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STL 472.502/90 Issue 6

A340 Flight Controls - EFCS

5.23

Controls and displays

•

Overhead panel

Pushbutton switches on the overhead panel allow
disconnection or reset of the primary and secondary
computers. They provide local warnings. Side 1
computer switches on the left-hand side are separated
from those of side 2 computers on the right-hand side.

•

Glareshield

Captain and First Officer priority lights, located in the
glareshield, provide indication if either has taken the
priority for his sidestick orders.

•

Lateral consoles

Captain and First Officer sidesticks, located on the
lateral consoles, provide the EFCS 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.

- 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 takeoff. They permit manual pitch trim
control.

•

Main instrument panel

ECAM display units and PFDs present warnings and
status information of the Flight control system.
Permanent indication of slat and flap positions are given
on the ECAM engine/warning display. Remaining flight
control surface positions are given on the FLT/CTL
system page, which is presented on the ECAM
system/status display.

•

Rudder pedals

Interconnected pedals on each crewmember’s side
allow mechanical yaw control through the rudder.

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Содержание A340 Series

Страница 1: ...Pilots THIS BROCHURE IS ISSUED 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 T...

Страница 2: ...STL 472 502 90 Issue 6...

Страница 3: ...m 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 Sys...

Страница 4: ...STL 472 502 90 Issue 6...

Страница 5: ...STL 472 502 90 Issue 6 1 General 1 1...

Страница 6: ...patible with existing worldwide air cargo system General arrangement A340 300 illustrated below 1 2 Typical cabin layout 239 seats A340 200 16 sleeperette 62 in pitch 42 Business class 40 in pitch 181...

Страница 7: ...enance System CMS Since its introduction in early 1993 the aircraft has been the most advanced long range airliner offering a major stride forward in airline profitability Certification basis includes...

Страница 8: ...ign speed VFE kt CAS 4 Structural life design aims The objectives for primary structure fatigue life are based on the average block time of 4 hours as follows Design life goal 20000 flights Threshold...

Страница 9: ...Cat C 65 65 Cat D 76 76 Rigid pavement Flexible pavement ACN Aircraft design specifications 7 Fuel capacity Center tank Inner tank LH Inner tank RH Outer tank LH Outer tank RH Trim tank ACTS Total 41...

Страница 10: ...erves 200nm alternate 0 2 000 4 000 6 000 8 000 10 000 0 40 80 120 0 20 40 295 passengers Payload tonnes 1 000lb Range nm A340 300 275t 1 ACT 7 300nm 295 passengers 19 3t cargo Performance payload ran...

Страница 11: ...STL 472 502 90 Issue 6 A340 General Performance with CFM56 5C2 powerplants rated at 31 200lb slst A340 200 takeoff A340 300 takeoff 1 7A...

Страница 12: ...STL 472 502 90 Issue 6 A340 General Performance with CFM56 C3 powerplants rated at 32 500lb slst A340 200 takeoff A340 300 takeoff 1 7B...

Страница 13: ...STL 472 502 90 Issue 6 A340 General Performance with CFM56 5C4 powerplants rated at 34 000lb slst A340 200 takeoff A340 300 takeoff 1 7C...

Страница 14: ...STL 472 502 90 Issue 6 A340 General Performance with CFM56 5C2 5C3 A340 200 initial cruise altitude A340 300 initial cruise altitude 1 8A...

Страница 15: ...STL 472 502 90 Issue 6 A340 General Performance with CFM56 5C4 A340 200 initial cruise altitude A340 300 initial cruise altitude 1 8B...

Страница 16: ...STL 472 502 90 Issue 6 A340 General Weight and balance A340 200 CG limits A340 300 CG limits 1 9...

Страница 17: ...118 78 99 51 115 06 Meter 12 66 45 23 27 23 43 22 32 65 38 61 Feet 41 54 148 23 89 34 141 22 107 11 126 69 Type of turn 2 Effective turn angle 61 5 Type of turn 1 Effective turn angle 77 95 Type of t...

