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sonaca aircraft S201 Aircraft Flight Manual

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S201 AFM
S201 AIRCRAFT FLIGHT MANUAL
Model:
Serial No:
Registration:
Document No. :
Date of Issue:
Approved by:
Signature:
Agency:
Stamp:
Original date of approval: 01/07/2019
compliance with information and limitations
handbook must be available on board of the
S201
SONAIR-S2-D-MAN-006
27/06/2019
Sonaca Aircraft S.A.
N/A
N/A
This airplane must be operated in
contained herein. This pilot operating
airplane at all times.

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  • Page 1 S201 AFM S201 AIRCRAFT FLIGHT MANUAL Model: S201 Serial No: Registration: Document No. : SONAIR-S2-D-MAN-006 Date of Issue: 27/06/2019 Approved by: Sonaca Aircraft S.A. Signature: Agency: Stamp: Original date of approval: 01/07/2019 This airplane must be operated in compliance with information and limitations contained herein.
  • Page 2 0 MANUAL ADMINISTRATION APPROVAL The content of approved chapters is approved by EASA. All other content is approved by Sonaca Aircraft S.A. under the authority of EASA DOA No. EASA.21J.614 in accordance with Part 21. RECORD OF REVISIONS All revisions of this manual, with the exception of - •...
  • Page 3 0 - MANUAL ADMINISTRATION S201 AFM 0.3 - LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES This section lists the pages of the manual, together with the revision corresponding to each page and the approving organism. Rev. Approved EASA EASA Page N°...
  • Page 4 0 - MANUAL ADMINISTRATION S201 AFM 0.3 - LIST OF EFFECTIVE PAGES EASA EASA 7-26 EASA EASA EASA 7-27 EASA EASA 5-10 EASA 7-28 EASA EASA 5-11 EASA 7-29 EASA EASA 5-12 EASA 7-30 EASA EASA 5-13 EASA 7-31 EASA...
  • Page 5 0 - MANUAL ADMINISTRATION S201 AFM 0.3 - LIST OF EFFECTIVE PAGES 7-69 EASA 7-85 EASA EASA 7-70 EASA 7-86 EASA EASA 7-71 EASA 7-87 EASA EASA 7-72 EASA 7-88 EASA EASA 7-73 EASA 7-89 EASA EASA 7-74 EASA 7-90...
  • Page 6 0 - MANUAL ADMINISTRATION S201 AFM 0.4 - TABLE OF CONTENT TABLE OF CONTENT MANUAL ADMINISTRATION ..............0-1 GENERAL INFORMATION ................1-1 LIMITATIONS ..................... 2-1 EMERGENCY PROCEDURES ............... 3-1 NORMAL PROCEDURES ................4-1 PERFORMANCE ..................5-1 WEIGHT AND BALANCE ................6-1 AIRPLANE AND SYSTEMS DESCRIPTION .............

  • Page 7: Table Of Contents

    1 - GENERAL INFORMATION S201 AFM 1.1 - TABLE OF CONTENT 1 GENERAL INFORMATION TABLE OF CONTENT TABLE OF CONTENT ................. 1-1 INTRODUCTION ................1-2 CERTIFICATION BASIS ..............1-4 WARNING, CAUTION AND NOTES ............ 1-5 AIRCRAFT DESCRIPTION AND DIMENSIONS ........1-6 DEFINITION AND ABBREVIATIONS ..........

  • Page 8: Introduction

    This manual includes the information required by CS-VLA to be furnished to the pilot of the Sonaca S201. It also contains supplemental data supplied by Sonaca Aircraft S.A., the aeroplane manufacturer. The Sonaca S201 is a two seat (side-by-side), single engine, tricycle fixed undercarriage, aluminium aircraft with a conventional low wing design.
  • Page 9 1.2 - INTRODUCTION NOTE THIS MANUAL IS WRITTEN FOR THE STANDARD ROTAX 914 F POWERED SONACA S201, AS MANUFACTURED ON THEIR PREMISES BY SONACA AIRCRAFT S.A. DIFFERENCES APPLICABLE TO POSSIBLE OPTIONS, AS INSTALLED OR APPROVED BY SONACA AIRCRAFT S.A., ARE INCLUDED IN APPLICABLE SUPPLEMENTS OF THIS HANDBOOK SECTION 9.

  • Page 10: Certification Basis

    1 - GENERAL INFORMATION S201 AFM 1.3 - CERTIFICATION BASIS 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.

  • Page 11: Warning, Caution And Notes

    1 - GENERAL INFORMATION S201 AFM 1.4 - WARNING, CAUTION AND NOTES WARNING, CAUTION AND NOTES The following definitions apply to warnings, cautions and notes used in the flight manual. WARNING WARNING: means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety.

  • Page 12: Aircraft Description And Dimensions

    AND DIMENSIONS AIRCRAFT DESCRIPTION AND DIMENSIONS 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.
  • Page 13 1 - GENERAL INFORMATION S201 AFM 1.5 - AIRCRAFT DESCRIPTION AND DIMENSIONS 2822 1161 DIMENSIONS IN THIS DRAWING ARE IN MILLIMETRES. For detailed description including Power plant and Systems, see Section 7. 27/06/2019 SONAIR-S2-D-MAN-006 Page : 1-7 Rev. : A...
  • Page 14 1 - GENERAL INFORMATION S201 AFM 1.5 - AIRCRAFT DESCRIPTION AND DIMENSIONS WING Metric Imperial Wing span: 9.243 m 30 ft. 4 inch Mean Aerodynamic Chord: 1.318 m 51.9 inch. Wing surface area: 11.845 m 131.75 sq ft. Wing loading: 59.10 kgm...
  • Page 15 1 - GENERAL INFORMATION S201 AFM 1.5 - AIRCRAFT DESCRIPTION AND DIMENSIONS EMPENNAGE Metric Imperial Horizontal stabilizer span: 2.822 m 9 ft 3 inch. Horizontal stabilizer surface area: 0.96 m 10 ft Elevator surface area: 1.02 m 11 ft Horizontal stabilizer angle of - 1.45...
  • Page 16 1 - GENERAL INFORMATION S201 AFM 1.5 - AIRCRAFT DESCRIPTION AND DIMENSIONS CONTROL SURFACE TRAVEL LIMITS Ailerons: ±2° up and 24 ±2° down Elevator: ±2° up and 22 ±2° down Trim tab: ±5° up and 23 ±5° down Rudder: ±2° left and right 0°...

  • Page 17: Definition And Abbreviations

    1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS DEFINITION AND ABBREVIATIONS General terminology / acronyms Alternating Current. Aircraft Flight Manual Altimeter. American Petroleum Institute Airspeed Indicator. ASTM American Society for Testing and Materials Anti Knock Index AVGAS Aviation gasoline.
  • Page 18 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS General airspeed terminology and symbols Calibrated Airspeed, being the indicated airspeed corrected for position and instrument error, Indicated Airspeed, being the speed shown on the airspeed indicator. KCAS Calibrated Airspeed expressed in knots.
  • Page 19 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS Meteorological terminology International Standard Atmosphere. The local pressure setting that if set on the subscale of an altimeter will cause the altimeter to indicate local altitude above mean sea level.
  • Page 20 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS Airplane performance and flight planning terminology Crosswind The velocity of the crosswind component for which adequate component control of the aircraft during take-off and landing can be demonstrated. The load factor.
  • Page 21 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS Weight and balance terminology and symbols Is the horizontal distance from the reference datum to the centre of gravity of an item. CG or CoG Centre of Gravity, being the point at which the airplane, or equipment, would balance if suspended.
  • Page 22 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS Avionics terminology ADAHRS Air Data and Attitude Heading Reference System Air Data Computer Automatic Direction Finder ADS-B Automatic Dependent Surveillance Broadcast AHRS Attitude & Heading Reference System Approach Along TracK...
  • Page 23 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS Heading Hazardous Obstacle Transmission wires Horizontal Situation Indicator Instrument Approach Procedure Instrument Flight Rules Instrument Landing System Instrument Meteorological Conditions Localizer Directional Aid LNAV Lateral Navigation LNAV +V Lateral Navigation with advisory Vertical Guidance...
  • Page 24 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS RAIM Receiver Autonomous Integrity Monitoring Reverse Frequency Lookup Remote RNAV Area Navigation Required Navigational Performance Search and Rescue SBAS Satellite Based Augmentation System Secure Digital Simplified Directional Facility SUSP...
  • Page 25 1 - GENERAL INFORMATION S201 AFM 1.6 - DEFINITION AND ABBREVIATIONS VNAV Vertical Navigation VHF Omnidirectional Range Visual Reporting Point Vertical Speed WAAS Wide Area Augmentation sYSTEM WFDE WAAS Fault Data Exclusion Transfer 27/06/2019 SONAIR-S2-D-MAN-006 Page : 1-19 Rev. : A...

