A330 Flight Deck and Systems Briefing

AIRBUS
A330
Flight deck and systems
briefing for pilots
THIS BROCHURE IS PROVIDED
FOR INFORMATION PURPOSES ONLY
AND ITS CONTENTS
WILL NOT BE UPDATED.
IT MUST NOT BE USED AS AN OFFICIAL REFERENCE.
FOR TECHNICAL DATA OR OPERATIONAL PROCEDURES,

PLEASE REFER TO THE
RELEVANT AIRBUS DOCUMENTATION
STL 472.755/92 issue 4 March 1999

STL 472.755/92 Issue 4
STL 472.755/92 Issue 4
Contents
1. General
2. Flight deck layout
3. Electrical system
4. Hydraulic system
5. Flight controls
6. Landing gear
7. Fuel system
8. Engine controls
9. Auxiliary power unit
10. Automatic flight system
11. Environmental control system
12. Electronic instrument system
13. Radio management and communication
14. Central Maintenance System.
STL 472.755/92 Issue 4

STL 472.755/92 Issue 4
1. General
STL 472.755/92 Issue 4 1.1

A330 General
A330 general arrangement Typical cabin layout
58.37 m A330-200 256 seats
A330-200 191ft 3in
9.37m
30ft 9in
18 sleeperette 42 Business 196 Economy

(62 in pitch) (40 in pitch) (32 in pitch)
10.7m A330-300 295 seats

35ft 1.3in 60.304m
198ft
58ft 5in
17.8m
6.67m 22.18m 18 sleeperette 49 Business 228 Economy
21ft 11in 72ft 9in
(62 in pitch) (40 in pitch) (32 in pitch)
A330 fuselage cross-section

208.2in
5.287m
63.66 m
A330-300 208ft 10in
Passenger cabin
9.37m 65.7in 91.7in
30ft 9in 1.67m 2.33m z True widebody
spaciousness and
adaptability
10.7m Lower cargo holds

35ft 1.3in 60.304m
198ft 67in
LD-3s 1.702m z Large, efficient, fully
55ft 2.5in
16.828m
compatible with existing

worldwide air cargo
6.67m 25.58 m
125in system
21ft 11in 83ft 11in
3.18m 222in
5.64m
STL 472.755/92 Issue 4 1.2

A330 General
Introduction Basic data
• The medium to long-range A330 is an all-new, wide-
body, twin-engine, twin-aisle aircraft.
A330-200 A330-300
• The design combines high technology developed for

the A320 and A340 with the wide experience gained MTOW* 230 000 kg 217 000 kg
MLW 180 000 kg 179 000 kg
from the A300 and A310 aircraft currently in world-
MZFW 168 000 kg 169 000 kg
wide service.
As with the A319, A320, A321 and A340, it will Max fuel capacity 139 090 lit 97 170lit
incorporate all of the following features : 41 100 ft
Max operating 41 100 ft
- two-man crew operation with CRT displays altitude
- electrically signalled flight controls Powerplants GE CF6-80E1A4 GE CF6-80E1A2
- sidestick controllers 70 000 lb 67 500 lb
- full authority digital engine control (FADEC)
RR Trent 772 RR Trent 768 / 772
- centralized maintenance system. 71 100 lb 67 500 lb / 71 100 lb
PW 4168 PW 4164 / 4168

• Since it’s introduction in December 1993 the aircraft is 68 000 lb 64 000 lb / 68 000 lb
the most advanced medium to long-range airliner
offering a major stride forward in airline profitability. Design speeds 330 kt CAS/0.86 330 kt CAS/0.86
Vmo/Mmo
• Certification basis includes : Underfloor cargo From 27LD3 to 32/33LD3/11 pallets

- JAR 25 at change 13 3LD3 + 8 pallets + bulk 19.7 m3
+ bulk 19.7 m3
- JAR AWO at change 1 for CAT II and CAT III and
autoland. * Max ramp weight 900 kg higher than MTOW
- ICAO annex 16 chapter 3 for noise.
STL 472.755/92 Issue 4 1.3

A330 General
Aircraft design specifications
1. Design weights (see page 1.3) 4. Structural life (design aims)
The objectives for primary structure fatigue life are as
2. Design speeds follows based on average block time of 4 hours :
VMO = 330 kt CAS - design life goal …………………………. 20000 flights
MMO = 0.86
VD = 365 kt CAS - threshold for initial inspection ………… 8 750 flights
MD = 0.93
VB = 260 kt CAS 5. Landing gear
MB = 0.78 The design aim is 25000 cycles safe life operation in
VLO (landing gear) extension accordance with FAR and JAR.
retraction
VLE (Landing gear extended) 250 kt CAS
6. Cabin pressure
3. Slat and flap design speeds
Lever Function Config. Design speed
position Max nominal operational 574 mb ±7 mb 8.33 psi ± 0.1 psi
No. VFE kt (CAS)
differential pressure
0 Climb/cruise/holding 0 -
1 Holding 1 240 Actuating cabin pressure 610 mb ± 7 mb 8.85 psi ± 0.1 psi
of discharge valve
1 Take-off 1+F 215
2 Approach 1* 205 Max relief valve overpressure 638 mb 9.25 psi
Take-off 2 196 Max negative differential 1.00 psi
- 70 mb
3 Take-off/approach 3 186 pressure
Full Landing Full 180
STL 472.755/92 Issue 4 1.4

A330 General
Aircraft design specifications
7. Fuel capacity
A330-200 A330-300
Litres US gallons Litres US gallons
Inner tank LH 42 000 11 095 41 904 11 070

Inner tank RH 42 000 11 095 41 904 11 070
Outer tank LH 3 650 964 3 624 957
Outer tank RH 3 650 964 3 624 957
Center tank 6 230 1 646 6 230 1 646
Trim tank 41 560 10 980 - -
Total 139 090 36 745 97 286 25 700
8. Pavement strength
Max ramp weight and max aft CG.
ACN
Flexible pavement Rigid pavement
Cat A Cat B Cat C Cat D Cat A Cat B Cat C Cat D
A330-200 61 66 77 105 52 61 73 85
A330-300 56 61 71 95 48 55 65 76
Tyres radial - main gear 1400 mm x 530 mm x R23

- nose gear 1050 mm x 395 mm x R16
STL 472.755/92 Issue 4 1.5
A330 General
Weight and balance
A330-200 CG limits A330-300 CG limits
STL 472.755/92 Issue 4 1.6

A330 General
Ground maneuvre capability Effective
turn angle
R5
Minimum turning radius R3
Towing
The A330 can be towed or pushed up to a nosewheel
angle of 78° from the aircraft centre line at all weights up
to maximum ramp weight without disconnecting the 10,684m
steering.
Taxiing Y
A
Minimum turning radii (with tyre slip) and minimum R4 Min. turning width
for 180° turn
pavement width for 180° turn are as shown.
R6
Outside
face of tire
Type of turn 1 Type of turn 2 Type of turn 1 Type of turn 2

A330-200 Effective turn angle Effective turn angle A330-300 Effective turn angle Effective turn angle
78° 62.3° 77.95° 64.5°
Meter (Feet) Meter (Feet) Meter (Feet) Meter (Feet)
Y 4.72 15.478 11.65 38.23 Y 5.342 15.53 12.10 39.7
A 34.27 112.4 43.58 143.0 A 38.13 125.1 47.16 154.7
R3 23.24 76.26 25.62 84.06 R3 26.49 86.9 26.78 94.3
R4 36.29 119.04 42.99 141.06 R4 36.96 120.9 43.36 142.3
R5 29.26 96.07 31.20 102.37 R5 32.37 106.2 34.26 112.4
R6 32.89 107.91 36.45 119.6 R6 34.60 113.5 38.01 124.7
X = 22.19 m / 72.8 ft X = 27.50 m / 90.23 ft
Type of turn 1 : Asymmetric thrust differential braking (pivoting on one main gear)
Type of turn 2 : Symmetric thrust no braking
STL 472.755/92 Issue 4 1.7

STL 472.755/92 Issue 4
2. Flight deck layout
STL 472.755/92 Issue 4 2.1

A330 flight deck layout
General provisions
• As the A330 is a medium long-range aircraft the
cockpit offers full provision for a 3rd occupant seat as
well as a folding 4th occupant seat.
First officer's sidestick
Captain's sidestick Sliding window

(Emergency evacuation)
Sliding window
(Emergency
evacuation)
First officer's
seat
Captain's seat
First officer's
Captain's briefcase
briefcase
Third occupant
Documentation
seat
stowage
Coat room/ Fourth

suitcase occupant seat
stowage
Rear console
STL 472.755/92 Issue 4 2.2

Forward view
FO boomset stowage
Overhead outlet Assist handle Ceiling light Sliding tables FO boomset jack panel Reading light
Window control
Escape rope stowage handle
Loudspeakers
Sidestick
Nose wheel
Hand microphone steering CTL
Ashtray
Roller sunblind Checklist stowage

Oxygen mask
Oxygen mask
Air conditioning
outlet
Waste bin
Waste bin
Flight documents Checklist stowage Flash light Window outlets Normal checklist Briefcase stowage
stowage storage
STL 472.755/92 Issue 4 2.3

Rear view : right aft corner
RAIN REPELLENT BOTTLE

OXY MASK
(OPTION)
4th OCCUPANT
AXE
CONSOLE
OXY MASK
Rear view : left aft corner
LIFE VEST
LIFE VEST
JACK PANEL
3rd
OCCUPANT
HEADSET CONSOLE
BOOMSET
STL 472.755/92 Issue 4 2.4

Pilots’ field of vision
Visibility
• Windows are designed to meet or exceed the

Aerospace standard.
• Geometry :
- windshield panels : flat glass
- lateral windows : curved acrylic.
Pilots’ vision envelope

140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 10 20 30 40 50°
50°
40
30
20
10
Wingtip
visible
0
10
20
30
Aerospace standard 580 B Pilot’s axis

Binocular vision
Downward visibility in
the pilot axis : 20°
STL 472.755/92 Issue 4 2.5

Pilots’ field of vision
Pilot’s eye position

25°
19°20’
7ft 10.7in
2.40m 21ft 10.6in
45ft 1.3in 6.67m
13.75m
111°
135°
Max. aft vision
with head rotated
about spinal column Pilot’s eye position
115°
1ft 9in
0.53m
62° 62°
135°
With head
42° 42°
moved 5 inches
outboard
30° 30°
36° 36°
STL 472.755/92 Issue 4 2.6

Pilots’ field of vision - landing
configuration CAT II DH = 100 ft
• This geometry improves external aircraft monitoring,
thereby increasing safety standards. Aircraft θ A V 0 RVR SVR
- Downward visibility in the pilot axis is 20°.
A330-200 5° 39.7 120 150 270 273
- Wing tips are visible from respective pilot stations. m (ft) (132) (394) (493) (887) (897)
A330-300 2.1° 38.2 120 120 240 243

m (ft) (127) (394) (394) (788) (798)
2.1°pitch Pilot’s eyes
θ
20° cockpit
cut-off angle
A 100ft
SVR
30m
B C
V (Visual segment) O (Obscured)
RVR
STL 472.755/92 Issue 4 2.7

Control and indication panels (shaded)
STL 472.755/92 Issue 4 2.8

Main features
• The main features are common with those developed for

the A320 and A340 families :
- sidestick controllers which leave the main instrument

panel unobstructed
- six display units (DU) interchangeable, switchable and
integrated into the same system architecture
(EFIS/ECAM).
• The other features evolve directly from the concepts

introduced with the A300/A310 family :
- ergonomic layout of panels, synoptically arranged

according to frequency of use (normal, abnormal,
emergency) within easy reach and visibility for both crew
members
- philosophy of panels (e.g., “lights out” philosophy for
overhead panel)
- principles of presentation of information (“need to know”
concept)
- monitoring of systems through an Electronic Centralized
Aircraft Monitor (ECAM)
- coherent system of colour coding for EFIS, ECAM and
panel lights.
STL 472.755/92 Issue 4 2.9

Sidestick arrangement
• Sidesicks are installed on the Captain’s and First
Officer’s forward lateral consoles.
• A dual pivot adjustable armrest behind each sidestick to
facilitate control is fitted on each seat, with position
indicators.
Pitch adjustment The handgrip includes two switches :

Position indicator - A/P disconnect/sidestick priority push-button
- Push-to-talk button
Neutral
Radio
Take-over PB
(A/P disconnection or take-over
from opposite sidestick)
STL 472.755/92 Issue 4 2.10

Sidestick operation
• Moving the sidestick results in “setting the aircraft • Control of the flight path is performed by the Electronic
trajectory” with a certain level of “g” for the requested Flight Control System (EFCS) which links the
manoeuvre depending on the amount of sidestick trajectory order with aerodynamic data to stabilize the
movement. aircraft and protect it from prohibited attitudes.
• Accuracy of movements is very precise since

backlash and friction are negligible.
Sidestick released :
Sidestick released : return to neutral
return to neutral
10 10
10 10
10 10
10 10
10 10
10 10
10 10
10 10
STL 472.755/92 Issue 4 2.11

Main instrument panels
STL 472.755/92 Issue 4 2.12

Captain and First Officer panels
• The CAPT and F/O panels are mirror images of each
other :
both incorporate two side-by-side Display Units (DUs)
(7.25 in x 7.25 in) :
. a Primary Flight Display (PFD)
. a Navigation Display (ND).
• This arrangement provides :
- better visibility on all DUs in normal configuration and in
case of reconfiguration (PFD ND or ECAM ND)
- the option to install a sliding table and a footrest in front
of each pilot.
• The PFD includes the complete Basic T with :
- attitude
- airspeed/Mach (with all upper and lower limits)
- altitude/vertical speed
- heading
- AFS status
- ILS deviation/marker
- radio altitude.
• The ROSE mode (ILS, VOR or NAV) : aircraft symbol in
screen centre, with radar availability
- ARC mode : heading up, horizon limited to a 90°
forward sector, with radar availability
- PLAN mode : north up, display centered on selected
waypoint.
• Engine display : in case of a total DMC/ECAM failure,
each pilot may display the ENG STBY page on his ND.
Note : In ROSE-NAV, ARC, and PLAN modes, MAP data
from FMS is presented.
STL 472.755/92 Issue 4 2.13

STL 472.755/92 Issue 4 2.14

Main centre panel
The centre panel groups :
- two DUs, one above the other, which are

interchangeable with the CAPT and F/O DUs :
• Engine Display (DU 1), showing :

- the main engine parameters (N1, EGT, N2 for GE
engines ;
EPR, EGT, N1, N2 for PW engines ; (EPR, TGT, N1,
N3 for RR engines)
- N1 (EPR) limit, N1 (EPR) command
- total fuel
- the flaps and slats position
- memo and warning
• System Display (DU 2) showing :

- an aircraft system synoptic diagrams page
- or the aircraft status (list of all operationally significant
items)
- standby instruments
- landing gear control and indications (including brakes)
- clock.
STL 472.755/92 Issue 4 2.15

Glareshield
• The Flight Control Unit (FCU) provides short-term • The EFIS control panels for :
interface between the Flight Management and - selection of desired ND modes (ROSE-ILS, -VOR, -
Guidance Computer (FMGC) and crew for : NAV, ARC, PLAN, ENG) and ranges
- engagement of A/P, A/THR - selection of baro settings.
- selection of required guidance modes • The master warning, master caution, autoland and
- manual selection of flight parameters SPD, MACH, sidestick priority lights.
ALT, V/SPD, HDG or track.
STL 472.755/92 Issue 4 2.16

Switching control
Central pedestal panel
In addition to the thrust levers and the engine control Multipurpose ECAM Multipurpose
functions, the main features on the pedestal are : CDU control panel CDU
- the Multipurpose Control and Display Units (MCDU) for

flight management functions and various other functions
such as data link, maintenance, etc. Radio Radio
management Power management
panel levers panel
- the Radio Management Panels (RMP) for tuning all
radio communications and the radio navigation as a Audio control Audio control
back-up to the normal operation through the Flight panel panel
Management and Guidance Computers (FMGC).

