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x. ORAL STUDY GUIDE - 737NG > FLIGHT CONTROLS > Flashcards

FLIGHT CONTROLS Flashcards

1
Q
  1. What is being tested when this stall test switch is pushed?
A

 SMYD (Stall Management & Yaw Damper Computer)

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2
Q
  1. When can you perform the test of the stall warning system?
A

 On the ground

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3
Q
  1. What electrical power must be available for

the stall test?

A

 AC power

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4
Q
  1. When is the stall warning system armed for

operation?

A

 Inflight

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5
Q
  1. Will the FO’s stick shaker be felt on the

Captain’s control column?

A

 Yes

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6
Q
  1. What does the amber color on the Leading

Edge Device annunciator represent?

A

 LED in transit

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7
Q
  1. What does the green color on the Leading

Edge Device annunciator represent?

A

 LED in extend or full extend position

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8
Q
  1. What color is the annunciator for an LED in

transit?

A

 Amber

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9
Q
  1. What color is the annunciator for an LED in a

proper position?

A

 Green or Extinguished (retracted)

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10
Q
  1. What is wrong if all lights on the LED are

extinguished?

A

 Nothing

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11
Q
  1. Why do leading edge flaps have just two

positions on the annunciator?

A

 They are either retracted or extended

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12
Q
  1. Why do leading edge slats have three

positions on the annunciator?

A

 Retracted, Extended or Full Extended

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13
Q
  1. When might a green light be an indication of

an abnormal condition?

A

 LED jammed or in an improper or uncommanded position

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14
Q
  1. If this panel was inoperative, where could you monitor LED’s in transit?
A

 Forward Instrument Panel LE flaps in transit light

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15
Q
  1. Is autoslat movement displayed on the LED annunciator panel?
A

 Yes

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16
Q
  1. Is autoslat movement displayed on the LE

FLAPS TRANSIT light on the Center Forward Panel?

A

 No, this light is inhibited during auto slat ops

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17
Q
  1. What happens when you press the test switch?
A

 All lights on the annunciator panel illuminate

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18
Q
  1. Do the LED annunciator lights test with the MASTER LIGHTS TEST switch on the forward panel?
A

 Yes

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19
Q
  1. At what flap setting do slats move to the

EXTEND position?

A

 Flaps1, 2, & 5

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20
Q
  1. At what flap setting do the leading edge flaps

move to FULL EXTEND?

A

 Flaps 1 or greater

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21
Q
  1. At what flap setting do slats move to the FULL

EXTEND position?

A

 Flaps 10 or greater

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22
Q
  1. How many ailerons are there?
A

 Two

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23
Q
  1. How many elevators are there?
A

 Two

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24
Q
  1. How many rudder sections are there?
A

 One

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25
Q
  1. How are the ailerons operated normally?
A

 Cables connect control wheels to the hydraulic PCUs (power control units)

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26
Q
  1. How are the ailerons operated with the loss of Hyd. System A or B?
A

 No change from normal

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27
Q
  1. How are the ailerons operated with loss of

both Systems A and B?

A

 Manually by cables

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28
Q
  1. What is installed on the ailerons to aid with

manual reversion flight?

A

 Balance tab

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29
Q
  1. How are the elevators operated normally?
A

 Cables connect control columns to PCUs

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30
Q
  1. Are the elevators interconnected?
A

 Yes, by a torque tube

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31
Q
  1. How are the elevators operated with the loss of System A or B?
A

 No change from normal

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32
Q
  1. How are the elevators operated with the loss

of both systems A and B?

A

 Manually by cables

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33
Q
  1. What is installed on the elevators to aid with

manual reversion flight?

A

 Balance tabs

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34
Q
  1. How is the rudder operated normally?
A

 Cables connected to hydraulic PCUs

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35
Q
  1. Are the rudder pedals interconnected?
A

 Yes

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36
Q
  1. Which hydraulic system normally powers the

main rudder PCU?

A

 Both A and B

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37
Q
  1. Which hydraulic system normally powers the main yaw damper?
A

 System B

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38
Q
  1. How is the rudder operated with the loss of

System A?

