Aerospool WT-9 Dynamic Technical specifications

LIMITED COMPANY
AEROSPOOL PRIEVIDZA
Airfield Prievidza
971 03 PRIEVIDZA
Sl vak Republic
Fax: [phone]
Tel.: [phone]
aer sp l@aer sp l.sk
www.aer sp l.sk
F L I G H T M A N U A L
FOR THE AEROPLANE
WT-9 Dynamic
Type: WT-9 Dynamic
Model:
erial No:
Registration:
Date of Issue:
Pages identified by „Appr“ are approved by the Civil Aviation Authority of the
ignature:
Authority:
tamp:
Original date of approval:
This aer plane has t be perated in c mpliance with inf rmati n and limitati ns c ntained
herein.

WT-9 Dynamic Club
FLIGHT MANUAL ection 0 Page 0-
1
0.1. RECORD OF REVI ION
Any revisi n f the present manual, except actual weight data, must be rec rded in the
f ll wing table and in case f appr ved Secti ns end rsed by the resp nsible
airw rthiness auth rity.
The new r amended text in the revised pages will be indicated by a black vertical line in
the right hand margin, and the Revisi n N . and the date will be sh wn n the b tt m
left side f the page.
Rev.
No.
Affected
ection
Affected
Pages Date
Approval Date Date
inserted ignature
1 2, 3 2-1,2, 3-3 08.12.03
08.12.03
2 3 3-2 22.09.04
22.09.04
3 7 2,7,8,9,10 01.10.06
01.10.06
4 2, 4, 5, 7 2-5,7,9,
4-1-3, 4-12,
5-4,
7-2, 7-11,12
15.01.07
15.01.07
5 7 7-12 17.08.10
17.08.10
5 1 1-4 21.02.07
21.02.07
6 7 7-5 28.11.07
28.11.07
7 0 1, 2 01.12.08
ZBWT9
10A/2008
- - 01.12.08
7 3 5, 6 01.12.08
ZBWT9
10A/2008
- - 01.12.08
8 0 1, 2 05.10.09
ZBWT9
11A/2009
- - 05.02.2010
8 2 1, 3, 6 05.10.09
ZBWT9
11A/2009
- - 05.02.2010
8 4 12 05.10.09
ZBWT9
11A/2009
- - 05.02.2010
Date:05.10.2009, Rev.: 8

WT-9 Dynamic Club FLIGHT MANUAL ection 0 Page 0-2
0.2 LI T OF EFFECTIVE PAGE
ection Page Date ection Page Date
0 0-1 05.10.2009 5 „Appr“ 5-1 01.12.2001
0-2 05.10.2009 „Appr“ 5-2 01.12.2001
0-3 01.12.2001 „Appr“ 5-3 01.12.2001
0-4 01.12.2001 „Appr“ 5-4 15.01.2007
„Appr“ 5-5 01.12.2001
1 1-1 01.12.2001
1-2 01.12.2001 6 6-1 01.12.2001
1-3 01.12.2001 6-2 01.12.2001
1-4 21.02.2007 6-3 01.12.2001
„Appr“ 6-4 01.12.2001
2 „Appr“ 2-1 05.10.2009
„Appr“ 2-2 08.12.2003 7 7-1 01.12.2001
„Appr“ 2-3 05.10.2009 7-2 15.01.2007
„Appr“ 2-4 01.12.2001 7-3 01.12.2001
„Appr“ 2-5 15.01.2007 7-4 01.12.2001
„Appr“ 2-6 05.10.2009 7-5 28.11.2007
„Appr“ 2-7 15.01.2007 7-6 01.12.2001
„Appr“ 2-8 01.12.2001 7-7 01.10.2006
7-8 01.10.2006
3 „Appr“ 3-1 01.12.2001 7-9 01.10.2006
„Appr“ 3-2 22.09.2004 7-10 01.10.2006
„Appr“ 3-3 08.12.2003 7-11 15.01.2007
„Appr“ 3-4 01.12.2001 7-12 15.01.2007
„Appr“ 3-5 01.12.2008
„Appr“ 3-6 01.12.2008 8 8-1 01.12.2001
8-2 01.12.2001
4 „Appr“ 4-1 15.01.2007 8-3 01.12.2001
„Appr“ 4-2 15.01.2007 8-4 01.12.2001
„Appr“ 4-3 15.01.2007 8-5 01.12.2001
„Appr“ 4-4 01.12.2001 8-6 01.12.2001
„Appr“ 4-5 01.12.2001
„Appr“ 4-6 01.12.2001 9 „Appr“ 9-1 01.12.2001
„Appr“ 4-7 01.12.2001 „Appr“ 9-2 01.12.2001
„Appr“ 4-8 01.12.2001
„Appr“ 4-9 01.12.2001
„Appr“ 4-10
01.12.2001
„Appr“ 4-11
01.12.2001
„Appr“ 4-12
05.10.2009
Date:05.10.2009, Rev.: 8

