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Page 7-42

Initial issue

7.22

Emergency Parachute System

The  aircraft  is  equipped  with  the  emergency  parachute  system  MAGNUM  601  S-LSA.  The  emergency  parachute
system  (EPS)  is  intended  to  save  lives  of  occupants,  but  the  activation  of  the  system  will  most  likely  destroy  the
aircraft. In adverse circumstances, the activation may cause serious injury or death to the occupants. It is important to
read carefully the EPS system description in this chapter and Chapter 3 - EMERGENCY PROCEDURES.
The EPS consists of a parachute, extraction device (rocket), activation handle and harnesses that are attached to the
fuselage structure.
A textile container with a parachute is attached to the board behind the instrument panel. The parachute is connected
to  the  fuselage  structure  by  means  of  two  main  straps  and  one  stabilizing  strap.  The  main  straps  are  fixed  to  the
attachment points on the firewall. The stabilizing strap that consists of steel rope is imbedded in the fuselage shell and
attached  to  the  auxiliary  spar  of  the  fuselage.  When  the  parachute  deploys,  the  steel  rope  is  pulled  out  from  the
fuselage skin.

A weakened composite cover to enable rocket’s smooth egress and parachute extrac

tion closes the opening in the

fuselage.
The rocket is attached to the firewall and it is connected to an actuator installed in the center console accessible for
both pilot and co-pilot. The actuator is labelled

RESCUE SYSTEM

. The lock securing the actuator has to be removed

before flight. Even after the lock is removed, the actuator protector secures the actuator from unintentional activation
of rescue system (Fig. 7-33).
Before activation, if possible, minimize the flight speed. If time permits, stop the engine to prevent the straps from
getting to the propeller.
Activation of EPS is performed by opening the rescue system actuator protector (I.) and pulling the actuator (II.)
(Fig. 7-33). Pull the actuator straight backward with a strong, steady and continuous force until the rocket activates.
Up to 12 kg / 26.5 lb force or greater may be required to activate the rocket.

1.

RESCUE SYSTEM

actuator

2.

RESCUE SYSTEM

actuator protector

3.

Lock

-

-

Fig. 7-33

Activating of EPS

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Содержание WT9 Dynamic LSA / Club

Страница 1: ...on Number F HVXC THIS HANDBOOK INCLUDES THE INFORMATION REQUIRED TO BE FURNISHED TO THE PILOT BY REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY THE AIRCRAFT MANUFACTURER AEROSPOOL SPOL S R O PAGES...

Страница 2: ...This page is left blank intentionally...

Страница 3: ...and in the case of approved chapters 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 page margin and...

Страница 4: ...Page B Initial issue This page is left blank intentionally...

Страница 5: ...pproved 3 19 Initial issue 1 2 Initial issue EASA Approved 3 20 Initial issue 1 3 Initial issue EASA Approved 3 21 Initial issue 1 4 Initial issue EASA Approved 3 22 Initial issue 1 5 Initial issue EA...

Страница 6: ...7 12 Initial issue EASA Approved 5 10 Initial issue 7 13 Initial issue EASA Approved 5 11 Initial issue 7 14 Initial issue EASA Approved 5 12 Initial issue 7 15 Initial issue EASA Approved 5 13 Initi...

Страница 7: ...sue 8 3 Initial issue 8 4 Initial issue 8 5 Initial issue 8 6 Initial issue 8 7 Initial issue 8 8 Initial issue 8 9 Initial issue 8 10 Initial issue 8 11 Initial issue 8 12 Initial issue 8 13 Initial...

Страница 8: ...Page F Initial issue Chapter Page Date Chapter Page Date...

Страница 9: ...pter Chapter Name 0 INTRODUCTION 1 GENERAL INFORMATION 2 LIMITATIONS 3 EMERGENCY PROCEDURES 4 NORMAL PROCEDURES 5 PERFORMANCE 6 WEIGHT AND BALANCE AND EQUIPMENT LIST 7 DESCRIPTION OF AIRCRAFT AND SYST...

Страница 10: ...Page H Initial issue This page is left blank intentionally...

Страница 11: ...5 DATA LOCATION AND CONTACT INFORMATION FOR RECOVERY OF APPROVAL DOCUMENTATION 0 2 0 6 SYMBOLS ABBREVIATIONS AND TERMINOLOGY 0 3 Speed 0 3 Meteorological Terms 0 3 Power Plant 0 4 Flight Performance a...

Страница 12: ...ary 2013 0 3 Continued Airworthiness Technical publications for continued airworthiness are released on the Aerospool website www aerospool sk and they may be downloaded free of charge Rotax Aircraft...

Страница 13: ...l airspeed with the aircraft in landing configuration vX Best angle of climb airspeed vY Best rate of climb airspeed v50 Airspeed at height 15m 50 ft Meteorological Terms AGL Above Ground Level MSL Ab...

Страница 14: ...is generally presented as a specific distance from the reference datum Lever Arm The horizontal distance from the reference datum to the center of gravity of a component Moment The weight of a compon...

Страница 15: ...ay OEM Original Equipment Manufacturer company that controls the engineering and design rights for the LSA or an assembly subassembly accessory or part installed in the aircraft the consumable materia...

Страница 16: ...52 km Speed 1 km h 0 54 knots 1 knots 1 852 km h 1 m s 1 9425 knots 1 knots 0 5148 m s 1 m s 196 86 fpm 1 fpm 0 00508 m s Pressure 1 atm 1013 25 mbar 101325 Pa 29 92 inHg 1 inHg 0 03342 atm 33 865 mba...

Страница 17: ...ns 1 3 Engine 1 3 Propeller 1 3 Three View Drawing 1 4 Ground Turning Clearance 1 5 1 4 SUMMARY OF PERFORMANCE 1 6 Weights 1 6 Top and Cruise Speeds 1 6 1 4 2 1 Top Speeds at Sea Level 1 6 1 4 2 2 Cru...

