Detailed Product Presentation. August 2005 Page 1

Transcription

1 Detailed Product Presentation August 2005 Page 1

2 Table of Contents 1. Superior Performance 6 Aircraft specifications and description 7 Range and Payload 9 Short field capability 17 Other performance qualities Cabin 20 General dimensions and characteristics 21 Passenger seats 25 Tables, Cabinets, Toilet 26 Cabin systems 29 Flexibility & Modularity Structure 33 General dimensions 34 Structure advantages and features 35 Aerodynamics 37 Wing attachment 38 Door and windows 39 Baggage compartment State-of-the-art systems 41 Honeywell integrated avionics 42 Williams FJ44-3A Engine 46 Landing gear system 48 Fuel system 52 Flight control system 56 Hydraulics system 58 Air condionning system 61 Power generation system 64 Ice & Rain protection system 66 Exterior Lighting system Certification 68 FAA & JAA commuter certification 69 Certification process 70 Program development Company background 74 GROB 75 ExecuJet Engineering and Manufacturing 82 Engineering expertise 83 Manufacturing of carbon fiber Customer Support 91 Maintenance 92 Warranty Comparisons 94 Performance tables 95 Range and Payload 97 Cabin cross sections 99 Cabin floorplans 100 Warranty 102 Other un-matched features and qualities 103 Back-up slides 105 Comparison with Part 25 jets 106 Carbon fiber technology principle 107

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4 The vision for the Utility Jet Project q Identified a market niche not well served turboprop flexibility in a jet q To exploit leading technologies for customer benefit q To provide high utility capability q To achieve excellent range / payload capability q A quantum price / performance advantage Page 3

5 The World s First Utility Jet Superior Capability q Flies further than other light business jets q Superior short field performance q Large cabin for passengers and cargo q Modern and reliable systems Maximum Flexibility q Superior range/payload capability q Single pilot capable q Quick change cabin configuration q Can access unimproved runways Page 4

6 Presentation Overview 1. Superior Performance 2. Cabin 3. Aircraft Structure 4. State of the art systems 5. Certification 6. Company background 7. Manufacturing and Design 8. Customer Support 9. Comparisons Page 5

7 1. Superior performance Page 6

8 Aircraft Specifications Product definition* q MTOW of 13,890 lbs (6300kg) q Aircraft Dimensions: q Length ft. q Wing Span 48.8 ft. q Height 16.8 ft. q 2 Williams FJ44-3A turbofan engines q Honeywell integrated avionics q An all composite, carbon fibre airframe q Reinforced undercarriage q 8 9 Passenger capability *As of August 15, subject to final confirmation Page 7

9 Aircraft Description Key Aircraft and Operating Data* Performance Specifications Max Operating Speed SL to 8000ft (VMO) Max Operating Speed 8000ft to 28440ft (VMO) Max operating Mach number (MMO) Stalling speed, MLW, forward CG, Landing configuration (VSO) Max Cruise, ISA, ft Rate of climb, AEO**, ISA, Sea Level, MTOW Rate of climb, OEI***, ISA, Sea Level, MTOW Balanced Field Length Landing distance from 50 ft (ISA, SL, Flaps 40, MLW) Maximum range, 1 pilot + 6 passengers (ISA, ft, NBAA IFR reserves, 100 nm) Maximum Operating altitude Value 260 KCAS 272 KCAS KCAS 407 KTAS 4360 ft/min 1260 ft/min 3000 ft 2950 ft 1800 nm ft m / 45.5 ft m / ft m / ft 5.12 m / 16.8 ft * Estimates subject to final confirmation ** All Engines Operative *** One Engine Inoperative Page 8

10 Range and Payload q Loaded with 7 persons (6 pax + 1 crew) range is 1800 NM q Maximum range of 1850 NM q At a full payload of 2491 lbs (1130 kg), aircraft range still exceeds 1200 NM Payload Specifications Ferry range Six Passengers + One Crew, Max Fuel Pax Seats Full (8 Pax + 1 Crew, available fuel) Max Payload with available fuel (MTOW) Payload Weight (lbs / kg) / / / 1130 IFR Range* (nm / km) 1850 / / / / 2371 *Specifications as of August 15, 2005 subject to final revision Page 9