Lighting Flood ACMS DFDR
control panel light print event
- the electrical rudder trim
Weather Engine master ATC
Radar TCAS
- the parking brake control
Engine start
Speed
- the speedbrake and flap control levers. brake Flaps/slats
Parking brake
Multipurpose
CDU
Multipurpose
Space printer
Rudder trim panel
Handset
STL 472.755/92 Issue 4 2.17

Overhead panel
• The overhead panel has a “single slope”. Space Space
• All controls on the overhead panel can be reached by either Space

pilot. Reset Space
panel Reading
light
• Two main zones are separated by protective padding.
- Forward zone : Reading
light Reset
- for most frequently used functions Maintenance panel
panel
- for system controls : arranged in three main rows :
Space
- centre row for engine-related systems arranged in a
Light
logical way Space
- lateral rows for other systems.
CVR panel
ADIRS Engine Fire
- Aft zone, not used in flight, mainly for a small Audio control
panel
maintenance panel corresponding to some maintenance Hydraulic power
APU Fire Radio managt
controls. panel
Flight control Fuel
• The push-button philosophy is identical to that already Flight control
Fuel
applied on existing Airbus aircraft.
EVAC Cargo
Electrics air cond.
Emer elec
GPWS
Cargo smoke
RCDR Oxygen Air conditioning
Ventilation
Calls
Anti ice Cabin press Engine start
Rain Wiper A Interior Wiper Rain

EXT
RPLNT P lighting RPLNT
lighting
U Signs
STL 472.755/92 Issue 4 2.18

3. Electrical system
STL 472.755/92 Issue 4 3.1

A330 electrical system
Electrical power generation
The electrical power generation comprises :
• Two engine-driven AC generators, nominal power 115
kVA
• One auxiliary power unit (APU) AC generator nominal
115 kVA
• One emergency generator (Constant Speed Motor
/Generator or CSM/G), nominal power 8.6 kVA,
hydraulically driven by the Green system.
• One static inverter fed by two batteries and working
either on the ground or when CSM/G inoperative.
• Two ground connectors, power 90 kVA
• DC network supplied via two main Transformer
Rectifier Units (200 A) and one essential (100 A).
A fourth TR (100 A) is dedicated to APU start or APU
battery charging.
• Three batteries nominal capacity 37 Ah, 28 V each :
- Two batteries used :
. in emergency configuration to feed some equipment
during RAT deployment or when CSM/G not
operating.
. On ground to provide an autonomous source.
- One dedicated to APU start
STL 472.755/92 Issue 4 3.2

Distribution - normal configuration
ELEC
DC
AC distribution network DC BAT DC APU
• In normal configuration, each engine-driven generator supplies BAT 1 BAT 2 APU BAT
25 V 26 V 25 V
its associated AC BUS. 5A 0A 5A
• The AC ESS BUS is normally supplied from AC BUS 1. DC 1 DC ESS DC 2
STAT
INV
TR 1 ESS TR TR 2 APU TR
DC distribution network 28 V 28 V 28 V 25 V
50 A 50 A 50 A 100 A
• In normal configuration, normal DC systems are split into two AC1 AC1 AC2 AC2
networks : DC BUS 1 in parallel with DC BAT BUS and DC
BUS 2.
• Each DC network is supplied by its own TR.
• More specifically, ESS TR systematically feeds DC ESS BUS,
which allows a better segregation between DC 1 and DC 2.
• Two batteries are connected to the DC BAT BUS via the
Battery Charge Limiter (BCL).
• Each battery has its own HOT BUS bar (engine/APU fire squib,
ADIRS, CIDS, PRIM and SEC computers, slide warnings,
parking brake, etc).
• The third battery is dedicated to APU starting.
STL 472.755/92 Issue 4 3.3

Distribution - abnormal configurations ELEC
DC
DC BAT DC APU
Generator failure
BAT 1 BAT 2 APU BAT
- if one generator fails, another will automatically take over : 25 V 26 V 25 V
0A 0A 0A
• if APU operative, APU generator will take over
DC 1 DC ESS DC 2
• if APU generator not available, the other engine generator SHED
will take over. LND RCVRY
- In case of total loss of all main generators : TR 1 ESS TR TR 2 APU TR
0V 0V 0V 0V
0A 100 A 0A 0A
• the EMER GEN will deliver 8.6 kVA since the Green
hydraulic system is still powered by engine-driven pumps AC1 EMER GEN AC2 AC2
or
TOTAL
- In case of loss of all engines : LOSS OF
• the EMER GEN will deliver 3.5 kVA since the Green ALL MAIN
hydraulic system is then powered by the RAT ; in this GEN
case the batteries take over when slats are extended.
TR failure
- if one TR fails, the other will automatically take over its
corresponding DC network via DC BAT BUS,
- In case of double TR failure :
• TR 1 and 2 : DC BUS 1 and DC BUS 2 are lost
• TR 1 (or 2) and ESS TR : The remaining TR supplies
DC BUS 1 + 2 and DC BAT BUS ; the DC ESS BUS is
lost.
STL 472.755/92 Issue 4 3.4

Control and display
Overhead panel
BAT BAT1 BAT2 APU BAT GALLEY COMMERCIAL
EMER ELEC PWR 1 FAULT FAULT FAULT AC ESS FEED FAULT
A
EMER GEN TEST MAN ON 2 26.8 v OFF/R OFF/R OFF/R OFF
U
T OFF
LAND APU O
FAULT
RECOVERY EMER GEN
AC ESS BUS ALTN
A
FAULT E AC BUS 1
BUS TIE AC BUS 2 E
U A
L L
ON T U
E OFF T E
O C O C
IDG 1 APU GEN IDG 2
EXT B EXT A
GEN GEN
FAULT
AVAIL AVAIL
FAULT FAULT FAULT FAULT
OFF AUTO ON
OFF OFF/R OFF OFF/R
ECAM
ELEC
DC
DC BAT DC APU
BAT 1 BAT 2 APU BAT

25 V 26 V 25 V
5A 0A 5A
DC 1 DC ESS DC 2
STAT
INV
TR 1 ESS TR TR 2 APU TR
28 V 28 V 28 V 25 V
50 A 50 A 50 A 100 A
AC1 AC1 AC2 AC2
STL 472.755/92 Issue 4 3.5

Circuit - breaker monitoring
• Circuit-breakers are installed in the avionics bay area

below the cockpit.
• Circuit-breakers are monitored by the CBMU (Circuit-

Breaker Monitoring Units) which output the identification
and status of each circuit-breaker.
• A specific C/B page is provided on the ECAM.

C/B
• Computer resets can be performed via system controls. ECMU1 VOLT SNSG …………………. X1 4XM
SFCC1 NORM DCBUS AVAI ………... X3 10CW
HYD PUMP G ENG2 …………………. X44 4JG2
ANTI ICE ENG2 ……………………….. W2 2DN2
DU SWTG CAPT ND …………………. S2 9WK1
HYD PUMP B ENG1 ………………….. U15 1JB
ADIRU1 155VAC ……………………… C8 4FP1
ANTI ICE PITOT 1 OR 3 …………….. D10 4DA1
303PP ………………………………….. 715VU 9PB
BUS 1/3 TIE CNTOR …………………. X12 10PC1
ANTI ICE 1 OR 3 PHC ……………….. N21 2DA3
EXTRACT FAN AVNCS ………………. J21 1HQ
ADIRU1 AOA1 26VAC ……………….. M80 5FP1
APU TR …………………………………. 5000VU 3PU3
SWTG FUEL BUS …………………….. W15 8PR
AUDIO ACP CAPT …………………….. A50 4RN1
AIR BLEED VLV ENG2 ……………….. D12 3HA2
XFEED VLV ENG1 MOT1-2 ………….. C15 40E1
STL 472.755/92 Issue 4 3.6

4. Hydraulic system
STL 472.755/92 Issue 4 4.1

A330 hydraulic system
Architecture
STL 472.755/92 Issue 4 4.2

A330 hydraulic system
General
• Three fully independent systems : Green, Blue, Yellow • Abnormal operation :
(nominal pressure at 3000 psi).
- in the event of one engine failure, the Green
• Normal operation :
electrical pump runs automatically for 25 seconds
when landing gear lever is selected up.
- four engine-driven pumps, two of which are for the
Green system - in the event of engine 2 failure, the Yellow electrical
pump runs automatically when flaps are not
- three electrical pumps that can act automatically as back-
retracted.
up
- In the event of both engine failure, RAT deployment
They are managed by the HSMU (Hydraulic System will be automatically controlled by the HSMU to
Monitoring Unit) which ensures all autofunctions (electrical pressurize the Green system.
pumps, RAT, monitoring, etc) ; manual override is
available on the overhead panel.
HYD
- one handpump on the Yellow system for cargo doors
operation when no electrical power is available. GREEN BLUE YELLOW GREEN
3000 3000 PSI 3000
PTU
ELEC ELEC ELEC RAT
OVHT 5600
RPM
1 1 2 2
LO AIR
PRESS
OVHT
STL 472.755/92 Issue 4 4.3

STL 472.755/92 Issue 4
5. Flight controls
STL 472.755/92 Issue 4 5.1

A330 flight controls - EFCS
Electronic Flight Control System (EFCS)
Surfaces :
• all hydraulically activated
• all electrically controlled
• mechanical back-up control :
- rudder
- Trimmable Horizontal Stabilizer
Elevators
Rudder
Flaps
Slats Spoilers
Trimmable
Horizontal
Ailerons Stabiliser (THS)
STL 472.755/92 Issue 4 5.2

General
The A330 fly-by-wire system is being designed to make

this new aircraft more cost effective, safer and more
pleasant to fly, and more comfortable to travel in than
conventional aircraft.
Basic principles
• A330 flight control surfaces are all :

- electrically controlled
- hydraulically activated
• Stabilizer and rudder can be mechanically controlled.
• Sidesticks are used to fly the aircraft in pitch and roll

(and indirectly through turn coordination, in yaw).
• Pilot inputs are interpreted by the EFCS computers for

moving the flying controls as necessary to achieve the
desired pilot commands.
• Regardless of pilot inputs, the computers will prevent :

- excessive maneuvres
- exceedance of the safe flight envelope.
STL 472.755/92 Issue 4 5.3

Computers
Electrical control of the main surfaces is achieved by two
types of computers :
• three flight control primary computers (PRIM) which can
process all three types of control laws (Normal,
Alternate, Direct)
• two flight control secondary computers (SEC) which can
process the Direct Control Law.
These computers perform additional functions including :
• speebrakes and ground spoiler command
• characteristic speed computation (PRIM only).
High-lift devices are commanded by two Slat/Flap Control

Computers (SFCC).
The SFCCs also command the aileron droop via the
primary or secondary computers.
In order to provide all required monitoring information to
the crew and to the Central Maintenance System (CMS),
two Flight Control Data Concentrators (FCDC) acquire the
outputs from the various computers to be sent to the
ECAM and Flight Data Interface Unit (FDIU). These two
FCDCs ensure the electrical isolation of the flight control
computers from the other systems.
STL 472.755/92 Issue 4 5.4

Power sources
Electrical power supply
The flight control computers (primary, secondary and Flight
Control Data Concentrator) are fed by various DC busbars.
This ensures that at least two flight control computers are
powered in the event of major electrical power losses such as
- failure of two main systems or
- electrical emergency configuration (CSM-G) or
- battery-only supply.
Normal Emergency
AC DC AC ESS DC ESS HOT
Primary 1 X X
(BACK UP)
Primary 2 X
Primary 3 X
X
Secondary 1 X (BACK UP)
Secondary 2 X X
(BACK UP)
FCDC 1 X
(SHED)
FCDC 2 X
STL 472.755/92 Issue 4 5.5

Power sources
Hydraulic power supply

Three hydraulic circuits (Green, Yellow, Blue) power the
flight controls.
System circuit Power source
Green 2 engine (N° 1 and 2) - driven pumps

1 electropump
1 RAT
Yellow 1 engine (N° 2) - driven pump

1 electropump
Blue 1 engine (N° 1) - driven pump

1 electopump
The distribution to the various control surfaces is designed

to cover multiple failure cases.
STL 472.755/92 Issue 4 5.6

Safety objectives
Safeguards were designed for protection against :
Loss of pitch control - extremely improbable (<10-9)
Loss of elevators - extremely remote (< 10-7)
Loss of roll control - extremely improbable
Permanent loss of THS - extremely improbable
Rudder loss or runaway - extremely improbable
In order to satisfy these objectives, the following architecture

applies :
- electrical signalling for spoilers, elevators and ailerons
- electrical and mechanical signalling in parallel for rudder

and THS.
STL 472.755/92 Issue 4 5.7

Dispatch objectives
The basic objective is to allow dispatch of the aircraft with at

least one peripheral or computer failed in order to increase
the dispatch reliability without impairing flight safety.
Systems Dispatch situation
3 IRS Maximum 1 inoperative or “off”

2 yaw rate gyros
3 PRIM
2 SEC
3 ADR Maximum 1 inoperative or “off”
3 IR - 2 Nz accelerometers Maximum 1 inoperative or “off”
2 FCDC Maximum 1 inoperative or “off”
3 PRIM/2 SEC Maximum 1 inoperative or “off”

Electro hydraulic and electro actuators Maximum 1 inoperative if it is not connected to 2 computers
No-go items are inboard aileron, elevator and yaw damper
actuators.
STL 472.755/92 Issue 4 5.8

Design principles
Two types of flight control computers : The two secondary computers (SEC) :
• PRIM (two channels with different software for
control/monitoring).
SEC (two channels with different software for • are able to process direct laws only
control/monitoring).
• either SEC can be the master in case of loss of all
• Each one of these computers can perform two tasks : primary computers
- process orders to be sent to other computers as a • each SEC can control up to 10 servo-loops
function of various inputs (sidestick, autopilot…) simultaneously ; each can provide complete aircraft
control.
- execute orders received from other computers so as
to control their own servo-loop. Electrically controlled hydraulic servo-jacks can
operate in one of three control modes depending
The three primary or main computers (PRIM) :
upon computer status and type of control surface :
• process all control laws (Normal, Alternate, Direct) as
• Active : the servo-jack position is electrically
the flight control orders.
controlled
• One of the three PRIM is selected to be the master ;
• Damping : the servo-jack position follows the
it processes the orders and outputs them to the other
surface movement
computers PRIM 1, 2 and 3, SEC 1 and 2) which will
then execute them on their related servo-loop. • Centering : the servo-jack position is maintained
neutral.
• The master checks that its orders are fulfilled by
comparing them with feedback received ; this allows
self-monitoring of the master which can detect a
malfunction and cascade control to the next
computer.
• Each PRIM is able to control up to eight servo-loops
simultaneously ; each can provide complete aircraft
control under normal laws.
STL 472.755/92 Issue 4 5.9
Schematic diagram
STL 472.755/92 Issue 4 5.10

