Page 1 FOR INFORMATIONAL PURPOSES ONLY. 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 472.502/90 Issue 6 January 2000 STL 472.502/90 Issue 6...
Page 2 STL 472.502/90 Issue 6...
Page 3: Table Of Contents
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 (APU) 10. Automatic Flight System 11. Environmental Control System 12. Electronic Instrument System (EIS) 13.
Page 4 STL 472.502/90 Issue 6...
Page 5: General
1. General STL 472.502/90 Issue 6...
Page 6 A340 General General arrangement Typical cabin layout A340-300 illustrated below A340-200 239 seats 16 sleeperette 42 Business class 181 Economy (62 in pitch) (40 in pitch) (32 in pitch) 295 seats A340-300 18 sleeperette 49 Business class 228 Economy (62 in pitch)
Page 7 Basic data Introduction • The ultra-long-range A340 is an all-new, wide-body, four-engine, twin-aisle aircraft. It is offered in two A340-300 A340-200 models, the -200 and -300 whose length is increased by two four-frame fuselage plugs. 275 000 kg MTOW* 275 000 kg...
Page 8 A340 General Aircraft design specifications 1. Design weights 4. Structural life (design aims) (see page 1.3) The objectives for primary structure fatigue life are based 2. Design speeds on the average block time of 4 hours, as follows : 330 kt CAS - Design life goal ………………………….
Page 9 Max ramp weight and max aft CG. A340 Flexible pavement Rigid pavement model Cat A Cat B Cat C Cat D Cat A Cat B Cat C Cat D A340-200 A340-300 Tire radials - 1400 mm x 530 mm x R23 STL 472.502/90 Issue 6...
Page 10 In typical airline long-range configuration, with typical international reserves and 200 nm alternate, the range is as follows : - A340-200 three-class : 239 passengers + baggage 8 000nm nominal - A340-300 three-class : 295 passengers + baggage 7 300nm nominal...
Page 11 A340 General Performance with CFM56-5C2 powerplants, rated at 31 200lb slst A340-200 takeoff A340-300 takeoff STL 472.502/90 Issue 6 1.7A...
Page 12 A340 General Performance with CFM56-C3 powerplants, rated at 32 500lb slst A340-200 takeoff A340-300 takeoff STL 472.502/90 Issue 6 1.7B...
Page 13 A340 General Performance with CFM56-5C4 powerplants, rated at 34 000lb slst A340-200 takeoff A340-300 takeoff STL 472.502/90 Issue 6 1.7C...
Page 14 A340 General Performance with CFM56-5C2/5C3 A340-200 initial cruise altitude A340-300 initial cruise altitude STL 472.502/90 Issue 6 1.8A...
Page 15 A340 General Performance with CFM56-5C4 A340-200 initial cruise altitude A340-300 initial cruise altitude STL 472.502/90 Issue 6 1.8B...
Page 16 A340 General Weight and balance A340-200 CG limits A340-300 CG limits STL 472.502/90 Issue 6...
Page 17 Minimum turning radii (with tire slip) and minimum pavement width for a 180° turn are as illustrated. Type of turn 1 Type of turn 2 Type of turn 1 Type of turn 2 A340-200 A430-300 Effective turn angle Effective turn angle Effective turn angle Effective turn angle 77.95°...
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Page 19: Flight Deck Layout
2. Flight Deck Layout STL 472.502/90 Issue 6...
Page 20 A340 Flight Deck Layout General provisions • As the A340 is a long-range aircraft the cockpit fully provides for a 3rd occupant seat, and a folding 4th occupant seat. • In addition, an optional crew rest compartment, Captain's sidestick First officer's sidestick adjacent to the cockpit, is available in place of a galley.
Page 21 A340 Flight Deck Layout Forward view FO boomset stowage Overhead outlet Assist handle Ceiling light Reading light Sliding tables FO boomset jack panel Window control Escape rope stowage handle Loudspeakers Sidestick Nose wheel steering CTL Hand microphone Ashtray Checklist stowage Roller sunblind Oxygen mask Oxygen mask...
Page 22 A340 Flight Deck Layout Rear view : Right aft corner RAIN REPELLENT BOTTLE OXY MASK (OPTION) 4th OCCUPANT CONSOLE Rear view : left aft corner OXY MASK LIFE VEST LIFE VEST JACK PANEL COCKPIT LIGHTING OCCUPANT HEADSET COAT STOWAGE CONSOLE BOOMSET SPARE BULB BOX PRINTER PAPER ROLL STOWAGE...
Page 23 A340 Flight Deck Layout 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 10 20 30 40 50°...
Page 24 A340 Flight Deck Layout Pilots’ field of vision STL 472.502/90 Issue 6...
Page 25 CAT II (DH = 100 ft) θ Aircraft • This geometry improves external aircraft monitoring, thereby increasing safety standards. - Downward visibility in the pilot axis is 20°. A340-200 3.7° m (ft) (394) - Wing tips visible from respective pilot seats. (30)
Page 26 A340 Flight Deck Layout Control and indication panels (shaded) STL 472.502/90 Issue 6...
