Aerospool WT9 Dynamic LSA Club LT airplane Flight manual

FLIGHT MANUAL
WT9 Dynamic LSA
Type: WT9 Dynamic LSA
Model: Club LT
Airplane Serial Number: DY-448/2012 LSA
Airplane Registration Number: OH-DLI
Publication Number: 0
Date of Issue: 16.07.2012
Signature:
Authority:
Stamp:
Original date of approval:
This airplane has to be operated in compliance with information and limitations contained herein.
Aerospool spol. s r. o., Letisková 10, 971 03 Prievidza Tel: +421 46 51 83 200, Fax: +421 46 51 83 250
Web: www.aerospool.sk
e-mail: [email protected]
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 0, Page 1
0.1 RECORD OF MANUAL REVISION
Any revision of the present manual, except actual weight data, must be recorded
in the following table and in case of approved sections endorsed by the responsible airworthiness
authority.
The new or amended text in the revised pages will be indicated by a black vertical line
in the right hand margin, and the Revision No. and the date will be shown on the bottom left side
of the page.
Rev.
No.
Affected
Section
Affected
Pages
Date of
issue
0
ALL
ALL
16.07.2012
Date of revision: 16.07.2012
Approval
Revision: 0
Date
Date
inserted
Signature
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 0, Page 2
0.2 LIST OF EFFECTIVE PAGES
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WT9 Dynamic LSA Club LT
Section
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FLIGHT MANUAL
Date
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Page
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 0, Page 4
0.3 TABLE OF CONTENTS
Section
Section title
1. .......................... ........................................................................................ GENERAL INFORMATION
2. .......................... ............................................................................................................. LIMITATIONS
3. .......................... .................................................................................... EMERGENCY PROCEDURES
4. .......................... ........................................................................................... NORMAL PROCEDURES
5. .......................... .........................................................................................................PERFORMANCE
6. .......................... .................................................. WEIGHT AND BALANCE AND EQUIPMENT LIST
7. .......................... ................................................................. AIRPLANE AND SYSTEM DESCRIPTION
8. .......................... ................................... AIRPLANE HANDLING, SERVICING AND MAINTENANCE
9. .......................... .......................................................................................................... SUPPLEMENTS
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 1, Page 1
1. GENERAL INFORMATION
Section
Page
1.1. ....................... INTRODUCTION .......................................................................................2
1.2. ....................... CERTIFICATION BASIS ..............................................................................2
1.3. ....................... WARNINGS, CAUTIONS AND NOTES .........................................................2
1.4. ....................... DESCRIPTIVE DATA ..................................................................................3
1.4.1. .................... AIRPLANE DESCRIPTION...........................................................................3
1.4.2. .................... TECHNICAL DATA .....................................................................................3
1.5. ....................... AIRPLANE VIEWS .....................................................................................4
1.5.1. .................... THREE VIEW DRAWING ............................................................................5
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
1.1.
FLIGHT MANUAL
Section 1, Page 2
Introduction
The airplane Flight Manual has been prepared to provide pilots and instructors
with information for the safe and efficient operation of this airplane. This manual contains
supplementary data supplied by the airplane manufacturer.
1.2.
Certification basis
CS-LSA
Certification Specification for Light Sport Aeroplanes.
1.3.
Warnings, cautions and notes
The following definitions apply to warnings, cautions and notes used in the flight manual.
WARNING
Means that the non-observation of the corresponding
procedure leads to an immediate or important degradation
of the flight safety!
CAUTION
Means that the non-observation of the corresponding
procedure leads to a minor or to a more or less long term
degradation of the flight safety!
NOTE
Draws the attention to any special item, not directly related
to safety but which is important or unusual!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
1.4.
Descriptive data
1.4.1.
Airplane description
FLIGHT MANUAL
Section 1, Page 3
WT9 Dynamic LSA Club LT is low-wing monoplane with fixed undercarriage. The airframe
consists of a sandwich shells from advanced composite material. There are two places in the cockpit,
side by side type. Airplane is equipped with towing hook. This aircraft is intended for sporting,
recreation, glider towing and tourist flying in accordance with VFR day.
Powerplant of the aircraft is the 4 cylinder, 4-stroke engine ROTAX 912 ULS
with a maximum takeoff RPM limitation 5800 min-1.
This plane is fitted with a 3 bladed in flight electrically adjustable propeller
and the following type and model is approved: WOODCOMP SR2000D with diameter 1700 mm.
1.4.2.
Technical data
Airplane
10,30 m2
9,00 m
6,40 m
2,00 m
7,82
1,185 m
Wing area
Wing span
Length
Height
Wing aspect ratio
Aerodynamic mean chord (MAC)
Control surfaces
0,273 m2
1,25 m
0,75 m2
2,28 m
1,68 m2
2,40 m
1,02 m2
1,022 m
Aileron area
Aileron span
Flap area
Flap span
Horizontal tail area
Horizontal tail span
Vertical tail area
Vertical tail span
Landing gear
Wheel spacing
Wheel base
Nose wheel diameter
Main wheel diameter
1,49 m
2,27 m
0,32 m
0,35 m
Weights
Empty weight
Maximum takeoff weight
Useful load
Fuel tank capacity
Date of revision: 16.07.2012
316,0 kg
600 kg
284,0 kg
126 l
Revision: 0
WT9 Dynamic LSA Club LT
1.5.
FLIGHT MANUAL
Airplane views
Date of revision: 16.07.2012
Revision: 0
Section 1, Page 4
WT9 Dynamic LSA Club LT
1.5.1.
FLIGHT MANUAL
Three view drawing
Fig. 1 Three view drawing
Date of revision: 16.07.2012
Revision: 0
Section 1, Page 5
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 2, Page 1
2. LIMITATIONS
Section
Page
2.1. ....................... INTRODUCTION .......................................................................................2
2.2. ....................... AIRSPEEDS...............................................................................................2
2.3. ....................... AIRSPEED INDICATOR MARKINGS ............................................................3
2.4. ....................... POWERPLANT..........................................................................................3
2.5. ....................... POWERPLANT INSTRUMENT MARKINGS ..................................................5
2.6. ....................... MISCELLANEOUS INSTRUMENT MARKINGS ..............................................5
2.7. ....................... WEIGHT ...................................................................................................6
2.8. ....................... CENTRE OF GRAVITY ................................................................................6
2.9. ....................... APPROVED MANOEUVRES .......................................................................6
2.10. ..................... MANOEUVRING LOAD FACTORS ..............................................................7
2.11. ..................... FLIGHT CREW...........................................................................................7
2.12. ..................... KIND OF OPERATION ...............................................................................7
2.13. ..................... FUEL ........................................................................................................7
2.14. ..................... MAXIMUM PASSENGER SEATING .............................................................7
2.15. ..................... OTHER LIMITATIONS................................................................................8
2.16. ..................... LIMITATIONS PLACARDS ..........................................................................8
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
2.1.
FLIGHT MANUAL
Section 2, Page 2
Introduction
Section 2 includes operating limitations, instrument markings, and basic placards necessary
for safe operation of the airplane, its engine, standard systems and standard equipment.
2.2.
Airspeeds
Airspeed limitations and their operational significance are shown below:
IAS
Speed
Remarks
km/h
mph
knots
VNE
Never Exceed speed
280
174
151
VNO
Normal Operating Limit
speed
250
155
135
VRA
Rough Air speed
225
140
121
VA
Manoeuvring speed
180
112
97
VFE
Maximum Flap Extended
speed
140
87
76
Date of revision: 16.07.2012
Revision: 0
Do not exceed this speed in any
operation.
Do not exceed this speed except in
smooth air, and then only with caution.
Do not exceed this speed except in
smooth air. Air movements in lee-wave
rotors,
thunderclouds,
visible
whirlwind, or over mountain crests are
to be understood as rough air.
Do not make full or abrupt control
movement above this speed, because
under certain conditions the aircraft
may be overstressed by full control
movement.
Do not exceed these speeds
with the given flap setting.
WT9 Dynamic LSA Club LT
2.3.
FLIGHT MANUAL
Section 2, Page 3
Airspeed indicator markings
Airspeed indicator markings and their colour code significance are shown below:
Speed or speed range (IAS)
Colour code
significance
Significance
km/h
mph
knots
White arc
76 - 140
47 - 87
41 - 76
Green arc
89 - 225
55 - 140
48 - 121
Yellow arc
225 - 280
140 - 174
121 - 151
Yellow triangle
112
70
60
Minimum approach speed.
Yellow line
180
112
97
Manoeuvring speed .
Red line
280
174
151
Never exceeded speed .
2.4.
Operating range with extended flaps.
(Lower limit is . Upper limit is .)
Normal operating range.
(Lower limit is . Upper limit is .)
Manoeuvres must be conducted with caution.
(Lower limit is . Upper limit is .)
Powerplant
Engine
Engine manufacturer
-
ROTAX Bombardier, Gunskirchen, Austria
Engine model
-
ROTAX 912 ULS
Takeoff (max. 5 min.)
73,5 kW / 100 hp
Continuous
69,0 kW / 94 hp
Takeoff (max. 5 min.)
5800 min-1
Continuous
5500 min-1
Maximum
135 °C
Maximum
130 °C
Minimum
50 °C
Maximum
7 bar / 102 psi
Minimum
0,8 bar / 12 psi
Maximum
0,06 l/h
Maximum
Airbox pressure + 0,40 bar / 5,80 psi
Normal
Airbox pressure + 0,25 bar / 3,63 psi
Minimum
Airbox pressure + 0,15 bar / 2,18 psi
Maximum power
Maximum RPM
Cylinder head
temperature
Oil temperature
Oil pressure
Oil consumption
Fuel pressure
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 2, Page 4
Oil grade:
Motorcycle oil of a registered brand with gear additives. Use only oil with API classification
„SG“ or higher! If using aircraft engine oil, then only blended one. Due to the high stresses
in the reduction gears, oils with gear additives such as high performance engine cycle oils are
required. Heavy duty 4-stroke engine cycle oils meet all the requirements. These oils are normally
not mineral oils but semi or fully synthetic oils.
WARNING
Never use AVGAS, LB 95 with fully synthetic engine oils!