EFCS - Computers and actuators
STL 472.755/92 Issue 4 5.11

Pitch control
STL 472.755/92 Issue 4 5.12

Pitch control
Pitch control is provided by two elevators and the THS :
- elevator deflections 30° nose up - 15° nose down
- THS deflections 14° nose up - 2° nose down.
Each elevator is actuated by two independent hydraulic
servo control units ;
L ELEV is driven by Green and Blue hydraulic jacks
R ELEV is driven by Green and Yellow hydraulic jacks
one servo control is in active mode while the other is in
damping mode.
In case of a failure on the active servo-jack, it reverts to
damping mode while the other becomes active.
In case of electrical supply failure to both servo-jacks of one
elevator, these revert to centering mode which commands a
0° position of the related elevator.
Autoflight orders are processed by one of the primary
computers.
Sidestick signals, in manual flight, are processed by either
one of PRIM 1 and 2 or SEC 1 and 2
The THS is driven by two hydraulic motors supplied by Blue

and Yellow systems ; these motors are controlled :
- either of the three electrical motors with their associated
electronics controlled by one primary computer each
- or by mechanical command from control wheels located
on the central pedestal.
The control wheels are used in case of major failure (Direct
Law or mechanical back-up) and have priority over any
other command.
STL 472.755/92 Issue 4 5.13
Roll control
G
Y Ailerons
B hyd jacks
G
6
5
4 Spoilers
3
2
1
SPLRS 2, 4 ,5
Autopilot NORM
commands PRIM (3)
(1) (2)
3 PRIM
1
FAIL
2
3
4
5
6
B
G
G
Y
SPLRS 3, 6
SEC
Sidestick (1) (2)
commands
STL 472.755/92 Issue 4 5.14

Roll control
Roll control is provided two ailerons and five spoilers (2 to 6) per
wing :
- aileron deflection is ± 25°
- spoiler max deflection is -35°. Deflection is reduced in CONF 2
and 3.
Each aileron is driven by two electrically signalled servo-controls

which are connected to :
- two computers for the inboard ailerons (PRIM 1 or 2 and SEC
1 or 2)
- one computer for the outboard ailerons (PRIM 3, SEC 1 or 2)
- one servo-control is in active mode while the other is in
damping mode.
In manual mode, above 190 kt the outboard ailerons are

centered to prevent any twisting moment.
In AP mode or in certain failure cases the outboard ailerons are

used up to 300 Kt. Each spoiler is driven by one electro-
hydraulic servo-control which is connected to one specific
computer.
In the event of a failure being detected on one spoiler, the

opposite spoiler is retracted and maintained in a retracted
position.
Autopilot orders are processed by one of the primary computers.
Sidestick signals, in manual flight, are processed by either one

of the primary or secondary computers.
Note : If the RAT is deployed to provide Green hydraulic power,

the outboard ailerons servo-controls revert to damping
mode in order to minimize hydraulic demands.
STL 472.755/92 Issue 4 5.15
Yaw control
STL 472.755/92 Issue 4 5.16

Yaw control
Yaw control is provided by one rudder surface :
- rudder deflection ± 31.6°.
The rudder is operated by three independent hydraulic
servo-controls, with a common mechanical input. This
mechanical input receives three commands :
- rudder pedal input
- rudder trim actuator electrical input
- yaw damper electrical input.
The mechanical input is limited by the Travel Limitation Unit
(TLU) as a function of airspeed in order to avoid excessive
load transmission to the aircraft. This function is achieved
by the secondary computers.
The rudder trim controls the rudder pedal zero load position
as a function of pilot manual command on a switch located
on the pedestal (artificial feel neutral variation). This
function is achieved by the secondary computers.
Yaw damper commands are computed by the primary or
secondary computers
In case of total loss of electrical power or total loss of flight
controls computers the back up yaw damper unit (BYDU)
becomes active for yaw damping function.
Autoflight orders are processed by the primary computers
and are transmitted to the rudder via the yaw damper servo-
actuator and the rudder trim actuator.
Note : in the event of loss of both yaw damper actuators the
yaw damping function is achieved through roll control
surfaces, in which case at least one spoiler pair is required.
STL 472.755/92 Issue 4 5.17

Left intentionally blank
STL 472.755/92 Issue 4 5.18

Additional functions devoted to
aileron and spoilers
Ailerons Six spoilers and two pairs of ailerons perform these
Ailerons receive commands for the following additional functions in following priority order :
functions :
• the roll demand has priority over the speedbrake
• manoeuvre load alleviation : two pairs of ailerons function
are deflected upwards - 11° max to reduce wing loads
in case of high “g” manoeuvre • the lift augmenting function has priority over the
speedbrake function
• lift augmentation (aileron droop) : two pairs of • if one spoiler surface fails to extend, the symmetrical
ailerons are deflected downwards to increase lift when surface on the other wing is inhibited.
flaps are extended.
Spoilers
Spoilers receive commands for the following additional
functions :
• manoeuvre load alleviation : spoilers 4, 5 and 6
• Ground spoiler functions : spoilers 1 to 6

• - 35° max for spoiler 1,
• - 50° max for spoilers 2 to 6
• Speedbrake functions : spoilers 1 to 6

• - 25° max for spoiler 1
• - 30° max for spoilers 2 to 6
STL 472.755/92 Issue 4 5.19

Slats/flaps controls
STL 472.755/92 Issue 4 5.20

Slats/flaps
• High lift control is achieved on each wing by :
- seven leading edge slats
- two trailing edge flaps
- two ailerons (ailerons droop function)
• Slat and flaps are driven through similar hydromechanical
systems consisting of :
- Power Control Units (PCU)
- differential gearboxes and transverse torque shafts
- rotary actuators.
• Slats and flaps are electrically signalled through the
SFCCs :
- control lever position is obtained from the Command
Sensor Unit (CSU) by the two SFCCs
- each SFCC controls one hydraulic motor in both of the
flap and slat PCUs.
• Aileron droop is achieved through the primary computers,
depending on flap position data received from the SFCC.
• The SFCC monitors the slats and flaps drive system
through feed-back Position Pick-off Units (FPPU) located
at the PCUs and at the outer end of the transmission
torque shafts.
• Wing Tip Brakes (WTB) installed within the torque shaft
system, controlled by the SFCC, prevent asymmetric
operation, blow back or runaway.
• A pressure-off brake provided between each hydraulic
motor of the PCU and the differential gearboxes, locks
the slat or flap position when there is no drive command
from the SFCC.
• Flight Warning Computers (FWC) receive slat and flap
position data through dedicated instrumentation Position
Pick-off Units (IPPU) for warnings and position indication
on ECAM display units.
STL 472.755/92 Issue 4 5.21
Controls and displays
FLT CTL
PRIM 2 SEC 2 PRIM 3
FAULT FAULT FAULT
OFF OFF OFF
SIDE STICK PRIORITY PFD

F/O
F/O
ECAM
ENGINE-
WARNING
ECAM
0
1
0
1
SYSTEM -
2 2 FLAPS WARNING
3 3
FULL FULL
RUD TRIM
NOSE NOSE
L R
RESET
L 19.7
STL 472.755/92 Issue 4 5.22

• Overhead panel • Main instrument panel
Pushbutton switches on the overhead panel allow ECAM display units and PFDs present warnings and
disconnection or reset of the primary and secondary status information on the Flight control system.
computers. They provide local warnings. Side 1 Permanent indication of slat and flap positions are given
computer switches on left-hand side are separated from on the ECAM engine/warning display. Remaining flight
those of side 2 computers on right-hand side. control surface positions are given on the FLT/CTL
system page which is presented on the ECAM
• Glareshield system/status display.
Captain and First Officer priority lights, located in the
glareshield, provide indication if either has taken the • Rudder pedals
priority for his sidestick orders. Interconnected pedals on each crew member’s side allow
mechanical yaw control through the rudder.
• Lateral consoles
Captain and First Officer sidesticks, located on the lateral
consoles, provide the flight controls computers with pitch
and roll orders. They are not mechanically coupled. They
incorporate a take-over pushbutton switch.
• Central pedestal
- Speedbrake control lever position is processed by the
primary computers for speedbrake control. A “ground
spoiler” position commands ground deceleration
(spoilers and ailerons).
- Rudder trim switch and reset pushbutton switch are
processed by the secondary computers. The local
rudder trim position indication is repeated on the ECAM
FLT/CTL system page.
- Flap control lever position is processed by the SFCC. It
allows selection of high-lift configurations for slats and
flaps. Lever position indication is repeated in the “flap
section” of the ECAM engine and warning display.
- Pitch trim wheels allow the setting of the THS position
for take-off. They permit manual pitch trim control.
STL 472.755/92 Issue 4 5.23

ECAM system page
STL 472.755/92 Issue 4 5.24

Control law introduction
• Flight through computers • Mechanical back-up
Depending upon the EFCS status, the control law is : During a complete loss of electrical power the aircraft
- Normal Law (normal conditions even after single is controlled by :
failure of sensors, electrical system, hydraulic - longitudinal control through trim wheel
system or flight control computer). - lateral control from pedals.
According to number and nature of subsequent

failures, it automatically reverts to :
- Alternate Law, or Overall Normal LAW schematic
- Direct Law.
STL 472.755/92 Issue 4 5.25

Normal Law - flight mode
Basic principle
• Highlights
- No direct relationship between sidestick and
control surface deflection.
- The sidestick serve to provide overall command
objectives in all three axes.
- Computers command surface deflections to
achieve Normal Law objectives (if compatible with
protections).
STL 472.755/92 Issue 4 5.26

Objectives
• Pitch axis : • Adaptation of objectives to :
Sidestick deflection results in a change of vertical - Ground phase : ground mode

load factor. . Direct relationship between stick and elevator available
The normal law elaborates elevator and THS orders so before lift-off and after touch-down.
that : . Direct relationship between stick and roll control
- a stick movement leads to a flight path variation surfaces.
- when stick is released, flight path is maintained without . Rudder : mechanical from pedals + yaw damper
any pilot action, the aircraft being automatically function.
trimmed. . For smooth transition, blend of ground phase law and
load factor (Nz) command law at take off.
• Lateral axis : Sidestick deflection results in initiating
roll rate. - Flight phase : flight mode
The pitch normal law flight mode is a load factor demand
Roll rate demand is converted into a bank angle demand. law with auto trim and full flight envelope protection. The
The Normal Law signals roll and yaw surfaces to achieve roll normal law provides combined control of the
bank angle demand and maintain it - if less than 33° - ailerons, spoilers 2 to 6 and rudder.
when the stick is released.
- Landing phase : flare mode
Pedal deflection results in sideslip and bank angle (with a . To allow conventional flare.
given relationship). . Stick input commands a pitch attitude increment to a
reference pitch attitude adjusted as a function of radio
Pedal input - stick free - results in stabilized sideslip altitude to provide artificial ground effect.
and bank angle (facilitates de-crabbing in crosswind).
STL 472.755/92 Issue 4 5.27

Engine failure or aircraft asymmetry
• By virtue of fly-by-wire controls and associated laws,
handling characteristics are unique in the engine failure
case :
- with no corrective action :

• stabilized sideslip and bank angle
• slowly diverging heading
• safe flight
- short-term recommended action :

• zero sideslip or sideslip target (take-off) with pedals
• then stabilize heading with stick input
• steady flight with stick free and no pedal force (rud-
der trim).
No corrective action Corrective action
β β
• This feature is made possible since roll controls can

be fully deflected with sidestick neutral.
The optimal pilot rudder application results in

optimum climb performance.
STL 472.755/92 Issue 4 5.28

Normal Law - flight mode Normal Law - protections
Main operational aspects and benefits • Protection does not mean limitation of pilot authority.
Full pilot authority prevails within the normal flight
• Automatic pitch trim envelope.
• Whatever the sidestick deflection is, computers have
• Automatic elevator to compensate turns up to 33° bank scheduled protections which overcome pilot inputs to
prevent :
• Aircraft response almost unaffected by speed, weight - excessive load factors (no structural overstressing)
or center of gravity location - significant flight envelope exceedances :
• speed overshoot above operational limits
• Bank angle resistance to disturbance stick free • stall
• extreme pitch attitude
• Precise piloting • extreme bank angle.
• Turn coordination
• Dutch roll damping Load factor protection

• Design aim
• Sideslip minimization
To minimize the probability of hazardous events when
high manoeuvrability is needed.
• Passenger comfort
• Load factor limitation at :
• Reduced pilot, workload
+ 2.5 g, -1 g for clean configuration
+ 2 g, 0 g when slats are extended.
• Increased safety
Rapid pull-up to 2.5 g is immediately possible.
STL 472.755/92 Issue 4 5.29

High speed protection High angle-of-attack protection
• Design aims • Design aims
To protect the aircraft against speed overshoot - Protection against stall
above VMO/MMO. - Ability to reach and hold a high CL (sidestick fully
Non-interference with flight at VMO/MMO. back), without exceeding stall angle (typically 3°/5°
below stall angle) : good roll manoeuvrability and
• Principle innocuous flight characteristics.
When speed or Mach number is exceeded (VMO + - Elimination of risk of stall in high dynamic manoeuvres
6 kt/MMO + 0.01) : or gusts.
- automatic, progressive, up elevator is applied - Non-interference with normal operating speeds and
(.1 g max) manoeuvres.
- pilot nose-down authority is reduced. - Load factor limitation maintained.
- Bank angle limited.
• Results - Available from lift-off to landing.
Maximum stabilized speed, nosed-down stick :
VMO + 15 kt • Windshear protection
MMO + 0.04 Windshear protection is ensured by
- SRS mode
- speed trend indication
- wind indication (speed and direction)
- flight path vector
- Windshear warning
- predictive windshear function of weather radar
(optional).
STL 472.755/92 Issue 4 5.30

High angle-of-attack protection Pitch attitude protection
• Principle • Design aim
When the AOA*) is greater than AOA prot, the basic To enhance the effectiveness of AOA and high-speed
objective defined by sidestick input reverts from
vertical load factor to AOA demand. protection in extreme conditions and in windshear
encounter.
• Result • Principle
- AOA protection is maintained if sidestick is left Pilot authority is reduced at extreme attitude.
neutral. • Result
- AOA floor results in GA power with an ensuing Pitch attitude limited :
reduction of AOA.
- nose-down 15°
- AOA max is maintained if sidestick is deflected
fully aft. - nose-up 30°, to 25° at low speed
Return to normal basic objective is achieved if the

sidestick is pushed forward. Bank angle protection
- When stick is released above 33° the aircraft
automatically rolls back to 33°.
- If stick is maintained, bank angle greater than 33° will be
maintained but limited to 67°.
- When overspeed protection is triggered :
. Spiral stability is introduced regardless of bank angle
α
. Max bank angle is limited to 45°.