Page 27 A340 Flight Deck Layout Main features • The main features, shared with those developed for the A320/A321/A330 family are: - Sidestick controllers which leave the main instrument panel unobstructed. - Six interchangeable and switchable display units (DU) which are integrated into the same system architecture (EFIS/ECAM).
Page 28 A340 Flight Deck Layout Sidestick arrangement • Sidesicks are installed on the Captain’s and First Officer’s forward lateral consoles. • To facilitate control, a dual pivot adjustable armrest with position indicators is fitted on each seat behind the sidestick. Pitch adjustment The handgrip includes two switches : - A/P disconnect/sidestick priority pushbutton Displays...
Page 29 A340 Flight Deck Layout Sidestick operation • Control of the flight path is performed by the • Moving the sidestick results in “setting the aircraft trajectory” with a certain level of “g” for the requested Electronic Flight Control System (EFCS) which links maneuver, depending on the amount of sidestick the trajectory order with aerodynamic data to stabilize the aircraft and protect it from prohibited attitudes.
Page 30 A340 Flight Deck Layout Main instrument panels STL 472.502/90 Issue 6 2.12...
Page 31 A340 Flight Deck Layout Captain and First Officer panels • The CAPT and F/O panels are mirror images of each • The ND offers up to three modes : other : Both incorporate two side-by-side Display Units (DUs) - ROSE mode (ILS, VOR or NAV) : Aircraft symbol (7.25 in x 7.25 in) : in screen center, with radar availability - ARC mode : Heading up, horizon limited to a 90°...
Page 32 A340 Flight Deck Layout STL 472.502/90 Issue 6 2.14...
Page 33 A340 Flight Deck Layout Main center panel The center panel includes : - Two DUs, above other, which interchangeable with the CAPT and F/O DUs : • Engine Display (DU 1), showing the: - Main engine parameters (N1, EGT, N2) - N1 limit, N1 command - Total fuel - Flaps and slats position...
Page 34 A340 Flight Deck Layout Glareshield • The Flight Control Unit (FCU) provides short-term • The EFIS control panels designed for the: interface between the Flight Management and Guidance Computer (FMGC) and crew for the: - Selection of desired ND modes (ROSE-ILS, -VOR, - NAV, ARC, PLAN, ENG) and ranges - Engagement of A/P, A/THR - Selection of baro settings.
Page 35 A340 Flight Deck Layout Switching control Central pedestal panel In addition to the thrust levers and the engine control ECAM Multipurpose Multipurpose control panel functions, the main features on the pedestal are the: - Multipurpose Control and Display Units (MCDU) for flight management functions and various other functions such as data link, maintenance, etc.
Page 36 Flight control controls. Fuel EVAC Cargo Electrics air cond. • The pushbutton philosophy is identical to that already Emer elec applied on previously existing Airbus aircraft. GPWS Cargo smoke RCDR Oxygen Air conditioning Ventilation Calls Engine start Anti ice Cabin press...
Page 37: Electrical System
3. Electrical System STL 472.502/90 Issue 6...
Page 38 A340 Electrical System Electrical power generation The electrical power generation is comprised of : • Four engine-driven AC generators, nominal power 75 kVA. • One auxiliary power unit (APU) AC generator nominal 115 kVA. • One emergency generator Constant Speed Motor /Generator) (CSM/G), nominal power 5.5 kVA, hydraulically driven by the Green system.
Page 39 A340 Electrical System Distribution - normal configuration AC distribution network • In normal configuration, each engine-driven generator supplies its associated AC BUS. • The AC ESS BUS is normally supplied from AC BUS 1-1. DC distribution network • In normal configuration, normal DC systems are split into two networks : DC BUS 1 in parallel with DC BAT BUS and DC BUS 2.
Page 40 A340 Electrical System Distribution - abnormal configurations Generator failure If one generator fails, another will automatically take over : • If APU is operative, APU generator will take over. • If APU generator is not available, the same side, external generator will take over.
Page 41 A340 Electrical System Control and display Overhead panel ECAM STL 472.502/90 Issue 6...
Page 42 A340 Electrical System 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. •...
Page 43: Hydraulic System
4. Hydraulic System STL 472.502/90 Issue 6...
Page 44 A340 Hydraulic System Architecture STL 472.502/90 Issue 6...
Page 45 A340 Hydraulic System General • Abnormal operation : • Three fully independent systems : Green, Blue, Yellow (nominal pressure at 3000 psi). - In the event of engine 1 or 4 failure, the Green electrical pump runs automatically for 25 seconds, •...
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Page 47 5. Flight Controls - EFCS STL 472.502/90 Issue 6...
Page 48 A340 Flight Controls - EFCS Electronic Flight Control System (EFCS) Surfaces : • All hydraulically activated • All electrically controlled • Mechanical back-up control : - Rudder - Trimmable Horizontal Stabilizer (THS). STL 472.502/90 Issue 6...
Page 49 A340 Flight Controls - EFCS General The A340 fly-by-wire system was designed and certificated to make this new aircraft more cost effective, more pleasant to fly, and more comfortable than conventional aircraft. Basic principles • A340 flight control surfaces are all : - Electrically controlled - Hydraulically activated.
