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sonaca aircraft S201, Aircraft Flight Manual

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S201 AFM 

 

7 - AIRPLANE AND SYSTEMS 

DESCRIPTION 

7.9 - POWERPLANT

 

 

27/06/2019 

SONAIR-S2-D-MAN-006 

Page : 7-65 

Rev. : A 

 

7.9.5

 

TURBOCHARGER CONTROL UNIT 

 

The applicable sections in the Rotax 914 F 

operator’s

 manual should be carefully 

read in conjunction with this section. 

A  throttle  arm  position  sensor  is  mounted  on  one  carburettor.  The  sensor 
measures  the  throttle  position  linearly  from  0%  to  115%,  corresponding  to 
engine idle and engine full (100%) power respectively. The TCU (Turbocharger 
Control  Unit)  utilizes  throttle  position  in  conjunction  with  aircraft  ambient 
pressure,  airbox  pressure,  engine  rpm  and  airbox  temperature  to  actuate  an 
electronically controlled waste gate to regulate the speed of the turbocharger / 
boost pressure in the engine airbox. 

 

Relationship between throttle position and engine power 

Throttle position 

Engine power 

115% 

100 % 

Full Power

 

100% 

85 % 

Maximum Continuous Power 

 

 

 

 

NOTE 

Throttle position from 108% to 110% result in a rapid rise in boost 

pressure. Avoid constant throttle settings in this range, as it may 

result in boost pressure control fluctuations (surging).  

To avoid unstable boost pressure the throttle should be moved 

smoothly through this range to full power (115% throttle position), 

or on a power reduction, to maximum continuous power (100% 

throttle position)  

Summary of Contents for S201

Page 1: ...Date of Issue 27 06 2019 Approved by Sonaca Aircraft S A Signature Agency N A Stamp N A Original date of approval 01 07 2019 This airplane must be operated in compliance with information and limitations contained herein This pilot operating handbook must be available on board of the airplane at all times ...

Page 2: ...manual with the exception of Temporary Revisions updates of the modification level updated mass and balance information updates of the Equipment Inventory and updates of the List of Supplements Must be recorded in the following table and in case of approved Sections endorsed by the Agency The new or amended text in the revised pages will be indicated by a black vertical line in the left hand margi...

Page 3: ...A 2 3 A EASA 2 4 A EASA 2 5 A EASA 2 6 A EASA 2 7 A EASA 2 8 A EASA 2 9 A EASA 2 10 A EASA 2 11 A EASA 2 12 A EASA 2 13 A EASA 2 14 A EASA 2 15 A EASA 2 16 A EASA 2 17 A EASA 2 18 A EASA 2 19 A EASA 2 20 A EASA 2 21 A EASA 2 22 A EASA 2 23 A EASA 2 24 A EASA 2 25 A EASA 2 26 A EASA 2 27 A EASA 2 28 A EASA 2 29 A EASA 2 30 A EASA 2 31 A EASA 3 1 A EASA 3 2 A EASA 3 3 A EASA 3 4 A EASA 3 5 A EASA 3 ...

Page 4: ...SA 5 17 A EASA 5 18 A EASA 5 19 A EASA 6 1 A EASA 6 2 A EASA 6 3 A EASA 6 4 A EASA 6 5 A EASA 6 6 A EASA 7 1 A EASA 7 2 A EASA 7 3 A EASA 7 4 A EASA 7 5 A EASA 7 6 A EASA 7 7 A EASA 7 8 A EASA 7 9 A EASA 7 10 A EASA 7 11 A EASA 7 12 A EASA 7 13 A EASA 7 14 A EASA 7 15 A EASA 7 16 A EASA 7 17 A EASA 7 18 A EASA 7 19 A EASA 7 20 A EASA 7 21 A EASA 7 22 A EASA 7 23 A EASA 7 24 A EASA 7 25 A EASA 7 26...

Page 5: ... A EASA 7 80 A EASA 7 81 A EASA 7 82 A EASA 7 83 A EASA 7 84 A EASA 7 85 A EASA 7 86 A EASA 7 87 A EASA 7 88 A EASA 7 89 A EASA 7 90 A EASA 7 91 A EASA 7 92 A EASA 7 93 A EASA 7 94 A EASA 7 95 A EASA 7 96 A EASA 8 1 A EASA 8 2 A EASA 8 3 A EASA 8 4 A EASA 8 5 A EASA 8 6 A EASA 8 7 A EASA 8 8 A EASA 8 9 A EASA 8 10 A EASA 8 11 A EASA 9 1 A EASA 9 2 A EASA 9 3 A EASA 9 4 A EASA 9 5 A EASA 9 6 A EASA...

Page 6: ... 0 4 TABLE OF CONTENT 0 MANUAL ADMINISTRATION 0 1 1 GENERAL INFORMATION 1 1 2 LIMITATIONS 2 1 3 EMERGENCY PROCEDURES 3 1 4 NORMAL PROCEDURES 4 1 5 PERFORMANCE 5 1 6 WEIGHT AND BALANCE 6 1 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 1 8 AIRPLANE GROUND HANDLING AND SERVICING 8 1 9 ADDITIONAL INFORMATION 9 1 ...

Page 7: ...v A 1 GENERAL INFORMATION 1 1 TABLE OF CONTENT 1 1 TABLE OF CONTENT 1 1 1 2 INTRODUCTION 1 2 1 3 CERTIFICATION BASIS 1 4 1 4 WARNING CAUTION AND NOTES 1 5 1 5 AIRCRAFT DESCRIPTION AND DIMENSIONS 1 6 1 6 DEFINITION AND ABBREVIATIONS 1 11 1 7 UNITS OF MEASUREMENT 1 20 1 8 SOURCE DOCUMENTATION 1 23 ...

Page 8: ... The Sonaca S201 is a two seat side by side single engine tricycle fixed undercarriage aluminium aircraft with a conventional low wing design The Sonaca S201 is certified based upon the EASA CS VLA Certification Standard Very Light Aircraft standard having a maximum Take Off Weight of 750 kg The Sonaca S201 is intended primarily for training and recreational flying It is not intended for aerobatic...

Page 9: ...POSSIBLE OPTIONS AS INSTALLED OR APPROVED BY SONACA AIRCRAFT S A ARE INCLUDED IN APPLICABLE SUPPLEMENTS OF THIS HANDBOOK SECTION 9 AIRCRAFT WHICH DIFFER FROM THE PRODUCTION STANDARD IN WHATEVER WAY ARE NOT ADDRESSED IN THIS MANUAL EXCEPT TO THE EXTENT THE SAID AIRCRAFT CORRESPONDS TO SONACA AIRCRAFT S A APPROVED MODIFICATIONS NOTE THIS EDITION OF THIS MANUAL IS BASED ON EASA REQUIREMENTS DEFINITIO...

Page 10: ...A 1 3 CERTIFICATION BASIS This type of aircraft has been approved by the European Aviation Safety Agency in accordance with CS VLA including Amendment 1 and the Type Certificate No EASA A 626 has been issued on 12 June 2018 Category of Airworthiness Normal Noise Certification Basis CS 36 Amendment 4 ...

Page 11: ...ual WARNING means that the non observation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION means that the non observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight safety NOTE draws the attention to any special item not directly related to safety but which is important or unusu...

Page 12: ...IONS The Sonaca S201 is a Very Light Airplane VLA certified under the rules of EASA CS VLA Amendment 1 It features two seats side by side a single Rotax 914F engine with a 3 blades fixed pitch DUC Flash R propeller a tricycle fixed undercarriage and an all aluminum structure with a conventional low wing design 1539 903 6737 2555 1180 655 1880 9243 1920 ...

Page 13: ...N 1 5 AIRCRAFT DESCRIPTION AND DIMENSIONS 27 06 2019 SONAIR S2 D MAN 006 Page 1 7 Rev A For detailed description including Power plant and Systems see Section 7 2822 1161 1474 1760 920 DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES ...

Page 14: ...an 9 243 m 30 ft 4 inch Mean Aerodynamic Chord 1 318 m 51 9 inch Wing surface area 11 845 m2 131 75 sq ft Wing loading 59 10 kgm 2 11 7 lbs sq ft Aspect ratio 7 04 Taper ratio 1 375 Dihedral 5o FUSELAGE Metric Imperial Fuselage length 6 m 19 ft 8 inch Overall length 6 675 m 22 ft 1 inch Overall width 1 16 m 46 inch Overall height 2 55m 100 inch ...

Page 15: ...surface area 0 96 m2 10 ft2 Elevator surface area 1 02 m2 11 ft2 Horizontal stabilizer angle of incidence 1 45o Vertical stabilizer span 1 47 m 16 ft Vertical stabilizer surface area 0 53 m2 6 ft2 Rudder surface area 0 59 m2 6 ft2 LANDING GEAR Metric Imperial Wheel track 1 92 m 6ft 4 inch Wheel base 1 54m 5ft 1 inch Brakes Hydraulic Main gear tyres pressure 3 4 bar 49 psi Nose gear tyre pressure 2...

Page 16: ... S2 D MAN 006 Page 1 10 Rev A CONTROL SURFACE TRAVEL LIMITS Ailerons 24o 2 up and 24o 2 down Elevator 28o 2 up and 22o 2 down Trim tab 13o 5 up and 23o 5 down Rudder 25o 2 left and right Flaps 0 1 Flaps up UP 10 1 Take off position T O 20 1 5 Approach position APP 30 2 Landing position LD ...

Page 17: ...nication radio CS VLA Certification Standard Very Light Aircraft DC Direct Current EASA European Aviation Safety Agency EFIS Electronic Flight Information System FAA Federal Aviation Authority GmbH Gesellschaft mit beschränkter Haftung company with limited liability GPS Global Positioning System IFR Instrument Flying Rules LED Light Emitting Diode MOGAS Automobile car gasoline N VFR Night Visual F...

Page 18: ...he ground VFE Maximum Flap Extended Speed being the highest speed permissible with wing flaps deployed VLOF Lift off Speed being the speed at which the aircraft generally lifts off from the ground during take off VNE Never Exceed Speed being the speed that may not be exceeded at any time VNO Maximum Structural Cruising Speed being the speed that should not be exceeded except in smooth air and then...

Page 19: ...timeter will cause the altimeter to indicate local altitude above mean sea level QFE The local airfield pressure setting that if set on the subscale of an altimeter will cause the altimeter to indicate local height above airfield Engine terminology CHT Cylinder Head Temperature EGT Exhaust Gas Temperature OHV Overhead Valve RPM Revolutions per minute being the number of revolutions per minute of t...

Page 20: ...asured during landing from actual touchdown to the end of the landing run Landing distance The distance measured during landing from clearance of a 15 m obstacle in the air to the end of the landing run Take off distance The take off distance measured from the actual start of the take off run to clearance of a 15 m 50 ft obstacle in the air Take off run The take off distance measured from actual s...

Page 21: ...f the airplane with engine fluids and oil at operating levels without fuel pax and baggages MAC Mean Aerodynamic Chord MLW Maximum Landing Weight Is the maximum weight approved for the landing touch down MTOW Maximum Take off Weight is the maximum weight approved for the start of the take off run Moment Is the product of the weight of an item multiplied by its arm SG fuel Specific Gravity is the r...

Page 22: ... Along TracK CDI Course Deviation Indicator CRS Course DME Distance Measuring Equipment EFB Electronic Flight Bag EGNOS European Geostationary Navigation Overlay Service EHSI Electronic Horizontal Situation Indicator FIS B Flight Information Services Broadcast FPA Flight Path Angle FS510 Flight Stream 510 GAGAN GPS Aided GEO Augmented Navigation GDU Garmin Display Unit GMA Garmin Multimedia Audio ...

Page 23: ...calizer Directional Aid LNAV Lateral Navigation LNAV V Lateral Navigation with advisory Vertical Guidance L VNAV Lateral Vertical Navigation LOC Localizer LOC BC Localizer Backcourse LOI Loss of Integrity LP Localizer Performance LPV Localizer Performance with Vertical Guidance LP V Localizer Performance with Advisory Vertical Guidance MFD Multifunction Display MLS Microwave Landing System MMC Mul...

Page 24: ...implified Directional Facility SUSP Suspend SVT Synthetic Vision Technology TACAN Tactical Air Navigation System TAS Traffic Awareness System TAWS Terrain Awareness and Warning System TCAS Traffic Collision Avoidance System TCH Threshold Crossing Height TFR Temporary Flight Restriction TIS Traffic Information Service TIS A Traffic Information Service Addressed TIS B Traffic Information Service Bro...

Page 25: ...N AND ABBREVIATIONS 27 06 2019 SONAIR S2 D MAN 006 Page 1 19 Rev A VNAV Vertical Navigation VOR VHF Omnidirectional Range VRP Visual Reporting Point VS Vertical Speed WAAS Wide Area Augmentation sYSTEM WFDE WAAS Fault Data Exclusion XFR Transfer ...

Page 26: ...ne unit system only imperial OR metric Imperial System Altitude in feet Speed in knots Climb speed in feet per minute Engine Manifold Pressure MAP in in Hg Engine Propeller Rotation speed in RPM revolution per minute Oil and Fuel pressures in psi Distance in Nm Metric system Fuel quantity in liters Temperatures in C degree Celsius tyre pressure in bar Other units than the ones that can be read on ...