11 Range and Payload Un-matched max payload Exceptional range when loaded Payload (lbs) lbs / 1130 kg 8 passengers 7 passengers 6 passengers High Speed Cruise Long Range Cruise Conditions: IFR Range (nm) ISA, FL410 Reserve: 847 lbs Fuel (100nm) Single Pilot: 200lbs (91kg) Each passenger: 200 lbs (91kg) Page 10

12 Range and Payload Central Europe Assumptions Range is 1,800nm (3334km) with zero wind Configuration: 6 Passengers and 1 pilot All systems normal, anti-ice OFF ISA Conditions, IFR reserve 100nm alternate The information shown in this map is for discussion purposes only Page 11

13 Range and Payload North America Vancouver Assumptions Range is 1,800nm (3334km) with zero wind Configuration: 6 Passengers and 1 pilot All systems normal, anti-ice OFF ISA Conditions, IFR reserve 100nm alternate The information shown in this map is for discussion purposes only Page 12

14 Range and Payload South Africa Assumptions Range is 1,800nm (3334km) with zero wind Configuration: 6 Passengers and 1 pilot All systems normal, anti-ice OFF ISA Conditions, IFR reserve 100nm alternate The information shown in this map is for discussion purposes only Page 13

15 Range and Payload SE Asia and Australia 540nm (1000km) Scale at Equator Assumptions Range is 1,800nm (3334km) with zero wind Configuration: 6 Passengers and 1 pilot All systems normal, anti-ice OFF ISA Conditions, IFR reserve 100nm alternate The information shown in these maps is for discussion purposes only Page 14

16 Range and Payload Middle East Assumptions Range is 1,800nm (3334km) with zero wind Configuration: 6 Passengers and 1 pilot All systems normal, anti-ice OFF ISA Conditions, IFR reserve 100nm alternate The information shown in these maps is for discussion purposes only Page 15

17 Range and Payload Central and South America Assumptions Range is 1,800nm (3334km) with zero wind Configuration: 6 Passengers and 1 pilot All systems normal, anti-ice OFF ISA Conditions, IFR reserve 100nm alternate The information shown in these maps is for discussion purposes only Page 16

18 Short Field Capability q The SP n has the best field performance: Similar take-off & landing performance to turboprops Better than the best jet competitor q Un-matched performance translates into lower risks Key performance figures Value Climb rates (MTOW): Time to FL370 (MTOW) - all engines ON - one engine OFF 4360 ft/min 1260 ft/min 13 min More flexibility in difficult airports and better mission performance Distances: - Balance field length - Landing distance 3000 ft 2950 ft Access to more airports Speeds (MLW): -V REF - Stalling speed 100 kt 77 kt Slowest speeds among light jets Specifications as of August 15, 2005 subject to final revision Page 17

19 Airfield Access Most other jets q Exceptional takeoff and landing performance q Un-improved runway capability q Maximum takeoff and landing altitude of 8500ft Number of Airports Accessible Unpaved Paved Total 0 above 3000 ft above 4000 ft Runway Length Access to up to 25% more airports than the best jet competitor Access to more airports than its main turboprop competitor Page 18

20 Other Performance Qualities q The SP n has good cruise performance: Max cruise speed of 407 kts Maximum ceiling of 41,000 ft q The SP n offers superior customer value: Fewer stops Less time wasted in commuting Less trade-off on weight More flexibility and quicker trips Key performance figures Maximum operating altitude Maximum operating Mach number M MO Maximum Cruise Speed (FL330, ISA) Value 41,000 ft kt Specifications as of August 15, 2005 subject to final revision Page 19

21 2. Cabin Page 20

22 General Cabin View Page 21

23 Internal Cabin Dimensions Cabin length 16.7 ft / 5.10 m Max Cabin Height 5.4 ft / 1.64 m Max Cabin Width 5.0 ft / 1.52 m Cabin Volume: 405 cu.ft / 11.5 m 3 Page 22

