic rollover
 * Increase in collective

5. On a fully articulated rotor head
 * Blades can feather flap, feather, lead and lag independently (each blade has a horizontal and vertical hinge).

6. 1 per rotation vertical vibration is due to what?
 * Blade out of track

7. How can a CH-46 have 2 main rotors and no tail rotor?
 * The two rotors spin opposite each other

8. Transverse flow effect is felt when?
 * Only at lower air speeds

9. Ground effect is affected by what?
 * Not effected by airspeed

10. What is the density altitude on a cold dry day?
 * Low density altitude due to high air density

11. Increased gross weight affects how?
 * a) Increase in power available
 * b) Increase in power required
 * c) Decrease in power available
 * d) No effect

12. What is true about retreating blade stall
 * Turbulent air, abrupt maneuvering and causes pitch up and roll left

13. How does a rigid rotor head allow for flapping?
 * Bending of rotor head

14. A fully articulated rotor head does not incorporate…
 * Flapping dampeners

15. Flapping causes the advancing blade to flap up and the CG to shift to the center of rotation causing?
 * An increase in Vrot, known as the Corriolis effect.

16. On a semirigid system the tip path plane is a line through the tips of the rotors and?
 * a) Chordline
 * b) Rotor hub
 * c) AOA line
 * d) Pitch plane

17. What is true of a helicopter in a 30 degree AOB turn?
 * The total lift vector must increase causing increased G loading

18. Linear velocity is parallel to the tip path plane and induced velocity is
 * Perpendicular to the tip path plane

19. In an autorotation flare, the rate of descent and ______ decrease and _________
 * Airspeed, rotor RPM increases

20. Max glide Airspeed in an autorotation is
 * Higher than max endurance Airspeed

21. What are the characteristics of in plane drag?
 * Anti-autorotative force in unpowered flight

22. When the pilot moves the cyclic forward, what happens to the mechanical axis with relation to the fuselage?
 * It remains stationary.

23. If not compensated for, a decrease in power will result in?
 * Yaw to the left due to anti-torque pedals

24. Ground effect is caused by?
 * Decrease in induced velocity, decrease in wingtip vortecies.

25. An increase in translational lift is due to?
 * A decrease in induced velocity

26. Flapping is caused by?
 * Dissymmetry of lift

27. Flapping?
 * Is directly proportional to airspeed

28. Flapping causes...
 * Blowback

29. In an autorotation, higher than optimum main rotor RPM leads to?
 * Increase in rate of descent

30. On density altitude charts, 1000’, 20 degrees C 80% RH leads to what DH?
 * 2200 feet, (looks like 2300)

31. Contributing factors to retreating blade stall?
 * High gross weight, low rotor RPM, turbulent air

32. Lead and lag are used to compensate for what?
 * Coreolis effect

33. Profile drag
 * Is parallel to the relative wind, perpendicular to lift

34. T/F: Rotational velocities are faster at the root than at the tip?
 * False

35. With 50% RH, air is half as dense?
 * False

36. In a dynamic rollover situation what must be true?
 * Lift produced must be close to weight

37. Rotor blade vortices are…
 * The same as wingtip vortices

38. The four regions of flow in an autorotation
 * Prop, autorotative, stall, reverse flow

39. When the nose of the aircraft suddenly pitches up in high speed flight
 * The pilot should NOT pull aft cyclic/ up collective

40. For autorotation entry, what is required?
 * Reduce in-plane drag (lower collective), reverse induced velocity, maintain/regain Nr

41. Too much cyclic movement in the flare can cause what?
 * Increased Nr up to the windmill brake state

42. In a semi-rigid rotor system, what allows flapping?
 * a) Flexing
 * b) It doesn’t flap
 * c) Vertical hinge pin
 * d) Horizontal hinge pin

43. In a conventional US helicopter the tail rotor can produce thrust to the left to:
 * Counter transmission drag

(This answer is disputed)

44. In forward flight, in comparison to each other, the rotor blades have
 * Unequal velocity, equal lifting moment, and unequal AOA.

45. On an airspeed vs. power required chart, a line from the origin that is tangent to the curve will determine
 * a) Max endurance airspeed
 * b) Max rate of descent
 * c)  Max range airspeed
 * d) None of the above

46. Helicopter drift in the direction of tail rotor thrust in a hover is called what?
 * a) Corriolis effect
 * b) Translating tendency
 * c) Transverse flow effect
 * d) Pilot error

47. As the AOA on a symmetric airfoil increases, what happens to the center of pressure?
 * Remains Constant

48. During the flare portion of an autorotation, what causes the increase of rotor RPM?
 * The increase in lift due to the change in angle of attack on the main rotor blades (think about the change in induced flow)

49. For a constant RPM rotor, what causes upward bending of the rotor blades?
 * Increase lift is greater than increase centrifugal force.

