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Remos G 2008 Series Pilot Operating Handbook

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  • Page 2 Rev. 01 – 07-01-2008 Aircraft Data Light Sport Aircraft REMOS GX with Rotax 912 UL-S Engine The REMOS GX was manufactured in accordance with the Light Sport Aircraft airworthiness standards and does not conform to standard category airworthiness requirements. Serial No.: Engine-Type: Year of constr.:...
  • Page 3 Rev. 01 – 07-01-2008 List of Effective Pages This POH consists of the following listed pages and sections. You will find a marking, indicating the revison and date of issue at the top border of each page. Insert latest changed pages, destroy superseded pages.
  • Page 4 Rev. 01 – 07-01-2008 Remarks and Alterations Applied Modifications Please make a notation below, if any changes have been made to this manual or to the plane. This manual is an important documentation for pilots in command to ensure a safe operation of the aircraft. Therefore it is recommended to keep this Operating Handbook updated with the newest information available.
  • Page 5 Rev. 01 – 07-01-2008 Remarks and Alterations Applied Modifications (continued) Pos. Page Concern Date Signature...
  • Page 6 Rev. 01 – 07-01-2008 Table of Contents General Information about this Handbook This Flight Operation Handbook is divided into several chapters. The structure of this handbook complies to the Light Sport Aircraft airworthiness standards. Section Description Page General Information 1-1 thru 1-3 Airplane and Systems Descriptions 2-1 thru 2-21 Operating Limitations...
  • Page 7 Rev. 01 – 07-01-2008 Views The REMOS GX is designed as full composite carbon fiber aircraft.