24 General Cabin Characteristics Designed for space and comfort q Biggest cabin volume in light jet category: 405 ft 3 / m 3 q Unique cabin cross section providing comfortable headspace q 5.4 ft / 1.64 m cabin height q Double club seating capable q Elegant but robust materials q Specified cabin noise level at long range cruise: 56 dbsil (76 dba) Leather Fabric (ultraleather) Loop carpet Carbon fiber Wood-like film Page 23

25 Key Cabin Features Lavatory with toilet, sink, closet and storage Dual pull-out tables for forward club Dual cabinets with various storages Movable forward cabin bulkheads Cabin seats with underseat storage Dual pull-out tables for aft club Page 24

26 Passenger Seats Engineered for convenience and quick-removal q Large underseat storage drawer q Extremely light seat structure q Special mechanism for removal in 30 sec q Mounted on rails to allow multiple configurations Key design features q Comfortable leather-covered seats q Designed specially for the GROB SP n q Inspired by the high-class car SUV designs q Full carbon fiber structure best ergonomics high strength: 21G forward, 15G down Leather upholstery Carbon fiber Movable armrest Large drawer Quick-release attachments Page 25

27 Cabin Console Tables Hinged table Dual forward console tables q Elegantly integrated in the sideledge layout q Designed for office and relaxation q Provided with individual glas holders Dual aft console tables q Innovative design for best use of cabin volume and more stability q Includes compartment for bottle storage q Special mechanism for quick removal Forward console table Page 26

28 Mid Cabin Cabinets Key features Key Lock q Fully integrated in the cabin layout and design q Best use of cabin volume q Key lock for on-the-ground safety q Multiple storage capabilities: Glasses / Cans Termos / Hot water Miscelleaneous / Entertainment 3 push-pull drawers Designed for quick removal q Mounted on rails to allow multiple configurations q Special mechanism for removal in 30 sec Quick-release mechanism Page 27

29 Forward Toilet Hinged door Galley / Wardrobe Hinged door Key features q Full toilet q Lavatory with sink and multiple storages q Galley or wardrobe q Direct and indirect lighting Designed for convenience and versatility q Fully isolated from cabin and cockpit by hinged doors q Easily removable for use of space as cargo q Elegant finish although resistant material Toilet Vanity cabinet Sink with Faucet Forward toilet module Page 28

30 Standard Cabin Systems Individual air gaspers and reading lights (LED) Dimmable up & down indirect lighting (LED) Individual oxygen masks EXIT 110V power outlets Emergency lighting / briefing Individual window blinds Page 29

31 Optional Cabin Features Office and Entertainment q Satcom with dual handset (cabin and cockpit) q Audio system with CD player and individual headsets q Video system with DVD player and individual 8-inch plug-in monitors q Airshow system with worldwide/regional maps and flight information 8.4 plug-in monitor Galley and Galley equipment q Full galley in lieu of forward toilet q High temperature oven q Microwave q Coffee maker Espresso machine Page 30

32 Interior flexibility Standard configuration Quick removal plug and play concept means removal of seats in ½ hour 50/50 cargo split configuration Page 31

33 Easy Loading and Modularity modular side-panels Main Features q Large door for ease of loading: 54 x 33 inch (137 x 84 cm) q Removable and modular sideliner for cargo application q Cabin net and strapping to secure the equipment transported Possible Applications q Quick change of cabin configurations q Air Ambulance q Dual configurations (cargo-pax combo) q Pallet loading Air Ambulance configuration Page 32

34 3. Aircraft Structure: an unbeatable advantage Page 33

35 Aircraft Structure General Dimensions m / ft m / ft 5.12 m / ft m / 45.5 ft Aircraft 3 views (approximate dimensions) Page 34

36 Structure Advantages Optimized design q Lighter structure q Integrated parts: Fuselage and vertical fin Wing Horizontal stabilizer q No rivets/bolts or extra attachment structure q Focus on aerodynamics and stress resistance rather than on manufacturing q Simple field repair q No fatigue limitation and no corrosion Page 35

37 Key Structural Features Forward pressure bulkhead Reinforcement wrapping belt Aft pressure bulkhead Integrated part Page 36

