Flight Design USA CTLS presentation

CTLS
Fast. Comfortable. Safe.
…and Fun!
Ideal for Traveling
Dimensions
Main Dimensions:
Wing span 28 ft 2 in.
Length
21 ft 8 in.
Wing area 107.4 sq-ft
Technical Data
Performance at MTOW 1,320 pounds
VH: maximum horizontal speed
138
mph
120
kt
VNE: maximum permissible airspeed (red line)
168*
mph
145
kt
Take-off run (flap +15 degrees)
812
feet
Take-off distance over 50 foot obstacle
1500
feet
Take-off distance over 50 foot obstacle
962
st. mi.
830
NM
*The never-exceed speed (VNE) limited by the maximum deployment speed for the ballistic recovery system or
national regulatory requirements
Weight, Dimensions and Capacities
Typical empty weight (LSA version; well equipped, including parachute)
770
lbs
Maximum take-off weight
1320
lbs
Fuel capacity
34.3
gal
Occupants: 2 – allowed weight per occupant ( Minimum 120 lbs)
260
lbs
Luggage: luggage area maximum
55
lbs
600
kg
Flight Characteristics
• CTLS control forces are quite light. The stick forces are well within
the pilot effort limits of the requirements. Stick force increases at
higher G loads
• CTLS is stable about all three axes in cruising flight and can be
trimmed at any speed from 53 mph (47 knots) upwards
• CTLS has an excellent glide ratio allows more landing choices in
case of engine problems
• CTLS is safely controllable and maneuverable during takeoff climb
and landing
• Rapid reversal of banks and sideslips are easy without exceeding
any limitations, this allows an easy transition between any of the
normal flight conditions
Flight Configurations
• Full control can be maintained while retracting and extending
the flaps within normal operating range from 47 to 94 mph (4081 knots). Lateral, directional, and longitudinal control is easily
possible down to 47 mph (40 knots).
• Operation of flaps and aircraft controllability function easily
within the defined flaps limits. Pitch trim effects are limited and
can be easily countered with pitch trim adjustment.
• The aircraft reaction to throttle changes in all flight
configurations is smooth and proper; no need to readjust rudder
trim with changed power setting, not in climb or in cruise. No
pitching up or down due to changed power setting.
• Rain has not been found to adversely affect the handling of the
aircraft.
Low Speed Control
• Aircraft controllability at low speeds is improved through double
winglets.
• Under wings level stall the aircraft shows no tendency to drop the
wings.
• Stall remains fully controllable; average recovery demonstrates
~100 feet of altitude loss.
• There is no tendency for the aircraft to spin from any configuration
Spin Recovery
Aircraft can be easily recovered from a one-turn spin with controls
used for recovery in normal manner.
Section 1
CTLS Structure
Fuselage Structure
The airframe primarily constructed from quality carbon fiber composite
materials — which permit excellent aerodynamic characteristics to be
achieved at an efficient structural weight.
Wing Structure
The wing is rectangular, cantilevered and designed in two parts
that are connected, like gliders, by two spar ends. The two main
pins interconnect them so the wing has single spar structure.
There is integral fuel tank holding 17 gallons in the inboard
leading edge section of the wing.
Normal ribs
Spar cap
Stiff ribs
winglet
tongue
Spar cap
Root ribs
Sloshing rib
Fuel tank rib
skin
Spar wall
Section 2
CTLS Landing Gear
Landing Gear
The CTLS is equipped with fiberglass sandwich main tricycle
landing gear with a steerable nose wheel.
Main Landing Gear
The main landing gear is constructed from composite materials for
good strength. The cantilever spring design insures proper deflection
behavior with good dampening on landings.
Tundra Landing Gear Option
The aircraft can be equipped with size 6.00 – 6 inch Tires
with a 6 Ply Rating and for 1,750 lbs
Larger wheel pants are included in option.
Slightly lower tire pressure can be used.
Gear Leg Connection
Nose Gear
The nose gear strut is attached to the lower
section of the large engine mount.
The rotating section, using journal bearings,
makes it steerable via control rods which
are attached directly to the pedals in the
cockpit
This telescopic spring strut contains urethane
inserts that act as springs and dampeners,
effectively preventing porpoising.
Nose Gear
The gear consists of strut and shock cylinder and equipped with a
telescopic spring- damper element.
Nose Gear
The big engine mount is attached directly to the fuselage and the
nose gear is attached to this mount. The gear is secured with bolt on
the top of nose gear.
Nose Wheel
The 4.00 – 6 inch nose wheel tires are qualified for 75 mph (65
knots) and 662 pounds per tire. The six-ply tires are installed
directly on the wheel axle and secured with self-locking nut.
