Page 3 JS-MD 3 Issue: 01 Aircraft Flight Manual JS-MD 3 AIRCRAFT FLIGHT MANUAL Type: JS-MD Single Model: JS-MD 3 Marketing name: JS-3 Rapture Serial number: Registration number: Document number: MD10-AFM-00-001 Title: JS-MD 3 Aircraft Flight Manual Issue Date of issue 14-Feb-20 Responsible for content Sören Pedersen / HOA...
Page 4 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Intentionally left blank Rev. 00 Rev. Date: 14-Feb-20 Page ii...
Page 5 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 0 Document Management Record of revision Issue Date Reason for Change Initial Issue 24.04.2019 Section 2.11: Aircraft compass removed from minimum equipment list Section 2.12: Value of aerotow weak link amended to 600daN Fig 2.14-1 Limitation Placard replaced Fig 2.14-1 Cockpit Masses Placard replaced...
Page 6 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 6.4-5 Lever arm of the non-expendable tail tank corrected to 4510 mm Figures 6.4-1, 6.4-2 & 6.4-3 removed Section 7.8.2.1 – minor text modifications Section 7.8.2.1, 7.8.2.2 , 7.8.3.1, 7.8.3.2 Heading added. Caution note added in section.
Page 7: List Of Effective Sections
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual List of effective sections Number Section Revision Date Reference of Pages 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 14.02.2020 Rev. 00 Rev. Date: 14-Feb-20 Page 0–3...
Page 8: Record Of Amendments
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Record of amendments Date of Issue/ Date of Signature Revision Insertion Rev. 00 Rev. Date: 14-Feb-20 Page 0–4...
Page 9: Table Of Contents
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table of contents JS-MD 3 AIRCRAFT FLIGHT MANUAL ..........i Document Management ............0–1 Record of revision ............. 0–1 List of effective sections ............ 0–3 Record of amendments ............. 0–4 Table of contents ............... 0–5 General ..................
Page 10 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Other limitations .............. 2–16 Limitations placards ............2–19 Emergency procedures ............3–1 Introduction ................ 3–1 Canopy jettison ..............3–1 Bailing out ................3–2 Stall recovery ..............3–3 Spin recovery ..............3–4 Spiral dive recovery ............3–5 Excessive sideslip recovery ..........
Page 11 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Permitted payload-range and CG envelope ....... 6-3 Optimisation of centre of gravity ........6-11 System description ..............7-1 Introduction ................. 7-1 Cockpit controls ..............7-1 Landing gear system ............7-15 Seats and safety harness ..........7-16 Pneumatic system ............
Page 12 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Manufacturer / Maintenance..........12-1 Rev. 00 Rev. Date: 14-Feb-20 Page 0–8...
Page 13: General
If a Jet Sustainer System is fitted, use this manual in combination with the latest approved JS-MD 3 Jet Sustainer Flight Manual Supplement. The marketing name for model JS-MD 3 is the JS-3 Rapture, and referred to in this manual as the JS-3.
Page 14: Warnings, Cautions And Notes
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Warnings, cautions and notes The following definitions apply to warnings, cautions and notes used in this Flight Manual. WARNING: Means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety.
Page 15: Descriptive Data
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Descriptive data The JS-MD 3 is a high-performance single-seat aircraft of conventional layout with a T-tail. Two wingspan configurations (15 m and 18 m) can be selected, both of which feature full-span flaperons. The cockpit is designed to protect the pilot in the event of a crash.
Page 16: Technical Data
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Technical data Geometry JS-3 15 m JS-3 18 m Wing span 15 m / 49.21 ft 18 m / 59.06 ft 9.95 m² / Wing area 8.75 m² / 94.18 ft 107.10 ft Aspect ratio 25.4 32.8...
Page 17: Three-View Drawing
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Three-view drawing JS-3 15 m Figure 1.6-1 JS-3 15 m Rev. 00 Rev. Date: 14-Feb-20 Page 1–5...