Page 27: ...2 CONVERSION FACTORS The figure below gives conversion factors for fuel quantities and masses Fuel SG 0 72 for AVGAS is based on ISA temperature at MSL Therefore fuel weights will be approximate for temperatures other than 15 degrees Celsius AVGAS Volume Mass Conversion Factors Diagram correct at less than 1 ...

Page 28: ...FM 1 GENERAL INFORMATION 1 7 UNITS OF MEASUREMENT 27 06 2019 SONAIR S2 D MAN 006 Page 1 22 Rev A The figure below gives conversion factors for speeds Speed Conversion Factors Diagram correct at less than 0 3 ...

Page 29: ...tors Manual For Rotax Engine Type 914 Series Ref No OM 914 See https www flyrotax com services technical documentation html Searching databank for 914 F will provide the OM as well as all relevant Service Bulletins and Service Letters 1 8 2 PROPELLER Manufacturer DUC Helices Model FLASH R No of blades 3 Diameter 1750 mm See the latest revision edition of the Instruction Manual for tri blade Flash ...

Page 30: ...Management EDM 900 Primary TSO STC 1 8 4 FLIGHT COMMUNICATION AND NAVIGATION INSTRUMENTS PFD Manufacturer Garmin Model G500 TXi Manual G500TXi Pilots Guide P N 190 01717 10 GPS COM1 NAV1 Manufacturer Garmin Model GTN 650 Manual GTN 650 Cockpit Reference Guide P N 190 01004 04 Transponder Manufacturer Garmin Model GTX 335R Manual GTX 335 345 Series Pilot s Guide P N 190 01499 00 Audio Panel Manufac...

Page 31: ...SONAIR S2 D MAN 006 Page 1 25 Rev A COM2 NAV2 if equipped Manufacturer Garmin Model GNC 255 A Manual GNC 255A 255B Pilot s Guide P N 190 01182 01 Backup Flight Instrument Manufacturer Bendix King Honeywell Model KI 300 Manual KI 300 KA310 Pilot s Guide P N 89000004 201 ...

Page 32: ...LE OF CONTENT 2 1 2 2 INTRODUCTION 2 2 2 3 AIRSPEED 2 3 2 4 AIRSPEED INDICATOR MARKINGS 2 4 2 5 POWERPLANT LIMITATIONS 2 5 2 6 MASS WEIGHT 2 11 2 7 DATUM CENTER OF GRAVITY RANGE 2 12 2 8 APPROVED MANOEUVERS 2 13 2 9 MANOEUVERING LOAD FACTORS 2 14 2 10 KIND OF OPERATIONS 2 15 2 11 OTHER LIMITATIONS 2 16 2 12 LIMITATION PLACARDS 2 25 ...

Page 33: ...erating limitations instrument markings and basic placards necessary for safe operation of the Sonaca S201 its engine standard systems and standard equipment The limitations included in this section and in Section 9 have been approved by European Aviation Safety Agency The minimum crew for operation of the S201 is one pilot ...

Page 34: ... speed 105 Do not make full or abrupt control movements above this speed as this may cause stress in excess of limit load factor VFE 10 Maximum flap 10 speed 105 Never exceed this speed with flaps T O setting VFE 20 Maximum flap 20 speed 95 Never exceed this speed with flaps APP setting VFE 30 Maximum flap extended speed 85 Never exceed this speed with flaps LD setting VS1 0 Stall speed 50 At maxi...

Page 35: ...45 85 Positive Flap Operating Range Lower limit is VS0 at maximum weight Upper limit is the maximum speed permissible with flaps LD setting Vfe Green arc 50 120 Normal Operating Range Lower limit is VS1 at maximum weight most forward CG with flaps retracted engine idling Upper limit is maximum structural cruising speed Yellow arc 120 135 Manoeuvres must be conducted with caution and only in smooth...

Page 36: ...inuous 5500 RPM Between 5500 and 5800 RPM Maximum 5 minutes More than 5800 RPM See Rotax 914 Line Maintenance Manual Ref MML 914 Coolant Temperature Maximum 120 C NOTE Always refer to the latest Engine Manufacturer document TCDS OM MM SB SI See https www flyrotax com services technical documentation html Searching databank for 914 F will provide the OM as well as all relevant Service Bulletins and...

Page 37: ... Maximum 102 psi 7 bar Oil Grade Specification See Rotax 914 Operator Manual Ref OM 914 See Rotax SI 914 019 for approved oil types When operating on unleaded fuels or MOGAS fully synthetic oil is recommended Oils for Diesel engines and oils with friction modifier are unsuitable NOTE Below 50 C Oil Temperature on ground Engine RPM limited to 2500 NOTE Ensure at least once per flight day to reach a...

Page 38: ...5 bar Maximum Airbox pressure 5 08 psi 0 35 bar Fuel Grade Specification see section 2 5 3 WARNING Exceeding maximum allowed fuel pressure will override the float valves of the carburetors and lead to engine failure NOTE On the S201 fuel pressure is directly measured as difference between fuel and airbox pressure Therefore the operating range as indicated on the EMS is 2 18 to 5 08 psi ...

Page 39: ...mits ENGINE START AND OPERATION TEMPERATURE LIMITS 914 F Maximum 50 C ambient air temperature Minimum 25 C oil temperature limitation NOTE Do not use concentrated water free propylene glycol based coolant NOTE Coolant component can be increased up to max 65 NOTE Normal operation does not allow negative load factor manoeuvres see section 2 10 In case of unintentional negative load factor the pilot ...

Page 40: ... RPM 5500 5800 RPM 5800 6400 RPM Oil Temperature 0 50 C 50 110 C 110 130 C 130 150 C Coolant Temperature None 0 120 C None 120 150 C Oil pressure 0 12 psi 29 73 psi 12 29 psi 73 102 psi 102 130 psi Exhaust Gas Temperature None 700 900 C 900 950 C 950 1000 C Fuel pressure 0 2 18 psi 2 18 5 08 psi None 5 08 5 8 psi Manifold Pressure None 25 35 4 in Hg 35 4 39 9 in Hg 39 9 42 in Hg Fuel level 0 5 L 5...

Page 41: ...l types WARNING Operation of engine on a fuel tank with less than 3 L fuel remaining wings level will lead to engine stop in flight NOTE Remaining fuel below 10 L in both tank will lead to low fuel indication on EMS NOTE The operator of the aircraft must select a standard operating fuel and establish its Approved Maintenance Program in accordance with the selected fuel When refueling with a fuel t...

Page 42: ...y the Engine Max RPM at 5800 Engine Max RPM Propeller RPM 2387 2700 2 6 MASS WEIGHT Metric Imperial Maximum Take off weight 750 kg 1650 lbs Maximum Landing weight 750 kg 1650 lbs Maximum Taxi weight 750 kg 1650 lbs Maximum Zero Fuel weight 750 kg 1650 lbs Maximum baggage weight Area 1 Area 2 35 kg 77 lbs Maximum baggage weight Area 1 35 kg 77 lbs Maximum baggage weight Area 2 25 kg 55 lb Refer to ...

Page 43: ...per surface of canopy slides Forward limit at 650 kg and below 0 876 m 2 873 ft 20 Forward limit at 750 kg 0 915 m 3 ft 23 Rear limit at 650 kg and below 1 021m 3 349ft 31 Rear limit at 750 kg 1 034 m 3 392 ft 32 aft of datum There is a linear variation between all points of the centrogram see section 6 4 WARNING It is the pilot s responsibility to ensure that the airplane is properly loaded Refer...

Page 44: ...the S201 with the flaps fully retracted Approved Manoeuvers Entry speed Steep turns 90 KIAS Lazy eights Chandelles Stalls excluding whip stalls angle of bank limited to 60 WARNING Aerobatics and intentional spins are prohibited WARNING Limit load factor would be exceeded by moving flight controls abruptly to their limits at a speed above VA Maneuvering must always be conducted smoothly and careful...

Page 45: ...ACTORS Load factor type Maximum value Maximum positive limit load factor 4 4 g Maximum negative load factor 1 76 g Maximum positive flap down load factor 2 2 g Maximum negative flap down load factor 0 g CAUTION 0 5g max for 5 sec for an engine proper running in case of inadvertent negative g manoeuvre see 2 5 1 Engine Limit ...

Page 46: ...nt required for day or night VFR are defined in paragraph 7 13 VFR flights in rain are authorized WARNING IFR flights and intentional flights into known icing conditions are prohibited The GPS navigator GTN 650 is approved for VFR USE ONLY NOTE Additional equipment may be required to fulfill national or specific requirements NOTE This aircraft complies with CS ACNS requirements for ADS B out ...

Page 47: ...TURE No limitation on external temperature other than engine temperature limitations defined in 2 5 1 2 11 3 BATTERY CHARGE Taking off for a flight with an empty battery is not permitted A battery voltage below 10V is considered empty and requires a maintenance action 2 11 4 OPERATION TIME OF ELECTRICAL EQUIPMENT Following a dual alternator failure it can be expected that the systems are supplied ...

Page 48: ...lug is protected by a 2 amps breaker 2 11 7 CANOPY LOCKING DEVICE Flight is authorized only with Canopy closed and properly latched Taxi with open canopy is allowed Caution should be applied to avoid unexpected forward canopy movement that could injure the flight crew Slow braking is recommended 2 11 8 LANDING GEAR FAIRINGS Operations without Landing Gear Fairings installed is authorized and does ...

Page 49: ...ata internally and therefore only requires external GPS Documents on Board Following GARMIN documents must be immediately available to the flight crew during flights GTN 6XX Cockpit Reference Guide P N 190 01004 04 Rev M or later Backup Flight Instrument The battery of the electronic standby instrument must be verified to be operational before flight or the electronic standby must be considered in...

Page 50: ...thetic Vision Terrain warning and avoidance system Optional Terrain point obstacle and wire obstacle information appears on the map and terrain display pages as red and amber terrain obstacles or wires and is depicted for advisory use only Aircraft maneuvers and navigation must not be predicated upon the use of the terrain display Terrain obstacle and wire information is advisory only and is not e...

Page 51: ... features must not be used as the primary or sole means of navigation or course guidance Navigation with QFE setting When flying procedures requiring the use of QFE barometric settings the pilot must ensure that the barometric setting for the source interfaced with the GTN is set to QFE as appropriate GTN does not support barometric VNAV for QFE operations ...

Page 52: ...fingers used to operate the G500 and GTN unless the Glove Qualification Procedure located in the Pilot s Guide Cockpit Reference Guide has been successfully completed The Glove Qualification Procedure is specific to a pilot glove avionic combinations NOTE This procedure does not modify the system to improve compatibility with a certain glove type It does only permit to validate if a certain glove ...

Page 53: ...ment approach Databases and Updates Databases identified as intended for helicopters must not be used These databases are identified by the word HELI or HELICOPTER in their title as displayed on the database status page see next page CAUTION Failure to turn off telephone audio when the telephone is not in use may result in telephone ringer or text message aural notifications being received during ...

Page 54: ...he aircraft is on the ground and stationary In flight database transfers or updates are prohibited Navigation Angle The Magnetic True Navigation Angle as selected on the System Units page must match the navigation angle selected on all interfaced GPS SBAS navigators NOTE It is the pilot s responsibility to perform Databases updates in accordance with applicable National Regulations ...

Page 55: ...he following or later software versions must be installed for this AFM revision to be applicable Software Item Version GDU 2 20 GTN 650 The Main and GPS software versions are displayed on the start up page immediately after power on All software versions displayed in Table 2 can be viewed on the System System Status or Connext Setup pages Software Item Version Main SW Version 6 50 GPS SW Version 5...

Page 56: ... 12 LIMITATION PLACARDS The following limitation and warning placards are placed in the aircraft and positioned in plain view of the occupants Other markings and placards are described and shown in section 9 4 On the instrument panel On the dashboard cap center Under the warning and caution lights ...

Page 57: ...TIONS 2 12 LIMITATION PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 2 26 Rev A Around the master switch In a place visible to pilot and passenger In plain sight of the pilot and co pilot passenger below the fuel selector ...

Page 58: ...S201 AFM 2 LIMITATIONS 2 12 LIMITATION PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 2 27 Rev A In between the flap indicator and handle On the baggage space separator channel ...

Page 59: ...S201 AFM 2 LIMITATIONS 2 12 LIMITATION PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 2 28 Rev A On the moveable trim tab indicator In between the trim wheel and trim indicator Left of the throttle ...

Page 60: ...FM 2 LIMITATIONS 2 12 LIMITATION PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 2 29 Rev A Adjacent to the fuel filler caps On the cowl access door On the inboard upper wing flap surface On the elevator surface ...

Page 61: ...S201 AFM 2 LIMITATIONS 2 12 LIMITATION PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 2 30 Rev A At the static ports location At the jacks On the wheel fairings ...

Page 62: ...d immediately above or below the first plate On the bottom of the rear fuselage below the horizontal stabilizer a third fireproof metal plate is placed with following information MANUFACTURER SONACA AIRCRAFT S A MODEL S201 SERIAL NO MSNXXX MANUFACTURED MM YYYY A C REG No AA BBB REGISTRATION HOME BASE OWNER NOTE The external crash plate content varies according to the country of registration ...