- When angle-of-attack protection is triggered, max bank
angle is limited to 45°.
Low energy warning

α
A low energy aural warning “SPEED SPEED SPEED” is
α
α triggered to inform the pilot that the aircraft energy

α
α
becomes lower than a threshold under which, to recover
a positive flight path angle through pitch control, the
*) AOA = α thrust must be increased.
STL 472.755/92 Issue 4 5.31

Reconfiguration control laws
No loss of Normal Law after a single failure.
Automatic reversion from Normal Law to Alternate or
Direct Law according to the number and nature of
subsequent failures.
Normal Control Law
Failures
(at least two failures detected)
Failures
(at least two failures -
second not self-detected)
Alternate Control Law
Crew
Pitch Direct Law
action
(failure detection
confirmation)
Mechanical back-up
STL 472.755/92 Issue 4 5.32

Alternate Law Direct Law
• Probability objective : 10-5/flight hour (10-3 under • Probability objective : 10-7/flight hour (10-5 under
MMEL). MMEL).
• No change for ground, take-off and flare mode • No change for ground mode and take-off mode
compared to Normal Law. compared to Normal Law.
• Flight mode : • Flight mode : Maintained down to the ground

- Pitch axis : as per Normal Law with limited pitch rate - in all three axes, direct relationship between stick
and gains depending on speed and CONF. and elevator/roll control surfaces which is center of
gravity and configuration dependent.
- Roll/yaw axes : Depending on failure :
1. The lateral control is similar to normal law (no • All protections are lost
positive spiral stability is introduced). Conventional aural stall and overspeed warnings are
2. Characterized by a direct stick-to-roll surface provided as for Alternate Law.
relationship which is configuration dependent.
• Main operational aspect :
• Protections : - manual trimming through trim wheel.
- pitch attitude : lost
- high speed : replaced by static stability
- high angle of attack : replaced by static stability
(Vc prot. Law)
+ aural stall warning when
α > α sw*
- low energy : lost
STL 472.755/92 Issue 4 5.33

Control law reconfiguration summary
Flight Control Computer

Surface deflection
Type Aircraft Surface Aircraft
objective deflection response
A order
Feedback
Computer Surface deflection

Type Surface deflection Aircraft
orders. response
B Kinematic
Control law Pitch Lateral
Normal Type A Type A
Alternate Type A Type A/B
Direct Type B Type B
STL 472.755/92 Issue 4 5.34

Mechanical back-up
• To sustain the aircraft during a temporary complete loss of
electrical power.
• Longitudinal control of the aircraft through trim wheel.

Elevators kept at zero deflection.
• Lateral control from pedals. Roll damping is provided by the

Back up Yaw Dumper Unit (BYDU).
• Message on PFD MAN PITCH TRIM ONLY (red).
STL 472.755/92 Issue 4 5.35

Control law status information
Besides ECAM messages, the pilot is permanently informed of control law status on PFD.
Normal Law Alternate Law Direct Law

Normal FMA indications Normal FMA indications Normal FMA indications +
USE MAN PITCH TRIM
Pitch attitude protection

+ Audio warning + Audio warning
Bank angle protection + ECAM messages + ECAM messages
with with
limitations, if any limitations, if any
STL 472.755/92 Issue 4 5.36

Control law status information
Crew information : PFD speed scale
STL 472.755/92 Issue 4 5.37

Priority display logic
Captain's side First Officer'side

Sidestick Annunciation Annunciation Sidestick
Take-over button Sidestick

CPT
depressed deflected
Green Red
Take-over button Sidestick

depressed in neutral
“Light off” Red
Sidestick Take-over button

deflected F/O depressed
Red Green
Sidestick Take-over button

in neutral depressed
Red “Light off”
STL 472.755/92 Issue 4 5.38

Priority logic
• Normal operation : Captain and First Officer inputs are
algebrically summed.
• Autopilot disconnect pushbutton is used at take-over

button.
• Last pilot who depressed and holds take-over button has

priority ; other pilot’s inputs ignored.
CHRONO CHRONO
• Priority annunciation :
- in front of each pilot on glareshield
- ECAM message
- audio warning. SIDE STICK PRIORITY SIDE STICK PRIORITY
• Normal control restored when both buttons are released.

CAPT F/O
• Jammed sidestick :
- priority automatically latched after 30 seconds
- priority reset by depressing take-over button on
previously jammed sidestick.
STL 472.755/92 Issue 4 5.39

STL 472.755/92 Issue 4
6. Landing gear
STL 472.755/92 Issue 4 6.1

A330 landing gear
STL 472.755/92 Issue 4 6.2

A330 landing gear
Main features
• Conventional landing gear with single bogie nose gear

and double bogie main landing gear with direct-action
shock absorbers.
• The main landing gear is also provided with a shock

absorber extension/retraction system.
• The main gears retract laterally ; nose gear retracts

forward into the fuselage.
• Electrically controlled by two Landing Gear

Control/Interface Units (LGCIU).
• Hydraulically actuated (Green system) with alternative

free-fall/spring downlock mode.
• Alternating use of both LGCIUs for each

retraction/extension cycle. Resetting the landing gear
control lever results in transition to the other LGCIU.
• Elimitation of gear lever neutral position through

automatic depressurization of landing gear hydraulic
supply at speeds above 280 kt.
• Elimitation of microswitches by use trouble-free proximity

detectors for position sensing.
STL 472.755/92 Issue 4 6.3

A330 landing gear
BLUE LO PR DISTRIBUTION LINE
A/SKID &
N/W STRG
AUTO/BRK ON TO OTHER
LO MED MAX DUAL VALVE
DECEL DECEL DECEL
PEDALS
OFF
ON ON ON
312VU
ACCUMULATORS
BLUE
HP
GREEN
HP
OFF
NORMAL SELECTOR
VALVE
ON
PULL & TURN
CONTROL VALVE
PARKING BRAKE
AUTOMATIC
BSCU SELECTOR
TO OTHER GEAR
DUAL
VALVE
TO OTHER
WHEELS
DUAL SHUTTLE
VALVE
TO OTHER
WHEELS
NORMAL SERVO
VALVE ALTERNATE
SERVO VALVE
PSIX1000
T ACCU PRESS
A TO ECAM
0 4
C 3 3
TO 1 1
H
OPPOSITE
WHEEL 0
BRAKES
STL 472.755/92 Issue 4 6.4

A330 landing gear
Braking system
• Carbon disc brakes are standard. • Parking brake (Blue hydraulic system supply or Blue
brake power accumulator :
• Normal system (Green hydraulic system supply) : - electrically signalled
- electrically signalled through antiskid valves - hydraulically controlled with brake pressure indication
- individual wheel antiskid control on gauges.
- autobrake function
- automatic switchover to alternate system in event of • The Braking and Steering Control Unit (BSCU) is digital
Green hydraulic supply failure. dual-channel double system (control and monitoring)
computer controlling the following functions :
• Alternate braking system with antiskid (Blue hydraulic - normal braking system control
system supply) : - anti-skid control (normal and alternate)
- electrically signalled through alternate servovalves - autobrake function with LO, MED, MAX.
- hydraulically controlled through dual valve - nosewheel steering command processing
- individual wheel antiskid control - brake temperature signal processing
- no autobrake function. - monitoring of all these functions.
• Alternate braking system without anti-skid (Blue

hydraulic system supply or Blue brake power
accumulator) :
- hydraulically controlled by pedals through dual valve
- brake pressure has to be limited by the pilot referring
to the gauges.
- no autobrake function
- no antiskid system
STL 472.755/92 Issue 4 6.5

A330 landing gear
Antiskid system schematic
AUTO/BRK
A/C LONGITUDINAL A/C SPEED LO MED MAX
DECELERATION AFTER IMPACT DECEL DECEL DECEL
(ADIRU) (WHEEL SPEED) ON ON ON
γ ir Vo γ prog
BSCU
Vo - γ ir .t Vo - γ prog .t
HIGHEST VALUE
OFF ON
AUTO BRAKE
V ref
- + + -
RELEASE RELEASE
ORDER ORDER
IF WHEEL SPD OR
<0.88 V ref
BLUE
AUTOMATIC
HYD
SELECTOR
GREEN
NORMAL NORMAL
SERVO SERVO
VALVE VALVE
ALTERNATE
SERVO
VALVE
WHEEL WHEEL
SPEED SPEED
STL 472.755/92 Issue 4 6.6

A330 landing gear
Braking principle
Antiskid system
• From touchdown, aircraft speed is computed based on

touchdown speed (wheels) and integrated deceleration
(ADIRS). This reference speed is compared with each
wheel speed to generate a release order for closing
the normal servovalve in case of skid exceeding 16%.
• Brake pedal orders open this servovalve which is also

modulated by anti-skid closing signals.
Autobrake system
• From touchdown, a specific speed is computed based

on touchdown speed (wheels) and programmed
deceleration (low, medium, max). This programmed
speed is compared with each wheel speed to generate
a release order for closing the normal servovalve to
meet selected deceleration.
• If the reference speed exceeds programmed speed

(contaminated or iced runways), the former will take
over for the antiskid to modulate the normal servovalve.
STL 472.755/92 Issue 4 6.7

A330 landing gear
Nose gear steering principle
A/SKID &
N/W STRG
ON
OFF BSCU LS PED

DA
50 70
PE
70 50
AL
S
DI
SC
C
S
DI
30
30
ON
10
10
ENG
70 70
50 30 10 10
30 50
OFF
NON TOWING POSITION
P
AND R
I
OPEN M AUTO PILOT
NLG DOWNLOCKED AND

COMPRESSED
LGCIU 1/2
NLG DOWNLOCKED AND
BOOGIES IN GROUND POS
CHANNEL 1
2
GEEN POWER
FROM NOSE GEAR
STEERING SERVO
DOORS CLOSING VALVE
CIRCUIT (WHEN
STEERING
DOORS ARE CLOSED)
SELECTOR
VALVE
NOSE
GEAR
NWS ANGLE
STL 472.755/92 Issue 4 6.8

A330 landing gear
Rudder pedals
Nosewheel
handle
STL 472.755/92 Issue 4 6.9

A330 landing gear
ECAM system page
STL 472.755/92 Issue 4 6.10

7. Fuel system
STL 472.755/92 Issue 4 7.1

A330 fuel system
Basic layout Tank arrangement
• Total fuel capacity
Outer tanks Inner tanks Center tank Trim tank Total CTR TANK
INNER TANK (for A330-200 only) INNER TANK
7300 litres 84 000 litres 41650 litres 6230 litres 139090 litres OUTER TANK OUTER TANK
A330-200
(5730 kg) (65940 kg) (32625 kg) (4890 kg) (109185 kg)
7248 litres 83808 litres 6230 litres 97 286 litres
A330-300
(5690 kg) (65790 kg) (4890 kg) (76 370 kg)
INNER TANK DIVISION
TRIM TANK
• Ventilation VENT TANK VENT TANK
- Each wing tank and the tail tank is separately vented

though its associated vent tank.
- These vent tanks are open to the atmosphere via flame
arrestors and NACA inlets.
- Location of ducts and float valves is designed to ensure
FUEL CELL
free venting over appropriate attitude ranges during
refueling and normal ground and flight manoeuvres.
- Pressure relief outlets protext the inner tank from over- NORMAL PUMPS
or under-pressure in case of failure or blockage of the
vent system or pressure refueling gallery. STBY PUMP
EMER SPLIT VALVE
STL 472.755/92 Issue 4 7.2

A330 fuel system
Control and monitoring
The Fuel Control and Monitoring System (FCMS)
controls the fuel system automatically
Two identical Fuel Control and Monitoring Computers

(FCMC) provide :
- fuel transfer control
- aircraft gross weight and center of gravity calculation
based on zero fuel weight and zero fuel center of
gravity entered by the crew.
- center of gravity control
- refuel control
- fuel quantity measurement and indication
- level sensing
- fuel temperature indication
- signals to FADEC for IDG cooling control.
STL 472.755/92 Issue 4 7.3

A330 fuel system
Engine feed
• In normal operation, each engine is independently Outer tank fuel transfer valves are used to cycle the
supplied by two continuously operating booster pumps inner tanks contents between 3500 and 4000 kg.
located in a dedicated collector box. These valves are closed when outer tanks are empty
for 5 minutes.
In the event of a pump failure, a standby pump
automatically comes on line. • Transfer to inner tanks can be manually selected
through the OUTR TK XFR pushbutton.
Collector boxes are maintained full by a jet pump
transfer action using booster pump pressure. When selected ON, the outer tanks fuel transfer
valves, outer and inner inlet valves are controlled
In cruise conditions, a single booster pump is able to OPEN.
supply flow to both engines.
• For A330-200 only :
• A cross-feed valve allows the engine on either wing to
be supplied from the opposite one. With fuel in the center tank, both CTR TK pumps are
running and the inner inlet valves are used
• Supply of fuel to each engine may be shut off by an independently to cycle their respective inner tank
engine LP valve driven by a double motor actuator. It contents between underfull and high level (Underfull
is controlled by either the ENG FIRE pushbutton or is set at approximately 2000 kg below high level).
the ENG master lever.
When the center tank is empty, the pumps are
• Automatic transfer of fuel from the outer tanks is automatically shut off, and both inner inlet valves
performed by gravity. This occurs when trim tanks close.
have been emptied and when either inner tank
reaches 3500 kg.
STL 472.755/92 Issue 4 7.4

A330 fuel system
Jettison system (on A330-200 only - optional)
• The jettison pipe is connected to the refuel gallery in
each wing. A dual actuator jettison valve is fitted.
• Fuel is jettisoned from the centre and inner tanks

simultaneously. All normal and STBY pumps are
running and a forward transfer into center tank is
initiated.
• The aircraft weight will be reduced at a rate of not less

than 70 tonnes/hour.
• Jettison is stopped when :

- the crew deselects the jettison pushbutton
- both level sensors dedicated to jettison become dry
- a signal from the FCMC indicates that the remaining
fuel on board reaches a value previously defined by
the crew via the FMGS MCDU (option : Preselection
of gross weight after jettison).
- sum of both inner quantity reaches 10 000 kg.
STL 472.755/92 Issue 4 7.5

A330 fuel system
Centre of Gravity control band relative to operational flight envelope
STL 472.755/92 Issue 4 7.6

A330 fuel system
CG control
• Automatic CG control begins in climb at FL 255 and • Forward transfer

stops in descent at FL 245 or when FMGS time to
- Forward transfer is required for example when
destination is below 35 minutes (or 75 minutes if the
computed CG = target CG.
trim tank transfer pump fails).
- Fuel transfer from the trim tank to the inner tanks is
• Aft transfer performed by the trim tank forward transfer pump
through the trim pipe isolation valve.
* A330-200 - On the A330-200, forward transfer is directed to the
Fuel for trim tank aft transfer is provided by the center center tank when it is not empty.
tank when it contains fuel or by the inner tanks when - Forward transfer is terminated when computed CG =
the center tank is empty. target CG - 0.5%.
* A330-300
The inner tanks provide fuel for trim tank aft transfer
through the engines feed pumps.
Aft transfer is terminated for example when computed

CG = target CG - 0.5%, or when an inner tank reaches
the low level.
STL 472.755/92 Issue 4 7.7

A330 fuel system
A330-200 A. FLOOR
IDLE
CLB
N1
X FEED 102.6%
%
ENG 1
OPEN ENG 2
CHECK 35°C
ON
L
CTR XFR TANK
L
EWD
F L2 FAULT FAULT FAULT F
L1 R1 R2
U FAULT FAULT
OFF FWD OFF
FAULT FAULT
U
OUTER TK E
E OFF OFF
OFF OFF
XFR EGT
L T TANK A L
L STBY U R STBY
°C
MODE
A
FEED FAULT
T
690 690
INR TK FUEL JETTISON 211 VU FAULT FAULT
ISOL ON FAULT
U O
AUTO
L SPLIT R ARM ACTIVE OFF FWD T OFF
O
OPEN
102 N2 102
SHUT SHUT OPEN %
OFF OFF ON ON F.F
2250 2250
KG/H
If JETTISON installed
FOB : 76470KG
FUEL
1 KG 2
7300 F. USED 7300
14600
2845 1150 1054 2845
31715 2550 31715