A

 System B and STANDBY rudder PCU

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39
Q
  1. How is the rudder operated with the loss of System B?
A

 System A and STANDBY rudder PCU

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40
Q
  1. How is the rudder operated with the loss of

both Systems A and B?

A

 STANDBY rudder PCU

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41
Q
  1. What happens if the FLT CONTROL A switch is moved to OFF?
A

 Flight control shutoff valve closes isolating flight controls from system A hydraulics

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42
Q
  1. What happens if the FLT CONTROL A switch is moved to STBY RUD?
A

 Activates the standby pump and opens the standby rudder shutoff valve

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43
Q
  1. What happens if the FLT CONTROL B switch is moved to OFF?
A

 Flight control shutoff valve closes isolating flight controls from the system B hydraulics

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44
Q
  1. What happens if the FLT CONTROL B switch is moved to STBY RUD?
A

 Activates the standby pump and opens the standby rudder shutoff valve

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45
Q
  1. What happens if both FLT CONTROL switches are moved to OFF?
A

 Pressure from both A and B systems is removed from the elevators, ailerons, and the rudder

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46
Q
  1. What happens if both FLT CONTROL switches are moved to STBY RUD?
A

 Standby rudder PCU is still powered, flight controls revert to manual ops, & standby yaw damper is enabled (turn switch on)

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47
Q
  1. Would the operation of the primary flight controls be affected by a loss of System A or B?
A

 No

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48
Q
  1. Would the operation of the primary flight controls be affected by the loss of Systems A and B?
A

 Yes

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49
Q
  1. On the modified rudder system, what does the

STBY RUD ON light mean?

A

 It indicates the standby rudder system is commanded on to pressurize the standby rudder power control unit

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50
Q
  1. What limits full rudder authority in flight after takeoff and before landing?
A

 At speeds above approx 135KTS, both hyd system A and B pressure are reduced by 25% each

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51
Q
  1. What is the purpose of the Force Fight Monitor (FFM)?
A

 It detects opposing pressure (force fight) between A and B actuators in the main rudder PCU

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52
Q
  1. What happens if opposing pressure is detected?
A

 The FFM automatically turns on the standby hydraulic pump, opens the standby rudder shutoff valve, and illuminates the STBY rudder on, MC, and flight control light

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53
Q
  1. How is the Captain’s control column connected to the primary flight controls?
A

 Cables to the aileron PCUs

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54
Q
  1. How is the FO’s control column connected to

the primary controls?

A

 Cables to the spoiler PCUs

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55
Q
  1. Are the Captain’s and FO’s control wheels

connected?

A

 Yes–by a cable drive system

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56
Q
  1. Would control forces be higher during manual

reversion flight?

A

 Yes–friction & air loads

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57
Q
  1. What happens if an aileron or spoiler becomes

jammed?

A

 Aileron transfer mechanism allows operating controls to be separated from non-operating controls

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58
Q
  1. How are the ailerons trimmed?
A

 Electronically repositioning the aileron feel

& centering unit

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59
Q
  1. Where is the aileron trim indicated?
A

 Top of the control column

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60
Q
  1. Do the control wheels move when the ailerons are trimmed?
A

 Yes

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61
Q
  1. Can the aileron trim be used during manual

reversion?

A

 Yes

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62
Q
  1. Should the aileron trim be used with an autopilot engaged? Why or why not?
A

 No! Abrupt roll if not in trim when the A/P is disengaged

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63
Q
  1. What happens if an elevator becomes jammed?
A

 Transfer mechanism allows separation of control columns to breakout operating control column

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64
Q
  1. What system is still available to assist with a jammed elevator?
A

 Stab trim

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65
Q
  1. How are the elevators trimmed?
A

 Only by mach trim above .615 mach

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66
Q
  1. How is pitch trim accomplished?
A

 Stab trim

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67
Q
  1. How many speeds does the stabilizer trim

motor have?

A

 Two

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68
Q
  1. When do these two speeds of stabilizer trim

motor operate?

A

 High speed with flaps extended and low speed with flaps retracted

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69
Q
  1. How is the rudder trimmed?
A

 Electronically and hydraulically repositioning the rudder Feel & ControlUnit

70
Q
  1. When the rudder trim is used, are the rudder pedals displaced?
A

 Yes

71
Q
  1. What is indicated by a FLT CONTROL LOW

PRESSURE light?