Страница 18: ...STL 472 502 90 Issue 6...

Страница 19: ...STL 472 502 90 Issue 6 2 Flight Deck Layout 2 1...

Страница 20: ...features Two crew bunks Two folding tables dining places A wardrobe and baggage stowage area Direct view into the cockpit yet complete separation for effective crew rest Direct access to the cockpit...

Страница 21: ...jack panel Reading light Window control handle Loudspeakers Nose wheel steering CTL Checklist stowage Oxygen mask Air conditioning outlet Waste bin Normal checklist storage Briefcase stowage Window ou...

Страница 22: ...BOTTLE OPTION OXY MASK LIFE VEST 3rd OCCUPANT CONSOLE OXY MASK LIFE VEST JACK PANEL HEADSET BOOMSET 4th OCCUPANT CONSOLE AXE L G LOCKING PINS BOX BOX AVIONIC BAY LIGHTING AND 28VDC 115VAC SOCKETS DOC...

Страница 23: ...shield panels flat glass Lateral windows curved acrylic Pilots vision envelope 2 5 Pilots field of vision 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 0 10 20 30 50 4...

Страница 24: ...STL 472 502 90 Issue 6 A340 Flight Deck Layout 2 6 Pilots field of vision...

Страница 25: ...his geometry improves external aircraft monitoring thereby increasing safety standards Downward visibility in the pilot axis is 20 Wing tips visible from respective pilot seats Aircraft A340 200 m ft...

Страница 26: ...STL 472 502 90 Issue 6 A340 Flight Deck Layout Control and indication panels shaded 2 8...

Страница 27: ...her features evolve directly from the concepts introduced with the A300 A310 family including the Ergonomic layout of panels synoptically arranged according to frequency of use normal abnormal emergen...

Страница 28: ...teral consoles To facilitate control a dual pivot adjustable armrest with position indicators is fitted on each seat behind the sidestick The handgrip includes two switches A P disconnect sidestick pr...

Страница 29: ...ck movement Accuracy of movements is very precise since backlash and friction are negligible 2 11 Control of the flight path is performed by the Electronic Flight Control System EFCS which links the t...

Страница 30: ...STL 472 502 90 Issue 6 A340 Flight Deck Layout 2 12 Main instrument panels...

Страница 31: ...n 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 T...

Страница 32: ...STL 472 502 90 Issue 6 A340 Flight Deck Layout 2 14...

Страница 33: ...nd 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 Memo and warning System Display DU 2 showing An aircraft system syno...

Страница 34: ...uter FMGC and crew for the Engagement of A P A THR Selection of required guidance modes Manual selection of flight parameters SPD MACH ALT V SPD HDG or track The EFIS control panels designed for the S...

Страница 35: ...ng control panel ECAM control panel Power levers In addition to the thrust levers and the engine control functions the main features on the pedestal are the Multipurpose Control and Display Units MCDU...

Страница 36: ...ght is mainly for a small maintenance panel corresponding to some maintenance controls The pushbutton philosophy is identical to that already applied on previously existing Airbus aircraft RCDR Oxygen...

Страница 37: ...STL 472 502 90 Issue 6 3 Electrical System 3 1...

Страница 38: ...tatic inverter fed by two batteries and working either on ground or when CSM G inoperative Two ground connectors power 90 kVA DC network supplied via two main Transformer Rectifier Units TR 200 A and...

Страница 39: ...DC systems are split into two 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 allow...

Страница 40: ...case of a total loss of all main generators The EMER GEN will deliver 5 5 kVA since the Green hydraulic system is still powered by engine driven pumps or In case of loss of all engines The EMER GEN w...

Страница 41: ...STL 472 502 90 Issue 6 A340 Electrical System 3 5 Control and display Overhead panel ECAM...

Страница 42: ...ed on the ECAM Computer resets can be performed via system controls C B ECMU1 VOLT SNSG SFCC1 NORM DCBUS AVAI HYD PUMP G ENG2 ANTI ICE ENG2 DU SWTG CAPT ND HYD PUMP B ENG2 ADIRU1 155VAC ANTI ICE PITOT...