  • Page 8: Paragr. Description Page

    Rev. 01 – 07-01-2008 General Information Table of Contents Paragr. Description Page Introduction Certification Quick Reference Technical Specifications General Information 1 - 1...
  • Page 9 This Operation Handbook is designed to help enable a safe and successful completion of each flight with the REMOS GX. It provides you with all necessary information for regular maintenance and operation of the aircraft. Therefore we recommend that the pilot keeps this Operating Handbook upgraded with the newest information available.
  • Page 10 Rev. 01 – 07-01-2008 General Information Layout: Main components are built in halfshells from composite fiber material, which are bonded together (carbon fiber, Kevlar and glass fiber). Engine: Rotax 912 UL-S Propeller: 2-blade ground adjustable (composite) Technical Specifications Specifications posted below are related with an MTOM of 1320 lb. Wingspan 30.6 ft Overall Length...
  • Page 11 Rev. 01 – 07-01-2008 Airplane and Systems Description Table of Contents Paragr. Description Page Paragr. Description Page Engine 2.14 Center Console 2-13 Propeller, Gearbox 2.15 Avionics Equipment 2-14 Fuel and Fuel Capacity 2.16 Secondary Instrumentation… 2-17 Engine Oil, Coolant 2.17 Glass Cockpit –...
  • Page 12 Rev. 01 – 07-01-2008 Airplane and Systems Description Engine Manufacturer: Bombardier-Rotax Engine type: 912 UL-S * Max. power: at take-off: 73,6 kW / 100 hp permanent: 69,9 kW / 95 hp Max. rpm: at take-off: 5,800 rpm. permanent: 5,500 rpm. Max.
  • Page 13 Rev. 01 – 07-01-2008 Airplane and Systems Description Engine Oil, Coolant Engine oil: Automotive engine oils * Engine oil capacity: 0.75 gallons (2.8 liters) Recommended oil: Motorcycle oil of a registered brand with gear additives Recommended cooling fluid: Conventional coolant, ethylene glycol based Coolant capacity: 0.65 gallons (2.5 liters) Ratio:...
  • Page 14 Cockpit Overview Cockpit example The following pages will give you more information about how to operate your REMOS GX. Note: Some of the illustrated devices or options may not be available, due to the regulations of the ASTM standard. Please ask your local dealer for more information.
  • Page 15 Rev. 01 – 07-01-2008 Airplane and Systems Description Airplane and Systems Description 2 - 5...
  • Page 16 Rev. 01 – 07-01-2008 Airplane and Systems Description Basic Instrumentation (“Explorer”) The basic equipment of your REMOS GX consists of the following: ASI, VSI, Altimeter, Slip Indicator, Magnetic Compass, Rotax FLYdat (rpm, operation hours indicator, exhaust gas-, oil pressure-, oil temp.-, CHT temp.-gauges).
  • Page 17 Rev. 01 – 07-01-2008 Airplane and Systems Description Rotax FLYdat The Rotax FLYdat represents an instrument, specially developed for the Rotax engine for indicating and acquisition of engine operating data. The operating data is being permanentely compared with the specific engine operating limit. If the signalled operating data exceeds the stored operating limit, the FLYdat will create a warning.
  • Page 18 Rev. 01 – 07-01-2008 Airplane and Systems Description Analog Engine Gauges (customized only) With the anlog engine gauges installed, there is no exhaust gas temperature and no hours of operation recording available. It is strongly recommended to maintain the values below, to achieve the maximum engine performance and endurance.
  • Page 19 Rev. 01 – 07-01-2008 Airplane and Systems Description 2.10 Control Panel Most of the major controls and switches to operate the aircraft are combined on the central control panel. All switches are labeled definitely. The following functions are contained: • Electric trim control lever (blue) •...
  • Page 20 Airplane and Systems Description 2.11 Electric Fuses The electrical system of the Remos GX consists of a Master-Bus system, which allows installation of additional equipment very easily. The Master-Bus is separated into Master and Avionics circuits, each populated by 6 automatic circuit breakers. An additional charge fuse is loctated in front of the firewall, beneath the battery bracket.
  • Page 21 Airplane and Systems Description 2.12 Cockpit Lighting The REMOS GX cockpit does feature an effective LED panel lighting system, which can be dimmed independently from the instrument lights. It is a dazzle-free system designed for Night-VFR use. At the left border of the cockpit frame, you will find the dim control knob. The system is activated when the instrument lighting switch located on the switchboard is switched on.
  • Page 22 Rev. 01 – 07-01-2008 Airplane and Systems Description 2.13 Dual Throttle, Oil Temperature Control, Additional Terminals Two extension panels are located to the left and to right of the cockpit frame which are used as follows: Left Panel (illustrated to the right) At the upper position the oil temperature control is installed.
  • Page 23 Rev. 01 – 07-01-2008 Airplane and Systems Description 2.14 Center Console The following controls are located on the center console: • Choke – green • Carburetor heat – yellow • Fresh air control – blue • Cabin heat – red •...
  • Page 24 The REMOS GX provides a modular cockpit system which enables to install a wide range of Comm and NAV equipment. A radio rack for the most popular devices, associated with the REMOS „plug-n-fly“ harnesses allows easy installation of add-on´s and guarantees interference-free operation.