WT-9 Dynamic Club FLIGHT MANUAL ection 0 Page 0-3
ection Page Date ection Page Date
Date:01.12.01

WT-9 Dynamic Club FLIGHT MANUAL ection 0 Page 0-4
0.3 TABLE OF CONTENT
ection
GENERAL 1
LIMITATION 2
EMERGENCY PROCEDURE 3
NORMAL PROCEDURE 4
PERFORMANCE 5
WEIGHT AND BALANCE / EQUIPMENT LI T 6
AIRPLANE AND Y TEM DE CRIPTION 7
AIRPLANE HANDLING, ERVICING
AND MAINTENANCE 8
UPPLEMENT 9
Date:1.12.2001

WT-9 Dynamic Club FLIGHT MANUAL ection 1 Page 1-
1
ECTION 1
GENERAL
Page
1.1 Introduction 1-1
1.2 Certification basis 1-1
1.3 Warnings, cautions and notes 1-1
1.4 Descriptive data 1-2
1.5 Three – view drawing 1-3
1.1 Introduction
The aer plane Flight Manual has been prepared t pr vide pil ts and instruct rs with
inf rmati n f r the safe and efficient perati n f this aer plane.
This manual c ntains supplementary data supplied by the aer plane manufacturer.
1.2 Certification basis
This type f airplane has been appr ved in Germany by the Deutscher Aer Club e.V.
(DaeC) in acc rdance with the German Certificati n Regulati ns and Airw rthiness
Requirements f r ultra light airplane f the DaeC (BFU des DaeC, Ausgabe 10/95) and
the Type Certificate N . 61179 has been issued n 23.10.2001.
The Civil Aviati n Auth rities f Sl vak Republic f ll wing an applicati n by
AEROSPOOL, sp l. s r. . Prievidza and after studying the d cumentati n Predpis
MDPT SR L 8/A and LU č. P- ULL-1 SR has issued the Type Certificate f
Airw rthiness
N . V-80/2004 dated April 25
th
2005 f r Type WT-9 Dynamic
Categ ry f Airw rthiness : Normal
1.3 Warnings, cautions and notes
The f ll wing definiti ns apply t warnings, cauti ns and n tes used in the flight
manual.
WARNING
Means that the n n- bservati n f the c rresp nding pr cedure
leads t an immediate r imp rtant degradati n f the flight
safety.
CAUTION
Means that the n n- bservati n f the c rresp nding pr cedure
leads t a min r r t a m re r less l ng term degradati n f the
flight safety.
NOTE
Draws the attenti n t any special item, n t directly related t
safety but which is imp rtant r unusual.
Date: 1.12.2001

WT-9 Dynamic Club FLIGHT MANUAL ection 1 Page 1-2
1.4 Descriptive data
1.4.1 Airplane description
WT-9 Dynamic Club S is l w-wing m n plane with fixed landing gear. The airframe
c nsists f a sandwich shells fr m advanced c mp site material. There are tw places
in the c ckpit, side by side type. This airplane is intended f r sp rting, recreati n and
t urist flying in acc rdance with VFR.
WT-9 Dynamic Club S has been appr ved by the DaeC in the Categ ry f
Airw rthiness : N rmal
As the p wer plant this airplane uses the 4 cylimder, 4 str ke ROTAX engines, 912
ULS. Pr pelers: This plane is fitted with 2 blades hydraulic c nstant speed MTV-21-A
1.4.2 Technical data
Wing span.................................................…. 9,00 m
Wing area…................................................... 10,3 m
2
Wing aspect rati ............................................ 7,82
Length............................................................. 6,4 m
Height.........................................................… 2,0 m
Aer dynamic mean ch rd ( MAC )............… 1,185 m
Control surfaces
Ailer n span………........................................ 1,25 m
Ailer n area…................................................. 0,273 m
2
Flap span………............................................. 2,28 m
Flap area…….................................................. 0,75 m
2
H riz ntal tail span……………….……......... 2,40 m
H riz ntal tail area…………………............... 1,68 m
2
Vertical tail span………………...............….... 1,022 m
Vertical tail area……………….................….. 1,02 m
2
Landing gear
Wheel spacing.……………………............…. 1,49 m
Wheel base..................................................…. 2,27 m
Main wheel diameter……………................… 0,35 m
N se wheel diameter………………………… 0,32 m
Weights
Empty weight ……………………………….….... 334,1 kg
Maximum take- ff weight…….....................……. 472,5 kg
Useful l ad……….....................................……..... 138,4 kg
Fuel tanks capacity…………................................. 126 litres
The ROTAX 912 ULS (73 kW- 100HP) with a maximum rpm limitati n n take ff f
5800 1/min. The pr peller MTV-21-A diameter is 1,7 m
Date: 1.12.2001