Page 63: ...F CONTENT 3 1 TABLE OF CONTENT 3 1 3 2 INTRODUCTION 3 2 3 3 ENGINE FAILURES 3 4 3 4 SMOKE AND FIRE 3 16 3 5 LANDING WITH DEFECTIVE TYRE 3 19 3 6 LANDING WITH DEFECTIVE BRAKES 3 19 3 7 RECOVERY FROM UNINTENTIONAL SPIN 3 20 3 8 PRECAUTIONARY LANDING 3 21 3 9 INSTRUMENT INDICATION OUTSIDE OF GREEN RANGE 3 22 3 10 OTHER EMERGENCIES 3 23 ...

Page 64: ... are extremely rare if proper pre flight inspections and maintenance are practised However should an emergency arise the procedures described in this section should be considered and applied as necessary to correct the problem In case of emergency the pilot should remember the following priorities 1 Keep control of and continue flying the aircraft 2 Analyse the situation 3 Apply applicable procedu...

Page 65: ... REMARKS VBG Best Glide Speed 65 The speed Flaps fully retracted which results in the greatest gliding horizontal distance Conditions Flaps retracted Airspeed VBG 65 KIAS Propeller wind milling propeller Wind zero Horizontal distance travelled still air is approximately 1 9 Nmi 3 5 km per 1000 ft 305 m descent i e glide ratio of 11 6 1 ...

Page 66: ...apply as needed With airplane stopped 3 Electric fuel pumps both off 4 Fuel selector valve off 5 Magnetos ignition off 6 Radio communication as required 7 Master switches off 8 Parking brakes on if required evacuate aircraft WARNING Do not open the cowlings If fire extinguisher is used discharge in the air intakes after propeller stopped NOTE Fire extinguisher is located in baggage compartment beh...

Page 67: ... on If engine does not provide enough power otherwise go to 7 5 Perform emergency landing refer to 3 3 4 EMERGENCY LANDING WITH ENGINE OFF If engine continues to run irregularly but able to maintain 65 KIAS level flight 6 Cabin heat close 7 Land as soon as practical 8 ELT optional equipment on CAUTION Minimum altitude recommended for short circuit in case of engine failure is 500 ft AGL CAUTION Ma...

Page 68: ...ck position power as required 3 Fuel selector valve change to opposite tank except if already empty 4 Auxiliary fuel pump on 5 Main fuel pump check circuit breaker pushed If engine did not restart 6 Start gliding descent at flaps UP 65 KIAS 7 Refer to 3 3 4 EMERGENCY LANDING WITH ENGINE OFF NOTE In case of Main fuel pump filter clogging engine may run irregularly and shut down if Full Power is app...

Page 69: ... and attempt a restart see 3 3 6 tighten harnesses declare emergency on radio and report location If re start fails 2 Ignition off 3 Fuel selector shut off 4 Aux fuel pumps off 5 Main fuel pump pull circuit breaker 6 Navigate join suitable landing area at or above 1500ft AGL 7 Speed VBG 65 KIAS 8 Flaps T O setting 9 ELT optional equipment on 10 Align for final approach 11 Flaps as required see not...

Page 70: ... low 4 Expect Engine Failure in Flight refer to 3 3 3 ENGINE FAILURE IN FLIGHT NOTE Flaps cannot operate without power on the main bus Make final flap selection before turning master switch off 11 sec are needed to re boot the Flap System if the master switch has been turned on again after being put off before the Flaps are in position NOTE In case of Main fuel pump filter clogging engine may run ...

Page 71: ...E Otherwise 3 Throttle reduce throttle to minimum for level flight 4 Land as soon as practical and remain vigilant for impending engine failure 3 3 7 HIGH OIL TEMPERATURE If oil temperature rises above 110 C 1 Throttle reduce below Max Continuous Power 2 Airspeed increase 3 Oil Pressure check If Oil Temperature rises above 130 C 4 Power idle 5 Prepare for emergency landing refer to 3 3 4 EMERGENCY...

Page 72: ...gine fails to restart or if height is insufficient 8 Proceed with an emergency landing with Power Off 3 3 4 WARNING After engine fire never attempt to re start the engine NOTE With engine off the propeller may continue rotating down to about 60 KIAS In such circumstances do not use starter step 6 If the propeller stops rotating either use starter or increase airspeed up to 80 KIAS to windmill An a...

Page 73: ...Fuel selector off 6 Main Fuel pumps pull circuit breaker 7 Aux Fuel pump off 8 Perform emergency landing refer to 3 3 4 EMERGENCY LANDING WITH ENGINE OFF Throttle lever blocked or engine not responding to power inputs 1 Throttle keep current setting 2 Land as soon as practicable 3 Perform emergency landing on selected airfield refer to 3 3 4 EMERGENCY LANDING WITH ENGINE OFF NOTE In case of thrott...

Page 74: ... TCU CAUTION light flashing 1 Throttle reduce to minimum acceptable 2 Oil pressure monitor 3 Land as soon as practicable 3 3 11 SUDDEN INCREASE IN ENGINE RPM AND MAP Possible overboost of turbocharger associated with TCU CAUTION light flashing 1 Throttle reduce immediately down to RPM MAP limits 2 Land as soon as practicable If Throttle is ineffective refer to 3 3 9 DEFECTIVE ENGINE CONTROLS ...

Page 75: ...elow if practicable to allow quicker cooling If variations continue after more than 30 seconds 3 TCU switch off 4 Continue flight adjusting power regarding OAT conditions and monitor engine parameters NOTE Normal air intake turbo heat rise is between 15 C at idle and 50 C at Full Power at ISA conditions Maximum airbox temperature before regulation is 88 C Leaving carburettor heater on with high po...

Page 76: ...e and red color in case of any primary parameter exceeding the red line low fuel below 20 L total quantity any sensor disconnected Refer to section 7 9 7 ENGINE for more information on the engine instrument operation NOTE Upon power up the RAL shows Red and yellow indicating it is functional Before each flight confirm that it is functional Non functioning RAL must be repaired before flight ...

Page 77: ... Reduce speed and MAP at least to maximum continuous limit Limited flying operation as boost pressure control may be unavailable or insufficient Reduce speed and boost pressure at least to maximum continuous limit Permanently on Cause N A The max admissible MAP is exceeded The lamp illumination will be deactivated if the MAP is reduced under 45 7 in Hg Remedy Reduce speed and MAP manually to be wi...

Page 78: ...heat close 5 Main Fuel Pump pull circuit Breaker 6 Fresh air venting open except if smoke comes in via those vents 7 Ignition switch off after the fuel in carburettors is consumed and engine has shut down 8 Emergency landing refer to 3 3 4 EMERGENCY LANDING WITH ENGINE OFF WARNING After engine fire never attempt to re start the engine NOTE Estimated time to empty carburetors after pumps are stoppe...

Page 79: ...ocedure on next page WARNING The Engine Monitoring System the radio and the transponder are not operational when the master switch is off NOTE Engine will continue to run with Master switch off as long as ignition is on providing power is supplied to Main Fuel pump by the Alternator 1 or the Battery see electrical system description in section Erreur Source du r envoi introuvable NOTE Flying with ...

Page 80: ...All switches off 8 ALT 2 switch on 9 All switches restore one by one waiting 10 seconds minimum between each Switch off bad circuit if smoke appears again 10 BATT switch on 11 Land as soon as practicable with canopy closed WARNING Never attempt to push an automatic pulled breaker after electrical fire CAUTION If conditions and location allows prefer landing as soon as possible instead of fire sour...

Page 81: ...d stop the aircraft If high vibrations at de rotation expect nose tyre depletion 1 Relieve weight on nose gear by applying back stick forces 2 If possible vacate runway at low speed and stop the aircraft 3 6 LANDING WITH DEFECTIVE BRAKES If aircraft veers off when applying brakes 1 Release brakes and apply rudder control to try to stay on runway 2 Apply smooth brake action on remaining brake as mu...

Page 82: ...dder pedals full rudder in direction opposite to spin 3 Longitudinal control forward 4 Lateral control ailerons neutral When rotation stops 5 Rudder pedals neutralize rudder immediately 6 Flaps UP if applicable 7 Lateral control use as required to level wings 8 Longitudinal control pull to level off avoiding stall warning WARNING Intentional spins are prohibited ...

Page 83: ...determine wind direction 2 Report your intention to land and the landing location via radio 3 Perform a low altitude pass into wind over the right hand side of the selected area with flaps extended as required and thoroughly inspect the landing area 4 Perform a circuit pattern 5 Perform normal approach and landing following procedures 4 4 12 and 4 4 14 6 After stopping the aircraft switch off all ...

Page 84: ...d in the logbook Exceeding of max admissible coolant temperature In case of one Coolant or EGT values out of tolerance for a single cylinder it may be the result of a loose sensor The aircraft should be serviced In case of several sensors indications in caution range Reduce engine power setting to the minimum necessary to maintain flight Carry out precautionary landing Oil temperature below 50 C I...

Page 85: ... pull lever slowly to avoid thermal shocks 2 Throttle increase If you fail to recover engine power land at the nearest airfield if possible or depending on the circumstances perform a precautionary landing according to paragraph 3 8 NOTE Progressive engine power decrease and associated EGT increase is a possible carburettor icing evidence and may occur when flying in visible moisture and below 15 ...

Page 86: ...y if corresponding equipment is switched on and dimmer is appropriate 2 Verify if corresponding circuit breaker is pushed 3 Assess situation and check voltage and amperage 4 Refer to section 7 13 MINIMUM INSTRUMENTS AND EQUIPMENTS FOR FLIGHT for flight continuation CAUTION Do not attempt to reset a tripped circuit breaker to avoid electrical fire ...

Page 87: ...wer consumption to ensure positive battery charge if required In the case of ALT 2 warning light illuminating 1 ALT 2 switch off for 10 seconds 2 ALT 2 switch on If ALT 2 warning light stays on 3 Switch off ALT 2 and other equipment to reduce power consumption to maximum 14 A consult table on next pages for total load calculation 4 Continue flight ensuring power consumption below 14 A in all cases...

Page 88: ...um only that which is absolutely necessary 3 Consider switching off Avionics 1 switch and pulling breaker of Backup Instrument Circuit Breaker to reduce current draw 4 Land as soon as practicable NOTE Failure of both alternators of the charge system will result in the main battery not being charged The engine will stop running when the battery is depleted about 30 min for a full battery The engine...

Page 89: ...1 5 EMS 1 2 GPS COM1 1 0 5 reception 4 Emission GPS NAV1 1 2 2 Audio Panel 1 0 8 Transponder 1 0 6 Reception 0 9 Emission Backup Instrument 1 2 Optional Radio COM2 function 1 0 6 Reception 4 2 Emission Optional Radio NAV2 function 1 0 6 Optional Heated Pitot 1 9 5 Stall Warning device 1 2 3 Landing light 1 1 2 Taxi light 1 1 2 Nav position Lights 2 0 5 1 total Strobe anti col Lights 2 1 2 total Pa...

Page 90: ...te Engine EMS G500TXi GTN650 COM2 Radio Flaps actuator In this case the Backup flight Instrument can be used until depletion of its standalone internal battery The percentage of remaining energy is indicated on the bottom left corner of the instrument when on battery mode The estimated autonomy with battery full vary between 30 min and 2 hours depending on the ambient temperature and screen bright...

Page 91: ...opy closed CAUTION Carbon Monoxide is clear and does not have any particular smell It is therefore not possible to detect it except if aircraft is equipped with a CO detector indicating possible contamination In case of other abnormal smell or fumes in cabin apply the same procedure NOTE Flying with canopy open is forbidden in normal condition In case of emergency canopy can be open up to 100 kts ...

Page 92: ... see table below Flap setting UP T O APP LD VFE KIAS N A 105 95 85 Approach speed KIAS 65 63 57 55 Landing distance 15m obstacle 585 560 495 475 Landing run 305 285 245 225 CAUTION Cruising with flaps extended will result in increased drag and higher fuel consumption Check fuel flow and evaluate remaining flight duration accordingly CAUTION Aircraft speed will increase in descent with flaps retrac...

Page 93: ...ormation on the PFD including a blank frozen or unresponsive display AHRS failure is indicated by the removal of the attitude heading information and a red X on the PFD Rate of turn information heading trend vector will not be available A heading failure will also occur as described in Section 3 2 1 ADC failure is indicated by Red X over the airspeed and altitude tapes Yellow X over the vertical s...

Page 94: ... alignment properly Continue to minimize maneuvering and seek smooth air for the first 5 minutes after the attitude becomes valid following the in air alignment restart If maneuvering or turbulence cannot be avoided carefully crosscheck the AHRS for correctness against other flight instruments NOTE PFD malfunctions or reboot must be recorded in the aircraft logbook or equivalent depending on the o...

Page 95: ...CTIONS If an ATTITUDE ALT or IAS monitor CAUTION is displayed in amber on the attitude display or airspeed altitude tape 1 Cross check flight instruments against all available information to determine which indications are correct 2 If installed check if heated pitot operative 3 Use correct instrument for end of flight ...

Page 96: ...ence instead of magnetic heading If GPS track is not available 1 Use standby compass for heading reference NOTE Without magnetic heading or GPS track the CDI provides no directional information Only course deviation information is presented and the orientation of the CDI is based on the selected course regardless of aircraft heading Course deviation indications will behave like a traditional CDI V...

Page 97: ...Display fan failure is indicated by an amber annunciation on the affected display Without fan cooling the affected display will overheat and shutdown 1 Prepare for loss of the affected display GPS Data Failure GPS data failure may be indicated by any or all of the following Loss of GPS course deviation information on HSI Amber LOI text on the PFD Amber DG text on the PFD Amber NO GPS POSITION text...