38 Aerodynamics Optimized aerodynamics q Modern supercritical airfoil q Efficient Fowler flap system q Exceptional surface quality q Delta fins for enhanced stability at low speed q Winglet to minimize the induced drag Aerodynamic model Page 37

39 Wing Attachment 15.5 cm / 6.1 inch Titatium Simple mounting concept q Removal/re-installation of wing on fuselage in 12 hours q 4 titanium-made fixations 22 cm / 8.5 inch q Each mount can hold up to 10 tons q No risk of corrosion Wing fixation Page 38

40 Doors & Windows Entrance door q Extra large door: 54 x 33 inch (137 x 84 cm) Glass windshield 84 cm / 33 inch 14 cabin windows q Comfortable for passenger boarding q Designed for easy loading: Luggage / Cargo Air ambulance 137 cm / 54 inch Windows q Large windshield designed for optimal pilot vision q Large cabin windows for best passenger comfort 14 windows, including 2 in entrance area Dimensions: 15.4 x 12.2 inch (39 x 31 cm) Door opening Page 39

41 Baggage Compartment Description q Total volume: 34 cu ft (0.96 m 3 ) q Below left hand engine: 32 cu ft (0.91 m 3 ) Main baggage compartment Includes a ski rack q Right hand side of nose cone: 2 cu ft (0.05 m 3 ) Nose baggage compartment Aft baggage compartment Designed for fly-away kit and pilot s equipment Aft baggage door q Size: 18 x 29 inch (46 x 73 cm) q Easy access to full volume of baggage compartment Loading Ski rack Exterior baggage compartments Page 40

42 4. State-of-the-art systems Page 41

43 Honeywell Integrated Avionics Page 42

44 Honeywell Integrated Avionics Cockpit Approach q Spacious design uses area efficiently q Low workload philosophy q Design for single or dual pilot operation Key Advantages of the APEX System q Latest technology based on large aircraft heritage q Easy ergonomic presentation Cockpit integration q Dark cockpit philosophy Page 43

45 Honeywell Integrated Avionics Key Features q Two 15 PFD s and two 10 MFD s q Color weather radar q Dual Flight Management System entry units (FMS) q Dual integrated Global Positioning System units (GPS) q Dual channel Air Data/Attitude and Heading Reference System (ADAHRS) q Enhanced Ground Proximity Warning System with windshear alert (EGPWS) Left primary flight display q Traffic Collision Alert System (TCAS II with Change 7) q Emergency Locator Transmitter (ELT) Page 44

46 Cockpit design Page 45

47 The Williams FJ44-3A Engine Page 46

48 The Williams FJ44-3A Engine q Proven manufacturer over 2000 engines delivered q Solid customer support 7 times #1 in Pro Pilot survey q Selected by leading Light Jet manufacturers q 2800 lbs of thrust excellent thrust/weight ratio q Extremely low in-flight shutdown rate history q Low operating economics q Full Authority Digital Engine Control (FADEC) q Long time between overhaul: 4000 hours (TBO) Page 47

49 Landing Gear System Page 48

50 Landing Gear System : Built for Robustness Un-improved runways capabilities q Large wheels and tires adapted to rough fields Main tires: 24 x 7.7 inch (61 x 19.5 cm) Low tire pressure: 94 psi (6.5 bars) q Large fuselage/ground clearance: Fuselage is 43 inch (1.1 m) above the ground* Reduces ground effect Increases distance from debris projections q Protection on control surfaces q Optional nose guard to divert debris Right hand landing gear * below the entrance door. Belly clearance is 80 cm (31.5 inch) Page 49

51 Landing Gear System Other features q Carbon brakes from ABSC * q Anti-skid system from ABSC * q System integrated with Honeywell avionics system q 3 levels of steering capabilities: +/- 10 steering angle at high speed taxing (> 10 kt) +/- 60 steering angle at low speed ( 10 kt) +/- 90 steering angle for towing Carbon brake * Aircraft Braking Systems Corporation Page 50

52 Landing Gear System Page 51

53 Fuel System Page 52

54 Fuel System General Description Fuel filters Integral wing fuel tank Main jet pumps Shut-off valves Gravity filler Scavenge pumps Vent tank Page 53

