Flight Controls Flashcards
Flight Controls subjects are
Fly by wire, Flight Control surfaces, slats and flaps, controls and indications, flight control computers FCC
Flt controls are ______________ controlled and ________________ actuated
Electrically / hydraulically
The THS Trimmable Horizontal Stabilizer is mechanically linked to
Cockpit controls should a temporary, complete loss of electrical power occur
The two hand wheels mechanically control
THS
There is no _________trim
Aileron
A/P , sidestick input F/CTL computes flight control surface actuators
________ FCC . 1 is capable of controlling the aircraft.
3 PRIM (Flight Control Primary Computers) actuate:
Normal, Alternate and Direct control laws; speedbrake and ground spoiler control; protection speed computation; rudder travel limit
2 SEC computers; flight control secondary computer (FCSC) actuate:
Direct control laws including yaw damper function; Rudder trim and rudder travel limit
3 PRIM / 2 SEC = 2 FCDC (Flight Control Data Concentrators) = acquire data signal = CMC
Central Maintenance Computer
If 1 computer is unable, another executes, except
Spoiler control
If all PRIM fail, each SEC becomes
Its master and controls its surfaces
Sidesticks become active when ________ power is available
Hydraulic
Simultaneous inputs by Captain and F/O are
Algebraically summed
After first engine is running, sidestick position
Indicator is on PFD
PFD = + combined sidestick order and > Max sidestick deflection
PFD = + combined sidestick order and > Max sidestick deflection
Two sidestick pb handgrip:
A/P disconnect/ sidestick priority pb ; ptt pb
If held for at least ____ seconds, the other sidestick is latched out and takeover pb can be released without losing priority
40
To reactivate sidestick,
Press takeover pb
Max elevator deflection
30º up 15 ºdown
Max THS deflection 14º up
2ºdown
Two electrically controlled hydraulic servojacks are fitted on each
Elevator
Servojacks 3 modes are
Active = electrically controlled; damping = follows surface; centering = hydraulica maintained in neutral position
Normal – 1 active and 1
Damping (some maneuvers can cause it active)
If active servojack fails, damped becomes
Active and dialed damping
If servojacks are not ___________/__________ controlled, switched to damping
Electrically / hydraulic
If ____ elevator servojacks not electrically controlled , automatically centering mode
4
Elevators by PRIM 1 – left and right elevators driven by
Green hydraulic jacks
If PRIM 1 fails, PRIM 2 assumes through
blue and yellow hydraulic jacks.
If PRIM 1 / PRIM 2 unavailable
Pitch control SEC 1 / PRIM 3 THS control
PRIM 1/2/3 fail
SEC elevator THS 0 (lost control)
Elevator indicator partially boxed amber if electrical failure detected by
PRIM
Blue or yellow hydraulic power available – mechanical control by
Cable of THS
If three PRIM fails, electrical control of
THS is lost
Ailerons max deflection
25º. Spoiler max deflection 35º.
Aileron droop =
Ailerons deflected when flaps extended
Each aileron servojack has two control modes
Active / damping
The system automatically selects Damping mode if _______ and _______ or ______ and _______ low pressure, or if respective computer fails
Green / yellow or blue and green
At high speed more than ____ kt in Conf 0 – outboard ailerons = 0 deflection
190
In A/P or in some failures, outboard ailerons up to ____ kt
300
If RAT only – outboard ailerons in
Damping – reduce hydraulic power consumption
Spoilers automatically retracted to
Zero if fault or loss of electrical control
Spoiler retains deflection at time of loss, or lesser deflection if aerodynamic forces push it if system
Loses hydraulic pressure
Roll control is achieved by ____ ailerons and ____ spoilers on each wing
Two / five
Yaw control on a single rudder surface, actuated by
3 independent hydraulic jacks (each by different hydraulic system)
Max rudder deflection is
+- 35º
PFTU
Pedal feel and trim unit
PRIM 1 = yaw damping and
Turn coordinator
No feedback to rudder pedals from
Yaw damping / turn coordination
In case of total electrical failure or loss of rudder control, flight control computers failure, Backup Control Module (BCM) controls
Yellow hydraulic jack or Blue (if yellow not available)
Rudder trim is
Manual flight
Rudder trim is ___/second in clean configuration
1º
Manual flight ____ authority of max rudder deflection ___ degrees
85% / 29
The BCM provides this amount of control of the rudder in case of total electrical failure:
Direct rudder command and yaw damping
The pilot can in manual flight apply rudder trim from the
RUD TRIM rotary sw on the pedestal: authority 85% of max rudder deflection limited to 29º
Spoiler max deflection 1 = 25º and 2 to 6=
30º
Speedbrakes inhibited if active
Maneuver load alleviation MLA; angle of attack protection; low speed stability; at least one thrust lever more than MCT; A.FLOOR
Speed brakes can be reset again___ sec after lever reset
5
Message SPEED BRK when speed brakes are extended
From 1,500 ft after takeoff until landing
Message SPEED BRK green / flashes amber
At least 1 engine idle; speed brakes extended during takeoff roll until reaching 1,500ft after takeoff
RTO > 72 kt spoilers armed – extend – idle / not armed
Extend at least 1 reverse other idle
GND SPLRS partially extend when reverse on at least
1 engine (other at idle) and 1 main gear compressed
The ground spoilers automatically extend during RTO >
72 kt
When speed brakes are selected, spoilers
1 to 6 are activated
Within_______________, which determine how aircraft flight control surfaces should be positioned
FCCs – control laws
Active Normal Law = all flight control surfaces function even after certain
FCC, hydraulic, electrical faults
Normal law protections:
Load factor limitation, pitch attitude, angle of attack, high speed, bank angle protections, and low energy warning, and also maneuver load alleviation
THS automatically set at ____degrees up until reset for required takeoff
4
Rotation maneuver in Direct Law with full
elevator authority
5 seconds blend ground mode in normal law – 5 seconds -
Flight mode
Normal law flight mode is a load factor demand law with
autotrim and full flight envelope protection.