Page 50 A340 Flight Controls - EFCS Computers Cockpit controls Electrical control of the main surfaces is achieved by two Each pilot has a sidestick controller to exercise control types of computers : of pitch and roll. The two sidestick controllers are not coupled •...
Page 51 A340 Flight Controls - EFCS Power sources Electrical power supply The flight control computers PRIM, SEC and FCDC 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...
Page 52: Flight Controls
A340 Flight Controls - EFCS 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 4) - driven pumps 1 electropump 1 RAT Yellow 1 engine (N° 3) - driven pump 1 electropump Blue 1 engine (N°...
Page 53 A340 Flight Controls - EFCS Safety objectives Safeguards were designed to protect against : Loss of pitch control - extremely improbable (<10 Loss of elevators - extremely remote (< 10 Loss of roll control - extremely improbable Permanent loss of THS - extremely improbable Rudder loss or runaway - extremely improbable To satisfy these objectives, the following architecture applies: - Electrical signalling for spoilers, elevators and ailerons...
Page 54 A340 Flight Controls - EFCS Dispatch objectives The basic objective is to allow aircraft dispatch with a peripheral or computer failure, in order to increase dispatch reliability without impairing flight safety. Systems Dispatch situation 3 IRS Maximum 1 inoperative or “off” 2 yaw rate gyros 3 PRIM 2 SEC...
Page 55 A340 Flight Controls - EFCS Design principles The two secondary computers (SEC) : Two types of flight control computers : • Are able to process direct laws only • PRIM (two channels with different software for control/monitoring). • Either SEC can be the master, in case of loss of all primary computers SEC (two channels with different software for control/monitoring).
Page 56 A340 Flight Controls - EFCS Schematic diagram STL 472.502/90 Issue 6 5.10...
Page 57 A340 Flight Controls - EFCS EFCS - Computers and actuators SPD-BRK SPD-BRK GND-SPLR GND-SPLR ROLL ROLL AILERONS AILERONS OUTBOARD INBOARD INBOARD OUTBOARD SPOILERS SPOILERS S1 P1 P2 S1 P1 P2 S2 P3 P3 P3 P3 S2 P2 P1 S1 P1 P2 S2 THS HYDRAULIC MOTORS...
Page 58 A340 Flight Controls - EFCS Pitch control STL 472.502/90 Issue 6 5.12...
Page 59 A340 Flight Controls - EFCS Pitch control Pitch control is provided by two elevators and the THS : The THS is driven by two hydraulic motors supplied by - Elevator deflections 30° nose up - 15° nose down Blue and Yellow systems ; these motors are controlled - THS deflections 14°...
Page 60 A340 Flight Controls - EFCS Roll control STL 472.502/90 Issue 6 5.14...
Page 61 A340 Flight Controls - EFCS Roll control In the event of a failure being detected on one spoiler, Roll control is provided by two ailerons and five spoilers the opposite spoiler is retracted and maintained in a (2 to 6) per wing : retracted position.
Page 62 A340 Flight Controls - EFCS Yaw control STL 472.502/90 Issue 6 5.16...
Page 63 A340 Flight Controls - EFCS Yaw control Yaw control is provided by one rudder surface : In case of total loss of electrical power or total loss of Rudder deflection ± 31.6°. flight controls computers, the Back Up Yaw Damper Unit (BYDU) becomes active.
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Page 65 A340 Flight Controls - EFCS Additional functions devoted to ailerons and spoilers Six spoilers and two pairs of ailerons perform these Ailerons functions in the following priority order : Ailerons receive commands for the following additional • The roll demand has priority over the speedbrake function.
Page 66 A340 Flight Controls - EFCS Slats/flaps controls STL 472.502/90 Issue 6 5.20...
Page 67 A340 Flight Controls - EFCS Slats/flaps • Wing Tip Brakes, (WTB) installed within the torque • High lift control is achieved on each wing by : shaft system and controlled by the SFCC, prevent - Seven leading edge slats, asymmetric operation, blow back, or runaway. - Two trailing edge flaps, - Two ailerons (ailerons droop function).
Page 68 A340 Flight Controls - EFCS Slats/flaps control STL 472.502/90 Issue 6 5.22...
Page 69 A340 Flight Controls - EFCS Controls and displays - Flap control lever position is processed by the SFCC. • Overhead panel Pushbutton switches on the overhead panel allow It allows selection of high-lift configurations for slats and flaps. Lever position indication is repeated in the disconnection or reset of the primary and secondary “flap section”...
Page 70 A340 Flight Controls - EFCS ECAM system page STL 472.502/90 Issue 6 5.24...
Page 71 A340 Flight Controls - EFCS Control law introduction • Flight through computers • Mechanical back-up During a complete loss of electrical power, the Depending upon the EFCS status, the control law is : aircraft is controlled by : - Longitudinal control through trim wheel, - Normal Law (normal conditions even after single - Lateral control from pedals.
Page 72 A340 Flight Controls - EFCS Normal Law - flight mode Basic principle Feedback computer Computer Side order stick F/CTL computer Feedback Surface Response Pilot's command • Highlights - No direct relationship between sidestick and control surface deflection. - The sidestick serves to provide overall command objectives in all three axes.
