AF3 MAYBE?? Flashcards
What flying controls have mechanical backup?
THS and Rudder
If one hydraulic system was to fail in the THS system, what would be the effect on the movement of the THS?
Due to the differential gearbox, the system moves with full torque at half speed.
How is Wing Tip Brake (WTB) conditions confirmed?
Detection by cross comparison of Asymmetry Position Pick-Off Unit (APPU) and Feedback Position Pick-off Unit (FPPU) signals. If any of these failures are detected by a Slat Flap Control Computer (SFCC) and confirmed by the second one, the WTBs are applied.
If a SFCC fails how is the Wing Tip Brake condition confirmed?
If an SFCC does not operate, the other SFCC receives a WTB-arm signal automatically. Thus, if the second SFCC subsequently detects a failure, a solenoid valve on each WTB is energized.
What conditions would cause the Wing Tip Brake (WTB) to operate?
Asymmetry, Runaway, Overspeed and Uncommanded movement
When does spoiler No1 operate?
Ground only
What are the 3 flight control laws?
Normal, Alternate and Direct Law
The Load Alleviation Function (LAF) is controlled by which flying control?
Ailerons
The aircraft has pre-set limitations and instructions called LAWS. What is their purpose?
Regardless of the pilots’ input, the computers will prevent excessive manoeuvres and make sure the safe envelope is not exceeded in pitch and roll axes. Normal law offers full protection.
In the event of simultaneous inputs on the side stick, what indications do the crew get?
In the event of simultaneous inputs on both side sticks the two green SIDE STICK PRIORITY lights, on the glareshield, come on and the “DUAL INPUT” voice message activates.
There are two servo controls for each aileron, for each elevator and for the yaw damping function. how do they interact?
In normal configuration, one servo control actuates the surface. It is called active servo control. The second, which follows the surface deflection, is in damping mode.
Which computer processes the aircraft flap and slats?
SFCC
Which computer processes the aircraft Yaw control?
FAC
Which computer processes the aircraft pitch and roll secondary controls?
SEC
Which computer processes the aircraft pitch and roll primary controls?
ELAC
Appling an extension selection to the flap / slat lever rotates the Command Sensor Unit (CSU), which issues a new position demand signal to each SFCC. how is the signal processed?
The position demand and the actual position from the Feedback Position Pick-off Unit (FPPU) are compared in the SFCC flap lanes. If the requested and actual positions are different, each lane generates command signals that are compared by the output module. If the command signals are in agreement, the output module generates drive commands for PCU valve block activation.
As the flap / slat moves closer to its target what stops overrun?
The degree of valve spool movement controls the rotation speed of
the motor. The position of the control valve spool is monitored by a
Linear Variable Differential Transducer (LVDT) mounted on one end
of the valve block. Closer to target the slower the movement.
How is rudder trim achieved?
The rudder trim is achieved by one or two electric motors at a time, each controlled by its associated FAC
How is Asymmetry defined?
Asymmetry is defined as a positional difference between the LH and RH APPUs. Asymmetry is usually due to a broken shaft between both APPUs. The asymmetry threshold is above 5° synchro positional difference between both APPUs.
If the SFCC confirms asymmetry, the WTB solenoid is energized, PCUs are de-energized and the flap drive system is stopped. How can this be reset?
A reset of the WTBs can be done on ground only via the Centralized
Fault Display System (CFDS) in the MCDU.
A side stick or an autopilot sends an electrical signal to the flight control computers for an aircraft manoeuvre. The computers use pre-set limitations and instructions called LAWS. Normal law is modified depending on the phase of flight it operates in?
1, Ground mode. Operates on the ground when the aircraft is electrically and hydraulically powered. There is a direct relationship between the side stick and the control surfaces.
2, Flight mode. Operates in the air after a gradual transition from ground mode just after lift-off. When the aircraft is in flight mode, the control surface deflection is not directly proportional to the side stick deflection.
3, Flare mode. Modifies the flight mode to give a conventional “feel” to the landing phase.
How is system redundancy built into the aileron servo control system?
In case of failure of one aileron servo control, the second one takes over and is controlled by the other ELAC. In this example, ELAC 1 still computes the orders and ELAC 2 is in slave mode.