Page 18 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual JS-3 18 m Figure 1.6-2 JS-3 18 m Rev. 00 Rev. Date: 14-Feb-20 Page 1–6...
Page 19: Limitations
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 2 Limitations Introduction Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of the aircraft, its engine (if fitted), standard systems and standard equipment. The limitations included in this section have been approved by the EASA. Rev.
Page 20: Airspeed Limits
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Airspeed limits Speed limitations and their operational significance are shown in Table 2.2-1 below: Speed Remarks Do not exceed this speed in any 280 km/h Never exceed speed operation and do not use more than 151 kts 1/3 maximum control deflection.
Page 21 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 2.2-2 below lists the maximum allowable airspeeds for each flap setting: Flap setting Deflection (°) 15 m 18 m -3° 280 km/h / 151 kts +0° +5° 230 km/h / 124 kts +13.5°...
Page 22 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Airspeed indicator markings The airspeed indicator markings and their colour code significance are given in Table 2.2-3: Marking Significance 15 m 18 m Positive Flap Operating Range. (Lower limit is 1.1 V White 97 to 160 km/h in landing configuration at...
Page 23: Power Plant Fuel And Oil
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual NOTE: is defined as the stall speed at maximum weight, in a specific selected configuration, with the CG in the most unfavourable position. See CS 22.49. Power plant fuel and oil Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement Section 2.4. Power plant instrument markings Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement Section 2.5.
Page 24: Mass
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Mass The mass limitations for the JS-3 are given in Table 2.5-1: Mass limits Mass definition 15 m 18 m 525 kg 600 kg Maximum Take-Off Mass 1157 lbs 1323 lbs Maximum Take-Off Mass without water 415 kg 430 kg ballast...
Page 25 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 2.5-2 displays the reduction in allowable non-lifting parts mass for take-off masses below the maximum allowed masses. Non-lifting parts mass structural limit Aircraft mass 15 m 18 m 350 kg 266 kg 211 kg 772 lbs 586 lbs...
Page 26: Centre Of Gravity
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Centre of gravity Table 2.6-1 displays the allowable Centre of Gravity (CG) range for the JS-3 in the 15 m and 18 m configurations: Distance from datum Centre of Gravity range (in flight) 15 m 18 m 270 mm...
Page 27 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 2.6-2 gives the forward and rear CG limits (no payload) for different empty masses that will allow a cockpit range of 70 kg to 115 kg. Empty Centre of Gravity range Forward limit Rear limit Empty mass...
Page 28: Approved Manoeuvres
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Approved manoeuvres This aircraft is certified in the Utility category (U). The following aerobatic manoeuvres are permitted in the 15 m and 18 m configuration: • Lazy eight • Chandelle • Steep turns •...
Page 29: Flight Load Factor Limits
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Flight load factor limits The minimum and maximum approved manoeuvring load factors are given in Table 2.8-1 below: Load Condition factor 15 m 18 m 207 km/h Maximum positive manoeuvre + 5.3 112 kts 207 km/h Maximum negative manoeuvre...
Page 30: Flight Crew
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Flight crew The minimum and maximum pilot mass is indicated on the cockpit placard or Placard Booklet. • Minimum cockpit mass: 70 kg (154.3 lbs) • Maximum cockpit mass: 115 kg (253.5 lbs) CAUTION: If the measured empty CG is not within the normal empty mass CG range, the minimum and maximum cockpit...
Page 31: Types Of Operation
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Types of operation The JS-3 is approved for: • VFR day operation • Cloud flying in 15 m and 18 m configuration without water ballast where national regulations permit. NOTE: For cloud flying the take-off mass must not exceed 418 kg (922 lbs), as listed in Section 2.5, and the engine must be retracted (if fitted).
Page 32: Minimum Equipment List
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Minimum equipment list Instruments and other equipment on the minimum equipment list must be approved. Refer to the accessory approval section in the JS-MD 3 Aircraft Maintenance Manual for details. The minimum equipment: •...
