Flight Design CTSW LSA Aircraft Operating

Transcription

Flight Design CTSW LSA
Aircraft Operating Instructions
CTSW2006
SERIAL NUMBER:
THIS DOCUMENT AND THE TECHNICAL DATA HEREON DISCLOSED ARE PROPRIETARY TO FLIGHT DESIGN AND SHALL
NOT BE USED, RELEASED, OR DISCLOSED IN WHOLE OR IN PART WITHOUT EXPRESS WRITTEN PERMISSION FROM
FLIGHT DESIGN
FLIGHT DESIGN
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Aircraft Type: CT-LSA
Page: 2
Table of Contents
Flight Design CTSW LSA ................................................................................................ 1
SERIAL NUMBER: .......................................................................................................... 1
1 Table of Contents ................................................................................................. 2
2 General Information .............................................................................................. 4
3 Airplane and Systems Descriptions ...................................................................... 9
3.1
Engine: Rotax® 912 ULS .............................................................................. 9
3.2
Propeller ...................................................................................................... 11
3.3
Fuel and fuel capacity.................................................................................. 12
3.4
Oil ................................................................................................................ 12
3.5
Operating weights and loading (occupants, baggage, fuel, ballast) ............ 12
3.6
Structures and Systems Description............................................................ 13
4 Operating Limitations.......................................................................................... 18
4.1
Stalling speeds at maximum takeoff weight (VS1 and VS0)........................ 18
4.2
Flap extended speed range (VS0 to VFE)................................................... 18
4.3
Maximum maneuvering speed (VA) ............................................................ 18
4.4
Never exceed speed (VNE) ......................................................................... 18
4.5
Crosswind and wind limitations.................................................................... 18
4.6
Service Ceiling............................................................................................. 19
4.7
Load factors................................................................................................. 19
5 Weight and Balance Information......................................................................... 21
5.1
Installed equipment list ................................................................................ 21
5.2
Center of gravity (CG) range and determination.......................................... 22
6 Performance: ...................................................................................................... 27
6.1
Takeoff and landing distances ..................................................................... 27
6.2
Best rate of climb......................................................................................... 27
6.3
Best angle of climb ...................................................................................... 27
6.4
Cruise speed ............................................................................................... 27
6.5
RPM ............................................................................................................ 27
6.6
Fuel consumption (gallons (liters) per hour) ................................................ 27
7 Emergency Procedures ...................................................................................... 28
8 Normal Procedures............................................................................................. 30
8.1
Preflight ....................................................................................................... 30
8.2
Engine start: ................................................................................................ 32
8.3
Taxiing......................................................................................................... 32
8.4
Normal Takeoff ............................................................................................ 33
8.5
Climb ........................................................................................................... 33
8.6
Cruise .......................................................................................................... 33
8.7
Descent ....................................................................................................... 33
8.8
Before Landing ............................................................................................ 33
8.9
Normal landing ............................................................................................ 33
8.10 After Landing ............................................................................................... 33
8.11 Shut down ................................................................................................... 34
8.12 Short field takeoff and landing procedures .................................................. 34
8.13 Balked landing procedure............................................................................ 34
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8.14 Information on stalls, spins and other useful pilot information ..................... 34
Aircraft Ground Handling and Servicing.............................................................. 35
9.1
Servicing fuel, oil, and coolant ..................................................................... 35
9.2
Towing (moving) and tie-down instructions ................................................. 35
10
Required Placards and Markings .................................................................... 36
10.1 Airspeed indicator range markings .............................................................. 36
10.2 Operating limitations on instrument panel ................................................... 36
10.3 Passenger Warning ..................................................................................... 36
10.4 “NO INTENTIONAL SPINS” ........................................................................ 36
10.5 Miscellaneous placards and markings......................................................... 36
11
Supplementary Information: ............................................................................ 38
11.1 Familiarization flight procedures .................................................................. 38
11.2 Pilot operating advisories ............................................................................ 38
12
Supplements ................................................................................................... 38
12.1 Three blade Neuform propeller.................................................................... 38
13
Revisions ........................................................................................................ 39
Appendix 1.
Equipment List .................................................................................. 41
AIRPLANES & ACCESSORIES............................................................................. 41
ENGINE MANAGEMENT (not with Dynon EFIS/EMS) .......................................... 48
AVIONIC & INSTRUMENTS .................................................................................. 49
Appendix 2................................................................................................................. 51
Variants of instrument panels for standard instrument board..................................... 51
Appendix 3................................................................................................................. 56
Variants of instrument panels for “Enlarged instrument panels” (Z-10113)................ 56
Appendix 4................................................................................................................. 61
Instruction for the flap manual operation................................................................... 61
9
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Note: In accordance FAR 21.190 Flight Design has established Aircraft Operating Instructions for the
CTSW. The content and format is defined by ASTM standard F2245 and supplemented as deemed
necessary by the manufacturer.
2
General Information
Read this before your first flight!
Each pilot must be familiar with the contents of the Aircraft Operating Instructions
Manual and abide by all placards, limitations and checklists. Additionally, all Service
Directives must be complied with and the Maintenance and Inspections Procedures
manual must be used for all maintenance. For maintenance of the Rotax ® engine, the
BRS emergency parachute system, and other installed equipment, refer to the original
manufacturers’ manuals.
Flight Design CT-LSAs are delivered worldwide, and comply with a variety of Light Sport
airworthiness standards. All configurations are equipped with non-certified engines that
meet ASTM standard F 2339. Unless otherwise specified, the information given is
common to all configurations. Where different, the information is given in the
appropriate appendices and supplements.
The Flight Design CTSWs delivered in the U.S.A. are built to conform to the U.S. Light
Sport Pilot rules and are intended for Day/VFR use.
This manual is for guidance when operating a CTSW aircraft and is not intended to
substitute for any required training received from an appropriately rated flight instructor.