Страница 43: ...STL 472 502 90 Issue 6 4 Hydraulic System 4 1...

Страница 44: ...STL 472 502 90 Issue 6 A340 Hydraulic System 4 2 Architecture...

Страница 45: ...ectrical pumps RAT monitoring etc manual override is available on the overhead panel one handpump on the Yellow system for cargo doors operation when no electrical power is available Abnormal operatio...

Страница 46: ...STL 472 502 90 Issue 6...

Страница 47: ...STL 472 502 90 Issue 6 5 Flight Controls EFCS 5 1...

Страница 48: ...0 Issue 6 A340 Flight Controls EFCS 5 2 Electronic Flight Control System EFCS Surfaces All hydraulically activated All electrically controlled Mechanical back up control Rudder Trimmable Horizontal St...

Страница 49: ...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 indi...

Страница 50: ...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 isolatio...

Страница 51: ...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...

Страница 52: ...reen Yellow Blue power the flight controls Note The distribution to the various control surfaces is designed to cover multiple failure cases System circuit Green Yellow Blue Power source 2 engine N 1...

Страница 53: ...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 To satisfy these objectives...

Страница 54: ...fety Systems 3 IRS 2 yaw rate gyros 3 PRIM 2 SEC 3 ADR 3 IR 2 Nz accelerometers 2 FCDC 3 PRIM 2 SEC Electro hydraulic and electro actuators Dispatch situation Maximum 1 inoperative or off Maximum 1 in...

Страница 55: ...then execute them on their related servo loop 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 mal...

Страница 56: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 10 Schematic diagram...

Страница 57: ...2 B Y THS HYDRAULIC MOTORS L ELEV B G R ELEV G Y 1 2 3 P1 P2 P3 MECH CONT P1 P2 S1 S2 P2 P1 S2 S1 ELECTRICAL MOTORS S2 S1 P1 S1 P3 S2 G Y YAW DAMPER ACTUATOR MECH CONT G Y B TRV LIM RUDDER 1 2 1 2 RUD...

Страница 58: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 12 Pitch control...

Страница 59: ...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 p...

Страница 60: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 14 Roll control...

Страница 61: ...n some failure cases the outboard aileron is centered to prevent any twisting moment In manual mode above 190 KT in CONF 0 the outboard ailerons are centered Each spoiler is driven by one electro hydr...

Страница 62: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 16 Yaw control...

Страница 63: ...ed 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 position va...

Страница 64: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 18 Left intentionally blank...

Страница 65: ...g additional functions Maneuver Load Alleviation Spoilers 4 5 and 6 max 9 deflection symmetrically Ground spoiler functions Spoilers 1 to 6 35 max for spoiler 1 50 max for spoilers 2 to 6 Speedbrake f...

Страница 66: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 20 Slats flaps controls...

Страница 67: ...s 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 Feedback Position Pick off U...

Страница 68: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 22 Slats flaps control...

Страница 69: ...brake control A ground spoiler position commands ground deceleration Rudder trim switch and reset pushbutton switch are processed by the secondary computers The local rudder trim position indication i...

Страница 70: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 24 ECAM system page...

Страница 71: ...r single failure of sensors electrical system hydraulic system or flight control computer According to the number and nature of subsequent failures it automatically reverts to Alternate Law or Direct...

Страница 72: ...ick and control surface deflection The sidestick serves to provide overall command objectives in all three axes Computers command surface deflections to achieve Normal Law objectives if compatible wit...

Страница 73: ...a given relationship Pedal input stick free results in stabilized sideslip and bank angle facilitates de crabbing in crosswind Adapting objectives to Ground phase ground mode Direct relationship betwe...

Страница 74: ...ized sideslip and bank angle Slowly diverging heading Safe flight Short term recommended action Zero sideslip or target take off with pedals Then stabilize heading with stick input Steady flight with...

