FLIGHT CONTROLS Flashcards
(92 cards)
1
Q
What inhibits speedbrake extension?
A
Speedbrake extension is inhibited if one of the following occurs: SEC1 and SEC3 both are faulty, or an elevator (L or R) is faulty, or angle-of-attack protection is active, or flaps are in configuration FULL, or thrust levers are above MCT position, or Alpha Floor is activated.
2
Q
w.r.t speed brake extension, What happens if SEC1 and SEC3 are both faulty?
A
Speedbrake extension is inhibited.
3
Q
w.r.t speed brake extension, What is the effect of a faulty elevator on speedbrake extension?
A
If either elevator (L or R) is faulty, speedbrake extension is inhibited.
4
Q
How does angle-of-attack protection affect speedbrake extension?
A
If angle-of-attack protection is active, speedbrake extension is inhibited.
5
Q
What flap configuration inhibits speedbrake extension?
A
If flaps are in configuration FULL, speedbrake extension is inhibited.
6
Q
w.r.t speed brake extension, What is the impact of thrust levers being above MCT position?
A
If thrust levers are above MCT position, speedbrake extension is inhibited.
7
Q
w.r.t speed brake extension, What occurs when Alpha Floor is activated?
A
If Alpha Floor is activated, speedbrake extension is inhibited.
8
Q
What is the maximum speedbrake deflection in manual flight for spoilers 3 and 4?
A
40 ° (reduced to 25 ° in CONF 0 when GW > MLW + 2 t)
GW = Gross Weight, MLW = Maximum Landing Weight
9
Q
What is the maximum speedbrake deflection in manual flight for spoiler 2?
A
20 ° (reduced to 12.5 ° in CONF 0 when GW > MLW + 2 t)
GW = Gross Weight, MLW = Maximum Landing Weight
10
Q
What is the maximum speedbrake deflection with the autopilot engaged for spoilers 3 and 4?
A
25 °
11
Q
What is the maximum speedbrake deflection with the autopilot engaged for spoiler 2?
A
12.5 °
12
Q
What is the maximum deflection of the ailerons?
A
The maximum deflection of the ailerons is 25 °.
13
Q
What happens to the ailerons when the flaps are extended?
A
The ailerons extend 5 ° down when the flaps are extended (aileron droop).
14
Q
What is the maximum deflection of the ROLL spoilers?
A
The maximum deflection of the spoilers is 35 °.
15
Q
What is the maximum elevator deflection?
A
The maximum elevator deflection is 30 ° nose up, and 17 ° nose down.
16
Q
What is the maximum THS deflection?
A
The maximum THS deflection is 13.5 ° nose up, and 4 ° nose down.
17
Q
When do ground spoilers retract after landing?
A
Ground spoilers retract after landing when they are disarmed.
18
Q
When do ground spoilers retract after a rejected takeoff?
A
Ground spoilers retract after a rejected takeoff when they are disarmed.
19
Q
When do ground spoilers retract during a touch and go?
A
Ground spoilers retract during a touch and go when at least one thrust lever is advanced above 20 °.
20
Q
What do ELACs compute regarding yaw orders?
A
The ELACs compute yaw orders for coordinating turns and damping yaw oscillations and send them to FAC
21
Q
What do ELACs do with the computed yaw orders? wHICH COMPUTER DO THEY SEND IT TO ?
A
They transmit the yaw orders to the FACs.
22
Q
Which computer computes the rudder trim orders . ELAC or SEC or FMGC?
A
The FMGC computes the rudder trim orders.
23
Q
Are the rudder trim rotary switch and the rudder trim reset pushbutton active with the autopilot engaged?
A
No, they are not active.
24
Q
What is the purpose of protections in flight control law?
A
Protections are intended to reduce the risks of overcontrolling or overstressing the aircraft.
25
How do protections in flight control laws assist the Pilot Flying (PF)?
Protections provide the PF with an instinctive and immediate procedure to ensure that the PF achieves the best possible result.
26
Rotation mode has which protections from normal law?
Pitch attitude protection &
High angle of attack protection
27
Flare mode has which protections from normal law?
High angle of attack protection
28
When does the rotation mode activate during takeoff roll ?
AND When does it end?
2 seconds after 70 kts
It ends 10 seconds after liftoff and when pitch attitude is greater than 8 degree
29
Ground mode during takeoff, what happens to the maximum elevator deflection ?