WT-9 Dynamic Club FLIGHT MANUAL ection 1 Page 1-3
1.5. Aeroplane views
Date: 01.12.2001
Ph t 2
Ph t 1

WT-9 Dynamic Club FLIGHT MANUAL ection 1 Page 1-4
1.5.1 Three – view drawing
Date: 21.2.2007 / Rev.: 5

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-1
ECTION 2
LIMITATION
Page
2.1 Introduction 2-1
2.2 Airspeed 2-1
2.3 Airspeed indicator markings 2-2
2.4 Power plant 2-2
2.5 Power plant instrument markings 2-3
2.6 Miscellaneous instrument markings 2-4
2.7 Weight 2-5
2.8 Centre of gravity 2-5
2.9 Approved manoeuvres 2-5
2.10 Manoeuvring load factors 2-6
2.11 Flight crew 2-6
2.12 Kinds of operation 2-6
2.13 Fuel, oil 2-6
2.14 Maximum passenger seating 2-7
2.15 Other limitations 2-7
2.16 Limitations placards 2-7
2.1 Introduction
Secti n 2 includes perating limitati ns, instrument markings, and basic placards
necessary f r safe perati n f the aer plane, its engine, standard systems and standard
equipment. The limitati ns included in this secti n have been appr ved by the Civil
Aviati n Auth rity f the Sl vak Republic.
2.2 Airspeed
Airspeed limitati ns and their perati nal significance are sh wn bel w:
peed IA Remarks
km/h MPH knots
V
NE
Never Exceed speed 280 174 150 D n t exceed this speed in any
perati n
V
NO
N rmal Operating Limit
speed 250 156 135 D n t exceed this speed except in
sm th air, and then nly with cauti n
V
RA
R ugh Air speed 225 140 121
D n t exceed this speed except in
sm th air. Air m vements in lee-wave
r t rs, thundercl uds, visible whirlwind,
r ver m untain crests are t be
underst d as r ugh air
Date: 05.10.2009, Rev.: 8 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-
2
peed IA Remarks
km/h MPH knots
V
A
Man euvring speed 165
103 88
D n t make full r abrupt c ntr l
m vement ab ve this speed, because
under certain c nditi ns the airplane
may be verstressed by full c ntr l
m vement
V
FE
Maximum Flap Extended
speed 140 88 75 D n t exceed these speeds with the
given flap setting.
2.3 Airspeed indicator markings
Airspeed indicat r markings and their c l ur-c de significance are sh wn bel w:
Marking IA value or range ignificance
km/h MPH knots
White arc
65 – 140
40 - 88
35 - 75
P sitive Flap Operating Range. ( L wer limit
is maximum weight 1.1 V
SO
in landing
c nfigurati n. Upper limit is maximum speed
permissible with flaps extended p sitive.)
Green arc 70 – 230 43 - 143 37 - 124
N rmal Operating Range. ( L wer limit is
maximum weight 1.1 V
S1
at m st f rward c.g.
with flaps and landing gear retracted ( if
retractable ). Upper limit is V
RA
.
Yellow arc 230 – 280
143 - 174 124 - 150
Man euvres must be c nducted with cauti n
and nly in sm th air.
Yellow triangle 100 62 53 Minimum Appr ach speed
Yellow line 165 103 88 V
A
Man evring speed
Red line 280 174 150 Maximum speed f r all perati ns.
2.4 Powerplant
Engine Manufacturer: ROTAX-B mbardier, Gunskirchen
Engine M dels: ROTAX 912 ULS
Maximum P wer - Take- ff: 73,5 kW / 100 HP
C ntinu us: 69 kW / 93,8 HP
Maximum Engine Speed – Take- ff: 5800 1/min ( 5 min )
C ntinu us: 5500 1/min
Maximum Cylinder Head Temperature: 135 ° C
Maximum Oil Temperature: 130 ° C
Maximum C lant Temperature: 120 ° C
Oil Pressure: Minimum: 0,8 bar ( 12 psi )
Maximum: 7 bar ( 102 psi )
Fuel Pressure: Minimum: 0,15 bar ( 2.2 psi )
Maximum: 0,4 bar ( 5.8 psi )
Fuel Grade: the f ll wing fuels can be used:
min. RON 95
Date: 8.12.2003 / Rev.: 1 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-
3
- EN 228 Super (Unleaded Aut m tive Gas line RON 95)
- EN 228 Super plus (Unleaded Aut m tive Gas line RON 98)
- AVGAS 100 LL (Due t the higher lead c ntent in AVGAS,
the wear f the valve seats, the dep sits in c mbusti n
chamber and lead sediments in the lubricati n system will
increase. Theref re, use AVGAS nly if y u enc unter
