auto flight system a300-600

A300-600 GROUND CONVERSION by Prapaipat T./BGFOR TG INTERNAL TRAINING ONLY

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A300-600 GROUND CONVERSION by Prapaipat T./BG

2

TOPICS

1. Introduction

2. Flight Augmentation Computer (FAC)

3. Thrust Control System

4. Auto Pilot and Flight Director (AP/FD)

5. AP/FD Vertical and Lateral guidance

FOR TG INTERNAL TRAINING ONLY





3

1. Introduction

AFS Energized

Electric power supply temporarily:

•When a/c power up, for computer self test

•When perform the annunciator light test






4

AFS computer redundancy

•Fail Operational capabilityFor precision approach, as soon as second AP engaged, if the active system fails, the second system takes over automatically

•Each computer consists of two independent processing channel (CMD and Monitor)

•Fail Passive capabilityIn case of disagreement between the two channels, the affected function or computer is disabled before it may affect A/C guidance






5

Main components and subsystems

THRUST

CONTROL

SYSTEM

TCC1 TCC2

ATS1 ATS2

TRP TRP

•Flight Control Computer (FCC)•Thrust Control Computer (TCC)•Flight Augmentation Computer (FAC)•Yaw Dampers•Pitch Trims






6

Pitch Trim

Yaw Damper

•Speed Parameters Computations

•Alpha Floor Protection

•Windshear Detection

FAC failure

1

2

3

4

2. Flight Augmentation Computer (FAC)

Flight Envelop Protection






7

FAC

•FAC is designed for yaw damping, pitch trimming, flight envelope protection and maneuvering speed computation

•FAC provides yaw command to the rudder, trim command to the horizontal stabilizer and all speed information signals to be displayed on PFD






8

Yaw Damper

A/C on ground

HYD. Available (B for 1,Y for 2)

A/C in flight

Yaw servomotor 1(2) o.k.

FAC 1(2) operative

ADC 1(2) operative

Power Supply available

Yaw damper Lever 1(2) On

IRS 1(2) and another one o.k.

Yaw Damper 1(2) engaged

Flaps> 15°






9

Yaw Damper






10

Turn Co-ordination

Engagement logic: AP not in CMD, flaps are not fully extended and no stall warning

Function active: If EFCU detects roll Control wheel deflection above threshold

AP assistance

Engagement logic: AP in CMD at SRS or GA mode

Function active: If IRS detects a lateral acceleration above threshold

Dutch roll damping

Engagement logic: Arming during the whole flight phase

Function active: If IRS detects a yaw rate

Yaw Damper- Block diagram






11

Yaw Damper






12

One Yaw Damper fails

Warning level 1Warning level 1Warning level 1






13

Both Yaw Damper fail







14

Pitch Trim

Pitch trim servomotor O.K.

FAC 1(2) operative

ADC1(2) operative


Pitch trim Lever 1(2) On

2 of 3 α- probes operative

Slats extended

Slats retracted

Pitch Trim 1(2) engaged

Pitch Trim 1(2) engaged






15

Pitch Trim

STALL TRIM

THETA TRIM






16

Pitch Trim control schematic

•Electric trim using either trim switches (rocking levers) on the control wheel.

•Manually by turning either trim wheel on the center pedestal.

•Automatically by AP (auto trim function), electric trim inputs are inhibited when AP-CMD is engaged.

•Automatically by FAC (AP-CWS, AP-off):

- Speed trim

- Alpha trim

- Stall trim

- Theta trim

THS can be commanded by






17

THS commanded by FAC

Speed trim and Mach trimActive: above 200 kt. and M 0.7 respectively

Available: with AP off, in CWS or in CMD

Action: nose up to optimize the longitudinal stability and handling qualities

Alpha trimActive: high AOA and high Mach number

Available: in clean configuration AP off or in CWS and speed brake lever is in the retracted position

Action: nose down to increase the pull-up stick force and prevent reaching an excessive AOA






18

Stall trimActive: high AOA and low speed

Available: with AP off and speed below 200 kt. - in S/F 15/0, 15/15, 15/20- in S/F 0/0 when above 300 ft. RA