During the takeoff roll, the system reduces the maximum up elevator deflection from 30° to 20°.
30
When does Automatic pitch trim freeze? Name the codnitions ( not limited)
-The flight crew enters a manual trim order
- The radio height is below 50 ft (100 ft with autopilot engaged)
- The load factor goes below 0.5 g
31
When is THS setting is limited?
When angle-of-attack protection is active, the THS setting is limited between the setting at the aircraft’s
entry into this protection and 3.5 ° nose down. (Neither the flight crew nor the system can apply
additional nose-up trim).
When the load factor is higher than 1.25 g or when the aircraft exceeds 33 ° of bank, the THS
setting is limited to values between the actual setting and 3.5 ° nose down.
When High Speed or High Mach Protection is active, the THS Setting is limited between the setting at
the aircraft’s entry into this protection and 11 ° nose-up.
32
With AP engaged, which protection of normal law is not avialable ?
With AP engaged , All protections of normal laws remain effective except pitch attitude protection
33
When the High AOA protection is activated, the normal law demand is modified and the sidestick input is.. ?
AOA demand
34
In Normal law how is roll control obtained?
Roll controls: aileron delfection is directly porportionaL to SS deflection with a maximum rateof 15 degree per seconds
35
What is the roll rate in normal law with AOA protection or pitch attitude protection active ?
In AOA protection and pitch attitude protection active the roll rate is reduced to 7.5 deg per scond ( from 15 deg per sec)
36
In flare mode , how is roll control obtained
Same as in flight mode
37
What happens if AOA protection or pitch attitude protection is active and full lateral deflection is maintained? w.r.t max bank angle
The bank angle will not go beyond 45 °.
38
What is the maximum bank angle if high speed protection is active and full lateral deflection is maintained?
The bank angle will not go beyond 40 °.
39
w.r.t to static spiral stability . What does the system do when high speed protection is operative?
It maintains positive spiral static stability from a bank angle of 0 °, returning to 0 ° when the sidestick is released.
40
What happensto auto trim if bank angle protection is active?
Auto trim is inoperative.
41
What happens to AP & FD if the bank angle exceeds 45 °?
The autopilot disconnects and the FD bars disappear.
42
When do the FD bars return after disappearing? (when bank angle was greater than 45)
When the bank angle decreases to less than 40 °.
43
Codntions for BEta target ?
44
WHat is the prupose of betar target ?
If one engine fails, the FAC modifies the sideslip indication slightly to show the pilot how much rudder
to use to get the best climb performance (**ailerons to neutral and spoilers retracted**).
zero the slip indication by applying the right amount of rudder
to get the best climb performance.
45
When is LAF active ? and functions of LAF ?
46
What is the rudder trim indication is cruise, staright and level , no fuel imbalance ,same thrust ?
the rudder trim should stay between 1 ° right and 2.3 ° left.
Note: This indication corresponds to a true rudder deflection within ± 1.5 °
47
Which failure the aircraft will go directly to direct law ?
IR 1 +2+3 fail
48
3 ADR fail , is it alternate law or direct law ?
ALternate law.
Only 3 IR failure is DCT LAW ( striaGHT away)
49
Which failure the aircraft reverts to direct law when flaps are set to CONF 2?
SEC 1 +2+3 fail
or
LGCIU 1+2 fail
50
In YAW ALTERNATE law , what is available ?
Only yaw damping ( damper authority limited to +- 5 degree)
There is no turn coordination
51
In alternate law , is there load factor limitation ?
Is there autotrim for pitch ?
Yes there is load factor limitation for pitch in alternate law
There is auto trim for pitch
52
Explain alternat law Pitch attitude limitation ( PAL)
The pitch attitude limitation is available in clean configuration only.
The flight control system introduces a gradual **decrease of sidestick authority**, *combined with a
**progressive pitch-down order***.
As a result, the pitch attitude is limited to approximately 20° at sea level and approximately 8° at max operating altitude.
This limitation does not protect the aircraft from stall.
53
Explain low sapeed stability ?
In artificial low speed stability replaces the normal angle-of-attack protection.
It is available for all slat/flap configurations, and the low speed stability is active from about 5 kt up to about 10 kt
above stall warning speed, depending on the aircraft’s gross weight and slat/flap configuration.
A gentle progressive **nose down signal is introduced,** that tends to keep the speed from falling
below these values.