Manufacturer:
Flight Design GmbH
Sielminger Str. 65
D – 70771 L.-Echterdingen
Basic description:
The CTSW is a conventional, two seat, high-wing aircraft, with three-axis controls.
The wings are fully cantilevered, incorporate integral fuel tanks, pushrod actuated
ailerons and slotted type flaps that extend downwards for slow speed flight, and reflex
upwards for cruise flight.
The aircraft is equipped with an all-moving stabilator with a trim tab and tricycle landing
gear with a steerable nose-wheel.
The primary structures are made of carbon fiber reinforced plastic.
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Views, dimensions:
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Page Intentionally Left Blank
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Airplane and Systems Descriptions
3.1
Engine: Rotax® 912 ULS
Description:
The Rotax 912 ULS is a four cylinder, horizontally opposed, normally aspirated four
stroke engine that incorporates air cooled cylinders with liquid cooled heads.
The propeller is driven via a 2.43 to 1 reduction gear box.
Limitations:
Performance (sea level, ISA):
Idle speed:
Oil pressure:
Oil temperature:
Cylinder head temperature:
Fuel pressure:
Engine starting and operating
Temperature limits:
100 hp @ 5800 rpm (5 min)
95 hp @ 5500 rpm continuous
1400 rpm approx.
29 to 73psi. (Normal range)
102psi.max. during a cold start
12psi is allowable below 3500 rpm
266°F (130°C) max
120°F (50°C) min
190-230°F (90-110°C) normal operating range
284°F (135°C) max.
2.2 to 5.8 psi max.
-13°F (-25°C) Min.
120°F (50°C) Max.
For a complete description of the engine and limitations, see the Rotax 912 Operator’s Manual.
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3.2
Propeller
The standard propeller is a Neuform TXR2-65-47-101.6, which is a 2-blade, composite,
ground adjustable propeller.
For the optional Neuform three blade carbon fiber propeller, CR3-65-47-101.6 see the AOI supplements.
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3.3
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Fuel and fuel capacity
Fuel specification: Premium Automotive Unleaded per ASTM D 4814, minimum AKI 91
for Rotax 912ULS.
Each wing has an integral fuel tank with a capacity of 17.1 gallons (65L) of which 16.5
gallons (62L) are usable.
The total fuel capacity is 34.2 gallons (130L), of which 33.0 gallons (124L) are usable.
For complete fuel specifications see the Rotax 912 Operator’s Manual.
3.4
Oil
Only Name-brand, semi-synthetic or full synthetic, 4-stroke motorcycle oil should be
used.
The engine is equipped with a friction clutch to guard against sudden propeller
stoppage: for this reason, oils with friction modifiers or additives that favor clutch
slippage should not be used.
Diesel engine oils are unsuitable because of their lower temperature tolerances.
For oil change intervals, see the Maintenance and Inspection Procedures Manual.
Note: If the engine is primarily run on AVGAS, more frequent oil changes will be
required because of possible lead build-up.
Oil capacity:
Max. Oil consumption:
3.2 quarts. (min. 2.1) or 3 liters (min. 2)
0.2 pt/hr or 0.1 l/hr
Note: For complete oil specifications see the Rotax 912 Operator’s Manual.
3.5
Operating weights and loading (occupants, baggage, fuel, ballast)
Maximum take off weight:
Typical empty weight:
Typical useful load
Maximum weight per seat:
Maximum baggage weight per side:
Maximum fuel load (34.2 gal)
Minimum single pilot weight
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1320 lbs
685 lbs
635 lbs
260 lbs
55 lbs
205.2 lbs
120 lbs
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(600 kg)
(311 kg)
(289 kg)
(118kg)
(25 kg)
(93.2 kg)
(54 kg)
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3.6
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Structures and Systems Description
Fuselage:
The fuselage of the CTSW is made of multiple layers of carbon fiber and aramid
(Kevlar®) laminated over a dense foam core creating a sandwich structure. The cabin
can resist loads from all sides. This provides superior pilot and passenger crash
protection and low structural weight.
Wings:
The cantilevered wing of the CTSW plugs into 4 hard points at the top of the cabin for
attachment to the fuselage. The overlapping spars resist lift loads. The main spar caps
are solid carbon fiber wrapped with S glass fibers over a dense Rohacell core. The
wing “skin” is a carbon fiber sandwich. The ribs are molded carbon fiber and bonded
into place.
Wingtips:
The wingtips of the CTSW are highly developed drooped type. They reduce stall speed,
improve stability and low speed control of the CTSW.
Fuel system:
Fuel is gravity fed to the engine from two integral wing tanks. The total capacity is 34.2
gallons (130L). The usable fuel quantity is 33.0 gallons (124L).
The operation of the fuel valve does not allow the ignition key to be inserted unless the
fuel valve is in the “On” position.
Electric system:
The Rotax 912 series of engines are equipped with a “Lighting Coil” type alternator and
a rectifier-regulator that converts and regulates the output of the alternator to a nominal
13.5 V – 14.2V 250W (roughly 18A).
The battery for the electric starting system is 12V sealed, AGM type.
The dual ignition system is a CDI (capacitive discharge).
Landing gear:
The landing gear of the CTSW is of the tricycle type. The nose wheel is steerable
through a direct link to the rudder pedals. The main gear legs are heavy duty machined
aluminum rods.
Brakes:
Hydraulic disk type, actuated through a handbrake lever. Parking brake is set by
simultaneous use of the brake lever and parking brake valve.
Control surfaces: The movable surfaces of the CTSW are of aramid-foam-aramid,
carbon-foam-aramid, carbon-foam-carbon sandwiches with carbon fiber spars and
attachment points.
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Rudder:
The rudder is of a conventional type and it is aerodynamically balanced and is operated
through foot pedals and cables.
Stabilator:
The stabilator is an all-moving type stabilizer with a counter-weight and anti servo/trim
tab. It is actuated through a flexible push pull cable connected to the dual control sticks.