Страница 18: ...mportant or unusual Procedures The procedures listed in this POH are formed into tables with three columns as shown in the example below Column A Column B Column C a Item 1 OFF b ITEM 2 As required c...

Страница 19: ...4 Engine manufacturer BRP Rotax GmbH Co KG Engine model number Rotax 912 ULS2 Engine type Horizontally opposed geared normally aspirated spark ignition Cooling Combined liquid and air Maximum takeoff...

Страница 20: ...Page 1 4 Initial issue Three View Drawing Fig 1 1 Three view drawing...

Страница 21: ...50 m 32 32 ft B Outside main gear radius 6 500 m 21 32 ft C Nose gear radius 5 380 m 17 65 ft D Inside main gear radius 4 260 m 13 98 ft CAUTION The data are valid for dry paved surface fully turned n...

Страница 22: ...20 0 kg 265 lb Maximum total baggage weight 2 x 20 0 kg 2 x 44 lb Top and Cruise Speeds 1 4 2 1 Top Speeds at Sea Level IAS KIAS Top speeds at sea level At 5800 rpm 240 130 At 5500 rpm 230 124 1 4 2 2...

Страница 23: ...39 1113 1070 nm 640 637 615 601 578 80 hh mm 5 31 5 09 4 39 4 19 3 45 km 948 944 911 890 856 nm 512 510 492 481 462 60 hh mm 4 08 3 52 3 29 3 14 2 49 km 711 708 683 668 642 nm 384 382 369 361 347 40 h...

Страница 24: ...gal 90 7 kg 200 lb Total usable fuel 119 0 l 31 44 U S gal 85 7 kg 189 lb Total unusable fuel 7 0 l 1 85 U S gal 5 0 kg 11 lb Maximum Engine Power Output Maximum takeoff power at 5800 rpm max 5 min 7...

Страница 25: ...POWER PLANT LIMITATIONS 2 5 Engine Limitations 2 5 Power Plant Instrument Markings 2 6 Taxi Power 2 6 2 4 WEIGHT LIMITS 2 7 2 5 CENTER OF GRAVITY LIMITS 2 7 2 6 APPROVED MANEUVERS 2 8 2 7 FLIGHT LOAD...

Страница 26: ...ASA Approved Initial issue 2 14 OTHER LIMITATIONS 2 13 Smoking 2 13 Dynon SkyView System Limitations 2 13 External Power Source and Battery 2 13 2 15 PLACARDS 2 14 Interior Placards 2 14 Exterior Plac...

Страница 27: ...ed permissible with flaps extended VFE 61 140 IAS 33 76 KIAS Green arc Normal operating range Lower limit is maximum weight stalling speed with flaps retracted VS Upper limit is maximum cruising speed...

Страница 28: ...essed by full control deflections 180 IAS 97 KIAS VO at minimum flying weight 140 IAS 76 KIAS Never Exceed Speed VNE VNE Do not exceed this airspeed in any operation 275 IAS 148 KIAS Rough Air Speed V...

Страница 29: ...rpm Idle 1400 rpm minimum Manifold pressure Maximum 29 5 inHg Coolant temperature Maximum 120 C Oil temperature Minimum 50 C Maximum 130 C Oil pressure Minimum 0 8 bar Maximum 7 0 bar Exhaust gas temp...

Страница 30: ...20 Oil temperature o C 50 90 110 50 90 110 130 130 Oil pressure bar 0 8 2 0 5 0 0 8 2 0 5 0 7 0 7 0 Exhaust gas temperature o C 200 880 880 Fuel pressure bar 0 15 0 15 0 50 0 50 Fuel flow meter l h 0...

Страница 31: ...MAC at 542 5 kg with straight line taper to 2 748 m 22 0 MAC at 600 0 kg 106 48 in 18 3 MAC at 1196 lb with straight line taper to 108 18 in 22 0 MAC at 1323 lb Rearward CG 2 824 m 28 5 MAC 111 18 in...

Страница 32: ...and intentional spins are prohibited 2 7 Flight Load Factor Limits Flaps Load Factor Flaps retracted FLAPS 0 0 4 2 Flaps extended FLAPS 1 15 FLAPS 2 24 FLAPS 3 35 2 0 Rotax 912 ULS2 limit is 0 5 for n...

Страница 33: ...G Fuelling must be done with respect to the allowed CG range and MTOW see Chapter 6 Use of unapproved fuel may result in damage of engine and fuel system and eventually can lead to the engine failure...

Страница 34: ...YPE 912 SERIES Doc No OM 912 and Rotax Service Instructions SI 912 016 latest edition Coolant Coolant capacity is approximately 2 5 l cooling system overflow bottle CAUTION Use only suitable conventio...

Страница 35: ...conditions are not allowed WARNING Flights in icing conditions are prohibited NOTE Cabin heating may be insufficient when the outside temperature is below zero and the engine loading is low 2 11 Kind...

Страница 36: ...must be operative Maximum airspeed 290 CAS 157 KCAS 303 IAS 164 KIAS Minimum height above terrain 660 ft 200 m WARNING The emergency parachute system must be operative otherwise the aircraft is not a...

Страница 37: ...hould be inspected and repaired as soon as practical Continuous operation of the aircraft with indications available only from backup instruments is not recommended 2 14 Other Limitations Smoking Smok...

Страница 38: ...unreadable it should be replaced List of all placards is given in the Aircraft Maintenance Manual AS AMM 10 000 Chapter 11 Interior Placards a Placards on the left part of instrument panel b Placards...

Страница 39: ...section wing flaps b Placards near fuel tank caps LH RH c Placard on the upper engine cowling near door for oil level check d Placards on the outer part of the main landing gear legs e Placard on the...

Страница 40: ...Initial issue h Placards near drain valves on the wing bottom part i Placards are located on the both sides of fuselage under the windows in baggage compartment j Placard is located on the emergency...