Page 33: Aerotow And Winch Launching
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Aerotow and winch launching Maximum approved towing speeds and maximum weak link ratings for the JS-3 are listed in Table 2.12-1. Maximum Maximum Launch method speed weak link rating 750 daN 150 km/h / (E.g.
Page 34: Other Limitations
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Other limitations Limitations when flying with water ballast Intentional manoeuvres not permitted when flying with water ballast: • Loops • Chandelles • Lazy eights • All aerobatic manoeuvres listed in the aerobatic category •...
Page 35 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Temperature restrictions when carrying water Flights with water ballast are prohibited in conditions where there is a risk of icing. When the outside air temperature is below 0 °C (32 °F), the water ballast must be dumped or a descent to lower altitudes (higher temperatures) must be conducted.
Page 36 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Limitations of high-speed flight If there are any indications that an airspeed limit may be exceeded (e.g. when flying in wave rotors, near thunderstorms or other turbulent conditions), extend the airbrakes carefully before exceeding 200 km/h / 108 kts).
Page 37: Limitations Placards
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Limitations placards Limitation placards can be either fixed against the side walls or instrument panel, or furnished as a single Placard Booklet located against the left-hand cockpit sidewall. The placard given in Figure 2.14-1 is fixed to the left side wall of the cockpit and contains the most important mass and speed limitations.
Page 38 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 2.14-2) and must correlate with the values in the mass and balance report. Figure 2.14-2 Cockpit masses placard Figure 2.14-3 gives the placard to be displayed in the baggage compartment. Figure 2.14-3 Baggage compartment placard NOTE: Refer to the JS-MD 3 Aircraft Maintenance Manual for all the required fixed placards or the equivalent Placard...
Page 39: Emergency Procedures
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 3 Emergency procedures Introduction Section 3 provides checklists and amplified procedures for handling emergencies that may occur. Canopy jettison To jettison the canopy, pull both left and right canopy jettison latches as far as possible and push the canopy upward with the latches.
Page 40: Bailing Out
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Bailing out The bailing out procedure is as follows: 1. Jettison the canopy as described in Section 3.2. 2. Release the safety harness. 3. To exit, lift out of the cockpit seat pan using the cockpit rim and push away from the aircraft to avoid striking the tail surfaces (and if possible, try to dive underneath the wing).
Page 41: Stall Recovery
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Stall recovery The JS-3 has very mild stall properties recognisable by the following: • The nose is in a higher than normal attitude relative to the horizon. • Slight buffeting approximately 2 km/h before the stall. •...
Page 42: Spin Recovery
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Spin recovery Spin recovery is performed using the standard spin recovery procedure: 1. Apply rudder in the opposite direction to the spin rotation. 2. Simultaneously release the elevator back pressure by moving the stick forward to the neutral position.
Page 43: Spiral Dive Recovery
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Spiral dive recovery A spiral dive may occur when: • The aircraft terminates spinning automatically but the pilot continues applying into-spin control inputs, or • During excessive slip angles with full rudder deflection. Indications of a spiral dive are a high bank angle, increasing airspeed and a high G-load.
Page 44: Excessive Sideslip Recovery
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Excessive sideslip recovery An excessive sideslip may occur when the pilot applies full cross control input. At a slip angle exceeding 20° (approximately 40° on the yaw string) rudder control forces reverse as the rudder is sucked into the wake of the stalled fin.
Page 45: Engine Failure - Jet Turbine
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Engine failure – Jet turbine Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement Section 3.2. Engine Fire Engine fire on the ground Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement Section 3.3. Engine fire in flight Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement Section 3.3.
Page 46: Electrical Fire
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Electrical fire An electrical fire is very unlikely due to the protection with circuit breakers for all systems. Each battery has a fuse at the terminals and each battery supply has a circuit breaker switch on the instrument panel. In the event of smoke or fumes coming from the instrument panel, perform the following actions: 1.