Ailerons:
The Frise type ailerons are controlled with push pull tubes and rod bearings and droop
automatically with selection of the flaps.
Flaps:
The flaps are of the slotted type, and a pre-selector switch is used to position the flaps
from -6° (or -12°) to +40º. The position of the flaps is indicated on the control panel. The
flaps are protected by limit switches at the end limits.
Pitch Trim:
Pitch trim is activated through a control wheel located adjacent to throttle quadrant, and
acts upon trim tab on the stabilator.
Aileron Trim:
Aileron trim is activated trough a control wheel located on the console between the pilot
seats.
Rudder Trim System:
Rudder trim is activated through a control wheel located on the cabin bulkhead above
the console and between the pilot seats.
BRS Parachute system:
Rocket deployed emergency parachute system. The system is actuated through the
red, “T” handle located on the cabin bulkhead between the pilot seats. The T handle is
secured on the ground with a tagged safety pin. The pin is removed for flight operations.
To deploy the parachute, the T handle is pulled out fully to the stop.
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*Standard Instrument Panel
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* - instrument panels can be choosen from the standard list (please see Appendix 2 [or Appendix
3 – for Z-10113 “Enlarged instrument panels”]) with accordance to the list of the instruments from
the Customer Order
Control Quadrant
Flap position indicator
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Ignition switch and starter
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FLYdat display: Rotax 912 ULS
Display
1
2
3
4
5
6
7
8
Description
Engine speed
Hours of operation
Exhaust gas temp. Forward
Exhaust gas temp. Aft
Cylinder head temperature
EGT Left / Right display*
Oil temperature
Oil pressure
Unit
RPM
hour
ºF (ºC)
ºF (ºC)
ºF (ºC)
Arrow
ºF (ºC)
PSI
Resolution
1
0.1
1 or 10
1 or 10
1
N/A
1
0.1
*note: The arrowhead pointer ← symbolizes left cylinder series.
The arrowhead pointer → symbolizes right cylinder series.
The left to right switching occurs at 6 to 8 second intervals.
For a detailed description of the system, see the FLYdat User’s guide.
FLYdat Warning and Alarms for the 912 ULS
Display
Engine speed
EGT
CHT
Oil temperature
Oil pressure: Max.
Oil pressure: Min
Unit
RPM
ºF(ºC)
ºF(ºC)
ºF(ºC)
PSI
PSI
Warning
5800
1616 (880)
302 (135)
284 (130)
87
(6.0 bar)
29
(2.0 bar)
Alarm
6000
1652 (900)
320 (145)
302 (140)
116 (8.0 bar)
14.5 (1.0 bar)
When one or more Warning limit value is exceeded, it is indicated on the display by
flashing numbers, and the warning (alert) lamp also flashes.
When one or more Alarm limit value is exceeded, it is indicated on the display by
flashing numbers, and the warning (alert) lamp illuminates continuously.
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Operating Limitations
4.1
Stalling speeds at maximum takeoff weight (VS1 and VS0)
VSO: Stalling speed or the minimum steady flight speed in the landing configuration.
VS1: Stalling speed or the minimum steady flight speed obtained in a specific
configuration.
VS
VS1
VS0
Flaps -6° (-12°)
Flaps 0°
Flaps 40°
44 KCAS (49 KCAS)
42 KCAS
39 KCAS
81 kmCAS (90 kmCAS)
77 kmCAS
72 kmCAS
4.2
Flap extended speed range (VS0 to VFE)
The White arc on the airspeed indicator is from VS0 to VFE Flaps 15°
VFE: Maximum flap extended speed.
VFE:
Flaps
0°
15°
30°
40°
100 KCAS
80 KCAS
62 KCAS
62 KCAS
185 kmCAS
148 kmCAS
115 kmCAS
115 kmCAS
4.3
Maximum maneuvering speed (VA)
VA: Design maneuvering speed. (Above this speed, full or abrupt deflection of the
control surfaces may cause structural failure).
VA:
98 KCAS at 1320 lbs
184 kmCAS
Never exceed speed (VNE)
4.4
VNE: Never-exceed speed
VBRS: Maximum emergency parachute system operating speed.
VNE:
VBRS:
145 KCAS
160 KCAS
269 kmCAS
296 kmCAS
4.5
Crosswind and wind limitations
The maximum demonstrated crosswind is 16 Kts (30 km).
CAUTION: Due to the light operating weights and low minimum flight speeds of Light
Sport Aircraft, operations with surface winds in excess of 25 knots (46 km) should not
be attempted.
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4.6
Service Ceiling
The Service Ceiling is the maximum altitude at which a climb rate of 100 ft/min. can be
achieved. For the CTSW it is 14,000 feet (4,250 m).
Note: An aircraft must be properly equipped and the pilot appropriately certificated for
operations above 10,000 feet (3,000 m).
Load factors
4.7
The maximum limit load factor is:
+ 4 g/ -2 g
+ 2 g/ -0 g
Flaps up
Flaps down
4.8 Maneuvers
Aerobatics, including intentional spins are prohibited.
Other limitations:
Flight in to known icing is prohibited
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Weight and Balance Information
5.1
Installed equipment list
Please see the Appendix 1.
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Center of gravity (CG) range and determination
5.2.1 Method for determining the Basic Empty Weight:
Place the aircraft level on three suitable scales. (If only one scale is available, use
leveling blocks and make separate measurements at each gear location).
The aircraft leveling reference is the top of the console (tunnel) that runs between the
pilot seats.
Note the following measurements:
G1: The weight found at the nose wheel location
G2: The combined weight found at the main wheel locations.
a:
35.63’’ (905 mm) The distance from the leading edge of the wing to the nose
wheel.
b:
58.07’’ (1475 mm) The distance from the main gear location to the nose wheel
location.
