Flight Controls Flashcards
Which Hydraulic System(s) normally power the primary flight controls?
Redundant Systems A and B – either system can operate all the primary flight controls
(Sec 9.010 p 2)
The loss of Hydraulic Systems A and B will render which spoiler panels inoperative?
Loss of A and B will render all spoiler panels inoperative
Sec 9.010 p 3
How do ailerons and elevators operate with the loss of both Hydraulic Systems A and B?
With the loss of A and B ailerons and elevators are operated manually
(Sec 9.010 p 5)
What happens when the FLT CONTROL A switch is positioned to STBY RUD?
- Flight Control Shutoff Valve for system A closes
- A FLT CONTROL LOW PRESSURE, FLT CONT annunciator and MASTER CAUTION illuminate
- activates the Standby Hydraulic System
- opens the Standby Rudder Shutoff Valve
(Sec 9.010 p 5)
What powers the rudder during Manual Reversion?
Standby Hydraulic System
Sec 9.010 p 5
Which are the roll control surfaces and how are they powered?
Ailerons and Flight Spoilers
Hydraulically System A and B, cable drive system
(Sec 9.010 p 5)
What happens when a single AILERON trim switch is pushed?
Nothing, both must be pushed simultaneously to command trim changes
(Sec 9.010 p 7)
Why is aileron trim prohibited with the autopilot engaged?
Any aileron trim applied when the autopilot is engaged can result in an out of trim condition and an abrupt rolling movement when the autopilot is disconnected
(Sec 9.010 p 8)
How many degrees of control wheel displacement initiates spoiler deflection?
Approx 10 Deg (1.6 units)
Sec 9.010 p 8
Which Flight Control Switch(es) are used for maintenance purposes only?
The SPOILER switches are use for maintenance purposes only
Sec 9.010 p 9
With a jammed or restricted Spoiler System, how is roll controlled?
force applied to the captain’s control wheel actuates the Aileron Transfer Mechanism (117 lbs force) and provides roll control using the ailerons
(Sec 9.010 p 10)
With a jammed or restricted Aileron System, how is roll controlled?
force applied to the first officer’s control wheel actuates the Aileron Transfer Mechanism and provides roll with flight spoilers
(Sec 9.010 p 10)
What does an illuminated FEEL DIFF PRESS light (amber) indicate?
excessive differential pressure within the Elevator Feel Computer
(Sec 9.010 p 12)
How does actuating the Stabilizer Trim Switch on the control wheel affect autoflight?
automatically disengages the autopilot
Sec 9.010 p 16
What is the purpose of the STAB TRIM switch on the Aft Electronic Panel?
bypass the control column actuated Stabilizer Trim Cutout Switches
(Sec 9.010 p 17)
What does the green band of the STAB TRIM indicator on the Control Stand indicate?
Takeoff trim range
Sec 9.010 p 18
What does an illuminated SPEED TRIM FAIL light (amber), during Master Caution Recall, indicate?
- during Master Caution Recall indicates failure of a single FCC channel
- indicates failure of the Speed Trim function
(Sec 9.010 p 21)
Describe the functions of the Stall Management Yaw Damper (SMYD) computers.
SMYD provide outputs for all stall warnings including:
- Stick Shaker
- signals to the pitch limit indicator and airspeed displays, and
- the GPWS windshear detection and alert
(Sec 9.010 p 24)
Which light is armed by selecting FLT CONTROL A or B switch to STBY RUD?
STANDBY HYD LOW PRESSURE is armed
Sec 9.010 p 27
When does the Main Rudder Power Control Unit (PCU) limit full rudder authority?
Above approx 137 kts Main Rudder PCU reduces HYD pressure to rudder by approx 25% (takeoff and landing)
(Sec 9.010 p 29)
What does the Rudder Trim Control Switch do?
Adjusts the rudder neutral position
9.010 p 29
How do you activate the Standby Yaw Damper?
Reset Yaw Damper switch to ON after manual reversion
Sec 9.010 p 32
What are the positions of the Speed Brake Lever, and what are the limitations?
Down detent, Armed, Flight detent, UP
Sec 9.010 p 34
What does the SPEED BRAKE DO NOT ARM light (amber) indicate?
An abnormal condition or abnormal test inputs to the Automatic Speed Brake System
(Sec 9.010 p 35)
During landing, when do the ground spoilers deploy?
when the aircraft is on the ground with the Speed Brake Lever in UP with any or no control wheel input
(Sec 9.010 p 37)
What would cause the LE FLAPS TRANSIT light (amber) to illuminate?
- any LE device in transit
- any LE device not in programmed position with respect to TE flaps
- a LE uncommanded motion condition exists
- alternate flap extension until LE devices are fully extended and TE flaps reach 15
–inhibited during autoslat operation
(Sec 9.010 p 39)
What is the normal position of the LE flaps for each FLAP lever position?
UP: LE Flaps retracted
1-40 TE Flaps: LE Flaps full extend
(Sec 9.010 p 44)
When do the LE slats deploy to FULL EXTEND?
When TE flaps lever selected beyond 25, LE Slats move to FULL EXTEND
(Sec 9.010 p 44)
Which flap settings have load relief?
Flaps 10, 15, 25, 30 and 40
Sec 9.010 p 49
When and how do the auto slats operate?
With takeoff flaps selected (1-25), LE Slats are in the extend position, when aircraft approaches stall angle, the slats automatically drive to full extend prior to Stick Shaker activation and return when angle of attack is sufficiently reduced
(Sec 9.010 p 44)
What does an AUTO SLAT FAIL light (amber) illumination during Master Caution Recall indicate?
failure of a single Stall Management Yaw Damper (SMYD) computer
(Sec 9.010 p 45)
Which devices move when the Alternate Flaps switch is placed in the DOWN position? Up position? Which system(s) move these devices?
DOWN: LEDs fully extend (and cannot be retracted), TE flaps move as long as switch is held in DOWN position.
UP: TE Flaps can be retracted in the UP position
LEDs are moved by Standby Hydraulic System
TE Flaps are moved by electric motor that moves mechanical drive system
(Sec 9.010 p 52)
