Welcome. Lancair International Lancair International Inc. manufactures advanced composite structures at its Redmond, Oregon facility, and has established.

Welcome

Lancair International Evolution – Discovery and

Discussion

Lancair InternationalLancair International Inc. manufactures advanced composite structures at its

Redmond, Oregon facility, and has established proprietary relationships with hand-selected vendors in the USA, Europe, Australia and the Philippines. Worldwide, Lancairs are owned and operated in 34 countries on five continents.

HISTORY IN THE MAKINGThe Lancair family of aircraft covers the range of private pilot aircraft from the solid two-seat Lancair Legacy, the economical two-seat Legacy fixed-gear to the four-seat, fixed-gear Lancair ES and the recently completed Evolution rounds out the companies current offering. The PT6 powered turbine will propel the Evolution to incredible speeds of up to 330 kts in pressurized comfort over 1,000 Nmiles.

Lancair’s goal is to continue to play an important part in shaping the future of modern aviation through innovation, technical advancements, design purpose, aesthetics and of course, performance refinements in the entire Lancair family of aircraft.

Redmond AirportLancair

International

• 1983 - Lance Neibauer starts Neico Aviation with the introduction of the Lancair 200 in Gardena, CA.

• 1985 - Lancair 200 flies - Compton, CA• 1986 - Company moves to Santa Paula,

CA • 1987 - Introduction of the 320/360• 1989 - Santa Paula workshop Fast Build

kit introduced• 1990 - Introduction of the Lancair IV• 1991 - Construction of the composite

shop on Cebu, Philippines Molds• 1992 - The Company starts business in

Redmond as Lancair International. That fall the Lancair IV-P was introduced

Milestones• 1994 - Super ES • 1995 – Lancair 320 displayed at Metropolitan Museum of Art in New York City • 1996 - Lancair Certified Aircraft moves to Bend• 1999 - Legacy introduced at Oshkosh • 2003 – Lance Neibauer sells the Company to Joe Bartels in February• 2003.5 - Evolution Design Project Begins• 2004 - Introduced the ES-P at Sun-n-Fun• 2007 – Evolution Public debut• 2008 – First Evolution Prototype Flies and Testing Begins• 2009 - Evolution Piston flies to OSH and then onto Lycoming. First Customer Evolution Flies

• Competencies– Aircraft Design

Lancair excels at aircraft engineering and design. Lancair aircraft are the industries recognized leader in performance and innovation.

– Composite ManufacturingLancair has been designing and manufacturing high strength

composite aircraft for 25 years. Lancair’s products lead their respective market segments in strength and weight efficiency.

– Aviation Technology InnovationLancair has forged a reputation on bringing innovative products

to the personal transportation market and continues to be copied by kit and certified aircraft companies alike throughout the world wide aviation market.

EVOLUTIONDESIGN ON A HIGHER PLANE

Engineering

Evolution Introduction Specifications Performance Design

Flight Characteristics Certification Standards Flight Test Results Loads and Structures Structural Testing

FAA Certification

Evolution Concept

EvolutionReality

• S/N EVO-0001T : 300 hours• S/N EVO-0003T : 180 hours• S/N EVO-0004P: 75 hours• S/N EVO-0002, 0005 – 0019 In process with 2 more scheduled to fly in 2009

• 4 place Turbo-prop or Piston Engine• Pressurized • Retractable gear • Conventional aerodynamic configuration• Full carbon fiber composite airframe

Evolution Turbine Specifications

• L e n g t h - 3 0 f t• H e i g h t - 1 0 f t• W i n g s p a n - 3 7 f t• W i n g A r e a - 1 3 3 f t ^ 2

• W i n g l o a d i n g - 3 2 . 3 # / f t ^ 2

• A s p e c t R a t i o - 1 0 . 3• P T 6 A - 1 3 5 A ( 7 5 0 S H P )• H a r t z e l l 8 2 . 5 ” 4 b l a d e p r o p e l l e r• 1 4 6 g a l l o n s ( S t a n d a r d R a n g e ) / 1 6 8 g a l l o n s ( E x t e n d e d

r a n g e )• E m p t y We i g h t - 2 3 5 0 l b s• G r o s s We i g h t - 4 3 0 0 l b s• U s e f u l L o a d - 1 9 5 0 l b s• P a y l o a d a f t e r f u e l - 8 0 0 l b s w i t h e x t e n d e d r a n g e

t a n k s / 9 5 7 l b s w i t h s t a n d a r d t a n k s

• L e n g t h – 2 8 . 7 f t• H e i g h t - 1 0 f t• W i n g s p a n - 3 7 f t• W i n g A r e a - 1 3 3 f t ^ 2

• W i n g l o a d i n g – 3 2 . 3 # / f t ^ 2

• A s p e c t R a t i o - 1 0 . 3• L y c o m i n g I E 2 P i s t o n ( 3 5 0 H P )• H a r t z e l l 8 2 . 0 ” 3 b l a d e p r o p e l l e r• 1 4 6 g a l l o n s ( S t a n d a r d R a n g e ) / 1 6 8 g a l l o n s