The Basic empty weight is the total of weights found at G1 and G2
G1 + G2 = G
Using the following formula, find the Empty Center of Gravity location of the aircraft.
((G2 x b): G) – a = X
X
The distance from the leading edge of the wing to the Cg location
Using the weights found on the scales and the weight and balance sheet determine the
Basic Empty Weight.
Complete the Weight & Balance and Equipment List.
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Sample Weight & Balance and Equipment List:
The acceptable empty Cg range is 9.45 to 13.78 inches.
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The acceptable empty Cg range is 240 to 350 mm.
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5.2.2 Determining the Weight and Balance
Using the following examples, find the loaded center of gravity location.
Using the center of gravity envelope, plot the loaded center of gravity.
Loaded Aircraft Cg Location:
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Performance:
The performance figures are based on sea level and standard atmospheric conditions
and a gross weight of 1320 lbs (600 kg) unless otherwise noted.
Takeoff and landing distances
6.1
Take-off distance over a 50ft (15 m) obstacle:
Landing distance over a 50ft (15 m) obstacle
762ft
967ft
(235 m).
(295 m).
112 kts
(205
6.2
Best rate of climb
VY = 78kts (154 km\h).
6.3
Best angle of climb
VX = 66 kts (122 km\h).
6.4
Cruise speed
Cruise speed at 75% power:
6.5
RPM
Minimum Idle:
Static
Normal climb
Maximum
Max. continuous
Normal cruise
Cruise @ 75%
km\h).
1400
4700
4800
5800 (5 min)
5500
4200 – 5200
5200
6.6
Fuel consumption (gallons (liters) per hour)
Climb power:
5.12
(19L)
Normal Cruise power:
3.44. – 5.82 (13 – 22L)
Max cruise:
6.88
(26L)
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Emergency Procedures
Engine failure:
The first action in the event of an engine failure is to lower the nose and to establish
best glide speed: 63 kts (115 km\h). If the failure occurs during takeoff, it is often best to
attempt a landing straight ahead and under control rather than try to turn and return to
the runway.
The next action should be to identify a field for landing, taking in to consideration
obstacles, field length, and wind direction.
Maintain a minimum speed of 63 kts(115 km\h) / 15° flaps until final approach.
Before touchdown, select flaps 40°
If there is sufficient time and the failure can be identified, a restart may attempted.
If the restart is successful it may be possible to proceed to a suitable landing area and
perform a precautionary landing.
Engine Failure:
In the event of fire shut off the engine:
Turn off the ignition
Shut off the fuel valve
Slip away from the fire if possible
Land as soon as possible
The Emergency Parachute system (BRS):
The BRS system may be used at a variety of altitudes and airspeeds. Situations that
might warrant it’s use may include;
•
•
•
•
•
•
•
A loss of control in Instrument Meteorological Conditions
A structural failure
A collision in flight
An irrecoverable spin
Pilot incapacitation
Jammed flight controls
Engine failure over hostile terrain
If possible, before activating the BRS, shut off the engine and tighten the seatbelts.
To activate the system, pull the T handle all the way to the stop.
CAUTION: The operator of a CTSW must be thoroughly familiar with the contents of the
BRS 1350 LSA Parachute Manual and abide by all instructions and limitations within.
Overturn on land:
•
•
•
Carefully unfasten the seat belts and lower yourself first, then your passenger.
Be careful of any spilled fuel – there may be a fire hazard!
Leave the airplane immediately.
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Normal Procedures
8.1
Preflight
A. Cabin
1. Aircraft documents
2. Flight controls
3. Spar Bolts
4. Ignition
5. Electrical equipment
6. Radio master
7. Master Switch
8. Flaps
9. Master switch
10. Fuel Valve
Check
Free and correct
Installed and secure
Off, key out
Off
Off
On
Down
Off
On
B. Left side
1. Main gear and tire
2. Baggage compartment
3. Antenna
4. Aft fuselage condition
5. Tie down
6. Vertical Stabilizer
7. Stabilator
8. Servo tab
9. Tie-down
10. Rudder
Check
Secure
Check
Check
Remove
Check
Check
Check
Remove
Check
C. Right Side
1. Vertical Stabilizer
2. Aft fuselage condition
3. Baggage compartment
4. Main gear and tire
Check
Check
Secure
Check
D. Left wing
1. Flap
2. Aileron
3. Wing tip
4. Wing leading edge
5. Pitot tube
6. Tie down
7. Fuel cap
Check
Check
Check
Check
Check
Remove
Secure
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E. Nose
1. Cowling
2. Exhaust stack
3. Nose gear
4. Engine intakes
5. Landing Light
6. Spinner
7. Propeller
8. Cowling
9. Oil quantity
10. Fuel
10. Static port
Secure
Secure
Check
Clear
Check
Secure
Check
Secure
Check
Drain and Check
Clear
F. Right Wing
1. Leading edge
2. Fuel Cap
3. Tie down
4. Wing tip
5. Aileron
6. Flap
Check
Secure
Remove
Check
Check
Check
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Engine start:
1. Preflight
2. Parking Break
3. Carburetor heat
4. Circuit breakers
5. Radios and Electrical equipment
6. Master Switch
7. Anti-collision lights
8. Fuel Valve
9. Ignition key
10. Choke
11. Throttle
12. Ignition Switch
13. Choke
14. Oil pressure
15. Radios
16. Flaps
Complete
Set
Off
In
Off
On
On
Open
In
As required
Closed
Start and release
Adjust
Check
Set
Up
8.3
Taxiing
1. Breaks and Steering
Check
Before Takeoff
1. Parking Brake
2. Seat belts
3. Doors
4. Flight Controls
5. Flight Instruments
6. Choke
7. Carburetor heat
8. Throttle
9. Engine Indications
10. Ignition
Set
Secure
Closed
Free and correct
Set
Off
Off
3200 rpm.
Check
Check Left, Right, & Both
(max. drop 300 rpm./ max. diff. 120 rpm.)