Страница 75: ...on does not mean limitation of pilot authority Full pilot authority prevails within the normal flight envelope Whatever the sidestick deflection computers have scheduled protections which overcome pil...

Страница 76: ...L angle sidestick fully back without exceeding stall angle typically 3 5 below stall angle good roll maneuverability and innocuous flight characteristics Elimination of stall risk in high dynamic mane...

Страница 77: ...When angle of attack protection is triggered max bank angle is limited to 45 Low energy warning A low energy aural warning SPEED SPEED SPEED is triggered to inform the pilot that the aircraft energy...

Страница 78: ...aw to Alternate or Direct Law according to the number and nature of subsequent failures Normal Control Law Pitch Direct Law Alternate Control Law Mechanical back up Failures at least two failures seco...

Страница 79: ...configuration dependent Protections Pitch attitude lost High speed replaced by static stability High angle of attack replaced by static stability Vc prot law aural stall warning when sw Low energy lo...

Страница 80: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 34 Control law reconfiguration summary Control law Normal Alternate Direct Pitch Type A Type A Type B Lateral Type A Type A B Type B...

Страница 81: ...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...

Страница 82: ...manently informed of control law status on PFD Normal Law Normal FMA indications Alternate Law Normal FMA indications Direct Law Normal FMA indications USE MAN PITCH TRIM Pitch attitude protection Ban...

Страница 83: ...STL 472 502 90 Issue 6 A340 Flight Controls EFCS 5 37 Control law status information Crew information PFD speed scale...

Страница 84: ...ilot who depresses and holds priority take over button has priority other pilot s inputs ignored Priority annunciation In front of each pilot on glareshield ECAM message Audio warning Normal control r...

Страница 85: ...er s side Annunciation Sidestick Annunciation Sidestick CAPT F O Green Light off Red Red Light off Green Red Red Sidestick deflected Sidestick in neutral Take over button depressed Take over button de...

Страница 86: ...STL 472 502 90 Issue 6...

Страница 87: ...STL 472 502 90 Issue 6 6 Landing Gear 6 1...

Страница 88: ...STL 472 502 90 Issue 6 A340 Landing Gear 6 2 Left intentionally blank...

Страница 89: ...ard 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 b...

Страница 90: ...STL 472 502 90 Issue 6 A340 Landing Gear 6 4...

Страница 91: ...ithout antiskid 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...

Страница 92: ...A C LONGITUDINAL DECELERATION ADIRU A C SPEED AFTER IMPACT WHEEL SPEED ir Vo prog Vo ir t Vo prog t HIGHEST VALUE OFF ON AUTO BRAKE V ref RELEASE ORDER RELEASE ORDER IF WHEEL SPD 0 88 V ref OR BLUE H...

Страница 93: ...rs open this servovalve which is also modulated by antiskid closing signals Autobrake system From touchdown a specific speed is computed based on touchdown speed wheels and programmed deceleration low...

Страница 94: ...3 0 10 10 30 50 70 P R I M AUTO PILOT NOSE GEAR STEERING SERVO VALVE STEERING SELECTOR VALVE NWS ANGLE GREEN POWER FROM NOSE GEAR DOORS CLOSING CIRCUIT WHEN DOORS ARE CLOSED CHANNEL 1 LGCIU 1 2 2 AND...

Страница 95: ...STL 472 502 90 Issue 6 A340 Landing Gear 6 9 Controls and displays Rudder pedals Nosewheel handle...

Страница 96: ...STL 472 502 90 Issue 6 6 10 A340 Landing Gear ECAM system page...

Страница 97: ...STL 472 502 90 Issue 6 7 Fuel System 7 1...

Страница 98: ...NACA inlets Location of ducts and float valves is designed to ensure free venting over appropriate attitude ranges during refueling and normal ground and flight maneuvers Pressure relief outlets prot...

Страница 99: ...uel Control and Monitoring Computers FCMC provide Fuel quantity measurement and indication Fuel transfer control Center of gravity control Level sensing Fuel temperature indication Refuel control Airc...