A

 Just that

72
Q
  1. Is this LOW PRESSURE light ever

deactivated? When?

A

 Yes, when standby rudder is on

73
Q
  1. In normal operation, would crew members be

concerned with operating the SPOILER switches?

A

 No

74
Q
  1. For what purpose are the SPOILER switches used?
A

 Maintenance

75
Q
  1. How do spoilers aid with roll control of the

airplane?

A

 Spoilers rise on the wing with up aileron when control wheel is displaced more than 10 degrees

76
Q
  1. How many spoiler panels are used as flight spoilers?
A

 8

77
Q
  1. From what hydraulic system do flight spoilers receive pressure?
A

 Half from A, half from B

78
Q
  1. What purpose other than roll control are the

spoilers used?

A

 Speedbrakes

79
Q
  1. When is flight spoiler activation initiated?
A

 Approx 10 degrees of control wheel displacement

80
Q
  1. Which hydraulic system normally powers the main rudder PCU?
A

 A and B systems

81
Q
  1. Which hydraulic system normally powers the

main yaw damper?

A

 B system

82
Q
  1. What condition would illuminate the yaw damper light?
A

 B flt control switch off or stby rudder,or the SMYD computer senses a system fault

83
Q
  1. If hydraulic System B fails will the yaw damper

switch move to OFF automatically?

A

 No

84
Q
  1. Will the yaw damper switch ever move to OFF

automatically?

A

 Yes (B flt control switch to Off or stby

rudder)

85
Q
  1. Can the yaw damper switch be turned ON after a loss of System B hydraulics (only)?
A

 No

86
Q
  1. When can the yaw damper switch be turned

ON after an automatic disengagement?

A

 A & B flight control switches in stby rudder

87
Q
  1. How are the Trailing Edge flaps normally operated?
A

 Hydraulically from system B

88
Q
  1. What is the backup system for operation of

the TE flaps if the B system fails?

A

 Electrically through the alternate flaps position switch

89
Q
  1. What happens when you move the ALT FLAPS MASTER switch to ARM?
A

 Activates the standby pump
 Arms alt flaps position switch
 Closes the trailing edge flap bypass valve

90
Q
  1. How then are the TE flaps extended?
A

 By an electric motor

91
Q
  1. Can the TE flaps be retracted with the ALT FLAPS POS switch?
A

 Yes

92
Q
  1. What feature normally available would not be

available during alternate flap operation?

A

 Asymmetry and skew protection

93
Q
  1. What happens to the LED’s when you activate

the ALT FLAPS POS switch?

A

 All LEDs go to full extend

94
Q
  1. Can the LED’s be retracted with this switch?
A

 No

95
Q
  1. Does the ALT FLAPS POS switch have to be

held down until LED’s arrive at the desired position?

A

 No

96
Q
  1. Does the ALT FLAPS POS switch have to be

held down until the TE flaps arrive at the desired position?

A

 Yes

97
Q
  1. Does the ALT FLAPS POS switch have to be

held in the up position?

A

 No (magnetically held UP)

98
Q
  1. What is the alternate flap duty cycle time for

flap positions 1 to 15?

A

 5 Minutes off

99
Q
  1. What is the alternate flap duty cycle time for

flap positions greater than 15?

A

 25 Minutes off

100
Q
  1. What would the illumination of the FEEL

DIFF Pressure light indicate?

A

 Excessive pressure differential

101
Q
  1. Which hydraulic systems send signals to

the Elevator Feel Computer?

A

 A and B Systems

102
Q
  1. Would the illumination of the FEEL DIFF

Pressure light mean that a hydraulic system has failed?

A

 Possibly

103
Q
  1. Could a problem with the elevator feel pitot

tube cause FEEL DIFF Pressure light to illuminate?

A

 Yes

104
Q
  1. What would the Speed Trim Fail light

mean?

A

 System failure (both channels)

105
Q
  1. What if the Speed Trim Fail light did not illuminate until recall?
A

 Single channel failure

106
Q
  1. If the Speed Trim Fail light illuminated

during recall, could it be reset?