Страница 41: ...RT 3 6 3 6 SMOKE AND FIRE 3 7 Engine Fire on Ground 3 7 Engine Fire on Takeoff 3 7 Engine Fire in Flight 3 8 Cabin Fire on Ground 3 8 Cabin Fire on Takeoff and in Flight 3 9 3 7 EMERGENCY DESCENT 3 9...

Страница 42: ...OF FLIGHT CONTROLS 3 21 Aileron Control Failure 3 21 Elevator Control Failure 3 21 Rudder Control Failure 3 21 3 12 SPINS 3 22 Inadvertent spin 3 22 3 13 OTHER EMERGENCIES 3 23 Vibrations 3 23 Fuel Se...

Страница 43: ...aft control and do not stop flying Always proceed in this order aviate navigate and communicate Analyze the situation While you maintain control of the aircraft evaluate the situation Check the engine...

Страница 44: ...500 ft 150 m AGL If the engine failure occurs during takeoff at low height pitch the nose down to maintain airspeed Landing should be made straight ahead turning only to avoid obstructions a Airspeed...

Страница 45: ...ctuating manifold pressure rough or irregular engine running If the engine partial power loss permits a level flight land at a suitable airfield as soon as possible There is a procedure to correct som...

Страница 46: ...d k IGNITION ON both circuits l Starter key First OFF hold START after engine is started release to CHARGE As soon as engine runs m Engine parameters Check n AVIONICS ON o FUEL PUMP OFF Unsuccessful s...

Страница 47: ...xtinguish with best available means WARNING While exiting the aircraft make sure the exit path is clear of other aircraft spinning propellers and other hazards Engine Fire on Takeoff a FUEL PUMP OFF b...

Страница 48: ...ter 3 8 3 j Safety harness Release k Canopy OPEN if stuck break glass with best available means l Aircraft Exit immediately m Fire Try to extinguish with best available means CAUTION After the fire ha...

Страница 49: ...n accordance with 3 8 1 g Safety harness Release h Canopy OPEN if stuck break glass with best available means i Aircraft Exit immediately j Fire Try to extinguish with best available means WARNING Ope...

Страница 50: ...ACTIVATE if off airfield e Field check Check the preferred area for landing carefully to inspect the terrain properties obstructions surface conditions f Circle pattern At a safe altitude as permitte...

Страница 51: ...insufficient runway remaining i Taxiing Do not taxi j Engine Perform normal engine shutdown k Crew Seek assistance CAUTION During landing keep the damaged wheel off the ground as long as possible usin...

Страница 52: ...Set 7700 e ELT REMOTE CONTROL ACTIVATE if off airfield f Flaps FLAPS 3 extend gradually check locked g Airspeed 110 115 IAS 59 62 KIAS h FUEL PUMP OFF i Fuel selector OFF j IGNITION OFF both circuits...

Страница 53: ...r ACTIVATE according to Chapter 3 13 4 b Emergency call Transmit MAYDAY 121 5 MHz giving position and intentions c Transponder Set 7700 d ELT REMOTE CONTROL ACTIVATE e Aircraft Exit immediately f Life...

Страница 54: ...onitor e Oil pressure Monitor f Landing Perform at nearest airfield CAUTION Be prepared for engine failure and emergency landing without engine power according to Chapter 3 8 3 High Oil Pressure a THR...

Страница 55: ...irfield CAUTION Be prepared for engine failure and emergency landing without engine power according to Chapter 3 8 3 High Coolant Temperature a THROTTLE Reduce power to minimum required for flight If...

Страница 56: ...ase in the ammeter reading is noted d MASTER SWITCH OFF ON If no increase in the ammeter reading is noted e All unnecessary electrical equipment OFF f Voltmeter Monitor battery voltage g Landing Perfo...

Страница 57: ...unnecessary equipment Disconnect all external equipment from the power outlets Operating time of battery in good condition is up to 30 minutes Be aware if the AVIONICS switch is turned off the radio c...

Страница 58: ...such as an EMS module fails or a RED X may overlay a single widget if a single engine sensor fails or is not connected Red X on RH D1000 MFD page a RH D1000 circuit breaker Check pressed in if open re...

Страница 59: ...e for monitoring of the engine speed f Backup fuel pressure indicator Use for monitoring of the fuel pressure g OIL PRESS warning lamp Use for monitoring of the oil pressure illumination of warning la...

Страница 60: ...he horizontal tail the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effectiveness j Windshield Open left window and if practical scrape ice fr...

Страница 61: ...mental positions of flaps if required by holding the flaps lever in desired position If you cannot control the aircraft in the longitudinal direction d RESCUE SYSTEM actuator ACTIVATE according to Cha...

Страница 62: ...ans for preventing an inadvertent stall and spin entry is good airmanship monitoring of the airspeed and avoiding abrupt maneuvers at low speed and altitude WARNING Intentional spins are prohibited WA...

Страница 63: ...dance with 3 8 1 CAUTION Be prepared for engine failure and emergency landing without engine power according to Chapter 3 8 3 Unsecured Canopy If the Before takeoff checklist is not performed properly...

Страница 64: ...ld with one hand d Canopy handle Pull down for canopy latching and locking see Chapter 7 12 e Canopy latching and locking Check by canopy frame and red ring position f Sliding windows CLOSE WARNING Du...

Страница 65: ...eciding to deploy EPS a Impact area Determine flat terrain no trees or obstacles if possible b Airspeed Minimum if possible c IGNITION OFF both circuits if time and altitude permit d RESCUE SYSTEM act...

Страница 66: ...ted WARNING Minimum height for EPS activation is 660 ft 200 m AGL and maximum airspeed is 303 IAS 164 KIAS CAUTION Ground impact is expected to be equivalent to touchdown from a height of approximatel...

Страница 67: ...G 4 11 4 7 BEFORE TAXIING 4 13 4 8 TAXIING 4 13 4 9 BEFORE TAKEOFF 4 14 Ignition and Engine Ground Tests 4 14 Before Line Up 4 15 4 10 TAKEOFF 4 16 Normal and Short Field Takeoff 4 16 Soft Field Takeo...

