PILOT'S OPERATING HANDBOOK
EVEKTOR EV-97 Eurostar SL · Pilot's Operating Handbook
Overview
The Pilot's Operating Handbook for the EV-97 Eurostar SL provides essential information for the safe and efficient operation of this ultra-light aeroplane. It includes details on limitations, emergency procedures, normal procedures, performance, and weight and balance.
- The EV-97 Eurostar SL is a low-wing monoplane designed for recreational flying.
- It features a fixed tricycle undercarriage and can seat two passengers side by side.
- The standard engine is the ROTAX 912UL with 80 hp, with an option for ROTAX 912ULS at 100 hp.
- The aircraft has a maximum take-off weight limit that must be adhered to.
- The handbook must be available onboard the aircraft at all times.
- The aircraft is certified for non-aerobatic operations only.
- Airspeed limitations include a never exceed speed (VNE) of 270 km/h.
- The aircraft is constructed from metal-composite materials.
Document
Source
Originally published by gardaeagle.it. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Pilot's Operating Handbook
- Year ·
- 2008
- File size ·
- 3.2 MB
- Publisher ·
- gardaeagle.it
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Wing span m ·
- 8.1
- Wing area m2 ·
- 9.84
- Fuselage width m ·
- 1.08
- Fuselage height m ·
- 2.47
- Fuselage length m ·
- 5.98
- Horizontal tail span m ·
- 2.5
- Main wheel diameter mm ·
- 350
- Nose wheel diameter mm ·
- 350
- Vertical tail height m ·
- 1.28
Performance
- Max speed kmh ·
- 270
- Stall speed kmh ·
- 58
- Cruise speed kmh ·
- 160
V-speeds
- VA_KIAS ·
- 86
- VFE_KIAS ·
- 67
- VNE_KIAS ·
- 146
- VNO_KIAS ·
- 103
What is the PILOT'S OPERATING HANDBOOK?
The PILOT'S OPERATING HANDBOOK is a pilot's operating handbook for the EVEKTOR EV-97 Eurostar SL, dated 2008.
Where does the PILOT'S OPERATING HANDBOOK come from?
This copy of the PILOT'S OPERATING HANDBOOK was originally published by gardaeagle.it and is hosted on Sprinkle as a free, searchable reference copy.
What year was the PILOT'S OPERATING HANDBOOK published?
The PILOT'S OPERATING HANDBOOK — the EVEKTOR EV-97 Eurostar SL pilot's operating handbook on file — is dated 2008.
Most owners only have the POH. Here's the essential set for the EVEKTOR EV-97 Eurostar SL.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
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In this document
General
This section introduces the handbook and outlines the certification basis and descriptive data of the aircraft.
Limitations
This section details the operational limitations, including airspeed, weight, and center of gravity.
Emergency Procedures
This section provides guidelines for handling emergency situations during flight.
Normal Procedures
This section outlines standard operating procedures for the aircraft.
Performance
This section includes performance data relevant to the aircraft's operation.
Weight and Balance
This section discusses the weight limits and balance considerations for safe operation.
Safety notes
- Do not exceed the VNE speed of 270 km/h in any operation.
- Avoid full or abrupt control movements above the manoeuvring speed (VA) of 160 km/h.
- Do not exceed the maximum structural cruising speed (VNO) of 190 km/h except in smooth air.
- Do not exceed the maximum flap extending speed (VFE) of 125 km/h with flaps extended.