  • Page 25 Rev. 01 – 07-01-2008 Airplane and Systems Description Combination A (“Explorer”/“Aviator I”-package with GPS option) This avionics package contains a Garmin SL-40 radio, along with a Garmin Mode-C(S) transponder GTX-327 (GTX-330). With the PS-E 1000 intercom there is an additional audio input provided, enabling connection of external audio equipment.
  • Page 26 Rev. 01 – 07-01-2008 Airplane and Systems Description Combination B (“Aviator II”/“Cross-Country”-package) This package consists of a Garmin SL-40 radio, a NAV/Comm Garmin SL-30, a Mode-S transponder Garmin GTX-330, along with the audio-panel Garmin GMA-340. An audio input allows connection of external audio devices.
  • Page 27 Rev. 01 – 07-01-2008 Airplane and Systems Description 2.16 Secondary Instrumentation – Right Hand Panel The right panel can be equipped with additional gauges and indicators depending on what primary flight instrumentation is installed (standard instrumentation illustrated to the left). The pictures below are showing the factory installed gauges.
  • Page 28 Alternatively to the common primary flight instruments, a glass cockpit system is available too (“Aviator I and Aviator II”-package). REMOS has decided for the reliable and well approved Dynon-Avionics system. This system consists of an EFIS D-100 as a primary flight display, along with an analog airspeed indicator, altimeter and slip indicator as back-up instrumentation.
  • Page 29 Rev. 01 – 07-01-2008 Airplane and Systems Description Glass-Cockpit version B (“Aviator II”-package) In comparison to version A the engine monitoring and various secondary gauges are combined in the Dynon EMS D-120 monitor, so some of the additional gauges are to be omitted. With the HS-34 HSI-module is installed you will find the airspeed indicator and the altimeter as a back-up instrumentation installed into the right panel (see 2.16).
  • Page 30 The EFIS D-100 is a so called “Primary Flight Display”, means, that all common primary flight instruments are to be simulated and displayed on one screen. REMOS is offering only the „Super-Bright-Version“ of the EFIS D-100, compared to the standard version, it provides a much brighter display, allowing very good visibility during broad daylight.
  • Page 31 The EMS D-120 is a so called „MFD – Multi Functional Display“. Like the EFIS D-100 it does collect a wide range of engine parameters and additional functions on one wide display screen. Installed in the REMOS GX the functions listed below are displayed by the EMS D-120. The following functions are covered by the EMS D-120: •...
  • Page 32 Rev. 01 – 07-01-2008 Operating Limitations Table of Contents Paragr. Description Page Airspeed Limits Cross Wind Limitations Service Ceiling Load Factors Prohibited Flight Maneuvers Center of Gravity Range Permissible Flight Maneuvers Operating Limitations 3 - 1...
  • Page 33 Rev. 01 – 07-01-2008 Operating Limitations Airspeed Limits Bez. Speed Description 155 mph Never exceed speed Airspeed which shall never be exceeded (134 kts) 137 mph Maximum airspeed at maximum continuous Maximum speed in level flight power setting (119 kts) 108 mph Maximum airspeed for all permissible Maneuvering speed...
  • Page 34 Rev. 01 – 07-01-2008 Operating Limitations Cross Wind Limitations Maximum demonstrated cross wind component 17 mph (15 knots) for take-off and landing: Service Ceiling Maximum permissible service ceiling: 15,000 ft Load Factors Safe multiple load range: +4.0 g, -2.0 g Prohibited Flight Maneuvers •...
  • Page 35 Rev. 01 – 07-01-2008 Operating Limitations Center of Gravity Range The permissible center of gravity range during flight has to be within the limits of: 9.6 thru 16.3 inch (measured from the leading edge of the wing, close to the fuselage). To determine the CG, the weight of the aircraft has to determined, equipped with all devices ready to fly except fuel and baggage.
  • Page 36 Rev. 01 – 07-01-2008 Weight and Balance Information Table of Content Paragr. Description Page Installed Equipment List Weight and Balance Form Center of Gravity (CG) Range and Determination CG-Calculation Calculation Example CG-Diagram Aircraft Specific Weights Weight and Balance Information 4 - 1...
  • Page 37 Rev. 01 – 07-01-2008 Weight and Balance Information Installed Equipment List • To meet the requirements of the Airspeed indicator LSA airworthiness standard, the • Altimeter listed minimum instrumentation is • Vertical speed indicator provided as basic equipment. • Compass •...
  • Page 38 Rev. 01 – 07-01-2008 Weight and Balance Information Center of Grafity (CG) Range and Determination To determine “CG”, put the aircraft on 3 weighing scales, positioned on a level surface. Before weighing, a level wing main chord has to be established (use pads between main wheels and scale beneath). A check-mark (R.P.) on the leading edge of the left wing, adjacent to the wing root is provided to ease examination to level wing main chord - use a flexible clear hose, filled with water as a spirit level.
  • Page 39 Rev. 01 – 07-01-2008 Weight and Balance Information CG-Calculation The following procedure has to be maintained for the correct calculation of the center of gravity “CG”. Moment (lb-Inch) = Weight (lb) x Arm (Inch) Moment Total (lb-Inch) Center of Gravity (Inch) = Weight Total (lb) Weight Moment...
  • Page 40 Rev. 01 – 07-01-2008 Weight and Balance Information Calculation Example The following example is given to show how to calculate the center of gravity „CG“. Weight Moment Inch lb-Inch Empty Weight 12.5* 8,375 Occupants 1,452.5 Fuel 37.8 4,536 Luggage 37.4 1,122 Weight Total: Moment Total:...
