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Shark UL Flight Manual

Flight manual UL aircraft
FLIGHT MANUAL
UL airplane
SHARK.AERO s.r.o
SHARK.AERO CZ s.r.o.
Version: AFM Shark-EN 60_2017-05-17_final
created from Czech original version :
AFM_Shark-CZ_60_2017-04-22_certifikat.doc
Flight manual UL aircraft
Airplane Type / version: SHARK UL
Serial number:
Registration:
Date of issue:
LAA - Approval number and date:
ULL - 05 / 2013
1.3. 2013 / 20.12. 2016
Manufacturer – stamp and signature :
The airplane must be operated according to informations and
limitations presented in this handbook.
This handbook must be available to pilot at any time of the
flight.
Flight manual UL aircraft
LIST OF THE REVISIONS AND THE EPAIRS
Ordinal No.
Number of document ­bulletin
It concerns to pages No.
Date of issue
Signature
1/13
2-1,2-2,2-6,2-9, 3-1 to 3-3, 3-6 to 3-8 4-1 to 4-11 5-1 to 5-5 6-2 7-8 to 7-10 appendix 3-3 format editing
5.3.2013
V.Pekár
2/13
2-6,2-7,6-1 to 6-7
15.3.2013
V.Pekár
3/13
2-6, 5-1,5-2,6-4,6-5,6-6
4.4.2013
V.Pekár
4/15
2-4, 2-6, 7-10, 7-18, 8-6
28.4.2015
J. Skočej
5/16
57-00
1-2,2-3,2-4,2-6, 3-6, 4-3, 4-7, 4-11,4-12, 5-2 to 5-6, 6-6, 7-1, 7-10, 7-11, 7-12, 7-14, 7-15, 7-18 to 7-27, 8-6
19.5.2016
V.Pekár
6/16
57-02
4-13
17.7.2016
V.Pekár
7/16
57-03
3-6 to 3-9, 5-2, 5-3, 7-1, 7-7, 7-14,7-19 to 7-29
22.8.2016
V.Pekár
8/16
57-04
4-15, 6-7 to 6-9
22.12.2016
V.Pekár
9/17
57-05
1-2, 2-1, 2-8, 2-9, 4-15, 6-2, 6-4, 6-5
1.2.2017
V.Pekár
10/17
57-06
Rewritten as a part of the LAA type certification requirements
1.4.2017
J.Dostál
Flight manual UL aircraft
Flight manual UL aircraft
Content
1. General ........................................................................ 1-1
1.1. Introduction .................................................................. 1-1
1.2. Certification bases ....................................................... 1-1
1.3. Warnings, cautions and notes ..................................... 1-1
1.4. Airplane basic description ............................................ 1-2
1.5. Three view drawing ...................................................... 1-3
2. Limitations .................................................................... 2-1
2.1. Airspeed ....................................................................... 2-1
2.2. Airspeed indicator markings ....................................... 2-1
2.3. analog airspeed indicator markings ............................. 2-2
2.4. Engine .......................................................................... 2-3
2.5. Engine instrument marking .......................................... 2-4
2.6. Weight limits ................................................................ 2-5
2.7. Center of gravity (CG) .................................................. 2-6
2.8. Approved maneuvers ................................................... 2-6
2.9. Maneuvering load factor G .......................................... 2-6
2.10. Flight crew ................................................................... 2-6
2.11. Kind of operation .......................................................... 2-7
2.12. Fuel .............................................................................. 2-7
2.12.1. Approved fuel types ..................................................... 2-7
2.12.2. Fuel tanks capacity ...................................................... 2-7
2.13. Other limitations ........................................................... 2-8
2.14. Placards ....................................................................... 2-9
3. Emergency procedures................................................ 3-1
3.1. Engine failure and emergency landing ........................ 3-1
3.1.1. Engine failure during take-off run ................................ 3-1
3.1.2. Engine failure during take-off ....................................... 3-1
3.1.3. In-flight engine failure .................................................. 3-2
3.1.4. Carburettor icing .......................................................... 3-2
3.2. In-flight engine restart .................................................. 3-2
3.3. Fire ............................................................................... 3-3
3.3.1. Engine fire on the ground ............................................ 3-3
3.3.2. Engine fire during take-off............................................ 3-3
3.3.3. Engine fire in flight ....................................................... 3-3
3.3.4. Cockpit / electrical fire .................................................. 3-4
3.4. Gliding .......................................................................... 3-4
3.5. Precautionary Landing ................................................. 3-4
3.6. Blown-Out Tire Landing ............................................... 3-4
3.7. Landing with Damaged Landing Gear ......................... 3-5
3.8. Landing gear retraction malfunction ............................ 3-5
3.9. Landing gear opening malfunction .............................. 3-5
3.10. Vibrations from engine or other engine problem ........ 3-6
Flight manual UL aircraft
3.11. Inadvertent icing encounter ......................................... 3-6
3.12. Extreme turbulence encounter .................................... 3-6
3.13. Electrical system malfunctions .................................... 3-7
3.14. Inadvertent Stall and spin recovery ............................. 3-8
3.14.1. Stall recovery ............................................................... 3-8