Full document text
EVEKTOR ñ AEROTECHNIK a.s. Letecka 1384 686 04 Kunovice CZECH REPUBLIC tel.: +420 572 537 111 fax: +420 572 537 900 marketing@evektor.cz www.evektor.cz PILOT'S OPERATING HANDBOOK EV-97 Eurostar SL i Document No.: EV97SLLPEN Date of Issue: 02/2008 Revision: EVEKTOR ñ AEROTECHNIK a.s. Letecka 1384 686 04 Kunovice Czech Republic tel.: +420 572 537 111 fax: +420 572 537 900 PILOTíS OPERATING HANDBOOK FOR ULTRA-LIGHT AEROPLANE Model: EV-97 Eurostar SL Registration: ......................... Serial No.: ......................... Approved by: Signature: .............................. Authority: .............................. Stamp: Date of approval: ...................... This English edition of the EV-97 Eurostar SL Pilotís operating handbook has been translated with care and is accurate to best of our knowledge. However, in all official matters the original Czech text is the authoritative and definite document. This aeroplane must be operated in compliance with information and limitations contained herein. This Pilotís operating handbook must be available onboard the aeroplane. PILOTíS OPERATING HANDBOOK ii Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 0.1 Record of revisions Any revision of the present manual, except actual weighing 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 left hand margin, and the Revision No. The date will be shown on the left hand bottom of the page. Rev. No. Affected Section Affected Pages Date Approval Date Date Inserted Signature 0 ii, iii, iv 4 4-3 7 7-6 1 Valid from S/N 20093511 01/2009 01/2009 Manufact. 0 ii, iii 2 4 4-2, 4-3, 4-4 2/2010 02/2010 Manufact. 0 ii, iii, iv 1 1-1 2 2-3, 2-4 3 7 7-8, 7-9, 7-10, 7-11, 7-12 3/2011 03/2011 Manufact. 03/2011 3 PILOTíS OPERATING HANDBOOK iii Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 0.2 List of Effective Pages Section Page Date Section Page Date 2 2-0 02/2008 i 02/2008 2-1 02/2008 ii 03/2011 2-2 02/2008 iii 03/2011 2-3 03/2011 iv 03/2011 2-4 03/2011 v 02/2008 2-5 02/2008 2-6 02/2008 2-7 02/2008 1 1-0 02/2008 2-8 02/2008 1-1 03/2011 2-9 02/2008 1-2 02/2008 2-10 02/2008 1-3 02/2008 2-11 02/2008 1-4 02/2008 2-12 02/2008 1-5 02/2008 3 3-0 02/2008 3-1 02/2008 3-2 02/2008 3-3 02/2008 3-4 02/2008 3-5 02/2008 3-6 02/2008 3-7 02/2008 3-8 02/2008 3 03/2011 PILOTíS OPERATING HANDBOOK iv Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN Section Page Date Section Page Date 4 4-0 02/2008 6 6-0 02/2008 4-1 02/2008 6-1 02/2008 4-2 02/2010 6-2 02/2008 4-3 02/2010 4-4 02/2010 7 7-0 02/2008 4-5 02/2008 7-1 02/2008 4-6 02/2008 7-2 02/2008 4-7 02/2008 7-3 02/2008 4-8 02/2008 7-4 02/2008 4-9 02/2008 7-5 02/2008 4-10 02/2008 7-6 01/2009 4-11 02/2008 7-7 02/2008 7-8 03/2011 5 5-0 02/2008 7-9 03/2011 5-1 02/2008 7-10 03/2011 5-2 02/2008 7-11 03/2011 5-3 02/2008 7-12 03/2011 5-4 02/2008 8 8-0 02/2008 5-5 02/2008 8-1 02/2008 5-6 02/2008 8-2 02/2008 5-7 02/2008 8-3 02/2008 5-8 02/2008 8-4 02/2008 5-10 02/2008 8-5 02/2008 9 9-0 02/2008 9-1 02/2008 9-2 02/2008 03/2011 3 PILOTíS OPERATING HANDBOOK v Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 0.3 Table of Contents Section General .........................................................................................1 (a non-approved section) Limitations ...................................................................................2 (an approved section) Emergency procedures................................................................3 (an approved section) Normal procedures ......................................................................4 (an approved section) Performance.................................................................................5 (a partly approved section) Weight and balance / equipment list ...........................................6 (a non-approved section) Aircraft and systems description ................................................7 (a non-approved section) Aircraft handling, care and maintenance ...................................8 (a non-approved section) Supplements ................................................................................9 PILOTíS OPERATING HANDBOOK 1-0 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN SECTION 1 1. GENERAL 1.1 Introduction 1.2 Certification basis 1.3 Warnings, cautions and notes 1.4 Descriptive data 1.4.1 Aircraft description 1.4.2 Technical data 1.5 Three-view drawing PILOTíS OPERATING HANDBOOK 1-1 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 1.1 Introduction The aeroplane Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of the EV-97 Eurostar SL ultra-light aeroplane. It also contains supplemental data supplied by the aeroplane manufacturer. 