Страница 100: ...er from center to inner tanks is initiated provided either center tank pump pushbutton is selected on With fuel in the center tank and CTR TK pumps running both inner inlet valves are used independent...

Страница 101: ...pumps are running and a forward transfer into center tank is initiated The aircraft weight will be reduced at a rate approximately 1000 kg per minute excluded fuel burn Jettison is stopped when The cr...

Страница 102: ...STL 472 502 90 Issue 6 A340 Fuel System 7 6 Center of Gravity control band relative to operational flight envelope...

Страница 103: ...ed pumps In this case cross feed valves 2 and 3 are open Aft transfer is terminated when Computed CG target CG 0 5 or When an inner tank reaches the low level Forward transfer Forward transfer is requ...

Страница 104: ...STL 472 502 90 Issue 6 A340 Fuel System 7 8 Controls and displays...

Страница 105: ...ystem 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 Crossfeed valves...

Страница 106: ...STL 472 502 90 Issue 6 A340 Fuel System 7 10 Refueling system...

Страница 107: ...ution 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 Refueling defu...

Страница 108: ...STL 472 502 90 Issue 6...

Страница 109: ...STL 472 502 90 Issue 6 8 Engine Controls 8 1...

Страница 110: ...uplicated 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...

Страница 111: ...STL 472 502 90 Issue 6 A340 Engine Controls CFM56 8 3 FADEC architecture...

Страница 112: ...6 Dual redundancy for electrical input devices ADIRS 1 2 TLAs engine parameters Dual redundancy for electrical part of control actuator Simplex system for hydro mechanical parts of the control Fault t...

Страница 113: ...mode A THR function of the FMGS when in automatic mode but limited to the value corresponding to the thrust levers position Limit thrust parameters are computed by the FADEC Since there is no mechaniz...

Страница 114: ...STL 472 502 90 Issue 6 A340 Engine Controls 8 6 Thrust control operations...

Страница 115: ...r not in CL detent CLB Flashing when aircraft is above thrust reduction altitude and thrust levers are not retarded to CL MCT Flashing in the case of engine failure if the non affected thrust levers a...

Страница 116: ...ough 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...

Страница 117: ...STL 472 502 90 Issue 6 9 Auxiliary Power Unit APU 9 1...

Страница 118: ...ther by using the aircraft 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 T...

Страница 119: ...STL 472 502 90 Issue 6 A340 Auxiliary Power Unit 9 3 Controls and display...

Страница 120: ...STL 472 502 90 Issue 6...

Страница 121: ...STL 472 502 90 Issue 6 10 Automatic Flight System 10 1...

Страница 122: ...tem 10 2 Architecture block diagram ADR IR ILS MLS ADF RA VOR DME CLOCK FCMC DATA BASE LOADER LGCIU SFCC FCU Primary Secondary Flight controls ECAM Maintenance EFIS CPC ATSU option ACARS option Thrust...

Страница 123: ...independent channels Color display One for CM 1 and one for CM 2 One for CM 1 and one for CM 2 For EIS and MCDU display For EIS display Unit Number per aircraft Comments Fault isolation and Detection...

Страница 124: ...472 502 90 Issue 6 A340 Automatic Flight System 10 4 Flight Management Guidance and Envelope System FMGS crew interface Primary Flight Display Navigation Display Navigation Display Primary Flight Disp...

Страница 125: ...lay 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 guidan...

Страница 126: ...and the FMGCs Four thrust levers linked to the FMGCs and FADECs provide the crew with autothrust or manual thrust control Two PFDs and two NDs provide visual interface with flight management and guida...

Страница 127: ...nvelope protection windshear aft CG detection Speed computation Flight management Functional architecture Navigation Flight planning functions assembly fuel management lateral revision Optimized perfo...

Страница 128: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Guidance Function 10 8 Flight Control Unit FCU...

Страница 129: ...conditions are not met By pushbutton action located on the FCU LOC APPR ALT AP1 AP2 A THR By action on the thrust levers On the ground setting the thrust levers to the TO GA or FLEX TO detents leads t...