11. Oil temperature
11. Throttle
12. Flaps
13. Trim
14. Radios
15. Parking Brake
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Idle
Set
Set
Set
Release
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Page: 33
Normal Takeoff
8.4
1.
2.
3.
3.
Flaps
Throttle
Carb heat
Climb
0° to 15°
Full
Off
59 kts (110 km\h) Flaps 15°
86 kts (160 km\h) Flaps -6°
Climb
8.5
1. Flaps
Flaps -6°
2. Airspeed
86 kts (160 km\h)
3. Power
5500 rpm (max. continuous)
Note: Best angle of climb speed: Vx = 66 kts, Flaps 0
Best rate of climb speed Vy = 78 kts, Flaps 0
Cruise
8.6
1. Power
2. Engine Instruments
Set
Check
Descent
8.7
1. Carburetor heat
2. Altimeter
As required
Set
Before Landing
8.8
1. Seatbelts
2. Airspeed
3. Flaps
Secure
54 kts
15° to 40°
(100 km\h)
Normal landing
8.9
Flaps
Airspeed
8.10
After Landing
1. Landing light
2. Flaps
AU 010 01000
Off
Retract
Rev. No.:3
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8.11 Shut down
1. Parking brake
2. Radios
3. Electrical equipment
4. Ignition
5. Master switch
Set
Off
Off
Off
Off
8.12 Short field takeoff and landing procedures
Flaps
15°
Parking brake
Set
Power
Full
Brakes
Release
Rotate
44 kts
(80 km\h)
8.13 Balked landing procedure
Power
Flaps
Airspeed
(110 km\h)
8.14
Full
15°
59 kts
Information on stalls, spins and other useful pilot information
Stalls:
The CTSW exhibits conventional characteristics with a slight buffet at the onset of the
stall. There is no tendency to roll in a coordinated stall. Directional control should be
maintained through use of the rudder.
Recovery is also conventional: release pressure on the control stick to reduce the angle
of attack. Apply full power, and slowly recover.
Spins
The CTSW is not certified for spins
In the event of an unintentional spin:
1. Reduce power to idle
2. Center the ailerons
3. Apply rudder in the opposite direction of rotation
4. When the rotation stops, smoothly recover from the resultant dive.
If an unintentional spin is entered and the altitude is such that a safe recovery cannot be
made, the ballistic parachute system should be deployed.
Steep turns
Enter with coordinated use of rudder and ailerons. Increase pitch and power as
necessary to maintain altitude and airspeed. Do not exceed 60° of bank angle.
Lead the roll out the number of degrees equal to half the bank angle.
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9
Page: 35
Aircraft Ground Handling and Servicing
9.1
Servicing fuel, oil, and coolant
Fuel
The fuel tanks are equipped with vented fuel caps that are located on the upper surface
of the wing. The fuel caps must be in place for flight, with the vents facing forward. A
calibrated dip stick, with left tank and right tank indications, is supplied to check the fuel
quantity. The aircraft must be grounded during refueling. Should fuel be spilled on the
Note: The aircraft finish may be damaged by exposure to fuel; any spills should be
immediately cleaned up.
Oil
For an accurate oil measurement:
1. Set the Parking brake
2. Check the Master switch is off, and the Ignition key is out.
3. Remove the top cowling.
4. Open the Oil tank
5. Turn the propeller 3 to 4 times in the direction of rotation.
6. Check the oil level
Coolant
To check the coolant level:
1. Set the Parking brake
2. Check the Master switch is off, and the Ignition key is out.
3. Remove the top cowling.
4. Open the cap of the coolant tank and add coolant to fill up the tank.
5. Make sure that no air is inside the cooling system.
6. Close the coolant tank cap.
7. If necessary, add coolant to the expansion tank.
9.2
Towing (moving) and tie-down instructions
Moving the CTSW:
The aircraft can be moved by one person.
1. Check that the parking brake is off.
2. Check that the area around the aircraft is clear of obstacles and people.
3. Push down on the tail boom of the aircraft to lift the nose gear off the ground.
4. Push the aircraft in needed direction.
Tie down instructions:
1. Install mooring lines from the ground to the tie-down rings on the undersurface of
the wings.
2. Place the tail boom tie-down strap around the tail boom and secure to the ground
with mooring lines.
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10 Required Placards and Markings
10.1 Airspeed indicator range markings
White range (flap operating range)
39 ... 62 kts (72 … 115 km/h)
Green range (normal operating range) 44 ... 120 kts (81 … 222 km/h)
Yellow range (caution range)
120 ...145kts (222 … 269 km/h)
Red line
(never exceed speed)
145 kts
(269 km/h)
10.2 Operating limitations on instrument panel
MAX: RPM 5800, EGT 1616F, CHT 248F, Oil Temp. 266F, Oil Press. 102 psi
or
MAX: RPM 5800, EGT 880ºС, CHT 120ºС, Oil Temp. 130ºС, Oil Press. 7 bar
10.3 Passenger Warning
The warning “This aircraft was manufactured in accordance with Light Sport Aircraft
airworthiness standards and does not conform to standard category airworthiness
requirements” is placed on the instrument panel or in a place where a passenger will
see it.
10.4 “NO INTENTIONAL SPINS”
The placard “NO INTENTIONAL SPINS” is placed close to the airspeed indicator.
10.5
Miscellaneous placards and markings.