1.2 Certification basis This aircraft type has been approved by the responsible airworthiness authorities listed below: CZECH REPUBLIC Type Certificate No.: ULL ñ 03/98/îdî 00 Date of approval: 2.10.2008 Approved by: Light Aircraft Association of Czech Republic Certificate of Airworthiness: ìPî 03/2011 3 PILOTíS OPERATING HANDBOOK 1-2 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 1.3 Warnings, cautions and notes The following definitions apply to warnings, cautions and notes 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 possible long term degradation of the flight safety. NOTE
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Draws attention to any special item not directly related to safety, but which is important or unusual. PILOTíS OPERATING HANDBOOK 1-3 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 1.4 Descriptive data 1.4.1 Aircraft description EV-97 Eurostar SL is an aircraft intended especially for recreational and touring flying, with a limitation to non-aerobatic operation. The EV-97 Eurostar SL is a single engine, metal-composite, low-wing monoplane of semimonocoque construction with two side-by side seats. The aeroplane is equipped with a fixed tricycle undercarriage with a controllable nose wheel. The powerplant is composed of the ROTAX 912UL (80 hp), four cylinder, four stroke engine and the three blade Klassic 170/3/R, fixed composite propeller (standard powerplant). Alternatively it is possible to upgrade the engine to the ROTAX 912ULS (100 hp) and other propellers according to consumerís request. PILOTíS OPERATING HANDBOOK 1-4 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 1.4.2 Technical data Wing span ...........................................8.1 m 26.57 ft area ............................................9.84 m2 105.92 ft2 MAC ...........................................1.25 m 4.10 ft loading ..................................... 45.7 kg/m2 9.37 lb/ft2 Aileron area .................................0.21 m2 2.26 ft2 Flap area .................................0.52 m2 5.60 ft2 Fuselage length..........................................5.98 m 19.62 ft width...........................................1.08 m 3.55 ft height..........................................2.47 m 8,12 ft Horizontal tail unit span ...........................................2.5 m 8.20 ft area ............................................1.95 m2 20.99 ft2 elevator area...............................0.8 m2 8.60 ft2 Vertical tail unit height..........................................1.28 m 4.21 ft area ............................................1.02 m2 10.93 ft2 rudder area .................................0.43 m2 4.67 ft2 Landing gear wheel track..................................1.6 m 5.25 ft wheel base..................................1.35 m 4.42 ft main wheel diameter ................. 350 mm 14 in nose wheel diameter ..................350 mm 14 in PILOTíS OPERATING HANDBOOK 1-5 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 1.5 Three-view drawing PILOTíS OPERATING HANDBOOK 2-0 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN SECTION 2 2. LIMITATIONS 2.1 Introduction 2.2 Airspeed 2.3 Airspeed indicator markings 2.4 Powerplant 2.5 Powerplant instrument markings 2.6 Miscellaneous instrument markings 2.7 Weight 2.8 Centre of gravity 2.9 Approved manoeuvres 2.10 Manoeuvring load factors 2.11 Crew 2.12 Kinds of operation 2.13 Fuel 2.14 Maximum passenger seating 2.15 Other limitations 2.16 Limitation placards PILOTíS OPERATING HANDBOOK 2-1 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.1 Introduction Section 2 includes operating limitations, instrument markings and basic placards necessary for the safe operation of the aircraft, its engine, standard systems and standard equipment. 