Fuel grade:
Following types of fuels can be used:
• Min. RON 95 EN 228 Super
(Unleaded Automotive Gasoline RON 95)
• EN 228 Super Plus
(Unleaded Automotive Gasoline RON 98)
• AVGAS 100 LL
(Due to higher lead content in AVGAS, the wear
of the valve seats, depositing in combustion chamber
and lead sediments in the lubrication system will
increase. Therefore use AVGAS only if you encounter
problems with vapour lock or if the other fuel types
are not available.)
• Fuel E10
(Unleaded gasoline blended with 10% ethanol)
Propeller
Propeller manufacturer
Propeller model
Propeller diameter
WOODCOMP spol. s r. o., Odolená Voda, Czech
republic
SR2000D, 3-bladed in flight electrically
adjustable
1700 mm
Additional data can be found in Section 7.9, or in the Operator’s Manual for engine
and in the User’s Guide for propeller.
WARNING
Never run the engine without propeller! This inevitably
causes engine damage and is an explosion hazard!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
2.5.
FLIGHT MANUAL
Section 2, Page 5
Powerplant instrument markings
According to customer requirement round one–purpose needle instruments
can be mounted. Powerplant analogue instrument markings and their colour code significance
are shown in table below:
Analogue powerplant instruments are not installed.
2.6.
Miscellaneous instrument markings
According to option of the customer miscellaneous instrument can be mounted.
Powerplant digital instrument markings and their colour code significance are shown table below:
Unit
Red Line
Minimum
Limit
Green Arc
Normal
Operating
Yellow Arc
Caution
Range
Red Line
Maximum
Limit
Tachometer
RPM
1400
1400 - 5500
5500 - 5800
5800
Manifold pressure
inHg
-
0,0 - 28,0
28,0 - 29,5
29,5
o
50
90 – 110
135
o
C
50
90 - 110
bar
0,8
2,0 - 5,0
C
250
300-800
Fuel pressure
bar
0,15
0,20 - 0,35
50 – 90
110 – 135
50 - 90
110 - 130
0,8 - 2,0
5,0 - 7,0
250-300
800-880
0,15 - 0,20
0,35 - 0,40
Fuel flow meter
l/h
-
0,0 - 25,0
Digital instrument
(Dynon SV-D1000)
Cylinder head
temperature
Oil temperature
Oil pressure
Exhaust gas
temperature
Fuel level
Date of revision: 16.07.2012
C
o
l
-
130
7,0
880
0,40
over 25,0
Red light annunciator will be illuminated with the remaining
7 litres of fuel in the fuel tank.
Revision: 0
WT9 Dynamic LSA Club LT
2.7.
FLIGHT MANUAL
Section 2, Page 6
Weight
Weights
Empty weight
316,0 kg
Maximum takeoff weight
600 kg
Maximum landing weight
600 kg
Useful load
284,0 kg
Maximum fuel weight
90,7 kg
Maximum occupant weight per seat
120,0 kg
Minimum weight solo pilot (with 40 kg of baggage)
54,0 kg
Minimum weight solo pilot (without baggage)
72,2 kg
Maximum weight in baggage compartment
40 kg
WARNING
Maximum takeoff weight is 600 kg!
2.8.
Centre of gravity
CG positions
Empty airplane CG position
12 ± 2% MAC
Position of CG in flight
20 ÷ 30% MAC
Rear centre of gravity limit is valid for en-route weight at maximum crew weight
and minimum fuel amount. Forward centre of gravity limit is valid for minimum pilot weight
and maximum capacity of the fuel tanks. Example to check the centre of gravity position is in Sect. 6.
WARNING
A flight shall not be commenced until the pilot-in-command
is satisfied that the mass of the airplane and centre
of gravity location are such that the flight can be conducted
safely!
2.9.
Approved manoeuvres
Appropriate entry speed (IAS)
Manoeuvre
km/h
mph
knots
Steep turns with the angle of bank up to 60°
145
90
78
Lazy eights
145
90
78
WARNING
Aerobatic manoeuvres and intentional spins are prohibited!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
2.10.
FLIGHT MANUAL
Section 2, Page 7
Manoeuvring load factors
IAS
Speed
Load factor
km/h
mph
knots
VA
Manoeuvring speed
180
112
97
+4
VNE
Never exceed speed
280
174
151
+4
VA
Manoeuvring speed
180
112
97
-2
VNE
Never exceed speed
Maximum Flap Extended
speed
280
174
151
-2
140
87
76
+2
VFE
2.11.
Flight crew
The minimum flight crew with which the airplane is allowed to fly is one pilot sitting
in the left pilot seat. The passenger or another pilot may occupy the right seat in the cockpit.
2.12.
Kind of operation
The aircraft WT9 Dynamic LSA Club LT is approved to perform flights in accordance
with VFR day only. Aerobatic manoeuvres and intentional spins are prohibited!
WARNING
IFR flights and flights in icing conditions are prohibited!
For flight operations the following minimum equipment must be installed:
• Magnetic compass
• Sensitive barometric altimeter
• Airspeed indicator
• Pilot’s safety belts
2.13.
Fuel
The fuels that can be used for the aircraft WT9 Dynamic LSA Club LT operation are listed
in Section 2.4 Powerplant and in the Operator’s Manual for engine ROTAX 912 ULS. Fuel tank's
capacities are in table below:
Left tank (l)
Right tank (l)
Total quantity of fuel in the tank
63,0
63,0
Unusable fuel quantity in the tank
2,9
2,9
Total usable quantity of fuel in the tank
60,1
60,1
2.14.
Maximum passenger seating
The maximum number of passenger aboard is one passenger sitting in the right seat
in the cockpit.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
2.15.
FLIGHT MANUAL
Section 2, Page 8
Other limitations
(a) Wind speed
The maximum demonstrated crosswind velocity for takeoff and landing is 12,4 m/s
(24 knots).
(b) Smoking
No smoking on board the aircraft.
(c) Glider towing
Maximum towing cable load is 3000 N. If the strength of tow cable is more than 3000 N
a weak link must be used. Maximum weight of glider to be towed is 750 kg. Maximum crew of towing
airplane is only a pilot.
2.16.
Limitations placards
Airspeed IAS
Never Exceed speed
VNE
151 knots
Normal Operating Limit speed
VNO
135 knots
Rough Air speed
VRA
121 knots
Manoeuvring speed
VA
97 knots
Maximum Flap Extended speed
VFE
76 knots
Maximum Landing Gear Operating speed
VLO
76 knots
Aerobatic manoeuvres and intentional spins are
prohibited!
IFR flights and flights in icing conditions are prohibited!
Maximum allowed filling of the fuel tanks in litres
Baggage
weight
(kg)
100
110
120
130
140
150
160
170
180
190
200
210
0
Full
Full
Full
Full
Full
Full
Full
Full
Full
Full
116
102
20
Full
Full
Full
Full
Full
Full
Full
Full
116
102
88
75
40
Full
Full
Full
Full
Full
Full
116
102
88
75
61
47
Crew weight (kg)
Maximum baggage
weight 40 kg!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 3, Page 1
3. EMERGENCY PROCEDURES
Section
Page
3.1. ....................... INTRODUCTION .......................................................................................2
3.2. ....................... ENGINE FAILURE ......................................................................................2
3.3. ....................... AIR START ...............................................................................................3
3.4. ....................... SMOKE AND FIRE .....................................................................................3
3.5. ....................... GLIDE ......................................................................................................4
3.6. ....................... LANDING EMERGENCY .............................................................................4
3.7. ....................... RECOVERY FROM UNINTENTIONAL SPIN ..................................................5
3.8. ....................... OTHER EMERGENCIES ..............................................................................6
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
3.1.
FLIGHT MANUAL
Section 3, Page 2
Introduction
Section 3 provides checklist and amplified procedures for coping with emergencies that
may occur. Emergencies caused by airplane or engine malfunction are extremely rare if proper
pre-flight inspections and maintenance are practised.
However, should an emergency arise, the basic guidelines described in this section should
be considered and applied as necessary to correct the problem.
3.2.
Engine failure
3.2.1.
Engine failure at takeoff roll
1. Throttle lever:
2. Ignition:
3. Brakes:
3.2.2.
Engine failure at takeoff up to height 164 ft
1. Sufficient runway:
2. Insufficient runway:
3.2.3.
Set to idle position.
Both circuits switched OFF.
Apply until stop.
Complete a normal landing without engine
power.
Perform emergency landing according
to procedure 3.6.1.
Engine failure at takeoff above height 164 ft
A. Sufficient altitude
1. Air start:
2. Unsuccessful start:
Start the engine according to procedure 3.3.
Perform emergency landing according
to procedure 3.6.1.
B. Insufficient altitude
1. Insufficient altitude:
3.2.4.
landing
according
Engine failure in flight
1. Air start:
2. Unsuccessful start:
3.2.5.
Perform emergency
to procedure 3.6.1.
Start the engine according to procedure 3.3.
Perform emergency landing according
to procedure 3.6.1.
Performance loss due to irregular running of the engine during flight
This situation may occur with carburettor icing: Apply carburettor pre-heating as required
to restore normal power, smooth running.
Or it can happen due to emptying of fuel tank (indication is loss of fuel pressure):
Select the non empty fuel tank.
If everything fails: perform an emergency landing according to procedure 3.6.1.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
3.3.
1.
2.
3.
4.
5.
6.
7.
8.
9.
FLIGHT MANUAL
Section 3, Page 3
Air start
Airspeed:
Altitude flight:
Field selection:
Fuel selector:
Choke:
Throttle lever:
Ignition:
Starter key:
Successful start:
Modify to 65 knots.
Check.
Select according to height available.
Open (non empty fuel tank selected).
Without choke.
Slightly move forward.
Both circuits switched ON.
Start the engine.
Adjust throttle to achieve smooth running
at 2500 RPM for approximately half
a minute before reaching required power.
Perform emergency landing according
to procedure 3.6.1.
10.Unsuccessful start:
WARNING
The rate of descent approximately 492 ft/min causes
measurable loss of altitude during the air start. If the air
start is unsuccessful up to height 492 ft above ground level,
perform the emergency landing according
to procedure 3.6.1!
3.4.
Smoke and fire
3.4.1.
Engine fire on the ground
1. Fuel selector:
2. Throttle lever:
3. Ignition:
Close.
Set full throttle.
Both circuits switched OFF
the fuel has been consumed.
Leave the cockpit immediately.
With best available means.
4. Crew:
5. Extinguish fire:
3.4.2.
after
Engine fire in flight
1. Fuel selector:
2. Throttle lever:
3. Ignition:
Close.
