LA 380 pour Air France 1 A 3

L’A 380 pour Air France 1

A 3 XX dimensions SPAN LENGTH HEIGHT A 3 XX / A 3 XX-F 79. 8 m 73 m 24. 1 m 2

Caractéristiques de l’A 380 Capacité passager Capacité fret Rayon d’action (max pax) MDTOW MLW MZFW OWE (masse de base) Charge marchande Capacité carburant Poussée moteur (slst) * Configuration Air France A 380 555/559* 38 LD 3 s or 13 palettes 18 LD 3 s* and 5 palettes* 8, 000 nm / 6700 nm* 560 t 386 t 361 t 277 t / 293. 1 t * 84 t / 67. 9 t * 310 000 l 302 k. N 3

Rayon d’action autour de Paris A 380/GP 7200 Rayon d’action avec charge marchande maximale passager (559 pax) 548 t/560 t: 6398 nm/6731 nm Vents les plus défavorables- probabilité annuelle de 85% ISA Marge de 3% sur le rayon d’action 4

L’ économie de l’ avion Ref : 747 -400, 416 sièges, Prix catalogue : 180 m$ 2000 Prix/siège -10% Coût direct Coût carburant d'opération/siège* -13. 5% -15% A 380 -800, 555 sièges, Prix catalogue: 216 m$ 2000 L’A 380 : un avion économiquement attractif *Comparaison basée sur un secteur de 6000 nm - coûts d ’opération standards Airbus 5

Nose Fuselage Dimensions A 380 A 340 A 320

L’A 380 : capacité et espace § Plus grand dehors 747 -400 § +35 % de capacité supplémentaire § 2 cabines distinctes (ponts principal et supérieur) Un confort et § Plus grand dedans 160’’ 241’’ 233’’ Fuselage large 259’’ Fuselage large flexibilité grâce à deux très larges cabines 7

La réponse A 380 De 4 à 9 de front De 4 à 11 de front DU CONFORT POUR LE PASSAGER Poste de repos et toilettes en soutes optionnels Palettes … ET DE LA CAPACITE CARGO 2 palettes LD 3 s et/ou palettes 8

Configuration A 380 Air France : 559 sièges Pont supérieur Pont principal 78 J, pas 48” 16 P, pas 82” 135 Y, pas 31” 330 Y, pas 31” 9

Les prochaines étapes du programme Gel de la Configuration Jan. 99 Autorisation commerciale Mi 2000 Clients de lancement Durant 2000 Définition terminée Premier Mise en vol service Fin 2001 Mi Début 2004 2006 10

Principales innovations • 2 Packs ( BP et HP ) • PA intégré au CDV • Génération électrique : fréquence variable. • CDV : concept EHA et EBHA • Fuel : optimisation du CG de l’ avion lors du remplissage. • Hydraulique : 5000 Psi. • LDG : 22 roues / aide au management de configuration. • Oxygéne : Systéme OBOGS ? • OIS / OMS : avion communicant / informations embarquées…. . • Station de maintenance : face au pylone + possibilité d’ interrogation à distance par terminaux sans fil. • Structures : CFRP / Glare • Portes : électriques • Moteurs : surveillance enrichie ( analyse des gaz en sortie …. . ) 11

Control and Display System 8 identical potentially interactive displays 2 multi-functions keyboards 2 multi-functions Cursor Control Devices 12

Maintenance station 13

To be examined in the mock-up 14

Rear Fuselage Same ladder in different positions

Air Generation pack concept - redundancy Conventional Technology BPV FCV RHX RDA ACM Advanced Technology BPV FCV 1 RDA RHX FCV 2 RDA LP ACM BPV FCV RHX RDA HP ACM BPV FCV 1 BPV FCV RHX RDA ACM RDA RHX FCV 2 RDA HP ACM Components: FCV: Flow Control Valve RHX: Ram Heat Exchanger RDA: Ram Door Actuator BPV: Bypass Valve ACM: Air Cycle Machine LP ACM No. of Components 3 3 3+3* 4 2 4+2* *for HX-mode Conventional: Most single failures result in loss of complete pack. Advanced: No cooling degradation due to most single failures. 16

Variable frequency network Objectives : • Significant improvement of the ATA 24 DMC and operational reliability • Reduction of the aircraft systems DMC • Re-open industrial competition Suppliers involved • TRW-LUCAS : 120 KVA variable frequency generator on test. • HONEYWELL-ALLIED : 150 k. VA generator in lab. in Feb 2001 • HAMILTON SUNDSTRAND: 150 k. VA gen. in lab. in Feb 2001 Network characterization under process with EUROCAE and RTCA (DO 160 update) 115 V AC network confirmed 17

AC network general architecture 4 x 150 k. VA VFG Engine 1 Engine 2 APU Engine 3 Engine 4 2 x 120 k. VA CF gen AC 1 <<Ext 1 AC 2 <<Ext 2 Galley 1 Galley 2 Ext 3>>AC 3 Ext 4>>AC 4 Galley 3 Galley 4 4 x 90 k. VA ext. connections 18