  • Page 26: Units Of Measurement

    1.7.1 UNITS USED IN THE MANUAL For safety reason, this manual uses the following philosophy: • The same units as the ones that can be read on any of the S201 instruments and equipment are used in this Manual. They are expressed in one unit system only, imperial OR metric : ➢...
  • Page 27 1 - GENERAL INFORMATION S201 AFM 1.7 - UNITS OF MEASUREMENT 1.7.2 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.
  • Page 28 1 - GENERAL INFORMATION S201 AFM 1.7 - UNITS OF MEASUREMENT The figure below gives conversion factors for speeds: Speed Conversion Factors Diagram (correct at less than 0.3 %) 27/06/2019 SONAIR-S2-D-MAN-006 Page : 1-22 Rev. : A...

  • Page 29: Source Documentation

    1 - GENERAL INFORMATION S201 AFM 1.8 - SOURCE DOCUMENTATION SOURCE DOCUMENTATION 1.8.1 ENGINE Manufacturer: BRP-Rotax GmbH & Co KG Model: 914 F2 -01 See the latest revision / edition of the Operators Manual For Rotax® Engine Type 914 Series, Ref No.: OM-914.
  • Page 30 1 - GENERAL INFORMATION S201 AFM 1.8 - SOURCE DOCUMENTATION 1.8.3 ENGINE INSTRUMENT Manufacturer: J.P. Instruments Model: EDM-900 See the latest revision / edition of the Pilot’s Guide for EDM-900, entitled “Pilot’s Guide, Engine Data Management, EDM-900 Primary TSO/STC”. 1.8.4 FLIGHT, COMMUNICATION AND NAVIGATION INSTRUMENTS •...
  • Page 31 1 - GENERAL INFORMATION S201 AFM 1.8 - SOURCE DOCUMENTATION • 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...
  • Page 32 2 - LIMITATIONS S201 AFM 2.1 - TABLE OF CONTENT 2 LIMITATIONS TABLE OF CONTENT TABLE OF CONTENT ................. 2-1 INTRODUCTION ................2-2 AIRSPEED ..................2-3 AIRSPEED INDICATOR MARKINGS ............ 2-4 POWERPLANT LIMITATIONS ............2-5 MASS (WEIGHT) ................2-11 DATUM & CENTER OF GRAVITY RANGE ..........2-12 APPROVED MANOEUVERS..............2-13...

  • Page 33: Introduction

    INTRODUCTION Section 2 includes operating 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.

  • Page 34: Airspeed

    2 - LIMITATIONS S201 AFM 2.3 - AIRSPEED AIRSPEED Airspeed limitations and their operational significance are shown below – Speeds at MTOW: SPEED KIAS REMARKS Never exceed Never exceed this speed in any operation speed Maximum Never exceed this speed unless in smooth air,...

  • Page 35: Airspeed Indicator Markings

    2 - LIMITATIONS S201 AFM 2.4 - AIRSPEED INDICATOR MARKINGS AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour-code significance are shown below – MARKING KIAS SIGNIFICANCE Positive Flap Operating Range • Lower limit is V at maximum weight White arc 45-85 •...

  • Page 36: Powerplant Limitations

    2 - LIMITATIONS S201 AFM 2.5 - POWERPLANT LIMITATIONS POWERPLANT LIMITATIONS 2.5.1 ENGINE • Engine : BRP Rotax Model: 914 F2 -01 NOTE Always refer to the latest Engine Manufacturer document (TCDS, OM, MM, SB / SI, …) https://www.flyrotax.com/services/technical- documentation.html Searching databank for "914 F"...
  • Page 37 2 - LIMITATIONS S201 AFM 2.5 - POWERPLANT LIMITATIONS • Oil Temperature: • Minimum: 50°C • Maximum: 130°C NOTE Below 50°C Oil Temperature on ground, Engine RPM limited to 2500 NOTE Ensure at least once per flight day to reach an Oil Temperature of 100°C to avoid oil dilution issues.
  • Page 38 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 2 - LIMITATIONS S201 AFM 2.5 - POWERPLANT LIMITATIONS • Coolant Grade (Specification): • Ethylene glycol based coolant mixed 50%/50% with distilled water • See Rotax SI-914-019 for approved coolant types. NOTE Do not use concentrated water free propylene glycol based coolant.
  • Page 40 2 - LIMITATIONS S201 AFM 2.5 - POWERPLANT LIMITATIONS 2.5.2 ENGINE INSTRUMENT MARKINGS Powerplant instrument markings and their colour code significance are shown below: Normal Minimum Caution Range Maximum Instrument Operating Range (Red) (Yellow) Range (Red) Range (Green) None 1600-5500 RPM 5500-5800 RPM 5800-6400 RPM Oil Temperature 0-50°C...
  • Page 41 2 - LIMITATIONS S201 AFM 2.5 - POWERPLANT LIMITATIONS 2.5.3 FUEL Type Capacity (liter) Capacity of each tank 73 l Minimum RON 95 / minimum AKI 91. MOGAS: EN 228 Super, EN 228 Super Approved fuel plus, ASTMD4814 grades Leaded AVGAS: AVGAS 100LL (ASTM D910).

  • Page 42: Mass (Weight)

    2 - LIMITATIONS S201 AFM 2.6 - MASS (WEIGHT) 2.5.4 PROPELLER • Propeller : DUC Hélices - Model: FLASH-R - 1750 mm Remark : No blade rework permitted. • Propeller Rotational speed restriction (2700 RPM) is covered by the Engine Max.

  • Page 43: Datum & Center Of Gravity Range

    2 - LIMITATIONS S201 AFM 2.7 - DATUM & CENTER OF GRAVITY RANGE DATUM & CENTER OF GRAVITY RANGE Metric Imperial % of MAC Datum Centreline of firewall front face bottom edge Longitudinal horizontal Upper surface of canopy slides reference Forward limit at 650 kg 0.876 m*...

  • Page 44: Approved Manoeuvers

    2.8 - APPROVED MANOEUVERS APPROVED MANOEUVERS This aeroplane is certified in the Normal Category. In addition to manoeuvre for normal flying, the following manoeuvers are approved for the S201 with the flaps fully retracted: Approved Manoeuvers Entry speed Steep turns*...

  • Page 45: Manoeuvering Load Factors

    2 - LIMITATIONS S201 AFM 2.9 - MANOEUVERING LOAD FACTORS MANOEUVERING LOAD FACTORS 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...

  • Page 46: Kind Of Operations

    S201 AFM 2.10 - KIND OF OPERATIONS 2.10 KIND OF OPERATIONS The Sonaca S201 is approved for day and night VFR operation. Minimum equipment required for day or night VFR are defined in paragraph 7.13. VFR flights in rain are authorized.

  • Page 47: Other Limitations

    NOTE Oxygen supply is not provided in the basic S201 2.11.2 TEMPERATURE No limitation on external temperature other than engine temperature limitations defined in 2.5.1.
  • Page 48 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS 2.11.5 STARTING ATTEMPTS Max starter time 10 seconds, followed by a cooling time of 2 min. Maximum 4 starting attempts. Do not operate the starter if the engine is running. 2.11.6 ELECTRONIC EQUIPMENT Auxiliary 12V plug is protected by a 2 amps breaker.
  • Page 49 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS 2.11.9 AVIONICS LIMITATIONS • Use of GPS navigation capabilities The system is to be used for situational awareness under VFR only. • ADAHRS and AHRS Normal Operating Mode The Attitude and Heading Reference System integrity monitoring function requires external GPS and Air Data to be provided to the AHRS.
  • Page 50 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS • Synthetic Vision (Optional) The synthetic vision presentation must not be used as the sole reference for aircraft control (without reference to the primary flight instruments). The synthetic vision presentation must not be used as the sole reference for navigation or obstacle/terrain/traffic avoidance.
  • Page 51 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS • Moving Map Moving map displays (ownship position relative to map features) must not be used as the primary or sole means of navigation or course guidance. • Navigation with QFE setting...
  • Page 52 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS • Polar operations Operating the GTN for primary navigation for latitudes above 89.00° N and below 89.00° S is prohibited. • Use of Gloves in flight No device may be used to cover fingers used to operate the G500 and GTN unless the Glove Qualification Procedure located in the Pilot’s Guide/Cockpit Reference...
  • Page 53 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS • Telephone audio in flight Telephone audio must not be distributed to the pilot or co-pilot unless a phone call is active. 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 critical phases of flight.
  • Page 54 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS Database updates via MMC / SD card or Flight Stream wireless transfers must be done while the aircraft is on the ground and stationary. In-flight database transfers or updates are prohibited.
  • Page 55 2 - LIMITATIONS S201 AFM 2.11 - OTHER LIMITATIONS 2.11.10 APPLICABLE SYSTEMS SOFTWARE This AFM is applicable to the following software versions. For each equipment, a short procedure to identify the current software version is provided. • G500TXi The following or later software versions must be installed for this AFM revision...