55 Fuel System Design philosophy q Two fuel pumps supplying each engine one main jet pump for normal operations one submerged boost pump for starting and back-up q 2 scavenge pumps per wing for continuous fuel transfer q One additional engine-driven pump on each engine for pressure at injection nozzles Jet pump q Cross-flow valve allowing supply from opposite wing Booster pump Page 54

56 Fuel System Key Features q 660 US gallon tank in the wing and center fuselage q Two gravity fuelling ports q Optional pressure fuelling point q Fuel control by the FADEC and display on the Honeywell avionics Fuel types available for use Crossflow valve Grade Specification Min Temp Max Temp Jet A ASTM-D deg C 93.3 deg C Jet A1 ASTM-D deg C 93.3 deg C JP 8 MIL-T deg C 93.3 deg C Chinese 3 Jet Fuel GB deg C 57.2 deg C RT C.I.S. GOST deg C 57.2 deg C TS-1 C.I.S. GOST deg C 57.2 deg C Page 55

57 Flight Control System Airbrakes Single slotted Fowler flaps Rudder and trim Dual control wheels Autopilot integrated with Honeywell avionics Elevator and trim Aileron and trim Page 56

58 Flight Control System Key Features q All-control rod engineering philosophy (no cables) More reliable and easier to maintain than cable-driven systems Design concept proven on previous GROB aircraft Elevator Trim q High level of redundancy Dual motors for the elevator trim Rudder and elevator control rods are split in aft fuselage Rudder Trim Empennage control surfaces Page 57

59 Hydraulic System Page 58

60 Hydraulic System Hydraulic reservoir Accumulators Hydraulic pump Page 59

61 Hydraulic System Operates: q The landing gear q The braking (normal and emergency) q The nose landing gear steering q The spoilers Key Features q One 3-liter reservoir q 3 accumulators: Main Brakes back-up Parking/emergency-braking back-up Hydraulic pump q One 3000 psi hydraulic pump q Widely available Mil-H-5606 hydraulic fluid Page 60

62 Air Conditioning System Page 61

63 Air Conditioning System General Description Two outflow valves Cabin overhead outlets Plenum chamber Cockpit overhead outlets Fan bleed ducting Windshield outlets Air cycle unit Cabin floor outlets Page 62

64 Air Conditioning System Honeywell Air Cycle Unit q Unusual for this class of aircraft q Better cooling capabilities than Vapor Cycle q Lower maintenance costs q Lower weight and power consumption Other features q Individual overhead air gaspers in cockpit, cabin and toilet q Cabin temperature selection from cockpit and cabin q P = 8.3 psi Aircraft altitude 41,000 ft / 12,496 m 35,000 ft / 10,667 m 30,000 ft / 9,143 m 25,000 ft / 7,620 m 20,000 ft / 6,096 m Cabin altitude 8,000 ft / 2,438 m 6,000 ft / 1,829 m 4,500 ft / 1,372 m 3,500 ft / 1,067 m 2,500 ft / 762 m Page 63

65 Power Generation System Main Battery Power Distribution Panel RH Generator Generator Control Units Auxiliary Battery LH Generator CB panel Page 64

66 Power Generation System Key Features q Two 400 Amps starter/generators q Two pure-lead-acid batteries: Main battery 40Ah Auxiliary battery 18Ah q Ground power connection: Supply power to entire system on ground Charge batteries q Essential vs. Non-essential power distribution concept Automatic re-configuration in case of engine failure Load shed of non-essential loads Starter generator Page 65

67 Ice and Rain Protection System Wing leading edge bleed air anti-ice Temperature control units Fan bleed port Horizontal stab. bleed air anti-ice (if required) Crossflow valve Electrical windshield anti-ice* HP bleed port Air intake bleed air anti-ice Probes electrical heating * Right hand heating is optional Page 66

68 Exterior Lighting System Key Features q Two anti-collision lights q Three navigation lights q Two landing/recognition lights q Two taxi lights q One wing inspection light (left hand side) q Optional logo lights Landing lights (wing fairing) Page 67