2.2 Airspeed Airspeed limitations and their operational significance are shown below: IAS Speed [km/h] [kts] Remarks VNE Never exceed speed 270 146 Do not exceed this speed in any operation. VA Manoeuvring speed 160 86 Do not make full or abrupt control movement above this speed, because under certain conditions the aircraft may be overstressed by full control movement. VNO Maximum structural cruising speed 190 103 Do not exceed this speed except in smooth air, and then only with caution. VFE Maximum Flap. Extending speed 125 67 Do not exceed this speed with flaps extended. PILOTíS OPERATING HANDBOOK 2-2 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.3 Airspeed indicator markings Airspeed indicator markings and their colour-code significance are shown below: IAS value or range Marking [km/h] [kts] Significance White arc 58-125 31-67 Positive Flap Operating Range. Green arc 75-190 40-103 Normal Operating Range. Yellow arc 190-270 103-146 Manoeuvres must be conducted with caution and only in smooth air. 270 146 Maximum speed for all operations. Red line 58 31 Stall speed in landing configuration (max. extended flaps, engine on idle) PILOTíS OPERATING HANDBOOK 2-3 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.4 Powerplant ROTAX 912 engine is installed in the aircraft of S/N Engine Model: ROTAX 912UL ROTAX 912ULS Engine Manufacturer: Bombardier-Rotax GMBH Max Take-off: 59.6 kW / 80 hp at 5800 rpm, max.5 min. 73.5 kW / 100 hp at 5800 rpm, max.5 min. Max. Continuous: 58 kW / 78 hp at 5500 rpm 69 kW / 93.8 hp at 5500 rpm Power Cruising: 37.7 kW / 50.6 hp at 4800 rpm 44.6 kW / 59.8 hp at 4800 rpm Max. Take-off: Max. Continuous: Cruising: Engine speed Idling: 5800 rpm, max. 5 min. 5500 rpm 4800 rpm ~1400 rpm Minimum: 60 ∞C 140 ∞F 60 ∞C 140 ∞F Cylinder head temperature: Maximum: 150 ∞C 302 ∞F (Evans coolant) 128 ∞C 262 ∞F (Glycol coolant) 135 ∞C 275 ∞F (Evans coolant) 128 ∞C 262 ∞F (Glycol coolant) Minimum: 50 ∞C 122 ∞F 50 ∞C 122 ∞F Maximum: 140 ∞C 284 ∞F 130 ∞C 266 ∞F Oil temperature Optimum: 90 ∞C - 110 ∞C 194 - 230∞F 90 ∞C - 110 ∞C 194 - 230∞F Maximum: 7,0 bar Minimum: 1.5 bar 0.8 bar Oil pressure: Optimum: 1.5-5.0 bar 2.0-5.0 bar Fuel: see 2.13 Oil: Automotive engine oil of registered brand with gear additives, but not aircraft oil (refer to engine Operator¥s Manual). API classification ÑSFì or ÑSGì. Standard Propeller and Manufacturer V 230C VZL⁄ Praha, Czech Republic Type: two blade fixed wooden propeller Propeller diameter: 1625 +2-3 mm 63.98+0.008 -0.01 in Propeller pitch: 18∞20¥ - 18∞55¥ WARNING The Rotax 912 UL has not been certified as an aircraft engine and its failure may occur at any time. The pilot is fully responsible for consequences of such a failure. 2.5 03/2011 3 PILOTíS OPERATING HANDBOOK 2-4 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN Powerplant instrument markings The analogous powerplant instruments are installed in the EV-97 aeroplane model SL version R, with following colour marking Function Minimum Limit (red line) Normal Operating (green arc) Caution Range (yellow arc) Maximum Range (red line) Engine speed (RPM) - 1400-5500 5500-5800 5800 R 912 UL 150 ∞C (Evans coolant) 128 ∞C (glycol coolant) Cylinder Head Tempe- rature (CHT) R 912ULS - - - 135 ∞C (Evans coolant) 128 ∞C (glycol coolant) R 912 UL 50-90 ∞C 110-140 ∞C 140 ∞C Oil Tempe- rature R 912ULS - 50-90 ∞C 110-130 ∞C 130 ∞C R 912 UL 1.5 bar 1.5 - 5.0 bar 5.0 - 7.0 bar Oil Pressu- re R 912ULS 0.8 bar 2.0 - 5.0 bar 0.8 ñ 2.0 bar 5.0 - 7.0 bar 7.0 bar cold engine starting NOTE The CHT limit with glycol coolant is 128 ∞C in order to not exceed coolant exit temperature limit 120 ∞C (Operators Manual for ROTAX Engine Type 912 Series ñ Part no. 899374).This limitation is based on Aircraft Manufacturer tests. 03/2011 3 PILOTíS OPERATING HANDBOOK 2-5 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.6 Miscellaneous instrument markings Unused PILOTíS OPERATING HANDBOOK 2-6 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.7 Weight Empty weight (standard equipment) ........ 275 kg ± 3 % 606 lbs ± 3 % NOTE Actual empty weight is stated in SECTION 6, par. 6.2 Max. take-off weight ...................................450 kg 992 lbs Max landing weight.....................................450 kg 992 lbs Max. weight of fuel ...................................... 