Fuel System Fuel system provides Protection of fuel volume following engine rotor failure (FAR 25. 903(d)(1)) Provision of wing bending relief and CG management Embodiment of TWA 800 accident recommendations Inner Engine Feed Tank Aft Center Tank Inner Transfer Tank e • Gauging technology under evaluation Enginnk ter Ta u • Refueling procedure under O eed F review with the airlines Aft center tank- 42 400 litres (-800 R and -900 only) Inner feed Tank - 28500 litres Inner Transfer Tank - 84400 litres Outer Eng Feed Tank - 28400 litres Outer Transfer Tank - 10600 litres Trim tank - 24 000 litres Outer Transfer Tank Trim Tank Vent Tanks 19

Increased hydraulic pressure 5000 psi Kick-off (1998) : current experience potential show stoppers criteria for trade-off action list Hydraulic fluid analysis Initial actions Trade-off study (PDR) Review with the airlines - system workshop 26/28 Oct 19 Final decision : 8 November 1999 + follow-up actions • System weight : - 1200 kg • Feasibility confirmed • Technical risk on Hydraulic system reduced Airline questionnaire 2 Hyd. benches for endurance Definition of standards Additional benches in suppliers 20

2 H/2 E Architecture Schematic Gen Gen Eng. 1 Eng. 2 EDP EDP APU Isolation Gen RAT Gen Gen Eng. 3 Eng. 4 EDP EDP EMP T/R Ailerons Spoilers Rudder Elevators THS Slats/Flaps Braking Alt. Ener Steering Alt. Ener Gear actuation L & R o/b & m/b Eng. 2 T/R Eng. 3 T/R L & R i/b L & R o/b L & R i/b & o/b 2, 4, 6, 8 (L&R) 6 (L & R) 4 (L & R) 1, 3, 5, 7 (L &R) Upper & Lower LOB & ROB LIB & RIB Pitch trim 1 PMV Pitch trim Slats Flaps LOB & ROB PMV Pitch trim 2 Slats PMF Alt. Ener Wing Gear Brakes PV Flaps Body Gear Brakes PV Nose Body Gears Nose & Wing Green System LIB & RIB Body Gears Electric System 1 Electric System 2 Yellow System 21

Nose gear & fuselage studies STATUS 14 150 Frame 11 Frame 10 Frame 12 STATUS 11 100 22

Main Gear Group • 4 post main gear group for 560 & 590 t • 4 wheel Wing gear • 6 wheel Body gear 560 t & 590 t MTOW • 5 post main gear group for growth • bay gives extra cargo volume with good central fuselage structure • compatible with pavement loading (being demonstrated by PEP) growth 23

Avionics for A 380 FCGC FCSC Flight control Ethernet network AFDX SFCC Engines Ethernet FADEC Network AFDX network ADIRU MMR VOR DME TACS : cameras, video switches AWLU OMT Radio comm. HFDR, VDR, SATCOM Sensors Recorders R/A Ctrl & Displays Ethernet network SELCAL, RAMP, AMU. . . CVR, DFDR cockpit IOM ACMF FDIF FW FCDC FM Cockpit ACR SCI ECM Surveillance ATC ACAS, TAWS, W/R energy ELM CBM HSy. M WACS SATCOM LEO/MEO NCR std by Avionics server connectors fuel&LG PHC WHC GCU APU GCU FQI/ Fu. M LG BC SC TP IRDC LG Utilities Air Gener. Gene. Temp ctl/ ration. Bleed mon. Temp Overheat detect. . Contr. Cabin Pressure Cabin Ventil. Ctl / Pressure Avioncs cooling Ventalation. Contr. . Cabin Intercom. . . Data -CIDS. Smoke detect. . Water/waste. ctl. Cabin LRU Cabin server IFE 24

On Board Information Gate Link Passenger Terminals Crew Station IFE FS Router VHF Flight Deck Info • • Charts and Maps Weather Electronic Library Electronic log book Cabin Services • • Passenger Manifest Consumables Tracking Financial Transactions Cabin Logbook, Checklist Maintenance Apps • FMS Nav Data Base • Operational S/W Loading • Fault Correction Guide • Quick Access Recorder IFE • Direct TV • Internet

A 3 XX Onboard Maintenance System concept Terminals Cockpit, cabin, Portable Uplink Downlink Control, reporting display, customisation programming Recording Printing Onboard Information Network Aircraft Condition Monitoring Acquisition and processing Ops. data Data Loading Consultation Centralized Maintenance S/W and data bases loading A/C Systems and engines Fault acquisition Tests activation Link Maintenance Electronic documentation BITE 26

A 3 XX Scenario for Advanced Materials Upper Floor Beams: CFRP for Pax version, Aluminium for freighter version Upper Fuselage Panels: Fibre Laminates (GLARE) Empennage: CFRP Outer Wing: Metal bonded Rear Pressure Bulkhead: CFRP Wing Panels: Advanced aluminium alloys Center Wing Box: CFRP Lower Fuselage Panels: Laser Beam Welded aluminium alloys Fixed Wing Leading Edge: Thermoplastic J-Nose 27