Pitch normal law – sidestick neutral and wings level -
1 G
Sidestick forward – load factor – increases / aft – load factor -
Decreases
Pitch trim automatic
Manual / A/P
Frozen automatic pitch trim:
Manual trim order; radio altitude < 100ft for flare; load factor < 0.5 g; high speed protection
Normal turns – up to ___ degrees bank, don’t hold back for keeping altitude
33
Establish a turn ,
release to neutral
Flare mode =
Direct stick to elevator relationship, with some damping by load factor and pitch rate feedbacks
At 50 ft – slight pitch
Down – pilot moves sidestick rearwards to maintain constant path = reproduce conventional aircraft aerodynamic characteristics
Once the aircraft is flying the required trajectory, or flight path, the sidestick can e release to
Its neutral position, and the aircraft will maintain 1g
The flight mode changes to flare mode at
Landing when passing 100ft. Flare mode is a direct stick to elevator relationship
Pitch normal law protections:
Load factor limitations, pitch attitude, angle of attack, high speed, low energy warning
Pitch normal law – sidestick – load factor limitation-
F/CTL computes – slats + 2.5g to -1 g / extended +2.0g to 0g
ECAM – G LOAD - > 1.4g or
< 0.7g
Pitch attitude ___ up / ____ up low speed / ______ down
30º / 25º / 15º
Pitch limits on PFD =
Green – PFD declutter > 25º up < 13º down
PFD V(red) >
30ºup – PFD normal between 22ºup and 10ºdown
Low end of speed = alpha -
Max lift attained
Conventional aircraft = stick shaker / A330 normal law – alpha= alpha protection -
System switches the elevator control from normal mode to protective
Protection mode =
Angle of attack proportional to sidestick deflection
Alpha max =
Maximum angle of attack available normal law < theoretical maximum
In the range between alpha protection and alpha max, sidestick
Commands alpha directly. A/P disconnects if Alpha Protection is active
Alpha protection, alpha max and A.FLOOR vary according to
Weight and configuration
Alpha prot and alpha max = flight computer =
PRIM
A.FLOOR – PRIM – activated through
A/Thrust system
Fly lower alpha protection-
Sidestick rearwards (protection)
If sidestick released angle returns
To alpha protection and stays there
Critical angle – A.FLOOR by A/Thrust system. A/Thrust commands
TOGA regardeless of lever position
A/Thrust armed or off engages TOGA when
Angle> threashould in acceleration config; ground speed variation; difference G/S and IAS; sidestick > 14º pitch ; attitude >25º; AOA is active
Exit AOA protection if
Pushed > 8º fwd; pushed > 0º fwd at least 1 sec (alpha < angle max); neutral or pushed fwd (angle
Exit A.FLOOR
Message TOGA LK on FMA
To cancel TOGA LOCK, thrust lever
reduced to thrust required to press A/THR instinctive disconnect pb
PFD VLS , Vangle Prot
Top of amber and black; V angle max top of red
VMAX – automatic – AP off,
Pitch trim frozen and positive spiral static stability, so release sidestick, aircraft wings level
Vmax prot =
Bank limit from 67º to 45º
High speed protection symbol =
Green at VMO + 4kt
Between 2,000ft and 100ft SPEED,SPEED,SPEED computed by PRIM’s with inputs
Aircraft config, airspeed deceleration rate, flight path angle