  • Page 56: Limitation Placards

    2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS 2.12 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.
  • Page 57 2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS 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: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 2-26 Rev. : A...
  • Page 58 2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS In between the flap indicator and handle: On the baggage space separator channel: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 2-27 Rev. : A...
  • Page 59 2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS In between the trim On the moveable trim wheel and trim Left of the throttle: tab indicator: indicator: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 2-28 Rev. : A...
  • Page 60 2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS Adjacent to the fuel filler caps: On the cowl access door: On the inboard upper wing flap surface: On the elevator surface: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 2-29 Rev. : A...
  • Page 61 2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS At the static ports location: At the jacks: On the wheel fairings: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 2-30 Rev. : A...
  • Page 62 2 - LIMITATIONS S201 AFM 2.12 - LIMITATION PLACARDS On a first fireproof metal plate attached to the aircraft: MANUFACTURER – SONACA AIRCRAFT S.A. MODEL – S201 SERIAL NO – MSNXXX MANUFACTURED – MM/YYYY On a second fireproof metal plate, placed immediately above or below the first plate: A/C REG.
  • Page 63 3 - EMERGENCY PROCEDURES S201 AFM 3.1 - TABLE OF CONTENT 3 EMERGENCY PROCEDURES TABLE OF CONTENT TABLE OF CONTENT ................. 3-1 INTRODUCTION ................3-2 ENGINE FAILURES ................3-4 SMOKE AND FIRE ................3-16 LANDING WITH DEFECTIVE TYRE ........... 3-19 LANDING WITH DEFECTIVE BRAKES ..........

  • Page 64: Introduction

    3 - EMERGENCY PROCEDURES S201 AFM 3.2 - INTRODUCTION INTRODUCTION 3.2.1 GENERAL Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by aeroplanes or engine malfunction are extremely rare if proper pre-flight inspections and maintenance are practised.
  • Page 65 3 - EMERGENCY PROCEDURES S201 AFM 3.2 - INTRODUCTION 3.2.2 AIRSPEED IN EMERGENCIES SPEED KIAS REMARKS The speed (Flaps fully retracted) which Best Glide results in the greatest gliding Speed (horizontal) distance. Conditions: Flaps - retracted Airspeed = 65 KIAS...

  • Page 66: Engine Failures

    3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES ENGINE FAILURES 3.3.1 ENGINE FIRE / FAILURE DURING TAKE-OFF RUN Aircraft on ground - reject take-off 1. Throttle - idle 2. Brakes - apply as needed. With airplane stopped –...
  • Page 67 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.2 ENGINE FIRE / FAILURE DURING TAKE-OFF CLIMB 1. Throttle position - check Full Power 2. Main and Auxiliary fuel pumps - check on 3. Fuel selector valve - change to opposite tank 4.
  • Page 68 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.3 ENGINE FAILURE IN FLIGHT Engine failure or engine stopped: 1. Turnkey position - check both ignition channels are on. 2. Throttle position - check position (power as required). 3. Fuel selector valve...
  • Page 69 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.4 EMERGENCY LANDING WITH ENGINE OFF 1. During descent glide - locate most suitable landing location, free of obstacles and preferably into wind. - if time and height permit, and if appropriate, attempt to identify reason for engine failure, correct and attempt a restart (see §3.3.6).
  • Page 70 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 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.
  • Page 71 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.6 LOW OIL PRESSURE 1. Oil temperature - check If oil temperature is high or increasing 2. Refer to 3.3.7 - HIGH OIL TEMPERATURE Otherwise, 3. Throttle - reduce throttle to minimum for level flight 4.
  • Page 72 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.8 ENGINE RESTART WITH AND WITHOUT WINDMILLING PROPELLER 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.
  • Page 73 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.9 DEFECTIVE ENGINE CONTROLS NOTE In case of throttle cable detached, the affected carburettor will run on Full Power, causing load imbalance between left and right cylinder banks and high vibrations •...
  • Page 74 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.10 SUDDEN DROP IN ENGINE RPM AND MAP Possible turbocharger failure, associated or not with TCU CAUTION light flashing: 1. Throttle - reduce to minimum acceptable 2. Oil pressure - monitor 3.
  • Page 75 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.12 PERIODICAL RISE AND DROP IN ENGINE RPM AND MAP Possible automatic regulation of the system due to airbox temperature limit 1. Carburettor heater - check pushed 2. Throttle - reduce to 65% or below if practicable to allow...
  • Page 76 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.13 EMS REMOTE ALERT LED INDICATION The EDM 900 Remote Alert LED (RAL) will flash in orange and red color in case - any primary parameter exceeding the red line...
  • Page 77 3 - EMERGENCY PROCEDURES S201 AFM 3.3 - ENGINE FAILURES 3.3.14 TCU CAUTION OR WARNING LIGHT INDICATION The Rotax TCU caution and warning lights will illuminate in following cases: Yellow Caution light Red Warning light • The Full Power time •...

  • Page 78: Smoke And Fire

    3 - EMERGENCY PROCEDURES S201 AFM 3.4 - SMOKE AND FIRE SMOKE AND FIRE 3.4.1 ENGINE FIRE 1. Throttle - full power. 2. Fuel selector - close. 3. Auxiliary Fuel pump - off. 4. Cabin heat - close. 5. Main Fuel Pump - pull circuit Breaker 6.
  • Page 79 3 - EMERGENCY PROCEDURES S201 AFM 3.4 - SMOKE AND FIRE 3.4.2 ELECTRICAL FIRE An electrical fire is often characterized by white smoke and an acrid smell. 1. Master switches - BATT and ALT 2 off (see NOTE and WARNING below).
  • Page 80 3 - EMERGENCY PROCEDURES S201 AFM 3.4 - SMOKE AND FIRE 5. Check Circuit Breaker panel - look for pulled breakers 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 source identification 6.

  • Page 81: Landing With Defective Tyre

    3 - EMERGENCY PROCEDURES S201 AFM 3.6 - LANDING WITH DEFECTIVE BRAKES LANDING WITH DEFECTIVE TYRE If aircraft veers off centreline during landing, expect main tyre depletion. 1. Apply rudder and/or brake action on opposite side 2. In case of runway excursion, refer to 3.3.1 ENGINE FIRE / FAILURE DURING TAKE-OFF RUN 3.

  • Page 82: Recovery From Unintentional Spin

    3 - EMERGENCY PROCEDURES S201 AFM 3.8 - PRECAUTIONARY LANDING RECOVERY FROM UNINTENTIONAL SPIN WARNING Intentional spins are prohibited! 1. Throttle - idle 2. Rudder pedals - full rudder in direction opposite to spin 3. Longitudinal control - forward 4. Lateral control...

  • Page 83: Precautionary Landing

    3 - EMERGENCY PROCEDURES S201 AFM 3.8 - PRECAUTIONARY LANDING PRECAUTIONARY LANDING A precautionary landing is generally carried out in cases where the pilot may be unable to continue the flight, the aircraft has no fuel reserve or possibly in bad weather conditions.

  • Page 84: Instrument Indication Outside Of Green Range

    3 - EMERGENCY PROCEDURES S201 AFM 3.9 - INSTRUMENT INDICATION OUTSIDE OF GREEN RANGE INSTRUMENT INDICATION OUTSIDE OF GREEN RANGE Exceeding of max. admissible engine speed - Reduce engine speed. - Record the stating duration and extend of over speed in the logbook.