Page 73 A340 Flight Controls - EFCS Normal Law - flight mode Objectives • Adapting objectives to : • Pitch axis : Ground phase : ground mode Sidestick deflection results in a change of vertical - Direct relationship between stick and elevator load factor.
Page 74 A340 Flight Controls - EFCS Normal Law - flight mode 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 : •...
Page 75 A340 Flight Controls - EFCS 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.
Page 76 A340 Flight Controls - EFCS High speed protection High angle-of-attack protection • Design aims • Design aims To protect the aircraft against speed overshoot - Protection against stall - Ability to reach and hold a high CL angle (sidestick above V Non-interference with flight at V fully back), without exceeding stall angle (typically 3°/5°...
Page 77 A340 Flight Controls - EFCS Pitch attitude protection High angle-of-attack protection • Design aim • Principle To enhance the effectiveness of AOA and high-speed When the AOA(*) is greater than AOA prot, the basic protection in extreme conditions and in windshear objective defined by sidestick input reverts from encounter.
Page 78 A340 Flight Controls - EFCS 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 -...
Page 79 A340 Flight Controls - EFCS Alternate Law Direct Law • Probability objective : 10 /flight hour (10 under • Probability objective : 10 /flight hour (10 under MMEL). MMEL). • No change for ground, takeoff and flare mode • No change for ground mode and takeoff mode compared to Normal Law.
Page 80 A340 Flight Controls - EFCS Control law reconfiguration summary Control law Pitch Lateral Normal Type A Type A Alternate Type A Type A/B Direct Type B Type B STL 472.502/90 Issue 6 5.34...
Page 81 A340 Flight Controls - EFCS 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 Damper Unit (BYDU).
Page 82 A340 Flight Controls - EFCS 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 Bank angle protection...
Page 83 A340 Flight Controls - EFCS Control law status information Crew information : PFD speed scale STL 472.502/90 Issue 6 5.37...
Page 84 A340 Flight Controls - EFCS Priority logic • Normal operation : Captain and First Officer inputs are algebraically summed up to applicable limits. • Autopilot disconnect pushbutton is used as priority take-over button. • Last pilot who depresses and holds priority take-over button has priority ;...
Page 85 A340 Flight Controls - EFCS Priority display logic Captain's side First Officer’s side Sidestick Annunciation Annunciation Sidestick Sidestick Take-over button CAPT deflected depressed Green Take-over button Sidestick depressed in neutral “Light off” Sidestick Take-over button deflected depressed Green Sidestick Take-over button in neutral depressed “Light off”...
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Page 87: Landing Gear
6. Landing Gear STL 472.502/90 Issue 6...
Page 88 A340 Landing Gear Left intentionally blank STL 472.502/90 Issue 6...
Page 89 A340 Landing Gear Main features • Conventional landing gear with single bogie nose gear, an outer gear and a double bogie main landing gear, with direct-action shock absorbers. • The main landing gear is also provided with a shock absorber extension/retraction system. •...
Page 90 A340 Landing Gear STL 472.502/90 Issue 6...
Page 91 A340 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 signaled ; - Electrically signalled through antiskid valves ; - Hydraulically controlled with brake pressure - Individual wheel antiskid control ;...
Page 92 A340 Landing Gear Antiskid system schematic AUTO/BRK A/C LONGITUDINAL A/C SPEED DECELERATION AFTER IMPACT DECEL DECEL DECEL (ADIRU) (WHEEL SPEED) γ ir γ prog BSCU γ γ Vo - ir .t Vo - prog .t HIGHEST VALUE AUTO BRAKE V ref RELEASE RELEASE ORDER...
Page 93 A340 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%.
Page 94 A340 Landing Gear Nose gear steering principle A/SKID & N/W STRG BSCU NON TOWING POSITION OPEN AUTO PILOT NLG DOWNLOCKED AND COMPRESSED LGCIU 1/2 NLG DOWNLOCKED AND BOOGIES IN GROUND POS CHANNEL 1 GREEN POWER FROM NOSE GEAR DOORS CLOSING STEERING SERVO CIRCUIT (WHEN VALVE...
Page 95 A340 Landing Gear Controls and displays Rudder pedals Nosewheel handle STL 472.502/90 Issue 6...
Page 96 A340 Landing Gear ECAM system page STL 472.502/90 Issue 6 6.10...
Page 97: Fuel System
7. Fuel System STL 472.502/90 Issue 6...
Page 98 A340 Fuel System Basic layout Tank arrangement • Total fuel capacity USABLE FUEL Total Total Outer Inner Center TRIM without witht tanks tanks TANK tanks ACTs ACTs ACTs 3650x2 42775x2 41560 6230 140640 155040 (liters) 7200x2 VOLUME (US gallons) 964x2 11301x2 10979 1902x2...
Page 99 A340 Fuel System Control and monitoring The Fuel System is automatically controlled by the Fuel Control and Monitoring System (FCMS). The FCMS operates in a fully automatic mode. Two identical Fuel Control and Monitoring Computers (FCMC) provide : - Fuel quantity measurement and indication ; - Fuel transfer control ;...