3.14.2. Spin recovery ............................................................... 3-8
3.15. USe of Rescue system ................................................ 3-9
4. Normal procedures ...................................................... 4-1
4.1. Pre-flight inspection ..................................................... 4-1
4.1.1. Cockpit ......................................................................... 4-1
4.1.2. Wing ............................................................................. 4-2
4.1.3. Landing gear ................................................................ 4-2
4.1.4. Powerplant ................................................................... 4-2
4.1.5. Control cables .............................................................. 4-3
4.1.6. Tail unit and fuselage .................................................. 4-3
4.1.7. Turning on of electric devices ...................................... 4-3
4.2. Engine starting ............................................................. 4-3
4.2.1. Engine warm-up and test ............................................. 4-4
4.3. Before taxiing ............................................................... 4-4
4.4. Taxiing ......................................................................... 4-6
4.5. Check on holding line .................................................. 4-6
4.6. normal take off ............................................................. 4-7
4.7. Climb ............................................................................ 4-7
4.8. Cruise .......................................................................... 4-8
4.9. Approach ..................................................................... 4-8
4.9.1. Descent ........................................................................ 4-8
4.10. Downwind .................................................................... 4-9
4.11. Normal landing ............................................................ 4-9
4.11.1. On Base Leg ................................................................ 4-9
4.11.2. On Final ....................................................................... 4-9
4.11.3. Landing ........................................................................ 4-9
4.11.4. After landing............................................................... 4-10
4.11.5. Engine shut down ...................................................... 4-10
4.11.6. Post-Flight Check ...................................................... 4-10
4.12. Short field take-off and landing procedures .............. 4-10
4.13. Balked landing procedures ........................................ 4-10
4.14. Fuel SYSTEM use ..................................................... 4-11
4.15. REPEATED TAKE OFF ............................................. 4-11
4.16. High speed flights ...................................................... 4-12
4.16.1. Turbulences ............................................................... 4-12
4.16.2. Maneuvering .............................................................. 4-12
4.16.3. Landing gear opening ................................................ 4-12
4.16.4. Propeller, engine RPM .............................................. 4-13
Flight manual UL aircraft
4.16.5. Flaps .......................................................................... 4-13
4.16.6. Landing gear retraction .............................................. 4-13
4.16.7. Flutter, high altitude flights ......................................... 4-13
5. Performance ................................................................ 5-1
5.1. Airspeed indicator system calibration .......................... 5-1
5.2. Stall speed ................................................................... 5-2
5.3. TAKE-OFF Distance .................................................... 5-2
5.3.1. In flight adjustable prop. NEUFORM TXR2-V-70 ....... 5-2
5.3.2. In flight adjustable prop. Woodcomp SR3000/2WN .... 5-3
5.3.3. On ground adjustable prop. DUC SWIRL 1680 ........... 5-3
5.4. Landing distance .......................................................... 5-4
5.5. Rate of climb ................................................................ 5-4
5.6. Cruise, endurance, range ............................................ 5-5
6. Airplane empty weight and COG determination .......... 6-1
6.1. Weight and center of gravity determination for flight .. 6-3
7. Technical Description of the airplane .......................... 7-1
7.1. AIRFRAME .................................................................. 7-2
7.1.1. Fuselage ...................................................................... 7-2
7.1.2. Cockpit canopy ............................................................ 7-2
7.1.3. Engine cowlings ........................................................... 7-2
7.1.4. Wing ............................................................................. 7-3
7.1.5. Ailerons ........................................................................ 7-3
7.1.6. Flaps ............................................................................ 7-3
7.1.7. Horizontal stabilizer ..................................................... 7-3
7.1.8. Elevator ........................................................................ 7-3
7.1.9. Rudder ......................................................................... 7-3
7.1.10. Airplane exterior surface painting ................................ 7-4