47 kg 104 lbs Max.baggage weight.................................... 15 kg 33 lbs 2.8 Centre of gravity Empty aircraft C.G. position (standard).....18±2 % MAC Operating C.G. range ............................. 20-34 % MAC 2.9 Approved manoeuvres Aeroplane Category: Normal The EV-97 Eurostar SL aeroplane is approved for normal and below listed manoeuvres: ! Steep turns not exceeding 60∞ bank ! Lazy eights ! Chandelles ! Stalls (except whip stalls) WARNING Aerobatics and intentional spins are prohibited ! PILOTíS OPERATING HANDBOOK 2-7 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.10 Manoeuvring load factors PILOTíS OPERATING HANDBOOK 2-8 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.11 Crew Minimum crew.................................................. 2 Minimum crew weight......................................55 kg 121 lb Maximum crew weight .............................see 6.2 WARNING Abide with max. take-off weight 450 kg (992 lb)! 2.12 Kinds of operation There are permitted day VFR flights only. WARNING IFR flights and flights under icing conditions are PROHIBITED! Instruments and equipment for VFR flights: 1 Airspeed indicator (marked according to 2.3) 1 Altimeter 1 Vertical speed indicator 1 Magnetic compass 1 Bank indicator 2 Safety harnesses PILOTíS OPERATING HANDBOOK 2-9 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.13 Fuel ! automotive petrol with min RON 95 ! EN 228 Premium ! EN 228 Premium plus ! AVGAS 100 LL Due to higher lead content in AVGAS, the wear of valve seats and deposits in the combustion chamber and lead sediments in the lubrication system will increase. Therefore, use AVGAS only if you encouter problem with vapour lock or if the other fuel types are not available. NOTE Use only fuel suitable for the respective climatic zone. Risk of vapour formation if using winter fuel for summer operation. For other suitable fuel types refer to the engine Operator¥s Manual. Fuel tank volume...............................65 l 17.2 USgals Unusable fuel quantity .........................2.9 l 0.77 USgals 2.14 Maximum passenger seating Number of seats.................................................................2 PILOTíS OPERATING HANDBOOK 2-10 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.15 Other limitations No smoking onboard the aeroplane. PILOTíS OPERATING HANDBOOK 2-11 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 2.16 Limitation placards CAUTION The owner (aircraft operating agency) of this aeroplane is responsible for the readability of placards during the aircraft service life. or NOTE The values stated on the placard ìLOAD LIMITS,ì are valid for the empty weight of the aircraft with standard equipment installed. The placard with values valid for the actual empty weight of the aircraft will be placed in the cockpit. 5800 5500 1400 ENGINE SPEED Max. Take-off (max. 5 min.) Max. Continuous Idling 5800 5500 1400 rpm rpm rpm Aerobatics and intentional spins are prohibited! AIRSPEED IAS Never exceed Manoeuvring Max. Flap Extended Stalling 270 km/h 160 km/h 125 km/h 58 km/h Unusable quantity of fuel 2.9 Litre This ultra-light aeroplane has been approved only for VFR day flights under no icing conditions. 5800 5500 1400 ENGINE SPEED Max. Take-off (max. 5 min.) Max. Continuous Idling 5800 5500 1400 rpm rpm rpm Aerobatics and intentional spins are prohibited! AIRSPEED IAS Never exceed Manoeuvring Max. Flap Extended Stalling 146 kts 86 kts 67 kts 31 kts Unusable quantity of fuel 0.77 USgal This ultra-light aeroplane has been approved only for VFR day flights under no icing conditions. or LOAD LIMITS Max.take-off weight 992 lbs Empty weight 606 lbs Max.baggage weight 33 lbs PERMITTED CREW WEIGHT [lbs] Fuel gauge 1 1 3/4 1/2 1/4 Fuel quantity US gals. 17.2 12.9 10.8 7.4 4.8 max. 33 lbs 250 275 288 309 324 1/2 17 lbs 266 291 304 325 340 No baggage 283 308 321 342 357 Fuel reserve (yellow warning lamp) 2.9 US gals Baggage weight Fuelling Max.take-off weight 450 kg Empty weight (without paint) 273 kg Max.baggage weight 15 kg PERMITTED CREW WEIGHT [kg] Fuel gauge 