Set full throttle.
Both circuits switched OFF after
the fuel has been consumed.
Try to extinguish the fire with side slip.
Perform emergency landing in accordance
with procedure 3.6.1.
4. Extinguish fire:
5. Emergency landing:
CAUTION
After the fire has been extinguished, do not start engine
again!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
3.4.3.
1.
2.
3.
4.
FLIGHT MANUAL
Fire in cockpit
Fire source:
Ignition:
Master switch:
Crew:
Locate.
Both circuits switched OFF.
Set OFF.
On the ground: Leave the cockpit.
During flight: Perform an emergency
landing in accordance with procedure 3.6.1.
Try to extinguish with best available means.
5. Try to extinguish
3.5.
Section 3, Page 4
Glide
Glide path will determine the field selection for emergency landing. The optimum gliding
performance is with retracted wing flaps and with stopped propeller.
In case of engine failure it is necessary to maintain the following optimum speeds
for given configuration.
Glide
km/h
mph
knots
130
81
70
Optimum descent airspeed (IAS)
Maximum gliding range
10
Rate of descent
3,0 m/s (590 ft/min.)
3.6.
Landing emergency
3.6.1.
Emergency landing
1. Airspeed:
2. Field selection:
3.
4.
5.
6.
Modify to 65 knots.
Select in the direction of the free area
without obstacles, if possible against
the wind.
Extend as required.
Close.
Both circuits switched OFF.
Set OFF.
Flaps:
Fuel selector:
Ignition:
Master switch:
CAUTION
The loss of height for 360° turn is approximately
492 ft!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
3.6.2.
FLIGHT MANUAL
Section 3, Page 5
Precautionary landing
In the event of the airplane failure, disorientation, shortage of fuel, dangerous
deterioration of the meteorological conditions (visibility, thunderstorm) and approaching sunset,
a precautionary landing should be conducted.
1. Select a suitable landing field, if possible against the wind.
2. Fly over selected field with wing flaps 15° and 65 knots airspeed at a height 164 ft AGL,
check properly the preferred area for landing to inspect the terrain properties
(obstructions, surface conditions).
3. Make landing circuit at a height 492 ft AGL or at a safe altitude as allowed by cloud base
with flaps 15° and 65 knots airspeed. Extend “down wind” position and make approach
with sufficient power.
4. Don’t lose sight on the selected field in the case of low visibility.
5. Landing approach with flaps for landing and sufficient power.
6. Arrange approach so that the desired touchdown spot will be immediately
after passing the edge of the selected landing field. In the case of object collision,
perform obstacle avoidance manoeuvre to the side.
7. After touchdown apply heavy breaking till stopped.
8. When the airplane comes to a stop, shut down the engine, master switch off, close
the main fuel selector, secure the airplane and seek assistance.
3.6.3.
Landing with a flat tyre
1. Landing approach:
With wing flaps 35° and airspeed
61 knots.
With the bank angle on the inflated tyre
at minimum touchdown speed.
Maintain ground roll direction.
2. Touchdown:
3. Direction after landing:
3.7.
Recovery from unintentional spin
For recovery from an unintentional spin the following procedure should be used:
1. Throttle lever:
Set to idle position.
2. Control stick:
Set neutral position, without deflection
of the ailerons.
3. Rudder control:
Apply full rudder opposite to the direction
of rotation.
4. Control stick:
Move forward of neutral in a brisk motion
until rotation stops.
5. Rudder control:
Immediately as rotation stops, neutralize
rudder position.
6. Control stick:
Make a smooth recovery from the resulting
dive.
WARNING
Intentional spins are prohibited!
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
3.8.
Other emergencies
3.8.1.
Control failures
FLIGHT MANUAL
Section 3, Page 6
Aileron control fault:
The airplane is possible to control laterally by the secondary effect of the rudder. Start
and termination of the yawing up to bank angle 15° is possible using the rudder only.
Rudder control fault: The yawing and the termination are conducted with help
of the lateral control of the ailerons.
3.8.2.
Vibrations
The powerplant can be the source of the vibrations.
1. Reduce engine speed to minimize the vibrations.
2. Proceed to the nearest airport for landing or select a suitable precautionary landing
field in accordance with procedure 3.6.2.
3.8.3.
Rescue system
Not installed.
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
3.8.4.
FLIGHT MANUAL
Section 3, Page 7
Unsecured cockpit canopy
If the „Before takeoff“ checklist is performed insufficiently (Section 4.5.5., point 13. Canopy
of cockpit), there is a danger of partial cockpit canopy latching and insufficient locking. The canopy is
equipped with a lock on the upper rear section of the frame and it is secured by the lock lever shot
backwards. The lock pin is projected as latch with compression spring. The gap approx. 8-12 mm will
be rise between fuselage and cockpit canopy, which is constant during straight line flight without
side-slipping due to the air flow and the function of the gas struts. Partial cockpit canopy latching
and non locking will stack up by the noise increase due to the agitated air through the gap between
fuselage and cockpit canopy. Partial cockpit canopy latching is possible to close safely during straight
line flight without side-slipping by the following way according to appropriate stage of flight.
3.8.4.1. During takeoff roll
1. Abort the takeoff, if the cockpit canopy unlatching, unlocking is detected during takeoff
roll.
2. Latch and lock the cockpit canopy by normal procedure after stopping. (The cockpit
canopy handle pull down and check the cockpit canopy latching and locking by canopy
frame and the red ring position) (see Section 7.8).
3.8.4.2. After unstuck or during climbing
1. Safely terminate takeoff.
2. Climb to safety altitude.
3. Fly straight line flight without side-slipping and carry out procedure 3.8.5.3 During level
flight.
3.8.4.3. During level flight
1.
2.
3.
4.
5.
6.
7.
Open the left ventilation sliding window on cockpit canopy.
Reduce speed to 65 knots.
Hold control stick by one hand.
The cockpit canopy handle pull down for cockpit canopy latching and locking.
Check the cockpit canopy latching and locking by canopy frame and red ring position.
Close the left ventilation sliding window on cockpit canopy.
Adjust flight airspeed to cruising speed.
WARNING
During side-slipping flights (incorrect turn – slipping turn,
skidding turn, and side slipping for landing) with partial
cockpit canopy latching or non locking due to asymmetrical
flow over fuselage by the air flow, the cockpit canopy will
be carved through the gap and subsequently will be full
open by help of the gas struts. The cockpit canopy will
become the braking shield, what will cause abnormal
airplane descent due to increased total drag!
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 4, Page 1
4. NORMAL PROCEDURES
Section
Page
4.1. ....................... INTRODUCTION .......................................................................................2
4.2. ....................... RIGGING AND DERIGGING .......................................................................2
4.3. ....................... DAILY INSPECTION ...................................................................................5
4.4. ....................... PRE-FLIGHT INSPECTION ..........................................................................5
4.5. ....................... NORMAL PROCEDURES AND CHECK LIST ..................................................8
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WT9 Dynamic LSA Club LT
4.1.
FLIGHT MANUAL
Section 4, Page 2
Introduction
Section 4 provides checklist and amplified procedures for the conduct of normal operation.
Normal procedures associated with optional systems can be found in Section 9.
4.2.
Rigging and derigging
4.2.1.
Rigging of the wings
The airplane has possibility of the wings disassembling for transportation purposes
or to save space in the hangar. There is a description for the rigging procedure of the right wing.
The procedure for the left wing is analogous. Thoroughly clean and lubricate all the wing fittings
and pins before each assembling.
1. Fit the spar end of the wing into the spar end (fork) of the wing central section
and push the wing along its longitudinal axis so that a connection slot between
the wing central section and the wing root is approx. 100 mm. Connect the hoses
from the Pitot probe (only right wing), prepare and adjust the wing fuel tank hoses
and connect the wiring for fuel tank conductive connection (if the wing is equipped
with fuel tanks) and position lights (Fig. 2).
2. Fully push the wing into the wing central panel and slide the wing tank fuel hoses
on their sockets together with theirs clamps. Carefully insert the wing flap lever
on the wing flap hinge. Take care of the hoses from the Pitot probe (only right wing)
and for fuel hoses (if the wing is equipped with fuel tanks) which must not be twisted!
3. Insert wing's pins to connect wing spar with the wing central section. The outer wing
pin is inserted through the access hole on the lower wing surface. The inner wing pin is
inserted from the cockpit interior (slightly lift and lower the wing tip to ease the pin's
insertion).
4. Insert rear spar into the fitting of the central section's rear spar. Secure all 6 pins
with safety pins (Fig. 3a and Fig. 3b).
5. Connect the wing flap lever with the wing flap hinge. Connect the flap control rod
to the wing flap lever using the wing flap rod pin. During this procedure the flap control
lever in the cockpit shall be set to the rearmost position and the wing flap
shall be deflected to maximum down position (Fig. 4).
6. Connect the aileron control rod 2 with the aileron control rod 1 and secure
the nut (Fig. 3a) with the safety pin. Tight the fuel hose clamps (if the wing is equipped
with fuel tanks).
7. Stick the adhesive tape on the gap between wing and wing centre section.
8. Repeat the procedure with the second wing. After checking the security of the all
connection. The connection slot between wing and the wing centre section should be
sealed with sticky tape.
WARNING
After rigging of the wings check for correct operation and
security of the aileron control pins and the flap control pins
as well as the connection of the hoses from the Pitot probe
and fuel hoses!
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 4, Page 3
Fig. 2 Insertion of the wing spar into the wing centre section, position of the wing pins (1, 2 and 3)
and the support points (A, B and C)
Aileron
control rod 2
Outer main
wing pin
Aileron
control rod 1
Attachment bolt
of aileron control rod
Safety pin
Fig. 3a Outer main wing pin and aileron's connection
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Inner main
wing pin
Section 4, Page 4
Auxiliary
wing pin
Safety pin
Safety pin
Fig. 3b Inner main and auxiliary wing pin
Wing flap hinge
Wing flap lever
Wing flap
Flap control rod
Flap rod pin
Safety pin
Fig. 4 Wing flap control connection
4.2.2.
Derigging of the wings
1. Drain central section fuel tanks and wing tanks (if the wing is equipped with fuel tanks).
2. Remove the adhesive tape covering the gap between wing and the wing centre section.
3. Disconnect aileron control rod 2 from the aileron control rod 1 (Fig. 3a). Release
the fuel hoses clamp (if the wing is equipped with fuel tanks).