  • Page 41 Rev. 01 – 07-01-2008 Weight and Balance Information CG-Diagram Weight and Balance Information 4 - 6...
  • Page 42 Rev. 01 – 07-01-2008 Weight and Balance Information Aircraft Specific Weights Below the aircraft specific data shall be notified. Pilots must use this information to ensure a correct weight and balance calculation prior to every flight. This is essential for a safe conduction of each flight. Empty Weight: Maximum Take-Off Weight: Maximum Payload:...
  • Page 43 Rev. 01 – 07-01-2008 Performance Table of Contents Paragr. Description Page Take-Off and Landing Distances Rate of Climb Take-Off Distance Effected by External Circumstances Take-Off Distance Effected by Pressure Altitude Pressure Altitude Diagramm Cruise Speeds, RPM, Fuel Consumption and Range Performance 5 - 1...
  • Page 44 Rev. 01 – 07-01-2008 Performance Take-Off and Landing Distances Description Take-off roll distance (Flaps 15°) 510 ft Take-off distance* (Flaps 15°) 730 ft Landing roll distance (Flaps 40°) 270 ft Landing distance* (Flaps 40°) 760 ft Rate of Climb Description Airspeed for best angle of climb V (IAS) 75 mph...
  • Page 45 Rev. 01 – 07-01-2008 Performance Take-Off Distance Effected by External Circumstances Determined data apply for ISA conditions and a dry, hard runway surface. Various circumstances have an effect on take-off and landing performance. According to ICAO-circular 601AN/55/2 it is recommended to use following ad-ons on roll- and air distances: Description On roll distance for dry grass...
  • Page 46 Rev. 01 – 07-01-2008 Performance Take-Off Distance Effected by Pressure Altitude Performance 5 - 4...
  • Page 47 Rev. 01 – 07-01-2008 Performance Pressure Altitude Diagramm Performance 5 - 5...
  • Page 48 Rev. 01 – 07-01-2008 Performance Cruise Speeds, RPM, Fuel Consumption and Range Rotax 912 UL-S, 100 hp engine Engine Speed Manifold Fuel True Maximum Maximum Pressure Consumption Airspeed Endurance Range rpm. InchHG at 3000 ft, mph hr : min. 5,400 3:31 5,100 4:02...
  • Page 49 Rev. 01 – 07-01-2008 Emergency Procedures Table of Contents Paragr. Description Page Door Emergency Eject Recovering from Stall Rescue System Operating the Rescue System Illustrated Rescue System Installation Engine Failure / Loss of Power before Take-Off Engine Failure after Take-Off Engine Failure in Flight Emergency Landing Procedure 6.10...
  • Page 50 Rev. 01 – 07-01-2008 Emergency Procedures This section will show you all the procedures which have to be applied in case of an emergency or another dangerous situation. You will also get important information regarding the use of the recommended rescue system. Door Emergency Eject Unlock the doors, by rotating back the door lock handle.
  • Page 51 Rev. 01 – 07-01-2008 Emergency Procedures Rescue System (optional) The installation of the rescue system shall be carried out complying with the recommendations of the manufacturer. To do so, the aircraft is already prepared for the installation of a BRS/Magnum rescue system.
  • Page 52 Rev. 01 – 07-01-2008 Emergency Procedures Illustrated Rescue System Installation 1. Emergency handle 2. Connection, kevlar bridles to main spar 3. Recovery system rocket 4. Parachute softpack 5. Rubber protection of the eject area Emergency Procedures 6 - 4...
  • Page 53 Rev. 01 – 07-01-2008 Emergency Procedures Engine Failure / Loss of Power before Take-Off If any trouble regarding engine power is determined during taxiing or take-off run, the following procedures shall be applied: • Pull throttle lever to idle position •...
  • Page 54 Rev. 01 – 07-01-2008 Emergency Procedures Engine Failure in Flight If the engine fails during flight, check the fuel level first. Now try to get the engine started again. If the engine does not start again, an emergency landing in gliding configuration has to be conducted. Emergency Landing Procedure 1.
  • Page 55 Rev. 01 – 07-01-2008 Emergency Procedures 6.11 In-Flight Engine Fire Procedure 1. Shut-off fuel flow by closing fuel valve 2. Push the throttle lever fully forward until engine stops 3. Try to extinguish the flames by a fast descent carried out as slip 4.
  • Page 56 Rev. 01 – 07-01-2008 Normal Procedures Table of Contents Paragr. Description Page Preflight Check Starting the Engine Taxiing Normal Take-Off Best Angle of Climb Speed (V Best Rate of Climb Speed (V Cruise Approach Normal Landing 7.10 Short Field Take-Off 7.11 Aborted Landing Procedure 7.12...
  • Page 57 Rev. 01 – 07-01-2008 Normal Procedures This section provides you with all the procedures for normal operation of the aircraft including preflight preparations. Preflight Check Before each flight the following checks have to be conducted: Checks outside the aircraft 1. Before moving the aircraft drain possible water from the fuel tank, using the drain valve Check engine oil level (between 1/2 and 1/4 of marking)* Check level of engine coolant (between min.
  • Page 58 Rev. 01 – 07-01-2008 Normal Procedures Checks inside the aircraft Check fuel level Check mounting of rescue system Check that both seats are properly secured in position Close and lock both doors Buckle up Set parking brake Check proper functioning of the flap drive and gauge Set oil temperature regulator flap to take-off position (cooler) Remove rescue system securing pin from emergency handle 10.
  • Page 59 Rev. 01 – 07-01-2008 Normal Procedures If the engine does not start, release the key to position "0", wait 2 minutes and repeat the procedure. Release ignition key, immediately after the engine has started Push the choke lever forward Switch of the electric fuel pump (if fitted) Starting a hot engine: 1.