Страница 68: ...nitial issue 4 18 ENVIRONMENTAL CONSIDERATION 4 23 Cold Weather Operation 4 23 Hot Weather Operation 4 23 4 19 OTHER NORMAL PROCEDURES 4 24 Stall 4 24 Sideslip 4 25 Crosswind Takeoff 4 26 Crosswind La...

Страница 69: ...he pitch control is released CAUTION The rudder does not return to neutral automatically when the yaw control is released NOTE The pitch trim range may be insufficient for the speeds less than 1 5 VS0...

Страница 70: ...ce before each flight WARNING If any problems are found they must be rectified before flying WARNING Remove the pitot probe cover before flight CAUTION Pay special attention to the parts which are aff...

Страница 71: ...of actuator attachment arming and locking service dates for expiration m Circuit breakers Pressed in n Brake Freedom of movement function set PARK o Wing flaps Freedom of movement set FLAPS 3 check l...

Страница 72: ...levator rudder attachment Secured f Elevator rudder sealing tapes All in place condition attachment 4 RIGHT FUSELAGE a Right wing walk Condition b Surface Condition 5 RIGHT WING TRAILING EDGE a Wing f...

Страница 73: ...hocks Remove 9 POWER PLANT a Propeller Condition check for nicks and damage attachment secured b Spinner Condition attachment c Air inlets Unobstructed d Oil cowl door OPEN e Operating fluids Check le...

Страница 74: ...chment suspension check d Tire Condition inflation wear 11 LEFT MAIN LANDING GEAR a Wheel fairing Condition attachment accumulation of debris b Main gear leg Condition attachment c Inspection hole cov...

Страница 75: ...hment 14 LEFT WING TRAILING EDGE a Aileron Condition remove control locks if installed freedom of movement without excessive play b Aileron attachment Secured c Aileron sealing tapes All in place cond...

Страница 76: ...tion to ground power unit It is located on the left side under the instrument panel a External power source Ensure that external power source is regulated to max 12 V 90 A DC b MASTER SWITCH Check OFF...

Страница 77: ...rcuits j Propeller area Clear k Starter key Hold START after engine started release to CHARGE As soon as engine runs l THROTTLE Adjust to achieve smooth running at approx 2500 rpm then decrease to app...

Страница 78: ...inimum pressure 2 00 bar within 10 seconds shut down the engine and investigate the cause The loss of lubrication can cause severe engine damage CAUTION At an engine start with low oil temperature con...

Страница 79: ...r pedals Adjust e CARBUR PREHEATING CLOSED 4 8 Taxiing When taxiing the direction of the aircraft is controlled by the rudder pedals which are connected to the nose wheel and rudder Use the minimum po...

Страница 80: ...ine speed by use of either circuit A or B is 115 rpm e THROTTLE Short MAX f Engine speed Check 5200 rpm 200 rpm g Engine parameters Check h CARBUR PREHEATING OPEN check carburetor preheating function...

Страница 81: ...ator Check removed lock see Chapter 7 22 Fig 7 33 b Controls Freedom of movement c TRIM Set neutral d Wing flaps FLAPS 1 check locked e CHOKE Check CLOSED f CARBUR PREHEATING Check CLOSED g Fuel selec...

Страница 82: ...avionics are working incorrectly Canopy is not properly latched and locked Weight and balance for both takeoff and landing is out of approved limits There is a frost ice snow or other contamination on...

Страница 83: ...er liftoff immediately to accelerate a Brake Release b THROTTLE Smoothly MAX c Engine parameters Check d Control stick Slightly tail low e Directional control Maintain with rudder control f Rotate Smo...

Страница 84: ...00 IAS 54 KIAS Best rate of climb airspeed VY at SL 127 IAS 69 KIAS CAUTION If the coolant or oil temperature approaches or exceeds limits reduce the climb angle to increase airspeed and possibly retu...

Страница 85: ...wing flaps a THROTTLE As required b Airspeed As required c TRIM As required d Engine parameters Monitor WARNING When descending with flaps extended do not exceed VFE CAUTION Engine undercooling and lo...

Страница 86: ...y NOTE Always extend the flaps gradually through incremental positions and trim the aircraft appropriately Optimum airspeed for flaps extension is FLAPS 1 at 130 IAS 70 KIAS FLAPS 2 at 120 IAS 65 KIAS...

Страница 87: ...er control h Wing flaps FLAPS 0 i Brake Apply heavily j After landing Perform according to Chapter 4 16 NOTE For maximum brake effectiveness retract the flaps hold the control stick full backward and...

Страница 88: ...E A thrust yawing moment is manifested in the case of the rapid full throttle application 4 16 After Landing a THROTTLE Adjust for taxiing b Wing flaps FLAPS 0 c TRIM Set neutral d FUEL PUMP OFF e LAN...

Страница 89: ...suitable air heater Temperature of hot air should not exceed 100 C Preheat until coolant and oil temperature exceed 20 C Before engine starting remove ice from the aircraft surfaces check the free mo...

Страница 90: ...zer and visual indication stall warning lamp The stall warning triggers approximately 9 19 km h 5 10 kts before the stall occurs The best means for preventing an inadvertent stall and spin entry is go...

Страница 91: ...wards the wingtip and may cause fuel shortage to the engine Even short term fuel shortage may cause the engine to stop immediately In a sideslip always set the higher wing tank on the fuel selector e...

Страница 92: ...ety altitude not below 165 ft 50 m AGL and 130 IAS 70 KIAS i Airspeed 122 127 IAS 66 69 KIAS see Chapter 5 5 j TRIM As required Crosswind Landing When landing in a strong crosswind use the minimum fla...

Страница 93: ...Initial issue Page 4 27 4 20 Noise Characteristics The noise level in accordance with requirements of the CS 36 Am 2 ICAO Annex 16 Volume I Chapter 10 10 4 b has been established to be 62 6 dB A...