Page 47: Other Emergencies
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Other emergencies Cable failure during winch launch In case of a cable failure during a winch launch, perform the following actions: 1. Immediately push the stick sufficiently forward to establish a nose-down attitude in order to regain flying speed. 2.
Page 48 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Flight with asymmetric water ballast load Asymmetric water ballast load may develop during flight if: 1. A main tank dump valve leaks. 2. One main tank dumps water faster than that the other, due to a partial opening valve, or dumping during prolonged unbalanced flight.
Page 49 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual • If only one valve is dumping water, close the dumping valves immediately to prevent full water ballast asymmetry developing. If the asymmetrical load cannot be rectified, the pilot is strongly recommended to: 1.
Page 50 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Spin recovery procedure with asymmetric water ballast load It may be possible to recover the JS-3 from a spin with a significant asymmetric water ballast load, provided correct recovery procedures are followed. The high rotation rate of approximately 120° per second may cause extended airbrakes to blank off the elevator.
Page 51 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Emergency landing with landing gear retracted Emergency landings with the landing gear retracted are not recommended, because the energy absorption ability of the spring mounted landing gear is much higher than the fuselage shell. However, if an emergency landing with the landing gear retracted is inevitable, land with the flaps in the landing position L.
Page 52 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Emergency landing on water During water landing tests with the landing gear retracted, it has been observed that the fuselage can submerge completely. The following procedure is recommended for an emergency landing on water: 1.
Page 53: Normal Operating Procedures
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 4 Normal operating procedures Introduction Section 4 provides checklists and amplified procedures for the conduct of normal operations. Normal operations associated with optional systems can be found in Section 9. Rigging and de-rigging Rigging The JS-3 can be rigged by three people without rigging aids or by two people if a fuselage cradle and wing stands are available.
Page 54 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Wing rigging 1. Ensure that the red rubber water drain plugs are inserted in the wing roots in front of the forward lift pin. 2. Clean and grease all pins and matching bushes, including the main pins.
Page 55 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual and ensure that it locks positively by pushing the lever over- centre. CAUTION: The flaperon sandwich can be damaged if excessive force is used and should be handled with care. WARNING: Never grease the water drain valve, the rubber-based seal may be damaged and become detached from the valve body.
Page 56 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Mount tailplane 1. Clean the tailplane pins and bushes. 2. Clean and lubricate the pitot-static auto-connectors. Ensure that the O-rings are serviceable. 3. Slide the tailplane onto the fin. Take care when the elevators slide into the elevator auto-coupler.
Page 57 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual De-rigging 1. Ensure that the non-expendable tail tank is drained of water. 2. Remove auxiliary items. 3. Remove the main batteries and lock the battery retainers back in position. 4. Remove the total energy tube and pitot-static tubes, as well as any temporary equipment (Logger etc.).
Page 58 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Removing the tailplane (horizontal stabilizer) 1. Unscrew the front attachment bolt using the hex socket key tip of the JS rigging tool. 2. Slide the tailplane forward. Take care to move the tailplane forward evenly so as not to damage the elevators or the elevator auto-coupler.
Page 59 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 10. Push the fuselage into the trailer. NOTE: To avoid unnecessary loads on the airbrake caps, do not leave the airbrakes locked for long periods (either rigged or de-rigged). The airbrake locking tool can be used for temporarily locking the airbrakes for maintenance or transportation, and the airbrakes should be unlocked when maintenance or transportation is complete.
Page 60: Daily Inspection
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Daily inspection After the aircraft has been rigged and always before the first flight of the day, the aircraft must be inspected carefully to ensure its airworthiness. The following inspection is essential for flight safety: Figure 4.3-1 Forward fuselage ①...
Page 61 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 4. Ensure proper connection of the flaperon and airbrake system: • With the control stick in the neutral position and the flap lever in position 3, the flaperon must be flush with the trailing edge at the root rib.
Page 62 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Landing gear ③ 1. Visually inspect the mechanism and locks. 2. Check the condition of the shock absorbing rubbers. 3. Check the tyre pressures: • Main wheel - 15 m: 2.5 bar (36.26 psi) •...