Action: nose down to assist the stall recovery

Theta trimActive: at high pitch rate and low speed

Available: with AP off, pitch above 10° and speed below 180 kts./ M 0.37

Action: nose down to ease the control of the pitch rate and attitude and prevent pitch from exceeding 30° (specially during GA)

THS commanded by FAC






19

Pitch Trim






20


One Pitch Trim Fails






21


Both Pitch Trim Fail






22

Flight Envelope Protection

•Speed Parameters computations

•Alpha floor protection (THR L)

•Windshear detection






23

Speed Parameters Computations

Min speed for flap and slat retraction Drift-down speed






24

VLS VMAXVC Trend Vss

Speed Parameters Computations






25

•Alpha-floor function is active above 100 ft. provided ATS is armed.

•FAC detects a too high AOA it send the signal to TCC to engage in Thrust Latch (THR L).

Alpha-Floor Protection

AOA minimum value which causes THR L engaged depends on F/S lever position:

-7° in clean configuration

-12° in 15°/0 °, 15°/15° and 15°/20° configurations

-11° in 30°/40° configuration






26

If the aircraft AOA exceeds a given value, ATS thrust latch modeengages in order to automatically apply thrust limit (THR limit) as selected on the TRP to ATS (except THR mode is already engaged)

The activation of α-floor protection is not accompanied by an AP/FD nose down order(the engaged AP/FD vertical mode remains engaged with the associated pitch command)

Alpha-Floor Protection

1

2






27

Operation envelope

•T.O. & GA up to 1300 ft. and

•During approach from 1300 ft. to 50’ RA

- Control ALT. as long as airspeed is above VSS

- Control of airspeed (selected speed +10 kt.) as long as a positive v/s is maintained

- Control of speed above VSS as long as required

- During recovery Max pitch attitude target is 21.5° (instead of 17.5° in normal)

Survival Strategies

Wind shear warning






28

FAC parameters display






29

One FAC fails






30

One FAC fails






31

Engagement &Operation

Introduction:ATS&TCC

Auto Thrust (A/THR)

ATS Fail

1

2

3

4

3. Thrust Control System






32

Auto Throttle System

Thrust Limit Computation

Thrust Control System






33

•Thrust Control Computer-TCC receives air bleed discrete, TAT, Mach, speed and altitude from ADC, N1 actual and N1 command from the PMCs and mode selected from TRP.

Thrust Limit Computation

•Permanent calculation of the engine thrust limit depending on the mode selected on the TRP and the aircraft operating conditions.






34

•Acquires and maintains the speed or the Mach selected on the FCU or computed by the FMC (automatic speed control)

•Acquires and maintains the THR limit computed by TCC or the target thrust computed by the FMC (automatic thrust control)

•Moves the throttles back to the idle position

Auto Throttle System-ATS






35

TCC 1(2) operative

One FAC operative

One ADC* operative


ATS Lever 1(2)- on

ATS Engagement Logic

*normally ADC1 is used

- Auto Thrust (A/THR)- Thrust Latch (THR L)- Auto Thrust (A/THR)- Thrust Latch (THR L)






36

ATS armed A/THR engaged

ATS-Operation






37

AP/FDAcquires/MaintainsMode

•LVL/CH descent until the levers reach the idle position

•In FLARE mode•In P.DES mode

Retards the throttles levers to idle (5° TLA.)

Retard(RETARD)

•V/S, ALT, GS or LAND mode•P.SPD engaged with AP/FD P.ALT•AP/FD off A/THR can engaged in SPD/MACH mode only

•The speed or Mach target selected on FCU, or•The target speed or Mach number computed by FMS

Speed/Mach(SPD/MACH, P.SPD)

•SRS, LVL/CH (climb), and•Go Around modes•P.THR engages with AP/FD P.CLB and initial phase of P.DES

•The thrust limit selected on TRP, or•Flex TO. Target thrust, or•The target thrust computed by FMS

Thrust(THR,P.THR)

A/THR Modes






38

THR L acquires and maintains thrust limit selected on TRP.