50. What causes a slight descent in the first stages of forward flight?
 * Too much forward cyclic.

51. A ____ in Nr will cause a ____ in airspeed needed to enter retreating blade stall.
 * Decrease/decrease

52. Air density will increase when temperature and humidity ____ and pressure ____
 * Decrease/increases

53. To tip the tip path plane aft, where must the blade pitch be the greatest?
 * 3 o'clock/90 degree position

54. What is the most effective method to stop dynamic rollover?
 * Steady smooth downward motion of the collective.

55. What limits Vne in straight and level flight?
 * Structural limitations and torque available

56. At 100% humidity, how much water vapor occupies the air by volume?
 * 4%

57. Which of the following is not a requirement to enter an autorotation?
 * Left pedal trim

58. During a steep approach at low airspeed you experience an uncommanded increase in the rate of descent. You may be experiencing what?
 * Vortex Ring State

59. On the H-v diagram, where would you not want to be?
 * Out of ground effect hover at 400 feet
 * Low altitude, high airspeed

60. What are indications of entering retreating blade stall in order of ocurrance?
 * Low frequency vibrations, nose pitches up, uncommanded left roll

61. During an autorotation, the inner section of the rotor system will be _____ due to the _____ ?
 * Stalled, excessive AoA

62. Your aircraft is power required greater than power available. Placing the collective down will?
 * Increase the rate of descent

63. High frequency vibrations/buzzing could be caused by?
 * The Barbell Shaft

64. What effect will a headwind have on max range airspeed?
 * It will increase the airspeed for max range

65. What is true regarding rotor blade vortices?
 * They are similar to the wingtip vortices produced by an airplane in forward flight

66. The virtual axis is
 * Perpendicular to the tip path plane

67. Moving the cyclic will do what to the rotor blades?
 * Cause a equal change in blade pitch but in opposite direction

68. If settling occurs with a reduced airspeed at max power, what should be done to ensure level flight?
 * Return to the original airspeed

69. If experiencing vortex ring state, what actions should be taken?
 * Forward cyclic and slight reduction of collective

70. During the initial phase of dissymetry of lift, the advancing blade feels increased linear flow, thus increasing ____ and increasing aerodynamic force causing the blade to flap ____.
 * AoA, up

71. A destructive vibration occurring in the rotor system when the aircraft is in contact with the ground is?
 * Ground resonance

72. If flying in the low/fast portion of the Height/Velocity diagram, why is this dangerous?
 * Pilot reaction time (a distractor is severity of menuever, this is NOT the correct answer. Also this is not the exact wording of the question...)

73. While in unpowered flight if induced flow increases, angle of attack also increases...

74. Hydrogen (not Nitorgen) makes up how much of the atmosphere?
 * less than 1%

75. During the flare of an autorotation, rapid cylic input may cause?
 * Rotor Overspeed

76. In high velocity forward flight, decreased induced velocity and increased AOA may lead the retreating blade to?
 * Stall

77. On a cold, dry day, one would expect the density altitude to...?
 * Decrease and air density to increase.

78. In a fully articulated rotor system, blades are able to...?
 * Flap, Feather, and Hunt (Lead/Lag) independently

79. Cockpit gauges indicate high TOT, high Ng, high rate of descent, and decaying Nr. You are experiencing ________?
 * Pr>Pa

80. Cockpit gauges indicate high TOT, high NG, high rate of descent, and normal Nr. You are experiencing __________?
 * Vortex Ring State

81. Mast Bumping occurs in what type of rotor system?
 * Semi-rigid

82. Primary cause for Mast Bumping...
 * Low G's

83. Recovery from Mast Bumping...
 * Aft cyclic then center (According to the test, this is a more appropriate initial step than a collective input)

84. Geometric imbalance is compensated for using...?
 * Underslinging

85. Max Ng and TOT at a constant forward airspeed with Nr decreasing is an indication of what condition and what should the pilot do?
 * PR>PA and the pilot should accelerate /decelerate to max endurance airspeed.