  • Page 60 Normal Procedures Taxiing The steerable nosewheel of the REMOS GX allows easy ground handling. Turns of 49 feet in diameter can be conducted easily. The main gear is equipped with effective hydraulic disc brakes, which are operated by a lever on top of the middle section between the seats.
  • Page 61 Rev. 01 – 07-01-2008 Normal Procedures Best Angle of Climb Speed (V The best angle of climb is achieved at an airspeed of 68 to 75 mph (59 to 65 kts). Please watch oil and water temperature during long periods of climbing. If an oil temperature regulation flap is mounted, it must be set to position "open"...
  • Page 62 Rev. 01 – 07-01-2008 Normal Procedures Approach To prepare for approach, switch on the electric fuel pump (if fitted) and set the elevator trim to the neutral position, set carburetor heat to "warm" (pull) as necessary. When entering final, we recommend establishing an airspeed of 75 to 80 mph (65 to 70 kts) and extending flaps to the 40°...
  • Page 63 Rev. 01 – 07-01-2008 Normal Procedures 7.12 Low Airspeed and Stall If the center of gravity is within the permissible range, the aircraft will be fully controllable until reaching the stall speed. If stall speed is reached, the pilot should lower the nose of the aircraft to reestablish a safe airspeed.
  • Page 64 Rev. 01 – 07-01-2008 Normal Procedures Performing a stall in turns CG at most rearward position (airspeeds in CAS), 30° bank Flap Position 0° 15° 30° 40° at idle 51 mph (44 kts) 47 mph (41 kts) 44 mph (38 kts) 44 mph (38 kts) min.
  • Page 65 Rev. 01 – 07-01-2008 Aircraft Ground Handling and Servicing Table of Contents Paragr. Description Page Paragr. Description Page Servicing Fuel, Oil and Coolant 8.14 Hydraulic Brakes and Wheels 8-10 Towing and Tie-Down Instructions 8-2 8.15 Nose Gear Servicing 8-15 100 hr Service 8.16 Changing Engine Oil 8-16...
  • Page 66 Towing and Tie-Down Instructions Due to the low weight of the REMOS GX it is very easy to move the aircraft on the ground by hand. That´s why there is no special equipment for towing provided. In no case the aircraft shall be towed by attaching any kind of towing equipment to the nose wheel! To tie the aircraft we recommend the use of three ropes (left wing, right wing, and tail).
  • Page 67 The first after sales service has to carried out after 20 hours of flight time. Thereafter, every 100 hours or at least every 12 months the aircraft has to maintained following the REMOS maintenance checklist. Refer to the detailed factory Checklist-B, latest issue! Visually check the outer skin of the aircraft for scratches, dents and other damage Change the engine oil (about 0.8 gallon) and the oil filter element...
  • Page 68 Every 300 hours, the following additional checks/services are required. The aircraft has to maintained following the REMOS maintenance checklist. Refer to the detailed factory Checklist-B, latest issue! Exchange brake fluid (use DOT 4 fluid; – aircraft brake fluid must NEVER be used)
  • Page 69 (ask your local dealer). With these supports mounted, wings are secured properly and the handling of the aircraft will be much easier. When the aircraft has to be moved by trailer, please ask your authorized REMOS dealer for advice. When placed on a trailer in a wrong way, serious damage could result.
  • Page 70 Rev. 01 – 07-01-2008 Aircraft Ground Handling and Servicing Connecting folded Wings to Fuselage Withdraw the main wing securing bolt from the wing and place it nearby. Ensure that the bolt stays clean until remounted. Remove the wing support aid bracket while a second person is supporting the wing at the wing tip. Now the second person at the wing tip moves the wing slowly forward while securing that the wing does not spin around its axis.
  • Page 71 Rev. 01 – 07-01-2008 Aircraft Ground Handling and Servicing Installing Horizontal Stabilizer Like connecting the wings it is recommended to follow this procedure by two persons. One person is needed to hold the stabilizer in place, while the second person applying the two fixing bolts into their bushes through the fuselage tail.
  • Page 72 Aircraft Ground Handling and Servicing 8.12 Airframe Servicing The body design of the REMOS GX consists of carbon fiber materials, which ensures extreme strength and a long lifetime of the whole aircraft. Maintenance is reduced to checks of the moving parts such as: locks, hinges and connections.
  • Page 73 Aircraft Ground Handling and Servicing 8.13 Main Gear Servicing The REMOS GX may be equipped either with a composite or with a steel main gear. As with the fuselage, the main gear requires no regular servicing. The hydraulic hoses of the brake system are located within the hollow gear legs on the fiberglass gear, or hidden from the strut covers on the steel version.
  • Page 74 8.14 Hydraulic Brakes and Wheels General The REMOS GX wheels consit of three aluminum rims connected to a wheel hub, a multiply tire is installed together with an inner tube. Please watch for correct air pressure to avoid damage to the wheels.
  • Page 75 Remove all three brake disc fixing screws and separate wheel from brake disc (not applicable with REMOS Brake System installed). The pad thickness has to be 0.08 In at least, while minimum thickness of the brake disc is 0.13 In.