  • Page 85: Other Emergencies

    3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10 OTHER EMERGENCIES 3.10.1 CARBURETTOR ICING 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°C OAT, especially at reduced power settings...
  • Page 86 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.2 ELECTRICAL EQUIPMENT FAILURES CAUTION Do not attempt to reset a tripped circuit breaker to avoid electrical fire 1. Verify if corresponding equipment is switched on and dimmer is appropriate 2.
  • Page 87 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.3 ALT 1 AND/OR 2 WARNING LIGHTS - ALTERNATOR FAILURE Alternator failure is evidenced by the illumination of the ALT 1 and/or ALT2 charge warning light. In the case of ALT 1 warning light illuminating: 1.
  • Page 88 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES If ALT 1 and ALT 2 warning lights illuminating: 1. Switch off Avionics 2 to reduce power consumption to maximum 14 A – consult table on next page for total load calculation (visible on EMS, should not be below -14A) 2.
  • Page 89 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES Electrical equipment and their associated current draw are listed in the table below. In case of emergency, calculate total load and ensure maximum 14 A. Significant power consumers are highlighted in bold.
  • Page 90 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES In the event of a total loss of aircraft electrical power, the following equipment will cease to operate: • 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.
  • Page 91 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.4 SUSPICION OF CABIN CARBON MONOXIDE CONTAMINATION 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.
  • Page 92 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.5 FAILURE OF FLAP OPERATING SYSTEM In the case where flap indicator does not respond to flap lever switch: 1. Confirm flap position visually 2. Set back flap lever to actual position 3.
  • Page 93 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.6 PFD FAILURES In all cases: Use backup instrument for attitude, airspeed, and altitude reference Refer directly to the navigation source for navigation information (such as GPS). Depending on the failure, consider resetting PFD using on-off button or both PFD1/A and PFD1/B circuit breakers simultaneously.
  • Page 94 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES NOTE If the AHRS is restarting in flight without an operative GPS navigator, attempt to minimize maneuvering and turbulence during and after the restart process. Without an operative GPS navigator, excessive maneuvering or turbulence may prevent the AHRS from completing alignment properly.
  • Page 95 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.7 PFD MALFUNCTIONS • If an ATTITUDE, ALT, or IAS monitor CAUTION is displayed in amber on the attitude display or airspeed/altitude tape: Cross check flight instruments against all available information to...
  • Page 96 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES • Heading Failure Heading failure is indicated by removal of the digital magnetic heading display on the HSI and a red annunciation. If GPS ground track is available, it will automatically be displayed in place of heading.
  • Page 97 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES - Synthetic Vision Malfunction (Optional) If the synthetic vision depiction is known or suspected to be inaccurate or malfunctioning: Turn off synthetic terrain using the PFD Terrain/SVT menu • Display Fan Failure...
  • Page 98 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES • Navigation Data Failure (VOR/LOC/GS) Navigation data failure may be indicated by any or all of the following: - Loss of course deviation information on PFD - Loss of glideslope/glidepath information on PFD...
  • Page 99 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.8 PFD WARNINGS, CAUTIONS AND ALERTS • WARNINGS, CAUTIONS, and Advisories 27/06/2019 SONAIR-S2-D-MAN-006 Page : 3-37 Rev. : A...
  • Page 100 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 27/06/2019 SONAIR-S2-D-MAN-006 Page : 3-38 Rev. : A...
  • Page 101 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 27/06/2019 SONAIR-S2-D-MAN-006 Page : 3-39 Rev. : A...
  • Page 102 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES • Terrain Alerts (Optional) Initiate maximum performance climb (maximum takeoff power and best angle of climb airspeed) 27/06/2019 SONAIR-S2-D-MAN-006 Page : 3-40 Rev. : A...
  • Page 103 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.9 GPS / COM / NAV MALFUNCTIONS • Data source – pressure altitude source inoperative or connection to GTN lost message Since the GTN is being used to forward pressure altitude to the transponder, it will not be receiving pressure altitude from the GTN while that message is present.
  • Page 104 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES 3.10.10 BACKUP INSTRUMENT MALFUNCTION • Sensor failure If any internal sensor fails, the corresponding parameter on the display will remain in the Red-X’ed state. If this occurs, the unit must be returned to the factory for service.
  • Page 105 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES performance and is sufficient to maintain positive aircraft control for VFR operations. When operating in the Degraded Mode, an amber CROSS CHECK message may be displayed on the screen. Cross Check may occur during extended periods of maneuvering. Reestablishing straight and level flight allows the unit to reacquire TSO criteria performance.
  • Page 106 3 - EMERGENCY PROCEDURES S201 AFM 3.10 - OTHER EMERGENCIES • Transition to and from battery The unit will automatically transition to internal battery if the aircraft power drops below approximately 7 VDC. At this point, one of two operational sequences will occur, depending on if the aircraft is on the ground or in the air.
  • Page 107 4 - NORMAL PROCEDURES S201 AFM 4.1 - TABLE OF CONTENT 4 NORMAL PROCEDURES TABLE OF CONTENT TABLE OF CONTENT ................. 4-1 INTRODUCTION ................4-2 AIRPSPEEDS FOR NORMAL OPERATING PROCEDURES ..... 4-2 CHECKLISTS FOR NORMAL OPERATING PROCEDURES ...... 4-3 HIGH ALTITUDE OPERATION ............4-34 STALL BEHAVIOUR .................

  • Page 108: Introduction

    4 - NORMAL PROCEDURES S201 AFM 4.3 - AIRPSPEEDS FOR NORMAL OPERATING PROCEDURES INTRODUCTION Section 4 provides checklist and amplified procedures for conducting of normal operation. Normal procedures associated with optional systems can be found in Section 9. AIRPSPEEDS FOR NORMAL OPERATING PROCEDURES Unless otherwise specified, the following speeds are based on a maximum weight of 750 kg.

  • Page 109: Checklists For Normal Operating Procedures

    The next page presents the steps to inspect the S201 before flight. Then, the following pages list inspection points to perform at each step. 27/06/2019...
  • Page 110 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 27/06/2019 SONAIR-S2-D-MAN-006 Page : 4-4 Rev. : A...
  • Page 111 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES Cabin - Ignition - off - Fuel selector valve - switch to A or B tank - Master switches - on - Fuel level indicator - verify fuel quantity...
  • Page 112 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES Left Wing and Main Gear - Chocks & Ropes - remove - Wheel fairing - check attachments and no cracks - Wheel and brakes - check fluid leaks, tyre inflation and wear...
  • Page 113 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES Nose Section and Nose Gear Refer to Section 7.9 for systems description and location in engine bay. - Cowling access doors (LH then RH) - rotate fasteners to open...
  • Page 114 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES - Check Oil level above 50% before long flight, replenish as required. Do not exceed the Max. level. - Close oil tank with cap - Close access doors (LH then RH) - rotate fasteners in airstream direction to close.
  • Page 115 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4. Right Wing and Main Gear - Leading edge condition - check OK (no deformations, no cracks).- - Fuel drain - drain for min. 2 sec - Fuel level...
  • Page 116 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES Right Fuselage - Access Hatches (underside of cabin) present and properly closed - Surface condition - check - Wing/fuselage fairings - check - Access doors under rear fuselage...
  • Page 117 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES Empennage - Tie-down rope - removed. - Antenna/e - check condition and attachments. - Horizontal and vertical stabilizers - check condition - Hinges, control horns, bolts, pushrods...
  • Page 118 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES Left Fuselage - Empennage fairings - check - Surface condition - check - Antenna/e - check condition and attachments. - Access doors under rear fuselage - closed...
  • Page 119 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.2 BEFORE START Strobe and navigation lights should be used as an indicator / warning of imminent engine start (i.e. switch on the strobe before starting the engine).
  • Page 120 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.3 AVIONICS START-UP 1. Fuel selector - check on fullest tank 2. Master switches - on. 3. Warning lights function test - check TCU and RAL illuminate for 1-2 sec when the Master Switch is triggered, then extinguish.
  • Page 121 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 5. PFD - wait for PFD on - press “Continue” when prompted 6. Avionics 1 Switch - on - wait for Audio Panel and GPS on - review databases dates - press “Continue”...
  • Page 122 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.4 STARTING THE ENGINE 1. Choke - pull for cold start only (engine at ambient T°) 2. Throttle - idle if choke used, - 1cm max forward from idle if choke is not used 3.
  • Page 123 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES CAUTION - The starter should be activated for a maximum of 10 seconds, followed by 2 minute pause to allow the starter to cool. - Increase the engine RPM only if oil pressure is steady above 29 psi (2 bar).
  • Page 124 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.5 TAXIING Taxi lights should be used as an aid to enhancing the aircraft’s visibility to other traffic or pedestrians. 1. Fuel selector - switch tank (to emptiest tank) 2.
  • Page 125 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.6 ENGINE CHECK BEFORE TAKE OFF CAUTION Always ensure Oil Temperature above 50°C before increasing engine speed above 2500 RPM CAUTION The engine check should be performed with the aircraft heading upwind and not on loose terrain (the propeller may suck grit which can damage the leading edges of blades).
  • Page 126 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES NOTE Only one ignition circuit (at a time) should be switched on/off during ignition/magneto check. NOTE The maximum difference between both drops may not exceed 150 RPM.
  • Page 127 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.7 BEFORE LINE UP 1. Controls - verify full and free movement, directions. 2. Ignition Switch - check on both circuits 3. Switches - verify, as required.
  • Page 128 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.8 TAKE-OFF CAUTION Ensure that engine oil temperature is above 50 °C prior to take off. 1. Brakes - apply pressure on pedals (parking brake off) 2. Throttle - Maximum Continuous Power 3.
  • Page 129 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.9 CLIMB 1. Throttle - Full Power, 5 800 rpm (for maximum 5 minutes). - Maximum Continuous Power, 5 500 rpm. 2. Airspeed = 68 KIAS = 65 KIAS Y,0°...
  • Page 130 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 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 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.11 DESCENT Adjust power to get the desired slope – typical cruise descent parameters are: 1. Speed - 110 KIAS 2. Descent rate - -600 ft/min 3. Throttle - adjust to about 65% power to keep speed constant 4.
  • Page 132 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.12 APPROACH Proceed with circuit pattern in accordance with the selected airfield procedure. 1. Auxiliary fuel pump - on 2. Landing light - on 3. Carburettor Heater - on if required (refer to section 4.4.21)
  • Page 133 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 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...
  • Page 134 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.15 GO-AROUND 1. Aircraft attitude - transition to level 2. Throttle - Full Power (max. 5800 RPM for max. 5 min.) 3. Carburettor heater - push to close if open 4.
  • Page 135 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 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...
  • Page 136 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.17 ENGINE SHUT-DOWN 1. Throttle - idle 2. Instruments - engine parameters within limits. 3. Avionics 1 and 2 switches - off 4. Aux fuel pump - off Wait for minimum 2 minutes between throttle setting reduction and ignition switch off to allow engine to cool down.
  • Page 137 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.18 POST-FLIGHT 1. Site - if possible park the aircraft on level area 2. Ignition - off 3. Master switches - check off 4. Fuel selector - off 5.
  • Page 138 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.19 FLIGHT IN RAIN No particular precautions are required when flying in rain. VMC should be maintained at all time. Avoid negative outside temperatures. Use Carburettor Heater if required (refer to section 4.4.21).
  • Page 139 4 - NORMAL PROCEDURES S201 AFM 4.4 - CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.4.21 FLIGHT IN COLD AND MOIST CONDITION If flying into humid area with Dew Point close to 0°C OAT, engine is warmed up with carburettor heater on full position.