4. Disconnect the flap control rod from wing flap lever. Disconnect the wing flap lever
from the wing flap hinge (Fig. 4).
5. Pull out all wing's pins (connecting the wing's main and auxiliary spar with the wing
central section) (Fig. 3a and Fig. 3b).
6. Pull out the wing along its longitudinal axis so that there is an approx. 100 mm distance
between the wing central section and the wing root (Fig. 2). Disconnect the hoses
from the Pitot probe (only right wing), the wing fuel tank hoses and wiring for fuel tank
conductive connection (if the wing is equipped with fuel tanks) and position lights.
7. Carefully pull the wing away from the wing centre section and put on soft mats.
8. Repeat above process also for second wing.
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WT9 Dynamic LSA Club LT
4.3.
FLIGHT MANUAL
Section 4, Page 5
Daily inspection
The daily inspection must be performed every day before flight of the airplane.
The scope of this inspection is to check the following:
1. Airplane log-book and airworthiness certificate.
2. Airplane technical log-book.
3. Cockpit.
4. Landing gear.
5. All control surfaces for full and free movement.
6. All surfaces of the airplane for cracks, nicks or any visible damage.
7. Powerplant and propeller.
8. Service fluids.
WARNING
If any problems are found they must be corrected before
flying!
4.4.
Pre-flight inspection
It is most important to perform a pre-flight inspection carefully to prevent possible trouble.
The pre-flight inspection is essential for flight safety. Pre-flight inspection proceeding is on Fig. 5.
CAUTION
Special attention must be devoted to the parts, which are
affected by high vibrations and high temperatures!
Fig. 5 Pre-flight inspection proceeding
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 4, Page 6
A. Cockpit:
Flight controls:
Master switch:
Ignition switch:
Loose items:
Check instruments:
Cockpit canopy glass:
Safety harness:
Rescue system actuator:
Fuel:
Check for freedom of movement.
Switched OFF.
Both circuits switched OFF.
Secure or remove.
Set “0” (zero).
Clean, check cockpit canopy lock.
Inspect.
Remove secure lock (if installed).
Check fuel quantity, check fuel selector.
B. Wing:
Surface:
Connection:
Fuel tank caps:
Pitot probe:
Leading edges:
Ailerons:
Flaps:
State of wing surface.
Wing pins fully inserted and secured.
State of fuel tank caps.
Pitot probe cover removed, check opening
for blockage.
Without damage, clean.
Check for freedom of movement
and security.
Without play, check hinges for security.
C. Fuselage:
Surface:
Static pressure receivers:
Antennas:
Cockpit wing walks:
Without damage.
Check opening for blockage.
Fixed, without damage.
Without damage.
D. Tail units:
Surface:
Control surfaces:
Tail skid:
Without damage.
Check for freedom of movement, without
excess play.
Check for secure attachment.
E. Landing gear:
Main wheel tyres:
Brakes:
Legs:
Nose wheel leg:
Date of revision: 16.07.2012
State, inflation (250 kPa).
Visually check condition of pads, brake
system for leaks.
State without damage, attachment.
Nose wheel tyre state, inflation (200 kPa)
attachment, suspension check, wheel free
of rotation.
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 4, Page 7
F. Powerplant
Propeller:
Attachment, leading edge blade state,
check for nicks and security, check spinner
for cracks and attachment.
Engine:
Check for any operating fluids leaks.
State of the engine cowlings.
State of the exhaust system attachment.
Check coolant level and oil level.
Engine attachment in rubber silentblocks.
Carburettors attachment.
State of hoses holders.
Condition and integrity of wires, plugs
Fuel filters.
Turn the propeller by hand several times
for odd noises or excessive resistance
and normal compression.
WARNING
Before cranking the propeller switch off both ignition
circuits. The propeller must be caught at the blade surface
every time. Do not catch at the edge!
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WT9 Dynamic LSA Club LT
4.5.
FLIGHT MANUAL
Section 4, Page 8
Normal procedures and check list
The standard cockpit control arrangement is shown in Fig. 6 and the actual instrument
panel is shown in Fig. 7 (see Section 7.4).
20
20
19
19
18
13
15
14
16
17
12
9
10
11
8
7
6
4
9
7
5
3
3
2
2
1
Fig. 6. The standard cockpit controls (see also Section 7.4)
1. Headset socket/jack
2. Seat and safety belt
3. Pocket
4. Brake lever
5. Wing flap lever
6. Trim lever
7. Control stick
8. Fuel selector
9. Rudder pedals
10. Throttle lever
Date of revision: 16.07.2012
11. Choke
12. Ignition, starter key, master switch
13. Instrument panel
14. Flight instruments
15. GPS, radio, transponder
16. Tachometer
17. Powerplant instruments
18. Magnetic compass
19. Ventilation flow baffle
20. Ventilation sliding window
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WT9 Dynamic LSA Club LT
4.5.1.
Section 4, Page 9
Before starting engine
1.
2.
3.
4.
Ignition:
Rudder pedals:
Control stick:
Throttle lever:
5.
6.
7.
8.
9.
10.
11.
Elevator trim control:
Fuel quantity:
Instruments:
Radio:
Seat and safety harness:
Brake:
Propeller pitch range:
12. Canopy of cockpit:
4.5.2.
FLIGHT MANUAL
Both circuits switched OFF.
Freedom of movement.
Freedom of movement.
Freedom of movement, set to idle
position.
Set to neutral position.
Check.
Setting and check-up of the value.
Function check.
Adjust and lock.
Function check.
Only electrically adjustable propellers:
Check the min. and max. propeller blade's
pitch.
Latched and locked.
Engine starting
Cold engine:
1. Brakes:
2. Fuel selector:
3. Choke:
4. Throttle lever:
5. Master switch:
6. Starter key:
7. Fuel pump:
8. Ignition:
9. Starter key:
10. As soon as engine runs:
11. Choke:
12. Warming up:
Date of revision: 16.07.2012
Set on parking position.
Left tank.
Activate.
Set to idle position.
Switch ON.
Switch to 1st position.
Switch ON and establish the fuel pressure
and then switch OFF.
Both circuits switch ON.
Actuate. Activate starter for max. 10 sec
only
without
interruption
followed
by a cooling period.
Adjust throttle lever to achieve smooth
running at approximately 2500 RPM, check
if oil pressure has risen within 10 sec
to 2 bar and monitor oil pressure.
De-activate.
Start warming up procedure according
to procedure 4.5.3.
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 4, Page 10
Warm engine (if the engine is already at operating temperature):
1. Brakes:
Set on parking position.
2. Fuel selector:
Left tank.
3. Throttle lever:
Set to idle position.
4. Master switch:
Switch ON.
5. Starter key:
Switch to 1st position.
6. Ignition:
Both circuits switch ON.
7. Starter key:
Actuate. Activate starter for max. 10 sec
only
without
interruption
followed
by a cooling period.
8. As soon as engine runs:
Adjust throttle lever to achieve smooth
running at approximately 2500 RPM, check
if oil pressure has risen within 10 sec
to 2 bar and monitor oil pressure.
4.5.3.
Engine warming up
In accordance with the Operator’s Manual for ROTAX 912 ULS start the warming up period
at 2000 RPM for approx. 2 minutes, continue at 2500 RPM, duration depending on ambient
temperature, until oil temperature reaches 50 °C. Check temperatures and pressures.
Engine ground test:
1. Ignition check:
2. Throttle response:
3. Minimum speed:
4. Idle speed:
5. Propeller pitch range:
4.5.4.
Check the two ignition circuits at 4000 RPM.
Speed drop with only one ignition circuit
must not exceed 300 RPM. Max. difference
115 RPM of speed by use of either circuit
A or B.
Short full throttle ground test, speed must
not exceed 5800 RPM.
Minimum speed on the ground at full
throttle must be 5500 ±200 RPM depending
on ambient temperature and pressure.
Check the idle speed 1600 ±100 RPM.
Only hydraulic adjustable propellers:
Set up engine speed at 4000 RPM, set up
min. pitch and then max. pitch. Between
these ends positions of propeller pitch
should be observed significant engine speed
variation and
acoustic
manifestation
generated by propeller.
Taxiing
Using of the throttle control (movement forward or backward) adjust power during taxiing.
Taxiing of the aeroplane is controlled by the rudder pedals which are connected to the nose wheel
steering. The wheel brakes are actuated by sliding the brake lever rearwards in the centre console.
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
4.5.5.
1.
2.
3.
4.
5.
6.
7.
8.
9. Seat and safety harness:
10. Canopy of cockpit:
1.
2.
3.
4.
5.
Freedom of movement.
Freedom of movement.
Set neutral position.
Set takeoff position.
Left tank.
Check for correct readings.
Check altimeter setting.
Set minimum fine angle (takeoff position)
(only when equipped with pitch adjustable
propeller).
Adjust and lock.
Latched and locked.
Normal takeoff
Fuel pump:
Throttle lever:
Control stick:
Direction on the ground:
Unstick:
6. Accelerating:
7. Fuel pump:
8. Throttle lever:
9. Flaps retracting:
4.5.7.
Section 4, Page 11
Before takeoff
Rudder pedals:
Control stick:
Elevator trim control:
Wing flaps:
Fuel selector:
Powerplant instrument:
Flight instrument:
Propeller:
4.5.6.
FLIGHT MANUAL
Switch ON.
Full throttle.
Set into neutral position.
Control by rudder pedals.
At speed at 49 – 51 knots (according
to takeoff weight).
Accelerate to speed 65 – 70 knots
(after unstuck).
Should be switched OFF after takeoff
in safety altitude.
Adjust throttle lever to max. continues
power (5500 RPM).
At height 164 ft AGL retract the wing flaps.
Climbing
Normal climb is conducted at climb speeds 70-76 knots in accordance with the takeoff
weight of the airplane. Monitor cylinder head temperature and oil pressure during climb. Oil
temperature limits must not be exceeded. In case of high readings, increase airspeed and reduce
engine power setting.
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
4.5.8.
FLIGHT MANUAL
Section 4, Page 12
Cruise
The range of cruising speeds is from 76 to 135 knots in accordance with the engine speed
setting from 4000 to 5500 RPM. The economy airspeed for best fuel economy is 97 knots,
the optimum operation is between 97 - 121 knots. In case of turbulence reduce the cruising speed
below 121 knots. Under certain conditions the airplane may be overstressed. The airplane is able
to be trimmed through the range of the cruising speeds.