Thrust Latch Mode-THR L

•α-floor protection is activated, or•The go lever are triggered in flight with slats retracted

Engagement: ATS lever is armed, it automatically engaged if:

THR L engagement is inhibited if A/THR is in THR mode






39

ATS arming lever

ATS mode indicator

ATS-Controls and Indicators

A/THR p/b switch

ATS disconnect p/b






40

One ATS fails







41

Both ATS fail






42

Introduction: FCC&AP actuator

FD:Operation&Failure

AP:Operation, Modes &Failure

1

2

3

4. Auto Pilot and Flight Director (AP/FD)






43

AP Actuator

Primary flight controls schematic






44

FCU/FMS

CWS

CMD

AP Actuator

AP connection to Flight controls






45

FCU/FMS

AP Actuator

FCC Input

Flight Control Computer-FCC






46

ADCProvides:Mach, computed airspeed, Baro corrected Alt., Alt. standardFCC computes:cruise guidance mode (SPD/MACH, ALT, V/S, ALT*), Mach signal is used for adjustment of flight control law gains

FMCProvides:guidance orders in navigation and profile mode, FMC receives the FCU discrete arinc words (mode selected)

FACProvides:A/C configuration data, Vmin, Vmax and α-average for flight envelope protectionPriority:side 1 has priority and trim function has priority over yaw damper function

TCCReceives: Information for the automatic thrust function depending on AP/FD longitudinal mode engaged

FCC Input






47

FCUProvides: The selected references (air speed, mach, Alt., HDG, V/S)Receives: from FCC actual A/C parameters for display synchronization and discrete words for mode engagement confirmation

ThrottlesTO/GA levers selection of the takeoff or GA mode

Dialogue between FCC

Receives: from output data bus opposite FCC

Used for:

1. Mode or mode phase synchronization,

2. The monitoring channel for

- Transmissions of cruise mode guidance orders,

- Synchronization between the two processors

FCC Input






48

VOROwn VOR bearing and course when used VOR mode

ILSProvides:1.ILS own parameters are used in Land mode2.ILS opposite used for RWY heading

comparison in align phase of Land mode3.LOC Deviation and selected RWY heading

are used in takeoff and roll out mode forguidance on the RWY axis

Radio Altimeter (RA)Provides: radio height parameter for1.Adjustment of FCC flight control law gains

in Land mode and2.Conditions to determine Land track (400 ft.)

Flare (50 ft.) and Align (30 ft.) conditionsIRS

Provides: Attitudes, attitude rates, acceleration for basic loops and various mode

FCC Input






49

FCU/FMS

AP Actuator

M1 M2

AP Actuators

Green hydraulic for HYD servo motor:AP1

Yellow hydraulic for HYD servo motor:AP2

Control Linkages






50

FCU/FMSAP Actuator

YAW BAR

FCC Output






51

FD provides vertical and lateral guidance in manual flying and with AP-CWS, basic modes are V/S and HDG

FD1 FD1FD2 FD2

Flight Director-FD






52

FD-Engagement conditions

FD1

FD2FD2FD1






53

Takeoff• RWY mode guidance along runway centerline up to 30 ft.• Using LOC signal

Landing

•Flare mode passing 30 ft. guidance for alignment with RWY center line

•During Roll Out mode guidance to recover and keep RWY centerline

FD-Yaw Bar






54

FD1 FD1FD2 FD2

FD-Failure






55

FD1 FD1FD2 FD2

FD-Failure






56

FAC1(2) Operative

FCC1(2) Operative

ADC1(2) Operative

IRS1(2) and other IRS operative

FCU Operative

One Pitch Trim engaged

One Yaw damper engaged

Pitch, Roll, Yaw* actuators avail.

Hydraulic supply O.K.

Bank angle < 45°

A/C airborne at least 4 sec.*

Flight/Ground signal avail.

(* Conditions not necessary for CWS mode)

AP-Engagement logic






57

• THS is controlled by the electric trim/Auto trim(The electric trim has priority over the Auto trim)

• Manual flying through the FCC and the AP pitch and roll actuators

• In CWS the present A/C pitch attitude and bank angle are maintained

AP-Control Wheel Steering mode (CWS)

• Pitch: +25°/-10°

• Bank:

- 0°-5° Wing level

- 5°-30° Bank hold

- 30°-45° maintain 30°

The pitch attitude and bank angle limitation:

• α-trim protection is available in clean configuration






58

•If the associated FD is displayed, AP engages in the same modes as FD, no FD is displayed AP engages in basic modes (V/S and HDG).