Page 100 A340 Fuel System Engine feed With fuel in the center tank and CTR TK pumps • In normal operation, each engine is independently running, both inner inlet valves used supplied by a continuously operating booster pump, independently to cycle the inner tank contents located in a dedicated collector box.
Page 101 A340 Fuel System Jettison system • The jettison pipe is connected to the refuel gallery in each wing. A dual actuator jettison valve is fitted. • Fuel is simultaneously jettisoned from the center and inner tanks. All cross-feed valves open automatically. All normal and STBY pumps are running and a forward transfer into center tank is initiated.
Page 102 A340 Fuel System Center of Gravity control band relative to operational flight envelope STL 472.502/90 Issue 6...
Page 103 A340 Fuel System CG Control • Automatic control CG begins when climbing through - If the center tank is not empty, fuel is transferred by FL255 and is terminated when descending through FL the trim tank forward transfer pump from the trim tank 245 or when FMGS time to destination is below 75 to the center tanks through the auxiliary forward minutes.
Page 104 A340 Fuel System Controls and displays STL 472.502/90 Issue 6...
Page 105 A340 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 On Board (FOB) is permanently displayed on upper ECAM DU.
Page 106 A340 Fuel System Refueling system STL 472.502/90 Issue 6 7.10...
Page 107 A340 Fuel System Refueling • Two standard 2.5 inch couplings are installed under the each wing. When both couplings are used, refueling time at nominal pressure (50psi) is approximately 33 minutes. • An isolation valve is provided between each pair of couplings and the refueling gallery.
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Page 109: Engine Controls
8. Engine Controls STL 472.502/90 Issue 6...
Page 110 A340 Engine Controls FADEC The engine shut-down rate, resulting from FADEC • Thrust control is operated through Full Authority Digital failures, will be at least as good as today’s latest Engine Control (FADEC) computers which : hydro-mechanical systems with supervisory override.
Page 111 A340 Engine Controls - CFM56 FADEC architecture STL 472.502/90 Issue 6...
Page 112 A340 Engine Controls FADEC and EIU One FADEC is 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 CFM56.
Page 113 A340 Engine Controls Thrust control system • Engine thrust control is provided by the FADEC 1, 2, 3 • Limit thrust parameters are computed by the FADEC. and 4, controlling engines 1, 2, 3 and 4 respectively. • Since there is no mechanization of the thrust levers (no •...
Page 114 A340 Engine Controls Thrust control operations STL 472.502/90 Issue 6...
Page 115 A340 Engine Controls Indications on ECAM upper DU Indications on PFD : FMA • The following indications may appear in the upper left corner of the PFD flight mode annunciator, (examples) : • ASYM : One thrust lever not in CL detent. •...
Page 116 A340 Engine Controls Thrust reverser • Reverser deployment selection is performed through conventional reverser controls. • If an outer engine reverser is inoperative, an interlock system prevents the deployment of the opposite thrust reverser. • At full aft throttle position, maximum reverse power is automatically limited, depending on ambient conditions.
Page 117: Auxiliary Power Unit (Apu)
9. Auxiliary Power Unit (APU) STL 472.502/90 Issue 6...
Page 118 A340 Auxiliary Power Unit General principles System display • On ground, the APU renders the aircraft independent - 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 for engine start.
Page 119 A340 Auxiliary Power Unit Controls and display STL 472.502/90 Issue 6...
Page 120 STL 472.502/90 Issue 6...
Page 121: Automatic Flight System
10. Automatic Flight System STL 472.502/90 Issue 6 10.1...
Page 122 A340 Automatic Flight System Architecture block diagram ADR / IR Primary Secondary ILS (MLS) Flight controls Flight controls ECAM FMGC Maintenance EFIS ATSU (option) CLOCK ACARS (option) Back-up FCMC DATA BASE LOADER LGCIU Thrust levers FADECs SFCC STL 472.502/90 Issue 6 10.2...
Page 123 A340 Automatic Flight System Architecture components Unit Number per aircraft Comments FMGC FMGEC 1 includes AFS/FIDS* Includes three independent channels MCDU Color display A/THR instinctive One for CM 1 and one for CM 2 disconnect switches AP take-over switches One for CM 1 and one for CM 2 North reference switches For EIS and MCDU display FM source switch...
Page 124 A340 Automatic Flight System Flight Management Guidance and Envelope System (FMGS) crew interface Navigation Primary Flight Navigation Primary Flight Display Display Display Display STL 472.502/90 Issue 6 10.4...
Page 125 A340 Automatic Flight System FMGS - AFS/FMS integration • The FMGS is made up of two computers (FMGC) including a management portion (FM), a flight guidance portion (FG) and a flight envelope portion (FE). This pilot interactive system provides : - Flight management for navigation, performance prediction and optimization, navigation radio aids tuning, and information display management,...
Page 126 A340 Automatic Flight System FMGS crew interface • Two PFDs and two NDs provide visual interface with • Three MCDUs (only two at a time) on the central flight management and guidance-related data such as : pedestal provide a long-term interface between the crew and the FMGECs, in terms of : On the PFD : - Flight plan definition and display,...
