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737 Systems > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

Describe roll control under normal conditions:

A
  • Capt’s control wheel connected by cables to aileron PCUs
  • F/O’s control wheel connected by cable to spoiler PCUs
  • Capt & F/O control wheels linked by cable drive system
  • Flight spoilers supplement ailerons at > 1.7 units control wheel movement
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2
Q

What happens if ailerons are jammed?

A
  • Ailerons and Capt’s control wheel inop
  • F/O uses spoilers for roll control

(If spoilers jammed, opposite occurs – Capt uses ailerons for roll control and F/O’s control wheel is inop – either way, a transfer mechanism allows use of unjammed controls by separating them from jammed controls)

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3
Q

What happens if a control column is jammed?

A

An override mechanism allows separation of columns to “break out” the unjammed control column

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4
Q

How are roll and pitch controlled with loss of both hydraulic systems?

A

Manual reversion (control cables assisted by balance tabs)

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5
Q

Describe the Mach Trim System:

A

Above Mach .615, the system automatically repositions the elevator feel + centering unit, which adjusts control column neutral position. This provides speed stability at higher Mach numbers.

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6
Q

What speed modes are available for main electric and autopilot stab trim?

A
  • Flaps retracted Low speed trim

* Flaps extended High speed trim

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7
Q

If the stabilizer is trimmed to the end of its electrical trim limits, is additional trim available?

A

Yes – use manual trim

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8
Q

What speed modes are available for main electric and autopilot stab trim?

A
  • Flaps retracted Low speed trim

* Flaps extended High speed trim

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9
Q

If the stabilizer is trimmed to the end of its electrical trim limits, is additional trim available?

A

Yes – use manual trim

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10
Q

What is the function of the control column actuated stabilizer trim cutout switches (not to be confused with pedestal-mounted STAB TRIM CUTOUT Switches or the STAB TRIM Override Switch)?

A

To stop stab trim operation when control column movement is opposite direction of trim movement

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11
Q

How can control column stab cutout trim switches be overridden (i.e. if trim stopped out of range)?

A

Place STAB TRIM Override Switch in OVRD

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12
Q

What is the function of the pedestal-mounted STAB TRIM CUTOUT Switches (MAIN ELECT and AUTOPILOT)?

A

To allow autopilot or main electric trim inputs to be disconnected from the stabilizer trim motor

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13
Q

Describe rudder control:

A
  • Rudder pedals connected by cable to main + standby rudder PCUs
  • Main rudder PCU powered by System A & B, but each system has its own input rod, control valve, and actuator.
  • Force Fight Monitor (FFM) detects opposing pressure (force fight) between A & B actuators. If a force fight occurs, the FFM automatically opens the Standby Rudder S/O Valve and turns on the Standby Pump. This illuminates the STBY RUD ON Light, M/C and FLT CONT System Annun Lights.
  • Standby rudder PCU powered by Standby Hydraulic System
  • Above 135K, System A and B pressure within rudder PCU reduced by 25% each
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14
Q

Describe rudder control:

A
  • Rudder pedals connected by cable to main + standby rudder PCUs
  • Main rudder PCU powered by System A & B, but each system has its own input rod, control valve, and actuator.
  • Force Fight Monitor (FFM) detects opposing pressure (force fight) between A & B actuators. If a force fight occurs, the FFM automatically opens the Standby Rudder S/O Valve and turns on the Standby Pump. This illuminates the STBY RUD ON Light, M/C and FLT CONT System Annun Lights.
  • Standby rudder PCU powered by Standby Hydraulic System
  • Above 135K, System A and B pressure within rudder PCU reduced by 25% each
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15
Q

When is hydraulic pressure to the rudder reduced?

A

Above 135K

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16
Q

When the YAW DAMPER Switch is placed ON, what happens?

A
  • Main YD engaged to main rudder PCU if FLT CONTROL B Switch ON.
  • Stby YD engaged to stby rudder PCU if FLT CONTROL A and B Switches in STBY RUD.
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17
Q

What is displayed by the YAW DAMPER Indicator on the main panel (installed only on 3AA-3FK)?

A

Main yaw damper movement of the rudder

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18
Q

What happens to the yaw damper if System B (its normal power source) fails?

A

YAW DAMPER Switch remains ON (w/ YAW DAMPER Light not illuminated), but no yaw damper is available (main or stby). However, if both System A and B lost, Standby System can power standby yaw damper (if YAW DAMPER Switch ON).

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19
Q

When the YAW DAMPER Switch is placed ON, what happens?

A
  • Main YD engaged to main rudder PCU if FLT CONTROL B Switch ON.
  • Stby YD engaged to stby rudder PCU if FLT CONTROL A and B Switches in STBY RUD.
20
Q

What happens to the yaw damper if System B (its normal power source) fails?

A

YAW DAMPER Switch remains ON (w/ YAW DAMPER Light not illuminated), but no yaw damper is available (main or stby). However, if both System A and B lost, Standby System can power standby yaw damper (if YAW DAMPER Switch ON).

21
Q

What happens if a rudder pedal cable breaks?

A

You can use rudder trim to move the rudder

22
Q

What happens if the rudder pedals jam?

A

Rudder is unavailable

23
Q

What is indicated by an OFF Flag on the Rudder Trim Indicator?

A

The indicator is inoperative

24
Q

With autopilot engaged, is it permissible to operate rudder trim? Aileron trim?