Page 63 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual positive flap with maximum aileron deflection must be at least 10 mm. Check that the wheels are attached positively to the wing. 7. Check that the control surface gap seals are installed and properly adhered to the wing recesses.
Page 64 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual was left in position during rain) by removing the tailplane and rotating it. 3. Ensure that the total energy and pitot-static probes are installed correctly and pushed all the way in. The pitot-static probe is positioned on the right-hand tailplane tip.
Page 65: Pre-Flight Check
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Pre-flight check Daily inspection Performed Control systems Functional check, positively connected, free movement and no play Expendable tail tank Valve opening positively checked Non-expendable tail Ensure empty or correctly loaded for CG tank range Water ballast system...
Page 66 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Figure 4.4-1 Pre-flight and pre take-off check placard Rev. 00 Rev. Date: 14-Feb-20 Page 4-14...
Page 67: Normal Procedures And Recommended Speeds
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Normal procedures and recommended speeds Winch Launch procedures Winch launching is performed using the CG hook in front of the main wheel. With a slow-accelerating winch, good aileron control is achieved using flap 3.
Page 68 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Winch launches executed at wing loads exceeding 55kg/m are not recommended, as many winches are not capable of achieving the high speed required for a safe winch launch. Recommended loads for winch launches 15 m 18 m Recommended maximum take-off weight for...
Page 69 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Aerotow launch procedure Aerotows are performed using the nose release hook. Refer to Section 2.12 for rope lengths. Initiate the ground run in negative flap (Flap setting 1). This will increase aileron efficiency at low speeds. In a crosswind take-off, keep the stick aft during the initial acceleration.
Page 70 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual slipstream of the tow plane. The swirling rope end may cause damage to the aircraft when releasing in the low tow position. NOTE: With the CG in the aft position the launch should be commenced with the trim in the full forward setting.
Page 71 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 4.5.4.2 Inter thermal cruise To optimise the glide performance, it is important to select the proper flap according to the weight and cruise speed. The flaps modify the camber of the airfoil, maintaining laminar flow over a wide range of lift coefficients.
Page 72 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 4.5.4.6 Lightning The JS-3 is not approved for flight where lightning strikes may occur. WARNING: Flights in conditions conducive to lightning strikes must be avoided. Approach The circuit can be flown with the flaps set to setting 3 to 5 (+5° to +16.7°). On final approach for landing the flaps can be changed to position L (+20°) for a shorter landing at a lower touchdown speed.
Page 73 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 4.5-5 gives the recommended airspeeds for the approach: Load configuration Minimum Recommended Approach Speeds: Minimum Max. Take-off (Various Approach Types) Mass Mass 105 km/h 120 km/h Calm conditions, no airbrakes 57 kts 65 kts 110 km/h 125 km/h...
Page 74 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual NOTE: Side-slipping the JS-3 on final approach is not recommended as it is an inefficient method to increase the sink rate. However, the aircraft can be side-slipped up to a speed of 203 km/h (110 kts). Partial water ballast has no noticeable effect on the flying characteristics during a sideslip.
Page 75 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual After touchdown the wheel brake can be activated. It is recommended to select negative flaps (Setting 1) after touchdown. This reduces the risk of nose-over when braking hard, reduces the chances of damaging the flaperon trailing edges on uneven surfaces and improves aileron control at low speeds.
Page 76 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Flying with water ballast The water ballast system allows the mass of the aircraft to be increased to achieve higher wing loads. Table 4.5-6 gives the tank capacity for the JS-3. Water Ballast Capacity (Litres) 15 m 18 m Main inboard wings...
Page 77 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Expendable tank loading chart Water Loading- Main Tanks (litres) Figure 4.5-2 NOTE: As a conservative approximation, add 1 litre of water in the expendable tail tank for every 30 litres of water in the main inboard wing tanks.