  • Page 140: High Altitude Operation

    REFUELING The aircraft must be connected to a ground bonding point before refuelling. On the Sonaca S201, the electrical bonding is done on the exhaust pipe. When refuelling with portable tanks, always use a funnel with incorporated fine filter. One exemplary is furnished with the aircraft.

  • Page 141: Engine Failure Training

    4 - NORMAL PROCEDURES S201 AFM 4.7 - ENGINE FAILURE TRAINING ENGINE FAILURE TRAINING 1. Navigate - start above landing area at 1500ft AGL 2. Throttle - reduce to idle 3. Speed 65 KIAS 4. Flaps - T/O setting 5. Oil Temperature...
  • Page 142 4 - NORMAL PROCEDURES S201 AFM 4.8 - HSI OPERATION HSI OPERATION When the PFD is used to display navigation data from the GTN, the 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.
  • Page 143 5 - PERFORMANCE S201 AFM 5.1 - TABLE OF CONTENT 5 PERFORMANCE TABLE OF CONTENT TABLE OF CONTENT ................. 5-1 INTRODUCTION ................5-2 PERFORMANCE TABLES AND DIAGRAMS ......... 5-3 27/06/2019 SONAIR-S2-D-MAN-006 Page : 5-1 Rev. : A...
  • Page 144 5 - PERFORMANCE S201 AFM 5.2 - INTRODUCTION INTRODUCTION Section 5 provides approved data for airspeed calibration, stall speeds and take- 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.
  • Page 145 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION The data present Calibrated Airspeed (CAS) versus Indicated Airspeed (IAS) assuming zero instrument error. The calibration is applicable for all flaps settings.
  • Page 146 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS KIAS [kts] 27/06/2019 SONAIR-S2-D-MAN-006 Page : 5-4 Rev. : A...
  • Page 147 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.2 ENGINE PERFORMANCE MAXIMUM CONTINUOUS POWER [kW] (Approx. 5500 RPM) Standard Atmosphere Delta temperature with standard temperature [°C] T (°F) T(°C) -2000 2000 4000 6000 8000 10000 12000 14000...
  • Page 148 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS MAXIMUM TAKE OFF POWER [kW] (Approx. 5800 RPM) Standard Atmosphere Delta temperature with standard temperature [°C] T (°F) T (°C) -2000 2000 4000 6000 8000 According to the above tables, the correction at all altitudes is approximately : •...
  • Page 149 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.3 PRESSURE ALTITUDE – DENSITY ALTITUDE 27/06/2019 SONAIR-S2-D-MAN-006 Page : 5-7 Rev. : A...
  • Page 150 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.4 STALL SPEEDS Conditions: Weight - 750 kg Flight - straight and level flight (non-turning) - load factor of 1 g. Engine - idle Vs : Stall speed [kts]...
  • Page 151 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS Following altitude loss can be expected during a wing level stall: Power setting Altitude loss Idle 250 ft 75 % 450 ft These values are valid for all flaps settings and for any weight & balance configuration within the approved limits.
  • Page 152 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.6 TAKE-OFF Conditions: Flaps - T/O setting Power - Full Power Airspeed - rotate at V = 55 KIAS Wind - zero Take-off distance Surface Take-off run 15m (50 ft) obstacle...
  • Page 153 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS Correction table below is given for take-off distance versus OAT and elevation. OAT and Altitude values are given in absolute measure. OAT [°C] -30 -25 -20 -15 -10 Hp [ft] <470 <470 <470 <470 <470 <470 <470 <470 <470 470 475 480 485 490...
  • Page 154 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.7 CLIMB PERFORMANCE – TAKE-OFF CLIMB Conditions: Full Power - MAP = 39 Weight - 750 kg Flaps - T/O setting - 63 KIAS with a climb angle of 12% x, 10°...
  • Page 155 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.8 CLIMB PERFORMANCE – CRUISE CLIMB Conditions: Full Power - MAP = 39 Weight - 750 kg Flaps - UP setting - 65 KIAS for best climb angle of 11% x, 0°...
  • Page 156 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS Conditions: Max. Continuous Power - MAP = 34.9 Weight - 750 kg Flaps - UP setting - 65 KIAS for best climb angle of 11% x, 0° - 68 KIAS for best climb rate of 540 ft/min Y, 0°...
  • Page 157 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.9 CRUISE SPEED Data provided for ISA condition Range ISA T° IASa Cons. 140l -45min [ft] °C [min-1] [kts] [kts] [l/h] 4500 4800 2000 5000 5500 4500 4800 4000...
  • Page 158 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.10 LANDING DISTANCE – FLAPS IN LANDING POSITION Conditions: Flaps - LD setting Power - idle Airspeed - approach at 55 KIAS Wind - zero Landing distance over 15 m...
  • Page 159 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS Correction table below is given for landing distance versus OAT and elevation. OAT and Altitude values are given in absolute measure. OAT [°C] -30 -25 -20 -15 -10 Hp [ft] <475 <475 <475 <475 <475 <475 <475 <475 <475 475 480 480 485 485...
  • Page 160 5 - PERFORMANCE S201 AFM 5.3 - PERFORMANCE TABLES AND DIAGRAMS 5.3.11 CLIMB GRADIENT ON GO-AROUND The S201 reaches a constant gradient of climb of 8.4% in the following condition: Full Power - MAP = 39 Weight - 750 kg...
  • Page 161 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...
  • Page 162 6 - WEIGHT AND BALANCE S201 AFM 6.1 - TABLE OF CONTENT 6 WEIGHT AND BALANCE TABLE OF CONTENT TABLE OF CONTENT ................. 6-1 INTRODUCTION ................6-2 DATUM PLANE AND REFERENCES ............ 6-2 WEIGHT AND CENTER OF GRAVITY LIMITS ........6-3 MASS AND BALANCE REPORT ............

  • Page 163: Introduction

    Upper surface of canopy left slide reference Upper surface of baggage compartment Transversal horizontal Reference beam just behind the seats Mean Aerodynamic Chord (MAC) of the SONACA S201 Length : 1318 mm MAC Leading Edge position : 612 mm 27/06/2019...

  • Page 164: Weight And Center Of Gravity Limits

    6 - WEIGHT AND BALANCE S201 AFM 6.4 - WEIGHT AND CENTER OF GRAVITY LIMITS WEIGHT AND CENTER OF GRAVITY LIMITS Metric Imperial % of MAC Forward limit 0.876 m 2.873 ft Rear limit 1.034 m 3.392 ft 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: Mass And Balance Report

    6 - WEIGHT AND BALANCE S201 AFM 6.5 - MASS AND BALANCE REPORT MASS AND BALANCE REPORT Mass & Balance must be calculated before every flight for Take Off and Landing condition. Fill the table on next page and check that you are within the authorized range.
  • Page 166 6 - WEIGHT AND BALANCE S201 AFM 6.5 - MASS AND BALANCE REPORT MOMENT MASS (mass x arm) ITEM [kg] [mm] [kg.mm] Empty aircraft …………. Pilot & 1150 passenger Baggage 1500 (Area 1) Baggage 2296 (Area 2) Fuel Mass at TO TOTAL at CG position=………….

  • Page 167: Aircraft Weighing

    AIRCRAFT WEIGHING Weighting 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.
  • Page 168 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.1 - TABLE OF CONTENT 7 AIRPLANE AND SYSTEMS DESCRIPTION TABLE OF CONTENT TABLE OF CONTENT ................. 7-1 INTRODUCTION ................7-2 AIRFRAME ..................7-3 FLIGHT CONTROLS ................7-4 INSTRUMENT PANEL ..............7-10 WARNING, CAUTION AND STATUS LIGHTS ........

  • Page 169: Introduction

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.2 - INTRODUCTION INTRODUCTION This section 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.