69 5. Certification Page 68

70 FAA and JAA Commuter Certification US and EU Certification Levels EASA CS23 Commuter category : planned for 1Q 2007 European Aviation Safety Agency Agence Européenne de la Sécurité Aérienne Europäische Agentur für Flugsicherheit FAR 14CFR Part 23 Commuter category: planned for 2Q 2007 Operating capabilities Single pilot operation MNPS, RVSM, P-RNAV compliant Operations in : - IFR & VFR day/night - Known icing conditions Page 69

71 The Certification Process (1) 1. Engineering review q Review of the engineering concepts by the Authorities 2. Structural Tests q One full airframe structure dedicated to these tests q Static tests conditions: x maximum loads are applied on the structure 72 C temperature Damage tolerance (defined defects in the structure) Wing static test q Fatigue tests : Minimum life time limit superior to 28,000 hours Actual test performed to 3-5 times this limit Page 70

72 The Certification Process (2) 3. Prototype tests q Ground tests q Flight tests 1 st flight performed on July 20, 2005 Full flight envelope testing by Q aircraft fully dedicated to flight tests Aircraft Type certification 4. Series aircraft tests First Flight: July 20, 2005 q Ground tests q Flight tests Aircraft Certificate of Airworthiness and Delivery to Customer Page 71

73 Flight test program underway Page 72

74 Program Development Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Launch project X Jan 04 Pre-design Apr 04 Detailed design Apr 04 Apr 05 Static tests Dec 04 Feb 05 Prototype assembly Jan 05 May 05 Ground test May 05 July 05 Flight test July 05 EASA Certification 31 Mar 07 X FAA Certification 30 Jun 07 X Unveiling the aircraft at Paris Air Show First flight: July 20 th, st deliveries Page 73

75 6. Company background Page 74

76 GROB Werke q World s most accomplished and most experienced composite aircraft manufacturer q More than 3500 aircraft delivered which have flown over 7 million hours on five continents q A precision automotive machine tools manufacturer Clients include Audi, BMW, Daimler Chrysler, Ford, General Motors, Volkswagen q ± 3000 employees and turnover of approximately 450,000,000 q Privately held, founded in 1926, in Aerospace since 1971 Aerospace Division Mattsies, Germany q Based in Germany with international operations in USA, Brazil and China Page 75

77 The GROB Group Page 76

78 GROB - Werke Aerospace Division q In-house manufacturing of all structural composite and metal parts: Fuselage Wing Control surfaces Landing gear Brackets and hinges q High-precision metal parts manufactured by GROB tooling division q In-house composite curing facilities Composites q Integration of complete OEMs systems on the airframe (avionics, air conditioning, engines, etc) q In-house testing capabilities: Static & Fatigue test Ground & Flight test Metal parts Systems Page 77

79 The GROB Legacy Gliders q More than 2500 gliders built q Altitude record of 49,000 ft Engine-powered gliders q More than 470 aircraft built since 1981 q Fixed engine / retractable engine Trainers q More than 400 pistons and turboprop aircraft q Certified for aerobatics q Flying and supported in Europe, US, Australia, Middle East Page 78

80 The GROB Legacy Business aircraft (G160 Ranger) q Up to 6 passenger seating in business aviation standards q Integrated avionics q More than 2000 nm of range q Certification underway G160 Ranger Research aircraft q Multiple altitude records q Largest aircraft made of composite (56m wingspan) q Designed for 48h of continuous flying Strato II Page 79

81 ExecuJet Aviation Group q Turnkey business aviation service concept q Bombardier business aircraft sales in 35 countries q Pilatus aircraft sales in 35 countries q Aircraft management & operations (over 80 a/c) q Aircraft charter q Aviation services (incl. FBO) q Airframe & engine maintenance q Employ 420 staff in multiple locations Facilities at Lanseria Airport, South Afirca q Based in Europe, Africa, Australia, Middle East & Central America Page 80

82 Strong Partnership GROB Aerospace - Development & Manufacture q Significant aviation experience and technical expertise in aircraft design and manufacture q Successful track record bringing training and high altitude aircraft to market q A strong can do culture and record of achievement ExecuJet Aviation Group - Sales & Support q ExecuJet Aviation Group (EAG) appointed as primary distributor q Comprehensive knowledge of the needs of business aircraft operators q Located in Europe, South Africa, Australia, Middle East & Central America q Capability includes sales, flight operations, maintenance & FBO Page 81