Due to economy reasons is recommended to maintain the following data:
Engine ROTAX 912 ULS
Engine power setting
Engine Speed
(RPM)
Performance
(kW)
Torque
(Nm)
Manifold pressure
(inHg)
Takeoff power
5 800
73,5
121,0
27,5
Continuous power
5 500
69,0
119,8
27,0
75 %
5 000
51,0
97,4
26,0
65 %
4 800
44,6
88,7
26,0
55 %
4 300
38,0
84,3
24,0
4.5.9.
Approach
Approach is conducted at airspeeds 65 - 70 knots with the throttle lever set to idle position.
For increasing the rate of descent it is recommended setting of wing flaps to landing position
(35° flaps deflection) and proceeding at airspeed 65 knots. In this configuration the gliding
range is 1:8.
Side slipping is conducted with airspeed 70 knots, and bank angle 30° with help of full
rudder deflection. The side slip direction is controlled by the bank.
4.5.10. Landing
Check fuel before approach for landing. Landing approach is conducted at small glide slope
angle due to long distance of the float before aeroplane's touchdown.
1. Propeller:
Set minimum angle (only when equipped
with pitch adjustable propeller).
2. Fuel selector:
Left tank.
3. Fuel pump:
Switch ON.
4. Approach:
Conduct at speed 65-70 knots according
to the weight.
5. Wing flaps:
As required extend the flaps down at speed
below 76 knots.
6. Elevator trim:
Adjust as required.
7. Levelling:
Begin approx. 10 - 6,5 ft above ground.
8. Touchdown:
Touchdown should be made with power-off
and on the main wheels first. The nose
wheel should be lowered smoothly
to the runway as speed is diminished.
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
9. Control during landing:
10. Braking:
FLIGHT MANUAL
Section 4, Page 13
Control the aeroplane with help
of the rudder pedals.
Apply braking as required. The main wheel
brakes are actuated via the handle
on the top of central tunnel between
the pilot seats.
4.5.11. Balked landing
1. Throttle lever:
2. Airspeed:
3. Flaps:
4. Elevator trim:
Smoothly adjust the throttle lever to full
open (a thrust yawing moment is
manifested in case of the steep setting
of the throttle lever).
Modify to 65 knots.
Retract the wing flaps if safe.
Adjust as required and proceed in climbing.
4.5.12. After landing
1.
2.
3.
4.
5.
Engine RPM:
Wing flaps:
Elevator trim:
Fuel pump:
Taxiing:
Adjust throttle for taxiing.
Retract the wing flaps.
Set to most rear position of neutral.
Switch OFF.
To the parking position.
4.5.13. Securing aeroplane
1.
2.
3.
Brakes:
Throttle lever:
Propeller:
4.
Instruments:
5.
Ignition:
6.
7.
8.
9.
Master switch:
Fuel selector:
Rescue system:
Cockpit leaving:
Date of revision: 16.07.2012
Set to “park” position.
Set to idle.
Set minimum pitch (takeoff position) (only
when equipped with pitch adjustable
propeller).
Switch OFF all electronic instruments
(avionics).
Switch OFF the first circuit and after 2-3 s
switch OFF the second circuit.
Switch OFF.
Close.
Lock the actuator (if installed).
After cockpit leaving the canopy should be
covered with the cloth dust-cover, to avoid
the effects of the sun.
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 4, Page 14
4.5.14. Takeoff and landing within crosswind
Operation in direct crosswinds of 12,4 m/s (24 knots) has been demonstrated.
Takeoffs under strong crosswind conditions normally are performed with the minimum flap
setting (position 0 or 1) necessary for the field length, to minimize the drift angle immediately after
takeoff. With the ailerons partially deflected into the wind, the airplane is accelerated to a speed
slightly higher than normal, then the elevator control is used to quickly, but carefully; lift the airplane
off the ground and to prevent possible settling back to the runway while drifting.
When clear of the ground, make a coordinated turn into the wind to correct for drift
and continue in takeoff.
When landing in a strong crosswind, use the minimum flap setting (position 1 or 2
maximum, never position 3) required for the field length. Although the crab or combination method
of drift correction may be used, the wing low method gives the best control.
After touchdown, hold a straight course with the steerable nose wheel, with aileron
deflection as applicable and occasional braking if necessary.
4.5.15. Aero towing
See 2.15 "Other limitations" for aero towing.
Takeoff and climbing with towed glider up to MTOW 410 kg do with flaps
in position 15°. At safe height (minimum 164 ft) retract the wing flap.
Takeoff and climbing with towed glider with water ballast or from MTOW 410 kg
up to MTOW 750 kg do with flaps in position 0°.
WARNING
Take care for maximum towing speed of towed glider!
CAUTION
After release of the glider the maximum speed for retracting
rope is 86 knots (when retracting mechanism is installed)!
WARNING
When appropriate and necessary, use guillotine lever of tow
rope (when retracting mechanism is installed)!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 5, Page 1
5. PERFORMANCE
Section
Page
5.1. ....................... INTRODUCTION .......................................................................................2
5.2. ....................... APPROVED DATA .....................................................................................2
5.2.1. .................... AIRSPEED INDICATOR SYSTEM CALIBRATION ...........................................2
5.2.2. .................... STALL SPEED ............................................................................................2
5.2.3. .................... TAKEOFF PERFORMANCE .........................................................................2
5.2.4. .................... LANDING DISTANCE .................................................................................3
5.2.5. .................... CLIMB PERFORMANCE .............................................................................3
5.3. ....................... ADDITIONAL INFORMATION ....................................................................3
5.3.1. .................... BALKED LANDING CLIMB .........................................................................3
5.3.2. .................... EFFECT ON FLIGHT PERFORMANCE AND CHARACTERISTICS ......................3
5.3.3. .................... DEMONSTRATED CROSSWIND PERFORMANCE ........................................3
5.3.4. .................... NOISE DATA ............................................................................................4
5.3.5. .................... AERO TOWING PERFORMANCE ................................................................4
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
5.1.
FLIGHT MANUAL
Section 5, Page 2
Introduction
Section 5 provides approved data for airspeed calibration, stall speed and takeoff
performance and non-approved additional information. The data in the charts has been computed
for condition of the standard atmosphere from actual flight tests with the airplane at maximum
takeoff weight and engine in good condition and using average piloting techniques.
5.2.
Approved data
5.2.1.
Airspeed indicator system calibration
IAS (knots)
27
30
32
36
42
48
54
60
67
74
CAS (knots)
30
32
35
38
43
49
54
59
65
70
IAS (knots)
79
84
89
95
99
110
121
132
144
154
CAS (knots)
76
81
86
92
97
108
119
130
140
151
IAS
CAS
- Indicated airspeed
- Calibrated airspeed
5.2.2.
Stall speed
The data is valid for following conditions: MTOW 600 kg, CG is 30% MAC, engine at idle:
Position wing flaps
0°°
15°°
35°°
Stall speed IAS in knots
48
45
41
Stall speed CAS in knots
49
46
43
5.2.3.
Takeoff performance
The data is valid for following conditions: H = 0 ft MSL, Temperature t = 15 °C, wing flaps
position 15°, MTOW 600 kg:
Takeoff run distance
(ft)
Takeoff distance
up to 50 ft
(ft)
Paved runway
482
1027
Non paved – grass
568
1142
Surface of the runway
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
5.2.4.
FLIGHT MANUAL
Section 5, Page 3
Landing distance
The data is valid for following conditions: H = 0 ft MSL, Temperature t = 15 °C, wing flaps
position 35°, landing speed 1,3 VS0, MTOW 600 kg, braking during roll:
Landing distance from
50 ft height
(ft)
Landing run distance
(ft)
Paved runway
863
246
Non paved - grass
892
276
Surface of the runway
5.2.5.
Climb performance
The data is valid for wing flaps retracted, MTOW 600 kg:
Attitude
(ft)
Speed IAS
(knots)
Rate of climb
(ft/min)
0
70
896
3281
70
622
6562
70
500
The service ceiling is 18 000 ft at the max. continuous power.
5.3.
Additional information
5.3.1.
Balked landing climb
The data is valid for following conditions: MTOW 600 kg, wing flaps position 35° (retracted
during balked landing):
Speed IAS at full throttle
application
Rate of climb after 5 s from
full throttle application
(ft/min)
0
65
830
3281
65
561
6562
65
433
Attitude
(ft)
5.3.2.
Effect on flight performance and characteristics
No disturbing effects on flight performance and characteristic of the aeroplane
WT9 Dynamic LSA Club LT were recorded during the flight tests.
5.3.3.
Demonstrated crosswind performance
The maximum demonstrated crosswind speed for takeoff and landing is 12,4 m/s
(24 knots).
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
5.3.4.
FLIGHT MANUAL
Section 5, Page 4
Noise data
The maximum noise data 58,7 dB (A) was measured during the flight tests according
to the German noise requirement LS – UL 96.
5.3.5.
Aero towing performance
The following table shows the takeoff and climbing performance:
Glider type
Duo Discus
MTOW
(kg)
750
Date of revision: 16.07.2012
Distance
(ft)
Takeoff
Takeoff up
roll
to 50 ft
1047
2356
Time of climb up to
(min:sec)
1312 ft
1968 ft
4:33
6:06
Revision: 0
Airspeed
(knots IAS)
Rate of
climb
(ft/min)
75
354
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 6, Page 1
6. WEIGHT AND BALANCE AND EQUIPMENT LIST
Section
Page
6.1. ....................... INTRODUCTION .......................................................................................2
6.2. ....................... WEIGHTING PROCEDURE .........................................................................2
6.3. ....................... WEIGHT AND BALANCE RECORD AND PERMITTED PAYLOAD RANGE ........3
6.4. ....................... MASTER MINIMUM EQUIPMENT LIST ......................................................5
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WT9 Dynamic LSA Club LT
6.1.
FLIGHT MANUAL
Section 6, Page 2
Introduction
This section contains the payload range with which the aircraft may be safely operated.
CG position is very important parameter which affects the safety of flight.
6.2.
Weighting procedure
To define the airplane CG it is necessary to weigh the empty airplane with standard
and optional equipment, with operating fluids of the engine but without the fuel in the fuel tanks
(for empty weight and empty moment see Weight and balance record).
The airplane is weighted with the help of three weighting-machines located under the left
and right main wheels and under the nose wheel.