  • Page 170: Airframe

    The wing has a high lift airfoil having the advantage of being only slightly sensitive to rain and reasonable amount of dust and insects. It is equipped with single slotted Fowler type flaps. S201 Fuselage structure: S201 Wing structure: 27/06/2019...

  • Page 171: Flight Controls

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.4 - FLIGHT CONTROLS FLIGHT CONTROLS Flight controls are composed exclusively of pushrods and torque tubes for ailerons and elevator, linked to both pilot and co-pilot sticks. The rudder is controlled by means of cables linked to pedals.
  • Page 172 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.4 - FLIGHT CONTROLS 7.4.2 AILERON CONTROLS 7.4.3 ELEVATOR CONTROL 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-5 Rev. : A...
  • Page 173 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.4 - FLIGHT CONTROLS 7.4.4 ELEVATOR TRIM The elevator trim is controlled manually via a wheel on the centre console. Moving the top of the wheel forward will apply a pitch down correction, and moving it rearward will apply pitch up correction.
  • Page 174 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.4 - FLIGHT CONTROLS 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: Instrument Panel

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.4 - FLIGHT CONTROLS 7.4.6 FLAP CONTROL Wing flaps are electrically controlled by a four-position lever located on the instrument panel (refer to paragraph 7.5). A mechanical flap indicator located next to the lever shows the current flap position.
  • Page 176 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.4 - FLIGHT CONTROLS Following flaps settings are defined on the S201: Selector Degrees flap Position deflection 0° 10° 20° 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).
  • Page 177 7.5 - INSTRUMENT PANEL INSTRUMENT PANEL The S201 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.
  • Page 178 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.5 - INSTRUMENT PANEL Number Component Function Operation on figure BATT Switch Battery power supply (Master Switch) Up : On / Down : Off ALT 2 Switch ALT 2 power supply (Master Switch)
  • Page 179 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.5 - INSTRUMENT PANEL JPI EDM900 Engine Monitoring System (EMS) See section 7.9.7 Warning lights Alternator and engine warning lights See section 7.6 Backup Bendix King / Honeywell KI300 – Backup Flight Instrument with See Section 7.7.5.2...
  • Page 180 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.5 - INSTRUMENT PANEL Flap selector Select position of Flaps (from top to bottom settings) (right) Pulled : choke on Choke Engage engine choke Pushed : normal operation Carburettor Pulled : heater on...

  • Page 181: Warning, Caution And Status Lights

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.6 - WARNING, CAUTION AND STATUS LIGHTS WARNING, CAUTION AND STATUS LIGHTS Warning lights are provided to announce hazardous system operation to the pilot. They are located at the top centre of the instrument panel as described...

  • Page 182: Instruments And Avionics

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS INSTRUMENTS AND AVIONICS 7.7.1 GENERAL INFORMATION The diagram in section 7.5 represents the instrument panel-mounted avionics. A description of specific equipment functionalities and operation is provided in the table below.
  • Page 183 DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 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. 27/06/2019...
  • Page 184 7.7 - INSTRUMENTS AND AVIONICS 7.7.3 PITOT-STATIC SYSTEM The anemometric system of the S201 is composed of: • A total pressure measurement line: A pitot tube is located below the left wing. Pressure distribution to the instruments is through flexible plastic hoses installed in the wing and central fuselage.
  • Page 185 7.7 - INSTRUMENTS AND AVIONICS The S201 may optionally be equipped by a Heated pitot tube. In this case, a “PITOT” switch is located in the right of the switch line on the instrument panel, as well as the corresponding Circuit Breaker.
  • Page 186 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 7.7.4 STALL WARNING A stall warning device is installed on the Right wing, 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.
  • Page 187 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 7.7.5 PRIMARY AND BACKUP FLIGHT DISPLAYS 7.7.5.1 PRIMARY FLIGHT DISPLAY (PFD) This aircraft is equipped with a G500 Txi system which provides attitude, heading, air data and navigation information to the pilot. These information’s are presented on a 10”...
  • Page 188 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Controls overview Dual concentric knobs and a capacitive touchscreen provide control of functions for the units. The touchscreen controls accept single touch, two finger pinch, and single finger swiping actions.
  • Page 189 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Colors The following colors are used consistently within the Txi system: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-22 Rev. : A...
  • Page 190 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Screen configuration The screen can be configured either in PFD or MFD mode, both having the EHSI shown below the flight instrument. Switching from PFD to MFD mode is done by pressing the “Split / Full”...
  • Page 191 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS The integrated EHSI display is used to display NAV information. Selection of the desired NAV source is done by clicking on the “CDI Source Selector” button. Standard HSI configuration In the case where no VOR or GS signal is received, no flag will appear on the EHSI.
  • Page 192 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Attitude The attitude display is a blue over brown presentation and optionally can display synthetic vision data (SVT). Standard rate turn marks are provided on the roll scale for bank angles less than 30 degrees.
  • Page 193 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS - Flight Path Marker (FPM): an indication of the current lateral and vertical path of the aircraft. The FPM is always displayed when synthetic terrain is selected for display.
  • Page 194 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Airspeed The airspeed tape on the left side of the PFD displays red/white striping to indicate the maximum allowable airspeed (VNE/VMO/MMO). This maximum allowable airspeed display is configured to indicate the appropriate maximum allowable airspeed for the airplane, including variations for altitude or Mach number.
  • Page 195 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Navigation Navigation information is presented on the PFD through a combination of horizontal situation indicator (HSI), a lateral deviation indicator (LDI) above the heading display, vertical deviation indicator (VDI), and GPS navigation status information.
  • Page 196 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • HSI The course pointer and deviation indicator are shown as a single, solid line for GPS 1 and VLOC 1, and as an outline with no fill for GPS 2 and VLOC 2. GPS and VLOC sources are further differentiated with color.
  • Page 197 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Lateral Deviation Indicator (LDI) A Lateral Deviation Indicator (LDI) is always displayed on the PFD above the heading display. This LDI shows course deviation, navigation source, and VLOC station identifier or GPS phase of flight.
  • Page 198 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Terrain Awareness and Alerting (Optional) The following terrain awareness and alerting functions may be provided by the Txi system: Terrain Proximity, Terrain FLTA, or TAWS-B. If the GTN navigator is equipped with TAWS-B, then the Txi will display TAWS-B parameters provided by the GTN.
  • Page 199 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Databases The G500/G600 Txi system utilizes databases to provide some system functions. Database status information is available to the pilot at system startup on the MFD splash screen and during normal operations on the MFD system status page for units with an MFD, or PFD Menu for PFD only units.
  • Page 200 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS CAUTION Not all obstacles or wires are included in the databases. The Garmin SafeTaxi database contains airport diagrams for selected airports. This database is updated on a 56-day cycle.
  • Page 201 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Crew profiles The crew profile function is provided for units which have an MFD to allow the management of pilot controlled settings. If the aircraft is operated by multiple pilots, each pilot can recall their individual settings for use.
  • Page 202 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • System Settings The Setup page provides pilot controls for click volume, time format, and local time offset. Controls are provided to set the nearest airport criteria so that airports not usable by the aircraft type do not appear in waypoint searches.
  • Page 203 7.7 - INSTRUMENTS AND AVIONICS 7.7.5.2 BACKUP FLIGHT DISPLAY The S201 is equipped by a backup flight instrument display on the right side of the instrument panel. The KI 300 Electronic Attitude Indicator is a panel mounted attitude, 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.
  • Page 204 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 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 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS Information on main system functionalities are given below. For more information, consult the KI300 Pilot’s Guide referenced in section 1.8. • Initial Power-on Upon initial power-on, the unit will display the company logo, battery status and software version.
  • Page 206 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Alignment On power-up, the unit will perform an initial alignment. The aircraft should not be subjected to taxing or excessive motions during this process. Alignment is not normally performed during flight.
  • Page 207 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 7.7.6 COMMUNICATION AND NAVIGATION 7.7.6.1 AUDIO PANEL An audio panel is installed on top of the avionics rack to distribute audio to the crew. The Audio Panel includes an intercom system (ICS), a marker beacon receiver, a COM clearance recorder, USB power jack, and Bluetooth®...
  • Page 208 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS The audio volume is controlled by the following way: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-41 Rev. : A...
  • Page 209 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 7.7.6.2 GPS / COM1 / NAV1 Comunication and Navigation are interfaced on the GTN 650 equipment located in the center of the instrument panel. The GPS navigation, VHF communication and navigation radio functions are operated by dedicated hard keys, a dual concentric rotary knob, or the touchscreen.
  • Page 210 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Auto ILS CDI Capture Auto ILS CDI Capture will not automatically switch from GPS to VLOC for LOC-BC or VOR approaches. NOTE Approaches using Auto ILS CDI operation is to be used for situational awareness under VFR only •...
  • Page 211 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS If a flight plan contains a waypoint or procedure that does not correspond to a waypoint or procedure in the navigation database in use, the waypoint or procedure will become locked (depicted as “locked”) in the flight plan.
  • Page 212 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Map page The settings chosen by the pilot on the Map page menu (including obstacle and wire display ranges) are saved over a power cycle. • Dedicated Terrain Page (Optional) The dedicated Terrain page will always depict point obstacles at zoom scales of 10 nm or less and depict wire obstacles at zoom scales of 5 nm or less.
  • Page 213 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Flight Plan Depiction The map page depicts the current active flight plan. When an off-route Direct To is active the flight plan will no longer be depicted on the map.
  • Page 214 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS When navigating using GPS guidance most legs are TO type legs where distance to the next waypoint decreases along the route. However, some procedures include FROM type legs. When navigating on a leg that is a FROM leg indications that it is a FROM leg include the TO/FROM flag indicating FROM and distances increasing in distance fields.
  • Page 215 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS CDI and VDI indications are equivalent to those of other GPS-based approaches (e.g.- LPV or LNAV+V). The GTN annunciates “VISUAL” in the annunciator bar to indicate a visual approach is active.
  • Page 216 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS - When the GTN is installed with a multiple TXi PFDs, it is highly recommended that GDU BARO SYNC be enabled and used during all VNAV operations.
  • Page 217 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Along Track Waypoints The GTN allows for the creation of flight plan waypoints that are based off an offset distance from a waypoint in the flight and places the new along track waypoint (ATK) in the flight plan.
  • Page 218 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS • Flight Stream 510 (Optional) The Flight Stream product line uses a wireless transceiver to provide data to and from a GTN to personal electronic devices (PEDs).
  • Page 219 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.7 - INSTRUMENTS AND AVIONICS 7.7.6.3 COM2 / NAV2 (Optional) If equipped, 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.