pr blems with vap ur l ck r if the ther fuel types are n t
available)
- Fuel E10 (unleaded gas line blended with 10% ethan l
Oil Grade: - engine il f a registered brand with gear additives. Use nly
il with API classificati n „SF“ r „SG“
- high perf rmance 4-str ke m t r cycle ils are rec mmended
- If using airplane engine il, then nly blended ne.
Oil capacity: 3,0 litre
Minimum: 2,0 litre
Oil c nsumpti n: max. 0,06 l/h
WARNING
Never use AVGAS, LB 95 with fully synthetic engine ils.
Pr peller Manufacturer: MT Pr peller
Pr peller M del: MTV-21-A, 2 blade, hydraulic c nstant speed
Pr peller Diameter: 1,7 m
Pr peller Blade Angle 13° - 30°
Additi nal data can be f und in Secti n 7, Subpart 7.9, in the Operat r Manual f r
engine ROTAX 912 ULS and in the User Guide f r pr peller MTV-21-A.
WARNING
Never run the engine with ut pr peller, this inevitably causes
engine damage and is an expl si n hazard.
2.5 Powerplant instrument markings
Acc rding t cust mer requirement r und ne–purp se needle instruments are fitted in
the instrument panel.
Date: 05.10.2009, Rev.: 8 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-
4
P werplant instrument markings and their c l ur c de significance are sh wn bel w:
Instrument Unit
Red Line
Minimum
Limit
Green Arc
Normal
Operating
Yellow
Arc
Caution
Range
Red Line
Maximum
Limit
Tachometer rpm 1 400 1 800 – 5 500 5500–5800 5 800
Oil temperature
indicator
o
C 50 90 – 110 50 – 90
110 – 130 130
Cylinder-head
coolant
temperature
o
C
90 – 110 50 – 90
110 – 120 120
Cylinder-head
temperature
indicator
o
C 90 – 110 110 – 135 135
Fuel-pressure
indicator bar 0,15 0,4
Oil-pressure
indicator bar 0,8 0,8 – 5 5 – 7 7
Fuel indicator l
2.6 Miscellaneous instrument markings
Acc rding t pti n f the cust mer miscellane us instrument can be m unted. The
f ll wing miscellane us instrument markings and their c l ur c de significance are
sh wn bel w:
Instrument Unit
Red Line
Minimum
Limit
Green Arc
Normal
Operating
Yellow
Arc
Caution
Range
Red Line
Maximum
Limit
Boost-pressure
gauge
in Hg 11,8 11,8-28 28-29,5 29,5
Fuel reserve
indicator
Red light annunciator will be illuminated with the
remaining fuel of 7 litre in each fuel tank.
Date: 1.12.2001 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-5
2.7 Weight
Empty weight - with fixed undercarriage …..……...334,1 kg
Maximum take- ff weight....……...............……. 472,5 kg
Maximum landing weight ……................……… 472,5 kg
Useful l ad ………........................................……138,4 kg
Maximum fuel weight ……............................…….... 91 kg
Maximum weight in Baggage C mpartment…...... 10 kg
WARNING
Maintain maximum take ff weight 472,5 kg
Depending n different c untries rules
2.8 Centre of gravity
P siti n f C.G.:
Empty airplane.....................................12 ± 2% MAC
P siti n f C.G. in flight…..................20 ÷ 30% MAC
Rear centre f gravity limit is valid f r en-r ute weight at maximum crew weight.
F rward centre f gravity limit is valid f r minimum pil t weight and minimum
capacity f the fuel tanks.
Example t check the centre f gravity p siti n is in Sect. 6.
2.9 Approved manoeuvres
WT-9 Dynamic Club S is certified in the N rmal Categ ry – Ultralight airplane. The
f ll wing man euvres are permited:
− teep turns with the angle of bank up to 60°
°°
° - appr priate entry speed is 140 km/h.
− Lazy eighths - appr priate entry speed is 140 km/h.
− Combat turns - appr priate entry speed is 200 km/h.
Date: 15.1.2007 / Rev.: 4
„Appr“
WARNING
A flight shall n t be c mmenced until the pil t-in-
c mmand
is satisfied that the mass f the airplane and centre f
gravity l cati n are such that the flight can be c nducted
safely!
WARNING
Aer batic man euvres and intenti nal spins are pr hibited!