86. Air density increases as temperature and humidity _____ and presure_____.
 * Decrease....Increase.

87. Air at 50% humidity is half as dense as Dry Air.
 * False

88. As outside air temp increases, what will happen?
 * Air density decreases

89. A plane defined by tips of rotor blades is
 * Tip path plane

90. In a rotating system the linear flow is greatest at blade root and least at the blade tip.
 * False

91. Induced drag is created as a result of the production of _____ and in-plane drag is the sum of the _____ in the plane of rotation.
 * lift...decelerating forces

92. As density altitude increases, the power required will increase because the rotor blade is/are less efficient.
 * True

93. A decrease in air density will
 * decrease rotor efficiency.

94. Which of the following factors affects density altitude?
 * Humidity and temp

95. Density altitude is pressure altitude corrected for
 * humidity and temp

96. On a cool, dry day one would expect
 * the density altitude to be low and the air density to be high

97. Rate of descent in autorotation is affected by which of the following
 * Nr

98. As temp increases above standard day conditions, density altitude will decrease.
 * False

99. Pressure altitude is based on which of the following elements
 * Standard atmosphere

100. What is pressrue altitude?
 * Altitude corresponding to particular static air pressure in standard atmosphere

101. Aircraft altimeters are constructed for the pressure-height relationship
 * and can determine the pressure altitude by dialing in 29.92

102. By volume hydrogen is approximately what percent of teh earth's atmosphere?
 * Less than one

103. Water composes approximately _____% of air by volume at 100% humidity.
 * 4%

104. High twist angles on a rotor blade are limited due to which of the following
 * High speeds

105. Constructing a rotor blade so that it's pitch angle increases as you go from the tip to the root is called
 * geometric twisting

106. Which of the following results are characteristic of geometric twisting
 * Improves helicopters performance by making lift distribution along the blade more uniform.

107. Using a ____ airfoil will eliminate rotor blade pitching moments
 * symetrical

108. Two major forces acting on the rotor head arc are
 * centrifugal and aerodynamic

109. Power required to rotate a rotor system is directly proportional to
 * in plane drag

110. In powere flight, when linear flow increases, which of the following changes will occur
 * AOA increases

111. In powered flight, the induced flow increases, the AOA
 * Decreases

112. As you increase density altitude, the power required/power available chart will show a/an
 * decrease in max power available

113. AOA is found between the chord line and the
 * relative wind

114. On the blade element diagram, the relative wind vector is the result of ___ and ___ vectors
 * induced flow and linear flow

115. What component counteracts main rotor torque in a hover
 * tail rotor

116. Which of the following functions does teh tail rotor serve
 * Controls aircraft about vertical axis.

117. In a single rotor helicopter, movement of the directional control pedals will
 * vary the pitch of the tail rotor blades

118. During ground resonance, if unable to takeoff, the pilot should
 * shut down the engine and apply the rotor brake

119. Rotor tip vortices
 * are created by high pressure air below the airfoil flowing to low pressure air above it.

120. Helicopter A weights 23,000 lbs and helicopter B weighs 22,000 lbs. Which produces more intense rotor tip vortices
 * Helo A

121. What two forces determine coning angle
 * aerodynamic force and centrifugal force

122. Linear flow is parallel to tip plane path while induced flow is
 * perpendicular to tip path plane

123. Within it's envelope, when there is a ______ in AOA, there is a corresponding increase in the _____
 * increase.....lift

124. Using a ____ airfoil will increase rotor blade pitching moments
 * non-symetrical

125. What is the extension of the centerline of the rotor mast called
 * mechanical axis

126. Which of the following is a description of the virtual axis
 * an apparent axis about which the rotor system appears to turn

127. What is the actual axis of rotation in forward flight
 * mechanical axis

128. More power is available for the main rotor system in forward flight because of the
 * vertical stabilizer

129. Tail rotor loading is decreased in forward flight by which of the following effects
 * vertical stab lift, weather vaning effect

130. Since the tail rotor is a thrust producer, in what direction does teh tail rotor cause the helo to drift?
 * Right

131. A system having an even number of rotor systems of the same design rotating in opposite directions
 * is effective since both torque effects blance each other out

132. In multi-rotor systems, the torque effect is compensated by having an ___ number of rotor systems rotating in ___ directions
 * even... opposite

133. During hovering right turn, you may experience a sudden uncommanded right yaw caused by
 * main rotor vortices

134. In the th-57 torque effect created by the main rotor system causes the fuselage to rotate
 * clockwise

135. What will happen to the fuselage when you add power
 * Yaw to the right due to torque effect.

136. Increase in helo weight causes what reaction
 * increase in power required

137. Power required is always increased by both
 * increase in DA and increase in weight

138. What is the lowest point on the power required versus airspeed curve
 * Max rate of climb

139. During reaward flight the TPP is perpendicular to the
 * Virtual axis

140. When the pilot of a th-57 helicopter moves the cyclic stick forward, the mechanical axis will ___ with respect to the fuselage
 * remain stationary

141. In a single rotor helicopter, moving the center of gravity forward will
 * require aft cyclic control movement to maintain original attitude.