Type of Fuel: 2 x beside filling cap
Tachometer
5800 RPM
Oil pressure gauge
max 102 psi 7 bar
min 12 psi 0,8 bar
Oil temperature gauge
266ºF
130ºС
for ULS,
Water temperature gauge 248ºF
120ºС
for ULS, cylinder head
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Throttle
lever box
Choke
lever box
Stabilator Trim
lever box
Brakes
lever box
Flaps
-6° (-12°), 0°, 15°, 30°, 40°
Oil quality
flap indicator
oil tank
Circuit Breakers
left side of the central console
Main Circuit Breakers
right side of the central console
Maintenance/packing interval
BRS Manual & Chute placard
Baggage Compartment
Baggage area
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11 Supplementary Information:
11.1
Familiarization flight procedures
See the Pilot Training Supplement for familiarization procedures
11.2
Pilot operating advisories
None at this time
12
Supplements
12.1
Three blade Neuform propeller
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13 Revisions
The Revisions pages are updated by Flight Design each time revision is issued. They
contain a list of all revisions made to the Pilot Operation Handbook since its original
issue.
Revision No.
Original Issue
Date Released
28.02.2005
Affected
Chapters
N/A
2
3
20.07.2005
05.10.2005
05.04.2006
AU 010 01000
Approved By
N/A
2 General Information
1
Affected
Pages
6; 8
3 Airplane and Systems
Descriptions
13; 14
4 Operating Limitations
15; 17; 19
10 Required Placards
and Markings
36
4.5Crosswind and wind
limitations
6 Performance
15
27
8.2 Engine starting
31
8.4 Normal takeoff
32
8.5 Best angle of climb
speed (VX);8.6 Cruise
10.5Miscellaneous
placards and markings
Total revised; Name of
document
changed;
insert part 12, Appendix
1,
Appendix
2,
Appendix 3, Appendix 4
33
Rev. No.:3
36
1-62
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Appendix 1.
Page: 41
Equipment List
Please check local certification rules !
AIRPLANE READY TO FLY CONSIST OUT OF A COMPONENT
"A"
CT 2006
MTOW 600kg (safe load 4 g) Vne 301 km/h
Certification UK 450 kg - Germany 472,5 kg - Australia 544 kg Canada 560 kg - USA 600 kg
Description
AIRPLANES & ACCESSORIES
A-10001
Airplane BfU/LTF-UL CTSW 2006 ready to fly no rescue
Equipment
Shortwings with downwards orientated winglets (reduces induced
drag and increases directional stability)
Increased rudder fin area
Increased stabilator antitap
3 tones painting inside the cabin
2-components outside painting - white 2 layers
Swiss or German aeronautical windows with green tone
Adjustable seats (length and hight)
4-points safety belts for each seat
2 luggage compartments accessible from outside & inside
Fabric cover for the luggage compartments
Luggage securety hooks in the luggage compartment
2 lockers on the cabin floor
Standard cockpit with three single panels
Handcap on cowling for quick oil and water check
Extra wide cabin doors with gas spring
Double steering, three axes
Prepared for rescue system Nylon Belts
Plexiglass steering cover
Manual stabilizer trim by lever
Electrical flap for -12° to +40° with pre-selection switch
Switch board panel with automatic fuses
Combination key switch
Central fuel valve
2 wing tanks for 65l = 130 l fuel
Steerable spring damped front wheel
Hydraulic disk brakes
Flight Instruments
Speed indicator D 80mm
Single pointer altimeter D 80 mm
Magnetic compass
Slip & bank indicator
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Engine:
Rotax 912 UL2 (80 HP) ready to fly installed
Airbox & Carburator heating
RPM meter
Oil pressure "bar" only
Oil temperature "°C" only
Cylinder head water temperature measurer "°C" only
Huge Batterie
Rotax engine guarantee
Propeller Neuform ground adjustable
Ground adjustable Neuform propeller 2 blades, with Spinner and
Spinner plate, already mounted
Flight and service manual, Engine and Airplane Logbook
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A-10050
Page: 43
Airplane BfU/LTF-UL CTSW ready to fly no rescue
Equipment
Shortwings with downwards orientated winglets (reduces induced
drag and increases directional stability)
3 tones painting inside the cabin
Swiss or German aeronautical windows with green tone
Adjustable seats (length and hight)
4-points safety belts for each seat
2 luggage compartments accessible from outside & inside
Fabric cover for the luggage compartments
Luggage securety hooks in the luggage compartment
2 lockers on the cabin floor
Standard cockpit with three single panels
Handcap on cowling for quick oil and water check
Extra wide cabin doors with gas spring
Double steering, three axes
Prepared for rescue system Nylon Belts
Plexiglass steering cover
Manual stabilizer trim by lever
Electrical flap for -12° to +40° with pre-selection switch
Switch board panel with automatic fuses
Combination key switch
Central fuel valve
2 wing tanks for 65l = 130 l fuel
Steerable spring damped front wheel
Hydraulic disk brakes
Flight Instruments
Speed indicator D 80mm
Single pointer altimeter D 80 mm
Magnetic compass
AU 010 01000
Rev. No.:3
Revision Date:
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Engine:
Rotax 912 UL2 (80 HP) ready to fly installed
Airbox & Carburator heating
RPM meter
Oil pressure
Oil temperature
Cylinder head water temperature measurer
Huge Batterie
Ground adjustable Neuform propeller, with Spinner and Spinner
plate, already mounted
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A-10011
Airplane CTSW 2006 LSA SPORT Version ready to fly no rescue
Equipment difference to CTSW 2006 BFU/LTF-UL
Outer paint and finish improved
Add-on parts reinforced (farings, wheel spads)
More stabile seats
Touch stability improved, by thicker or different layers
A-10060
Airplane CTSW LSA SPORT Version ready to fly no rescue
Equipment difference to CTSW BFU/LTF-UL
Outer paint and finish improved
Re-inforced optional parts (fairings, wheel pants)
More comfortable seats with thicker padding.