The airplane position for weighting has to be adjusted to be levelled the side edge
of the cockpit. The reference point (RP) is leading edge of wing root section where wing-fuselage
radius starts. Measure the distance from datum point to centre of main landing wheel axle and nose
wheel axle.
The leading edge of Mean Aerodynamic Chord (MAC) is located in distance 77 mm
rearward from RP. CG position is expressed as a distance from MAC leading edge (
(mm))
and as a MAC ratio (
(% MAC)).
CG position after loading of airplane (crew, fuel and baggage or additional equipment)
can be calculated as follows (see CALCULATION OF FLIGHT CG POSITION in Section 6.3):
1. Determine the partial weights of crew , fuel *, baggage and add them
to empty weight to get total weight .
2. Calculate the partial moments of crew , fuel *, baggage and add them
to empty moment to get total moment .
3. Calculate the position of CG on MAC (in mm). Calculate the position of CG on MAC
(in %MAC)
4. Check if the flight CG is inside of allowed range (For safety flight it must be considered
that the fuel is consumed during flight what results in moving of CG forward!).
* Be careful to use fuel weight (in kg) not fuel volume (in litres)!
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WT9 Dynamic LSA Club LT
6.3.
FLIGHT MANUAL
Section 6, Page 3
Weight and balance record and permitted payload range
Permitted crew + passenger weight with
Date
Empty
weight
(kg)
Empty
moment
(kg.mm)
CG
Position
(%)
16.07.12
316,0
76628,0
13,97 %
Max. baggage 40 kg
Max.
Min.
(kg)
(kg)
119,4
54,0
Half baggage 20 kg
Max.
Min.
(kg)
(kg)
No baggage
Max.
Min.
(kg)
(kg)
165,8
212,3
54,0
Approved
Date
72,2
Condition: Aircraft in the range from maximum possible fuel amount of 126,0 litres to minimum fuel of 7 litres.
Date of revision: 16.07.2012
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Signed
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 6, Page 4
CALCULATION OF FLIGHT CG POSITION
Empty airplane ( )*
kg
Empty moment ( )*
(See Weight and balance record)
kg.mm
Weight ( )
Distance from RP ( )
Moment ( = . )
(kg)
(mm)
(kg.mm)
(See Weight and balance record)
Crew ( )
kg
720 mm
kg.mm
Fuel** ( )
kg
240 mm
kg.mm
Baggage ( )
kg
1100 mm
kg.mm
Total weight ( )
kg
Total moment ( )
kg.mm
= + + + = + + + Calculation of CG position on MAC (in mm):
= − 77 =
− 77 = Calculation of CG position on MAC (in %MAC), (MAC = 1185 mm):
%!" = · 100 =
· 100 = %!"
!"
1185
Permitted flight CG position is in range 20,00-30,00 %MAC!
Calculated flight CG position is whitin permitted range:
YES
NO
Date, place
*
**
Signature
Empty weight includes operating fluids of engine and standard equipment.
Attention, make sure that weight of fuel (in kg) was used in calculation!
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WT9 Dynamic LSA Club LT
6.4.
FLIGHT MANUAL
Section 6, Page 5
Master minimum equipment list
The following minimum instrument equipment is requested:
Flight and navigation instruments:
1. Airspeed indicator.
2. Sensitive barometric altimeter.
3. Magnetic compass.
Powerplant instruments:
1. Fuel indicator.
2. Tachometer.
3. Oil temperature indicator
4. Oil pressure indicator.
5. Cylinder head temperature indicator.
Additional equipment:
1. Master switch of the electrical system with circuit breakers.
2. Battery – located in front of the firewall.
3. Safety harness – 4 point static harness restrain system is attached to the fuselage
structure.
4. Limitation placards - in accordance with Section 2.16.
CAUTION
If additional equipment is mounted within the magnetic field
of the compass, it may affect the readings of the compass!
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 7, Page 1
7. AIRPLANE AND SYSTEM DESCRIPTION
Section
Page
7.1. ....................... INTRODUCTION .......................................................................................2
7.2. ....................... AIRFRAME ...............................................................................................2
7.3. ....................... FLIGHT CONTROLS ...................................................................................2
7.4. ....................... INSTRUMENT PANEL................................................................................4
7.5. ....................... LANDING GEAR SYSTEM...........................................................................6
7.6. ....................... SEATS AND SAFETY HARNESS ...................................................................7
7.7. ....................... BAGGAGE COMPARTMENT ......................................................................7
7.8. ....................... DOORS, WINDOWS AND EXITS.................................................................7
7.9. ....................... POWERPLANT..........................................................................................8
7.10. ..................... FUEL SYSTEM ......................................................................................... 12
7.11. ..................... ELECTRICAL SYSTEM .............................................................................. 13
7.12. ..................... PITOT AND STATIC PRESSURE SYSTEM ................................................... 13
7.13. ..................... AVIONICS .............................................................................................. 13
7.14. ..................... MISCELLANEOUS EQUIPMENT ............................................................... 13
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WT9 Dynamic LSA Club LT
7.1.
FLIGHT MANUAL
Section 7, Page 2
Introduction
This section provides a description of the operation of the airplane and its systems. Refer
to Section 9, Supplements, for details of optional systems and equipment.
7.2.
Airframe
WT9 Dynamic LSA Club LT is a single engine aircraft, controlled aerodynamically, made
of advanced composite material, low-wing monoplane with two side-by side seats. The airplane is
equipped with a fixed tricycle undercarriage.
Fuselage:
The fuselage sandwich shell is divided in the symmetry plane. The shell is of three layer
construction. The external and internal shell layers are made of glass and carbon fibre fabrics, which
are saturated with a resin. Between them there is a filling of hard foam panels. The fin is made
together with the fuselage. The wing central panel is fixed at the fuselage.
There are two places in the cockpit, side by side type. The interior width is 1,15 m. A lifting
cockpit canopy hinges forward. The canopy opening system is assisted by a gas strut. The wing
central panel with span 2,45 m is fixed at the fuselage. There is an integral tank in the forward box
of the wing central panel.
Wing:
The tapered wing is a monospar construction with a rear auxiliary spar for the aileron
and flap attachments. The main spar caps are made from carbon rovings. The slotted flaps are
rectangular sandwich construction. The flap is attached to the wing with four hinges. The aileron is
attached to the upper surface of the wing with three hinges. The spars of right and left wings are
joined to the wing central panel spar with the help of two pins. The third connecting point is the pin
in the rear auxiliary spar. An aileron control system consists of duraluminium rods. The control
handle of flaps is attached to the top of central tunnel in the cockpit. The movement by help
of the rods and the bellcranks is transmitted to the flap's torsion tube in the wing,
next the movement from the flap's torsion tube is transmitted to the flaps. Optional wing fuel tanks
are integral part of wing structure. They are connected with central section tanks with simple hose
connection and tightened with clamps.
Horizontal tail unit:
The horizontal tail unit consists of a stabilizer and elevator. The stabilizer consists
of sandwich shells from advanced composite material. The stabilizer is fixed at the fin. The width
of the horizontal tail unit is 2,4 m, (similar width as the wing central panel) and allows
the transport of the fuselage with regular truck.
The elevator consists of two parts, which are joined together by help of the elevator
control.
Vertical tail unit:
The vertical tail unit consists of the fin and rudder and has trapezoidal shape. The rudder
consists of a sandwich shell from advanced composite material. The rudder is attached by three
hinges at the fin.
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
7.3.
FLIGHT MANUAL
Section 7, Page 3
Flight controls
The aircraft has dual controls with two control sticks. The ailerons are controlled by control
sticks, connecting rods and arms. The elevator is controlled by control sticks, connecting rods.
The rudder is controlled by steel cables attached at the rudder pedals and guided alongside
the fuselage sides to the rudder. The rudder pedals position is adjustable (see Maintenance Manual,
Directional control system, page 1-22).
The wing flaps are controlled by a flap lever located on the top of central tunnel manually.
The slotted link allows four positions of the flaps: retracted, takeoff (flaps deflection 15°), landing
position (flap deflection 24°) and landing position (flap deflection 35°). Movement with help of rods
and bellcranks is transmitted onto the flap's torsion tube and from the flap's torsion tube
is transmitted onto the flaps with help of the rod.
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WT9 Dynamic LSA Club LT
7.4.
FLIGHT MANUAL
Section 7, Page 4
Instrument panel
The Instrument panel arrangement is shown in the following figure (Fig. 7).
32
31
30
28
25
21
29
26 27
23
22
15
14
24
17 18 19
16
13
20
14
12
11
13
7 8 9 10
5
6
4
3
2
1
Fig. 7 Instrument panel
1. Brake lever
12. Flap control unit
23. Radio
2. Throttle lever resistance setting 13. PTT button and trim control
24. Dynon SkyView SV-D1000 (2)
3. Throttle lever
14. Pedals adjustment handle
25. Airspeed indicator
4. Trim control select switch
15. 12V Socket
26. Intercom
5. Fuel selector
16. Switches*
27. Trim indicator
6. Choke
17. Ignition
28. USB connector (1)
7. Oil flap control
18. Starter key
29. USB connector (2)
8. Carburettor pre-heating
19. Master switch
30. Propeller governor
9. Cabin ventilation
20. Circuit breakers**
31. Check lights (CL) and
Buttons (B)***
10. Cabin heating
21. Altimeter
11. TOW mechanism handle
22. Dynon SkyView SV-D1000 (1)
32. Magnetic compass
*
AVIONICS, ACL, LAND, FUEL PUMP
**
Circuit breakers are listed on the next page
***
OVER SPEED WARNING (CL), FUEL PUMP (CL), FUEL RES. LEFT (CL), FUEL RES. RIGHT (CL), D-1000 (CL),
CHARGE (CL), TEST (B)
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 7, Page 5
Circuit breakers installed at instrument panel
1.
Auto Pilot
Circuit breaker value
(A)
3
2.
ACL / NAV
5
3.
Landing Lights
10
4.
Fuel Pump
2
5.
D-1000
8
6.
D-1000
8
7.
Radio
5
8.
Transponder
3
9.
Propeller
10
10.
Trim Control
2
11.
Flaps Control
8
12.
Socket 12V
10
13.
Avionic (behind panel)
1
No.
Protected instrument
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
7.5.