1 1 3/4 1/2 1/4 Fuel quantity ltr. 65 52 39 29 16 max. 15 kg 115 125 134 141 150 1/2 8 kg 122 132 141 148 157 No baggage 130 140 149 156 165 Fuel reserve (yellow warning lamp) 12 liters Baggage weight Fuelling PILOTíS OPERATING HANDBOOK 2-12 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN PILOTíS OPERATING HANDBOOK 3-0 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN SECTION 3 3. EMERGENCY PROCEDURES 3.1 Introduction 3.2 Engine failure 3.2.1 Engine failure during take-off run 3.2.2 Engine failure during take-off 3.2.3 Engine failure in flight 3.3 In-Flight start 3.4 Smoke and fire 3.4.1 Fire on ground 3.4.2 Fire during take-off 3.4.3 Fire in flight 3.5 Glide 3.6 Landing emergencies 3.6.1 Emergency landing 3.6.2 Precautionary landing 3.6.3 Landing with a flat tire 3.6.4 Landing with a defective landing gear 3.7 Recovery from unintentional spin 3.8 Other emergencies 3.8.1 Vibration 3.8.2 Carburettor icing PILOTíS OPERATING HANDBOOK 3-1 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.1 Introduction Section 3 provides checklists and amplified procedures for coping with various emergencies that may occur. Emergencies caused by aircraft 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 during take-off run 1. Throttle - decrease to idling 2. Ignition - switch off 3. Brake 3.2.2 Engine failure during take-off 1. Speed - gliding at 110 km/h (60 kts) 2. Altitude - below 50 m (160 ft): land in take-off direction - over 50 m (160 ft): choose landing area 3. Wind - find direction and velocity 4. Landing area - choose free area without obstacles 5. Flaps - extend as needed 6. Fuel cock - shut off 7. Ignition - switch off 8. Propeller - set to the horizontal position by means of starter (for the two blade propeller) 9. Safety harness - tighten 10. Master switch - switch off before landing 11. Land NOTE Skip 6-10 if necessary. PILOTíS OPERATING HANDBOOK 3-2 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.2.3 Engine failure in flight 1. Speed - gliding at 110 km/h (60 kts) 2. Altitude - below 50 m (160 ft): land in flight direction - over 50 m (160 ft): choose landing area 3. Wind - evaluate direction and velocity 4. Landing area - choose free area without obstacles 5. Flaps - extend if necessary 6. Fuel cock - shut off 7. Ignition - switch off 8. Propeller - set to the horizontal position by means of starter (for the two blade propeller) 9. Safety harness - tighten 10. Master switch - switch off before landing 11. Land PILOTíS OPERATING HANDBOOK 3-3 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.3 In-Flight start 1. Speed - gliding at 110 km/h (60 kts, 68 mph) 2. Altitude - check 3. Landing area - choose according to altitude 4. Master switch - switch on 5. Fuel cock - open 6. Electric fuel pump (if installed) - switch on 7. Choke - as necessary (for cold engine) 8. Throttle - for 1/3 power 9. Ignition box - switch to BOTH and activate starter If the engine cannot be started, increase the flight speed to 200 km/h (110 kts, 124 mph) so that air flow can rotate the propeller, thus enabling the engine to start. WARNING The loss of altitude during in-flight engine starting is about 400 m (1300 ft) and must be taken into consideration. 3.4 Smoke and fire 3.4.1 Fire on ground 1. Fuel cock - shut off 2. Throttle - full 3. HOT AIR knob (if installed) - push 4. Master switch - switch off 5. Ignition - switch off 6. Abandon the aeroplane 7. Extinguish fire if it is in your power or call for a fire-brigade. PILOTíS OPERATING HANDBOOK 3-4 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.4.2 Fire during take-off 1. Fuel cock - shut off 2. Throttle - full 3. HOT AIR knob (if installed) - push 4. Speed - 100-110 km/h (54-60 kts) 5. Master switch - switch off 6. Ignition - switch off 7. Land and brake 8. Abandon the aeroplane 9. Extinguish fire if it is in your power or call for a fire-brigade 3.4.3 Fire in flight 1. Fuel cock - shut off 2. Throttle - full 3. HOT AIR knob (if installed) - push 4. Master switch - switch off 5. Ignition - switch off after using up fuel in carburettors and engine stopping 6. Choose of area - heading to the nearest airport or choose emergency landing area 7. Emerg. landing - perform according to par. 3.6.1 8. Abandon the aeroplane 9. Extinguish fire if it is in your power or call for a fire-brigade. NOTE Estimated time to pump fuel out of carburettors is 30 seconds. PILOTíS OPERATING HANDBOOK 3-5 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.5 Glide An example of the use of gliding is in the case of engine failure. 