Page 78 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 4.5.7.1 Filling procedure 1. Determine the quantity of water ballast to be carried. The quantity of water ballast in the tail is calculated using the graph in Figure 4.5-2. 2. Determine the quantity of water to be loaded in each tank. In the 18 m configuration the tips must be filled if water is carried in the main tanks.
Page 79 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 4.5.7.2 Dumping procedure 1. Open the valves by shifting the dump valve lever forward and down. The combined dump rate of the main tanks is approximately 50 litres per minute. The dump rate will slow down when approximately 20 % of water is left.
Page 80 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual WARNING: Residual air may create undue pressure during flights with partially loaded or empty tanks. Always check to ensure that the vent holes of the fin tanks are always open and that the pressure relieve valve in the main tank is functional.
Page 81 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual High altitude flight At higher altitudes the air speed indicator will indicate values lower than the true airspeed due to the lower air density. This does not influence loads on the structure, but it does mean that the colour markings on the air speed indicator are not correct at high density altitude.
Page 82 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual The fixed placard is illustrated in Figure 4.5-4. The equivalent limitations are provided in the Placard Booklet. Figure 4.5-4 WARNING: The aircraft is not approved for flights above 9000 m (30000 ft) AMSL. CAUTION: At higher altitudes the true airspeed (TAS) is higher than the indicated airspeed (IAS).
Page 83 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Using bug wipers in flight The operation of the bug wipers in flight depends on the winder system installed. Refer to the instructions of the winder manufacturer for details on the operation. The following basic rules apply: 1.
Page 84 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Aerobatics The entry speeds and recommended maximum G-loads for approved aerobatic manoeuvres are given in Table 4.5-7 below. Aerobatic entry speed Flap setting Entry speed G-load Lazy Eight 180 km/h (97 kts) Chandelle 150 km/h (81 kts) Steep turn...
Page 85: Performance
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 5 Performance Introduction Section 5 provides approved data for airspeed calibration, stall speeds, take-off performance and other non-approved information. The data in the charts has been computed from actual flight tests with the aircraft in good conditions and using average piloting techniques.
Page 86 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Stall speeds The stall speeds (IAS) for the 15 m and 18 m configurations of the JS-3 are given in Table 5.2-1 and Table 5.2-2. Table 5.2-1 gives the stall speeds for the JS-3 (15 m configuration) with the airbrakes retracted and CG in the foremost position: 15 m Configuration (forward CG) Gross weight...
Page 87 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual With the CG in the forward position the elevator may not be able to produce a sufficiently high angle of attack to completely stall the wings with positive flap settings. In this case, the stall speeds are defined by the minimum achievable speed for the specific flap setting.
Page 88: Non-Approved Information
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Non-approved information Demonstrated crosswind performance The JS-3 has very good crosswind handling characteristics due to its polyhedral wing shape allowing high bank angles during touchdown. The maximum demonstrated crosswind components are: • During aerotow: 25 km/h (14 kts) •...
Page 89 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Flight polar Figure 5.3-1 illustrates the calculated polar for the JS-3 in the 15 m and 18 m configurations for two wing load cases: Figure 5.3-1 Rev. 00 Rev. Date: 14-Feb-20 Page 5-5...
Page 90 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 5.3-1 gives the coefficients of the second-degree polynomial approximation of the JS-3’ polar curve in the 15 m and 18 m configurations for a specific reference mass. Configuration Reference mass 450 kg 992 lbs 500 kg 1102 lbs...
Page 91: Weight And Balance
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 6 Weight and balance Introduction Section 6 contains the payload range for the JS-3 aircraft within which it can be operated safely. The procedures for weighing and establishing the permitted payload range is given in JS-MD 3 Aircraft Maintenance Manual, including: •...
Page 92 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Weight and Balance Record Sheet: 15 & 18 m configuration Permitted pilot weights S/N: Empty Empty Non- Non- Approval weight Date Expendable fin Expendable Name / position tank(s) empty fin tank(s) full EMPTY) Signature Table 6.2-1...