  • Page 76 Release the brake hose retaining clamp and withdraw the whole wheel/brake assembly from the wheel axle. Remove the three brake disc fixing screws for separating brake system from wheel (not applicable with the REMOS Brake System installed). Aircraft Ground Handling and Servicing 8 - 12...
  • Page 77 Rev. 01 – 07-01-2008 Aircraft Ground Handling and Servicing Disassembling the brakes – Steel main gear See above. Assembling brakes and wheels – Steel main gear Assembling is carried out in reverse order. After assembling check thoroughly, for sufficient space between brake hose and tire, check that the torque bolt has engaged to it´s retaining bolt at the axle bracket plate.
  • Page 78 Aircraft Ground Handling and Servicing Hydraulic brake system The REMOS GX may be equipped with the Matco brake system (basic) or alternatively with the high performance REMOS Brake System. Both are hydraulically operated systems operated by a single lever on the center console. This layout allows to control braking performance very precisely while access is granted from both seats.
  • Page 79 Aircraft Ground Handling and Servicing 8.15 Nose Gear Servicing The nose gear on the REMOS GX consists of a dip tube, guided by three maintenance-free slide bearings fixed to the fuselage. Rubber spring elements are deferred over the dip tube which carries a wheel fork made from steel at its lower end.
  • Page 80 To refill, you need about 0.8 gallons of new engine oil as recommended. Please refer also to the Rotax operators manual latest issue for detailed information. 8.17 Exhaust System Servicing The REMOS exhaust system used on the REMOS GX is manufactured from stainless steel. To provide suitable cabin temperature, especially in cold climates, a cabin heating system is included.
  • Page 81 8.19 Airbox System and Air Cleaner Element The REMOS air intake system consists of a carburetor heating system in conclusion with a special airbox. This system needs no servicing during regular service intervals.
  • Page 82 Aircraft Ground Handling and Servicing 8.20 Cockpit Panel System The modular cockpit panel system installed into the REMOS GX enables easy access to the installed devices for servicing or alterations. Regardless we strongly recommend to contact an avioncs shop for all electrical belongings.
  • Page 83 Rev. 01 – 07-01-2008 Aircraft Ground Handling and Servicing Now remove both upper cradle retaining screws. The whole radio rack assembly can be swung out of the cockpit frame Pull out the rack and disconnect all harnesses from the installed devices. Assembly Assembling is carried out in reverse order.
  • Page 84 Aircraft Ground Handling and Servicing 8.21 Aircraft Structure and Paintwork The whole airframe of the REMOS GX is produced to the latest procedures of carbon fiber composite technique. We only use certified epoxy resins for construction, which guarantees the most possible durability of the aircraft structure.
  • Page 85 Rev. 01 – 07-01-2008 Required Placards and Markings Table of Contents Paragr. Description Page Placard Positioning Airspeed Indicator Range and Markings Operating Limitations (applied to center console) Passenger Warning No Intentional Spins Miscellaneous Placards and Markings Required Placards and Markings 9 - 1...
  • Page 86 Rev. 01 – 07-01-2008 Required Placards and Markings Placard Positioning Pos. See page : Required Placards and Markings 9 - 2...
  • Page 87 Rev. 01 – 07-01-2008 Required Placards and Markings All airspeed markings posted in this paragraph does meet the requirement of the ASTM standards. Airspeed Indicator Range and Markings Marking CAS Airspeed/Range Description Minimum airspeed with flaps Red Line, low 44 mph extended Airspeed range for flaps White Arc...
  • Page 88 Rev. 01 – 07-01-2008 Required Placards and Markings Operating Limitations (applied to center console) The following limitation placards are applied to the center console inside the cabin. Applied to position Applied to position Passenger Warning Applied to position Required Placards and Markings 9 - 4...
  • Page 89 Rev. 01 – 07-01-2008 Required Placards and Markings No Intentional Spins Applied to position Miscellaneous Placards and Markings The following safety placard is located in front of the rescue system area, indicating that no luggage or clothes should be placed there. This is a safety advisory to guarantee the proper operation of the rescue system (if installed).
  • Page 90 Rev. 01 – 07-01-2008 Required Placards and Markings Beside the sight fuel gauge behind the seats you will find the following decal, which indicates the "fuel empty" position. When the indicated fuel quantity is level with that marked by the decal, 0.5 gallons of fuel remains in the fuel tank.
  • Page 91 Required Placards and Markings Outside the cabin this placard is located adjacent to the fuel filler. It indicates the recommended fuel qualities approved for the REMOS GX. Refer to the engine operators manual to check for additional fuel types. Required Placards and Markings 9 - 7...
  • Page 92 Rev. 01 – 07-01-2008 Required Placards and Markings Outside the aircraft, located beneath each wing main bolt, you will find this safety placard, concerning safety precautions regarding the folding or reassembling of the wings. On both sides of the fuselage, beneath each static port you will find this decal. Please keep in mind, that both static ports have to be kept clean.
  • Page 93 Rev. 01 – 07-01-2008 Supplementary Information Table of Contents Paragr. Description Page 10.1 Flight Training Supplement 10.1-1 to 10.1-9 10.2 Towing Glider Supplement 10.2-1 to 10.2-13 Supplementary Information 10 - 1...