•Only the Auto trim is available.

•In dual mode the selection of another vertical or lateral mode causes the disengagement of AP2, except below 400 ft. with LAND green on FMA

AP-Command modes (CMD)

•Flight control deflections (Pitch and Roll) are initially maintained then smoothly corrected to achieve the selected flight path.

•AP controls the rudder only when the slats are extended.

• Supervisory Control Wheel Operation• AP Actuator Override

Sub-functions of CMD modes are as follow:






59

•Enables the crews to manually assist AP in capturing LOC/GS or in capturing or tracking VOR radial

•Combines the orders and characteristics of CMD and CWS modes

CMD-Supervisory Control Wheel Operation

•CMD remains displayed on FMA






60

CMD-Actuator Override

•Roll and Yaw actuators can be overridden to allow the crew to regain manual control of the associated flight control surface

•AP roll and yaw actuator is overridden if a force greater than threshold is applied on the control wheel or rudder pedals

•During AP actuator is overridden, the actuator is declutched andmechanically controlled by the pilot

•Any attempt to override AP in pitch results in the automatic disengagement of AP






61

FCU

PFD

FD p/b

(Capt. Switching)

FD p/b

(F/O Switching)

FD/FPV selector sw. FD/FPV selector sw.

Controls and Indicators






62

FD roll bar

FD pitch bar

LOC deviation display

GS deviation display

AP/FD Displays






63

5. AP/FD Vertical and Lateral guidance5. AP/FD Vertical and Lateral guidance

Take Off mode (T/0)1

Vertical Speed mode (V/S)2

Level Change mode (LVL/CH)3

Altitude mode (ALT)

4 Profile mode (P.xxx)

5

6 Heading Hold mode (HDG)

Heading Select mode (HDG/S)

VOR mode (VOR)

7

Localizer mode (LOC)

8

Land mode

9

Go Around mode (GA)

10

11

Navigation mode (NAV)

12






64

Before T/O

Cockpit Preparation






65

Preset speed activation:

•After T/O, LVL/CH selection at acceleration altitude

•ALT mode is selected

•ALT* is engaged

•Speed <> Mach reach at cross over altitude






66

30 ft.

Available with FDs only or FDs and AP-CWS

Go lever triggered for T/O

Take Off mode (T/0)1






67

•FCU speed +10 kts., or

•Max value between speed on FCU or existing speed at the time of engine failure

T/0-Pitch mode

Speed Reference System (SRS)

Provide pitch bar as a reference for the pilot to adjust the A/C pitch attitude in order to obtain A/C takeoff speed:






68

HDG or HDG/S mode

HDG/S engages if previously selected and ILS/LOC frequency and course have not been selected

RWY mode

•Available if ILS/LOC frequency and course are selected and signal are valid

•A yaw bar replaces FD roll bar

•Automatically disengages at 30 ft. RA and HDG or NAV mode engages

T/0-Roll mode






69

AP/FD pitch mode which is recommended to use for step climb or descent ≤ 2000 ft.

30 ft.

Vertical Speed mode (V/S)2






70

Manual engagement:

1. Setting new altitude then

2. Pulling the V/S knob, and then

3. Setting the desired V/S

Automatic engagement:

•On ground at the AFS power up

•When FD on with no AP or no FD is displayed

•Disengaged vertical mode by pressing on p/bsecond time

•Changing to the new ALT which is beyond the capture range in ALT* engaged

•Land mode is deselected between GS* and LAND green on FCU

V/S Engagement






71

Manual disengagement:

Selecting another pitch mode

Automatic disengagement:

•ALT* mode engages,

•In approach with LAND mode arm on FCU, GS* or

•V/S mode reversion occurs

V/S Disengagement

V/S mode reversion:

•To maintain V/S the speed may:

- Decrease to VLS + 5 kt. in climb

- Increase to VMAX in descent

•If VLS + 5 kt. or VMAX is reached, an automatic reversion from V/S to LVL/CH mode occurs






72

30 ft.