142. With an engine loss in a hover, the pilot must move the ___ to the___ when the failure occurs to compensate for the reduced tail rotor thrust
 * cyclic... right

143. The main rotor must be tilted to the ___ in order to counter teh affect of the tail rotor, thus the helicopter will tend to land on the ___ skid first
 * left...left (the RIGHT skid will lift off first on take off)

144. The virtual axis of a rotor system always remains perpendicular to the
 * tip path plane

145. When making a vertical takeoff, what will happen to the tail rotor power requirements
 * Increase

146. In a no-wind hover, a pedal turn to the ___ in the th-57 would cause the tail rotor to deman ___ power
 * left...more

147. The fully articulated head allows lead lag by ____ and flapping by ___
 * vertical hinge pin....horizontal hinge pin

148. In order to tilt the rotor disc to the left, blade pitch must decrease at the ___ and increase at the ___ positions
 * 12 O'clock....6 O'clock

149. Which of the following characteristics is associated w/ best range airspeed
 * increases with a head wind

150. The additional performance produced by the rotor system because of forward flight is called
 * translational lift

151. One phenomena which decreases power required while hovering in ground effect is
 * reduction of induced flow

152. Max power for climb
 * is available at max endurance airspeed

153. An increase in density altitude
 * has no effect on max endurance airspeed

154. Best range airspeed in a no-wind situation is
 * is located at the point where a line drawn from the origin becomes tangent to the power required curve

155. In a single rotor helo, a change in fuselage center of gravity location will result in
 * opposite proportional change in cyclic position to maintain a hover

156. If while in a hover, the helo enters uncontrolled flight to right even though pilot has applied full left cyclic, the helo may
 * have exceeded right center of gravity limits

157. With an aft center of gravity shift on helos, the nose attitude will move ____ and the pilot must compensate with ___ cyclic
 * up...forward

158. What effect does airspeed have on rotor blade flapping
 * Increased airspeed increased flapping

159. What statement reflects blade flapping in forward flight
 * Varies the angle of attack on the blades

160. Because of the effect of blowback while accelerating in forward flight, what must you do to maintain level flight
 * Trim cyclic forward

161. To compensate for dysemetry of in a semirigid rotor system in forward flight, the blades will do which of the following actions
 * advancing blade flaps up and retreating blades flap down

162. Disymetry of linear flow experienced by the rotor blade in forward flight causes the blade to do which of the following motions
 * Retreating blade flaps down and induced flow decreases

163. During the initial phase of disymetry of lift and the resulting flapping effect, the advancing blade feels increasing linear flow, thus increasing ____ and increasing aerodynamic force causing the blade to flap ____
 * AOA...up

164. Translational lift increases available lift due to
 * decrease induced flow

165. Translational lift is increased while
 * increasing forward airspeed

166. Which of the following chracteristics is related to a semirigid rotor system
 * flapping is accomplished by a horizontal hinge pin (trunion)

167. Max range airspeed of a helo in an autorotation
 * higher than maximum endurance TAS.

168. Which of the following chracteristics best describes powered flight best range airspeed
 * lower with a prevailing tail wind

169. Powered flight best range airspeed will
 * increase with a head wind

170. Ground effect increases lift when the rotor system is operating within approximately one rotor diamter surface by
 * decreasing induced flow

171. Ground effect
 * is not affected by airspeed

172. Fore and aft asymetry of lift, or transverse flow, continue in forward flight due to
 * coning

173. Flapping action of rotor blades while transitioning to forward flight will
 * cause blowback

174. What will occur when centers of mass in rotor blades are at different radii to the mechanical axis
 * geometric imbalance

175. The solution to geometric imbalance in the semirigid rotor system is
 * the underslung configurations

176. Flapping of the rotor blades in forward flight will
 * be directly proportional to airspeeds

177. Without flapping in forward flight, the helo would develop what phenomenon
 * disymetry of lift

178. The semi-rigid rotor head compensates for dissymetry of lift by
 * horizontal hinge pins.

179. When the pro-autorotative forces equal in-plane drag, the rotor RPM will be
 * stabilized

180. The ____ which enable the pilot to ____ RPM during autorotative flight
 * pro-autorotative force... increase

181. Anti autorotative forces
 * will cause the rotor system to decelerate

182. When transitioning into forward flight the aircraft will settle because of
 * ground vortex

183. When first transitioning to forward flight, _____ power may be required because of the effect of ____
 * more....ground effect