Page 98: ... on HSI 1 Select alternate navigation source or refer directly to external navigation data AHRS ALIGN If an AHRS ALIGN Keep Wings Level annunciation is displayed on the attitude indicator in flight limit aircraft operation to 10º bank 5º pitch NOTE For aircraft equipped with optional COM2 NAV2 radio a failure of COM2 will generate a NAV2 failure message on the PFD This is due to the fact that the ...

Page 99: ...S201 AFM 3 EMERGENCY PROCEDURES 3 10 OTHER EMERGENCIES 27 06 2019 SONAIR S2 D MAN 006 Page 3 37 Rev A 3 10 8 PFD WARNINGS CAUTIONS AND ALERTS WARNINGS CAUTIONS and Advisories ...

Page 100: ...S201 AFM 3 EMERGENCY PROCEDURES 3 10 OTHER EMERGENCIES 27 06 2019 SONAIR S2 D MAN 006 Page 3 38 Rev A ...

Page 101: ...S201 AFM 3 EMERGENCY PROCEDURES 3 10 OTHER EMERGENCIES 27 06 2019 SONAIR S2 D MAN 006 Page 3 39 Rev A ...

Page 102: ...M 3 EMERGENCY PROCEDURES 3 10 OTHER EMERGENCIES 27 06 2019 SONAIR S2 D MAN 006 Page 3 40 Rev A Terrain Alerts Optional Initiate maximum performance climb maximum takeoff power and best angle of climb airspeed ...

Page 103: ...e restoration of the navigation functions as soon as possible Baro alt input failure Barometric altitude is required for descent VNAV functionality and automatic sequencing of altitude terminated legs If the BARO altitude input to the GTN has failed enroute barometric VNAV will not be available The pilot will also be required to manually sequence any altitude terminated legs Temperature input fail...

Page 104: ...EMORY ERROR message is displayed and the instrument becomes inoperable If this occurs the unit must be returned to the factory for service Degraded Attitude During mode errors in pitch or roll may be observed during long accelerations or decelerations however attitude information is always available it is never removed or made un available Errors will not exceed TSO limit specifications When a cro...

Page 105: ...t to reacquire TSO criteria performance The CROSS CHECK message will automatically clear once normal operations are resumed Attitude Re alignment In the case where a manual attitude alignment is required initiate the following alignment procedure Attitude roll pitch alignment may be performed by momentarily pressing the rotary knob to present the brightness adjust menu then pressing and holding th...

Page 106: ...rspeed as follows In Flight If airspeed is above 40 knots transition will occur to battery with no pilot action required Only the amber ON BATTERY indication will be shown no other popup menus or messages will be presented On Ground If airspeed is below 30 knots a shutdown timer will be displayed If the pilot takes no action the unit will automatically shut down in approximately 45 seconds This is...

Page 107: ... 1 Rev A 4 NORMAL PROCEDURES 4 1 TABLE OF CONTENT 4 1 TABLE OF CONTENT 4 1 4 2 INTRODUCTION 4 2 4 3 AIRPSPEEDS FOR NORMAL OPERATING PROCEDURES 4 2 4 4 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4 3 4 5 HIGH ALTITUDE OPERATION 4 34 4 6 STALL BEHAVIOUR 4 34 4 7 ENGINE FAILURE TRAINING 4 35 ...

Page 108: ...KIAS REMARKS Vx Best Angle of Climb Speed 65 The speed at MTOW flaps fully retracted which results in the greatest altitude gain over a given horizontal distance i e largest climb angle VY Best Rate of Climb Speed 70 The speed at MTOW flaps fully retracted which results in the greatest altitude gain over a given time period VLOF Lift off Speed 55 The speed at which the aircraft lifts off the groun...

Page 109: ...field maintenance activities Incomplete or careless inspection can result in an accident Carry out the inspection following the instructions in the Inspection Check List The next page presents the steps to inspect the S201 before flight Then the following pages list inspection points to perform at each step NOTE The word condition in the instructions means a visual inspection of surface for cracks...

Page 110: ...S201 AFM 4 NORMAL PROCEDURES 4 4 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 27 06 2019 SONAIR S2 D MAN 006 Page 4 4 Rev A 1 2 3 4 5 6 7 ...

Page 111: ...aps move to LD setting Master switches off Avionics verify condition Control System visual inspection free movement up to stops no abnormal play in stick Brakes push on both pedals and engage parking brake check for no leaks in the cockpit Canopy attachment condition clean Cockpit check for loose objects Fire extinguisher verify presence correct support attachment safety pin in place and pressure ...

Page 112: ...ges control horn bolts and pushrod check free motion and condition Wing tip check condition Strobe Nav light and lens check for condition Pitot tube security unobstructed remove cover Leading edge condition check OK no deformations no cracks Taxi landing lights and lens check for cracks and condition Fuel level open fuel cap and check fuel level Fuel vent underside of wing unobstructed Access Hatc...

Page 113: ...htened Check Engine mount and exhaust manifold condition Check for visible oil leaks Engine cowling condition check Propeller and spinner condition check Radiators and circuits Oil Water check for leaks or dirt Air intakes check Gascolator drain Through RH access door Repeat same checks as for LH door plus Coolant overflow bottle check level in the overflow bottle replenish as required Open oil ta...

Page 114: ...d the Max level Close oil tank with cap Close access doors LH then RH rotate fasteners in airstream direction to close Check secured Tyre condition inflation wear Wheels security general condition Wheel fairing check attachments and no cracks Wheel strut general condition no cracks Chocks and tie down ropes remove Suspension and undercarriage test by gently pulling downward on propeller blades roo...

Page 115: ...ck condition Strobe Nav light and lens check for condition Wing trailing edge check condition Aileron check freedom of movement check surface condition Aileron attachments and hinges control horn bolts pushrod check free motion and condition Flap hinges control horn bolts and pushrod check free motion and condition Chocks Ropes Remove Wheel fairing check attachments and no cracks Wheel and brakes ...

Page 116: ...D MAN 006 Page 4 10 Rev A 8 Right Fuselage Access Hatches underside of cabin present and properly closed Surface condition check Wing fuselage fairings check Access doors under rear fuselage closed Static Port unobstructed and clean Antenna e check condition and attachments Empennage fairing check ...

Page 117: ...nnage Tie down rope removed Antenna e check condition and attachments Horizontal and vertical stabilizers check condition Hinges control horns bolts pushrods check free motion and condition Elevator check for free movement and condition Tab check for secure attachment and condition Rudder check for secure attachment and condition ...

Page 118: ... 2019 SONAIR S2 D MAN 006 Page 4 12 Rev A 7 Left Fuselage Empennage fairings check Surface condition check Antenna e check condition and attachments Access doors under rear fuselage closed Static Port unobstructed and clean Wing fuselage fairings check Ground Power Supply unplugged ...

Page 119: ...inent engine start i e switch on the strobe before starting the engine 1 Pre flight inspection completed 2 Weight and Balance calculated and within range see chap 6 3 Emergency equipment on board 4 Passenger briefed 5 Seats seatbelt and harnesses adjust and secure 6 Brakes parking brake on 7 Throttle free movement on full actuation range 8 Canopy closed and latched not mandatory 9 TCU switch alway...

Page 120: ...cated fuel tank levels are in accordance with visual checks during pre flight inspection verify REM fuel parameter is in line with fuel tank level correct using Refuel function if required Refer to section 7 9 7 reset fuel used see Caution below CAUTION Always check EMS fuel level indication before flight and compare with visual level checked during pre flight inspection Always reset fuel used and...

Page 121: ...s operative check if no errors are indicated on GPS and PFD after start up set PFD screen layout in recommended layout for start up and take off refer to 7 7 5 7 Avionics 2 Switch on wait for Backup Instrument battery warm up and instrument self calibration Do not move the aircraft during calibration check if no errors indicated on screen 8 PFD and Backup Instrument check both indicating airspeed ...

Page 122: ...mpt if start fails See Caution below Immediately after engine start up 6 Throttle adjust for smooth running at 2000 rpm 7 Oil pressure check if in green range within 10 seconds 8 EMS verify battery charging 9 Choke cold engine if used gradually release 10 Avionics switches both on 11 Warm engine 2000 rpm for 2 minutes then 2500 rpm until oil temp is 50 C WARNING Do not operate the aircraft if any ...

Page 123: ...ne rpm only as required to keep oil pressure steady Refer to section 2 5 1 for RPM Pressure and Temperature limitations To avoid shocks in the gearbox start the engine with the throttle lever set to idle if Choke is used or 10 open at maximum when engine is already warm Oil Temperature above 40 C then wait 3 seconds for engine to reach constant speed before accelerating engine rpm NOTE It is good ...

Page 124: ...al position or as required for wind 6 Power and brakes as required 7 Brakes check 8 Instruments check Apply power and brakes as needed Apply brakes to control movement on ground Taxi carefully when wind velocity exceeds 15 knots Hold the control stick in neutral position or as required using conventional techniques CAUTION Failing to apply pressure on brake pedals while releasing the parking brake...

Page 125: ...uel selector fullest tank 7 Choke off 8 Carburettor heater off 9 Auxiliary Fuel Pump on 10 Ignition Switch both circuits 11 Throttle adjusted for 4000 RPM 12 Switch to Magneto L check RPM drop 500RPM 13 Ignition Switch both circuits 14 Switch to Magneto R check RPM drop 500RPM 15 Ignition Switch both circuits CAUTION Always ensure Oil Temperature above 50 C before increasing engine speed above 250...

Page 126: ...xiliary Fuel Pump on 22 Throttle Max Continuous Power 23 Throttle Full Power 24 Check engine parameters RPM stabilized around 5200 RPM typical value for no wind ISA condition all Pressures and Temperatures within green ranges no abnormal vibrations 25 Reduce Power to idle If Oil Temperature above 100 C cool down shortly the engine at 3000 RPM before Take Off procedure NOTE Only one ignition circui...

Page 127: ...y as required 4 Auxiliary fuel pump check on 5 Instruments verify all 6 Altimeter set QNH QFE 7 Engine parameters verify temperatures pressures current voltage 8 Fuel quantity confirm as required 9 Circuit breakers all in 10 Flaps T O setting 11 Fuel selector check on fullest tank 12 Trim T O setting 13 Canopy check closed and latched 14 Safety harnesses on and tight CAUTION If carburetor heater i...

Page 128: ... 63 KIAS at height of 50 ft AGL 7 Flaps UP setting above 300 ft AGL at min 65 KIAS 9 Auxiliary fuel pump off above 300 ft AGL 10 Brakes apply briefly brakes to stop wheel rotation 11 Transition to climb CAUTION Ensure that engine oil temperature is above 50 C prior to take off WARNING Take off is prohibited if The engine is running unsteadily or intermittently The engine parameters instrument indi...

Page 129: ...s verify Oil temperature and pressure Coolant temperature within limits CAUTION If the coolant temperature or oil temperature approach their limits reduce the climb angle to increase airspeed and thus fulfill the limits WARNING Fuel level indication on EMS is only accurate when aircraft is in level flight attitude During climb there is less fuel than indicated and during descent there is more fuel...

Page 130: ...06 2019 SONAIR S2 D MAN 006 Page 4 24 Rev A 4 4 10 CRUISE Refer to section 5 for recommended cruising speeds WARNING Avoid using a tank below 3 L as engine stoppage will result When one tank is empty or close to empty the fuel selector valve should be switched to the fullest tank ...

Page 131: ...ine temperature for cooling see Caution hereunder Expect fuel consumption of about 17 L h during cruise descent WARNING Fuel level indication on EMS is only accurate when aircraft is in level flight attitude During climb there is less fuel than indicated and during descent there is more fuel than indicated Always check fuel level before initiating a climb descent to ensure sufficient fuel reserve ...

Page 132: ...4 4 21 4 Speed and Flaps settings sequentially Flaps setting Speed UP Descent speed 105 KIAS T O 105 95 KIAS APP 95 85 KIAS 5 Trim position as required 6 Fuel selector fullest tank 7 Parking brake valve check off 8 Brake check symmetrical pressure on pedals CAUTION During traffic pattern EMS Remaining Fuel is the most accurate indication Crosschecking with fuel gages will be performed only if the ...

Page 133: ...age 4 27 Rev A 4 4 13 ON FINAL 1 Flaps LD setting 2 Approach speed 65 to 55 KIAS 3 Throttle as required to achieve 3 slope 4 27pprox 2800 RPM 4 4 14 LANDING 1 Speed on final VREF 55 KIAS at 50 ft AGL 2 Throttle reduce to idle at 4 27pprox 50 KIAS 3 Nose wheel gently lower to ground 4 Apply brakes as required ...

Page 134: ...nsition to level 2 Throttle Full Power max 5800 RPM for max 5 min 3 Carburettor heater push to close if open 4 Wing flaps retract to T O as soon as possible and UP when reaching 65 knots at 300 ft minimum height 5 Airspeed VX 65 KIAS 6 Trim as required 7 Auxiliary fuel pump off 300 ft minimum 8 Landing light off 9 EMS Remaining fuel check for sufficient quantity ...

Page 135: ... 006 Page 4 29 Rev A 4 4 16 AFTER LANDING 1 Vacate runway 2 Engine speed set as required for taxi 3 Wing flaps UP setting 4 Throttle reduce during taxi to ensure max 2500 RPM if Oil Temperature below 50 C CAUTION Taxi with reduced speed on soft grass or uneven airfields to avoid propeller ground strike ...