  • Page 220: Flight Crew And Cabin

    S201 AFM 7.8 - FLIGHT CREW AND CABIN FLIGHT CREW AND CABIN The S201 can be used with the following crew: - Minimum crew : 1 pilot (left hand seat preferably) - Maximum occupants : 2 7.8.1 CANOPY OPENING AND CLOSING The airplane is equipped with a sliding canopy mechanism.
  • Page 221 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.8 - FLIGHT CREW AND CABIN 7.8.2 COCKPIT LAYOUT The cockpit layout is configured conventionally. Baggage space is immediately behind the seats and can be accessed easily by moving the seat backrest forward by lifting the small lever on each seat’s external side.
  • Page 222 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.8 - FLIGHT CREW AND CABIN 7.8.3 SEATS AND SAFETY HARNESSES Seats are constructed in aluminium and covered with cushions. Each seat can be adjusted backwards and forwards for comfort with forward movement, which is slightly raising the seat height, in order to ensure that the rudder pedals can easily be reached by all pilots –...
  • Page 223 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.8 - FLIGHT CREW AND CABIN 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.
  • Page 224 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.8 - FLIGHT CREW AND CABIN 7.8.4 BAGGAGE COMPARTMENT The baggage compartment comprises two sections positioned behind the seats and is designed to carry up to 35 kg (77 lb) in total.
  • Page 225 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.8 - FLIGHT CREW AND CABIN 7.8.5 CABIN HEAT SYSTEM Heated air (warmed by a heat exchanger around the engine exhaust) can be selected via a selection lever located on the instrument panel. Refer to the instrument panel layout in paragraph 7.5.
  • Page 226 7.8 - FLIGHT CREW AND CABIN 7.8.6 EMERGENCY LOCATION TRANSMITTER (OPTIONAL) The S201 can be equipped by an optional ELT system. If equipped, an emergency switch is located on the instrument panel immediately above the PFD. When activated using the switch on the instrument panel, the ELT will send a distress signal via radio and satellite that will allow SAR services to easily locate the aircraft.

  • Page 227: Powerplant

    The engine’s Operator Manual is provided with the aircraft. 7.9.1 ENGINE – GENERAL The S201 is equipped by a Rotax 914 F which is a 4-stroke, 4-cylinder, horizontally opposed, turbocharged spark ignition engine with one central camshaft using pushrods driven OHV (2 valves per cylinder).
  • Page 228 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT Following items should be inspected during pre-flight check: Fuel pressure regulator and pipes leading to/from it Engine mount Throttle and Choke cables on both carburettor All visible wirings Coolant...
  • Page 229 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 7.9.2 COOLING SYSTEM The Rotax 914 features dual cooling means: • Cylinders are air cooled. • Cylinder heads are liquid cooled via a closed circuit system with an expansion tank. A camshaft driven coolant pump circulates coolant from a radiator through the cylinder heads, then through an expansion bottle and back to the radiator.
  • Page 230 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 7.9.3 LUBRIFICATION SYSTEM The engine is provided with a dry sump forced lubrication system with a camshaft driven main pump with integrated pressure regulator and additional suction pump. The main pump delivers oil from the oil reservoir, through an oil cooler (radiator) and oil filter to points of lubrication.
  • Page 231 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 7.9.4 OPERATING CONTROLS Engine power is controlled by means of a hand operated throttle lever situated on the cabin centre console. Forward movement of the throttle lever increases engine power output and backward movement decreases engine power output.
  • Page 232 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 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.
  • Page 233 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT The TCU controls two indicator lights mounted on the instrument panel. When supply voltage is supplied to the TCU (master switch is switched on) the TCU is subjected to a self test. Both the BOOST and CAUTION lights should illuminate for 1 to 2 seconds and then turn off.
  • Page 234 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 7.9.6 PROPELLER The aircraft is equipped by a DUC Hélices FLASH-R 3 blade, 1750mm diameter, ground adjustable propeller. It is constructed from carbon fiber with an Inconel leading edge protection.
  • Page 235 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 7.9.7 ENGINE MONITORING SYSTEM (EMS) The Sonaca 201 features a JPI EDM900 instrument to control all powerplant parameters. An explanation of the control screen is given in the picture below, and essential information about control buttons is given in the next pages.
  • Page 236 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT Buttons operations Action on EMS In the Automatic mode, tapping the STEP button stops Scanner autosequencing and changes to Manual STEP mode. Each tap of the STEP button then displays the next measurement in the sequence.
  • Page 237 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT • Detailed information on important functionalities: o Fuel management: USD (used fuel) is automatically reset whenever you perform REFUEL on your EDM (except if TRIP mode = yes). After filling your tanks and prior to engine start you should inform the EDM that the aircraft has been filled.
  • Page 238 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT Trip mode is typically used if you want to track the total fuel used over a multi- stop cross country. To have the USD parameter continuously accumulate total consumed fuel, set TRIP? Y. ‘Trip Mode’ is described in the ‘Program Mode section’...
  • Page 239 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 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°...
  • Page 240 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT next page). Coolant: shock cooling alarm is set to -51°C/minute. Average cool rates of -22°C/minute to -28°C/minute are normal 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-73 Rev. : A...
  • Page 241 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT • Engine Diagnosis Chart: The following charts can be used to diagnose engine problems and perform troubleshooting in your aircraft. 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-74 Rev. : A...
  • Page 242 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.9 - POWERPLANT 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-75 Rev. : A...

  • Page 243: Fuel System

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 7.10 FUEL SYSTEM The airplane has 2 fuel tanks located each in the inside leading edge of each wing. Each tank is equipped with a vent with an internal inlet at the inboard top of the tank and the outlet underneath the wing.
  • Page 244 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 7.10.1 FUEL TANKS The Sonaca 201 is equipped with 2 wing tanks, each tank integrated within the inboard wing leading edges and equipped with strainers in pick up line and drain fittings.
  • Page 245 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 7.10.2 FUEL SELECTOR Fuel tank feed selection is enabled by a red coloured, three-position (RIGHT, LEFT, OFF) rotary fuel selector valve, located at the bottom centre of the instrument panel / front of centre console.
  • Page 246 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 7.10.4 FUEL FILTER AND PRESSURE REGULATOR In addition to the finger screen in the tank outlet, the fuel feed from the fuel pumps enters a filter, also called Gascolator, which filters dusts and sediments as well as water that may have accumulated in the tanks.
  • Page 247 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 7.10.5 FUEL FLOW METERS The Sonaca 201 is equipped with two fuel flow meters to measure the amount of fuel per hour pumped to the pressure regulator, and the amount returning from the regulator to the tank.
  • Page 248 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 7.10.6 FUEL QUANTITY INDICATION AND EVALUATION The Sonaca 201 features 3 independent methods to assess and manage fuel quantity on board. These methods are described below. • Fuel quantity indication on EMS : After EMS start-up, the fuel quantity is indicated in the bottom right corner of the screen on two gages, one per fuel tank.
  • Page 249 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM 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 and must be evaluated visually using both procedures on next pages.
  • Page 250 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.10 - FUEL SYSTEM • Visual fuel quantity evaluation : The remaining fuel quantity in each fuel tank can be evaluated visually after opening the fuel filler cap: Visual mark Corresponding fuel level...