Страница 94: ...Page 4 28 Initial issue This page is left blank intentionally...

Страница 95: ...TABLE OF CONTENTS 5 1 GENERAL 5 2 5 2 AIRSPEED CALIBRATION 5 3 5 3 STALL SPEEDS 5 5 5 4 TAKEOFF DISTANCE 5 7 5 5 RATE OF CLIMB 5 9 5 6 CRUISE PERFORMANCE AND FUEL CONSUMPTION 5 10 5 7 LANDING DISTANC...

Страница 96: ...ditions 15 C and 1013 25 mbar at sea level The performance tables do not take into account the expertise of the pilot or the maintenance condition of the aircraft The performance illustrated in the ta...

Страница 97: ...ated airspeed assumes zero instrument error IAS CAS FLAPS 0 FLAPS 1 FLAPS 2 FLAPS 3 0 15 24 35 VS0 61 74 64 75 76 68 80 79 79 VS 78 88 88 87 88 80 90 90 89 89 85 94 94 93 94 90 98 98 97 98 95 103 102...

Страница 98: ...s NOTE Indicated airspeed assumes zero instrument error KIAS KCAS FLAPS 0 FLAPS 1 FLAPS 2 FLAPS 3 0 15 24 35 VS0 33 40 35 41 41 37 43 42 43 VS 42 48 48 47 47 45 50 50 50 50 50 54 54 53 54 55 58 58 57...

Страница 99: ...AS 40 KCAS Wing level stalls Flaps positions IAS CAS KIAS KCAS Cruise FLAPS 0 0 78 88 42 48 Takeoff FLAPS 1 15 68 80 37 43 Landing normal FLAPS 2 24 64 75 35 41 Landing emergency FLAPS 3 35 61 74 33 4...

Страница 100: ...50 Takeoff FLAPS 1 15 74 85 40 46 Landing normal FLAPS 2 24 Landing emergency FLAPS 3 35 NOTE Maximum altitude lost during turning stall is 490 ft Altitude loss is maximum value determined during fli...

Страница 101: ...ance considerably RWY surface PAVED dry asphalt NON PAVED dry grass ISA conditions Ground roll Takeoff distance over 50 ft 15 m Ground roll Takeoff distance over 50 ft 15 m Pressure altitude OAT ISA O...

Страница 102: ...2 763 233 1435 437 0 3 667 203 1277 389 822 250 1545 471 10 13 716 218 1371 418 882 269 1659 506 20 23 767 234 1469 448 945 288 1777 541 30 33 819 250 1570 478 1010 308 1899 579 8000 30 31 597 182 114...

Страница 103: ...1027 987 951 917 885 856 828 6000 124 67 914 879 846 815 787 760 735 8000 123 66 746 717 689 664 640 619 598 10000 122 66 563 540 519 500 482 465 450 Pressure altitude Climb speed Rate of climb m s ft...

Страница 104: ...0 4 300 160 158 168 20 5 13 6 3 59 4 500 170 167 176 22 2 14 5 3 83 4 800 184 180 191 22 2 16 3 4 31 5 000 194 189 200 22 8 17 4 4 60 5 500 216 209 222 24 4 20 4 5 39 5 800 226 218 232 25 2 22 0 5 81...

Страница 105: ...5 5 91 20 5 13 6 3 59 4 500 92 90 95 22 2 14 5 3 83 4 800 99 97 5 103 22 2 16 3 4 31 5 000 105 102 108 22 8 17 4 4 60 5 500 117 113 120 24 4 20 4 5 39 5 800 122 118 125 25 2 22 0 5 81 6000 4 300 83 82...

Страница 106: ...urface PAVED dry asphalt NON PAVED dry grass ISA conditions Landing distance over 50 ft 15 m Ground roll braked Landing distance over 50 ft 15 m Ground roll braked Pressure altitude OAT ISA OAT ft C C...

Страница 107: ...164 2286 697 1003 306 0 3 1944 593 578 176 2461 750 1080 329 10 13 2087 636 620 189 2642 805 1160 353 20 23 2236 681 664 202 2830 862 1242 379 30 33 2389 728 710 216 3024 922 1327 405 8000 30 31 1740...

Страница 108: ...60 Wind direction 75 Wind velocity 6 0 m s 11 7 knots Crosswind component 5 2 m s 10 1 knots Headwind component 3 0 m s 5 8 knots The maximum demonstrated crosswind speed for takeoff was 8 3 m s 16 1...

Страница 109: ...Initial issue EASA Approved Page 5 15 Fig 5 2 Crosswind U S Standard Units...

Страница 110: ...Page 5 16 EASA Approved Initial issue This page is left blank intentionally...

Страница 111: ...Aircraft Weight and CG Limits 6 8 Weight and Balance Loading Form 6 11 Example of Calculation 6 13 6 5 LOADING DATA 6 14 Weights and Moments of Variable Masses Metric Units 6 14 Weights and Moments of...

Страница 112: ...e Datum to the point of each load s application is known as the CG Arm The Reference Datum is located 1 975 m 77 76 in forward from inner surface of the firewall The inner surface of the firewall is i...

Страница 113: ...ht column a Added column for installed items b Removed column for removed items 6 Record the item s CG arm into the Weight Change column s Arm column a Added column for installed items b Removed colum...

Страница 114: ...lled in their correct location h Inflate the aircraft s tires to their recommended operating pressures i Verify oil brake fluid and coolant are at their prescribed maximum levels j Close covers and ot...

Страница 115: ...g Calculate and record the Empty Weight Moment by totaling the appropriate columns Calculate and record the Empty Weight CG using formula given in the form h Calculate the correction for unusable fuel...

Страница 116: ...EIGHED Including operating fluids without unusable fuel Weighing point Scale reading kg lb Tare kg lb Net weight kg lb x Arm m in Moment kg m lb in 100 Main LH A Main RH A Nose B Empty Weight Moment C...