  • Page 94: Table Of Contents

    Rev. 01 – 07-01-2008 10.1 Flight Training Supplement Table of Contents Paragr. Description Page Introduction 10.1-2 Take-Off 10.1-3 Climbing 10.1-4 Cruise 10.1-5 Stall 10.1-6 Slip 10.1-6 Gliding 10.1-7 Descent 10.1-7 Approach 10.1-7 Touch Down 10.1-9 Flight Training Supplement 10.1 - 1...

  • Page 95: Introduction

    Introduction This chapter should enable you to familiarize yourself with the flight performance and flight characteristics of the REMOS GX. To conduct these instructions you have to refer to the appropriate sections provided by the POH. The following pages describe flight characteristics experienced during various flights...

  • Page 96: Take-Off

    Rev. 01 – 07-01-2008 10.1 Flight Training Supplement Take-Off Take-off under normal conditions 1. After the preflight check has been carried out, extend flaps to 15° position. 2. Ensure that the elevator trim is in correct position. 3. Whenever possible, take-off directly into wind. The maximum crosswind limitation for take-off is 17 mph (15 kts) demonstrated.

  • Page 97: Climbing

    Rev. 01 – 07-01-2008 10.1 Flight Training Supplement Climbing Climbing after Take-off Once airborne, establish an indicated airspeed of 85 to 88 mph (73 to 76 kts). This airspeed will achieve the aircraft´s best rate of climb, resulting in a 1,000 to 1,050 ft/min climb rate. During the climb it is essential to watch oil- and water (CHT) temperatures.

  • Page 98: Cruise

    When flying in gusty weather conditions the maximum permissible airspeed of 123 mph (107 kts) should not be exceeded for safety reasons. The REMOS GX offers very stable flight characteristics even in heavy weather conditions, similar to that of a Cessna 172.

  • Page 99: Stall

    10.1 Flight Training Supplement Stall The REMOS GX is fully controllable when flying at a wide range of airspeeds. At airspeeds below the lower speed limit, the aircraft will display very stable stall characteristics. If the airspeed is reduced by the pilot gradually pulling back on the control stick, aerodynamic buffet will occur, indicating that the aircraft is approaching the stall speed.

  • Page 100: Gliding

    Avoid airspeeds above 75 mph (65 kts) or below 55mph (48 kts) when on final. Due to the excellent gliding performance of the REMOS GX, higher airspeeds would not be helpful during the flare and would extend landing.
  • Page 101 Approach in crosswind conditions Crosswinds will not have a big effect to the flight characteristics of the REMOS GX as long as cross-wind component stays within the maximum demonstrated speed up to 17 mph (15 kts). Conducting a...

  • Page 102: Touch Down

    Touch down under normal conditions Landing the REMOS GX is much easier than landing many other aircraft. The aircraft has very good low speed characteristics and so is very controllable all the way through the landing phase. After a good approach has been conducted the REMOS GX does not require much action to result with a perfect touch down.
  • Page 103 Rev. 01 – 07-01-2008 10.2 Glider Towing Supplement Table of Contents Paragr. Description Page General Information 10.2-3 Introduction 10.2-3 Certification 10.2-3 Quick Reference 10.2-3 Airplane and Systems Descriptions 10.2-4 Cockpit 10.2-4 Operating Limitations 10.2-5 Maximum permissible Towing Speed (V 10.2-5 Maximum Weak Link Strength 10.2-5 Maximum permissible All Up Weight of the Glider to be Towed 10.2-5...
  • Page 104 Rev. 01 – 07-01-2008 10.2 Glider Towing Supplement Table of Contents Paragr. Description Page Emergency Procedures 10.2-10 Engine Failure 10.2-10 Additional Procedures 10.2-10 Failure of the Release Clutch 10.2-10 Normal Procedures 10.2-11 Preflight Check 10.2-11 Take-Off 10.2-11 Descent and Landing 10.2-11 Aircraft Ground Handling and Servicing 10.2-12...

