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TR > 9 Flight Controls > Flashcards

9 Flight Controls Flashcards

1
Q

FLT CNTRL SWITCH OFF

A

closes flight control shutoff valve for isolation of hydraulic pressure to rudder, aileron, elevators

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2
Q

YAW DAMPER SWITCH
ON

A
  • engages main yaw damper to main rudder power control unit when B FLT CTRL switch is ON
  • engages STBY yaw damper to STBY rudder power control unit if BOTH A and B FLT CTRL switches are in STBY RUD
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3
Q

🟧 LOW QUANTITY
🟧 LOW PRESSURE

A
  • ALWAYS armed
  • armed only when STBY pump operation has been selected or automatic STBY function is actived
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4
Q

ALTERNATE FLAP SWITCH
ARMED

A

Closes TE flap bypass valve, activates STBY pump, and arms the ALTERNATE FLAPS position switch [allows stby system to power LE devices and thrust reversers]

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5
Q

🟧 FEEL DIFF PRESS
armed when:
illuminates:

A

A - TE flaps are up or down
I - excessive differential pressure in elevator fuel computer. [either HYD system or elevator Pitot system fails]

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6
Q

🟧 MACH/SPEED TRIM FAIL
illuminate when:

A
  • system failed, or
  • SINGLE FCC failure upon recall
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7
Q

🟧 AUTO SLAT FAIL

A
  • auto slat fail, or
  • SINGLE SMYD computer failed
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8
Q

🟧 SPEED BRAKE DO NOT ARM

A

upon landing speed below 60 KIAS En speed brake NOT down

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9
Q

🟧 SPEEDBRAKES EXTENDED
FLT
GND
not illuminate

A

F - SB beyond armed AND: TE flaps extended more than F10 OR radio altitude less than 800 feet.
G - speed brake DOWN detent and ground spoilers NOT stowed
N - with HYD A pressure below 750 PSI

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10
Q

FLAP LOAD RELIEF
- arms when:
- operation

A

A - Flaps 10 to 40
O - goes down 1 flap setting

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11
Q

🟧 LE FLAPS TRANSIT

A

uncommanded position OR 2 or more LE FLAPS or SLATS have moved away from commanded position

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12
Q

PRIMARY FLIGHT CONTROLS
Pitch
Roll
Yaw

A

P - 2 elevators + movable hor stab
R - 2 ailerons + 8 flight spoilers
Y - rudder effective from 40-60 knots

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13
Q

AILERONS
CPT
FO
interconnect

A

CPT control wheel connected by cables to aileron PCU
FO control wheel connected by cables to spoiler PCU
- interconnected by a cable drive system

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14
Q

when flight spoilers assist ailerons

A

excess of 10 degrees with respect of deflected control wheel

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15
Q

PITCH CONTROL/ELEVATOR
- horizontal stabilizer powered
- control column connection

A

H - Electrically powered stabilizer, controlled by trim
C - connected to elevator PCU which are powered by HYD A and B

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16
Q

Elevator feel system
- powered
- inputs

A

P - HYD A and B pressure
I - elevator pitot and stabilizer position

17
Q

MACH TRIM SYSTEM
- automatically accomplished:
- Operation

A

A - above Mach .615
O - FCC use date from ADIRU co compute MACH trim actuator. Actuator repositions elev feel and centering unit

18
Q

HORIZONTAL STABILIZER
- positioned by
- AP and main electric trim speeds
- Manual trim
- Trim authority

A

P - Single electric trim motor
A - High speed [flaps ext] and Low speed [flap retracted]
M - accomplished by cables, can trim beyond electrical limits
Trim authority:
- Main electric trim: Flaps extended: 0.05-14.5 Units, Flaps retracted: 3.95 - 14.5 Units
- Autopilot Trim: 0.05-14.5 Units
- Manual trim: -0.20 - 16.9 Units

19
Q

SPEED TRIM SYSTEM
- which situations:
- when operated:

A

Situations: high thrust, low gross weight, aft CG

Operation conditions:
- STS mach gain is fully enabled between 100 KIAS- .60 MACH with fadeout to 0 at .68M
- 10 seconds after T/O
- 5 seconds following release of trim switches
- AP NOT engaged
- sensing of trim required

20
Q

Stall Identification and control
- enhanced by:
- what happens with high AOA
- what will EFS increase
- when is this inhibited

A

E - by yaw damper, elevator feel shift and STS
W - SMYD reduces yaw damper commanded rudder movement
W - Increase HYD A pressure to elevator feel and centering unit during a stall (approximately doubles control column forces)
W - when a/c on the ground, radio altitude < 100’, AP engaged. with EFS active and descending below 100’ RA it remains active until AOA is reduced below approximately stick shaker threshold

21
Q

what will STS do when airspeed decreases towards stall speed

A

STS trims stabilizer NOSE DOWN and enable speed trim above stick shaker AOA: this will make sure the pilot must pull more aft column to stall the aircraft

22
Q

YAW CONTROL/RUDDER
- powered by
- speed > 135 KTS
- FFM operation

A

P - hydraulically powered rudder + digital yaw damper system: each set of rudder: mechanically connected by cables to input levers of the main and standby rudder PCU’s
S - both HYD A + B pressure are each reduced within the main PCU by approximately 25% each: this limits full rudder authority for T/O + LDG