A

 Yes

107
Q
  1. What is the purpose of the Speed Trim?
A

 To return the airplane to a trimmed speed condition

108
Q
  1. What are some of the conditions for Speed Trim operation?
A

 Airspeed between 100 KIAS and MACH 0.5, 10 sec after takeoff; 5 sec following release of trim switches
 Autopilot not engaged
 Sensing of trim requirements

109
Q
  1. What does the Speed Trim system trim?
A

 The stabilizer

110
Q 
110. What is the purpose of the Elevator Feel
Shift Module (EFS)?
A

 Along with the speed trim and yaw damper help identify and prevent further movement into a stall condition

111
Q
  1. How does it prevent further movement?
A

 Increases forward control column force to

approx four times normal feel pressure

112
Q
  1. What would the MACH TRIM FAIL light mean?
A

 System failure (both computers)

113
Q
  1. What if the MACH TRIM FAIL light

illuminated only during recall?

A

 Single channel failure

114
Q
  1. If the MACH TRIM FAIL light illuminated

during recall, could it be reset?

A

 Yes

115
Q
  1. When is mach trim automatically

accomplished?

A

 Above .615 MACH

116
Q
  1. With failure of the mach trim system, what

is your speed restriction?

A

 280 KTS / .82 MACH

117
Q
  1. What does the Mach Trim system trim?
A

 The elevators

118
Q
  1. What is the purpose of the Mach Trim

System?

A

 Provides speed stability at higher MACH numbers (by preventing mach tuck)

119
Q
  1. What would the illumination of the AUTO SLAT FAIL light mean?
A

 System failure (both computers)

120
Q
  1. What if the AUTO SLAT FAIL light illuminated only during recall?
A

 Single SMYD channel failure

121
Q
  1. If the AUTO SLAT FAIL light illuminated only on recall, would it extinguish when recall was reset?
A

 Yes

122
Q
  1. If the AUTO SLAT FAIL light were ON,

would autoslats work?

A

 No

123
Q
  1. If the AUTO SLAT FAIL light were ON,

would autoslats work with PTU power?

A

 No

124
Q
  1. What does the SPEED BRAKE DO NOT

ARM light mean?

A

 Abnormal condition or test inputs to automatic speed brake system

125
Q
  1. What does the SPEED BRAKE ARMED light mean?
A

 A valid automatic speed brake system input

126
Q
  1. When is the STAB OUT OF TRIM light armed?
A

 (A / Pops) Auto-pilot engaged

127
Q
  1. What does the STAB OUT OF TRIM light

mean?

A

 Auto-pilot is not trimming stabilizer properly (may be on momentarily with large power or configuration changes)

128
Q
  1. What does the YAW DAMPER indicator display?
A

 Yaw damper movement of the rudder

129
Q
  1. Does the YAW DAMPER indicator display

rudder pedal input?

A

 No

130
Q
  1. What can be determined from the Trailing

Edge (TE) Flap indicator?

A

 Flap position, Asymmetry or skew condition

131
Q
  1. What electrical power is needed for the flap position indicator?
A

 28V AC (transferbus #2)

132
Q
  1. How would you be able to determine an

asymmetry condition?

A

 A split needle of the TE Flap indicator

133
Q
  1. What does the illumination of the LE

FLAPS TRANSIT light indicate?

A 
 Any LED in transit
 Any LED not in programmed position
 Slat skew or asymmetry (inboard 3 only)
 During alternate flap extension until
reaching TE flaps 10
134
Q
  1. Does the LE FLAPS TRANSIT light work during autoslat extension?
A

 No HIGHER POWER AVIATION

135
Q
  1. What causes the LE FLAPS EXT light to illuminate?
A

 All LED’s extended (full ext with flaps 10 thru40 )

136
Q
  1. What other indicator can you use to determine position of the LED’s?
A

 LED annunciator panel

137
Q
  1. What is indicated by the illumination of the

SPEED BRAKES EXT light?

A

 In flight: beyond armed and TE flaps >10, or RA < 800ft RA

138
Q
  1. Does the SPEED BRAKE LEVER have to be armed to get spoilers on an RTO?
A

 No

139
Q
  1. Why doesn’t the SPEED BRAKE LEVER

have to be armed during an RTO to get spoilers?