FLIGHT MANUAL
Section 7, Page 6
Landing gear system
The main wheels of the model Club LT are mounted on spring legs, which are attached
to the left and to the right outside of the wing central panel. The nose wheel leg is attached
at the fire wall (Fig. 8). The nose wheel is sprung by help of rubber components and is controlled
with the rudder pedals.
The main wheels on both legs are equipped with hydraulic disc brakes. The main wheels
are braked by brake system unit, which is located under the pilot seats. The main wheel brakes
are actuated via the brake lever handle placed on the top of central tunnel between the pilot seats.
This handle actuates the parking brake too.
The tyres of the main landing gear have dimensions 15x6,00-6, the tyre of the nose wheel
has dimensions 13x5,00-6. Wheels are equipped with wheel fairings.
Fig. 8 Fixed undercarriage
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
7.6.
FLIGHT MANUAL
Section 7, Page 7
Seats and safety harness
The plane has two side-by-side seats which are fixed, un-adjustable. The back support
of the seats is glued into the fuselage construction as the frame. The safety belts – 4 point static
harness restraint system is attached to the left and right seat side panel and to the strut behind
the back support of the seats.
7.7.
Baggage compartment
The baggage compartment is situated behind the seats. Maximum baggage weight is stated
on a placard near the compartment. Hard objects may not be carried in the baggage compartment
without a suitably designed lashing or anchorage.
7.8.
Doors, windows and exits
The cockpit canopy consists of one part. The Plexiglas is glued on the composite frame.
The canopy is attached to the front section of the fuselage by pins which make it possible
for the canopy to be tilted forward. For easier manipulation, the weight of the canopy
is counterbalanced by two gas struts which allow it to open effortlessly. On the lower frame there
are handles outside the canopy. The canopy is equipped with a lock on the upper rear section
of the frame (see Fig. 9) and the red ring on lock pin as the correct cockpit canopy locking indicator.
CORRECT latching and locking
Latched (2) but unlocked (1)
WRONG!
Date of revision: 16.07.2012
CORRECT latching and locking
Latched (2) but partially locked (1) Clearly locked (1) but unlatched (2)
WRONG!
WRONG!
Fig. 9 Cockpit canopy latching and locking
Revision: 0
WT9 Dynamic LSA Club LT
7.9.
FLIGHT MANUAL
Section 7, Page 8
Powerplant
Powerplant consists of 4 cylinder horizontally opposed 4-stroke engine ROTAX 912 ULS
and a 3-bladed in flight electrically adjustable propeller WOODCOMP SR2000D.
These engines are suitable for aircraft, but they must never fly at locations, airspeeds,
altitudes, or in any other circumstances from which a successful no-power landing cannot be made,
after sudden engine stoppage.
Engine:
ROTAX 912 ULS is 4-stroke, 4 cylinders horizontally opposed, spark ignition engine, one
central camshaft-push-rods-OHV. Combined liquid cooled cylinder heads and ram air cooled
cylinders. Dry sump forced lubrication. The engine is fitted with an electric starter, AC generator,
mechanical fuel pump and the reduction gear with integrated shock absorber (Fig. 10).
For more information regarding ROTAX 912 ULS see the Operator’s Manual for engine
ROTAX 912 ULS.
WARNING
Due to carburettors, flying in icing conditions is prohibited!
The periodic inspections must be performed according to the maintenance schedule
(see the Maintenance Manual for ROTAX 912 ULS).
There are two laminated cowlings (upper and lower) which cover the engine compartment.
The disassembly and assembly of the upper cowling is easy – just release the quick-closing locks.
The upper cowling is usually removed during engine pre-flight inspection to check the engine
compartment, operating fluids quantity (oil, coolant) and to check engine installation.
After removing the upper cowling of the engine, check the following:
1. Oil quantity check: Remove the cover of the oil tank. The oil level in the oil tank should
be between two marks (max./min.) on the dip-stick, but must never fall below the min.
mark.
2. Coolant quantity check: Remove the cover of the expansion tank. The coolant level
in the overflow bottle should be between min. and max. mark.
The lower cowling is removed after unscrewing of attachment screws connecting
the cooler to the cowling face side, and then unscrew the attachment screws connecting
the cowling to the firewall border.
Date of revision: 16.07.2012
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WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 7, Page 9
10
8
7
9
4
5
6
4
3
2
1
Fig. 10 Powerplant ROTAX 912 ULS
1. Cabin venting and engine intake
6. Expansion tank
2. Cooling air distributor to cylinders
7. Oil tank
3. Oil cooler
8. Coolant overflow bottle
4. Carburettor
9. Airbox
5. Ignition
10. Regulator
Propeller:
SR2000D is 3-bladed in flight electrically adjustable aircraft propeller with diameter
1700 mm of mixed structure. The propeller is controlled with electronic constant speed instrument
which is shown below (Fig. 11). For operation instruction see Operation manual delivered
by producer of equipment.
Fig. 11 Electronic constant speed instrument
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FLIGHT MANUAL
Intentionally left blank
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Section 7, Page 10
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Intentionally left blank
Date of revision: 16.07.2012
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Section 7, Page 11
WT9 Dynamic LSA Club LT
7.10.
FLIGHT MANUAL
Section 7, Page 12
Fuel system
The integral fuel tanks are located in the forward box of the wing central panel
and in wing's leading edge. The fuel system scheme is shown at figure below (Fig. 12).
The fuel is fed to engine driven fuel pump through the fuel selector located inside
the cockpit below the instrument panel from the left or right fuel tank (in dependence on position
of fuel selector). Fuel line between left fuel tank and fuel selector is equipped with an electric fuel
pump. Engine driven fuel pump supplies the fuel into the carburettors through the fuel flow meter.
Unconsumed fuel flows back through the return piping into the left fuel tank. In the fuel system
is installed also fuel pressure sensor.
Fuel tank vent pipe is outgoing from the upper part of each fuel tank, proceeds along
the rescue system board, inside of central tunnel and discharge through the lower surface of fuselage
in front of main beam.
Fuel quantity indicators indicate the amount of fuel in left and right fuel tank. Red light
annunciators will be illuminated when 7 litres of fuel remain in corresponding fuel tank.
Fig. 12 The fuel system diagram
CAUTION
Electric fuel pump running when the left fuel tank is not
selected can cause its damage!
NOTE
The tanks in wings are connected with the fuselage tanks
with a hose. The hose diameter is not enough to fill
the fuselage tank from wing tank when refuelling. Please
wait when the fuel from the wing tank comes into
the fuselage tank, and then fill up till the wing tanks are full!
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 7, Page 13
The left tank must be used for all takeoffs and landings. When you are flying with full tanks,
use the left tank for 30 – 40 minutes before changing to the right tank. This makes space in the left
tank for the return of unconsumed fuel without venting it overboard.
Monitor the fuel quantity when you are doing long flights or flights with low fuel quantity.
To maximize range/endurance when the red annunciator lights flash (7 litters of fuel in each fuel
tank), the following procedure is recommended:
1. Select the right tank and use this tank until all the fuel is consumed.
2. Change back to the left tank where more than 7 litres of fuel due to fuel return is.
(7 litres of fuel allows approximately 20 minutes of flying depending on power settings).
3. Continue flying and landing procedure with the electric fuel pump on as written
in this manual.
NOTE
When the fuel tank annunciator starts to flash there is about
7 litres of fuel in the fuel tank what allows approximately
20 minutes of flying depending on power settings!
7.11.
Electrical system
There are electrical system diagrams in the Maintenance Manual for the airplane
WT9 Dynamic LSA Club LT. The wiring system depends on instrumentation and other electric
equipment of an individual airplane according to a customer’s desire. The dual engine ignition
is a separate part of the electric system. Each of two ignition circuits has its own break switch.
The detailed description of the ignition and the AC generator is listed at the Operator’s Manual
for ROTAX 912 ULS engine.
7.12.
Pitot and static pressure system
The Pitot probe for the airspeed indicator is located bellow the right wing. Pressure
distribution to individual instruments in the cockpit is done through flexible plastic hoses. The static
pressure receivers are located on the both sides of the fuselage behind the cockpit. Keep the system
clear to assure its right function.
7.13.
Avionics
The following avionics are mounted in the airplane: radio and intercom. This equipment
must be connected with the headphones and with the antenna. The airplane might be equipped
with other instruments such as GPS, transponder, board computer. These flight and navigation
instruments are mounted as an option of the customer (see Section 9). For right operation
of the instruments and for more details see the corresponding manuals supplied with installed
instruments.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
7.14.
FLIGHT MANUAL
Miscellaneous equipment
Rescue system Magnum 601 S-LSA:
Not installed.
Date of revision: 16.07.2012
Revision: 0
Section 7, Page 14
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 8, Page 1
8. AIRPLANE HANDLING, SERVICING AND MAINTENANCE
Section
Page
8.1. ....................... INTRODUCTION .......................................................................................2
8.2. ....................... AIRPLANE INSPECTION PERIODS ..............................................................2
8.3. ....................... AIRPLANE ALTERATIONS OR REPAIRS .......................................................5
8.4. ....................... GROUND HANDLING / ROAD TRANSPORT ................................................5
8.5. ....................... CLEANING AND CARE ...............................................................................5
8.6. ....................... WINTER OPERATION................................................................................6
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WT9 Dynamic LSA Club LT
8.1.
FLIGHT MANUAL
Section 8, Page 2
Introduction
This section contains factory recommended procedures for proper ground handling
and servicing of the airplane. It also identifies certain inspection and maintenance requirements
which must be followed if the airplane is to retain that new-plane performance and dependability.
It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic
and flying conditions encountered.
The airframe surfaces should be protected with light plastic foil or cloth cover against dust.
All engine intakes, vents, the fuel vents and pitot static system should be covered before long term
airplane parking or storing, due to contamination by foreign objects (insects, birds).
The external surfaces of the airplane should be washed with a sufficient quantity
of the water and an adequate quantity of detergent. Do not apply petrol or chemical solvents
for cleaning the external surfaces of the airplane.
It is advisable to park the airplane inside a hangar or eventually inside other weather-proof
space with stable temperature, good ventilation, low humidity and dust-free environment.
The parking place should be protected against possible damage caused by sun radiation, humidity
and wind. Sunbeams reflected through the canopy can magnify and may cause spot heating, which
can create damage to the cockpit area and the upholstery.
8.2.
Airplane inspection periods
8.2.1.
Powerplant
The engine periodic inspections and maintenance are conducted
to the procedures contained in the Maintenance Manual for ROTAX 912 ULS.