Страница 117: ...n 100 897 48 Weight kg lb 339 9 Reg Number Weight Change Removed Moment kg m lb in 100 Arm m in Weight kg lb Serial Number DY 487 2013 LSA Added Moment kg m lb in 100 Arm m in Weight kg lb Aircraft WT...

Страница 118: ...ft of reference datum and as a percentage of the MAC The relationship between CG arm and percentage of the MAC is detailed in the Chapter 6 2 3 Metric Units U S Standard Units Empty weight Max 410 8 k...

Страница 119: ...Initial issue EASA Approved Page 6 9 Fig 6 2 Operating Weight CG limit Metric Units...

Страница 120: ...Page 6 10 EASA Approved Initial issue Fig 6 3 Operating Weight CG limit U S Standard Units...

Страница 121: ...r blank Weight and Moment Limits Chart refer to Chapter 6 6 Weight and Balance Loading Form Aircraft Serial Number Reg Number Date WT9 Dynamic LSA Club No Item Example aircraft Your aircraft Weight Mo...

Страница 122: ...Page 6 12 EASA Approved Initial issue Fig 6 4 Check of flight weight moment limits Example Metric Units...

Страница 123: ...obtained this must be lower than the weight limits given in Chapter 2 4 Adding the static moments in lines No 1 through 5 the resulting static takeoff moment line No 6 is obtained 5 Adding the weights...

Страница 124: ...16 4 15 18 10 32 6 22 77 15 48 8 30 36 20 64 10 37 95 25 80 12 45 54 30 96 14 53 13 36 12 16 60 72 41 28 18 68 31 46 44 20 75 90 51 60 25 94 88 64 50 30 113 85 77 40 35 132 83 90 30 40 151 80 103 20...

Страница 125: ...Initial issue EASA Approved Page 6 15 Fig 6 5 Weights and moments of variable masses chart Metric Units...

Страница 126: ...2 41 15 24 20 29 88 20 31 25 37 35 25 39 30 44 82 30 47 35 52 29 35 55 40 59 76 40 63 45 67 23 45 71 50 74 70 50 79 60 89 65 60 94 70 104 59 71 10 80 119 53 81 26 90 134 47 91 42 100 101 57 110 111 73...

Страница 127: ...Initial issue EASA Approved Page 6 17 Fig 6 6 Weights and moments of variable masses chart U S Standard Units...

Страница 128: ...Page 6 18 EASA Approved Initial issue Fuel Quantity and Weight Conversion Chart Metric Units Fig 6 7 Fuel quantity and weight conversion chart Metric Units...

Страница 129: ...Initial issue EASA Approved Page 6 19 Fuel Quantity and Weight Conversion Chart U S Standard Units Fig 6 8 Fuel quantity and weight conversion chart U S Standard Units...

Страница 130: ...Page 6 20 EASA Approved Initial issue 6 6 Weight and Moment Limits Chart Metric Units Fig 6 9 Operating weight and moment chart Metric Units...

Страница 131: ...Initial issue EASA Approved Page 6 21 Weight and Moment Limits Chart U S Standard Units Fig 6 10 Operating weight and moment chart U S Standard Units...

Страница 132: ...6 2 Main wheel fairing left D32110100A 1 Main wheel fairing right D32120100A 1 Brake system Beringer 1 Windows JWP 2 NAV ACL lights AveoFlashLP LSA 2 Landing lights LED N6130 001 1 Flight Display scre...

Страница 133: ...na SP 2000 1 Transponder antenna AV 22 1 VOR LOC antenna CI 158C 1 GPS antenna SV GPS 250 1 Water thermostat Franz F1102 1 Oil thermostat Silent Hektik F1110 1 Electric fuel pump MSI E1F 1 Fuel flow t...

Страница 134: ...Page 6 24 EASA Approved Initial issue This page is left blank intentionally...

Страница 135: ...stem 7 6 7 4 FLIGHT DECK ARRANGEMENT 7 7 Left Section of Instrument Panel 7 9 Center Section of Instrument Panel 7 9 Right Section of Instrument Panel 7 10 Center Console and Pedestal Panel 7 11 7 5 F...

Страница 136: ...ust System 7 26 Air Induction System 7 26 Oil System 7 26 Ignition and Starter System 7 26 Engine Instruments 7 27 7 15 PROPELLER 7 32 7 16 FUEL SYSTEM 7 32 System Description 7 32 Fuel Management 7 3...

Страница 137: ...The construction of the wing includes conventional design with main spar rear shear web root rib and fuel tank ribs The upper and lower skins are bonded to the spars ribs and rear shear web Wing spar...

Страница 138: ...of the aileron includes skin web root and tip ribs The aileron is attached to the upper skin of the wing by means of three hinges The aileron has a mass balance weight attached in front of hinge line...

Страница 139: ...the sealing tapes Unglued sealing tapes cause a significant decrease of the effectiveness of the control surfaces The elevator is controlled by control sticks through mechanical linkage consisting of...

Страница 140: ...dder has a mass balance weight located in its horn The gap between rudder and vertical stabilizer is sealed by the sealing tapes Unglued sealing tapes cause a decrease of the effectiveness of the cont...

Страница 141: ...ide under the instrument panel there are remote controls for adjustment of rudder pedals The instrument panel is arranged primarily for use by the pilot sitting in the left seat Fig 7 4 1 Flight displ...

Страница 142: ...tor 39 Fuel selector 25 Flight hours counter 40 Pitch trim lever 26 Pedals adjustment handle 41 Brake lever 27 12 V 10 A Power outlet 42 Master switch 28 Bank indicator 43 Rescue system actuator 29 Au...

Страница 143: ...GINE FIRE STALL LH FUEL RES RH FUEL RES EMS OIL PRESS CHARGE and TEST button In the left lower corner 12 V 10 A power socket output is located Center Section of Instrument Panel In the center section...