  • Page 251: Electrical System

    7.11 - ELECTRICAL SYSTEM 7.11 ELECTRICAL SYSTEM This paragraph describes electrical systems on board of the S201 and includes wiring diagrams which are relevant or can aid the pilot’s understanding of the aircraft’s systems with respect to the operational procedures described in this manual.
  • Page 252 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.11 - ELECTRICAL SYSTEM 27/06/2019 SONAIR-S2-D-MAN-006 Page : 7-85 Rev. : A...
  • Page 253 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.11 - ELECTRICAL SYSTEM 7.11.2 CHARGE SYSTEM The alternating current (AC) output of the engine driven alternator is routed to a rectifier / regulator where it is rectified and regulated, to provide 12V direct current (DC) output available to the aircraft systems.
  • Page 254 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.11 - ELECTRICAL SYSTEM NOTE Alternator 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.
  • Page 255 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.11 - ELECTRICAL SYSTEM 7.11.4 MAIN BUS Following equipment are directly connected to the main bus and may become non-operational in case of main bus power supply failure: Auxiliary fuel pump Flaps Cabin and instruments light(s) Strobe, navigation and taxi lights.
  • Page 256 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.11 - ELECTRICAL SYSTEM NOTE The engine ignition system is independent of the aircraft electrical system (except for starter motor operation) and will operate even with the master switch and / or any circuit breaker(s) off. However the engine requires adequate power supply to at least one electrical fuel pump to remain operational (to prevent fuel starvation).
  • Page 257 7.11 - ELECTRICAL SYSTEM 7.11.10 EXTERNAL POWER CONNECTION The S201 is equipped by a ground power supply receptable, to allow for easy power connection when on ground. The ground power supply can also be used for starting the engine, but limitations from sections 2.11.3 and 2.11.5 must always be complied with.
  • Page 258 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.11 - ELECTRICAL SYSTEM For Ground Power Supply able to provide multiple voltage, care must be taken to always select 14V mode and check actual output voltage before connecting the unit to the aircraft.

  • Page 259: Landing Gear

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.12 - LANDING GEAR 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.
  • Page 260 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.12 - LANDING GEAR 7.12.2 BRAKING SYSTEM The aircraft braking system is differential, foot controlled braking system acting on both wheels of the main landing gear through disk brakes. Each brake calliper, on left and right hand wheels, is separately actuated by an independent hydraulic line.
  • Page 261 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.12 - LANDING GEAR Right wheel Left wheel brake pedal brake pedal Parking brake valve To actuate the brakes using pedals, apply pressure on the top of each pedals using your toes. This will rotate the pedals around their central axis, and compress the two brakes cylinders.

  • Page 262: Minimum Instruments And Equipments For Flight

    7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.13 - MINIMUM INSTRUMENTS AND EQUIPMENTS FOR FLIGHT 7.13 MINIMUM INSTRUMENTS AND EQUIPMENTS FOR FLIGHT The following minimum instrumentation and equipment is required for day VFR flight : • One Airspeed, Altitude and Attitude indications operative (Either on PFD or on Backup Flight Instrument) •...
  • Page 263 7 - AIRPLANE AND SYSTEMS DESCRIPTION S201 AFM 7.13 - MINIMUM INSTRUMENTS AND EQUIPMENTS FOR FLIGHT In addition, following minimum instrumentation and equipment are required for night VFR flights: • One operative NAV source (GPS, NAV1 or NAV2 if equipped) and its interfaced display (PFD if used for EHSI) •...
  • Page 264 8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.1 - TABLE OF CONTENT 8 AIRPLANE GROUND HANDLING AND SERVICING TABLE OF CONTENT TABLE OF CONTENT ................. 8-1 INTRODUCTION ................8-2 AIRPLANE INSPECTION INTERVALS ..........8-3 AIRPLANE ALTERATION OR REPAIRS ..........8-4 GROUND HANDLING ...............

  • Page 265: Introduction

    8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.2 - INTRODUCTION INTRODUCTION This section contains factory-recommended procedures for proper ground handling 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.

  • Page 266: Airplane Inspection Intervals

    8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.3 - AIRPLANE INSPECTION INTERVALS AIRPLANE INSPECTION INTERVALS Refer to the maintenance manual 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: •...

  • Page 267: Airplane Alteration Or Repairs

    8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.4 - AIRPLANE ALTERATION OR REPAIRS AIRPLANE ALTERATION OR REPAIRS 8.4.1 MODIFICATIONS It is mandatory that you contact the aircraft manufacturer and get its authorization prior making any modifications to the aircraft, to ensure that the airworthiness of the aircraft is not affected.

  • Page 268: Ground Handling

    HANDLING AND SERVICING S201 AFM 8.5 - GROUND HANDLING GROUND HANDLING The S201 can be manoeuvred on ground with or without tow bar. Read carefully following procedures to ensure safe manoeuvres. CAUTION Check surrounding aircraft and hangar doors / pillars before maneuvering the aircraft on ground.
  • Page 269 8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.5 - GROUND HANDLING 8.5.2 GROUND HANDLING WITHOUT TOW BAR If you wish to move the aircraft on the ground otherwise than under its own power, it is best to pull the aircraft forwards or push it backwards by hand holding one or more propeller blades, close to the spinner.
  • Page 270 8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.5 - GROUND HANDLING 8.5.3 TOWING BY VEHICLE ON GROUND The aircraft may be towed at slow speed on an even ground by a rope attached to a vehicle. In this case, following precautions must be taken: 1.
  • Page 271 8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.5 - GROUND HANDLING 8.5.4 PARKING It is advisable to park the aircraft inside a hangar, or alternatively inside any other suitable space (garage), with stable temperature, good ventilation, low humidity and a dust-free environment.
  • Page 272 8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.5 - GROUND HANDLING 8.5.6 JACKING Jacking must be done by authorized maintenance operators in accordance with the Maintenance Manual. NOTE Nobody is authorized in the cockpit during aircraft jacking operation.

  • Page 273: Cleaning And Care

    8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.6 - CLEANING AND CARE CLEANING AND CARE This paragraph describes cleaning procedures, explains the recommended cleaning agents and give caution notes. 8.6.1 PAINTED SURFACES Use efficient cleaning products to clean the aircraft surface. Oil spots on the aircraft surface may be cleaned with petrol / gasoline.
  • Page 274 8 - AIRPLANE GROUND HANDLING AND SERVICING S201 AFM 8.6 - CLEANING AND CARE 8.6.4 ENGINE Refer to the latest revision of the ROTAX 914 F operator manual for cleaning information. WARNING Use only approved cleaning agent for cleaning metal parts. Non observance can lead to damage to the cooling system and engine.
  • Page 275 9 - ADDITIONAL INFORMATION S201 AFM 9.1 - TABLE OF CONTENT 9 ADDITIONAL INFORMATION TABLE OF CONTENT TABLE OF CONTENT ................. 9-1 INTRODUCTION ................9-2 ENHANCED SAFETY TAKE-OFF ............9-3 OTHER MARKINGS AND PLACARDS ..........9-4 LIST OF SUPPLEMENTS..............9-9 AMENDMENTS ................

  • Page 276: Introduction

    9 - ADDITIONAL INFORMATION S201 AFM 9.2 - INTRODUCTION INTRODUCTION This section contains the appropriate supplements necessary to safely and efficiently operate the aeroplane when equipped with various optional systems and equipment not provided 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.

  • Page 277: Enhanced Safety Take-Off

    9 - ADDITIONAL INFORMATION S201 AFM 9.3 - ENHANCED SAFETY TAKE- ENHANCED SAFETY TAKE-OFF 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...

  • Page 278: Other Markings And Placards

    9 - ADDITIONAL INFORMATION S201 AFM 9.4 - OTHER MARKINGS AND PLACARDS OTHER MARKINGS AND PLACARDS The 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.
  • Page 279 9 - ADDITIONAL INFORMATION S201 AFM 9.4 - OTHER MARKINGS AND PLACARDS 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:...
  • Page 280 9 - ADDITIONAL INFORMATION S201 AFM 9.4 - OTHER MARKINGS AND PLACARDS Between the cabin heat system controls: Around the canopy handle: Adjacent to the microphone jacks: 27/06/2019 SONAIR-S2-D-MAN-006 Page : 9-6 Rev. : A...
  • Page 281 9 - ADDITIONAL INFORMATION S201 AFM 9.4 - OTHER MARKINGS AND PLACARDS 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: 27/06/2019...
  • Page 282 9 - ADDITIONAL INFORMATION S201 AFM 9.4 - OTHER MARKINGS AND PLACARDS 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: List Of Supplements

    9 - ADDITIONAL INFORMATION S201 AFM 9.6 - AMENDMENTS LIST OF SUPPLEMENTS NONE at initial issue of this document Date Manufacturer Document Reference Title Section 1 - General: system or equipment specifically addressed. Section 2 - New limitations markings or placards.

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