11 °C 10
10°C
APU
4800 10°C
FOB : 76470 KG
GW 216000 KG
CG 28%
STL 472.755/92 Issue 4 7.8

A330 fuel system
A330-300
A. FLOOR
IDLE
CLB
N1
X FEED 102.6%
%
ENG 1
OPEN ENG 2
CHECK 35°C
ON
EWD
F L2
F
L1 R1 R2
U FAULT FAULT FAULT FAULT
U
OUTER TK E
E OFF OFF
OFF OFF
XFR EGT
L T TANK A L
L STBY U R STBY
°C
MODE
A
FEED FAULT
T
690 690
INR TK FUEL 211 VU FAULT FAULT
ISOL ON FAULT
U O
AUTO
L SPLIT R OFF FWD T OFF
OPEN N2
O 102 102
SHUT SHUT %
OFF OFF F.F
2250 2250
KG/H
FOB : 73420KG
FUEL
1 KG 2
7300 F. USED 7300
14600
1650 1650
2845 2845
31715 31715
- 15 °C - 21
- 20°C
- 20°C
FOB : 73420 KG 4300
GW 185000 KG
CG 28%
STL 472.755/92 Issue 4 7.9

A330 fuel system
STL 472.755/92 Issue 4 7.10

A330 fuel system
Control and indication
• No crew action is required for normal operation except
initiation and termination.
• Indications :
- fuel data (quantity, temperature) are available from a

Fuel Quantity Indication (FQI) system
- Fuel quantity is permanently displayed on upper ECAM
DU
- Fuel system synoptic on lower ECAM DU is displayed
according to ECAM logic
- low level warning is totally independent from FQI.
• Abnormal operations :
- Fuel feed sequence may be operated manually

- cross-feed valve may be operated manually
- forward and (some) inter tank transfers may be initiated
manually
- gravity feed is possible.
STL 472.755/92 Issue 4 7.11

A330 fuel system
Refueling system
A330-200 A330-300
CTR TK
INR TK INR TK INR TK INR TK
OUTR TK OUTR TK OUTR TK OUTR TK
TRIM TRIM
INLET PIPE INLET INLET INLET PIPE INLET
REFUEL VALVE VALVE VALVE REFUEL REFUEL VALVE VALVE REFUEL
ISOL ISOL ISOL ISOL ISOL ISOL
INLET VALVE VALVE VALVE INLET INLET VALVE VALVE VALVE INLET
VALVE VALVE VALVE VALVE
INLET INLET
VALVE TRIM TK VALVE TRIM TK
STL 472.755/92 Issue 4 7.12

A330 fuel system
Refueling
• Two 2.5 inch couplings are installed in the leading edge • Refueling/defueling is controlled from an external panel,
of the right wing and of the left wing (optional on the located in the fuselage fairing under the RH belly fairing,
A330-300), enabling all tanks to be filled from empty in and can be carried out with battery power only.
some :
Optional : Refueling can be controlled from the cockpit
- 33 minutes on the A330-200
• Gravity refueling can be achieved by overwing refueling
- 25 minutes on the A330-300 or 35 minutes if the left points
wing refueling point is not installed.
• Defueling is accomplished by means of fuel pumps and
for the outer and trim tanks, via transfer valves.
• An isolation valve is provided between couplings and
the refueling gallery.
• A refueling inlet valve is provided for each tank,

allowing distribution to a diffuser to reduce turbulence
and avoid electrostatic build-up.
• An automatic refueling system controls the refuel

valves to give preselected fuel load and correct
distribution.
STL 472.755/92 Issue 4 7.13

STL 472.755/92 Issue 4
8. Engine controls
STL 472.755/92 Issue 4 8.1

A330 engine controls
FADEC
• Thrust control is operated through Full Authority Digital • FADEC also called Engine Control Unit (ECU for GE
Engine Control (FADEC) computers which : engines) or Engine Electronic Controller (EEC for PW
- command the engines to provide the power best and RR engines) is a fully redundant digital control
suited to each flight phase system which provides complete engine management.
- automatically provide all the associated protection Aircraft data used for engine management is transmitted
required : to the FADEC by the Engine Interface Unit (EIU).
• either in manual (thrust lever) Each engine is equipped with a fan-case-mounted

• or in automatic (authothrust) with a fixed thrust lever. FADEC supporting the following functions :
• Engine performance and safety improvement over - gas generator control

current hydromechanical control system. - engine limit protection
- engine automatic starting
Simplification of engine/aircraft communication - engine manual starting
architecture. - power management
- engine data for cockpit indication
Reduction of crew workload by means of automatic - engine condition parameters
functions (starting, power management). - reverser control and feedback
- fuel used computation
Ease of on-wing maintenance. - fuel recirculation control (RR engines)
- FADEC cooling (RR engines)
• The system design is fault-tolerant and fully duplicated,
with ‘graceful degradation’ for minor failures (i.e. sensor
failures may lose functions but not the total system).
The engine shut-down rate resulting from FADEC

failures will be at least as good as today’s latest
hydromechanical systems with supervisory override.
STL 472.755/92 Issue 4 8.2

A330 engine controls - GE CF6-80E1A
FADEC architecture
STL 472.755/92 Issue 4 8.3

A330 engine controls - PW4164
FADEC architecture
STL 472.755/92 Issue 4 8.4

A330 engine controls - RR Trent
FADEC architecture
STL 472.755/92 Issue 4 8.5

FADEC and EIU
One FADEC located on the engine with dual redundant
channels (active and standby) each having separate 115
VAC aircraft power sources to provide engine starting on
ground and in flight.
Additional features
Dedicated FADEC alternator provides self power above :

12% N2 for GE engines
5% N2 for PW engines
8% N3 for RR engines
- Dual redundancy for electrical input devices (ADIRS 1 + 2,

TLAs, engine parameters).
- Dual redundancy for electrical part of control actuator.
- Simplex system for hydromechanical parts of the control.
- Fault tolerance and fail-operational capability.
- High level of protection against electromagnetic

disturbance.
- Interface between the FADEC system and the other aircraft

systems mainly performed by the EIU through digital data
buses.
- One EIU per engine located in the avionics bay.
- Care taken to preserve system segregation for safety and

integrity.
STL 472.755/92 Issue 4 8.6
Thrust control system
• Engine thrust control is provided by the FADEC 1 and 2 • Limit thrust parameters are computed by the FADEC.
controlling engines 1 and 2 respectively.
• Since there is no mechanization of the thrust levers (no
• Thrust selection is performed by means of : servomotor) any thrust lever displacement must be
- thrust levers when in manual mode, performed manually.
- A/THR function of the FMGS when in automatic mode,
but limited to the value corresponding to the thrust • According to the thrust lever position the FADEC
levers position. computes :
- thrust rating limit
- N1* (EPR)** when in manual mode
- N1* (EPR)** which can be achieved in automatic mode
(A/THR).
* for GE engines
** for PW, RR engines
STL 472.755/92 Issue 4 8.7

Thrust control operations
STL 472.755/92 Issue 4 8.8

Indications on ECAM upper DU
GE engines PWE engines RR engines
STL 472.755/92 Issue 4 8.9

Indications on PFD : FMA
• Following indications may appear on the PFD flight mode

annunciator, in the upper left corner : (examples only)
• ASYM : One thrust lever not in CL detent.

• CLB : Flashing when aircraft is above thrust
reduction altitude and thrust levers are not
retarded to CL.
V/S HDG • MCT : Flashing in case of engine failure if the

non-affected thrust levers are not set at
MCT.
ASYM
• A-FLOOR : When thrust is at MTO and an alpha-floor
20
condition is encountered.
180
10
160
140
10
120
STL 472.755/92 Issue 4 8.10

Thrust reverser
• Reverser deployment selection is performed through

conventional reverser controls.
• Automatic maximum reverse power limitation versus

ambient conditions with full aft throttle position.
• Display of reverser status on ECAM upper DU.
STL 472.755/92 Issue 4 8.11

STL 472.755/92 Issue 4
9. Auxiliary power unit
STL 472.755/92 Issue 4 9.1

A330 auxiliary power unit
General principles System display
• On ground, the APU makes the aircraft self-contained
by :
- providing bleed air for starting engines and for the air
conditioning system
- providing electrical power to supply the electrical
system.
• In flight, provision of back-up power for the electrical
system, the air conditioning system and engine start.
• The APU can be started using either dedicated battery,
external power or normal aircraft supply.
The normal flight envelope does not impose any
limitations for starting except when batteries are
supplying starting power.
• The APU is automatically controlled by the Electronic
Control Box (ECB) which acts as a FADEC for
monitoring start and shut-down sequences, bleed air and
speed/temperature regulation.
• Control and displays are located :
- on the overhead panel for APU normal operation and
fire protection
- on the ECAM for APU parameter display
- on the external power control panel next to the nose
landing gear
- on the REFUEL/DEFUEL panel for APU shut-down.
STL 472.755/92 Issue 4 9.2

A330 auxiliary power unit
Controls and display
925VU
APU
FIRE
AGENT APU
FIRE
TEST SQUIB
PUSH
APU DISCH
APU
MASTER SW SHUT OFF
FAULT
ON/R
START
(EXTERNAL CONTROL PANEL)
AVAIL
ECB
ON
APU BLEED VALVE 2 STAGES COMPRESSOR
3 STAGES TURBINE
GEAR BOX
APU
GEN
OIL
PUMP
STARTER
COMBUSTION CHAMBER
FUEL SUPPLY
FLAP
MOTOR
STL 472.755/92 Issue 4 9.3

STL 472.755/92 Issue 4
10. Automatic flight system
STL 472.755/92 Issue 4 10.1

A330 automatic flight system
Architecture block diagram
ADR / IR FCU
Primary Secondary
ILS (MLS)
Flight controls Flight controls
ADF
ECAM
RA FMGC
Maintenance
VOR EFIS
DME CPC
ATSU option
CLOCK
ACARS option
Back-up
FCMC Nav
DATA
BASE
LOADER
LGCIU
FADECs Thrust levers
SFCC
STL 472.755/92 Issue 4 10.2

Architecture components
Unit Number per aircraft Comments
FMGC 2 FMGEC 1 includes AFS/FIDS*
FCU 1 Includes three independent channels
MCDU 3 Colour display
A/THR instinctive 2 One for CM 1 and one for CM 2

disconnect switches
AP take-over switches 2 One for CM 1 and one for CM 2
North reference switches 1 For EIS and MCDU display
FM source switch 1 For EIS display
* Fault isolation and Detection System
OBRM (On-board Replaceable Modules)
- Solid-state memory modules plugged into the front face

of the computer.
- Cost and logistic improvement for software changes.
- Software change can be achieved in situ using a

common replaceable module reprogrammer.
STL 472.755/92 Issue 4 10.3

Flight Management Guidance and Envelope System (FMGS) crew interface
SPD MACH HDG TRK ALT LWL/CH V/S FPA
LAT
HDG V/S
TRK FPA
HDG V/S 100 1000 UP

FPA
FCU
TRK
SPD PUSH
METRIC
MACH TO
ALT
LEVEL
AP 1 AP 2 OFF
DN
LOC A/THR ALT APPR
PFD1 ND1 ND2 PFD2

GS394TAS 388 LWG/004
GS394TAS 388 LWG/004
249/16 93MM
SPEED G/S LOC CAT 2 AP1 0 1 18:35 249/16 0 1 93MM SPEED G/S LOC CAT2 AP1
DH 100 1FD2 35 2 35 2 18:35
DH 100 1FD2
34 3 3
A/THR 34 A/THR
33 4 33 4
3000 OL 3000
FMGC 1 FMGC 2
OL
20 20 CGC CON 20 20
180 CGC CON 180
015
AVD AVD 015
10 10 10 10
160 20 AVD AVD 160 20
13 00 13 00
80 80
60
140 140
60
7 LWG TILT LWG 7
010 TILT 010
10 10 -3,00 10 10
160
-3,00
160
40
40
120 790 120 790
OM 2R OM
2R
VOR2 VOR2
TBN 1020 VOR1 GAI VOR1 GAI TBN 1020
109.30 QNH AVD AVD 109.30 QNH
CGCM CGCM
4.7 NM 103 NM 4.7 NM
31 32 33 34 3 103 NM 31 32 33 34 3
NAV ACCY UPGRADED NAV ACCY UPGRADED
FM1 IND RDY SPARE FM2 FM1 IND RDY SPARE FM2
BRT BRT
DIR PROG PERF INIT DATA DIR PROG PERF INIT DATA
RAD FUEL SEC MCDU RAD FUEL SEC MCDU

F-PLN F-PLN
NAV PRED F-PNL MENU NAV PRED F-PNL MENU
AIR A B C D E AIR A B C D E
PORT PORT
ä ä
F G H I J F G H I J
ä
ä
ä ä
M M
ä
ä
F K L M N O F K L M N O
C C
A A
D D
I 1 2 3 I 1 2 3
P Q R S T U P Q R S T U
L L
M M
F 4 5 6 F 4 5 6
E E
M M
U V W X Y N U V W X Y N
7 8 9 7 8 9
U U
DWFY DWFY
. ∅ + Z - + Δ CLR . ∅ + Z - + Δ CLR
MCDU Thrust levers MCDU

STL 472.755/92 Issue 4 10.4
FMGS - AFS/FMS integration
• Composed of two computers (FMGC) including a
management part (FM), a flight guidance (FG) and a
flight envelope part (FE), this pilot interactive system
provides :
- flight management for navigation, performance
prediction and optimization, navigation radio tuning and
information display management,
- flight guidance for autopilot commands (to EFCS), flight

director command bar inputs and thrust commands (to
FADECs)
- flight envelope and speed computation.