83 7. Engineering and Manufacturing Page 82

84 Engineering Expertise q State of the art 3D-CAD systems q Finite Element Analyses q Computerised aerodynamics models q Partnership with world-reknown OEMs Williams Honeywell Goodrich q In-house static and fatigue testing q Ground and flight testing 3D modeling Page 83

85 Carbon Fiber Technology q Light weight q High strength and rigidity q Optimized aerodynamic surfaces (no rivets) q Non corrosive q Unlimited fatigue life q Low maintenance q Simple field repairs q Extreme climate proven Carbon fiber and Honeycomb core q Low parts count Carbon fiber is as strong as aluminum but 44% lighter Page 84

86 Carbon Fiber Technology Creation of the Airframe 1. A positive core is created based on the aircraft engineering data 2. A negative mold is created to the shape of the core 3. The airframe structure is manufactured in the mold: q Honeycomb or foam plates with carbon fibre fabric on both sides q Resin applied to bind materials and create strength 4. The structure is heated and fused together in a large heating chamber 5. The fuselage structure re-heated outside the mold Page 85

87 Carbon Fiber Technology 1. Creation of the core Page 86

88 Carbon Fiber Technology 2. Creation of the molds Page 87

89 Carbon Fiber Technology 3. Structure created in carbon fiber sandwich Page 88

90 Carbon Fiber Technology 4. First heating at 60 C / 140 F in the mold Page 89

91 Carbon Fiber Technology 5. Second heating at 80 C/176 F outside the mold Page 90

92 8. Customer Support Page 91

93 Superior Maintenance Capabilities Around the World q World-wide service and support in place through ExecuJet q Certified for all types of maintenance (airframe, engines, avionics, systems, etc.) q Authorized to service multiple business aircraft models including Bombardier and Pilatus Scandinavia Germany Switzerland To be defined Middle East Mexico South Africa Australia To be defined ExecuJet Locations Page 92

94 Superior Warranty Offer q Comprehensive coverage for all major components and systems q Meets or exceeds industry standards q Engine backed by Williams and supported at any authorised facility Aircraft part Fuselage and wing composite structure made by GROB Other structural elements made by GROB Engines (directly via Williams) Honeywell avionics All other vendor parts and equipment Aircraft interior Exterior paint Warranty Period 7 years or 7000 flight hours 3 years or 1500 flight hours 3 years or 1500 flight hours 5 years 2 years or 1000 flight hours 2 years 2 years Page 93

95 9. Comparisons Page 94

96 Comparison vs. Turboprops GROB SP n Utility Jet Pilatus PC12 King Air C90B King Air B200 King Air 350 Piaggio Avanti Range with seats full * (nm) Typical Pax * (Normal Configuration) or Available Volume * (Cabin + Baggage) (cu ft/m 3 ) 439 / / / / / / Cabin Height * (ft/m) 5.4 / / / / / / 1.76 Max Payload** (lbs/kg) 2491 / / / / / / 907 Field Performance** (TOFL in ft/m) 3000 / / / / / / 869 Rate of Climb * (ft per min) * Source: Conklin and de Decker Fall 2004 ** Source: BC & A May 2005 Page 95

97 Comparison vs. Part 23 Light Jets GROB SP n Utility Jet Cessna CJ1+ Cessna CJ2+ Cessna CJ3 Raytheon Premier I Swearingen SJ30-2 Range with seats full * (nm) Typical Pax * (Normal Configuration) Available Volume * (Cabin + Baggage) (cu ft/m 3 ) 439 / / / / / / 6.90 Cabin Height * (ft/m) 5.4 / / / / / / 1.43 Max Payload** (lbs/kg) 2491 / / / / / / 862 Field Performance** (TOFL in ft/m) 3000 / / / / / / 1070 Rate of Climb * (ft per min) * Source: Conklin and de Decker Spring 2005 ** Source: BC & A May 2005 Page 96