Touch stability improved, by thicker or different layers
A-10102
Airplane component CTSW 2006 Section S ready to fly no rescue
Equipment difference to CTSW 2006 BFU/LTF-UL
White door windows 0,5 mm thinner
No Fabric cover for the luggage compartments
No plexiglass steering cover
Not prepared for rescue system
3 Fuses
Weight optimised and selected Parts
Flight Instruments
Bräuniger ALPHAMFD Combi instrument
Magnetic compass
Engine:
Rotax 912 ULS (100 HP) already installed
No Airbox & no carburator heating
Bräuniger ALFAMFD Combi instrument
Small Batterie
Ground adjustable Neuform propeller, with Spinner and Spinner
plate, already mounted
Little comfort package
Heating system with stanless steel muffler
Wheel- and main leg gear fairings
Additional MECAPLEX double fresh air windows in the left door
window
Additional map holders in the cockpit
Two sockets 12V
Door locks
Parking brake
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B-00010X
Addition on price 912 ULS 100HP (n. Sec. S) big starter
Rotax 912 ULS with big Starter instead 912 UL2
B-00012X
Addition on price 912 FR ULS 100PS (n. Sec. S) France
Rotax 912 ULS with big Starter instead 912 UL2, special version
France with blue cylinder heads
B-00011X
Oil- and Waterthermostat (Only 912ULS) with big cooler
Optimizes the Oil- and Watertemperatur
C-00205x
Add-On Neuform 3 Blade Prop. Black & White w- L./E protection
C-00200x
Add-On price Kaspar 3-Blade var.p. prop
In-flight adjustable 3-Blade propeller, mechanical-hydraulic
C-00201x
Add-On price Neuform 3-Blade var.p. prop
In-flight adjustable 3-Blade propeller, mechanical-hydraulic
Z-11020X
Rotax slipper clutch
Protection against shock loading of engine by ground contact of
propeller
D-12100X
Junkers Light Speed Rescue system w. add. Belts
Max. 300 km/h, mounted, belts inside structure
D-12200X
BRS 5 1050 rescue system soft pack w. add. Belts
275 km/h, mounted, belts inside structure
D-12300X
BRS 1350 Rescue system
600 kg - 1350 lbs, mounted, belts inside structure
D-12400X
BRS Kevlar front harness instead of standard harness
Special BRS Kevlar belts instead of standard belts
Z-10100++
Z-10010x
Z-10110x
Z-10120x
Z-10150x
Z-10160x
Z-10170x
Z-10130x
Z-10140x
Z-10180x
Comfort package (not Section S) 2006 w. 3-aches trim system
and new depositions
3-Axes trim system manual
Heating system with stanless steel muffler
Wheel- and landing gear fairings
12 V connector
Additional MECAPLEX double fresh air windows in door windows
Additional map holders in the cockpit, mainframe and doors
Door locks
Parking brake
ACL- & Position lights (green, white, red) LED version
Z-10114++
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Sun Visors left & right
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Z-10111X
Page: 47
Special heating for very low out side temperaturs
Z-10112
Sport seats with adjustable headrest and improved upholstery
Z-10113
Enlarged instrument panels add-on price (not with standard VDO
engine instruments)
Z-10172
Cowling with Quick Fasteners
Z-10161x
Z-10201
Z-10200x
Photowindow Add-On price
instead of ventilation window
Cross country Heavy Duty Landing Gear
Tundra Wheels w. wheel fairings (only together with Z-10201)
Frontwheel 6x4 Mainwheels 6x6
Z-10202X
Stronger tires 6 ply
Z-10210x
Floats prep. (with metal attchm. parts "ORDER MAY 2005"
Stainless steel bolts & nuts, special surface treatment, metal parts for
float attachment
Z-10220x
Z-10230x
3 Wheel Amphibfloats ("1150") " Add-On price instead of trycicle
landing gear
Floats complete mounted
4 Wheel Amphibfloats ("1300") "ORDER from 05/2006" Add-On
price instead of trycicle landing gear
Floats complete mounted
Z-10250
Landing light none certified
Z-10251
Instrument lights
LED lights per instrument
Z-10252
Cabin light & fuel indicator light
LED lights trimable
Z-13050.1++
Black leather seats (add-on-price)
Seats and stick base covered with same leather
Z-13050.2++
Light Brown leather seats (add-on-price)
Seats and stick base covered with same leather
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Z-13060.1++
Z-13060.2++
Z-13060.3++
Z-13060.4++
Z-13061.1++
Z-13061.2++
Z-13061.3++
Z-13061.4++
Z-13062.1++
Z-13062.2++
Z-13062.3++
Z-13062.4++
Three color decals SN 1
Three color decals SW 1
Three color decals UP 1
Z-14000X
Add-On Aero towing equipped
Reinforcement of fuselage & fin, clutch, mirrow, special cooler
Z-14100X
Add-On Reinf. of fusel. for tow.(no fin & clutch)
Z-14200X
Add-On fin for towing (no clutch) only with Z-14100X
Z-13070
Call Signs
Making and mounting of call signs
Confirmity Statement at costs
Export Certificate
ENGINE MANAGEMENT (not with Dynon EFIS/EMS)
Z-15100X
Add-on price Rotax Fly Dat °C & bar
Digital engine information system instead of analog instruments:
black box, 4* EGT, 1*CHT, oil temp., RPM, hours, oil pressure.
Warning when maximum values are exeeded!
Z-15101X
Add-on price Rotax Fly Dat °F & PSI
Digital engine information system instead of analog instruments:
black box, 4* EGT, 1*CHT, oil temp., RPM, hours, oil pressure.
Warning when maximum values are exeeded!
Z-15100.1X
Add-on price for UMA analogue gauges in °C & bar
Z-15101.1X
Add-on price for UMA analogue gauges °F & PSI
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Revision Date:
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AVIONIC & INSTRUMENTS
Z-10800x
DYNON 100 - 120 EFIS & EMS Dual Display (only with Z-10113)
Complete electronic flight and engine management. ASI und Altimeter
as 2 1/4" analog back up.
Z-10350x
King KY 97 A Com & Transponder KT 76 A Mode A/C (*
PM intercom, 2 PTT push bottoms, 2 Antennas, 2 Dave Clark H13.10
S head sets, ready mounted. FTZ & FAA certified.