•Recommend to use for step climb or descent exceeding 2000 ft.

•AP/FD maintains the selected target speed by adjusting pitch attitude and A/THR maintains the thrust limit or at idle

•LVL/CH engages only if the selected altitude and A/C present altitude differ ≥ 250 ft.

Level Change mode (LVL/CH)3






73

Manual engagement:

1.Selecting a new altitude, and

2.Pushing LVL/CH p/b or pulling the ALT SEL knob

Automatic engagement:

LVL/CH mode engages automatically due to V/S mode reversion

While in LVL/CH:

•The selected target altitude and speed/Mach can be changed at any time

•If the target speed/Mach is ≤ VLS or ≥ V MAX /M MO, the AFS maintains VLS or V MAX/M MO

LVL/CH Engagement






74


Selecting another pitch mode

LVL/CH Disengagement


•ALT* mode engages, or

•In approach with LAND mode arm on FCU, GS* or

•LVL/CH mode reversion occurs

LVL/CH mode reversion: in climb/descent

•Pushing illuminated LVL/CH p/b changes engaged mode to V/S

•Automatic reversion to V/S if no AP is engaged in CMD and the FD recovers after a temporarily loss






75

•Profile mode contains sub modes:

- AP/FD: P.CLB, P.ALT, P.DES

- A/THR: P.THR, P.SPD, RETARD

Profile mode (P.xxx)4

•Couples the FMS order to AP/FD in longitudinal axis and to A/THR

•Operation envelope is from the thrust reduction altitude to:

- GS* for precision approach,or

- FAF/Final Descent Point/1000 ft.AGL whichever is earlier for non-precision approach






76

Profile armed during Taxi

Go lever triggered for T.O.

Thrust reduction altitude

Profile modes transitions

In Profile mode:

• The speed range is between VLS and VMAX

• During climb target altitude is FCU altitude. Constraints may be missed this cause altitude constraints are deleted.






77

Reaching level off altitudeBefore TOD, target altitude selected

and ALT SEL pulled

Passing TOD

In descent at idle

Profile modes transitions

Profile mode is manually disengaged by pulling the SPD/MACH knob which results in a manual reversion from Managed modes to Selected modes:

- LVL/CH mode in climb/cruise

- ALT mode in level flight






78

30 ft.

Arming phase

Altitude hold phase

ALT capture phase

Altitude mode (ALT)5






79

Arming phase

Automatic arms if a climb or a descent mode is engaged and target altitude is set

1 ALT capture phase

Automatic engages:

•When A/C is in the capture range of the selected target alt.

•The capture range varies depending on A/C vertical speed

2

Altitude hold phase •ALT mode engages when the A/C reaches the selected altitude, or

•An immediate level-off by pressing ALT hold p/b AP/FD engages directly in ALT mode

3

ALT Engagement






80

•Automatic disengages in approach with LAND mode armed, when GS capture

•Manual disengaged by selecting another pitch mode, or

ALT Disengagement






81

Automatic engages:

•On ground at AFS power up,

•Any other lateral mode disengagement by pressing p/b a second time

•LAND is deselected, between LOC* and Land green of FCU

•Go Around mode engages

Heading Hold mode (HDG)6

Disengagement:

•Manual by select another roll mode

•Automatic at 30 ft. NAV armed for T/O, VOR* or LOC* on FMA






82

HDG/S mode acquires and maintains the selected heading on FCU

Heading Select mode (HDG/S)7

Push-Pull-Turn technique

Turn: the heading selector knob in the direction of the desire heading

(Blue index on ND heading scale)

Push: the heading selector knob to synchronize heading window on the present a/c heading in any roll mode except HDG/S

Pull: the heading selector knob to engage HDG/S mode






83

HDG/S mode acquires and maintains the selected heading on FCU

HDG/S Disengagement


Selecting another roll mode


VOR or LOC is captured

Manual reversion:

HDG/S reversion to HDG occurs if the crew pushes the HDG/S p/b a second time






84

NAV armed for takeoff

Navigation mode (NAV)8

Couples the FMS to AP/FD in lateral axis along the FMS lateral flight plan (F-PLN)

When NAV pb. is pressed:

- NAV engages if present a/c track is within 10 NM from active F-PLN

- NAV arms if a/c track is more than 10 NM from active F-PLN -






85

Operation envelope is from 30 ft. AGL at take off to:

- LOC* for ILS approach or a LOC-only approach

- MDA-MDH for other types of non-precision approaches

When a/c entries a flight plan discontinuity, NAV automatically switches to HDG and AP disconnects.