Страница 130: ...t any time actions are acknowledged on the FCU itself and on the FMA Flight Mode Annunciator Selected guidance or managed guidance is available for SPEED MACH control LATERAL guidance and LEVEL CHANGE...

Страница 131: ...s vertical path is maintained as defined by the FMGC taking into account the flight plan constraints inserted in the system and the clearance altitude selected on the FCU OP CLB OP DES mode allows uni...

Страница 132: ...controls the target speed Mach e g If AP FD V S mode is selected then A THR is in SPEED mode 2nd case AP FD pitch mode controls the target speed Mach then A THR mode controls the thrust e g If AP FD o...

Страница 133: ...over altitude is automatically provided Manual SPD MACH selection is available to the pilot via the SPD MACH conversion pushbutton AP FD and A THR SPD MACH modes SPEED MACH managed or selected may eit...

Страница 134: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Autothrust Function 10 14 A THR operation A THR can be armed active or de activated...

Страница 135: ...ically 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 c...

Страница 136: ...MCT detent Notes In both cases this maneuver also engages FD TO mode SRS RWY if ILS selected The lowest FLX TO thrust is limited to CL thrust Cruise Thrust levers must be set To be CLB detent To the M...

Страница 137: ...mum 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 The alpha floor signal is computed...

Страница 138: ...ht Management 10 18 General architecture MCDU 3 switchable for FM function in case of MCDU 1 or 2 failure FIDS FM BACK UP NAV FE Com Mon EFIS CP 1 EFIS CP 2 AP CONTROLS FMGC 1 FCU FM FMGC 2 MCDU 1 BAC...

Страница 139: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Flight Management 10 19 Functional architecture Normal configuration...

Страница 140: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Flight Management 10 20 Functional architecture One FMGC failed Functional architecture Normal configuration Functional architecture One MCDU failed...

Страница 141: ...independently entries are auto matically transmitted on the other MCDU and applied to both FMGCs Independent mode Automatically operative if mismatch occurs between the FMGCs Independent operation of...

Страница 142: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Flight Management 10 22 Left intentionally blank...

Страница 143: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Flight Management 10 23 Position indication...

Страница 144: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Flight Management 10 24 MCDU ND...

Страница 145: ...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 the availability of navaids and sensors FMGC automati...

Страница 146: ...otune frequency course priority is Manual tune Specified navaid for approach Radio position computation Display purpose logic Five DMEs can be scanned simultaneously One DME for display purposes Two D...

Страница 147: ...m radio and inertial sensor mixing Provision for GPS and MLS Flight plan stringing Flight plan definition by company route or city pair Departure and arrival procedures including associated speed alti...

Страница 148: ...STL 472 502 90 Issue 6 A340 Automatic Flight System Flight Management 10 28 Left intentionally blank...

Страница 149: ...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 m...

Страница 150: ...ights 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...

Страница 151: ...of Descent T D is provided on ND From T D down to the highest altitude constraint ECON descent speed is held by the elevator and IDLE thrust by the A THR If this status can no longer be held or mainta...

Страница 152: ...STL 472 502 90 Issue 6...

Страница 153: ...STL 472 502 90 Issue 6 11 Environmental Control System 11 1...

Страница 154: ...STL 472 502 90 Issue 6 A340 Environmental Control System 11 2 Air conditioning schematic...

Страница 155: ...control system Hot air is delivered to the air supply ducts through the related zone trim air valves The trim air valves are controlled through the temperature requirements of each zone and duplicated...

Страница 156: ...STL 472 502 90 Issue 6 A340 Environmental Control System 11 4 Air conditioning Air bleed...

Страница 157: ...lic 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...

Страница 158: ...STL 472 502 90 Issue 6 A340 Environmental Control System 11 6 Avionics ventilation...

Страница 159: ...under floor valve in flight Manual control partially opens the overboard valve fan failure or cockpit smoke removal Pack bay ventilation Maintains a mean temperature compatible with the structure cons...