7.2. Landing gear ................................................................ 7-4
7.2.1. Front undercarriage ..................................................... 7-4
7.2.2. Main undercarriage ...................................................... 7-5
7.2.3. Undercarriage retraction and extension ...................... 7-6
7.3. CONTROL SYSTEMS ................................................. 7-8
7.3.1. Elevator control ............................................................ 7-8
7.3.2. Aileron control .............................................................. 7-8
7.3.3. Rudder control ............................................................. 7-9
7.3.4. Flaps ............................................................................ 7-9
7.3.5. Elevator trim tab control ............................................... 7-9
7.4. ELECTRIC SYSTEM ................................................. 7-10
7.5. Fuel system ............................................................... 7-10
7.6. COCKPIT - interior and instruments .......................... 7-12
7.7. POWER UNIT .............................................................. 7-16
7.7.1. Technical data ........................................................... 7-17
7.8. PROPELLER ............................................................. 7-18
Flight manual UL aircraft
7.8.1. DUC SWIRL 3 blade, on the ground adjustable
propeller, diameter 1680 mm ..................................... 7-18
7.8.2. Woodcomp SR 3000 2W two blade in flight electrically
adjustable propeller ................................................... 7-19
7.8.3. Woodcomp KW 20W - two blade hydraulically in flight
adjustable .................................................................. 7-20
7.8.4. Neuform TXR2-V-70 .................................................. 7-21
7.9. Rescue system .......................................................... 7-22
7.9.1. Description of rescue system Stratos/Junkers Magnum
501 ............................................................................. 7-22
7.9.2. The activation mechanism ......................................... 7-23
7.9.3. Rescue system installation ........................................ 7-24
7.10. Towing system ........................................................... 7-25
7.11. Position lights............................................................. 7-26
7.12. Landing Light ............................................................. 7-26
7.13. ELT Unit ..................................................................... 7-27
7.14. Autopilot ..................................................................... 7-28
8. Airplane handling, care and maintenance ................... 8-1
8.1 Wing Dismounting ....................................................... 8-1
8.1.1. Remove flaps ............................................................... 8-1
8.1.2. Disconnect aileron controls ......................................... 8-2
8.1.3. Disconnect rear wing spar pin ..................................... 8-2
8.1.4. Disassemble the main wing spar pins ......................... 8-2
8.1.5. Disconnect fuel hoses and fuel sensors sockets......... 8-3
8.1.6. Remove wing spars out of center-wing ....................... 8-3
8.1.7. Disconnect pitostatic system hoses ............................ 8-3
8.1.8. Secure wings by hangaring (transport) jigs ................. 8-3
8.2. Stabilizer disassembly ................................................. 8-3
8.3. Parking and mooring ................................................... 8-4
8.3.1. General ........................................................................ 8-4
8.3.2. Cover of pitot tube ....................................................... 8-4
8.3.3. Mooring ........................................................................ 8-4
8.4. Hangaring, Ground Handling ....................................... 8-5
8.5. Towing ......................................................................... 8-6
8.6. Tire pressure................................................................ 8-6
9. Supplements ................................................................ 9-1
Page 1-1
Flight manual UL aircraft
1. GENERAL
1.1. INTRODUCTION
This handbook is provided with your airplane to allow you obtain as much knowledge as possible for the airplane operation. Read this manual before your first flight and make sure you understand all the information summarized here.
1.2. CERTIFICATION BASES
This aircraft was manufactured in accordance ultralight airworthiness standards and does not conform to standard category airworthiness requirements.
The following standards were used for approval and testing:
UL-2 Czech Republic requirements of LAA LTF-UL German requirements for ultralight airplanes
ASTM standard Requirements for Light Sport Aircraft (LSA) valid in
USA and used as a background for European light airplane standards.
1.3. WARNINGS, CAUTIONS AND NOTES
The following definitions applied to WARNINGS, CAUTIONS and NOTES are used in this manual:
WARNING: INFORMATION which could prevent personnel injury or
loss of life
CAUTION: INFORMATION which could prevent damage of equipment
NOTE: INFORMATION of special importance to pilot
Page 1-2
Flight manual UL aircraft
1.4. AIRPLANE BASIC DESCRIPTION
SHARK is an all-composite low-wing ultralight airplane with retractable undercarriage, tandem seats configuration, designed for fast cross-country flights.