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-6
2.10 Manoeuvring load factors
Manoeuvre speed peed
Load factors
km/h
MPH knots
V
A
- Man euvring speed 165 103 88 + 4
V
NE –
Never exceed speed 280 174 150 + 4
V
A
– Man euvring speed 165 103 88 -2
V
NE –
Never exceed speed 280 174 150 -2
V
FE
– Maximum Flap Extended
speed 140 88 75 + 2
2.11 Flight crew
The minimum flight crew with which the airplane is all wed t fly is ne pil t sitting in
the left pil t seat. The passenger r an ther pil t may ccupy the right seat in the
c ckpit.
2.12 Kinds of operation
The airplane WT-9 Dynamic Club S is appr ved t perf rm flights in acc rdance with
VFR nly. Aer batic man euvres and intenti nal spins are pr hibited!
WARNING
IFR flights and flights in icing c nditi ns are pr hibited.
F r flight perati ns the f ll wing minimum equipment must be installed:
- Magnetic c mpass
- Sensitive bar metric altimeter
- Airspeed indicat r
- Pil t’s Safety belts
2.13 Fuel, oil
The f ll wing fuels and ils can be used f r the airplane WT-9 Dynamic Club S : see
chapter 2.4 P werplant and the Operat r’s Manual f r engine ROTAX 912 ULS
Date: 05.10.2009, Rev.: 8 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2-7
Left tank ( l ) Right tank ( l )
The total quantity of fuel in the tank 63 63
Unusable fuel in the tank 2,9 2,9
The total usable quantity of fuel in the tank 60,1 60,1
2.14 Maximum passenger seating
The maximum number f passenger ab ard is ne passenger sitting in the right seat in
the c ckpit.
2.15 Other limitations
a) Wind speed
The maximum cr sswind c mp nent limit acc rding t the airw rthiness
requirements f r take ff and landing is 6 m/s (12 knots).
b) moking
NO MOKING n b ard the ultralight airplane.
2.16 Limitations placards
Airspeed IA
km/h MPH knots
Never Exceed speed V
NE
280 174 150
N rmal Operating Limit speed V
NO
250 156 135
R ugh Air speed V
RA
225 140 121
Man euvring speed V
A
165 103 88
Maximum Flap Extended
speed V
FE
140 88 75
Aerobatics, intentional spins and stalls are prohibited!
IFR flights and flights in icing conditions are prohibited !
Date: 15.1.2007 / Rev.: 4 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 2 Page 2- 8
Maximum allowed filling of the fuel tanks in litres
Baggage
weight (kg)
Crew weight (kg)
80 90 100 110 120 130 140
0 81 67 53 40 26 12 0
5 74 60 46 33 19 5 0
10 67 53 40 26 12 0 0
Maximum Baggage
weight 10 kg
Date: 1.12.2001 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 3 Page 3-
1
ECTION 3
EMERGENCY PROCEDURE
Page
3.1 Introduction 3-1
3.2 Engine failure 3-1
3.3 Air start 3-2
3.4 moke and fire 3-2
3.5 Glide 3-3
3.6 Landing emergency 3-3
3.7 Recovery from unintentional spin 3-4
3.8 Other emergencies 3-5
3.1 Introduction
Secti n 3 pr vides checklist and amplified pr cedures f r c ping with emergencies that
may ccur. Emergencies caused by aer plane r engine malfuncti n are extremely rare
if pr per preflight inspecti ns and maintenance are practised.
H wever, sh uld an emergency arise, the basic guidelines described in this secti n
sh uld be c nsidered and applied as necessary t c rrect the pr blem.
3.2 Engine failure
3.2.1 Engine failure at take-off roll
1. Thr ttle lever - set t idle p siti n
2. Igniti n - b th circuits switched ff
3. Brakes - apply till st p
3.2.2 Engine failure at take-off up to height 50 m
1. Airspeed - m dify t 120 km/h
2. Field selecti n - land straight ahead n m re than 15° left r right int
wind if p ssible. Gr und l p if required.
3. Igniti n - b th circuits switched ff
4. Fuel select r valve - cl se
3.2.3 Engine failure at take-off above height 50 m
1. Airspeed - m dify t 120 km/h
2. Field selecti n - select in the directi n f the free area with ut bstacles,
if p ssible int wind
3. Igniti n - b th circuits switched ff
4. Fuel select r valve - cl se
5. Flaps - extend as required
Date: 1.12.2001 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 3 Page 3-
2
3.2.4 Engine failure in flight
1. Airspeed - m dify t 120 km/h
2. Field selecti n - acc rding t height available
3. Air start - in acc rdance with item 3.3
4. In case f an unsuccessful air start, perf rm emergency landing in acc rdance
with item 3.6.1.
3.2.5 Performance loss and irregular running of the engine during flight
This situati n may ccur with carburett r icing.
Apply carburett r pre-heating as required t rest re n rmal p wer, sm th running.
Or it can happen because f empty fuel tank, the indicat r is the fuel pressure l ss –
select the n n empty fuel tank.
If everthihg fails perf rm an emergency landing.
3.3 Air start
1. Airspeed -m dify t 120 km/h
2. Altitude flight - check
3. Field selecti n - select acc rding t height available
4. Fuel select r valve - pen
5. Ch ke - if the engine is already in perating temperature,
start the engine with ut ch ke
6. Thr ttle lever - at c ld engine set t idle p siti n
- at warm engine slightly pen
7. Igniti n - b th circuits switched n
8. Starter butt n - actuate
As s n as engine runs, adjust thr ttle t achieve sm th running at 2500 r.p.m f r
appr ximately half a minute bef re increasing p wer as required.
WARNING
The rate f descent appr x. 2.3 m/s causes measurable l ss f
altitude during the air start. If the air start is unsuccessful up t
height 150 m ab ve gr und level, perf rm emergency landing
acc rding t item 3.6.1.
3.4 moke and fire
3.4.1 Engine fire on the ground
1. Fuel select r valve - cl se
2. Thr ttle lever - full pen
3. Igniti n - b th circuits switched ff after c nsumpti n f
the fuel
4. Crew - leave the c ckpit immediately
5. Extinguish fire - with best available means
3.4.2 Engine fire in flight
1. Fuel select r valve - cl se
2. Thr ttle lever - full pen
3. Igniti n - b th circuits switched ff after c nsumpti n f
the fuel
Date: 22.9.2004 / Rev.: 2 „Appr“