Страница 160: ...STL 472 502 90 Issue 6 A340 Environmental Control System 11 8 Cabin pressure control...

Страница 161: ...valves are associated with the automatic controllers In normal operation cabin altitude and rate of change are automatically controlled from FMGC flight plan data Cruise flight level landing field el...

Страница 162: ...STL 472 502 90 Issue 6...

Страница 163: ...STL 472 502 90 Issue 6 12 Electronic Instrument System EIS 12 1...

Страница 164: ...ay Master warning and caution lights Primary flight display EFIS switching Loudspeaker ECAM switching ECAM control panel EFIS control panel Navigation display Master warning and caution lights Primary...

Страница 165: ...cated on each crewmember s instrument panel 1 PFD Primary Flight Display 1 ND Navigation Display System operation ECAM Electronic Centralized Aircraft Monitor On the center instrument panel for both c...

Страница 166: ...STL 472 502 90 Issue 6 A340 Electronic Instrument System 12 4 EFIS ECAM architecture...

Страница 167: ...s able to drive all six DUs with four independent formats PFD ND E WD SD SDAC System Data Acquisition Concentrator Two identical SDACs The SDACs are connected to the DMCs and FWCs FWC Flight Warning C...

Страница 168: ...and ECAM switching Benefits Dispatchability No operational degradation when a DMC fails or some external computers fail ADIRS FWC SDAC etc With one DMC and one DU failed all functions remain available...

Страница 169: ...STL 472 502 90 Issue 6 A340 Electronic Instrument System 12 7 Reconfiguration possibilities Architecture...

Страница 170: ...STL 472 502 90 Issue 6 A340 Electronic Instrument System 12 8 Reconfiguration F O on EFIS DMC3...

Страница 171: ...STL 472 502 90 Issue 6 A340 Electronic Instrument System 12 9 Reconfiguration ECAM on DMC1 F O on EFIS DMC1...

Страница 172: ...STL 472 502 90 Issue 6 A340 Electronic Instrument System 12 10 DU reconfiguration...

Страница 173: ...Aircraft attitude Air speed Altitude and vertical speed Heading and track Autoflight information Vertical and lateral deviations Radio NAV information The two NDs Navigation Displays provide medium t...

Страница 174: ...STL 472 502 90 Issue 6 12 12 A340 Electronic Instrument System EFIS Control panels...

Страница 175: ...tude Altitude indication G S and LOC scales and DEV indexes Altimeter baro setting display Approach capability and decision height VFE or actual configuration Speed trend Alpha max speed Radio altitud...

Страница 176: ...02 90 Issue 6 12 14 A340 Electronic Instrument System EFIS ND ARC mode 33 34 35 0 1 2 3 4 OL CDN ANG AMB AVD CGC LMG TILT 3 00 2R GAI VOR1 CGCM 103 NM 240 160 240 160 GS 394 TAS 388 249 16 LMG 004 93...

Страница 177: ...STL 472 502 90 Issue 6 12 15 A340 Electronic Instrument System EFIS ND ROSE NAV mode...

Страница 178: ...STL 472 502 90 Issue 6 12 16 A340 Electronic Instrument System EFIS ND PLAN mode GS 394 388 249 16 BRACO 097 33 NM 18 35 N GEN BRACO FRZ RNC E S 160 W 80 TAS...

Страница 179: ...STL 472 502 90 Issue 6 12 17 A340 Electronic Instrument System EFIS ND ROSE ILS mode...

Страница 180: ...fic Advisory AMBER Proximate intruder WHITE Relative altitude vertical speed 2 5 nm range ring Other intruders WHITE EMPTY No bearing intruders GS T AS 195 200 280 20 8 NM 5 18 35 5 NM 12 5 2NM 10 12...

Страница 181: ...ument System EFIS ND EGPWS optional 2000 ft 2000 ft 1000 ft 1000 ft Aircraft elevation Aircraft elevation 250 ft when gear down 500 ft when gear up 250 ft when gear down 500 ft when gear up 1000 ft 10...