  • Page 105: General Information

    Quick Reference For the use as a glider towing aircraft, the REMOS GX is equipped with the Tost E85 tow release clutch, connected to the fuselage tail by a specially developed mounting frame. To release the tow rope a release lever is located on the left hand side of the pilot seat (colored yellow).

  • Page 106: Airplane And Systems Descriptions

    Cockpit Inside the cabin of the REMOS GX a tow release handle is installed. You will find that handle located at the left hand side of the pilot seat, colored yellow. If the handle is pulled out, the tow rope will be disengaged.

  • Page 107: Operating Limitations

    1300 lb as maximum weight of the glider to be towed, when operated with the standard ground adjustable propeller. During glider towing operations the REMOS GX must be operated only by one pilot (no passenger allowed, except for training/instruction). The total take-off weight (towing aircraft + glider) must not exceed 2,400 lb.

  • Page 108: Weight And Balance Information

    The following additional equipment is required for the use as glider towing aircraft: 1 x Tost tow release clutch, type E 85 1 x REMOS mounting frame for tow release clutch 1 x Release handle (colored yellow) 1 x REMOS oil temperature regulation flap 1 x Back view mirror Glider Towing Supplement 10.2 - 6...
  • Page 109 Rev. 01 – 07-01-2008 Weight and Balance Information The following equipment is not part of the center of gravity calculation, but necessary for glider towing: Towing rope with ring connector* Weak link 300 daN (green) Back view mirror. The pilot has to ensure, that the required weak link is attached to the tow rope, Attention: otherwise the structure of the aircraft may get overloaded! * Tow ropes made of polyamide, polyester and polypropylene manufactured to aviation standards may be...

  • Page 110: Performance

    Rev. 01 – 07-01-2008 Performance Take-Off Distances Aircraft Type MTOM Minimum Speed for Take-Off Press. Alt./ Glider Speed Best Climb Distance Air Pressure mph (kts) mph (kts) ft / InHG ASK 13 1,120 57 (50) 67 (58) 1,560 0 / 29.98 Twin Astir 1,270 69 (60)

  • Page 111: Take-Off Distances Effected By External Circumstances

    Rev. 01 – 07-01-2008 Performance Take-Off Distances Effected by External Circumstances Various circumstances will have an effect on the take-off distance of the aircraft. The following listing gives you an estimation of the values: • Dry grass strip +15 to 20% •...

  • Page 112: Emergency Procedures

    If an engine failure occurs during glider towing, the glider pilot must be informed immediately by radio to disengage the tow rope. Alternatively, the rope can be released at the towing aircraft. For further information, please refer to Section 6 "Emergency Procedures" included in the REMOS GX Pilot Operating Handbook.

  • Page 113: Normal Procedures

    Rev. 01 – 07-01-2008 Normal Procedures Preflight Check Check tow release clutch to assure proper function and clean condition. Take-Off During take-off, special care has to be taken that the climb rate and airspeed are adopted are to the required values of the towed glider. Watch your rate of climb immediately after take-off (do not exceed the gliders climb capability)! To maintain permissible water- and oil temperatures during climb and descent, the aircraft must be equipped with an oil temperature regulation flap.

  • Page 114: Aircraft Ground Handling And Servicing

    Rev. 01 – 07-01-2008 Aircraft Ground Handling and Servicing Servicing Tow Release Clutch During regular servicing intervals, the tow release clutch has to be cleaned, lubricated and checked to assure proper operation. A general overhaul of the release clutch has to be conducted after 4 years / 4000 towing operations. For further information refer to the separate operators manual of the manufacturer.

  • Page 115: Required Placards And Markings

    Rev. 01 – 07-01-2008 Required Placards and Markings Cockpit Inside the cabin of the REMOS GX the following placards are applied, when equipped for towing gliders. Adjacent to the airspeed indicator: Adjacent to the tow release handle: Release Clutch Outside the aircraft the following placards are applied, when equipped for towing gliders.
  • Page 116 Rev. 01 – 07-01-2008 Pilot Operating Handbook REMOS GX ASTM Edition Editor, Layout und Graphics: Hans Fuchs Flight testing and advisory: Josef Sporer, Nikolas Sporer Copyright REMOS Aircraft GmbH Flugzeugbau © REMOS 2007-2008, all rights reserved...

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