Page 136: ... Wait for minimum 2 minutes between throttle setting reduction and ignition switch off to allow engine to cool down 5 Ignition off 6 All electrical systems switches off 7 Master switches off 8 Fuel selector off CAUTION Under normal conditions the engine temperatures stabilize during descent landing and taxi at values suitable to stop the engine If necessary cool for minimum 2 minutes the engine at...

Page 137: ...Fuel selector off 5 Parking brake use as necessary only for short period parking below one day 6 Wheel chocks use as necessary for long term parking above one day 7 Secure the airplane refer to section 8 5 5 for more information Move control stick rearward and secure it together with the seat belt bottom laps Use the anchor eyes on the wings and fuselage rear section to secure the airplane to the ...

Page 138: ...and dim as required 2 Rear red cabin light turn on to illuminate cabin and panel as required 3 EMS PFD GPS Backup displays dim as required using automatic dimming function or manual controls refer to section 7 7 and 7 9 7 NOTE The rear red cabin light can be turned on off using the switch located immediately next to the light The luminosity of the light can be adjusted using the instrument panel d...

Page 139: ...s Take off Climb and Go Around carburettor heater off pitot heat on optional equipment Flight carburettor heater on open slowly to avoid thermal shock pitot heat on optional equipment Descent Approach Landing carburettor heater on pitot heat on optional equipment After Landing pitot heat off optional equipment CAUTION Always close carburettor heater during operation at maximum continuous power or ...

Page 140: ...ITUDE OPERATION Not covered in basic S201 configuration Refer to limitations section 2 11 1 4 6 STALL BEHAVIOUR Refer to Section 5 3 4 for stall behaviour information WARNING In case of suspicion of dust or dirt in fuel do not refuel the aircraft NOTE The operator of the aircraft must select a standard operating fuel and establish its Approved Maintenance Program in accordance with the selected fu...

Page 141: ...roach adjust landing pattern in order to be at an adequate height above the landing spot during approach 7 Flaps as required 8 Speed approach between 55 60 KIAS as required to maintain desired glideslope and depending on flaps setting 9 Gently touch down on main wheels at 55 KIAS 10 Nose wheel maintain above ground using elevator control until airspeed below 50 KIAS then gently lower to ground 11 ...

Page 142: ...course pointer may autoslew to the correct course when using GPS navigation When using VLOC navigation the course pointer will not autoslew and must be rotated to the correct course by the pilot CAUTION The pilot must verify the active course and waypoint for each flight plan leg The pilot must verify proper course selection each time the CDI source is changed from GPS to VLOC ...

Page 143: ... AFM 5 PERFORMANCE 5 1 TABLE OF CONTENT 27 06 2019 SONAIR S2 D MAN 006 Page 5 1 Rev A 5 PERFORMANCE 5 1 TABLE OF CONTENT 5 1 TABLE OF CONTENT 5 1 5 2 INTRODUCTION 5 2 5 3 PERFORMANCE TABLES AND DIAGRAMS 5 3 ...

Page 144: ...off performance and non approved additional information The data in the charts has been computed from actual flight tests with the aeroplane and engine in good condition and using average piloting techniques If not stated otherwise the performance stated in this section is valid for maximum take off weight 750 kg and under ISA conditions canopy closed landing gear fairing installed ...

Page 145: ...ED CALIBRATION The data present Calibrated Airspeed CAS versus Indicated Airspeed IAS assuming zero instrument error The calibration is applicable for all flaps settings KIAS kts CAS kts KIAS kts CAS kts 38 40 92 95 43 45 97 100 48 50 102 105 53 55 106 110 58 60 111 115 63 65 116 120 67 70 121 125 72 75 126 130 77 80 131 135 82 85 136 140 87 90 141 145 ...

Page 146: ...S201 AFM 5 PERFORMANCE 5 3 PERFORMANCE TABLES AND DIAGRAMS 27 06 2019 SONAIR S2 D MAN 006 Page 5 4 Rev A 40 50 60 70 80 90 100 110 120 130 140 40 50 60 70 80 90 100 110 120 130 140 CAS kts KIAS kts ...

Page 147: ...67 66 0 59 15 87 85 84 82 80 79 78 76 75 74 72 71 70 69 68 67 66 2000 52 11 87 85 83 81 80 78 77 76 74 73 72 70 69 68 67 66 65 4000 45 7 86 84 82 81 79 78 76 75 73 72 71 70 68 67 66 65 64 6000 38 3 85 83 82 80 78 77 75 74 73 71 70 69 68 66 65 64 63 8000 30 1 84 82 81 79 77 76 74 73 72 70 69 68 67 66 64 63 62 10000 23 5 83 81 80 78 76 75 73 72 71 69 68 67 66 65 63 62 61 12000 16 9 82 80 79 77 75 74...

Page 148: ...85 84 82 81 79 78 77 76 74 4000 45 7 98 96 94 92 91 89 87 86 84 83 81 80 78 77 76 75 73 6000 38 3 97 95 93 91 90 88 86 85 83 81 80 79 77 76 75 74 72 8000 30 1 96 94 92 90 88 87 85 83 82 80 79 78 76 75 74 73 71 According to the above tables the correction at all altitudes is approximately 5 for an increase of temperature of 15 C with respect to ISA temperature and 10 for an increase of temperature ...

Page 149: ...S201 AFM 5 PERFORMANCE 5 3 PERFORMANCE TABLES AND DIAGRAMS 27 06 2019 SONAIR S2 D MAN 006 Page 5 7 Rev A 5 3 3 PRESSURE ALTITUDE DENSITY ALTITUDE ...

Page 150: ...Flaps LD KIAS CAS KIAS CAS KIAS CAS KIAS CAS 0 1 00 51 49 50 47 45 42 44 41 15 1 04 52 50 51 48 45 43 45 42 30 1 15 55 53 53 51 48 45 47 44 45 1 41 60 58 58 56 52 50 51 49 60 2 00 70 69 68 67 61 59 60 58 When approaching stall speed the aircraft will start gently buffeting If airspeed is further reduced the aircraft will lose lift which results in a stalls Depending on CG the aircraft nose may not...

Page 151: ...and for any weight balance configuration within the approved limits 5 3 5 WIND COMPONENTS The maximum demonstrated cross wind component for take off and landing is 19 kts CAUTION Always maintain the aircraft in straight flight no slip using gentle rudder and ailerons control inputs during stall Failing to do so will result in spin The aircraft nose is off centered by 3 from the aircraft centerline...

Page 152: ...m Grass Apply following multiplying factors to distance on concrete surface Dry grass 1 2 Wet grass 1 3 NOTE The following factors are to be applied to the computed take off distance for the noted condition Headwind Subtract 6 m 20 ft from table distances for each knot headwind Tailwind Add 24 m 79 ft from table distances for each knot tailwind up to 10 knots Sloped Runway Increase decrease table ...

Page 153: ...70 470 470 470 475 480 485 490 1000 470 470 470 475 480 490 495 500 505 510 510 510 510 510 2000 500 510 515 520 525 525 525 525 525 530 535 540 550 555 3000 540 540 540 540 545 555 560 565 570 570 570 575 575 575 4000 565 575 580 590 590 590 590 590 595 605 610 620 625 630 5000 610 610 610 615 620 630 640 645 650 655 655 660 665 670 6000 645 655 665 670 675 680 680 685 695 700 705 710 720 725 700...

Page 154: ...ft 30 20 10 0 10 20 30 0 14 13 13 12 11 10 9 2000 14 13 12 11 10 9 9 4000 13 12 11 10 10 9 8 6000 12 11 11 10 9 8 8 8000 11 11 10 9 8 8 7 Climb rate at VY 10 ft min Delta with ISA C AP ft 30 20 10 0 10 20 30 0 915 865 810 760 710 655 620 2000 875 825 770 720 670 620 585 4000 830 780 730 680 635 585 550 6000 785 735 690 625 595 550 515 8000 735 690 630 585 555 510 480 CAUTION Maximum take off power...

Page 155: ...ISA C AP ft 30 20 10 0 10 20 30 0 915 865 810 760 710 655 620 2000 875 825 770 720 670 620 585 4000 830 780 730 680 635 585 550 6000 785 735 690 625 595 550 515 8000 735 690 630 585 555 510 480 Climb Angle at Vx 0 Delta with ISA C AP ft 30 20 10 0 10 20 30 0 13 12 11 11 10 9 9 2000 12 12 11 10 9 9 8 4000 12 11 10 9 9 8 8 6000 11 10 10 9 8 8 7 8000 10 10 9 8 8 7 7 CAUTION Maximum take off power sho...

Page 156: ...AS for best climb rate of 540 ft min Climb rate at VY 0 ft min Delta with ISA C AP ft 30 20 10 0 10 20 30 0 670 865 585 540 495 450 420 2000 630 825 545 500 460 415 390 4000 590 780 505 465 425 385 355 6000 545 735 470 415 390 350 325 8000 505 690 415 380 355 315 290 Climb Angle at Vx 0 Delta with ISA C AP ft 30 20 10 0 10 20 30 0 10 13 9 8 7 7 6 2000 10 13 8 8 7 6 6 4000 9 12 8 7 6 6 5 6000 8 11 ...

Page 157: ...00 93 97 25 479 5000 98 102 27 450 5500 112 115 34 393 4000 7 4500 84 92 19 619 4800 93 100 23 546 5000 98 105 25 508 5500 112 118 31 437 6000 3 4500 84 95 17 727 4800 93 103 20 628 5000 98 108 23 578 5500 112 122 29 488 8000 1 4500 84 97 15 868 4800 93 106 18 729 5000 98 112 21 664 5500 112 126 27 548 10000 5 4500 84 101 12 1058 4800 93 110 16 859 5000 98 115 19 769 5500 112 130 25 620 add or sub...

Page 158: ... 225 m 730 ft 475 m 1560 ft Grass Apply following multiplying factors to distance on concrete surface Dry grass 1 2 Wet grass 1 4 NOTE The following factors are to be applied to the computed landing distance for the noted condition Headwind Subtract 6 m 20 ft from table distances for each knot headwind Tailwind Add 24 m 79 ft from table distances for each knot tailwind up to 10 knots Sloped Runway...

Page 159: ...75 475 475 475 480 480 485 485 1000 475 475 475 475 480 480 480 485 485 490 495 495 500 500 2000 475 480 485 485 490 495 495 500 505 505 510 515 515 520 3000 490 495 500 505 505 510 515 515 520 525 525 530 535 535 4000 510 510 515 520 525 525 530 535 535 540 545 545 550 555 5000 525 530 535 535 540 545 550 550 555 560 560 565 570 570 6000 545 545 550 555 560 560 565 570 575 575 580 585 590 590 700...

Page 160: ...Vx 30 60 KIAS with a climb angle of 8 4 Climb Angle Delta with ISA C AP ft 30 20 10 0 10 20 30 0 9 8 8 7 7 6 6 2000 8 8 7 7 6 6 5 4000 8 7 7 6 6 5 5 6000 7 7 6 6 5 5 5 8000 7 6 6 5 5 5 4 The corresponding rate of climb for the climb angles are given below Climb Rate Delta with ISA C AP ft 30 20 10 0 10 20 30 0 615 560 510 460 405 355 320 2000 560 510 460 410 360 310 275 4000 510 460 410 360 310 26...

Page 161: ... 16 Volume I Part II Chapter 10 Amendment 11 10 4 b and as the aircraft Maximum Take Off Mass of the S201 is 750 kg the maximum permitted Noise Level to be met is 74 25 dB A It has been demonstrated that the noise level using the standard Take Off and Climb procedure in ISA condition at sea level is Propeller pitch setting angle Noise Level 25 67 9 dB A 0 6 dB a ...

Page 162: ... D MAN 006 Page 6 1 Rev A 6 WEIGHT AND BALANCE 6 1 TABLE OF CONTENT 6 1 TABLE OF CONTENT 6 1 6 2 INTRODUCTION 6 2 6 3 DATUM PLANE AND REFERENCES 6 2 6 4 WEIGHT AND CENTER OF GRAVITY LIMITS 6 3 6 5 MASS AND BALANCE REPORT 6 4 6 6 AIRCRAFT WEIGHING 6 6 6 7 EQUIPMENT LIST 6 6 ...

Page 163: ...ircraft weighting including the installed equipment during the weighing of the aircraft are contained in the applicable Maintenance Manual Ref SONAIR S2 D MAN 002 S201 6 3 DATUM PLANE AND REFERENCES Reference description Reference location Datum point Centre of firewall front surface bottom edge engine side Longitudinal horizontal reference Upper surface of canopy left slide Transversal horizontal...

Page 164: ...Page 6 3 Rev A 6 4 WEIGHT AND CENTER OF GRAVITY LIMITS Metric Imperial of MAC Forward limit 0 876 m 2 873 ft 20 Rear limit 1 034 m 3 392 ft 32 Maximum Take Off Weight 750 kg or 1650 lbs The Weight and CG of the Aircraft must always be within the limits depicted in the following centrogram in kg vs MAC ...

Page 165: ... authorized range WARNING Aircraft CG and MTOW limitations must be adhered to at all times WARNING For each flight the most forward CG i e with take off fuel and the most rearward CG i e with landing fuel must be calculated and must be within aircraft CG range and weight limits NOTE Fuel weight kg is fuel volume liters x fuel density 0 72 for Avgas NOTE All Mass and Balance calculations are made u...