98 Range and Payload vs. Turboprops * Only the King Air 350 can carry more load, but only for short missions Payload (lbs) GROB SPn Utility Jet King Air C90B King Air 350 King Air B200 Piaggio Avanti P Conditions: Reserve 100nm alternate IFR Range (nm) * Source: BC & A May 2005 Page 97

99 Range and Payload vs. Part 23 Light Jets * The GROB SP n Utility Jet outperforms all light jets competitors Payload (lbs) GROB SPn Utility Jet Cessna CJ1+ Cessna CJ2+ Cessna CJ3 Raytheon Premier IFR Range (nm) Conditions: Reserve 200nm alternate * Source: BC & A May 2005 Page 98

100 Cabin Cross section comparisons * SWEARINGEN SJ30-2 KING AIR C90/B200/350 CITATION CJ2 CITATION CJ3 PILATUS PC-12 RAYTHEON PREMIER I GROB SP n UTILITY JET AVANTI P ft 5.0 ft 4.1 ft The SP n oval cabin cross section is designed to offer the biggest head space. * Source: Conklin and de Decker Fall 2004 Page 99

101 Cabin Turboprops floor plan comparision * KING AIR B200 AVANTI P-180 KING AIR 350 GROB SP n UTILITY JET PILATUS PC12 Volume available for seating 16.7 ft Unlike turboprops, the SP n allows for a comfortable double club layout * Source: Conklin and de Decker Fall 2004 Page 100

102 Cabin Light jets floor plan comparision * SINO SWEARINGEN SJ30-2 RAYTHEON PREMIER I CITATION CJ2 CITATION CJ3 GROB SP n UTILITY JET Volume available for seating 16.7 ft The SP n cabin is much larger than these of other FAR 23 jets * Source: Conklin and de Decker Fall 2004 Page 101

103 Warranty comparison Aircraft part GROB SP n Utility Jet Cessna CJ1 Cessna CJ2 Cessna CJ3 Raytheon Premier 1 Swearingen SJ30-2* Airframe 7 yrs / 7000 hrs 5 yrs / 5000 hrs 5 yrs / 5000 hrs 5 yrs / 5000 hrs 5 yrs / 5000 hrs 5 yrs / 2500 hrs Minor metal structures 3 yrs / 1500 hrs N/A N/A N/A N/A N/A Engines 3 yrs / 1500 hrs 2 yrs / 1000 hrs 3 yrs / 1750 hrs 3 yrs / 1500 hrs 3 yrs / 1500 hrs 3 yrs / 1500 hrs Honeywell avionics 5 yrs 5 yrs 5 yrs 5 yrs 5 yrs 2 yrs Vendor parts 2 yrs / 1000 hrs 1 yr 1 yr 1 yr 2 yrs 2 yrs / 1000 hrs Aircraft interior & Exterior paint 2 yrs 1 yr 1 yr 1 yr 2 yrs 1 yr Source: Conklin and de Decker Fall 2004, except otherwise mentioned * Source: SJ30-2 manufacturer Page 102

104 Other Un-Matched Features and Qualities q Un-improved runway capability q Modular and versatile cabin q Latest avionics technology q State-of-the-art systems q No fatigue / corrosion Page 103

105 Page 104

106 Back-up slides Page 105

107 Comparison vs. Part 25 Light Jets GROB SP n Utility Jet Cessna Citation II Citation Encore Citation Bravo Hawker 400XP Range with seats full * (nm) Typical Pax * (Normal Configuration) Available Volume * (Cabin + Baggage) (cu ft/m 3 ) 439 / / / / / 10.2 Cabin Height * (ft/m) 5.4 / / / / / 1.46 Max Payload** (lbs/kg) 2491 / / / / / 930 Field Performance** (TOFL in ft/m) 3000 / / / / /1100 Rate of Climb * (ft per min) * Source: Conklin and de Decker Fall 2004 ** Source: BC & A May 2005, except Citation II: Conklin & de Decker Page 106

108 Carbon Fiber Technology Steps to Create Composite Fibre 1 one simple mould 2 carbon/glass fibre sheets wet laminated with epoxy resin 3 light sandwich core 4 vacuum foil 5 ambient pressure 6 suction 7 low temperature curing 8 seal Page 107