Airplane is equipped with 100HP Rotax 912 ULS engine and one of propellers acc. paragraph 7.8.
Wing span
7,9 m
Length
6,85 m
Height
2,3 m
Wing area
9,5 m2
MAC length
1,237 m
Swept wing angles
3,53° / 13,8° / 39,8°
Existing version of the airplane, approved by calculations and tests, cover installation of engines Rotax 912ULS with optional equipment.
All versions are calculated and tested for MTOW 600kg, but this specific Flight manual has defined limits, valid for UL category in Czech Republic under LAA CZ.
Marking of a specific airplane version is defined in introduction of this flight manual. Deviations from the basic version are described in the following box:
Page 1-3
Flight manual UL aircraft
1.5. THREE VIEW DRAWING
Strana 2-1
Flight manual UL aircraft
2. LIMITATIONS
All speeds shown in this manual are indicated speeds. The conversion table in chapter 5.1. can be used to get the real speeds.
2.1. AIRSPEED
Speed
IAS
km/h
CAS
km/h
VNE
Never exceed speed
327
333
VRA
Maximal speed in hard turbulence
249
250
VA
Maneuvering speed
175
170
VFE
Maximum speed with open flaps
143
140
WARNING: Above Maneuvering speed use only small deflections
of control surfaces - the airplane may be easily overloaded!
2.2. AIRSPEED INDICATOR MARKINGS
EFIS/EMS Dynon SkyView
NEVER EXCEED
SPEED:
327 - km/h
CAUTION RANGE:
249 - 327 km/h
NORMAL
OPERATION RANGE:
105 - 249 km/h
FLAPS OPERATING
RANGE:
50 - 143 km/h
Page 2-2
Flight manual UL aircraft
2.3. ANALOG AIRSPEED INDICATOR MARKINGS
CAUTION:
All speeds in this manual are determined by primary airspeed
indicator displayed on EFIS (Dynon SkyView, FLYMAP). Analog
airspeed indicator, used as emergency one, may indicate slightly
different speeds – see item 5.1.
NORMAL
OPERATION
RANGE:
105 - 249
km/h
CAUTION
RANGE:
249 - 327
km/h
FLAPS
OPERATING
RANGE:
50 - 143
km/h
NEVER EXCEED
SPEED:
327m/h
Page 2-3
Flight manual UL aircraft
2.4. ENGINE
SHARK is powered by 100HP ROTAX 912 ULS engine.
Airplane
Engine type
SHARK
ROTAX 912 ULS
Max. take-off power (kW)
73,5
Max. continuous power (kW)
69
Max. engine speed (5 min)
5 800 ot/min
Max. engine speed (continuous)
5 500 ot/min
Max. cylinder head temperature (°C)
150
Max. oil temperature (°C)
140
Oil pressure - minimum (bar)
0,8 below 3500 rpm
2,0 above 3500 rpm
Oil pressure: maximum, cold start only (bar)
7
Oil pressure: normal operation (bar)
2,0 – 5,0
Fuel pressure: min-max (bar)
0,15 – 0,4
Operation range of outside temperature
-25°C
+ 50°C
For more details see Operator’s Manual for all versions of Rotax 912
supplied with the engine.
WARNING:
Flying this aircraft must always be done with the possibility of a
safe landing due to loss of engine power.
The pilot is fully responsible for consequences of such failure
Page 2-4
Flight manual UL aircraft
2.5. ENGINE INSTRUMENT MARKING
The airplane is equipped with the integrated engine display. Values can be displayed in the integrated EFIS/EMS (Dynon SkyView, FLYMAP, GARMIN ...), on separate EMS unit (MiniEIS, EMSIS, VIGILUS ...) or on conventional imaging devices.