Page 127 A340 Automatic Flight System 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) Optimized performance (speed/altitude, prediction) Vertical profile...
Page 128 A340 Automatic Flight System - Guidance Function Flight Control Unit (FCU) STL 472.502/90 Issue 6 10.8...
Page 129 A340 Automatic Flight System - Guidance Function AP/FD modes Mode engagement (or arming as long as engagement Available modes conditions are not met) : Guidance Managed mode Selected mode - By pushbutton action (located on the FCU) LOC - APPR - ALT, AP1 - AP2 - A/THR. Lateral HDG - TRK B/C*, B/C, LOC*, LOC...
Page 130 A340 Automatic Flight System - Guidance Function AP/FD operation Lateral modes NAV : Lateral navigation • The aircraft can be operated in ‘selected guidance’ with flight references selected by the crew, or in ‘managed • Lateral track is defined by the FMGC, according to the guidance’...
Page 131 A340 Automatic Flight System - Guidance Function Vertical modes Common modes Approach • ILS available : Level changes [managed guidance (CLB, DES), selected - GLIDE capture and track, guidance (OP CLB, OP DES)]. - FLARE, - LAND, • In CLB/DES modes vertical path is maintained as - ROLL-OUT.
Page 132 A340 Automatic Flight System - Autothrust Function AP/FD and A/THR mode interaction 1st case : AP/FD pitch mode controls a vertical flight path (V/S or G/S or FINAL,) then A/THR mode controls the target speed/Mach. e.g. If AP/FD V/S mode is selected, then A/THR is in SPEED mode.
Page 133 A340 Automatic Flight System - Autothrust Function AP/FD and A/THR SPD/MACH modes 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. •...
Page 134 A340 Automatic Flight System - Autothrust Function A/THR operation - A/THR can be armed, active or de-activated STL 472.502/90 Issue 6 10.14...
Page 135 A340 Automatic Flight System - Autothrust Function 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.
Page 136 A340 Automatic Flight System - Autothrust Function A/THR mechanization The thrust levers can only be moved manually by the Cruise pilot. Thrust levers must be set : Takeoff - To be CLB detent Thrust mode selection : - To the MCT detent (engine failure case). - On ground TO limit mode is automatically selected at - The A/THR modes become active according to power up.
Page 137 A340 Automatic Flight System - Flight Management Flight envelope protection Flight envelope protection is achieved by generating maximum and minimum selectable speeds, windshear warning and aft CG warning. Also computed as part of this protection are the maneuvering speed and the flap and slat retraction speeds.
Page 138 A340 Automatic Flight System - Flight Management General architecture EFIS CP 1 EFIS CP 2 AP CONTROLS FMGC 1 FMGC 2 FIDS MCDU 1 MCDU 2 MCDU 3 BACK UP NAV BACK UP NAV MCDU 3 switchable for FM function, in case of MCDU 1 or 2 failure STL 472.502/90 Issue 6 10.18...
Page 139 A340 Automatic Flight System - Flight Management Functional architecture - Normal configuration STL 472.502/90 Issue 6 10.19...
Page 140 A340 Automatic Flight System - Flight Management Functional architecture - One FMGC failed Functional architecture - Normal configuration Functional architecture - One MCDU failed STL 472.502/90 Issue 6 10.20...
Page 141 A340 Automatic Flight System - Flight Management Two FMGCs associated to two MCDUs provide a redundant configuration. • Normal mode operation : dual mode crosstalk FMGC 1 FMGC 2 buses - Each FMGC makes its own computation. - One FMGC is master - the other one is slave. - Both FMGCs are synchronized.
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Page 143 A340 Automatic Flight System - Flight Management Position indication STL 472.502/90 Issue 6 10.23...
Page 144 A340 Automatic Flight System - Flight Management MCDU STL 472.502/90 Issue 6 10.24...
Page 145 A340 Automatic Flight System - Flight Management Lateral navigation • Position computation : • The FMGC position is associated with a high or low criterion, which is based on an Estimated Position - Before flight, the three IRSs are aligned on airfield Error (EPE).
Page 146 A340 Automatic Flight System - Flight Management Radio navigation architecture Radio navigation Each FMGC tunes its own side radio navaids, except when in single operation : - One VOR, one ILS, one ADF (if belonging to the F- RADIO NAV FMGC 2 FMGC 1 PLN) and five DMEs may be autotuned at the...
Page 147 A340 Automatic Flight System - Flight Management 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.
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Page 149 A340 Automatic Flight System - Flight Management Back-up NAV function • A back-up source of navigation is available in the MCDU 1 and the MCDU 2, to cover FMS failure cases. • No database 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...
Page 150 A340 Automatic Flight System - Flight Management Flight plan aspects • Flight plan optimization through the performance • Advisory functions : database : - Fuel planning ; - Optimum speeds ;. - Optimum altitude and step climb ; - Optimum and maximum recommended altitudes ; - Ttime/distance/EFOB to enroute diversion airfields.