1. Speed - ~110 km/h (60 kts) 2. Flaps - retracted 3. Instruments - within permitted limits 3.6 Landing emergencies 3.6.1 Emergency landing 1. Emergency landings are generally carried out in the case of engine failure and the engine cannot be re-started. 2. Speed - 110 km/h (60 kts) 3. Trim - trim the aeroplane 4. Safety harness - tighten 5. Flaps - as needed 6. Radio station - report your location if it is possible 7. Fuel cock - shut off 8. Ignition - switch off 9. Master switch - switch off PILOTíS OPERATING HANDBOOK 3-6 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.6.2 Precautionary landing A precautionary landing is generally carried out in the cases where the pilot may be dissorientated, the aircraft has no fuel reserve or possibly in bad weather conditions. 1. Choose landing area, determine wind direction 2. Report your plan to land and land area location if a COMM is installed in the aeroplane 3. Perform low-altitude passage into wind over the right-hand side of the chosen area with flaps extended to the ìTAKE-OFFì position at a speed of 110 km/h (60 kts) to thoroughly inspect the area. 4. Perform flight around the chosen area 5. Perform an approach at increased idling with fully extended flaps 6. Reduce power to idle run when fly over the runway threshold and touch-down at the very beginning of the chosen area 7. After stopping the aeroplane switch off all switches, shut off the fuel cock, lock the aeroplane and look for help NOTE Watch the chosen area permanently during precautionary landing. 3.6.3 Landing with a flat tire 1. When floating at landing, keep the damaged wheel above ground as long as possible using the ailerons 2. Maintain the direction at landing run, applying foot control 3.6.4 Landing with a defective landing gear 1. If the main landing gear is damaged, perform touch-down at the Lowest speed possible and maintain direction at landing run, if possible 2. If the nose wheel is damaged perform touch-down at the Lowest speed possible and hold the nose wheel over a runway by means of the elevator control as long as it is possible PILOTíS OPERATING HANDBOOK 3-7 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.7 Recovery from unintentional spin WARNING Intentional spins are prohibited! The spin characteristics of this aircraft have not been tested. The procedure bellow is only for information. The aircraft has no tendency to spontaneously enter into an uncontrollable spin if normal piloting techniques are used. This standard procedure can be used to recover from an intentional spin: 1. Throttle - reduced to idle 2. Control stick - ailerons neutralised 3. Rudder pedals - full opposite rudder 4. Control stick - forward elevator control as required to stop a spinning 5. Rudder pedals - immediately after stop of a rotation neutralise the rudder 6. Recovery of the dive PILOTíS OPERATING HANDBOOK 3-8 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 3.8 Other emergencies 3.8.1 Vibration If any forced aircraft vibrations appear, it is necessary: 1. To set engine speed to such power rating where the vibrations are lowest. 2. To land on the nearest airfield or to perform a precautionary landing according to 3.6.2. 3.8.2 Carburettor icing Carburettor icing mostly occurs when entering into an area of ice formation. The carburettor icing shows itself through a decrease in engine power and an increase of engine temperatures. To recover the engine power, the following procedure is recommended: 1. Speed - 110 km/h (60 kts) 2. Throttle - set for 1/3 power 3. If possible, leave the icing area 4. Increase the engine power gradually to cruise conditions after 1-2 minutes If you fail to recover the engine power, land on the nearest airfield (if possible) or, depending on the circumstances, perform a precautionary landing according to 3.6.2. PILOTíS OPERATING HANDBOOK 4-0 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN SECTION 4 4. NORMAL PROCEDURES 4.1 Introduction 4.2 Assembly and disassembly 4.3 Pre-flight inspection 4.4 Normal procedures 4.4.1 Before entering cockpit 4.4.2 After entering cockpit 4.4.3 Before engine starting and Engine starting 4.4.4 Engine warm up, Engine check 4.4.5 Taxiing 4.4.6 Before take-off 4.4.7 Take-off 4.4.8 Climb 4.4.9 Cruise 4.4.10 Descent 4.4.11 Check before landing 4.4.12 On base leg 4.4.13 On final 4.4.14 Landing 4.4.15 Balked landing 4.4.16 After landing 4.4.17 Engine shutdown 4.4.18 Flight in rain PILOTíS OPERATING HANDBOOK 4-1 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 4.1 Introduction Section 4 provides checklists and amplified procedures for the conduct of normal operation. Normal procedures associated with optional systems can be found in section 9. 4.2 Assembly and disassembly For assembly and disassembly procedures refer to the Technical Description, Operating and Maintenance Manual for the Ultra-light Aeroplane EV-97 Eurostar SL. 4.3 Pre-flight inspection The pre-flight inspection performance is very important by reason that incomplete or careless performance could cause aircraft failure. The following pre-flight inspection procedure is recommended by the aircraft Manufacturer: PILOTíS OPERATING HANDBOOK 4-2 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN " Check if ignition is switched off in the cockpit 1. Wing ! Wing surface condition ! Leading edge condition ! Pitot tube condition ! Landing light condition (if installed) 2. Wing tip ! Surface condition ! Check of tips attachment ! Condition and attachment of position lights (if installed) 3. Aileron ! Surface condition ! Attachment ! Play ! Free movement 4. Flap ! Surface condition ! Attachment ! Play 5. Rear part of fuselage ! Surface condition ! condition of antennas (top and bottom fuselage surface) - if installed 6. Vertical tail unit ! Surface condition ! Play ! Free movement 7. Horizontal tail unit ! Surface condition ! Attachment ! Play ! Free movement ! Trim tab condition 8. see 5 9. see 4 10. see 3 11. see 2 12. see 1 02/2010 2 PILOTíS OPERATING HANDBOOK 4-3 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN 13. Landing gear ! Check of main and nose landing gear attachment ! Check cable control of controllable nose wheel (if it is installed) ! Condition of tires ! Condition and attachment of wheel spats 14. Engine Checks before the first flight of the day ñ it is necessary to remove upper engine cowling: ! Engine cowlings condition ! Check of engine intake space (on cowlings) ! Engine bed condition ! Fuel and Electric system visual check ! Water radiator hoses check ! Check on cooling liquid volume in the expansion tank on the engine body (replenish as required up to max. 2/3 of the expansion tank volume) ! Fuel system draining Checks before every flight ! Cleanness of air intakes ! Oil quantity check (between marks ñ flattenings on the dip stick) ! Check on cooling liquid level in the overflow bottle (volume should be approx. 0.2 litre) ! Engine attachment check ! Proper closing of the upper cowling ! Other checks according to engine manufacturer instructions CAUTION It is advisable to turn the propeller by hand with the ignition switched off in the case where the engine has been out of operation for a long time. Avoid excessive pressure on a blade tip and trailing edge. 15. Propeller ! Propeller attachment ! Blades, Hub, Spinner condition ! Other checks acc. to propeller manufacturer instructions 16. Cockpit ! Master switch - switched on ! Check canopy OPEN/CLOSE indication light (or a message on the EFIS display) function ! Ignition - switched off ! Master switch - switched off 2 02/2010 PILOTíS OPERATING HANDBOOK 4-4 Date of Issue: 02/2008 Revision: Document No.: EV97SLLPEN ! Instruments - check of condition ! Fuel gauge - fuel quantity check (for fuel quantity check switch on Switch box and Master switch, then switch off!) ! Controls - visual check - check for proper function - check of plays - check of flaps extension - check of free movement up to the stops ! Check for free items ! Check of safety belts condition and attachment ! Canopy - Condition of attachment, cleanliness 02/2010 02/2010 2