An example of FLYMAP engine operating variables:
Warning limits of Indicator Unit:
912 ULS
TACH - Max. RPM [1/min]
5800
EGT - Exhaust gas temperature [ºC]
860
CHT - Cylinder head temperature [ºC]
150
OIL - Oil temperature [ºC]
140
- Oil pressure, max [bar]
7
- Oil pressure, min [bar]
0,8
- Oil pressure, normal [bar]
2 – 5
ERT - Engine room temperature [ºC]
70
TFUEL - Fuel temperature [ºC]
70
normal values are displayed in green color  values with higher attention are displayed in yellow
critical values are displayed in red
Page 2-5
Flight manual UL aircraft
2.6. WEIGHT LIMITS
Empty weight: standard version (kg)
290 kg
Empty weight: fully equiped (kg)
320 kg (max 325 kg)
Max. take-off weight: NO Ballistic Recovery System installed (kg)
450 kg
Max. take-off weight: Ballistic Recovery System installed (kg)
472,5 kg
Max. crew weight:
calculated for max take-off weight (kg)
177 kg
Min. crew weight: (kg)
55 kg
Max. crew weight: rear seat (kg)
95 kg
Max. one pilot weight: (kg)
110 kg
Max. weight in baggage compartment (kg)
- for solo flight from front seat
25 kg
Max. weight in baggage compartment (kg)
10 kg
MAXIMAL CREW WEIGHT (kg)
depends on fuel and baggage quantity
Fuel tank filling
Fuel gauge indication
full
3/4
1/2
1/4
30 min
of flight
Fuel quantity in liters
100
75
50
25
5
kg
72
54
36
18
3,6
Baggage weight
Max: 10 kg
½ : 5 kg
Without baggage
Max. crew weight has to be written indelibly for specific measured weight of airplane.
WARNING:
Do not exceed these weight limits. Pay attention to fuel quantity,
especially when 2 persons are on board.
DO NOT EXCEED maximum take-off weight.
Page 2-6
Flight manual UL aircraft
2.7. CENTER OF GRAVITY (CG)
The values for ready to fly airplane (including fuel, crew, baggage).
Front center of gravity limit
16 % MAC
Rear center of gravity limit
34 % MAC
See Section 6 for center of gravity calculation. Retraction of landing gear moves CG 0,5-1% backwards.
2.8. APPROVED MANEUVERS
The Shark Airplane may perform:
- turns required for normal flying
- practicing falls
- steep turn (max. bank 60°)
WARNING:
All maneuvers must be performed with a positive overload
because the fuel and lubrication system is designed for positive
overloads. All maneuvers must be performed in a maneuver
envelope with maximum positive + 4g and negative -2g overload.
WARNING: Aerobatics, intentional stalls and spins are prohibited.
Maximum angle of bank: 60°
2.9. MANEUVERING LOAD FACTOR G
Flap up 0° Maximum positive center of gravity load factor
+ 4
Maximum negative center of gravity load factor
- 2
Flaps down Maximum positive center of gravity load factor
+ 2
Maximum negative center of gravity load factor
0
2.10. FLIGHT CREW
Minimum crew on board 1 pilot Maximum crew on board 2 persons
Page 2-7
Flight manual UL aircraft
2.11. KIND OF OPERATION
WARNING: Only VFR day flights are permitted.
WARNING:
IFR flights and flying in clouds is prohibited.
Flights in icing conditions are prohibited.
2.12. FUEL
2.12.1. Approved fuel types
Premium unleaded automtive fuel (Natural 95 in Czech - Standard spec.
for Automotive Spark-Ignition Engine Fuel, ASTM D 4814) or AVGAS 100
LL. NOTE: Due to the higher lead content in AVGAS, the wear of the valve
seats, the deposits in combustion chamber and lead sediments in the lubrication system will increase. Therefore, use AVGAS only if other fuel types are not available.
For more details see Operator’s Manual for all versions of Rotax 912
supplied with the engine.
2.12.2. Fuel tanks capacity
Fuel tank types
Standard
Long Range
Fuel tank capacity (each wing tank)
50 liters
75 liters
Total fuel capacity
100 liters
150 liters
Unusable fuel
1 liter
Page 2-8
Flight manual UL aircraft
2.13. OTHER LIMITATIONS
Max. crosswind component
16 knots
( 8 m/s )
Max. wind in runway direction
30 knots
( 15 m/s )
Maximum outside temperature
50° C
Minimum outside temperature
-25° C
Heavy rain or excessive moisture can cause mild decrease of airplane performance. During these poor conditions we recommend to increase take-off and landing speed approximately about 10 km/hour.
WARNING: No smoking on board!
Page 2-9
Flight manual UL aircraft
2.14. PLACARDS
Production label:
SHARK.AERO
SHARK UL 034/2017
… The serial number of the particular
airplane (total serial number / year of manufacture)
Registration label:
Matriculation:
Producer: SHARK Aero spol. s r.o.
Type/Name : SHARK
Production number/year:
Empty weight: kg
Max. take-off weight: 472,5 kg
Front and rear seat / luggage weight limit label:
Front seat limit
Rear seat limit
Luggages limit
solo
110 kg
0 kg
25 kg
2+lugg.