WT-9 Dynamic Club FLIGHT MANUAL ection 3 Page 3-
3
4. Try t extinguish the fire with side slip
5. Perf rm emergency landing in acc rdance with item 3.6.1.
CAUTION
After extinguishing the fire d n t start engine again!
3.4.3 Fire in cockpit
1. Fire s urce - l cate
2. Igniti n - b th circuits switched ff
3. Master switch - ff
4. Crew - leave the c ckpit n the gr und ,
- perf rm emergency landing acc rdance with item 3.6.1.
5. Try t extinguish - with best available means
3.5 Glide
Glide path will determine the field selecti n f r emergency landing. The ptimum
gliding perf rmance is with retracted wing flaps and with st pped pr peller.
In case f engine failure it is necessary t maintain the f ll wing ptimum speeds f r
given c nfigurati n.
Optimum descent
airspeed IA km/h MPH knots
120 75 65
Maximum gliding range 11
Rate of descent 3,0 m/s 600 ft/min
3.6 Landing emergency
3.6.1 Emergency landing
1. Airspeed - m dify t 110 km/h
2. Field selecti n - select in the directi n f the free area with ut
bstacles, if p ssible int wind
3. Seat belts and harness - fasten
4. Flaps - extend as required
5. Fuel select r valve - cl se
6. Igniti n - b th circuits switched ff
7. Master switch - ff
CAUTION
The l ss f height f r 360 ° turn is appr x.. 120 m.
Date: 8.12.2003 / Rev.: 1 „Appr“