Страница 144: ...akers with their values is shown in the table below Marking Protected instrument Circuit breaker value A AVIONICS Avionics relay 1 NAV ACL Navigation and anti collision lights 5 LAND Landing lights 1...

Страница 145: ...ing control labelled CARBUR PREHEATING PULL TO OPEN Cabin venting control labelled CABIN VENTILATION PULL TO OPEN Cabin heating control labelled CABIN HEATING PULL TO OPEN Fuel selector Choke control...

Страница 146: ...eter is input through the barometric adjustment knob at the lower left of the instrument The barometric altimeter setting of Dynon SkyView SV D1000 altimeter is input through the knob when set to BARO...

Страница 147: ...Document No 101321 016 revision Q or later Flight Display displays the information in the following screen arrangements EFIS with compass rose EMS arrangement screen 1 Fig 7 5 EFIS with g load indica...

Страница 148: ...Page 7 14 Initial issue Fig 7 5 Arrangement screen 1 Fig 7 6 Arrangement screen 2...

Страница 149: ...Initial issue Page 7 15 Fig 7 7 Arrangement screen 3 Fig 7 8 Arrangement screen 4...

Страница 150: ...Page 7 16 Initial issue Fig 7 9 Arrangement screen 5 Fig 7 10 Arrangement screen 6...

Страница 151: ...e from a reference pressure and displays the result in climb or descent Bank Indicator Bank indicator is displayed by the Dynon SkyView SV D1000 In addition a slip indicator is installed in the left s...

Страница 152: ...s of push pull rod and lever Torsion tube mechanically interconnects both wing flaps There is a booster gas strut in the flap control system The booster decreases the pilot effort when extending the w...

Страница 153: ...ped with a wheel fairing The wheel fairing is removable to provide access to the tire 7 9 Baggage Compartment The baggage compartment is located between the occupant s backrest and baggage bulkhead A...

Страница 154: ...houlders insert the belt anchors B into the buckle F and lock them To loosen the belts pull the top edge of adjusting clip D outwards and loosen the belt E as required Tighten the seat belts by pullin...

Страница 155: ...set the rudder control to neutral position nose gear straight Pull the pedal s adjustment handle Fig 7 4 When the pedals are released the springs will automatically try to set the pedals to aft positi...

Страница 156: ...canopy To open the canopy from inside pull the lock lever forwards with one hand Fig 7 13 A grab the canopy handle with the other hand and push to lift the canopy To close the canopy from outside grab...

Страница 157: ...l is connected with the nose wheel and this connection acts as a control lock To lock the aileron control systems set the ailerons to neutral position and fix them to the wing on the trailing edge usi...

Страница 158: ...ine is attached to the airframe by means of a metal tube engine mount through the rubber engine mounts 1 Overflow bottle 8 Regulator 2 Oil tank 9 Air filter 3 Carburetor 10 Airbox 4 Oil thermostat 11...

Страница 159: ...ease of friction The throttle control is mechanically linked by steel cables with the carburetors The choke control labelled CHOKE is a grey handle located in the center console The mixture is enriche...

Страница 160: ...oil pump integrated pressure regulator and oil pressure sensor The oil pump draws the engine oil from the oil tank through the oil thermostat low oil temperature or also through oil cooler high oil t...

Страница 161: ...HT LTR Voltage BATT VOLTS Current AMPS AMPS Ignition MAG A MAG B Other data consumed fuel volume LTRS USED remaining flight time TIME REM actual operational range RANGE fuel volume at next way point W...

Страница 162: ...Page 7 28 Initial issue Fig 7 16 Arrangement screen 1 Fig 7 17 Arrangement screen 2...

Страница 163: ...Initial issue Page 7 29 Fig 7 18 Arrangement screen 3 Fig 7 19 Arrangement screen 4...

Страница 164: ...Page 7 30 Initial issue Fig 7 20 Arrangement screen 5 Fig 7 21 Arrangement screen 6...

Страница 165: ...Initial issue Page 7 31 Fig 7 22 Arrangement screen 7 Fig 7 23 Arrangement screen 8...

Страница 166: ...ith check valve to the FUEL selector valve inlet From the right fuel tank the fuel flows through the coarse fuel filter and fine filter to the FUEL selector valve inlet From the FUEL selector valve th...

Страница 167: ...ection fuel tank 37 l 5 3 way distributor 18 RH center section fuel tank 37 l 6 Restrictor jet 19 RH wing fuel tank 26 l 7 Fuel flow transducer 20 Drain valve 8 EMS module 21 Fuel filter 9 Fuel pressu...

Страница 168: ...There is a fuel float type of fuel level sensor in the both left and right fuel tank Fuel level sensor is installed in the root rib of fuselage fuel tanks Fuel quantity is displayed by Dynon SkyView...

Страница 169: ...e SkyView recall a previously programmed amount of fuel which represents the full fuel load of the aircraft SkyView FULL is set to 100 l Press PRESET to have SkyView recall a previously programmed amo...

Страница 170: ...s pull the brake lever backward as required When parking the aircraft set the brake lever to position PARK When the maximum brake action is required set the brake lever to position MAX A brake system...

Страница 171: ...first and then to position START Dynon SkyView SV D1000 displays are connected through a circuit breaker to the MASTER SWITCH Avionics RDST XPDR intercom are activated by a separate switch labelled A...

Страница 172: ...rough the air hose to the control box The proportion of heated to fresh air is controllable by means of controllers labelled CABIN HEATING and CABIN VENTILATION Fig 7 4 The means of control is as foll...

Страница 173: ...Initial issue Page 7 39 Fig 7 29 Air outlets for cockpit venting Fig 7 30 Windshield demist knob...

Страница 174: ...ater and moisture that enters the system The drain sumps should be checked at the annual inspection or in any case when water in the system is known or suspected Pressure distribution to individual in...

Страница 175: ...ncies when the MASTER SWITCH has to be set OFF only the stall warning system of Dynon SkyView D1000 will be available visual indication on EFIS screen and headset sound Stall warning system has follow...