Section 3
CTLS Windscreen
and Windows
Windshield & Windows
The windshield and windows of the
CTLS are made of perspex
(plexiglass, acrylic glass) and are
formed at high temperatures.
Windshield & Windows
Superior side view through
large windows with generous,
adjustable ventilation
Section 4
CTLS Control System
Aileron Control System
Aileron Control System
Control stick
Inner rocker and intermediate
support
Guide pin
Right wing
root rib
Short push-rod
Rod rockers and
flap rocker
Aileron Control System
Rear support
Rod rocker outer holder
Stop bushes
Flap Control System
Transverse
rod
Flap push-rod
Beam
Right flap
Left
flap
Flap
actuator
Flap upper
rocker
Main
bulkhead
Flap Control System
Flap actuator
and T-bracket
Transverse rod rear view
Transverse rod
adjustment
Flap Control System
Flap
position
indicator
Flap
control
switch
Manual
override
Stabilator Control System
Rudder Control System
Cables
Rudder Control System
Turnbuckle
Lever
Rudder stop device
3-Axis Trim System
Aileron and Rudder trimming:
Rudder trim
control
Aileron trim
control
Trim position indicators
3-Axis Trim System
Stabilizer trimming
Trim
control
Cables
Stabilizer
Section 5
CTLS Fuel System
Fuel System
A fuel tank with a capacity of 17 gallons is integrated into each wing.
The diagram of the Fuel System is shown below.
Fuel flapper valve
Fuel flapper valve
Fuel Tank
A fuel tank with a capacity of 17 gallon is integrated in the inboard
leading edge section of the wing (“wet wing”).
Filler
cap
Sloshing
rib
Flapper
Valve
Fuel Intake
Fuel intake is conveyed through fuel screens in the wing root rib.
The intake located at lowest area of tank.
Fuel
intake
Fuel Lines
Fuel is gravity fed via two large volume steel lines in each A-pillar.
Even with almost empty tanks, sufficient fuel is available in sideslip
to ensure a safe landing. The fuel lines are jointed via a Yconnection inside the cockpit
Fuel line
Handle
Y-connection
Fuel Valve & Fuel Filter
• The fuel valve handle is located on the instrument panel and is
reachable by a pilot fastened with the safety belts.
• The fuel filter is located after the fuel valve and is easy removable
for maintenance.
• Fuel is drained from outside from the single-point fuel drain.
Fuel filter
Fuel valve
Fuel System Drainage
The fuel flows into the gascolator, which has an additional fine
filter, is the lowest system point and has the drain valve. The engine
pump takes fuel from this point, and sends fuel to the carburetors.
Unused fuel is pumped back to the gascolator.
Back line
Gascolator
Optional Fuel Sensors
The fuel pressure sensor and flow meter, if installed are in the
cockpit behind fuel filter.
The pressure sensor is installed in a separate line in engine
compartment.
Flow
meter
Pressure
sensor
Section 6
CTLS Cabin Heat &
Defrost Systems
Carb Heating System
The carburetor heat air comes from the same exhaust shroud for the
cabin heating system. Air for this shroud is supplied from an inlet
near the front underside of the lower cowling.
Air inlet
Cabin Heating System
Heat distribution in cockpit via ankle air nozzles
Hot air outlet
Defrosting System
Windscreen defrost air is provided from the top of the instrument
cowl (called the “mushroom”)
Control
handles
Heat
Source
Windscreen
Outlets
Carburetors
Cabin Heat
Hot air for
carburetors
Section 7
CTLS Electrical
Systems
Electrical System
Block diagram - power supply
The 12V electrical system
design is based on the
ASTM F2245 (design
specifications for LSA)
requirements for night
flight.
A 12V, 7Ah lead-gel battery
has a maximum output of
250 Watt
Charging is by a DC
alternator integrated into the
engine.
Electrical System
Block diagram — avionics
installation without VOR / HS34
Block diagram — avionics
installation with VOR / HS34
Section 8
CTLS Cockpit
Cockpit
Interior
•
Superior overview through large
window areas
•
Attractive two-tone interior
design
•
Wide and long cabin fits tallest,
or wider, pilots
•
Large gull-wing doors
•
Adjustable seats with 4-point
harness
• Variety of cockpit options
• Fire extinguisher
Safety Belts
The AmSafe airbag V23 System consist of these core components:
• Seatbelt airbag assembly (SAA)
• Cable interface Assembly and Retractable Extension cable assembly
• Electronics module assembly
• Inflator assembly
Section 9
CTLS Engine
Systems
Engine
CTLS is equipped by Rotax 912 ULS engine: 100 hp; TBO 2,000
hours.