A

 During an RTO, auto speed brake system works when: Wheel Spin–up (60knots), reverse thrust is selected

140
Q
  1. Does the SPEED BRAKE LEVER have to be armed to get spoilers on landing?
A

 Yes

141
Q
  1. When does the SPEEDBRAKE system

operate on landing?

A

 Armed (light on); both throttles to idle; flight spoilers deploy: Wheel spin – up (60 knots); ground spoilers deploy: right main gear strut compresses RA < 10 ft (if wheel spin-up is not sensed, flight spoilers deploy on any gear compression, right main gets the ground spoilers)

142
Q
  1. In flight, what is controlled by the speed brake lever?
A

 Flight spoilers symmetrically

143
Q
  1. What are the cautions concerning the use

of the speedbrake lever in flight?

A

 Caution should be exercised in a turn since it greatly Increase roll rate
 Moving the Speed Brake lever past the flight detent causes buffeting and is prohibited in flight

144
Q
  1. What is the significance of the green band on the Stabilizer Trim Scale?
A

 Allowable range for takeoff

145
Q
  1. Why are gates on the Flap Lever

positioned at the 1 and 15 degree settings?

A

 Go-around flap settings

146
Q
  1. What do you have to do to get past the

gates on the Flap Lever?

A

 Push the handle down as you move it

147
Q
  1. What are normal landing flap settings?
A

 Flaps 30 and flaps 40

148
Q
  1. When the flap handle is at 5 degrees, where are the LED’s?
A

 Leading edge flaps: full extend

 Leading edge slats: extend

149
Q
  1. When the flap handle is at 15 degrees,

where are the LED’s?

A

 Leading edge flaps: full extend

 Leading edge slats: full extend

150
Q
  1. Does the flap handle move during autoslat operation
A

No

151
Q
  1. Does the flap handle move during flap

blowup operation?

A

 No

152
Q
  1. Should the flap lever be moved during

alternate flap operation?

A

 Yes, as called for in the checklist

153
Q
  1. What does the takeoff configuration

system monitor?

A 
 Parking Brake (if it is set)
 Trim (takeoff range)
 SpeedBrake (handle down detent)
 Spoilers (All boards down)
 Flaps (takeoff configuration)
 LE devices (not in takeoff configuration)
154
Q
  1. Can you cancel the takeoff configuration warning?
A

 No

155
Q
  1. When will you get a configuration

warning?

A

 On the ground and either or both thrust levers are advanced for takeoff

156
Q
  1. What is the purpose of the Stab Trim Cutout switches?
A

 Disconnect stab trim during a runaway

157
Q
  1. Which of the Stab Trim Cutout switches

will cause disengagement of the A/P if engaged?

A

 Stab trim A/P cutout

158
Q
  1. How is aileron trim accomplished?
A

 Electrically through aileron F&C Unit

159
Q
  1. Do the ailerons move when they are

trimmed?

A

 Yes

160
Q
  1. Can the autopilot trim the ailerons?
A

 No

161
Q
  1. Can you trim the ailerons with the autopilot

engaged?

A

 Yes, but you should NOT

162
Q
  1. Where is aileron trim indicated?
A

 Top of yoke

163
Q
  1. How is the rudder trim accomplished?
A

 Through the rudder feel & centering unit

164
Q
  1. Do the rudder pedals move when the rudder is trimmed?
A

 Yes

165
Q
  1. Can the autopilot trim the rudder?
A

 No

166
Q
  1. Does the rudder have trim tabs?
A

 No

167
Q
  1. Where is rudder trim indicated?
A

 Aft pedestal indicator

168
Q
  1. Can the rudder be trimmed with a loss of hydraulics?
A

 No

169
Q
  1. What is the purpose of the Stab Trim

Override switch?

A

 Bypasses the control column actuated stab trim cutout switches (under floor) to restore power to the stabilizer trim switches

170
Q
  1. Is the Stab Trim Override switch electrical or mechanical?
A

 Electrical

x. ORAL STUDY GUIDE - 737NG (18 decks)

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