A

Rudder trim — yes

Aileron trim — no

25
Q

What is indicated by the FEEL DIFF PRESS Light?

A

Excessive difference sensed by elevator feel computer, possibly due to:
• Difference in pressure between elevator pitot tubes
• Difference between System A and System B output pressures
• Erroneous activation of elevator feel shift module

26
Q

When do slats move from “extend” to “full extend” position?

A
  • FLAP Lever moved to 10° or beyond (3LC> 30° or beyond), or
  • Autoslats function if approaching stall with Flaps 1°/2°/5° (3LC> 1°/2°/5°/10°/15°/ 25°)(Slats return to “extend” position when pitch angle sufficiently reduced)
27
Q

Describe function of flap load relief:

A

• Flaps automatically retract to previous position if VFE exceeded by 1 knot. Flaps automatically re-extend at 4 knots below VFE.
• Example: Flaps 40° (VFE 162K)
@ 163K, flaps retract to 30°, @ 158K, flaps re-extend to 40°
• Functions only with flaps at 30°/40° (3LC> 10°/15°/25°/30°/40°)

28
Q

Describe function of flap load relief:

A

• Flaps automatically retract to previous position if VFE exceeded by 1 knot. Flaps automatically re-extend at 4 knots below VFE.
• Example: Flaps 40° (VFE 162K)
@ 163K, flaps retract to 30°, @ 158K, flaps re-extend to 40°
• Functions only with flaps at 30°/40° (3LC> 10°/15°/25°/30°/40°)

29
Q

Which leading edge devices have skew detection?

A

3 inner slats on each wing (the outboard slats and LE flaps are not monitored)

30
Q

Is slat skew protection available during autoslat operation?

31
Q

Is asymmetry/skew protection available using the alternate extension system?

32
Q

What happens when the ALTERNATE FLAPS Master Switch is placed in ARM?

A
  • Closes TE Flap Bypass Valve
  • Activates Standby Pump (allowing Stby Sys to power LEDs & reversers)
  • Arms ALTERNATE FLAPS Position Switch
33
Q

What happens when the ALTERNATE FLAPS Master Switch is placed in ARM?

A
  • Closes TE Flap Bypass Valve
  • Activates Standby Pump (allowing Stby Sys to power LEDs & reversers)
  • Arms ALTERNATE FLAPS Position Switch
34
Q

What happens if Flap/Slat Electronic Unit (FSEU) detects TE asymmetry or skew?

A
  • Closes TE Flap Bypass Valve

* Displays needle split

35
Q

What happens if Flap/Slat Electronic Unit (FSEU) detects TE uncommanded motion?

A
  • Closes TE Flap Bypass Valve

* No needle split, but needle position disagrees with FLAP Lever

36
Q

What happens if Flap/Slat Electronic Unit (FSEU) detects LE improper position or LE slat skew?

A

• LE FLAPS TRANSIT Light illuminated with LE DEVICES annunciator panel displaying an amber TRANSIT Light, an incorrect green EXT or FULL EXT Light, or no light illuminated.

37
Q

What happens if Flap/Slat Electronic Unit (FSEU) detects LE uncommanded motion?

A
  • Shuts down LE control

* LE FLAPS TRANSIT Light illuminated

38
Q

SPEED TRIM FAIL Light

A

Failure of the Speed Trim System

If light activated by M/C Recall, it indicates failure of a single FCC channel of the related system

39
Q

MACH TRIM FAIL Light

A

Failure of the Mach Trim System

If light activated by M/C Recall, it indicates failure of a single FCC channel of the related system

40
Q

AUTO SLAT FAIL Light

A

Failure of the auto slat system

If light activated by M/C Recall, it indicates failure of a single SMYD computer

41
Q

AUTO SLAT FAIL Light

A

Failure of the auto slat system

If light activated by M/C Recall, it indicates failure of a single SMYD computer

42
Q

SPEEDBRAKES EXTENDED Light

A

In flight – SPEED BRAKE Lever beyond ARMED w/ TE flaps > 10° or RA

43
Q

SPEED BRAKE DO NOT ARM Light

A

3AA-3CL
• Abnormal condition of Speed Brake LAS (Flaps UP)
3CM>

• Abnormal condition of auto speed brake system Note: Light deactivated with SPEED BRAKE Lever DOWN

All aircraft
•

44
Q

What is required for Automatic Speed Brakes to deploy?

A

RTO or landing with SPEED BRAKE Lever DOWN
• Main wheels spin up (> 60K), and
• Reverse thrust levers raised

Landing with SPEED BRAKE Lever ARMED and SPEED BRAKE ARMED Light on
• Thrust levers IDLE, and
• RA 60K) or
• Strut compression (any for flight spoilers, R MLG strut required for ground spoilers)

45
Q

What is required for Automatic Speed Brakes to deploy?

A

RTO or landing with SPEED BRAKE Lever DOWN
• Main wheels spin up (> 60K), and
• Reverse thrust levers raised

Landing with SPEED BRAKE Lever ARMED and SPEED BRAKE ARMED Light on
• Thrust levers IDLE, and
• RA 60K) or
• Strut compression (any for flight spoilers, R MLG strut required for ground spoilers)

46
Q

What is the function of the Speed Brake Load Alleviation System?

A

Limits speed brake deployment under certain high gross weight/airspeed combinations.

50% detent - Maximum SPEED BRAKE Lever position when LAS activates

737 Systems (12 decks)

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