•NAV mode reversions:

-Manual:

-from NAV to HDG by pressing NAV pb.

-from NAV to HDG/S by using Push-Pull-Turn technique

-Automatic:

-from NAV to HDG if Go around

-from NAV to HDG if FMC associated to the engaged AP fails

*AP disengages, FD remains engaged in HDG mode

NAV mode transitions






86

30 ft.

•Arming phase (VOR blue)

•Capture phase (VOR* green)

•Tracking phase (VOR green)

VOR mode (VOR)9

Note: HDG/S mode must be used together with VOR or VOR-DME raw data






87

VOR arming

By pressing the V/L p/b in the following configuration,

provided VOR frequency/course are set on the onside

VOR control panel:

- Both FD are displayed, both NAV/ILS/VOR sw. are in VOR

- One AP in CMD, onside NAV/ILS/VOR sw. is in VOR

VOR Engagement






88

•VOR* and VOR modes, AP supervisory override function available

•Bank angle is limited at 25°at Norm or at 15° in 15 position

•Manual mode transition can be initiated by selecting another roll mode

Automatic engages when a/c is in the capture range of the VOR radial

VOR capture VOR tracking phase

Automatic engages when a/c reaches the selected VOR radial

VOR Engagement






89

•Arming phase (LOC blue)

•Capture phase (LOC* green)

•Tracking phase (LOC green)

Localizer mode (LOC)10

Manual armed

by pressing the V/L p/b provide ILS or LOC frequency and course have been set:

•If both FD are displayed at least one NAV/ILS/ VOR sw. must be in the ILS position, or

•If one AP in CMD, the onside VOR/NAV/ILS sw. must be in the ILS position






90

Automatic armed

When LAND p/b is pressed provided an ILS frequency and a course have been set

LOC Engagement






91

Capture phase

- Automatic engages when the A/C is in the capture range of the localizer beam

- AP supervisory override function is available

Tracking phase

Automatic engages when a/c reaches the LOC beam

LOC mode disengagement

Manual disengages: can be initiated by selecting another roll mode, or by pushing LAND p/bor selecting another pitch mode

Automatic disengages: when GA mode engages (using HDG mode)

LOC Engagement






92

LAND selected on FCU

LOC capture

Established on LOC beam

Land mode11






93

At 400 ft. RA

At 50 ft. RA(FLARE+ALIGN)

At 30 ft. RA

Land Engagement

At main landing gear touchdown






94

- Excessive LOC or GS beam deviation warning is activated, or

(beam deviation > 1/3 dot and 1 dot respectively),

- All AP’s disengage (AP- off warning), or

- RA1 and RA2 comparison is greater than 15 ft.

- Long flare duration

(A/C are not on ground within 15 secs. after passing 50 ft. RA)

light are flashing when a/c in Land mode, altitude < 200 ft.RA and if:

Land Disengagement

AUTO LAND






95

SRS+HDG

Engagement by triggering GO levers

•In flight GA engages if slats out

•Within 30 secs. after touchdown GA engages if Manual landing only

•More than 30 secs. After touchdown with slats extended T.O. modes activate and AP2 disengages

Mode transition

•A/C reaches go-around altitude, ALT* and HDG mode engage, or

•A manual mode transition occurs when another pitch or roll mode is engaged

Go Around mode (GA)12






96

A force greater than threshold value is applied

in pitch on control column

The pitch trim motion is stopped by holding the pitch

trim wheel

Manually disengaged by pressing the AP disconnect p/bor AP lever to OFF position

AP disengagement






97

AP disengagement






98

The End…The End…





auto flight system a300-600

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