Transponder incl. antenna and altitude encoder
Z-10500x
Becker AR 4201 COM & Transponder ATC 4401-175
S head sets, ready mounted. FAA & FTZ certified.
Z-10550x
Becker AR 4201 COM & Transponder BXP6401-2-(01) Mode S
S head sets, ready mounted. FAA & FTZ certified.
Z-10900x
GARMIN SL 40 COM & Transponder GTX 327 Mode C
S head sets, ready mounted. FAA certified.
Z-10201X
Z-10650x
NO HEADSETS
Skyforce IIIC enhanced Atlantic Intl (* (only with Com/T package)
Incl. antenna and data cable cockpit mounted and 57 mm
Instruments in the standard panel
Z-10651x
Skyforce IIIC enhanced USA (* (only with Com/T package)
Z-10652x
Skyforce IIIC enhanced Pacific Intl (* (only with Com/T package)
Z-10950x
Garmin GPS 396 American Database (only with Com/T package)
Incl. antenna and data cable cockpit mounted
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Z-10960x
Garmin GPS 296 European Database (only with Com/T package)
Z-10961x
Garmin GPS 296 American Database (only with Com/T package)
Z-10700x
ELT (*
Emergency transmitter (required in Austria), completely mounted FAA certified
Z-10025x
Pictoral Pilot 1-Axes Autopilot not certifed
Aileron & turn & bank indicator
Z-10022x
Altrak Altitude hold (none certified only with Z-10025x)
Stabiliser
Z-10040x
TruTrack DigiFlight IIVS 2-Axes Autopilot not certifed
Aileron & Stabiliser with vertical steering
Z-15451.2X
Z-15452X
Variometer ft/min
Add-on price 3-P Altimeter only for 80 mm panel layout
Z-16000.1X
ASI in km/h
Z-16000.3X
ASI in kts
Z-16100.1X
Altimeter in mbar
Z-16100.2X
Altimeter in hg
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Appendix 2.
Variants of instrument panels for standard instrument board
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Rev. No.:3
Revision Date:
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Rev. No.:3
Revision Date:
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Rev. No.:3
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Rev. No.:3
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Appendix 3.
Variants of instrument panels for “Enlarged instrument panels” (Z-10113)
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Appendix 4.
Instruction for the flap manual operation
1
Для активации ручного режима
платы
управления
закрылками
необходимо:
1) To activate the manual operation of the flap control
printed circuit board ( PCB) , do as follows:
А)
Ручку
управления
закрылками
повернуть
на
180°
относительно
положения 15°, после чего засвечиваются
светодиод VD1 и центральные сегменты
индикатора автоматического режима (при
условии работоспособности процессора).
Это означает включение ручного режима и
отключение автоматического . Система
управления находится в режиме ожидания.
A) Turn the flap control switch by 1800 with reference to
150 position to illiminate the LED display VD 1 and
central segments of the automatic operation indicator
(provided the processor is in proper working condition)
This is to notify that the manual operation is switched on
and
the automatic operation is switched off. The control
system is in the stand-by mode.
VD1
В). При повороте ручки управления на 1800
относительно положения 300 начинается
движение закрылков вверх.
B) When the flap control switch is turned by 1800 with
reference to 300 position, the flaps start to retract( flaps
move up)
VD2
Ограничителем хода закрылков является
концевой выключатель, расположенный на
пластине электро-механизма МТ-10, что
соответствует максимальному отклонению
закрылков вверх. Во время движения
закрылков светится светодиод VD2.
Located on the plate of the electric mechanism MT-10 is
the limit switch which has the function to limit the
movement of flaps. This corresponds to the maximum
up deflection. When the flaps move, the LED display
VD2 illuminates.
C) После остановки движения закрылков
ручку переключателя необходимо вернуть
в нейтральное положение – (пункт 1А)
C) When the movement of flaps has been
accomplished, the control switch should be reset to a
neutral position (see item 1A).
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D) При повороте ручки управления на 1800
относительно положения 00 начинается
движение закрылков вниз. При этом
загорается светодиод VD3. Ограничителем
хода является концевой выключатель на
МТ-10
D) When the flap control switch is turned by 1800 with
reference to 00 position, the flaps start to extend ( flaps
move down).
At this point, the LED display VD3 illuminates. The limit
switch located on the MT-10 has the function to limit the
movement of flaps.
Е) Промежуточные положения закрылков
(например 00,150, 300) выбираются
визуально по положению закрылков
относительно крыла. При необходимости
перевести закрылки в промежуточные
положения, необходимо задать движение
закрылков вверх или вниз до требуемого
положения, после чего остановить ход
закрылков переводом ручки управления в
нейтральное положение (пункт 1А)
2) Для перехода в автоматический режим
переместить ручку в одно из положений (12°, 0°, 15°, 30°, 40°) при этом появится
индикация на дисплее, соответствующая
выбранному
положению.
Остановка
движения закрылков в этих положениях
происходит
автоматически.
При
необходимости
перепрограммировать
установленные
положения
автоматического режима действовать по
инструкции
«Установки
положений
закрылков».
E) Intermidiate flap position ( for instance, 00,150,300)
are to be selected by sight according to the position of
flaps with respect to the wing.
To set the flaps in intermediate positions, if
necessary,encure that flaps move up or down as far as
the required position.After that,stop the movement of
flaps by setting the flap control switch in a neutral
position (item 1A).
VD3
AU 010 01000
2) To activate the automatic operation,set the switch in
one of the designated positions (-12°,0°, 15°, 30°, 40°),
accompanied by an indication at the display
corresponding to the selected position.The movement of
flaps in these positions is to be stoped automatically.
To change the settings of the automatic operation,if
necessary,comply with the instructions «Setting-up of
flap positions».
Rev. No.:3
Revision Date:
05.04.2006

Flight Design CTSW LSA Aircraft Operating

Transcription

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