• The FMGS offers two types of guidance achievable by
AP/FD :
- “managed” : guidance targets are automatically

provided by the FMGS as a function of
lateral and vertical flight plan data
entered in the Multipurpose Control and
Display Units (MCDU).
- “selected” : guidance targets are selected by the

pilot on the glareshield Fight Control
Unit (FCU).
Selected guidances mode always have priority over the
managed guidance modes.
STL 472.755/92 Issue 4 10.5

FMGS Crew interface
• Three MCDUs (only two at a time) on the central • Two PFDs and two NDs provide visual interface with
pedestal provide a long-term interface between the crew flight management and guidance-related data such as :
and the FMGCs in terms of :
on PFD :
- flight plan definition and display - FMGS guidance targets
- armed and active modes
- data insertion (speeds, weights, cruise level, etc.) - system engagement status
- selection of specific functions (direct to, offset, on ND :

secondary flight plan). - flight plan presentation
- aircraft position and flight path
• One FCU on the central glareshield provides a short- - navigation items (radio aids, wind).
term interface between the crew and the FMGCs.
• Two thrust levers linked to the FMGCs and FADECs

provide autothrust or manual thrust control selection to
the crew.
PFD ND
SPEED ALT CRZ NAV AP1
GS 394 TAS 388 LMG/004
1FD2 249/16 93 NM
0 1
A/THR 35 2 18:35
34 3
33 OL 4
315
320 CDN
10 10 ANG
300 20 AMB
310 00 AVD
80
280
10 10
CGC LMG TILT
260
305 -3,00
2'30 2R
780 STD
VOR1 GAI
CGCM
33 34 35 0 103 NM
STL 472.755/92 Issue 4 10.6

General functions
• Guidance function
Fail operational architecture*

Operation
Modes
• Autothrust AP/FD and A/THR mode relationship
Operation
Modes
• Flight envelope
Envelope protection --------------- (windshear, aft CG detection)

Speed computation
• Flight management
Functional architecture
Navigation
Flight planning functions -------- (assembly , fuel management, lateral revision)
Optimisation performance ------ (speed/altitude, prediction)
Vertical profile
* Fail operational refers to a single failure of a system which does not modify the aircraft’s flight path.
STL 472.755/92 Issue 4 10.7

A330 automatic flight system - guidance function
Flight Control Unit (FCU)
STL 472.755/92 Issue 4 10.8

AP/FD modes
Available modes Mode engagement (or arming as long as engagement
conditions are not met).
Guidance Managed mode Selected mode - By pushbutton action (located on the FCU) LOC -
APPR - ALT, AP1 - AP2 - A/THR.
Lateral NAV HDG - TRK
B/C*, B/C, LOC*, LOC - By action on the thrust levers. On the ground, setting
RWY the thrust levers to the TO/GA or FLEX/TO detents
RWY TRK leads to AP/FD mode engagement (SRS/RWY).
GA TRK During approach, setting the thrust levers to TO/GA
ROLL OUT engages go-around mode.
Vertical SRS (TO and GA) OP CLB, OP DES - By action on the FCU selection knobs (speed
CLB, DES V/S - FPA selection knob, HDG/TRK selection knob, altitude
ALT ALT*, ALT selection knob, V/S-FPA selection knob).
G/S*, G/S
FINAL DES • Push action engages managed mode
FLARE
• Pull action engages selected mode -
Speed FMGC reference FCU reference e.g speed or Mach selected mode pushed in flight
ECON, Auto SPD, SPD LIM engages managed speed profile (usually ECON).
STL 472.755/92 Issue 4 10.9

AP/FD operation Lateral modes
• The aircraft can be operated in ‘selected guidance’ with NAV : lateral navigation
flight references selected by the crew, or in ‘managed
guidance’ with references computed by the system. • Lateral track is defined by the FMGC according to the
flight plan introduced in the system.
• If the AP/FD controls a vertical trajectory the A/THR
controls the target SPEED/MACH. LOC : LOC axis capture and track
If the AP/FD controls a target speed, the A/THR controls
the thrust. • LOC is armed if LOC pushbutton is pressed ; LOC
capture replaces NAV.
• Selected guidance always has priority over managed
guidance, which means that the PF may select a speed, HDG/TRK
lateral or vertical path at any time ; actions are
acknowledged on the FCU itself and on the FMA (Flight • Selection of HDG/TRK references is obtained by turning
Mode Annunciator). the dedicated switch located on the FCU.
• Selected guidance or managed guidance is available for • HDG/TRK is engaged by pulling on lateral selector ;
SPEED/MACH control, LATERAL guidance and LEVEL HDG/TRK value can be selected before or after pull
CHANGE execution. action.
• Heading track preselection is possible on ground before

take-off, in flight as from 30 ft height.
STL 472.755/92 Issue 4 10.10

Vertical modes Common modes
Level changes [managed guidance (CLB, DES), selected Approach • ILS available
guidance (OP CLB OP DES)]. - GLIDE capture and track
- FLARE
• In CLB/DES modes vertical path is maintained as
- LAND
defined by the FMGC, taking into account the flight plan
- ROLL OUT
constraints inserted in the system at the clearance
altitude selected on the FCU.
• ILS not available, RNAV approach
selected on MCDU :
• OP CLB (OP DES) mode allows the aircraft to climb or
descend uninterrupted toward FCU selected altitude,
- LATERAL guidance on the F-PLN
maintaining a TARGET SPEED (managed or selected)
- VERTICAL guidance and descent
with a fixed given thrust. ALT constraints are ignored.
allowed down to MDA.
Altitude hold
Take-off • SRS
- with engines running V2 + 10 holding
• It is active if aircraft reaches FCU altitude, intermediate
- with one engine out VA (1) holding if VA>V2
flight plan altitude constraints when ALT pushbutton is
V2 holding if VA<V2.
depressed on FCU or when V/S is set to zero.
(1) VA = aircraft speed when the engine
V/S/FPA
failure occurs.
• V/S/FPA is engaged by pulling on V/S/FPA selector.
• RWY :
V/S or FPA value can be selected before or after a pull
- Track hold or LOC centerline hold.
action.
Go-around • SRS (as take-off).
• GA TRK hold.
STL 472.755/92 Issue 4 10.11

A330 automatic flight system - autothrust function
AP/FD and A/THR mode relationship
1st case
AP/FD pitch mode controls a vertical fligh path (V/S

or G/S or FINAL) then A/THR mode will control the
target speed/Mach.
e.g. if AP/FD V/S mode is selected
A/THR is in SPEED mode SPEED G/S LOC CATII AP1
DH= 200 1 FD2
A/THR
2nd
AP/FD pitch mode controls the target speed/Mach

then A/THR mode will control the thrust
e.g. if AP/FD open CLB mode is selected

A//THR is in THR CLB mode THR CLB OP CLB NAV AP1
1 FD2
A/THR
STL 472.755/92 Issue 4 10.12

AP/FD and A/THR SPD/MACH modes
In SPD/MACH managed mode AP/FD and A/THR SPD/MACH modes
• Is engaged by pushing the FCU SPD selector knob. SPEED/MACH managed or selected may either be
controlled by AP/FD pitch mode or A/THR mode.
• AP/FD or A/THR holds the SPEED/MACH as provided The reasons for this are as follows.
by the FMS.
• An AP/FD pitch mode may control a flight or an
• Speed preset for next flight phase is available by indicated airspeed - but not both at the same time.
entering preset value on the MCDU ; speed preset • Thus, if the pitch mode (elevator) controls a flight
becomes active at flight phase change. path, (G/S of V/S) the A/THR controls the IAS, but if
the pitch mode controls a speed (OPEN CLB/OPEN
• Crossover altitude is automatically provided. DES) then the A/THR will control a thrust.
SPD/MACH selected mode Consequently, AP/FD pitch mode and A/THR are
linked so that, if no AP/FD engaged, A/THR can be
• Is engaged by pulling the FCU SPD selector knob. active in SPD/MACH mode.
• Crossover altitude is automatically provided.
• Manual SPD/MACH selection is available to the pilot via

the SPD/MACH conversion push-button.
STL 472.755/92 Issue 4 10.13

A/THR operation - A/THR can be armed, active or de-activated
STL 472.755/92 Issue 4 10.14

A/THR main features
Each engine thrust is electrically controlled by the
associated FADEC (FULL Authority Digital Engine
Control) which is fully integrated in the autothrust system.
The A/THR function is computed in the FMGC.
The FADECs receive A/THR commands directly from the

AFS via an ARINC 429 bus.
Selection of thrust limit mode is obtained from the Thrust

Lever Angle (TLA). A / THR ACTIVE RANGE
inop engine
both eng
ines
T.O
FLX T CLB
MC
/G A IDL
TO E
STL 472.755/92 Issue 4 10.15

A/THR mechanisation
The thrust levers can only be moved manually by the Cruise
pilot.
Thrust levers must be set :
Take-off
- to be CLB detent
Thrust mode selection
- to the MCT detent (engine failure case).
- On ground TO limit mode is automatically selected at
power up. - The A/THR modes become active according to AP/FD
mode selection.
- FLX/TO limit mode is selected by setting a FLX/TO
temperature on the MCDU (TO page). Approach
Take-off is performed : Thrust levers must be set to CLB (or MCT engine failure
case) detent :
- in limit mode, by manually setting the thrust lever to
TO/GA detent. - ATS SPD mode is active
- in FLX/TO limit mode, by manually setting to Go Around

FLX/TO/MCT detent.
GA mode engagement is achieved by setting the thrust
Notes : levers to TO/GA detent ;
- In both cases, this manoeuvre also engages FD TO (A/THR armed ; GA thrust is applied via the FADEC).
mode (SRS RWY if ILS selected).
This maneuvre also engages AP/FD GA mode.
- The lowest FLX/TO thrust is limited to CL thrust.
Alpha floor
If the alpha floor function is activated, A/THR increases

the thrust to the GA thrust limit.
STL 472.755/92 Issue 4 10.16

Flight envelope protection
Flight envelope protection is achieved by generating
maximum and minimum selectable speeds, windshear
warning and stall warning. Also computed as part of this
protection are the maneuvering speed and the flap and
slat retraction speeds.
The alpha-floor signal is computed by the flight control

computers.
Speed computation (PFD scale)
STL 472.755/92 Issue 4 10.17

A330 automatic flight system - flight management
General architecture
EFIS CP 1
FCU EFIS CP 2
AP CONTROLS
FMGC 1 FMGC 2
FE FG FE FG
Com Com Com Com
Mon Mon Mon Mon
FM FM
FIDS
MCDU 1 MCDU 2
BACK UP NAV MCDU 3 BACK UP NAV
MCDU 3 switchable for FM function in case of MCDU 1 or 2 failure

STL 472.755/92 Issue 4 10.18
Functional architecture - Normal configuration
DMC 1 DMC 3 DMC 2
FMGC1 FMGC 2
MCDU 1 MCDU 2
FM
NORM MCDU 3
BOTH BOTH
ON 2 ON 1
STL 472.755/92 Issue 4 10.19

Functional architecture - One FMGC failed Functional architecture - Normal configuration
DMC1 DMC3 DMC2 DMC1 DMC3 DMC2
FMGC1 FMGC2 FMGC1 FMGC2
MCDU1 MCDU2 MCDU1 MCDU2
FM FM
NORM MCDU3 NORM MCDU3
BOTH BOTH BOTH BOTH
ON 2 ON 1 ON 2 ON 1
DMC1 DMC3 DMC2
FMGC1 FMGC2
MCDU1 MCDU2
OFF
FM
NORM MCDU3
BOTH BOTH MCDU 2 brightness knob
ON 2 ON 1 on "OFF"
STL 472.755/92 Issue 4 10.20

Two FMGCs associated to two MCDUs provide a
redundant configuration
• Normal mode operation : dual mode

crosstalk
FMGC 1 FMGC 2
- Each FMGC makes its own computation. buses
- One FMGC is master - the other one is slave.
- Both FMGCs are synchronized.

MCDU MCDU
- Both MCDUs act independently (entries are auto-
matically transmitted on the other MCDU and
applied to both FMGCs). FMGC 1 FMGC 2
• Independent mode
- Automatically operative if mismatch occurs between
FMGCs.
MCDU MCDU
- Independent operation of FMGC with associated
MCDUs. FMGC 1
(Data insertion and display related to the side
concerned.
- One FMGC remains master.

MCDU MCDU
Single mode
- One FMGC fails.
- Either MCDU can be used to enter or display data

related to the remaining FMGC.
STL 472.755/92 Issue 4 10.21
STL 472.755/92 Issue 4 10.22

Position indication
STL 472.755/92 Issue 4 10.23

MCDU
1 5 10 15 20 25
ECON DES AI101
CRZ OPT REC MAX
1L FL390 1R
2L REQD DIST TO LAND = 70NM 2R

DIR DIST TO DEST = 89NM
3L < REPORT 3R ND
BRG / DIST
TO GS394TAS 388 LWG/004
4L / 4R 249/16 93MM
0 1 18:35
UPDATE AT 35 2
34 3
5L 5R
* 33 OL
4
VOR 1 / FREQ ACY FREQ / VORZ
6L ATH / 114.4 HIGH 117.2 / DDM 6R
CGC CDN
AVD
AVD
60
LWG TILT
-3,00
160
40
2R
VOR2
VOR1 GAI
AVD
CGCM
103 NM
NAV ACCY UPGRADED
STL 472.755/92 Issue 4 10.24

Lateral navigation
• Position computation • The FMGC position is associated with a high or low

criterion which is based on an Estimated Position Error
- Before flight, the three IRSs are aligned on airfield or (EPE).
gate position (manually or via database).
- At take-off, the position is automatically updated to This EPE depends upon the flying area (en route,
the runway threshold. terminal, approach) and is permanently compared to
- In flight, position updating is computed using radio Airworthiness Authorities Accuracy Requirements
navaids (DME, VOR, ILS and GPS when available). (AAAR).
The FMGC position is a blend of IRS and radio If EPE > AAAR, then LOW is displayed on MCDU
position. On a medium-term basis the FM position will and the position must be cross-checked with raw
tend towards the radio position, if any drift occurs. data (ADF/VOR needles, DME reading).
• Navigation mode selection Each time HIGH (or LOW) reverts to LOW (or HIGH)
the message NAV ACCUR DOWNGRAD (or
- If the aircraft is equipped with GPS primary, the UPGRAD) is displayed on NDs and MCDUs.
FMGC uses the GPIRS position in priority (IRS-GPS
mode).
- if the GPIRS position is not available or if the aircraft
is not equipped with GPS primary, depending upon
availability of navaids and sensors, FMGC
automatically uses the best navigation means to
compute the most accurate position :
IRS - DME/DME
IRS - VOR/DME
IRS - ILS/DME
IRS only.
STL 472.755/92 Issue 4 10.25
Radio navigation Radio navigation architecture
Each FMGC tunes its own side radio navaids except
when in single operation :
- one VOR, one ILS, one ADF (if belonging to the F-PLN) RADIO NAV
and five DMEs may be auto tuned at the same time. FMGC 2 VOR 1 FREQ
SIU / 128.50
FREQ/ VOR 2
115.70 /TGO
FMGC 1
CRS CRS
- manual tuning always has priority over autotuning. 075
ILS / FREQ
( )
- autotune priority rules are done according to FMGS ( )/( )

CRS
( )
logics ; ADFI / FREQ FREQ/ ADF 2
10E / 415.00 415.00 / 10E
for example : FMGC 1 FMGC 2
• VOR autotune (frequency course) priority is :

RMP 1 RMP 2
- manual tune
- specified navaid for approach
VOR 1 VOR 2
- radio position computation
- display purpose logic. DME 1 DME 2
• Five DMEs can be scanned simultaneously ILS 1 ILS 2
ADF 1 ADF 2
- one DMEs for display purpose
- two DMEs for radio position computation when in
DME/DME mode
- one DMEs for VOR/DME position computation
when in VOR/DME mode
- one DME is linked to ILS/DME.
STL 472.755/92 Issue 4 10.26

Navigation and flight planning
Navigation Flight plan stringing
• Aircraft position determination. • Flight plan definition by company route or city pair.
• Aircraft position referenced to the flight plan. • Departure and arrival procedures including associated
speed/altitude/time constraints.
• Automatic VOR/DME/ILS/ADF selection.
• Standard flight plan revision (offset, DIR TO, holding
• Automatic guidance along flight plan from take-off to pattern, alternate flight plan activation, etc.).
approach.
• Additional flight plan revisions linked to long-range flights
• IRS alignment. (DIR TO mechanization, AWY stringing).
• Ground speed and wind computation. • Secondary flight plan creation similar to primary flight
plan.
• Polar navigation.
• Definition of five cruising levels on the flight plan.
• Optimum radio and inertial sensor mixing.
• Extension of the data base capacity.
• Provision for GPS and MLS.
STL 472.755/92 Issue 4 10.27

STL 472.755/92 Issue 4 10.28

Back-up NAV function
• A back-up source of navigation is available in the MCDU 1
and the MCDU 2, to cover failure cases.
• No data base is available in the MCDUs. The FM F-PLN is

permanently downloaded in the MCDUs (from the FMS to
which the MCDU is linked) and the back-up NAV is
selectable on MCDU menu page if FM source is on ’normal’
position.
• The following features are provided.
- Lateral revision using :
. ‘direct to’ (DIR TO) modification

. clearing of discontinuity
. waypoint deletion
. waypoint lat/long definition and insertion.
- F-PLN automatic sequencing.
- Track and distance computation between waypoints.
- IRS position using one ADIRS (onside or ADIRS 3,

according to pilot selection).
- F-PLN display on ND with crosstrack error.
STL 472.755/92 Issue 4 10.29

Flight plan aspects
• Flight plan optimisation through the performance • Advisory functions :

database :
- fuel planning.
- optimum speeds. - optimum altitude and step climb.
- optimum and maximum recommended altitudes. - time/distance/EFOB to en route diversion airfields.
- optimum step climb.
• Fuel vertical guidance related to flight plan predictions,
The computation are based on : from initial climb to approach.
- flight conditions (multiple cruise levels, weights, center of

gravity, meteorological data).
- cost index given by the airline.
- speed entered on the FCU or given in the flight plan.
• Performance predictions :
- time, altitude, speed at all waypoints.