Daily inspection:
Check after 25 hr. of operation:
Check after 50 hr. of operation:
100 hr. check:
TBO (Time Between Overhaul):
according
Is carried out in accordance with the instructions
for execution of the pre-flight inspection, which
are contained in Section 4, item 4.4.
Must be carried out according to the Maintenance
Manual for ROTAX 912 ULS Series.
Must be carried out according to the Maintenance
Manual for ROTAX 912 ULS Series.
Must be performed according to the Maintenance
Manual for ROTAX 912 ULS Series every 100 hr.
of operation or 1 year, whichever comes first.
The renewal of the spark plugs, the fuel filter
and the coolant are carried out after 200 hr.
of operation.
2000 hr. or 15 years, whichever comes first.
Oil change
It must be performed according to the Maintenance Manual for ROTAX 912 ULS Series.
There is an oil drain screw at the bottom of the oil tank. There is an oil filter at the left side beside
the propeller gearbox. At every oil change, replace the oil filter and open the old one with special
tool, to ensure the engine is not producing chips. Remove filter insert, cut top and bottom cover off,
unroll and check it for metal chips, foreign matter, contamination and abrasion. This check is
important as it allows conclusions regarding the condition of the engine and gives information about
a possible cause of any failure.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
8.2.2.
FLIGHT MANUAL
Section 8, Page 3
Propeller
The propeller in operation does not require any special maintenance. In case
of propeller contamination wash its surface with a piece of cloth dipped in warm water with addition
of the usual detergent. The operator is allowed carry out repairs to common little nicks
on the leading edges, up to a maximum size of 4 mm. This repair can be done by using epoxy resin
with filler. The damaged place is to be degreased and fill with resin. After hardening the resin
the repaired area is to be sanded and protected with enamel or varnish of the epoxy or polyurethane
type. Replace the parts supplied by producer and remove the cone from the propeller. Any other
dismantling is forbidden. The repair of large damage must be carried out by the manufacturer
or by an authorised service centre. Operator’s Manual for propeller WOODCOMP SR2000D includes
additional information about maintenance.
TBO (Time Between Overhaul):
8.2.3.
1500 hours.
Airframe
Daily inspection:
Is carried out in accordance with the instructions
for the execution of the pre-flight inspection, which
are contained in Section 4.4.
Check after 25 hr. of operation:
It
must
be
performed
according
to the Maintenance Manual for WT9 Dynamic LSA
after the first 25 ± 2 hr. operation together
with the engine check. The scope of this check is
same as the check after 50 hr. of operation.
Check after 50 hr. of operation:
It
must
be
performed
according
to the Maintenance Manual for WT9 Dynamic LSA
after the first 50 ± 3 hr. of operation together
with the engine check. The scope of this check is
same as the check after 25 hr. of operation.
The following work should be carried out:
1. Fixed undercarriage: Check the legs attachment into the wing central panel
and into the fuselage. Check the control of the nose wheel, brakes and tyres.
2. Outside surface check: Check all control surface shafts, the rods, the articulated joints,
the hinges, the control cables, and the auxiliary tail skid. Sparingly lubricate the control
service hinges. Thoroughly clean and lubricate the piston rod of the canopy gas struts.
3. Check the control cable guides: Lubricate the roller-bearings of the elevator control
rod.
4. Check charging: Charge battery if necessary, cleaning.
5. Powerplant: Visually check the hoses for condition, damage, leaks, attachment
and security, the rubber flange of the air filter for cracks. Visually check exhaust system
for condition, cracks, deformation or damage. Lubricate the bowden cable for throttle
and starting carburettor (choke) (see the Maintenance Manual for ROTAX 912 ULS).
6. Check the brake fluid level: Check the fluid level in the brake system unit, which is
located under the pilot seat. Check the brakes for operation.
7. Control surfaces deflections: To check the control surfaces deflections see Control
Surfaces Deflections Record, which is contained in the Maintenance Manual
for WT9 Dynamic LSA.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
100 hr. check:
FLIGHT MANUAL
Section 8, Page 4
Must be performed every 100 hr. of operation
or 1 year, whichever comes first. This inspection
must be performed by qualified staff. The scope
of this inspection is the same as the check
after 50 hr. of operation covering the following work:
1. Full cleaning of the airplane.
2. Check airplane surfaces for mechanical damage and cracks.
3. Pay special attention to:
- Undercarriage and its attachment into the wing central panel.
- Wing-fuselage connection reliability, clearances, spar ends state.
- Engine mount, welded areas, rubber engine mounts, security of attachment bolts:
engine-engine mount, engine mount-firewall.
4. Visually check condition and integrity of wires, check charging – charge battery,
function of the signal bulbs, function of the fuel quantity indicator, fuel drains
and fuel vents for blockages, fuel filters.
5. Visually check condition of the instruments and the avionics (connector, a plug)
and for correct operation.
6. Lubricate according to the Lubrication Chart.
7. Check tyres for condition, cuts, uneven or excessive wear and slippage – replace if
needed.
Lubrication Chart:
The manufacturer recommends using grease and oil without acid for lubrication only. Apply
the lubricants sparingly without contaminating of the airframe.
Check condition of the bearings of the main wheels – clean and lubricate if needed,
at least every 2 years.
Check condition of the bearings of the nose wheel – clean and lubricate if needed,
at least twice per year.
Lubricate:
Sparingly lubricate:
Main and rear spar pins.
The axle of the nose wheel leg.
Guide tube of the flap control lever.
The pins of the nose undercarriage leg and
support bearings.
The hinges of the control surfaces, movable parts
of the control surfaces, bearings of the ailerons,
the pedals and the brake control lever, all control
cables at inlet into the terminations (in engine
compartment).
Battery:
The aircraft is equipped with 17 Ah lead-acid battery. The powerplant is equipped
with an AC generator, which recharges the battery in the flight.
Battery is dry and hermetically closed. It doesn’t release any toxic or explosive gas.
The battery needs a visual check of the attachment and security.
Rubber parts:
All rubber parts (hoses, tyres, etc.) have to be changed after 5 years of operation.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
8.3.
FLIGHT MANUAL
Section 8, Page 5
Airplane alterations or repairs
It is essential that the responsible airworthiness authority be contacted prior to any
alterations on the airplane to ensure that the airworthiness of the airplane is not violated.
For repairs refer to the applicable Maintenance Manual. The operator is allowed replace parts
supplied by the producer only. The repairs to damaged skin must be carried out by qualified staff
in accordance with approved procedures.
WARNING
After airplane repairs, repainting or mounting of additional
instruments or equipment it is necessary to check weights
and CG positions!
8.4.
Ground handling / Road transport
The airplanes can suffer higher stress loads on the ground than in the air. In this case it can
result a potential menace of the safety, as the airplane construction is designed for the manoeuvring
load. The high aircraft normal accelerations are occurred at the hard landing, during the taxiing
at the rough surface and during the driving through a hole at road.
Don’t use unnecessary transportation in the road.
CAUTION
The airplane is equipped with mooring eyes which are
screwed into the threaded hubs on the wing lower surface
located approx. half way along the wing. It is also necessary
to moor the nose wheel landing gear!
CAUTION
Push or pull the airplane from the propeller blade root only,
never at the wing tips or the control surfaces!
8.5.
Cleaning and care
Regular cleaning and care of the powerplant, propeller, wings and the airframe is
the first consideration for safe and efficient operation. Cleaning and care should be based
on climatic and flying conditions. The exterior painted surfaces should be cleaned with clear water
using a sponge or soft cotton towel and chamois. These surfaces should also be protected
with a silicone free hard wax reapplied at least once a year by hand or with a rotating cloth disc.
Clean the Plexiglass canopy only as necessary using a soft cotton towel and clear water
mixed with a small amount of mild detergent. Protect the canopy with anti-static cleaning agents
which are made specifically for Plexiglas.
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 8, Page 6
CAUTION
Do not clean the canopy with alcohol, acetone or lacquer
thinner, because the canopy is made from acrylic. Acrylic
becomes fragile after contact with these liquids!
8.6.
Winter operation
The cooling system of the cylinder heads is filled with a mixture of anti-freeze and water,
which protects the cooling system against freezing up to -38 °C. Check coolant with dense meter
or glycol tester before winter operation to prevent the failure of the radiator or cooling system due
to ice.
If the temperature is below this value, the coolant must be drained or renewed
with pure anti-freeze liquid. The coolant must be renewed every two years. Use only coolant
according to the current Operator’s Manual for ROTAX 912 ULS.
If low cylinder head or oil temperatures occur during operation under low outside
temperature, then the following is recommended:
Cover a part of radiator face by a duralumin sheet or drawing paper of appropriate
dimensions, insert it between the radiator and the bottom engine cowling.
Cover the oil cooler face or a part of the face only, by a duralumin sheet or drawing paper
attached with a suitable adhesive tape (or bend the oil cooler with that tape) and lag the oil tank.
CAUTION
The temperature limits of the coolant, cylinder heads and oil
must be checked after these arrangements!
I winter operation is advisable to disconnect the ventilation intake hose (VIH) (Fig. 13)
due the better performance of heating system. After disconnecting the ventilation intake hose close
the socket for the hose. Otherwise the ram air will be lost through this opening.
Ventilation intake hose
(VIH)
Fig. 13 Ventilation intake hose
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
FLIGHT MANUAL
Section 9, Page 1
9. SUPPLEMENTS
Section
Page
9.1. ....................... INTRODUCTION .......................................................................................2
9.2. ....................... LIST OF INSERTED SUPPLEMENTS .............................................................2
9.3. ....................... SUPPLEMENTS INSERTED .........................................................................2
Date of revision: 16.07.2012
Revision: 0
WT9 Dynamic LSA Club LT
9.1.
FLIGHT MANUAL
Section 9, Page 2
Introduction
This section contains the appropriate supplements necessary to safely and efficiently
operate the airplane when equipped with various optional systems and equipment not provided
with the standard airplane.
NOTE
Additional individual equipment in accordance
with a customer’s request will increase the airplane empty
weight and reduce the allowed useful load!
9.2.
List of inserted supplements
Inserted supplements are listed in "Checklist of equipment" which is part of production
documentation.
9.3.
Supplements inserted
For operation and handling with inserted supplements see corresponding Operation
manuals.
Date of revision: 16.07.2012
Revision: 0
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