Page 166: ...T mass x arm kg mm 1 Empty aircraft WE 2 Pilot passenger 1150 3 Baggage Area 1 1500 4 Baggage Area 2 2296 5 Fuel Mass at TO 706 6 TOTAL at TO 1 thru 5 CG position MAC 7 Estimated mission Fuel burn Mass 706 8 Total at Landing 6 7 CG position MAC INFORMATION CG position Moment Mass CG position in MAC 100 CG position 612 mm 1318 mm ...

Page 167: ...hting the empty aircraft is a maintenance task performed by an approved Maintenance Organisation Refer to the SONACA S201 Maintenance Manual for aircraft weighing instructions This is needed periodically or when a modification or a repair is made to the aircraft 6 7 EQUIPMENT LIST ITEM Metric Weight Arm Moment kg mm kg mm ...

Page 168: ...7 1 TABLE OF CONTENT 7 1 7 2 INTRODUCTION 7 2 7 3 AIRFRAME 7 3 7 4 FLIGHT CONTROLS 7 4 7 5 INSTRUMENT PANEL 7 10 7 6 WARNING CAUTION AND STATUS LIGHTS 7 14 7 7 INSTRUMENTS AND AVIONICS 7 15 7 8 FLIGHT CREW AND CABIN 7 53 7 9 POWERPLANT 7 60 7 10 FUEL SYSTEM 7 76 7 11 ELECTRICAL SYSTEM 7 84 7 12 LANDING GEAR 7 92 7 13 MINIMUM INSTRUMENTS AND EQUIPMENTS FOR FLIGHT 7 95 ...

Page 169: ...n provides description and operation of the aeroplane and its systems It includes a basic description of the airframe the control systems the cabin and instrument panel as well as key elements of the aircraft like powerplant anemometric system and landing gear Refer to Section 9 Supplements for details of optional systems and equipment ...

Page 170: ...of 6061 T6 aluminium alloy sheet assembled by the means of blind rivets with exception of the main spar being built of 2024 T3 aluminium alloy This high strength aluminium alloy construction provides long life and low maintenance costs thanks to its durability and corrosion resistant characteristics The wing has a high lift airfoil having the advantage of being only slightly sensitive to rain and ...

Page 171: ...to pedals The nose gear is controlled by pushrods permanently linked to pedals Flaps are controlled by pushrods and torque tubes linked to an electrical actuator located in the centre console The elevator trim tab is controlled by a push pull cable 7 4 1 CONTROL STICKS The aircraft is equipped with dual control sticks The control sticks operate in the standard pitch and roll elevator and aileron c...

Page 172: ...S201 AFM 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 4 FLIGHT CONTROLS 27 06 2019 SONAIR S2 D MAN 006 Page 7 5 Rev A 7 4 2 AILERON CONTROLS 7 4 3 ELEVATOR CONTROL ...

Page 173: ...down correction and moving it rearward will apply pitch up correction A trim level indicator is provided left of the actuation wheel indicating on a mobile scale the current trim tab position The indicator provides a blue area for nose down trimming a white area for nose up trimming and a green area near the centre to indicate the take off position WARNING Always select take off position before ta...

Page 174: ...GHT CONTROLS 27 06 2019 SONAIR S2 D MAN 006 Page 7 7 Rev A 7 4 5 RUDDER PEDALS AND NOSE WHEEL STEERING The aircraft is fitted with nonadjustable dual rudder pedals which control the rudder and steer the nose wheel Refer to section 0 for seat adjustment ...

Page 175: ...chanical flap indicator located next to the lever shows the current flap position The flap motor is located in the cabin centre console The two wing flaps are interconnected via a torque tube which is driven at a single point by the flap motor In case of a failure in the linkage system this prevents the flaps from being deployed to asymmetrical positions See section 7 5 for the location of the fla...

Page 176: ... LD 30 The flap controller is powered from the main bus The flap controller in turn powers the flap motor via a circuit breaker located on the instrument panel refer to paragraph 7 5 The Flap control necessitates a power up time of 11 sec The Flap cannot be actuated during that period of time WARNING The flap system becomes non operational with loss of power to the main bus The main bus is powered...

Page 177: ...1 model Instrument panel features traditional flight instruments an Engine Monitoring System EMS a radio and transponder a VOR indicator equipment switches and breakers a cabin heating control a glove box an optional RAM mount for portable equipment and a 12V auxiliary plug The layout is a follow 1 2 3 4 14 5 6 9 16 13 15 7 11 12 17 18 10 8 ...

Page 178: ...art Button 2 Engage starter motor Push On Ignition Key 3 Disconnect Ignition Full Left OFF Select Ignition R Middle 1 R Select Ignition L Middle 2 L Select Ignition R L Full Right BOTH PFD 4 Garmin G500 TX I Primary Flight Display See section 7 7 5 1 Audio Panel 5 Garmin GMA345 Distribute audio to crew See section 7 7 6 1 GPS 6 Garmin GTN 650 GPS Navigator with integrated Radio and Transponder See...

Page 179: ...uipment switches 11 From Left to right TCU Freeze the turbo waste gate position when off AVI 1 Switches Audio Panel and GPS AVI 2 Switches COM2 and Backup Instrument Instrument lights Switches instrument integrated lighting Anti collision lights Switches strobe lights Navigation lights Switches position lights Landing light Switches landing light s Taxi light Switches taxi light s Aux fuel pump Sw...

Page 180: ...ushed normal operation Carburettor heater 15 Engage carburettor heater Pulled heater on Pushed heater off Circuit breaker board 16 Circuit breakers for all electrical systems Refer to section Erreur Source du r envoi introuvable Cabin heat system 17 Top lever windscreen defogging Middle lever feet heating Bottom lever heating control Left closed Right open Refer to section 7 8 5 Aux 12V Plug 18 12...

Page 181: ...top centre of the instrument panel as described below All warning lights except the EMS RAL can be dimmed by turning the light housing and can be tested by pushing on them The EMS RAL features a self test at start up of the EMS display Refer to sections 3 10 3 3 3 13 and 3 3 14 for information on causes and adequate action in case of warning light illumination EMS Remote Alert LED ALT 1 Charge cau...

Page 182: ... GPS Provide GPS NAV COM and Remote XPDR control functionalities Refer to section 7 7 6 2 8 JPI EDM900 Engine Monitoring System Refer to section 7 9 7 Refer to section 7 9 7 Not shown Garmin GTX 335 R Transponder Mode A C S ADS B compatible Refer to section 1 8 10 Backup Flight Instrument KI300 Display Flight information Refer to section 7 7 5 2 7 Optional Garmin GNC 255A COM2 NAV2 radio 8 33 25kH...

Page 183: ...ND AVIONICS 27 06 2019 SONAIR S2 D MAN 006 Page 7 16 Rev A 7 7 2 VACUUM SYSTEM The S201 is not equipped by a traditional vacuum system Instead all instruments use electric power to generate attitude and directional information Refer to 7 7 5 for more information ...

Page 184: ...ment line Static ports are located on both sides of the rear fuselage Both ports are joined to equalize pressure A drain bottle is located under the co pilot seat to evacuate moisture and is checked during maintenance activities The Altimeter ASI VSI and alticoder are connected to this line Keep the pitot head clean to ensure proper functioning of the system Ensure that the Pitot tube cover is rem...

Page 185: ... moist weather condition it is recommended to switch the pitot heater on to avoid pitot icing Icing can be recognized by an indicated airspeed increase in level flight without increasing throttle In case of icing switching the pitot heat should be sufficient to eliminate ice from the pitot tube After landing it is recommended to switch off the pitot as soon as possible to avoid unnecessary current...

Page 186: ...g connected to a buzzer in the cockpit The system is programmed to start alerting the pilot between 5 and 10 KIAS before the wing stall Refer to section 4 6 for stall behaviour information NOTE When approaching stall speed aileron and elevator controls might have a reduced effect on aircraft motion It is recommended to keep sufficient margin on airspeed during take off approach and landings ...

Page 187: ... pilot PFD functions are supported by an integrated AHRS ADC a magnetometer and a link to the GTN 650 GPS A detailed G500Txi Pilot s Guide is available as well as trainer software applications See section 1 8 for source documentation A power button is provided at the top right corner of the bezel on each display When the display is ON pressing the power button results in an onscreen menu with cont...

Page 188: ...s and shading Display range can be controlled using two finger pinching Map panning can be accomplished using single finger swiping The enhanced HIS map display range can be controlled using two finger pinch or single finger swipe Display brightness Display brightness is controlled automatically based on input to a bezel mounted photocell The brightness level can be manually adjusted using control...

Page 189: ...S201 AFM 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 7 INSTRUMENTS AND AVIONICS 27 06 2019 SONAIR S2 D MAN 006 Page 7 22 Rev A Colors The following colors are used consistently within the Txi system ...

Page 190: ...essing the Split Full button indicated below PFD configuration MFD configuration The integrated EHSI can be set up as standard HSI or with a Minimap overlay The standard view is better suited to radio navigation while the Minimap overlay is better suited to GPS navigation Both modes are shown on the pictures below Switching from one mode to the other is performed via the Menu button located to the...

Page 191: ...tor button Standard HSI configuration In the case where no VOR or GS signal is received no flag will appear on the EHSI However the green indicator will not be displayed on it until a signal is received Primary Flight Data The PFD displays attitude heading airspeed barometric altitude and vertical speed data Airspeed and altitude displays include a six second trend indicator Pilot selectable bugs ...

Page 192: ...30 nose down or 50 nose up Slip skid information is shown using a white trapezoid below the sky pointer Synthetic Vision Technology Optional SVT may optionally be provided to assist the pilot in maintaining situational awareness with regard to the terrain obstacles and traffic surrounding the aircraft Enabling this option is done by purchasing the software and installing it by the mean of a SD Car...

Page 193: ...le display of heading marks displayed just above the horizon line on the PFD Airport Signs pilot selectable signposts displayed on the synthetic terrain display indicating the position of nearby airports that are in the G500 G600 database Runway Highlight a highlighted presentation of the location and orientation of the runway s at the destination airport The synthetic terrain display is intended ...

Page 194: ...ions The airspeed tape does not adjust these additional markings including VNO landing gear or flap speed limitations for variations with aircraft weight altitude or other factors Airspeed reference bugs are provided on the airspeed tape on are pilot configurable via Menu Airspeeds True airspeed and groundspeed are displayed below the airspeed tape and are always in knots Barometric Altitude and V...

Page 195: ...DI source selection can be synchronized across multiple Txi PFDs if enabled by the pilot Automation of CDI source selection and course selection is provided in the following situations Localizer CDI Switch Prompting the CDI button on the PFD will flash when established on the final approach course of a LOC based approach if the CDI source is GPS This serves as a reminder to change the CDI source t...

Page 196: ...dition the HIS can display two simultaneous bearing pointers sourced from GPS or VHF NAV DME distances can be displayed adjacent to the HSI The bearing pointer display and navigation source are pilot controlled under the PFD Menu HSI Setup Bearing Pointers sub menu An enhanced HIS may be selected by the pilot under the PFD Menu HSI Options sub menu The enhanced HSI includes an integral moving map ...

Page 197: ...e sensing correction Reverse sensing correction inverts the course deviation needle and to from indicator so that they correctly indicate the direction of the course and waypoint The course deviation needle will be deflected in the direction of the desired course and the to from indicator will point in the direction of the waypoint similar to how the HIS depiction inverts with heading changes Mess...

Page 198: ...cale The Terrain Proximity function is present on the system regardless of other higher level terrain functions that may be selected If SVT is enabled in the Txi system then the Terrain FLTA function is provided Forward Looking Terrain Alerts and Reduced Terrain Clearance Alerts are provided for terrain obstacles and wires If TAWS B is enabled in the Txi system then the same alerts as the Terrain ...

Page 199: ...te on the System Status page The GDU utilizes two sets of databases those which are active and standby databases which are databases whose valid period has not yet begun Upon reaching the effective date of a standby database the pilot is prompted to update the database in use Internal database validation prevents incorrect data from being displayed Databases can be updated using an SD card by Sync...

Page 200: ...cycle If not updated within 180 days of the expiration date FliteCharts or ChartView will no longer function The airport directory database contains information on landing facilities such as operating hours services available and transportation lodging resources Airport directory information may be available from multiple sources and coverage areas This database is updated on a 56 day cycle The ma...

Page 201: ...as active at a time New profiles are created with the settings currently in use Aircraft Audio Interface The Pilot PFD is interfaced to the aircraft audio system to provide aural alerts altitude alerter minimums terrain If multiple PFDs are installed only the Pilot PFD is interfaced to the audio system to prevent duplicated aural alerts Advisory Notifications An Advisory notification system is ava...

Page 202: ...Measure for temperature barometric pressure nav angle altitude fuel distance and wind speed are pilot controllable via the System Units page These units are propagated throughout the system with the exception of Air Temperature Reference and Fuel Computer units which only affect the display being used to make the selection The units and markings on the PFD are not user configurable They match the ...

Page 203: ...e airspeed altitude vertical speed and slip instrument The instrument is self contained and directly incorporates all of the sensors required to measure and display the listed flight parameters All information is displayed on a color 3 5 diagonal LCD display in traditional aerospace symbology The unit also contains a rechargeable battery capable of providing continued operation in the event of air...

