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737 Study > Flight Control Panel/landing gear lever > Flashcards

Flight Control Panel/landing gear lever Flashcards

0
Q

FLIGHT CONTROL PANEL

flight control switches
ON (guarded position)

A

Normal position

Opens flight control shutoff valve to

  • aileron
  • elevator
  • elevator feel
  • rudder
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1
Q

FLIGHT CONTROL PANEL

Flight control switches
OFF

A

Closes flight control shutoff valve

Corresponding hydraulic system pressure is isolated from

  • aileron
  • elevator
  • elevator feel
  • rudder

Yaw damper switch flips off when sys B switch is placed OFF

Illuminates respective:

  • LOW PRESSURE light
  • FEEL DIFF PRESS light
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2
Q

FLIGHT CONTROL PANEL

Flight control switches
STBY RUD

A

Closes flight control shutoff valve, isolating

  • aileron
  • elevator
  • elevator feel
  • rudder

Activates sby pump

  • low pressure light will blink, then extinguish when sby rudder SOV opens
  • pressurises sby rudder PCU

Illuminates STBY RUD ON light

Thrust reversers powered by sby hydraulics if necessary

Yaw damper can be re-engaged, activating sby yaw damper if both FLT CONTROL switches to SBY RUD

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3
Q

FLIGHT CONTROL PANEL

LOW PRESSURE lights (A and B (amber)

A

Low hydraulic pressure to corresponding flight control units
- <1300psi to elevator aileron & rudder

Extinguishes when FLT CONTROL switch moved to STBY RUD and sby rudder SOV opens
-light function changes to sby rud SOV position indicator

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4
Q

FLIGHT CONTROL PANEL

SPOILER switches (A and B)
ON/OFF
A

ON (guarded position)
-hyd pressure to flt spoilers locking them down

OFF
-closes A/B spoiler SOV cutting hyd pressure to A/B powered flight spoilers

-ground spoilers not affected

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5
Q

FLIGHT CONTROL PANEL

YAW DAMPER light (amber)

A

Yaw damper not engaged or inop

-losing B hyd pressure does not cause light to come on but aye damper is inop.

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6
Q

FLIGHT CONTROL PANEL

YAW DAMPER switch
OFF

A

Yaw damper disengaged. Light illuminated

Solenoid released to OFF

  • B FLT CONTROL switch OFF position
  • power interruption to #1 transfer bus >2 sec
  • yaw damper rate gyro or actuator fail
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7
Q

FLIGHT CONTROL PANEL

YAW DAMPER switch
ON

A

Primary yaw damper engaged if B FLT CONTROL switch is ON

engages sby yaw damper to sby rudder PCU if both A and B FLT CONTROL switches are in the sby rudder position

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8
Q

FLIGHT CONTROL PANEL

SBY HYD lights (amber)
LOW QUANTITY light

A

Always armed

Illuminates at approx 50%

Leak in sby system will empty sby system and take B sys to 72%

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9
Q

FLIGHT CONTROL PANEL

SBY HYD lights (amber)
LOW PRESSURE light

A

Armed with sby pump on or when automatic sby function activated

Indicates low output pressure of electric motor driven sby pump <1300psi

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10
Q

FLIGHT CONTROL PANEL

SBY HYD lights (amber)
STBY RUD ON light

A

Illuminated when sby rudder PCU is pressurised

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11
Q

FLIGHT CONTROL PANEL

ALTERNATE FLAPS switch
OFF (guarded)

A

Normal position

Closes LE sby SOV

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12
Q

FLIGHT CONTROL PANEL

ALTERNATE FLAPS switch
ARM

A

arms sby hydraulic LOW PRESSURE light

Starts sby pump

Arms alternate flaps control switch

TE flap bypass valve goes to bypass position to prevent hyd lock of the flap drive

Disables LE UCM (un-commanded) function

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13
Q

FLIGHT CONTROL PANEL

ALTERNATE FLAPS CONTROL switch
Limitations

A

Max 230kts to begin extension

Functions only when ALTERNATE FLAPS switch in ARM

Allow 15 seconds after releasing the position switch to avoid damage to the altn flaps motor clutch

After a complete extend/terrace cycle allow 5 mins for cooling before attempting another extension

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14
Q

FLIGHT CONTROL PANEL

ALTERNATE FLAPS control switch
DOWN

A

Momentarily

  • opens LE sby SOV
  • fully extends all LE devices using sby hydraulic pressure
  • 30sec LE flaps
  • 1min LE slats

Held down

  • extends TE flaps electrically
  • takes 2min 0°-15°
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15
Q

FLIGHT CONTROL PANEL

ALTERNATE FLAPS control switch
UP

A

Retracts TE flaps electrically

LE devices remain extended and cannot be retracted by the alternate flaps system

16
Q

FLIGHT CONTROL PANEL

FEEL DIFF PRESS light (amber)

A

Illuminates with a 25% difference in pressure in the elevator feel computer

Possibly lost A or B hydraulics or elevator feel pitot system may have failed

17
Q

FLIGHT CONTROL PANEL

SPEED TRIM FAIL light (amber)

A

Failure of both FCC (flight control computer) speed trim functions

Illuminates on recall
-failure of single FCC channel

18
Q

FLIGHT CONTROL PANEL

MACH TRIM FAIL light (amber)

A

Dual channel light- illuminated indicates failure of both Mach trim functions in FCC (flight control computer)

illuminates on recall
-single FCC channel fail

Both channels failed do not exceed 280kts/.82 Mach

19
Q

FLIGHT CONTROL PANEL

AUTO SLAT FAIL light (amber)

A

Dual channel

Illuminated indicates failure of both autoslat channels of SMYD (stall management yaw damper)

On recall
-single SMYD failure

20
Q

Mach Trim system description

A

Provides automatic positioning of the elevators as a function of Mach number.

Counteracts tuckunder (nose down at high speeds)

  • downwash behind wing decreases, increasing AOA of horizontal stabiliser
  • center of pressure moves aft as speed increases

System armed above M .615

Operates with or without autopilot

21
Q

Auto slat system description

A

Slats go from EXT to FULL EXT providing a additional lift at high angles of attack (near stall)

Retract from FULL EXT to EXT when angle of attack reduced

LE FLAP TRANSIT light inhibited with autoslat extend

Works only with flap 1, 2 or 5
SFP- F1-25

Uses hyd B system
-if pressure is low PTU provides pressure from A sys and fluid from B system

23
Q

LANDING GEAR LEVER

Landing gear lights (RED) are illuminated when?
PHOTO

A

LANDING GEAR LEVER

  • related landing gear is in disagreement with LANDING GEAR lever position (in transit or unsafe)
  • landing gear is not down and locked (with either or both thrust levers at idle, below 800ft)
24
Q

Speed trim system description

A
  • Improves flight characteristics during ops with low gross weight, aft CofG and high thrust with autopilot disengaged.
  • Commands stabilizer in direction opposite to the speed change to help return the aircraft to the trimmed speed.
  • Fully enabled between 100kts-M0.60 with fadeout to zero by M.068
  • Operates 10s after takeoff, 5 seconds following release of trim switches, A/P not engaged

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