The flight crew can override this demand
In addition, stall warnings (crickets + STALL synthetic voice message and STALL STALL
message on PFD) are activated at an appropriate margin from the stall condition.
The PFD speed scale is modified to show a black/red barber pole below the stall warning.
The α floor protection is inoperative.
54
Explain high speed stability ?
Above VMO or MMO, a nose up demand is introduced to avoid an excessive increase in speed.
The flight crew can override this demand.
In addition, the aural OVERSPEED alert (VMO + 4 or MMO + 0.006) remains available.
55
Explain bank angle protection in alternate law ?
No bank angle protection is provided. However, both PFDs display the BANK BANK message
and "BANK BANK" aural alert is triggered, when the bank angle exceeds 45 °. (NEO)
Note: The AP will disconnect, if speed exceeds VMO/MMO, or if the bank angle exceeds 45 °.
56
In dirfect law the SS & elevator is directly proportional , but what does this deflection have to do with CG?
DIRECT LAW:
In all configurations the maximum elevator deflection varies as a function of CG.
It is a compromise between adequate controllability with the CG forward, and not-too-sensitive
control with the CG aft.
57
DCT LAW , what does FMA show ?
USe man pitch trim
58
What is roll direct?
The roll direct law is a direct stick-to-surface-position relationship. System gains are set
automatically to correspond to slat/flap configuration.
With the aircraft in the clean configuration, the maximum roll rate is about 30 °/s.
With slats extended, it is about 25 °/s.
To limit roll rate, the roll direct law uses only ailerons and spoilers N° 4 and 5.
If spoiler N° 4 has failed, spoiler N° 3 replaces it.
If the ailerons have failed, all roll spoilers become active.
59
What is YAW MECHANICAL CONTROL
YAW MECHANICAL CONTROL
The pilot controls yaw with the rudder pedals.
The yaw damping and turn coordination functions are lost.
60
WHat is the purpose of abnormal atittude law?
If for any reason the aircraft goes far outside the normal flight envelope and reaches an extreme
attitude, the flight control law will be modified.
The abnormal attitude law will engage and will **provide the PF with maximum efficiency to recover
normal attitude.**
61
WHat mode in pitch, roll & yaw When the abnormal attitude law engages?
When the abnormal attitude law engages:
- The pitch alternate law with no protection is active (no load factor limitation)
- The roll direct law is active
- The yaw mechanical law is active
- Autotrim is not available. Therefore, USE MAN PITCH TRIM is displayed on the PFDs
- F/CTL DIRECT LAW is displayed on the ECAM
62
When the aircraft returns within the normal flight envelope, the abnormal attitude law disengages and which conditions remain for the remainder of the flight ?
When the aircraft returns within the normal flight envelope, the abnormal attitude law disengages and
the following conditions remain for the remainder of the flight:
- The pitch alternate law without reduced protection is active, Refer to DSC-27-20-20 Alternate Law
Without Reduced Protection
- The roll direct law is active
- The yaw alternate law is active
- F/CTL ALTN LAW is displayed on the ECAM.
63
WHat is the purpose of mechanical back up ?
to manage a temporary and total electrical loss, the temporary loss of five fly-by-wire computers, the
loss of both elevators, or the total loss of ailerons and spoilers.
64
How does the aircraft fly in pitch and roll in mechanical backup?
PITCH:
The pilot manually applies trim to the THS to control the aircraft in pitch.
The PFDs display “MAN PITCH TRIM ONLY” in red
LATERAL:
The pilot uses the rudder pedals as the mechanical backup to laterally control the aircraft
65
Rudder trim knob , how man deg per second ?
moves the neutral point of the artificial feel by the equivalent of one degree of rudder travel per second
66
RUD RESET pb, how many degree per second ?
By pushing the RESET pb, the zero trim position is ordered at 1.5 °/s.
67
RUD TRIM RESET Pb, when AP engaged , does it work ?
The RESET pb is not active, when the autopilot is engaged.
68
Does Crew action on the pitch trim wheel does not disconnect the ELACs?
Crew action on the pitch trim wheel does not disconnect the ELACs (micro-switches,
actuated by the override mechanism, ensure that the computers remain synchronized
with the manually-selected position).
69
What is The relationship between the aircraft CG and the THS setting shown on the trim wheel , in flight and on ground?