Page 204: ... SONAIR S2 D MAN 006 Page 7 37 Rev A The Rotary Knob with pushbutton provides the pilot access to all of the interactive functions of the KI 300 The figure below depicts the pushbutton selection of various functions and the table describes the role of the Rotary Knob in each function ...

Page 205: ...alled has failed self test or is in a low temperature state the battery life will show 0 Thermal stabilization On initial power on the various internal sensors must thermally stabilize While this is occurring the corresponding indicator area will be covered by a red X and there is a HEATING message in the center of the display At room temperature this process takes approximately 1 minute At colder...

Page 206: ...ired refer to section 3 10 10 Brightness adjustment The screens brightness is either manually or automatically controlled By default after power on the automatic mode is selected In the automatic mode the brightness will be adjusted based on the ambient light detected by the bezel mounted light sensor Pushing the rotary knob displays the brightness adjustment menu Once displayed rotating the contr...

Page 207: ...ios is reduced by Avionics Squelch ASQ When no audio is detected ASQ processing further reduces the amount of background noise Intercom squelch threshold adjustments are handled automatically by the system Pushbutton keys control audio selection When a key is selected a green annunciator on the key is illuminated Annunciator brightness is adjusted automatically by photocell dimming Key brightness ...

Page 208: ...S201 AFM 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 7 INSTRUMENTS AND AVIONICS 27 06 2019 SONAIR S2 D MAN 006 Page 7 41 Rev A The audio volume is controlled by the following way ...

Page 209: ...PS navigation VHF communication and navigation radio functions are operated by dedicated hard keys a dual concentric rotary knob or the touchscreen In addition the Transponder control is also located on the GTN screen Important information about specific functionalities are listed below For more information on the use of the GTN 650 refer to the GTN 650 Cockpit Reference Guide P N 190 01004 04 lat...

Page 210: ... displayed on the start up database verification page immediately after power on for those databases with an effective or expiration date Databases with no effective or expiration date e g terrain database are considered effective upon installation in the GTN Database information can also be viewed on the System System Status page The Obstacle Database has an area of coverage that includes the Uni...

Page 211: ...with Smart Airspace and airspace alerts Smart Airspace de emphasizes depicted airspace that is not near the aircraft s current altitude Airspace Alerts provide a message indication to the flight crew when the aircraft s current ground track will intercept an airspace type that has been selected for alerting Transponder Control The GTN is interfaced to a Garmin GTX 335R transponder for control and ...

Page 212: ...f displaying a large quantity and variety of data Map data is layered to ensure that data which is typically more critical is drawn above less critical data however at some zoom scales and configurations the map may be cluttered with large amounts of data Controls are provided on the Map and Weather pages for the pilot to select which data displayed the declutter level and the zoom scales at which...

Page 213: ...l range data is derived from the interfaced fuel totalizer data Data entered in the Fuel Planning pages will not update the fuel range ring User Defined Waypoints When a User Defined Waypoint is created a default name will automatically be provided and the pilot is given the option to enter a different name for the waypoint Pages which have the autofill function will prevent some waypoint names fr...

Page 214: ... a database that contains the VRP in order to appropriately display the VRP on the MFD map If the database on the PFD MFD does not contain the VRP the VRP will display on the MFD map as an intersection Advisory Visual Approaches The GTN will provide advisory visual approaches to many runways in the aviation database Lateral guidance for the visual approach is aligned with the runway bearing Vertic...

Page 215: ...NAV The GTN can provide multi waypoint descent baro VNAV guidance for the enroute and initial approach phases of flight Altitudes associated with instrument procedures are retrieved from the navigation database when the procedure is added to the flight plan Altitudes in cyan on the GTN are valid VNAV guidance waypoints and the GTN will provide vertical guidance based on the displayed altitude cons...

Page 216: ...light path angles FPA of 6 or less and vertical speed required of no less than 4000 fpm If a flight plan change is made during a VNAV descent VNAV will be recalculated and could result in active VNAV path changes If the current VNAV FPA is less than 1 a new VNAV path may be computed during a flight plan change and result in a new Top of Descent point This can also occur during VNAV Direct To opera...

Page 217: ... other flight plan waypoints Along track waypoints cannot be created on a Vectors to Final VTF approach and are limited to the lateral constraints of the flight plan This means that the pilot cannot place an ATK before the first waypoint of a flight plan or after the last waypoint of a flight plan ATKs are fixed once placed and will not move if the referenced waypoint is changed or removed from th...

Page 218: ...en be available on the GTN Limitations regarding database operations are found in Section 2 23 Garmin provides a list of tested and compatible devices that can be used with the Flight Stream Connection to the Flight Stream may be possible with devices other than those on the supported device list but Bluetooth and or Wi Fi stability and wireless data integrity cannot be guaranteed For details abou...

Page 219: ... a COM2 NAV2 radio is installed below the GPS Navigator Refer to Pilot s Guide of the GNC 255A for information on functionalities and interface NOTE For aircraft equipped with optional COM2 NAV2 radio a failure of COM2 will generate a NAV2 failure message on the PFD This is due to the fact that the link between both equipment is powered by the COM2 circuit ...

Page 220: ...ther side Latching mechanisms are provided inside the cabin at the top of the roll over bar in the centre and outside on the centre of the canopy After unlocking the mechanism with the key rotate the handle toward right wing to open To close and lock the canopy push main canopy fully in contact with front canopy and rotate the handle in flight direction After closing check proper locking by applyi...

Page 221: ... forward by lifting the small lever on each seat s external side See section 7 8 4 for more information A fire extinguisher 1 is held in place against the right retaining wall of the baggage space A hammer 2 to break the canopy for an emergency escape in case it is jammed is held in place in the baggage compartment between both seats An adjustable red interior cockpit light 3 is positioned behind ...

Page 222: ...the seat height in order to ensure that the rudder pedals can easily be reached by all pilots see warning and note on next page The longitudinal adjustment lever is located between the pilot legs as indicated in the circles below To adjust seat 1 Pull lever left 2 Adjust seat as required 3 Release lever 4 Move seat forward and backward until mechanism is locked This is confirmed by the lever going...

Page 223: ... maximum comfort and security WARNING Ensure that the seat s is are securely locked into position after adjustment Always adjust seat before starting the engine NOTE For easier operation adjust the seat before climbing in aircraft as the pilot weight will create more friction in the system NOTE Prior to each flight ensure that the seat belts are firmly secured to the airframe and that the belts ar...

Page 224: ...rea 2 a higher larger back section Up to 35 kg 77 lb of luggage may be loaded in Area 1 and 25 kg 55 lb in Area 2 subject to a total maximum baggage weight of 35 kg 77 lb Regardless of the manner in which baggage is loaded it is the obligation of the pilot to ensure that the aircraft CG is within the permissible limits All baggage must be properly secured under the baggage net supplied with the ai...

Page 225: ...rewall valve by moving the bottom lever to the right This valve can be closed by moving the lever back to the left to be closed immediately in case of engine fire or fumes The heated air is then distributed to either feet vents or windscreen demisting vents by the mean of respectively the middle and top levers Cold air Air vents located on the lower right and left sides of the instrument panel are...

Page 226: ... radio and satellite that will allow SAR services to easily locate the aircraft These emergency signals are sent on the 121 5 MHz and 406MHz frequencies A Buzzer in the cockpit will also indicate to the pilot that the ELT is active The ELT will also activate itself automatically in case of forward deceleration above 3g for instance in case of crash landing NOTE It is the responsibility of the owne...

Page 227: ...ntally opposed turbocharged spark ignition engine with one central camshaft using pushrods driven OHV 2 valves per cylinder The engine features liquid cooled cylinder heads with air cooled cylinders It utilizes dry sump forced lubrication and has a dual contactless capacitor discharge ignition system The turbocharger boost is controlled by an electronic control unit ensuring optimum manifold press...

Page 228: ... Following items should be inspected during pre flight check Engine mount Throttle and Choke cables on both carburettor Fuel pressure regulator and pipes leading to from it Exhaust and pipes leading to from it including turbo other side of engine Oil and Coolant radiators All visible wirings Coolant pipes ...

Page 229: ...sed by a pressure cap At temperature rise of the coolant an excess pressure valve in the expansion tank opens and coolant flows via a hose at atmospheric pressure to an overflow bottle mounted on the firewall When cooling down the coolant in the overflow bottle is sucked back into the cooling circuit Refer to latest revision of Rotax operator maintenance manuals and latest revision of Rotax servic...

Page 230: ...by a piston blow by gasses Oil temperature is sensed by a sensor located on the oil pump housing The lubrication circuit is vented at the oil reservoir The oil reservoir is located on the firewall The turbocharger is supplied with oil via a separate oil line from the main pump Return oil from the turbocharger is collected in a stainless steel sump and is sucked back to the suction pump and then pu...

Page 231: ...ttle lever past the 100 throttle selection requires the manipulation of the detent control enabling knob located on the throttle lever This will allow to select throttle settings between 100 and 115 which corresponds to Full Power setting A choke knob round is positioned in the right centre of the instrument panel Refer to paragraph 7 5 Pulling out the choke knob activates the choke mechanism A Ca...

Page 232: ...aircraft ambient pressure airbox pressure engine rpm and airbox temperature to actuate an electronically controlled waste gate to regulate the speed of the turbocharger boost pressure in the engine airbox Relationship between throttle position and engine power Throttle position Engine power 115 100 Full Power 100 85 Maximum Continuous Power NOTE Throttle position from 108 to 110 result in a rapid ...

Page 233: ...ld illuminate for 1 to 2 seconds and then turn off If not this indicative of a deficiency and the engine should not be taken into operation before the problem has been identified and rectified Refer to section 3 3 14 for information on cause and remedy in case of warning light illumination in flight CAUTION When supply voltage to the TCU fails the waste gate servo and thus the waste gate flap will...

Page 234: ...ual listed in section 1 8 2 for more information The following table lists approved ground adjusted pitch settings Other settings impact aircraft performance and noise and must be approved Propeller setting Blade pitch setting angle Impact on performances Standard 25 No impact see Section 5 content Other settings No other settings approved See section 9 NOTE Changing the setting affects the airpla...

Page 235: ...s given in the next pages Further functions and explanation can be found in the latest issue of the JPI EDM 900 Pilot s Guide furnished with your aircraft Screen layout presentation see next page for operation via control buttons Temperatures per cylinder indications Current engine of power Multifunction message area Fuel level indication based on fuel tank sensors Fuel consumption indication base...

Page 236: ...l modes holding the LF button for three seconds will toggle between Standard and Normalize NRM views Holding LF during power up will display the primary alarm limits after the self test is complete DIM Tapping DIM brightness decreases or holding DIM brightness increases allows decrease or increase brightness respectively LF DIM Holding both the LF and DIM buttons simultaneously will display the Ho...

Page 237: ...EL On start up If there is no need to adjust the REM remaining fuel on board fuel parameter simply tap NO to quit otherwise tap YES then on the next screen tap ADD SUB You can then select either ADD or SUBSTRACT buttons to adjust to the desired quantity the REM parameter New REM Initial REM adjustment The minimum value for REM parameter is 0 L Holding the ADD or SUBSTRACT buttons pressed will allo...

Page 238: ...SD parameter continuously accumulate total consumed fuel set TRIP Y Trip Mode is described in the Program Mode section of the EDM 900 Pilot s Guide o Hobbs time The EMS has an integrated timer that will display EMS total time Airframe and Engine Hobbs time Recommended EMS use see next pages NOTE Typically TRIP is set to N so that USD will be reset every time you fuel the aircraft See section 7 10 ...

Page 239: ...age 7 72 Rev A In the next pages recommended settings and use of the EMS are presented for each flight phase 30 C in all EGTs in single EGTs and CHTs consistent with past climbs EGTs Should be in the 700 to 900 C range 55 to 165 C Cooler than cruise due to fuel cooling 165 C above the others ...

Page 240: ...IRPLANE AND SYSTEMS DESCRIPTION 7 9 POWERPLANT 27 06 2019 SONAIR S2 D MAN 006 Page 7 73 Rev A Coolant shock cooling alarm is set to 51 C minute Average cool rates of 22 C minute to 28 C minute are normal next page ...

Page 241: ...ANE AND SYSTEMS DESCRIPTION 7 9 POWERPLANT 27 06 2019 SONAIR S2 D MAN 006 Page 7 74 Rev A Engine Diagnosis Chart The following charts can be used to diagnose engine problems and perform troubleshooting in your aircraft ...

Page 242: ...S201 AFM 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 9 POWERPLANT 27 06 2019 SONAIR S2 D MAN 006 Page 7 75 Rev A ...

Page 243: ...a filter A drain valve is located in the lowest point of the each tank Tank outlets lead to a fuel selector valve situated on the central console in the cockpit Fuel return lines return excess fuel supplied by the fuel pump to the fuel tank in use The system is configured as in the diagram below Fuel selector handle with extension Fuel selector valve Fuel tank Fuel tank filler cap Fuel pressure re...

Page 244: ...MD4814 Leaded AVGAS AVGAS 100LL ASTM D910 Unleaded AVGAS UL91 ASTM D7547 WARNING Do not fly with fuel under unusable fuel level The fuel pickup is located inboard rearward in the fuel tank The aircraft should at not be subjected to sustained side slip when fuel tanks are nearly empty as this may expose the fuel lift pipe to suck air thereby starving the engine of fuel leading to engine failure Unu...