( E x t e n d e d r a n g e )• E m p t y W e i g h t - 2 6 0 0 l b s• G r o s s W e i g h t - 4 3 0 0 l b s• U s e f u l L o a d - 1 7 0 0 l b s• F u l l F u e l P a y l o a d ( 1 2 0 G a l = 7 2 0 l b s ) - 9 8 0 # ’ s

Evolution Piston Specifications

Get Proper numbers for here

Evolution Turbine Performance• 3 3 0 K TA S @ 3 9 G P H @ F L 2 5 0• 3 0 4 K TA S @ 3 0 G P H @ F L 2 8 0• 2 7 0 K TA S @ 2 4 G P H @ F L 2 8 0• Vy 1 0 5 K I A S 3 3 0 0 F P M S L I S A• R O C @ F L 2 8 0 1 5 0 0 F P M• V x 8 5 K I A S • L a n d i n g A p p r o a c h S p e e d 7 9 K I A S• S t a l l S p e e d 6 1 K I A S @ 4 3 0 0 l b s• Ta k e o f f d i s t a n c e 1 4 0 0 f t S L I S A o v e r 5 0 f t• L a n d i n g d i s t a n c e 1 0 0 0 f t S L I S A• 8 7 6 n m w i t h I F R R e s e r v e a t 3 3 0 K TA S• 1 0 1 7 n m w i t h I F R R e s e r v e a t 3 0 4 K TA S

Evolution Piston Performance

• 2 7 0 K TA S @ 2 2 G P H @ F L 2 5 0• 2 4 0 K TA S @ 1 7 . 5 G P H @ F L 2 5 0• Vy 1 0 5 K I A S 2 0 0 0 F P M S L I S A• V x 8 5 K I A S• V L E 1 8 0 K I A S / V F E ( 1 0 ° ) 1 6 0 K I A S • L a n d i n g A p p r o a c h S p e e d 7 9 K I A S• S t a l l S p e e d 6 1 K I A S @ 4 3 0 0 l b s• Ta k e o f f d i s t a n c e 1 2 0 0 f t o v e r 5 0 f t• L a n d i n g d i s t a n c e 1 4 0 0 f t o v e r 5 0 f t• 1 3 0 0 n m w i t h I F R R e s e r v e a t 2 7 0 K TA S• 1 7 0 0 n m w i t h I F R R e s e r v e a t 2 4 0 K TA S

• Side stick controls• Pilot configurable for 5’2” to 6’6”

(5th% Female / 95th% Male)• 4 position seat back angle• Adjustable 6.5” fore-aft• Adjustable rudder pedals

• Crashworthy seats-all occupants• Automatic Climate Control• Enhanced Pilot visibility• AmSafe Airbag Seatbelts

Evolution Cockpit

Evolution Cockpit• G900 flight instruments

• Synthetic Vision• Highway in the Sky• Datalink Weather• Safe Taxi• Approach Plates• TAWS• TCAS

• Automatic Pressurization Scheduling• Dukes Certified Digital Control System

(Developed for the Eclipse jet)• Single cabin door with emergency exit baggage

door

Evolution Features

• Wide track trailing link landing gear (8” stroke)• Single slotted fowler flaps• BRS capable

• Chute tested, rocket design not complete• CAD Designed-CNC masters• Repeatable Tooling• 18 X 4.4 high pressure tubeless tires

• First set of tires lasted 272 landings• Parker High energy brake system

• Wheel and brake system specially designed for Evolution TSO’d• Energy capacity twice that of 6.00 X 6 brakes

N927LE Flight tested utilizing CFR 14 FAR 23 procedures for:

Stall FAR 23.49, 201, 203, 207 Controllability and Maneuverability FAR 23.143(a) Trim FAR 23.161, 677 Reference Landing Approach Speed FAR 23.73 Longitudinal Control FAR 23.145(d) Elevator Control Force in Maneuvers FAR 23.155 Static Longitudinal Stability FAR 23.175 Static Directional and Lateral Stability FAR 23.177 Dynamic Stability FAR 23.181 Vibration and Buffeting FAR 23.251

Flight Characteristics

Lightest test weight 2,805 lbs, Heaviest test weight 4,291 lbs

Forward test CG 120.17” (5.99% of Mean Aerodynamic Chord)

Aft test CG 130.38” (29.95% of Mean Aerodynamic Chord)

The four weight / CG regions are depicted on the weight and balance chart presented in this report. Limited ballast positions dictated the extremes of the envelope actually attainable.