Page 151 A340 Automatic Flight System - Flight Management Vertical profile • Takeoff • Descent SRS control law maintains V2 + 10 up to thrust Top of Descent (T/D) is provided on ND. reduction altitude where max climb thrust is applied. V2 From T/D down to the highest altitude constraint, + 10 is held up to acceleration altitude (ACC ALT).
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Page 153: Environmental Control System
11. Environmental Control System STL 472.502/90 Issue 6 11.1...
Page 154 A340 Environmental Control System Air conditioning schematic STL 472.502/90 Issue 6 11.2...
Page 155 A340 Environmental Control System Air conditioning The hot compressed air is cooled, conditioned and The trim air system has several features to ensure that delivered to the fuselage compartments and then no substantial comfort degradation occurs in case of discharged overboard through two outflow valves. trim air valve or hot air valve failure;...
Page 156 A340 Environmental Control System Air conditioning - Air bleed STL 472.502/90 Issue 6 11.4...
Page 157 A340 Environmental Control System Pneumatic • Pressurized air is supplied for air conditioning, air starting, wing anti-ice, water pressurization and hydraulic reservoir pressurization. • System operation is electrically monitored 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.
Page 158 A340 Environmental Control System Avionics ventilation STL 472.502/90 Issue 6 11.6...
Page 159 A340 Environmental Control System Ventilation • Battery ventilation • Avionics ventilation Provided by ambient air being drawn around the Provides ventilation and cooling of avionics and batteries and then vented directly outboard via a electronic equipment under digital control (without any venturi.
Page 160 A340 Environmental Control System Cabin pressure control STL 472.502/90 Issue 6 11.8...
Page 161 A340 Environmental Control System Pressurization • The pressurization control system is fully automatic. • It is a dual system, with automatic switchover after failure. Each system is alternatively used from one flight to the other. Two outflow valves are operated by any of three independent electric motors.
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Page 163: Electronic Instrument System (Eis)
12. Electronic Instrument System (EIS) STL 472.502/90 Issue 6 12.1...
Page 164 A340 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 E/WD Loudspeaker EFIS switching EFIS switching Loudspeaker ECAM switching...
Page 165 A340 Electronic Instrument System General The Electronic Instrument System (EIS) performs a display function for : • Flight operation : EFIS (Electronic Flight Instrument System located on each crewmember's instrument panel : - 1 PFD (Primary Flight Display) - 1 ND (Navigation Display) •...
Page 166 A340 Electronic Instrument System EFIS / ECAM architecture STL 472.502/90 Issue 6 12.4...
Page 167 A340 Electronic Instrument System Components • DU (Display Unit) Display function - Six identical full-color DUs - 7.25in x 7.25in case size - Symbol generator resident in DU • DMC (Display Management Computer) Acquisition and processing functions - Three identical DMCs - Each DMC has two independent channels : EFIS/ECAM - Each DMC is able to drive all six DUs with four...
Page 168 A340 Electronic Instrument System Architecture Availability objectives • Fully redundant EIS architecture : • With one DMC and one DU failed, all functions remain available : Partitioned DMCs (3 EFIS functions/3 ECAM functions) to drive the 6 DUs : - EFIS 1, - Full reconfiguration capability ;...
Page 169 A340 Electronic Instrument System Reconfiguration possibilities - Architecture STL 472.502/90 Issue 6 12.7...
Page 170 A340 Electronic Instrument System Reconfiguration - F/O on EFIS DMC3 STL 472.502/90 Issue 6 12.8...
Page 171 A340 Electronic Instrument System Reconfiguration - ECAM on DMC1 + F/O on EFIS DMC1 STL 472.502/90 Issue 6 12.9...
Page 172 A340 Electronic Instrument System DU reconfiguration STL 472.502/90 Issue 6 12.10...
Page 173 A340 Electronic Instrument System - EFIS The EFIS (Electronic Flight Instrument System) is used The two NDs (Navigation Displays) provide medium-term for flight operations. 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 ;...
Page 174 A340 Electronic Instrument System - EFIS Control panels STL 472.502/90 Issue 6 12.12...
Page 175 A340 Electronic Instrument System - EFIS PFD - Approach Approach capability and decision height AP/FD and A/THR engagement status Selected altitude 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 Outer market “light”...
Page 176 A340 Electronic Instrument System - EFIS ND - ARC mode LMG 004° 249/16 18:35 TILT -3,00 VOR1 CGCM 103 NM STL 472.502/90 Issue 6 12.14...
Page 177 A340 Electronic Instrument System - EFIS ND - ROSE/NAV mode STL 472.502/90 Issue 6 12.15...
Page 178 A340 Electronic Instrument System - EFIS ND - PLAN mode BRACO / 097° 249/16 33 NM 18:35 BRACO STL 472.502/90 Issue 6 12.16...
Page 179 A340 Electronic Instrument System - EFIS ND - ROSE/ILS mode STL 472.502/90 Issue 6 12.17...
Page 180 A340 Electronic Instrument System - EFIS ND - TCAS (optional) VOR APP 065° T AS D-LG 280/20 8 NM 18:35 D-LG FF33M Resolution Advisory : AT H LGAT Proximate intruder : WHITE + 09 Relative altitude/ Traffic Advisory : vertical speed AMBER 2.5 nm range ring D130M...