Page 245: ...pump is connected directly to the Alternator 1 and the battery using a diode bridge The pump is not operated when Alternator 1 and Battery Master switch are off The auxiliary fuel pump is connected to the main bus which is supplied in power by Alternators 1 and 2 as well as by the Battery If the main pump fails the auxiliary fuel pump can be operated via power from the main bus provided that the c...

Page 246: ... two separate branches one for each carburettor A fuel pressure sensor is connected in parallel of the fuel pipe branches Fuel return lines return excess fuel supplied by the fuel pump s to the fuel tank in use In normal operation a pump will deliver 120 L hour to the regulator the engine will use 25 L hour and about 95 L hour will return to the fuel tank NOTE Fuel pumps are equipped with an integ...

Page 247: ...ation on the use of this indication The following table allows troubleshooting an abnormal fuel flow indication Observed indication Cause Engine idle approx 3 5L h Full power approx 30L h Normal condition Engine idle approx 3 5L h Full power below 20L h and engine stalling Fuel pump filter clogged No indication at all or 0L h Both sensors failed Connector behind instrument disconnected High fuel f...

Page 248: ...wo gages one per fuel tank A red warning range in programmed for the last 5 L per tank The indicator minimum 0 L corresponds to unusable fuel quantity See also notes on next page WARNING Fuel level indication on EMS is only accurate when aircraft is in level flight attitude During climb there is less fuel than indicated and during descent there is more fuel than indicated Before initiating climb o...

Page 249: ...fore each flight via the Refuel option Continuously monitor the Fuel Used parameter in flight and make sure it is in line with initial quantity fuel on board minus remaining indicated quantity Refer to section 7 9 7 for information on EMS functionalities and use NOTE The EMS will only indicate exact fuel levels between 0 and 60 L Fuel levels between 60 and 74 L are shown as Full on the instrument ...

Page 250: ... mark Corresponding fuel level Illustration Above 3 above sealant mark Above 70 L Between 2 and 3 between top and bottom sealant edge Between 65 and 70 L Between 1 and 2 between tank bottom and bottom sealant edge Between 30 and 65 L Below 1 fuel not covering the bottom of the tank Below 30 L NOTE Fuel level evaluation is only accurate when the aircraft is parked level on even ground Select approp...

Page 251: ...of the aircraft s systems with respect to the operational procedures described in this manual Refer also to paragraphs 7 5 and 7 9 7 11 1 ELECTRICAL SYSTEM OVERVIEW WIRING DIAGRAMS The electrical system is described on the schematics below For detailed electrical wiring diagrams refer to the Aircraft Maintenance Manual 1 Power Generation circuit The next page describes the electrical systems power...

Page 252: ...S201 AFM 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 11 ELECTRICAL SYSTEM 27 06 2019 SONAIR S2 D MAN 006 Page 7 85 Rev A ...

Page 253: ...both alternators are operating in parallel Alternator 2 will deliver most of the electrical power due to it s higher regulated voltage This is the normal operating configuration Alternator 1 relay is automatically powered as soon as any of the two Master switches are on or engine running It will supply power to main bus as long as the engine is running even if Master Switches BATT and ALT 2 are tu...

Page 254: ...rnator 1 does not charge the battery below 3000 RPM ALT 2 Master Switch must be on during warm up and taxiing to ensure positive charge and prevent battery depletion NOTE Battery life is optimal when stored in cool temperatures 0 30 C To prevent premature battery failure avoid as much as possible parking in direct sunlight on hot days Battery deep discharge will result in battery failure Always st...

Page 255: ... and taxi lights 7 11 5 MASTER AND STARTER SWITCHES The Sonaca 201 is equipped with a dual master switch mounted on the instrument panel connected to Battery and Alternator 2 relays The starter switch is a push button mounted on the instrument panel and can be activated after powering the main bus 7 11 6 IGNITION SWITCHES Two ignition switches are grouped into a turnkey switch located on the left ...

Page 256: ...rical system incorporates two alternator charge warning lights located in the warning lights row on the upper central part of the instrument panel refer to paragraph 7 5 The light corresponding to the failed alternator will illuminate if there is an AC generator alternator failure The main bus system voltage indicated on EMS will result in a reduced reading Refer to section 3 10 3 for action in ca...

Page 257: ... side behind the foot step A marking is placed immediately above the power receptacle The Ground Power circuit is protected against permanent power and reverse polarity by the mean of a relay and a diode In addition it is protected against overload by the mean of a 100A fuse The connection between Power Receptacle and Battery is only established once a voltage of 14V is supplied on the smallest pi...

Page 258: ...might result in voltage tripping overvoltage and damage to the battery Before connecting a Ground Power Supply always make sure that The male connector to be used is of type AN2551 3 pin The power source has a voltage of 14V Is protected for loads of max 100 Amps in any case It is able to supply min 75 Amps if used for engine starting It is able to supply min 50 Amps If used for charging the batte...

Page 259: ...N 006 Page 7 92 Rev A 7 12 LANDING GEAR 7 12 1 LANDING GEAR STRUCTURE The landing gear is a tricycle landing gear with a steerable nose wheel The main landing gear uses a single continuous aluminium leg The nose landing gear incorporates a spring and is attached to the engine mount truss ...

Page 260: ... pilot By pushing the top of the rudder pedal in order to rotate it the Master Hydraulic Cylinder is actuated The pilot and copilot left brake pedals actuate the left wheel brake and pilot and copilot right brake pedals actuate the right wheel brake Brake liquid tanks for both left and right hand hydraulic lines are located behind the rudder pedals on top of the copilot Master Hydraulic Cylinders ...

Page 261: ...d until the valve has reached its rearward stop To release the Parking Brake apply pressure on pedals and move the valve forward in the same way Pressure on both pedals should always be applied when engaging and disengaging the parking brake valve 7 12 3 TYRES Tyre approved types Nose Landing Gear Tyre Michelin Aviator 5 00 5 10 120 Main Landing Gear Tyres Michelin Air 380X150 15X6 00 5 6 120 Tyre...

Page 262: ...kup Flight Instrument Compass magnetic heading Chronometer integrated in radio Fuel gauges Oil pressure indicator Oil temperature indicator Coolant temperature indicator Outside air temperature indicator Tachometer First aid kit compliant with national legislation Fire extinguisher Hammer to break the canopy in case of emergency canopy blocked Personal Location Beacon PLB or Emergency Location Tra...

Page 263: ...ht Independent portable light for each crew member station One radio communication Equipment Other equipment are mandatory when required by the airspace to be flown One radio communication Equipment One navigation equipment One transponder WARNING The Aircraft is certified with its original instrumentation Notwithstanding that user installed equipment may include certified or uncertified GPS or an...

Page 264: ...6 2019 SONAIR S2 D MAN 006 Page 8 1 Rev A 8 AIRPLANE GROUND HANDLING AND SERVICING 8 1 TABLE OF CONTENT 8 1 TABLE OF CONTENT 8 1 8 2 INTRODUCTION 8 2 8 3 AIRPLANE INSPECTION INTERVALS 8 3 8 4 AIRPLANE ALTERATION OR REPAIRS 8 4 8 5 GROUND HANDLING 8 5 8 6 CLEANING AND CARE 8 10 ...

Page 265: ...and servicing of the aeroplane It also identifies certain inspection and maintenance requirements which must be followed It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered This document does not replace the maintenance manual Refer to the maintenance manual ref SONAIR S2 D MAN 002 supplied with the aircraft for more...

Page 266: ...nual ref SONAIR S2 D MAN 002 supplied with the aircraft for more information Inspections and servicing should be carried out according to at least the following periods After the first 25 flight hours Thereafter after every 100 flight hours or annually whichever is soonest and as stipulated in the latest revision of the applicable engine manufacturer and propeller manufacturer documentation ...

Page 267: ...at the EASA be contacted by the manufacturer prior to any alterations on the aeroplane to ensure that airworthiness of the plane is not violated If the aircraft weight is affected by a modification a new mass and balance determination is necessary This should be completed comprehensively and new data figures should be recorded in all relevant documentation 8 4 2 REPAIRS For repairs refer to the ma...

Page 268: ...ts Once the tow bar is secured eventually ask somebody to remove the wheel chocks and make sure the parking brake of the aircraft is released then manoeuvre the aircraft gently by pulling the tow bar forward pushing rearward or rotating the nose wheel by applying a side movement on the Tow Bar handle Always pay attention to not hit the propeller blade with tow bar while manoeuvring the aircraft CA...

Page 269: ... may be pushed down at the locations indicated by a red circle below in order to lift the nose of the aircraft for manoeuvring purposes It is best to press down on both points at once to spread the load It is also acceptable to push the aircraft carefully backwards by putting pressure on the wing leading edges close to the root directly on a nose rib or on the horizontal stabilizer leading edge ne...

Page 270: ...h ropes on the upper part of both Main Landing Gear legs immediately below the fuselage attachment 3 Carefully tighten the ropes to the vehicle making sure that no force is applied on the propeller or any other part of the aircraft 4 Release Parking brakes 5 Start slow towing 6 Stop immediately in case one or several aircraft wheels are stranded in a ditch or in soft ground or if the ropes enter i...

Page 271: ...he aircraft against possible damage caused by wind and gusts For this reason the aircraft is equipped with mooring eyes located on the lower surfaces of the wings and one under the tail Mooring procedure 1 Verify Fuel selector shut off Master switch switched off 2 Verify Ignition switched off 3 Secure the control stick s using the seat belts lower laps 4 Close air vents 5 Close and lock canopy 6 M...

Page 272: ...d also be gently supported to prevent the aircraft from rolling To lift a wing push from underneath the wing only at the intersection of the front spar with a rib and using a support that has a large contact area with the wing lower surface to spread the lifting load on a sufficient length of the spar and rib Avoid pushing directly on the skin Lift only one wing at a time This procedure can be use...

Page 273: ...the aircraft surface may be cleaned with petrol gasoline Take care not to spill cleaning agent on the canopy 8 6 2 CANOPY The canopy may only be cleaned by window cleaning agent adapted to perspex Use either a soft clean cloth sponge or deerskin 8 6 3 INTERIOR SURFACES Upholstery and covers may be removed from the cockpit brushed and washed in lukewarm water with a small quantity of detergents Dry...

Page 274: ...r cleaning information 8 6 5 PROPELLER DUC propeller blades are made of Carbon Fiber with an Inconel blade leading edge protection Use of DUC cleaning treatment ref 01 80 003 or similar Refer to the latest revision of the DUC Flash R operator manual for more details WARNING Use only approved cleaning agent for cleaning metal parts Non observance can lead to damage to the cooling system and engine ...

Page 275: ...T 27 06 2019 SONAIR S2 D MAN 006 Page 9 1 Rev A 9 ADDITIONAL INFORMATION 9 1 TABLE OF CONTENT 9 1 TABLE OF CONTENT 9 1 9 2 INTRODUCTION 9 2 9 3 ENHANCED SAFETY TAKE OFF 9 3 9 4 OTHER MARKINGS AND PLACARDS 9 4 9 5 LIST OF SUPPLEMENTS 9 9 9 6 AMENDMENTS 9 9 ...

Page 276: ...ed with the standard aeroplane Each supplement covers only a single system device or piece of equipment The supplement may be issued by the aeroplane manufacturer or by any other manufacturer of the applicable item Each supplement is approved by the EASA and contains all deviations and changes relative to the basic Flight Manual Chapter 1 to 8 Each supplement is a self contained miniature Flight M...

Page 277: ...l Power stabilized on brakes TCU switch off down position Release brakes and perform normal take off Above safety altitude TCU switch on NOTE Switching TCU off when Full Power is set freezes the turbo wastegate to fully closed position ensuring maximum power even in case of TCU failure NOTE This procedure requires additional workload and is not recommended for normal operation ...

Page 278: ...following markings and placards are placed in the aircraft and positioned in plain view of the occupants Markings concerning limitations or warnings are described and shown in section 2 12 On the instrument panel under the circuit breakers PITOT COM2 and NAV2 are optional equipment and the markings must only be installed if the aircraft is equipped ...

Page 279: ...06 2019 SONAIR S2 D MAN 006 Page 9 5 Rev A Under the switches PITOT is an optional equipment and the marking must only be installed in the aircraft is equipped Around the dimmer knob On the choke and carburettor heater actuators In a place visible to pilot and passenger ...

Page 280: ...1 AFM 9 ADDITIONAL INFORMATION 9 4 OTHER MARKINGS AND PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 9 6 Rev A Between the cabin heat system controls Around the canopy handle Adjacent to the microphone jacks ...

Page 281: ... 9 4 OTHER MARKINGS AND PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 9 7 Rev A Adjacent to the parking brake handle On the spacing panel between the cockpit and baggage area 1 On the emergency hammer handle Adjacent to each fuel drain ...

Page 282: ... 4 OTHER MARKINGS AND PLACARDS 27 06 2019 SONAIR S2 D MAN 006 Page 9 8 Rev A On the LH rear fuselage behind foot step above ground power receptacle If equipped with optional ELT in the cabin on baggage bay separation behind co pilot seat ...

Page 283: ...cturer Document Reference Title Section 1 General system or equipment specifically addressed Section 2 New limitations markings or placards Section 3 Additional emergency procedures Section 4 Additional normal procedures Section 5 Affected performance and new performance tables Section 6 Effect on Weight and balance 9 6 AMENDMENTS NONE at initial issue of this document ...

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