Страница 182: ...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 Permanent displ...

Страница 183: ...s but not immediate action Indications GREEN for normal long term operations WHITE for titling and guiding remarks BLUE for actions to be carried out or limitations MAGENTA for particular messages e g...

Страница 184: ...FT UNSAFE TERRAIN CLEARANCE FORESEEN WINDSHEAR A P TAKEOVER pb THRUST LEVER NOT IN IDLE POSITION FOR LANDING TRAFFIC OR POTENTIAL COLLISION PERMANENT 1 2 sec 1 5 sec PERMANENT 1 2 sec 3 pulses PERMANE...

Страница 185: ...STL 472 502 90 Issue 6 12 23 A340 Electronic Instrument System ECAM Display unit...

Страница 186: ...STL 472 502 90 Issue 6 12 24 A340 Electronic Instrument System ECAM E WD Typical ENGINE CONTROL PARAMETERS FUEL QUANTITY INDICATION FLAPS SLATS POSITION ECAM UPPER DISPLAY E WD MEMO INFORMATION...

Страница 187: ...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 u...

Страница 188: ...0 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...

Страница 189: ...n 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 monito...

Страница 190: ...00ft OR EIS associated system pages FWS flight phases ELEC PWR 1st ENG STARTED 2nd ENG T O PWR 80 KTS LIFT OFF start 1500 FT 800 FT TOUCH DOWN 80 KTS 2nd ENG SHUT DOWN 5MN AFTER 1 2 3 4 5 6 7 8 9 10 F...

Страница 191: ...STL 472 502 90 Issue 6 12 29 A340 Electronic Instrument System ECAM Failure related mode...

Страница 192: ...STL 472 502 90 Issue 6 12 30 A340 Electronic Instrument System Architecture Flight Warning System FWS...

Страница 193: ...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 c...

Страница 194: ...STL 472 502 90 Issue 6...

Страница 195: ...STL 472 502 90 Issue 6 13 1 13 Radio Management and Communication...

Страница 196: ...STL 472 502 90 Issue 6 A340 Radio Management and Communication 13 2 Radio Management Panel RMP...

Страница 197: ...tem 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 overh...

Страница 198: ...STL 472 502 90 Issue 6 A340 Radio Management and Communication 13 4 RMP architecture...

Страница 199: ...nt operating modes exist Automatic tuning VOR DME ILS and ADF are automatically controlled by the FMGC Manual tuning To select a specific frequency through the FMGC MCDU which overrides the automatic...

Страница 200: ...STL 472 502 90 Issue 6 A340 Radio Management and Communication 13 6 COMM Audio Control Panel ACP...

Страница 201: ...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 max...

Страница 202: ...STL 472 502 90 Issue 6...

Страница 203: ...STL 472 502 90 Issue 6 14 A340 Central Maintenance System CMS 14 1...

Страница 204: ...STL 472 502 90 Issue 6 A340 Central Maintenance System 14 2 Left intentionally blank...

Страница 205: ...S 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 v...

Страница 206: ...ntral Maintenance System 14 4 Architecture CMC Central Maintenance Computer ACARS Aircraft Communication And Reporting System CMC 1 ACARSMU PRINT ER A4 FORMAT DAT A LOADER 1 MCDU if installed 2 3 CMC...

Страница 207: ...splay 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 Mu...

Страница 208: ...STL 472 502 90 Issue 6 A340 Central Maintenance System 14 6 Examples of use...

Страница 209: ...BLEED FAULT UTC 1032 FLIGHT PHASE TAKEOFF ROLL ATA 36 11 42 SOURCE BMC3 MESSAGE THRM 5HA3 FAN AIR V 12HA3 SENSE LINE INTERMITTENT CLASS 1 IDENTIFIERS CP1C CPC2 ATA 30 11 MESSAGE DISPLAYED ANTI ICE F O...

Страница 210: ...STL 472 502 90 Issue 6...

Страница 211: ...s 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...

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