Page 181 A340 Electronic Instrument System - EFIS ND - EGPWS (optional) + 2000 ft + 2000 ft + 1000 ft + 1000 ft Aircraft elevation Aircraft elevation - 250 ft when gear down - 250 ft when gear down - 500 ft when gear up - 500 ft when gear up - 1000 ft - 1000 ft...
Page 182 A340 Electronic Instrument System - ECAM General • The ECAM (Electronic Centralized Aircraft Monitor) is used for systems operation. • ECAM is based on the “need to know” concept. System data is displayed only when required. - Data processing is fully automatic and, as such, does not require any additional crew action or selection.
Page 183 A340 Electronic Instrument System - ECAM Arrangement • ECAM (EFIS) color philosophy • ECAM displays arrangement : - Warnings : RED for configuration or failure Upper DU Lower DU requiring immediate action. - Engine primary indication, - Aircraft system - Cautions : AMBER for configuration or failure - Fuel quantity information, synoptic diagram or...
Page 184 A340 Electronic Instrument System - ECAM Audible warning definition WARNING SIGNAL CONDITION DURATION SILENCING Depress* CONTINUOUS RED WARNINGS PERMANENT MASTER WARN lt REPETITIVE CHIME AMBER CAUTION 1/2 sec SINGLE CHIME Second push on A/P DISCONNECTION TAKEOVER pb 1.5 sec BY TAKE OVER pb CAVALRY CHARGE Depress A/P DISCONNECTION...
Page 185 A340 Electronic Instrument System - ECAM Display unit STL 472.502/90 Issue 6 12.23...
Page 186 A340 Electronic Instrument System - ECAM E/WD Typical ECAM UPPER DISPLAY (E/WD) - ENGINE CONTROL PARAMETERS - FUEL QUANTITY INDICATION - FLAPS/SLATS POSITION - MEMO INFORMATION STL 472.502/90 Issue 6 12.24...
Page 187 A340 Electronic Instrument System - ECAM S/D - A340 cruise page System pages ECAM LOWER DISPLAY (SD) 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)
Page 188 A340 Electronic Instrument System - ECAM 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 472.502/90 Issue 6 12.26...
Page 189 A340 Electronic Instrument System - ECAM Operating modes • Four ECAM system page presentation modes: 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.
Page 190 A340 Electronic Instrument System - ECAM Automatic flight phase Engine** start APU** DOOR WHEEL ENGINE CRUISE WHEEL DOOR associated system pages *FLT L/G EXTENDED PHASE 6 AND ALT < 15000ft NO TO PWR flight phases FLT CTL page replaces wheel page for 20 seconds when either sidestick is moved or when rudder deflection is above 22°.
Page 191 A340 Electronic Instrument System - ECAM Failure-related mode STL 472.502/90 Issue 6 12.29...
Page 192 A340 Electronic Instrument System Architecture - Flight Warning System (FWS) STL 472.502/90 Issue 6 12.30...
Page 193 A340 Electronic Instrument System • 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.
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Page 195: Radio Management And Communication
13. Radio Management and Communication STL 472.502/90 Issue 6 13.1...
Page 196 A340 Radio Management and Communication Radio Management Panel (RMP) STL 472.502/90 Issue 6 13.2...
Page 197 A340 Radio Management and Communication Concept • The 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 ;...
Page 198 A340 Radio Management and Communication RMP architecture STL 472.502/90 Issue 6 13.4...
Page 199 A340 Radio Management and Communication 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 : •...
Page 200 A340 Radio Management and Communication COMM - Audio Control Panel (ACP) STL 472.502/90 Issue 6 13.6...
Page 201 A340 Radio Management and Communication COMM - Audio system The audio integrating system provides the management of audio signals produced, feeding radio communications, radio navigation and interphone systems : • Basic installation includes : - Three Audio Control Panels (ACP) : Two on pedestal, one on overhead panel ;...
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Page 203: Central Maintenance System (Cms)
14. A340 Central Maintenance System (CMS) STL 472.502/90 Issue 6 14.1...
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Page 205 A340 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 ;...
Page 206 A340 Central Maintenance System Architecture : Central Maintenance Computer ACARS : Aircraft Communication And Reporting System VHF 3 PRINT ER ACARS MU DAT A LOADER (A4 FORMAT ) MCDU CMC 1 CMC 2 BIT E if installed Aircraft S ystems STL 472.502/90 Issue 6 14.4...
Page 207 A340 Central Maintenance System Advantage of the CMS • Optional equipment A revised maintenance concept provides a : - ACARS (Aircraft Communication And Reporting System) which dialogue with the CMC to display - Reduction in the duration of operations ; information or initiate tests.
Page 208 A340 Central Maintenance System Examples of use 14.6 STL 472.502/90 Issue 6...
Page 209 A340 Central Maintenance System Examples 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 1027 COCKPIT EFFECTS FAULTS INTERMITTENT...
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Page 211 Company will be pleased to explain the basis thereof. This document is the property of Airbus Industrie and is supplied on the expressed condition that it is to be treated as confidential. No use or reproduction may be made thereof other than that expressly authorized.

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