110 kg
kg
10 kg
2 max
110 kg
kg
0 kg
Basic information placards:
This product is not subject of
the Czech Civil Aviation Authority approval
and is operated at the user's own risk.
AEROBATICS MANEUVERS AND
INTENTIONAL SPINS ARE PROHIBITED
Page 2-10
Flight manual UL aircraft
Basic LAA CZ label:
OPERATION INFORMATIONS AND LIMITS - speeds IAS
Matriculation
Empty weight
kg
Max. take-off weight
kg
Max. payload
kg
Max. baggage weight for 1 pers. / 2. pers.
25 / 10
kg
Min / Max. pilot weight
55 / 110
kg
Max. passanger weigh (rear seat)
95
kg
Stalling speed with flaps VSO
50
km/hour
Max. speed with not-retracted undercarriage V
LO
150
km/hour
Maximum flap extended speed V
FE
143
km/hour
Max maneuvering speed V
A
175
km/hour
Max speed in hard turbulency V
RA
249
km/hour
Never exceed speed V
NE
327
km/hour
MAXIMAL CREW WEIGHT (kg)
DEPEND ON FUEL AND BAGGAGE QUANTITY
Fuel tank
filling
Fuel gauge indication
full
3/4
1/2
1/4
30min
of flight
Fuel quantity in liters
100
75
50
25
5
Baggage
weight
Max: 10 kg
½ : 5 kg
Without baggage
Engine limit information:
ENGINE SPEED
Max. take-off (max 5min) 5 800 rpm
Max. continuous 5 500 rpm
Idling 1 400 rpm
Page 2-11
Flight manual UL aircraft
FUEL TANK VOLUME. LIMIT - standard FUEL TANK VOLUME LIMIT - LongRange
BAGGAGE WEIGHT LIMIT
TYRES PRESSURE
- on the wing, walk-around area for access to
cockpit
- on the aerodynamic control surfaces
Rescue system info - on the tail / small on the Rescue System cover
tyre 300 kPa
Baggage
max. / solo
flight
10 / 25 kg
50 liters
Natural 95
min. MON 85 RON 95
75 liters
Natural 95
min. MON 85 RON 95
Page 3-1
Flight manual UL aircraft
3. EMERGENCY PROCEDURES
This section provides checklist of emergency situations which may occur. Emergency situations caused by airplane or engine malfunction are extremely rare with proper preflight inspections and maintenance. However, an emergency situation may occur. The guidelines, described in this section, should be applied to solve the problems. All air speed values in this chapter are presented in km/h - Indicated Airspeed.
3.1. ENGINE FAILURE AND EMERGENCY LANDING
3.1.1. Engine failure during take-off run
- throttle reduce to idle
- ignition off
- master switch off
- brakes as required
3.1.2. Engine failure during take-off
- airspeed - 120 km/h
- landing site - below 150 ft - land straight ahead
- above 150 ft - choose suitable landing area in the runway direction or nearest suitable site clear of obstacles.
- master switch off
- ignition off
- fuel tank valve shut
- fuel pump off
- flaps extend as needed
- undercarriage extended / check
- safety belts tighten
after touchdown:
- brakes as required
Page 3-2
Flight manual UL aircraft
3.1.3. In-flight engine failure
- airspeed 120 km/h
- trim trim
- landing site selection select
Check situation, if master switch and ignition are on and fuel valve is open, continue according to procedure 3.2. (in-flight engine start) or by emergency landing according to procedure 3.1.2 (if the engine cannot be started up).
3.1.4. Carburettor icing
- airspeed 140 km/h (optimal)
- throttle try to find RPM with smallest loss of power
- leave the icing area (if possible)
- after 1-2 minutes increase slowly engine power to cruise speed
- when engine power is not recovered, land on the nearest airfield or off-airfield following the procedure described in Chyba! Nenašiel sa žiaden zdroj odkazov.
3.2. IN-FLIGHT ENGINE RESTART
- airspeed 120 km/h
- master switch on
- fuel tank valve open tank with more fuel (check)
- choke closed (as the engine is warm)
- fuel pump on
- throttle idle (when choke is activated), 1/3 of travel otherwise.
- ignition on
- starter start up
- if the engine cannot be started up (not enough power from battery), increase the airspeed to 150-170 km/h to rotate the propeller to support the engine starting.
WARNING: Loss of height needed for in-flight engine starting is
approximately 600 ft.
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