The torque settings used for testing was de-rated MCP – 1280 ft lbs (~460 hp)

Balk landing control (FAR23.77(c))- Excellent

Stalling behavior (FAR23.201, 23.203) - flaps clean, take off, landing, turning flight- excellent

Approach to landing control (FAR23.177) - Excellent

Control harmony - Excellent Visibility over nose- Excellent Ground handling- Excellent

Flight Test Highlights

Get Correct FAR Refs here

Evolution Wt & Cg Envelope

Flight Envelope Loads Structural Testing

Loads and Structures

8

7

6 5

4

3

21

9

10

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

120.0 121.0 122.0 123.0 124.0 125.0 126.0 127.0 128.0 129.0 130.0 131.0

Fuselage Station [in]

Airc

raft

Wei

ght [

lb]

Flight Envelope Weight and Center of Gravity

*Aircraft loading shown with combination of four people (800 LBS), 140 LBS baggage, and 144 gallons of fuel (1010 LBS)

Loads and Structures

V – n Diagram

V-n DiagramLancair Evolution

4300 LBS Gross Weight

-5

-4

-3

-2

-1

0

1

2

3

4

5

6

7

0 50 100 150 200 250 300

Airspeed (KEAS)

g L

oa

d

Loads calculated per FAR 23 requirements, Subpart C - Structures

Aircraft has three aerodynamic configurations and the Flight Envelope per FAR 23.333 and 23.245

Method based on McMaster using methods acceptable to FAA in previous aircraft certification programs

Evolution Wing with aileon deflection

-0.0500

0.0000

0.0500

0.1000

0.1500

0.2000

0.2500

0.00 50.00 100.00 150.00 200.00 250.00

Spanwise Location, y, inches

Coef

ficien

t of L

ift, C

l

Basic Lift

Additive Lift

Total Lift

Loads and Structure Design

Wing section wind tunnel tested at Texas A&M wind tunnel

Test Loads = Calculated Loads + EV factor (1.28X)

Load Tests Wing

Positive / Negative bending and shear with torsion

Landing Gear Attachments Fuselage Attachments or

Fuselage Wing Box Horizontal Stabilizer Vertical Stabilizer Flaps and Control Surfaces Pressure Vessel

Loads and Structures

Ultimate load test = 192% Limit Load

Evolution Wing Load TestZ Shear

0

1000

2000

3000

4000

5000

6000

7000

8000

0 20 40 60 80 100 120 140 160 180 200 220

Wing Station

Sh

ea

r (L

BS

)

Test

PMAA2 Z Shear

Evolution Wing TestBending Moment

0

100000

200000

300000

400000

500000

600000

700000

800000

0 20 40 60 80 100 120 140 160 180 200 220

Wing Station

Mo

men

t (IN

LB

S) Test

PMAA2 X Moment

Load Tests Wing

Positive Load case is 5.5g

maneuver case at forward CG zero fuel condition

Loads and Structures

Evolution Wing TestAsymmetric Bending Moment

0

100000

200000

300000

400000

500000

600000

700000

0 20 40 60 80 100 120 140 160 180 200 220

Wing Station

Mo

me

nt

(IN

LB

S) Test

PMAA2 X Moment

Load Tests Wing - Fuselage

Attachments 212,500 IN LBS across

center section

Evolution Wing Load TestAsymmetric Z Shear

0

1000

2000

3000

4000

5000

6000

7000

0 20 40 60 80 100 120 140 160 180 200 220

Wing Station

Sh

ea

r (L

BS

)

Test

PMAA2 Z Shear

Loads and Structures

Evolution Wing Load TestZ Shear

-1000

0

1000

2000

3000

4000

5000

6000

0 20 40 60 80 100 120 140 160 180 200 220

Wing Station

Sh

ear

(LB

S)

Test

Landing 2 Z Shear

Load Tests Wing - Landing Gear Attachments

Evolution Wing TestTorsion

-160000

-140000

-120000

-100000

-80000

-60000

-40000

-20000

0

0 20 40 60 80 100 120 140 160 180 200 220

Wing Station (IN)

IN L

BS

mo

men

t

test

Landing 2 YMoment

Load Tests Horizontal Stabilizer Symmetric

Unchecked Va maneuver per FAR 23.423(a) Asymmetric

100 / 55 % per FAR 23 .427(b)

Load Tests Vertical Stabilizer

Three load point with wiffel tree and lead shot

Aft fuselage with symmetric and asymmetric horizontal loads

Load Tests Flaps and Control Surfaces

Ground Vibration Test and Flutter Analysis

Ground Vibration Test Conducted by ISMB Germany

Flutter Analysis Conducted by Norbert Niedbal

FAA Certification Meeting –

Certification by Subpart Standardized Testing Compliance issues (No unique Special Conditions Proposed)

Results – Acceptance & Agreements

Next Phase -

December 1, 2008 with FAA Small Aircraft Directorate

CONCLUSION : • The Evolution design is a completely different design philosophy than any previous Lancair Kit product.• Beginning with FAA Certification Standards as the basis, Lancair invested five years and 5 million dollars in getting it right.• Lancair International is committed to seek engineering solutions for all fleet aircraft not meeting the highest safety standards possible.