- estimated time of arrival, distance to destination.
estimated fuel on board at destination.
- energy circle.
STL 472.755/92 Issue 4 10.30

Vertical profile
• Take-off • Descent
SRS control law maintains V2 + 10 up to thrust reduction Top of Descent (T/D) is provided on ND.
altitude where max climb thrust is applied. V2 + 10 is From T/D down to the highest altitude constraint, ECON
held up to acceleration altitude (ACC ALT). descent speed is held by the elevator and IDLE thrust by
the A/THR. If this status can no longer be held or
• Climb maintained, geometric segments will be followed
Energy sharing is applied for acceleration (70% thrust) between the constraints.
and for altitude (30% thrust) from ACC ALT up to first
climb speed. Max climb thrust is kept - altitude and • Approach
speed constraints are taken into account. From DECEL point, a deceleration allows configuration
changes in level flight.
• CRZ
Steps may exist and/or may be inserted. Approach phase is planned to reach approach speed at
1000 ft above ground level.
Flight plan - vertical definition

STEP CLIMB T/D
SPD/MACH
T/C ALT.TRANSITION
SPD/MACH
ALT.TRANSITION
SPD LIM
MULTIPLE FL CRUISE
SPD LIM
ALT
CONSTRAINTS
ALT SPD ACCEL
CONSTRAINTS
SPD
DECELERATE
ACCEL
FINAL
THR RED
THR RED
ORIGIN
TAKE OFF CLIMB CRUISE DESCENT APPROACH GO AROUND
STL 472.755/92 Issue 4 10.31

STL 472.755/92 Issue 4
11. Environmental control system
STL 472.755/92 Issue 4 11.1

A330 environmental control system
STL 472.755/92 Issue 4 11.2

Air conditioning
The hot compressed air is cooled, conditioned and To control the temperature in the different upper deck
delivered to the fuselage compartments and then zones, the quantity of trim air added is controlled through
discharged overboard through two outflow valves. the cockpit and cabin temperature control system. Hot air
is delivered to the air supply ducts through the related
Fresh air can also be supplied to the distribution system zone trim air valves. The trim air valves are controlled
through two low-pressure ground connections. A ram air through the temperature requirements of each zone and
inlet supplies emergency air to fuselage if there is a duplicated for cabin zone flexibility.
complete failure of the air generation system during flight.
A mixing manifold, mixes fresh air with cabin air. The trim air system has several features to ensure that no
substantial comfort degradation occurs in case of trim air
The cabin air that enters the underfloor area, is drawn valve or hot air valve failure ; a hot cross-bleed valve is
through recirculation filters by fans. The recirculation fans installed between the two hot air manifolds and will open
then blow the air through check valves to the mixing to maintain trim air supply to all riser ducts in the event of
manifold. The flight deck is supplied by fresh air only. hot air failure (blocked closed). Moreover, in the event of
trim air valve failure (blocked open) and/or duct overheat,
Hot bleed air is tapped downstream of the pack valves. as the shut-off valve is normally closed and there are two
The air flows through two hot air valves which control the riser ducts per cabin zone, only half of each zone will lose
pressure of the hot trim air going into two hot air its trim air supply. The flight deck is permanently supplied
manifolds. by a constant restricted trim air flow in addition to the
normal controlled trim air supply.
STL 472.755/92 Issue 4 11.3

Air conditioning - Air bleed
STL 472.755/92 Issue 4 11.4

Pneumatic
• Pressurized air is supplied for air conditioning, air
starting, wing anti-ice, water pressurization and hydraulic
reservoir pressurization.
• System operation is electrically by Bleed Monitoring

Computers (BMC), and is pneumatically controlled.
• A leak detection system is provided to detect any

overheating in the vicinity of the hot air ducts.
(*) For engine 2 the bleed valve closure due to APU

bleed valve open will occur only if the x bleed valve is
not selected close.
(**) For GE engnes only
* if installed
STL 472.755/92 Issue 4 11.5

Avionics ventilation
STL 472.755/92 Issue 4 11.6

Ventilation
• Avionics ventilation
Provides ventilation and cooling of avionics and
electronic equipment under digital control (AEVC) and
without any crew intervention.
• Cabin fans provide air blown to the avionics
compartment.
• Extract fan (continuously on) blows air through the
overboard valve (on ground), or the under-floor valve
(in flight).
• Manual control opens the overboard valve (fan failure
or smoke removal).
• Pack bay ventilation
Provided to maintain a mean temperature compatible
with the structure constraints. In flight, air is fed from
outside through a NACA air inlet. On ground, air is blown
by a turbofan which is carried out by the air bleed
system.
• Battery ventilation
Provided by ambient air being drawn around the
batteries and then vented directly outboard via a venturi.
• Lavatory and galley ventilation
Provided by ambient cabin air extracted by a fan and
exhausted near the outflow valves.
STL 472.755/92 Issue 4 11.7

Cabin pressure control
STL 472.755/92 Issue 4 11.8

Pressurization
• The pressurization control system operates fully
automatically.
• Dual system with automatic switchover after failure.

Alternative use for each flight. Two outflow valves are
operated by one of three independent electric motors.
Two of these are associated with automatic controllers.
• In normal operation, cabin altitude and rate of change

are automatically controlled from FMGC flight plan data :
- cruise flight level, landing field elevation, QNH

- time to top of climb, time to landing.
• In case of dual FMGC failure, the crew has to manually

select the landing field elevation. The cabin altitude
varies according to a preprogrammed law.
• In case of failure of both pressurization system auto-

controllers, the manual back-up mode is provided
through the third outflow valve motor.
STL 472.755/92 Issue 4 11.9

STL 472.755/92 Issue 4
12. Electronic instrument system
STL 472.755/92 Issue 4

12.1
A330 electronic instrument system
Cockpit arrangement
Captain : First Officer :
EFIS control panel EFIS control panel
Navigation display Navigation display
Master warning Master warning

and caution lights and caution lights
Primary flight display Primary flight display
PFD ND E/WD ND PFD

1 1 2 2
SD
EFIS switching Loudspeaker Loudspeaker EFIS switching
ECAM switching
Engine/warning
display
ECAM control panel
System display
STL 472.755/92 Issue 4

12.2
General
The Electronic Instrument System (EIS) performs a
display function for :
• flight operation. EFIS (Electronic Flight Instrument
System) on each crew member instrument panel :
- 1PFD (Primary Flight Display)
- 1 ND (Navigation Display)
• system operation. ECAM (Electronic Centralized Aircraft
Monitor)
On the centre instrument panel for both crew members :
- 1 E/WD (Engine/Warning Display)
- 1 SD (System Display)
The crew remains in the INFORMATION/ACTION loop
at all times and is able to CHECK and OVERRIDE the
automation (if necessary).
STL 472.755/92 Issue 4 12.3

EFIS / ECAM architecture
STL 472.755/92 Issue 4 12.4

Components
• DU (Display Unit)
Display function
- Six identical full-colour DUs
- 7.25in x 7.25in case size
- Symbol generator resident in DU
• DMC (Display Management Computer) Acquisition and
- Three identical DMCs processing functions
- Each DMC has two independent channels :

EFIS/ECAM
- Each DMC is able to drive all six DUs with four
independent formats (PFD ; ND ; E/WD ; SD).
• SDAC (System Data Acquisition Concentrator) Acquisition of system data for
- Two identical SDACs transmission to FWC and DMC
- The SDCAs are connected to the DMCs and FWCs
• FWC (Flight Warning Computer) Acquisition and

- Two identical FWCs processing of : Alert messages
Memos
- Each FWC is connected to all DMCs.
Aural alerts
Flight phases
Auto callout
STL 472.755/92 Issue 4 12.5

Architecture Availability objectives
• Fully redundant EIS architecture • Departure with one DMC and one DU failed all functions
remain available :
Partitioned DMCs (three EFIS functions/three ECAM
functions) to drive the six DUs. - EFIS 1
- Full reconfiguration capability. - ECAM
- Independence between EFIS and ECAM switching. - EFIS 2
• Benefits • After two failures (normal operation) or one failure (MEL
operation) the following functions remain available :
- Dispatchability.
- EFIS 1 or 2
- No operational degradation when a DMC fails or some
external computers fail (ADIRS, FWC, SDAC, etc.) - ECAM
- Copy of remaining EFIS on the opposite side.
STL 472.755/92 Issue 4 12.6

Reconfiguration possibilities - Architecture
STL 472.755/92 Issue 4 12.7

Reconfiguration - F/O on EFIS DMC3
STL 472.755/92 Issue 4 12.8

Reconfiguration - ECAM on DMC1 + F/O on EFIS DMC1
STL 472.755/92 Issue 4 12.9

DU reconfiguration
PFDU1 FAILED PFDU2 FAILED
PFDU NDU E/WDU NDU PFDU

1 1 2 2
E/W DU FAILED
SDU
E/W DU NOT FAILED

E/W DU NOT FAILED
E/W DU FAILED
E/W DU FAILED
PFD/ND PFD/ND
SWITCHING
ECAM/ WD XFR
NORM
CAP F/O
AUTO XFR
MANUAL XFR
STL 472.755/92 Issue 4 12.10

A330 electronic instrument system - EFIS
The EFIS (Electronic Flight Instrument System) is used The two NDs (Navigation Displays) provide medium-term
for flight operation. flight information :
The two PFDs (Primary Flight Displays) provide short- - location of the aircraft with respect to navigation aids :
term flight information : FMS flight plan and map data
- aircraft attitude - weather radar information.
- air speed
- altitude and vertical speed
- heading and track
- autoflight information
- vertical and lateral deviations
- radio NAV information.
PFD ND E/WD ND PFD

1 1 2 2
CAPT EFIS F/O EFIS
SD
ECAM
STL 472.755/92 Issue 4 12.11

Control panels
The capt and F/O control panels are part of the FCU ( Flight Control Unit)
SPD MACH HDG TRK ALT LWL/CH V/S FPA

LAT
CSTR WPT VOR.D NDB ARPT HDG V/S ARPT NDB VOR.D WPT CSTR
QFE QNH TRK FPA QFE QNH
ROSE NAV 40 40 ROSE NAV
VOR ARC 20 80 HDG V/S 100 1000 UP 20 80 VOR ARC
TRK FPA
In Hg hPa PUSH
In Hg hPa
LS PLAN 10 160 SPD METRIC 10 160 LS PLAN
MACH TO
ALT
LEVEL
PULL PULL
ENG 320 AP 1 AP 2 OFF 320 ENG
STD STD
DN
1 2 1 2
ADF VOR ADF VOR ADF VOR ADF VOR

FD LS LOC A/THR
ALT APPR LS FD
OFF OFF OFF OFF
Capt. EFIS control panel F/O EFIS control panel
Options keys
CSTR WPT VOR.D NDB ARPT

QFE QNH
ND mode
ROSE NAV 40
Control the display VOR ARC 20 80
ND range
of G/S and LOC In Hg hPa
LS PLAN 10 160
scales of the PFD PULL
STD ENG 320
1 2
VOR/ADF selector
Control the display ADF VOR ADF VOR
FD LS (ADF 2 optional on A330)
of the flight director OFF OFF
of the PFD
PFD Controls ND Controls
STL 472.755/92 Issue 4 12.12

PFD - Approach
Approach capability
and decision height
AP/FD and A/THR
engagement status
Selected altitude
VFE or actual configuration
Altitude indication
Speed trend
Target airspeed
Minimum selectable speed
Alpha protection speed
G/S and LOC scales
and DEV indexes.
Alpha max speed
Radio altitude Outer market “light”
ILS ident + freq Altimeter baro
setting display
ILS - DME distance
ILS course
STL 472.755/92 Issue 4 12.13

ND - ARC mode
GS 394 TAS 388 LMG 004°

249/16 93 NM
0 1
35 2
34 3 18:35
33 OL 4
CDN
ANG
AMB
AVD
240 240
CGC LMG TILT
-3,00
160 160
.2R
VOR1 GAI
CGCM
103 NM
STL 472.755/92 Issue 4 12.14

ND - ROSE/NAV mode
GS 200 TAS 210 TOE / 163°

210 / 20 10.5 NM
15 18 18 : 35 ETA
12
TOE
21
TOE 07
TS
9
24
QM33L Waypoint
LFBO
33L
6
Airport
5
27
3 10 TOU
30
0 33
Distance scale ADF 2
ADF 2
M TS M= manually tuned
STL 472.755/92 Issue 4 12.15

ND - PLAN mode
GS 394 TAS 388 BRACO / 097°

249/16 33 NM
18:35
N
GEN BRACO
FRZ
W RNC E
80
160
STL 472.755/92 Issue 4 12.16

ND - ROSE/ILS mode
GS 165 TAS 150 ILS APP ILS2 109.3

095/20 CRS 327°
24 TBN
Wind direction
21 27
Wind force
18
Glide deviation
30
Localizer deviation Glide scale
bar 15
33
12
0
9
VOR 1 3
M
TOU 6
VOR 1
M = manually tuned 15.3 NM
STL 472.755/92 Issue 4 12.17

ND - TCAS (optional)
GS 195 TAS 200 VOR APP D-LG 065°

280/20 6 5.8 NM
9 18:35
3
D-LG
12
FF33M
0
ATH Resolution Advisory :
-01
RED
LGAT
33R
Proximate intruder : 33
15
WHITE -11 + 09
Relative altitude/
vertical speed Traffic Advisory :
AMBER
18
30
2.5 nm range ring D130M

-03
Other intruders :
21
WHITE EMPTY 27
VOR 1
24
DDM
R
No bearing
intruders 12.5 NM 5.2NM + 10 12.4NM
STL 472.755/92 Issue 4 12.18

A330 electronic instrument system - ECAM
Arrangement
• ECAM (EFIS) colour symbology • ECAM displays arrangement
- Warnings : RED for configuration or failure requiring Upper DU Lower DU
immediate action.
- Engine primary indication - Aircraft system synoptic
- Cautions : AMBER for configuration or failure
- Fuel quantity information diagram or status messages.
requiring awareness but not immediate
- Slats/flaps position
action.
- Warning/Caution
- Indications : GREEN for normal long-term operations. or Memo messages.
WHITE for titling and guiding remarks.
BLUE for actions to be carried out or
limitations.
MAGENTA for particular messages, e.g.
inhibitions.
STL 472.755/92 Issue 4 12.21

Audible warning definition WARNING SIGNAL CONDITION DURATION SILENCING
CONTINUOUS RED WARNINGS PERMANENT Depress*

REPETITIVE CHIMIE MASTER WARN lt
SINGLE CHIME AMBER CAUTION 1/2 sec.