184. What is teh self-induced rotation of a rotor system in unpowered flight
 * autorotation

185. Ground effect is caused by
 * decrease in induced flow and wing tip vortex

186. Geometric imbalance is alleviated in a rigid rotor head by
 * bending of the rotor head

187. Which of teh following statments is characteristic of geometric imbalance in the semirigid rotor system.
 * Is nearly eliminated by aligning the blade's center of mass with the centerline of the flapping hinge

188. The internal vibration as a rotor system goes into forward flight (at approximately 10-15 knots) is caused by
 * transverse flow

189. Less than optimum airspeed during autorotative flight will have which of the following results
 * increased rate of descent

190. When flying at low altitude, high speed, succesful transition to a safe autorotation is unlikely due to
 * pilot reaction time

191. Flying in the shaded portions of the height velocity diagram
 * is not recommended in case of engine failure

192. During the flare at the end of an autorotation, the ____ flow vector ___. The resulting increase in angle of attack creates more lift.
 * induced...increases

193. An autorotative flare will increase rotor RPM and
 * decrease A/S and decrease rate of descent

194. Which of the following statements is true concerning in-plane drag
 * Anti-autorotative force in unpowered flight

195. Anti autorotative force _____ when the pilot ____ the collective in autorotative flight
 * increase....raises

196. Succesfull autorotative entry does not include which of the following requirements
 * Up collective to slow rate of descent

197. In unpowered flight, the ____ is reveresed
 * induced flow

198. During unpowered flight, which of the following vectors is reversed
 * induced flow

199. If the resultant aero forces vector of a blade element is forward of the vertical, then the blade element is
 * pro-autorotative

200. When does the vortex ring state take place
 * when a/c settles into its own downwash and rotor vertices

201. if vibrations and loss of control response occurs during a steep approach of less than 40 knots and rate of descent greater than 800 fpm, the helo is probably
 * entering a vortex ring state condition

202. Concerning the height-velocity diagram, what conditions should be avoided
 * hovering out of ground effect below 100ft.

203. In forward flight, retreating blade stall causes a nose up pitching moment because of
 * phase lag action on the stalled sector of the rotter diameter

204. The increased angle of attack, on the retreating blade at high forward airspeed may cause
 * blade stall

205. During an autorotation, the inner section of the rotor system will be ___ due to the ___
 * stalled.... excessive angle of attack

206. Two factors that affect autorotative rate of descent are
 * airspeed and rotor RPM

207. During autorotation rotor speeds below optimum RPM
 * will cause a increase in rate of descent.

208. During the transition to unpowred flight, ____ maintains rotor speed until induced flow is fully reversed
 * inertia

209. IOT transition from powered to unpowered flight you must do which, if any, of the following actions
 * reduce inplane drag, reverse induced flow, regain and maintain RPM

210. The constant RPM of a rotor system in autorotation will stabilize at a constant value when which of the following actions take place
 * pro-autorotative forces are equal to the anti-autorotative forces

211. An increased induced flow occuring at low rotor heights and approximately 15 knots is
 * ground vortex

212. An undesirable structural twisting of the main rotor blade at or near the speed of sound could occur because of
 * compressibility

213. Recovery from compressibility may include the following steps
 * decrease Nr, decrease airspeed, decrease DA

214. ____ frequency vibrations can be caused by a loose aircraft component vibrating sympathetically with the rotor system.
 * Medium

215. Which of the following may contribute to the rolling tendency during dynamic rollover
 * increased collective

216. Which, if any, of the following actions is teh most effective way to stop a rolling motion and prevent dynamic rollover
 * a smooth moderate collective reduction

217. Which of the folling actions contribute to mast bumping
 * Low G maneuvers

218. If settling is encountered, with a reduced airspeed at maximum power, what should be regained to insure level flight
 * Maximu endurance airspeed

219. What is ground resonance
 * Destructive vibrations

220. A destructive vibration in the rotor system when the aircraft is in contact with the ground is
 * ground resonance

221. In the event of vortex ring state the pilot should apply
 * slight down collective and forward cyclic

222. With the cockpit indication of increased rate of descent, high Ng, high TOT, decaying Nr, the pilot is experiencing
 * Power required exceeding power available

223. When experiencing Pr<Pa, among the cockpit indications are
 * high Ng and decaying Nr.