As an option the engine can be equipped with a friction clutch and
thermostats for the oil and water-cooling systems.
Engine Control
The engine controls are located in the center console. The throttle
box is mounted into console behind the panel.
Warning! Choke only for warm up engine — never during flight!
Throttle
lever
Throttle
cables
Choke
cables
Holders
of levers
Stabilizer trim Choke lever
tab control wheel
Engine Control
Control cables are connected to carburetors. The engine default if cables
were disconnected is that the engine runs at full throttle.
Throttle
Cable
Choke
Right
Cable Carburetor
Left
Carburetor
Choke
Cable
Throttle
Cable
Firewall
Carburetor
Choke Lever
Carburetor
Throttle Lever
Carburetor
Choke Lever
Section 10
CTLS Brake Systems
Brake System
Brake System
Brake System
Brake is hand actuated via main cylinder using the brake handle.
Brake handle
Throttle
Parking
brake
Brake System
Main cylinder rod
Main cylinder
Section 11
CTLS Propeller
Propeller
Propeller
The CTLS may be equipped with various propellers:
• Neuform CR3-65-47-101.6 3-blade, composite propeller,
adjustable
• Sensenich 3-blade, composite propeller, ground adjustable
• Neuform CR3-V-R2H, 3-blade, hydraulically activated
variable pitch, composite propeller
• Kaspar- Brändel
propeller
KA1, 3-blade variable pitch, composite
Section 12
CTLS Instruments
and Panel
Instrument Panel
4
3
2
5
1
6
1
Vertical speed indicator small 21/4 inch,
analog
2
Slip indicator
3
Airspeed indicator large 31/8 inch,
analog
4
Three pointer altimeter large 31/8 inch,
analog
5
Analog engine instrumentation UMA
6
Hobbs hour counter
Instrument Panel
5
4
3
2
1
6
9
10
7
8
1
Altimeter small 21/4 inch, analog
2
Airspeed indicator small 21/4 inch,
analog
3
Autopilot FD Pilot 2 axis / 2 axis + VS
4
Dynon EFIS D60 Flight Information
System
5
GPS Garmin 495/496 (optional)
6
Analog engine instrumentation UMA
7
Hobbs hour counter
8
Radio Garmin SL 40 (optional)
9
Transponder Garmin GTX 327 Mode
A/C (optional)
10
Transponder Garmin GTX 328/330
Mode S (optional)
Instrument Panel
3
4
3
1
Transponder Garmin GTX330 Mode S
2
Radio Garmin SL 30 (optional)
3
Dynon Double Screen SkyView SVD1000 (synthetic vision)
Dynon Autopilot commanded from
SkyView Screens (optional)
2
1
4
GPS GArmin 696 XM (optional)
5
5
PS Engineering PM 3000 intercom
6
6
ELT Artex ME406 406Mhz
Instrument Panel
4
3
5
2
1
3
6
9
8
7
1
Altimeter small 31/8 inch, analog
2
Airspeed indicator small 31/8 inch,
analog
3
Garmin Double Screens G3X PFD /
MFD
4
Trutrak FD-Pilot II VSGV Autopilot
(optional)
5
Trutrak ADI-instrument to display bank
angle, pitch and direction (electronic
directional gyro)
6
Garmin GMA 240 audio panel
7
Garmin GNS 530 W Nav / Com / GPS
(optional)
8
Radio Garmin SL30 (standart)
9
Transponder Garmin GTX330 Mode S
10
ELT Artex ME406 406Mhz
10
Section 13
CTLS Avionics
Avionics
G3X
• Garmin G3X - a multifunctional
device that is designed to display
flight information and equipped with
one, two or three displays;
• The functional unit includes a
magnetometer, ADAHRS and
monitoring of the engines;
• The sensors also allow to deduce
information about the temperature of
the cylinder heads, exhaust gas
temperature, oil temperature, the state
fuel pump and much more.
Avionics
Dynon
SkyView
• Very bright, high-resolution screens
driven by advanced graphic
processors create highly visible and
readable displays. Screen resolutions
are 1024x600, Brightness is over 1350
nits. Displays are fully dimmable for
night flight;
• Two multi-position joysticks offer
easy and intuitive control of your
SkyView displays;
• SkyView Displays are shipped with a
U.S. and South American terrain
database installed. Every other region
of the world can be downloaded from
our Worldwide Terrain Data page.