A/P DISCONNECTION Second push on
BY TAKE OVER pb 1.5 sec TAKE OVER pb
CAVALRY CHARGE Depress
A/P DISCONNECTION MASTER WARN lt
DUE TO FAILURE PERMANENT
or TAKE OVER pb
CLICK LANDING CAPABILITY 1/2 sec (3 pulses)

CHANGE
CRICKET NIL
STALL PERMANENT
+
“STALL” message
(synthetic voice)
INTERMITTENT SELCAL CALL PERMANENT Depress

BUZZER RESET key on ACP
CABIN CALL 3s NIL
EMER CABIN CALL 3s REPEATED NIL

3 TIMES
BUZZER
MECH CALL As long as outside NIL
pb pressed
ACARS * Message reading on MCDU
CALL or ALERT PERMANENT or Depress MASTER CAUT
1.5 sec new ALTITUDE

C CHORD ALTITUDE ALERT or selection or depress
PERMANENT MASTER WARN pb
AUTO CALL OUT HEIGHT
(synthetic voice) ANNOUNCEMENT PERMANENT NIL
BELOW 400 FT
GROUND PROXIMITY UNSAFE TERRAIN IN
WARNING CLEARANCE PERMANENT NIL
(synthetic voice) FORESEEN
“WINDSHEAR”
(synthetic voice) WINDSHEAR REPEATED 3 TIMES NIL
* All aural warnings may be cancelled by depressing “PRIORITY LEFT” 1 sec NIL
“PRIORITY RIGHT” A/PTAKE OVER pb
the EMER CANC pb on ECAM control panel or the
(synthetic voice)
MASTER WARN lt except for some warnings like
THRUST LEVER NOT PERMANENT THRUST LEVER
overspeed or L/G not down. “RETARD” (synthetic voice) IN IDLE POSITION
FOR LANDING
* If option is installed TCAS * TRAFFIC OR
POTENTIAL COLLISION PERMANENT NIL
(synthetic voice)
STL 472.755/92 Issue 4 12.22

Display unit Engine / warning display
ENGINES control indication

Total FUEL
FLAPS / SLATS position
MEMO WARNING/CAUTION messages

- Reminder of functions - Title of the failure
temporarily used under - Corresponding procedures
normal operation (actions to be performed)
- TO or LDG MEMO
(key items for TO or LDG)
MEMO
or
WARNING / CAUTION messages

Overflow symbol
System display
SYSTEM synoptics SYSTEM synoptics STATUS

corresponding to : Operational status of the
- Warning / caution situation
or aircraft after failure
- Advisory situation STATUS including recovery
- Crew manual selection procedures
- Current flight phase
Permanent data :
- TAT
- SAT
- UTC
- GW
- CG
TAT = 19°C G.W. 170300 KG
SAT = 18°C 17 H 03 C.G. 28.1 %
STL 472.755/92 Issue 4 12.23

E/WD - engines Typical
ECAM UPPER DISPLAY (E/WD)
6 6
10 N1 10
%
120 120
EGT
1222 °C 1222
N2 - ENGINE CONTROL PARAMETERS

102 % 102 - FUEL QUANTITY INDICATION
- FLAPS/SLATS POSITION
F.F
12250 KG/H 12250
FOB : 55200 KG
SEAT BELTS WING A.ICE
- MEMO INFORMATION
STL 472.755/92 Issue 4 12.24

S/D - A330 cruise page
System pages
14 system pages can be displayed :
- BLEED (Air bleed)
- COND (Air conditioning)
- PRESS (Cabin pressurization)
- ELEC AC (AC electrical power)
- ELEC DC (DC electrical power)
- C / B (Circuit breakers)
- F / CTL (Flight controls)
- FUEL (Fuel)
- HYD (Hydraulic)
- APU (Auxiliary power unit)
- ENGINE (Secondary engine parameters)
- DOOR / OXY (Doors / oxygen)
- WHEEL (Landing gear, braking, ground spoilers, etc.)
- CRUISE (Cruise)
STL 472.755/92 Issue 4 12.25

Control panel
Note : In the event of complete failure of the ECAM control panel electronics,
the CLR, RCL, STS, EMER CANC and ALL remain operative since the
contacts are directly wired to the FWCs/DMCs.
STL 472.755/92 Issue 4 12.26

Operating modes
• Four modes of ECAM system pages presentation :
NORMAL mode : automatic flight phase related mode :
- MEMO on E/WD
- most suitable system page on SD.
MANUAL mode : use of the ECAM control panel

- any of the system pages may be called-up on SD by
pressing the corresponding selector keys of the
ECAM control panel.
ADVISORY mode : parameter trend monitoring
- corresponding system page on SD with affected
parameter pulsing.
FAILURE RELATED mode :
- Failure indication and abnormal/emergency proce-
dures on E/WD
- affected system synoptic on SD.
STL 472.755/92 Issue 4 12.27

Automatic flight phase
Engine**
start
APU**
EIS
associated DOOR WHEEL ENGINE CRUISE WHEEL DOOR
system pages *FLT L/G EXTENDED
CTL PHASE 6 AND ALT < 15000ft
2nd ENG SHUT DOWN

OR
2nd ENG T.O. PWR NO TO PWR
1st ENG STARTED
1500 FT
TOUCH DOWN
800 FT
5MN AFTER
ELEC PWR
LIFT OFF
80 KTS
80 KTS
FWS
flight phases 1 2 3 4 5 6 7 8 9 10
* FLT CTL page replaces wheel page for 20 seconds when either sidestick is moved or when rudder
deflection is above 22°.
** APU page or ENG START page automatically displayed during start sequence.
STL 472.755/92 Issue 4 12.28

Failure-related mode
MASTER MASTER
CAUTION CAUTION
Engine / warning display System display
ENGINE control indication

Total FUEL
FLAPS / SLATS position

Corresponding system synoptic
with failure indication
Failure indication
corrective action
TAT + 19°C G.W. 170300 KG
SAT + 18°C 17 H 03 C.G. 28.1 %
CLR
STL 472.755/92 Issue 4 12.29

Architecture - Flight Warning System (FWS)
STL 472.755/92 Issue 4 12.30

• The FWS performs (in real time) the computation and

management of central warnings and cautions
- Warning/caution hierarchical classification (level 3 :
red warning, level 2 : amber caution, level 1 : simple
caution) and priority rules.
- Warning/caution inhibitions.
- Operational failure categorization : independent
failure, primary failure, secondary failure.
• The FWS directly activates the crew attention getters
(aural and visual) and uses the EIS (ECAM : E/WD and
SD) to display the warning/caution messages.
• The FWS also computes the MEMO information
(presented on the E/WD) and performs an automatic radio
height call-out function.
STL 472.755/92 Issue 4 12.31

STL 472.755/92 Issue 4
13. Radio management and
communication
STL 472.755/92 Issue 4 13.1

A330 radio management and communication
Radio Management Panel (RMP)
STL 472.755/92 Issue 4 13.2

Concept
• Radio Management Panel (RMP) system provides :
- crew control of all radio communication systems.
- back-up to the two FMGCs for controlling all radio

navigation systems.
• Basic installation includes :
- two RMPs on pedestal
- a third RMP on overhead panel (not available for

NAV back up).
• The ATC transponder is tuned by a separate

conventional control panel.
STL 472.755/92 Issue 4 13.3

RMP architecture
STL 472.755/92 Issue 4 13.4

Concept architecture
Communications tuning
Any communication receiver can be tuned from either of
the three RMPs. Either RMP can take over from the
other in the event of failure.
Navigation tuning
Three different operating modes exist :
• Automatic tuning : VOR/DME, ILS and ADF are

automatically controlled by the
FMGC.
• Manual tuning : for selection of a specific

frequency through the FMGC
MCDU which overrides the
automatic function of the FMGC.
• Back-up tuning : when both FMGCs are

inoperative, any NAV receiver
may be tuned by the crew from
RMP 1 or 2.
When one FMGC is inoperative, the remaining one

controls all receivers.
STL 472.755/92 Issue 4 13.5

COMM - Audio Control Panel (ACP)
STL 472.755/92 Issue 4 13.6

COMM - Audio system
The audio integrating system provides the management of
all audio signals produced by feeding the radio
communications, radio navigation and interphone systems :
• Basic installation includes :
- three Audio Control Panels (ACP) - two on pedestal,

one on overhead panel.
- one Audio Management Unit (AMU) in avionics bay.
- one SELCAL code selector in avionics bay.
• Provision exists for supplementary ACPs.
• All selections and volume adjustments are carried out by

the crew through ACPs.
• All ACPs are fitted for maximum capacity (three VHF, two
HF, public address, calls, two VOR, two ADF, ILS and
provision for MLS).
• Each ACP and associated AMU electronic card are fully

independent and microprocessor controlled.
• Optional : The Satellite Communication (SATCOM)

system allows the exchange of information between the
ground station and the aircraft (technical information,
voice transmission) via satellites.
STL 472.755/92 Issue 4 13.7

STL 472.755/92 Issue 4
A330 Central Maintenance System
STL 472.755/92 Issue 4 14.1

STL 472.755/92 Issue 4 14.2

A330 Central Maintenance System (CMS)
General
Line maintenance of the electronic systems is based on
the use of a Central Maintenance System (CMS).
The purpose of the CMS is to give maintenance

technicians a central maintenance aid to intervene at
system or subsystem level from multipurpose CDUs
located in the cockpit :
- to read the maintenance information.

- to initiate various tests.
Two levels of maintenance should be possible using the

CFDS :
- maintenance at an out-station (LRU change).

- maintenance in the hangar or at the main base
(troubleshooting).
STL 472.755/92 Issue 4 14.3

Architecture
CMC : Central Maintenance Computer

ACARS : Aircraft Communication And
Reporting System
VHF 3
PRINTER 3 * *
(A4 FORMAT) 2 ACARS MU DATA LOADER
MCDU 1
CMC 1 CMC 2
BITE
*
if installed
Aircraft Systems
STL 472.755/92 Issue 4 14.4
Advantage of the CMS
A revised maintenance concept provides a :
- reduction of the duration of operations

- reduction of the maintenance crew training time
- simplification of technical documentation
- standardization of the equipment
- simplification of the computers which no longer display
any BITE
Integration of the CMS
The CMS includes :
• Basic equipment
- the BITE (Built-In Test Equipment) for each electronic
system.
- two fully redundant Central Maintenance Computers
(CMCs).
- three MCDUs (Multipurpose Control Display Units)
- one printer.
• Optional equipment
- ACARS (Aircraft Communication And Reporting
System) which dialogue with the CMC for display of
information or initiation of tests.
- Data Loader which allows to upload data bases and
operational software or to download system reports
from various onboard computers.
STL 472.755/92 Issue 4 14.5

Example of use
STL 472.755/92 Issue 4 14.6

Example of use (cont’d)
MAINTENANCE CURRENT FLIGHT REPORT LEG-00
AIRCRAFT IDENTIFICATION / F-GGEA ENGINE ON/ENGINE OFF / 1015/1720 PRINTING

DATE / MAR31 DATE : APR02
TYC : 1406
FROM/TO : LFBO/LFBT
FLIGHT NUMBER : AIB
COCKPIT 1027
EFFECTS FAULTS
ATA 36-11 UTC : 1032 ATA 36-11-42 INERMITTENT CLASS 1

MESSAGE DISPLAYED FLIGHT PHASE : SOURCE : BMC3 IDENTIFIERS :
ENG 2 BLEED FAULT TAKEOFF ROLL MESSAGE : CP1C CPC2
THRM (5HA3)/FAN AIR-V
(12HA3)/SENSE LINE
ATA 30-11 UTC : 1033 ATA 36-11-16 HARD CLASS 1

MESSAGE DISPLAYED FLIGHT PHASE : SOURCE : PHC2 IDENTIFIERS :
ANTI-ICE F/O PROBE CLIMB MESSAGE : ADIRU1 ADIRU2
R STATIC PROBE (8DA2)/ ADIRU3
PHC2 (6DA2)
ATA 24-53 UTC : 1822 ATA 24-53-00 HARD CLASS 1

MESSAGE DISPLAYED FLIGHT PHASE : SOURCE : SDAC IDENTIFIERS :
ELEC AC 1.1 BUS FAULT CRUISE MESSAGES : CBMU
POWER SUPPLY INTERRUPT
STL 472.755/92 Issue 4 14.7

STL 472.755/92 Issue 4
AIRBUS
31707 Blagnac Cedex

France
Telephone 05 61 93 33 33
©Airbus Industrie 1999

All right reserved.
The statements made herein do not constitute an offer.
They are based on the assumptions shown and are
expressed in good faith. Where the supporting grounds for
these statements are not shown, the Company will be
pleased to explain the basis thereof.
This document is the property of Airbus Industrie and is
supplied on the express condition that it is to be treated as
confidential. No use or reproduction may be made thereof
other than that expressly authorised.
Printed in France
STL 472.755/92 Issue 4

A330 Flight Deck and Systems Briefing

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What are the main systems covered in the document?

What are the main systems covered in the document?

What is the Central Maintenance System (CMS) and what are its main components?

What is the Central Maintenance System (CMS) and what are its main components?

AIRBUS

IT MUST NOT BE USED AS AN OFFICIAL REFERENCE.

FOR TECHNICAL DATA OR OPERATIONAL PROCEDURES,

STL 472.755/92 issue 4 March 1999

STL 472.755/92 Issue 4

STL 472.755/92 Issue 4 1.1

18 sleeperette 42 Business 196 Economy

10.7m A330-300 295 seats

A330 fuselage cross-section

10.7m Lower cargo holds

compatible with existing

STL 472.755/92 Issue 4 1.2

• The design combines high technology developed for

PW 4168 PW 4164 / 4168

• Certification basis includes : Underfloor cargo From 27LD3 to 32/33LD3/11 pallets

STL 472.755/92 Issue 4 1.3

STL 472.755/92 Issue 4 1.4

Inner tank LH 42 000 11 095 41 904 11 070

Total 139 090 36 745 97 286 25 700

Tyres radial - main gear 1400 mm x 530 mm x R23

A330-200 CG limits A330-300 CG limits

STL 472.755/92 Issue 4 1.6

Minimum turning radius R3

Type of turn 1 Type of turn 2 Type of turn 1 Type of turn 2

STL 472.755/92 Issue 4 1.7

STL 472.755/92 Issue 4 2.1

First officer's sidestick

Captain's sidestick Sliding window

Coat room/ Fourth

STL 472.755/92 Issue 4 2.2

Roller sunblind Checklist stowage

STL 472.755/92 Issue 4 2.3

RAIN REPELLENT BOTTLE

STL 472.755/92 Issue 4 2.4

• Windows are designed to meet or exceed the

Pilots’ vision envelope

Aerospace standard 580 B Pilot’s axis

STL 472.755/92 Issue 4 2.5

Pilot’s eye position

STL 472.755/92 Issue 4 2.6

A330-300 2.1° 38.2 120 120 240 243

2.1°pitch Pilot’s eyes

STL 472.755/92 Issue 4 2.7

STL 472.755/92 Issue 4 2.8

• The main features are common with those developed for

- sidestick controllers which leave the main instrument

• The other features evolve directly from the concepts

- ergonomic layout of panels, synoptically arranged

STL 472.755/92 Issue 4 2.9

Pitch adjustment The handgrip includes two switches :

STL 472.755/92 Issue 4 2.10

• Accuracy of movements is very precise since

STL 472.755/92 Issue 4 2.11

STL 472.755/92 Issue 4 2.12

STL 472.755/92 Issue 4 2.13

STL 472.755/92 Issue 4 2.14