F - Force Flight Monitor, detects opposing pressure between A + B actuators (when disconnected or jammed). Output is used to automatically turn on STBY HYD PUMP, open STBY rudder shutoff valve

23
Q

YAW CONTROL/ RUDDER
- Rudder trim operation
- SMYD provides:

A

R - electrically repositions the rudder + feel centering unit which adjusts the rudder neutral position.
S - provides yaw damper inputs to main rudder PCU OR STBY rudder PCU

24
Q

YAW CONTROL/RUDDER
- connection with PCU
- Standby PCU

A

C - 2 independent input rods, 2 individual control valves, 2 separate actuators [ 1 for HYD A, 1 for HYD B]
S - 1 separate input rods and control valve and powered by STBY hydraulic system

25
Q

YAW CONTROL/RUDDER
- Yaw damper controlled via
- yaw damper capability
- rudder pedal movement with yaw damper

A

Y - [MAIN + STBY yaw damper] controlled via SMYD computers: this receives input from both ADIRU’s , control wheels, yaw damper switch
Y - EITHER yaw damper is capable of: Dutch Roll prevention, Gust Damping, Turn Coordination
R - rudder pedals do not move during yaw damper operation

26
Q

SPEED BRAKE LEVER
- Lever stop feature
- electrical power lost
- AUTO function AFTER RTO or LDG

A

L - prevents speedbrake lever to extend beyond FLIGHT DETENT.
E - Lever stop removed and full SB lever movement
A - IF either thrust lever is advanced, the SPEED BRAKE lever automatically moves down defend and all spoilers retract

27
Q

AUTO SB SYSTEM
- Ground operation: AUTO SB system operates when:
- During NO FLAP landing

A

Operate when:
- SPEED BRAKE lever in armed position
- SPEED BRAKE armed light illuminated
- Radio altitude < 10 feet
- Landing gear strut compresses on touchdown [L or R]
- BOTH thrust levers restarted to IDLE
- MAIN landing gear wheels spin up (>60 KTS)

D - speed brake lever will NOT move beyond FLIGHT DETENT and spoilers will NOT fully extend

28
Q

SPEED BRAKE lever in DOWN position (LDG or RTO), the AUTO SPEED BRAKE SYSTEM will operate when:

A
  • Main LG wheel spins up (> 60 KTS)
  • BOTH thrust levers are retarted to IDLE
  • Reverse thrust levers are positioned for reverse thrust [SB will automatically move towards UP]
29
Q

TE DEVICES
- TE flap positions and purpose
- LE flaps/slats movement with LE flaps positions

A

TE FLAPS:
- F1-F15 provide increase lift
- F15-F40 provide increase lift + drag

Flap lever UP - F25
- LE flaps extend to full extend
- TE slats extend to extend position
F30-F40
- LE slats extend to FULL extended position

30
Q

Flap load relief protection system
- flap relief active
- when retract/extend
- MAX speed flaps
- max altitude flaps extended

A

protects TE flaps from excessive air loads. Function of FSEU (Flap Slat Electronic Unit) receives data from Left ADIRU
F - flap lever does not move, but the flap indicator shows flap retraction + re-extension

Flaps will retract to 1 flapsetting lower at MAX SPEED + 1 KTS
FLAPS will extend to 1 flaps setting at MAX SPEED -4 KTS

F1,F2,F5 - 250 KIAS
F10 - 210 KIAS
F15 - 200 KIAS
F25 - 190 KIAS
F30 - 175 KIAS
F40 - 162 KIAS

M - 20.000 feet

31
Q

TE Flaps operated ALTN

A

electrically by 2 alternate flap switches: NO asymmetry or Skew protection provided. The switch must be held down until flaps in desired position.

32
Q

LE FLAPS ALTN operation

A

alternate flap switch energizes the STBY pump (hydraulic): held momentarily in DOWN position FULLY extends the LE devices

33
Q
  • PSEU action upon detecting TE asymmetry OR skew condition
A
  • closes the TE flap bypass valve
  • Displays a needle split on flap position indicator
  • shows position of L + R wing TE flaps
  • It protects against roll by maintaining flap symmetry
34
Q

PSEU LEADING EDGE
- Uncommanded motion detected when NO TE flap position or autoslat is commanded and:

  • Action of PSEU:
A

EITHER:
- 2 LE flaps move on one wing
- 2 or more Slats move on one wing

  • Shuts down the LE control (and illuminates 🟧 LE FLAPS TRANSIT). In addition: the PSEU maintains pressure on the retract lines and depressurizes the extend and full extend lines (to prevent unwanted motion)
35
Q

PSEU TRAILING EDGE
- Uncommanded motion detected when NO FLAP LEVER or Flap Load Relief command is present and the TE flaps:

  • Action of PSEU:
A

EITHER
- move away from commanded position
- continue to move after reaching a commanded position
- move In a direction opposite to that commanded

  • shuts down the TE drive unit by closing the TE flap bypass valve. Shutdown can’t be reset: FCM must use ALTN flaps

TR (18 decks)

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