Avionics
Dynon SkyView
• A system backup battery will provide
over an hour of backup power to a
Display and Modules. Each Display
requires its own Backup Battery for
redundancy;
• SkyView can be mounted closer to the
engine, allowing easier wire routing;
• The SV-ADAHRS-200 is a complete
MEMS-based attitude reference and
air data computer, integrated with a
digital compass;
• Integrated autopilot;
• SkyView includes standalone HSIs
Transponder
• Garmin GTX327 Mode A/C
Full-featured digital transponder features 200-watt output and
dedicated pushbutton keys for squawk code selection, plus a
pilot selectable datafield.
Transponder
• Garmin GTX330 mode A/C/S with TIS
250-watt digital transponder is IFR-certified and offers data link
capabilities with Traffic Information Services (TIS) interface.
Includes a pilot selectable datafield and optionally provides ADS-B
out with extended squitter.
Transponder
• Garmin GTX328 mode A/C/S without TIS
All solid-state transponder designed to satisfy European
VFR/Class 2 requirements. Features pushbutton squawk code
selection.
Circuit Breaker Panel
Each electrical device is connected via a thermal
circuit breaker (ETA 2-5700-IG2-K10-DD) located
on breaker panel.
Section 14
CTLS Battery
Battery
Hawker SBS8
Hawker SBS15
Battery Installation
Battery installed on firewall,
using composite bracket.
Backup Battery
Dynon EFIS D100, FlightDeck D180, EFIS
D60, Garmin GPS496/696 have internal
backup battery.
• Dynon SkyView SV-D1000 has external
backup battery SV-BAT-320 (1 per each
screen).
Backup battery
• Garmin G3X system has backup battery IBBS-12V-4AH:
Technical data:
Input: 10-15 volt DC
Output: 12 volt, 6 Amp
Capacity: 4Ah
Section 15
CTLS Lighting
Lights
Tail light
Lights
Wingtip Lights
Lights
Anti Collision Light Thiesen ERB, ACL 2 - RED
Lights
Landing light
Lights
LED landing light Whelen
model 71125
LED landing light
Whelen model 71424
Lights
Cockpit light
Section 16
CTLS Warning
Systems & Antennae
Warning System
CTLS warning system consist of:
• Panel alarm lights: EMSrelated alarm ”Engine Alarm”
and Alternator/Rectifier alarm
“Generator Alarm”
• Instrument built-in
preconfigured alarm indicators
• Audio alarm output is
connected via intercom and
headsets
Antenna
• COMM antenna Comant CI 121 and ELT antenna
Antenna
• Transponder antenna Comant CI 105
Section 17
CTLS Airframe
Emergency Parachute
Rescue System
The Airframe Emergency Parachute System is installed as standard
equipment on the CTLS Light Sport Aircraft.
1
2
Rescue System
The following Airframe Emergency Parachute Systems is installed on
the aircraft (in the USA)
• BRS 1350 HS (canister)
The parachute system is attached with 2 front harnesses and 2 rear
harnesses. All 4 harnesses (item 2) are joined together with metal
link. The parachute is connected with link using incremental bridle
(item 1).
The parachute system is activated by an activation handle.
When the parachute recovered the aircraft is suspended under the
parachute with approx. 13° nose down.
Harness Installation
The harnesses are attached to primary structure of aircraft and
properly secured to prevent damaging or loosen during normal
operation.
The front harnesses are attached to the arms of big engine mount.
The each harness is looped around the arm at the point where the big
engine mount attached to the fuselage. The big engine mount is a
steel structural part. The harnesses routed in fuselage along A-pillar,
through fuselage root rib to luggage compartment. The harnesses are
properly folded and packed in manner to ensure that the harnesses
will be satisfactory stripped free during extraction and parachute
deployment.
BRS 1350 Installation
Rescue System
The handle activation is installed on the top of tunnel between
occupant seats
Handle for
rescue system
activation
Remove Pin
Before Flight!
Section 18
CTLS Aircraft
Operating
Instructions
Aircraft Operating
Instructions
TABLE OF CONTENTS:
• General
• Limitations
• Emergency Procedures
• Normal Procedures
• Performance
• Weight and Balance, Equipment
Introduction
Limitations
Limitations
Limitations
Limitations
Emergency Procedures
Emergency Procedures
Emergency Procedures
Emergency Procedures
Emergency Procedures
Normal Procedures
Normal Procedures
Performance
Weight and Balance
Weight and Balance
Flight Design CTLS…
the Best Choice for the
Professional Flight School
ARE YOU FLYING LESS THESE DAYS?
WE CAN CHANGE THAT!
FLIGHT DESIGN USA
Tel.: 860 - 963 - 7272 • Fax: 860 - 963 – 7152
[email protected]
www.FlightDesignUSA.com
FLIGHT DESIGN GmbH
[email protected] www.FlightDesign.com

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