Страница 176: ...and attached to the auxiliary spar of the fuselage When the parachute deploys the steel rope is pulled out from the fuselage skin A weakened composite cover to enable rocket s smooth egress and parac...

Страница 177: ...er an inflated parachute may drag the aircraft By pulling several parachute lines that are beside one another the parachute will become empty and minimize the dragging After landing on water exit the...

Страница 178: ...Page 7 44 Initial issue This page is left blank intentionally...

Страница 179: ...owing 8 3 Parking 8 4 Tie Down Instructions 8 5 Jacking and Leveling 8 6 8 3 SERVICING OF OPERATING FLUIDS 8 7 Fuel Servicing 8 7 Fuel Contamination and Sampling 8 9 Oil Servicing 8 11 Coolant Servici...

Страница 180: ...OH is provided at delivery Aircraft Maintenance Manual AMM Aircraft Maintenance Manual is divided into chapters as specified by ATA A current copy of the AMM is provided at delivery Service Bulletins...

Страница 181: ...w bar is engaged to the nose leg by means of a pin It is also possible to tow the aircraft by holding the propeller blades at the blade root Before towing check if the space around the aircraft is cle...

Страница 182: ...in the retracted position pitch trim fully forward and the wheels must be chocked For extended and unattended parking as well as in unpredictable wind conditions in areas where a danger of propwash f...

Страница 183: ...FF both circuits f BRAKE Check PARK g Wheel chocks Put the chocks 1 in front of and behind the main wheels h Mooring eyes Screw mooring eyes 2 into the left and right lower wing surface near inspectio...

Страница 184: ...MASTER SWITCH and IGNITION must be switched OFF Nobody is allowed to be in the cockpit Raise aircraft a MASTER SWITCH Check OFF b IGNITION Check OFF both circuits c BRAKE Check PARK d Aircraft Positio...

Страница 185: ...H and IGNITION must be switched OFF Nobody is allowed to be in the cockpit WARNING Ground the aircraft before refuelling If a funnel is used it must be conductively connected to the filler neck before...

Страница 186: ...both circuits c BRAKE Check PARK d Fire extinguisher Place near fuel tank being filled e Ground wires Attach to the exhaust tube f Fuel tank cap Remove g Fueling Pour the suitable fuel type to desired...

Страница 187: ...alves are located in the lowest point of each tank on wings and fuselage bottom surfaces Fig 8 5 Drain each fuel tank to remove accumulated water if any as follows WARNING MASTER SWITCH and IGNITION m...

Страница 188: ...Page 8 10 Initial issue Fig 8 5 Fuel draining...

Страница 189: ...y used MOGAS or AVGAS When operating with leaded AVGAS fuels perform maintenance checks according to the latest Maintenance Manual for Rotax engine type 912 Series More frequent oil changes will assur...

Страница 190: ...Oil cowl door Open e Oil tank cap Open f Propeller Crank in direction of the engine rotation by hand several times until a noticeable gurgle is heard check for odd noises or excessive resistance and n...

Страница 191: ...OTE For complete coolant specifications see OPERATORS MANUAL FOR ROTAX ENGINE TYPE 912 SERIES Doc No OM 912 and Rotax Service Instructions SI 912 016 latest edition Coolant replenishing a MASTER SWITC...

Страница 192: ...e vibration in the landing gear WARNING MASTER SWITCH and IGNITION must be switched OFF Nobody is allowed to be in the cockpit Tire inflating a BRAKE PARK b IGNITION Check both circuits OFF c Wheel fa...

Страница 193: ...a soft cloth or chamois and rub with moderate pressure until all dirt oil scum and bug stains are removed Never rub a dry windshield or windows Finally wipe the cleaner off with soft flannel cloths CA...

Страница 194: ...OFF both circuits c BRAKE Check PARK d Upper engine cowling Remove e Engine temperature Check if the engine is cooled down to ambient temperature f Engine compartment Clean as required g Upper engine...

Страница 195: ...e and finished with a chamois a MASTER SWITCH Check OFF b IGNITION Check OFF both circuits c BRAKE Check PARK d Propeller Clean as required WARNING MASTER SWITCH and IGNITION must be switched OFF Nobo...

Страница 196: ...ht and change of CG position Engine preheating It is possible to start the engine without needing to preheat if the outside temperature is above 5 C It is recommended to preheat the engine and oil if...

Страница 197: ...vent the failure of the radiator or cooling system due to ice If the outside temperature is below coolant mixture freezing point the coolant mixture must be drained or renewed using a pure coolant to...

Страница 198: ...Page 8 20 Initial issue This page is left blank intentionally...

Страница 199: ...e 9 1 9 SUPPLEMENTS TABLE OF CONTENTS 9 1 INTRODUCTION 9 2 9 2 MANUAL IMPROVEMENT REQUEST FORM 9 3 9 3 SAFETY OF FLIGHT AND SERVICE DIFFICULTY REPORT FORM 9 4 9 4 CHANGE OF AIRCRAFT OWNER ADDRESS NOTI...

Страница 200: ...tomer s request may increase the aircraft empty weight and reduce the allowed useful load If there are any suggestions for improvements to the content of the manual please use the form in the Chapter...

Страница 201: ...mprovement to the content of the manual or if errors or omissions were found please submit the proposed changes by means of MANUAL IMPROVEMENT REQUEST form Fill the form and sent it to the above state...

Страница 202: ...ed increasing reliability of aircraft we would like to ask you for your assistance in the case of safety of flight or service difficulty Fill the feedback form and sent it to the above stated address...

Страница 203: ...ol sk CHANGE OF AIRCRAFT OWNER ADDRESS NOTIFICATION Aerospool reference No Date Dear owner Fill the change of address notification form and sent it to the above stated address via post or email Name o...

Страница 204: ...Page 9 6 Initial issue This page is left blank intentionally...

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