The relationship between the aircraft CG and the THS setting shown on the trim wheel is only applicable for takeoff. The limits of the THS
normal setting range for takeoff are indicated by a green band on the pitch trim wheel.
- In flight, when in direct law, the pilot uses the THS conventionally to fly in trim. In flight, the
aircraft pitch trim setting depends on aircraft CG, weight, altitude and speed. Consequently,
the relation between the aircraft CG, and the THS setting displayed on the pitch trim wheel,
does not apply in flight.
70
AFter touch down when does THS return to zero ?
Following nosewheel touchdown, as the pitch attitude becomes less than 2.5 ° for more than 5 s,
pitch trim is automatically reset to zero
71
WHen both pilot apply full deflection on their respective SS , what happens ?
The flight control laws limit the combined order to the equivalent of the full deflection of one
sidestick.
72
How can you deactivate the other sidestick and take full control?
A flight crewmember can deactivate the other sidestick and take full control, by pressing and
keeping pressed the sidestick pb.
To deactivate the other sidestick, the flight crewmember must press their sidestick pb for 40s.
The other sidestick is permanently deactivated, until any flight crewmember presses their
sidestick pb.
73
If one SS is deactivates on ground , how will you know ?
If one sidestick was deactivated on ground, the **CONFIG L(R) SIDESTICK FAULT **alert is
triggered at takeoff power application, or during the TO CONFIG test
74
Explain RED ARROW & Green CAPT or FO light on SIde sttick priority light (on glare shield)
Red arrow light : - comes on in front of the flight crew losing authority.
Sidestick priority audio : A “PRIORITY LEFT” or “PRIORITY RIGHT”
audio voice message is given each time priority is taken.
Green CAPT and F/O lights :
- Both lights flash when the flight crew move both sidesticks simultaneously and neither takes
priority.
When the flight crew has taken priority by pressing the takeover pushbutton and the other flight
crew's sidestick is not at neutral, the light in front of the flight crew with priority lights up. It goes
out when the other flight crew returns their stick to the neutral position.
75
How is spolier fault - EXTENDED shown on ECAM FLT CTL page?
∆ : Spoiler fault extended (amber)
76
How is spolier fault - retracted shown on ECAM FLT CTL page?
1 : Spoiler fault retracted (amber)
77
RUdder trim position is shown in whoch colour ( flt ctl page)
BLUE
78
MEMO : SPD BRK (amber) what does it mean ?
This memo appears in amber when the speedbrakes should be retracted
79
MEMO : SPD BRK (green) what does it mean ?
This memo appears in green when the speedbrakes are extended
80
When does WTB activate?
WTBs which activate in the case of an uncommanded movement of the surfaces, such as:
runaway, asymmetry or over speed. They cannot be released in flight.
They use blue and green
hydraulic power for the slats and for the right wing flaps, and blue and yellow hydraulic power for
the left wing flaps
81
What does POB do ?
The POB locks the transmission when the slat or flap surfaces have reached the selected position
or if hydraulic power fails
82
How many flaps lever positions are there ?
5
0, 1, 2, 3 and FULL
83
When does in Configuration 1 + F, the flaps retract to 0 °
automatically at 210 kt (before the airspeed
reaches VFE)
84
When does flap extend to flaps 10 automatically from CONF 1
When in configuration 1, the flaps extend to 10 ° automatically at 100 kt.
85
What is alpha speed lock ?
n inhibits slat retraction at high angles-of-attack and low speeds.
When the FLAPS lever is set to 0, the slats alpha/speed lock function activates and inhibits slats
retraction, if:
- The AOA is above 8.5 °, or
- The speed is less than 148 kt.
86
WHats is slat angle at CONF 1
and CONF 1+F
1. 18/0
2. 18/10
87
What is difference between CEO & NEO flaps angle on CONF full ?
CEO , CONF FULL : 27/35
NEO , CONF FULL 27/40
88
What are Holding flaps?
89
What are approach flaps
2 & 3 ( not 1, 1 is only for holding )
90
At GA , if pilot selectz CONF 1, what flaps setting does he get ?
CONF 1 or CONF 1+F
CON 1+F
91
What indication when WTB is active ?
“S (F) LOCKED” legend, appears in amber, in association with an ECAM caution, when the
wingtip brakes are applied, or when the system detects a non-alignment between two flaps.
92
WHat indication when slat alpha/speedlock function is active.
“A-LOCK” legend pulses in green