Page 93: Permitted Payload-Range And Cg Envelope
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Permitted payload-range and CG envelope The JS-3 CG envelope is based on the allowable flying mass and CG ranges given in Section 2.5 and Section 2.6. Care must be taken that the CG stays within the allowable limits. The following loads have an effect on the CG position: •...
Page 94 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual expendable fin tank. The moment arms are measured from the datum with the following sign convention: Figure 6.3-1 Rev. 00 Rev. Date: 14-Feb-20 Page 6-4...
Page 95 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Max Mass Moment arm Momen Load point inch Pilot (with parachute) 253.5 -645 -25.4 Pilot Cockpit ballast 44.1 -450 -17.7 Cockpit (removable) O2 bottle AL248 Baggage compartment Water ballast - main ~156 ~344 WingM Water ballast –...
Page 96 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Figure 6.3-2 and Table 6.3-2 give the maximum mass and the moment arms of the various variable loads for JS-3 with two separate non- expendable fin tanks fitted from SN 080 and onwards: Figure 6.3-2 Max Mass Moment arm...
Page 97 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual To determine if a selected load falls within the CG envelope, as illustrated in Figure 6.3-3, the following procedure can be used: 1. List all the loads in table format as illustrated in Table 6.3-1 2.
Page 98 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Mass Moment (kg.m) Load point Mass x Arm/1000 Empty aircraft 131.6 Pilot and parachute -645 -58.1 Water ballast – main 34.1 Expendable tail tank 4285 24.9 Non-expendable tail tank 4510 40.1 O2 bottle AL248 Totals: 524.7 172.6...
Page 99 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Figure 6.3-3 illustrates the envelope for the 15 m configuration. Figure 6.3-3 Rev. 00 Rev. Date: 14-Feb-20 Page 6-9...
Page 100 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Figure 6.3-4 illustrates the envelope for the 18 m configuration. Figure 6.3-4 Rev. 00 Rev. Date: 14-Feb-20 Page 6-10...
Page 101: Optimisation Of Centre Of Gravity
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Optimisation of centre of gravity The CG of the aircraft is shifted towards the aft 25 % of the CG to obtain optimum overall performance. The procedure to set up the CG optimally is as follows: 1.
Page 102 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Expendable tail tank The expendable tail tank is only used to offset the CG change due to the water ballast in the main wing tanks. Mass Moment arm Load point inch Expendable tail tank 4240 TAIL1 Table 6.4-1...
Page 103 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Fuselage tank (optional) A fuselage tank may be installed instead of the fuel tanks of the Sustainer system. Filling the fuselage tanks moves the CG aft. The required minimum cockpit weight is therefore higher when water is added to the fuselage tanks.
Page 104 MD10-AFM-00-001 JS-MD 3 Aircraft Flight Manual Issue: 01 Fuel tanks Fuselage tanks are installed as part of the Jet Sustainer system. Filling the fuselage tanks moves the CG aft. The required minimum cockpit weight is higher when fuel is added to the fuselage tanks. The table below indicates the maximum weight and moment arm of the fuselage tanks.
Page 105 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Non-expendable tail tank Adding water to the non-expendable ballast tail tank moves the CG rearwards. The required minimum cockpit weight increases when water is added to the tail tank. Table 6.4-5 indicates the maximum weight and moment arm of the non- expendable ballast tank.
Page 106 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Table 6.4-7 gives the load (litres of water) of the non-expendable ballast tail tank to achieve a CG on the 75% mark. Non-expendable tail tank load requirements to obtain optimum cg (kg) (Fuel tanks full) Pilot + Parachute -6.7...
Page 107 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Additional pilot weight is required to move the CG forward towards the optimum position (75% from the front position). Permanent ballast can be removed from the cavity in the tail, in accordance with aircraft Maintenance Manual, to reduce the minimum cockpit weight.
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Page 109: System Description
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 7 System description Introduction Section 7 gives a description of the aircraft systems as well as instructions on the use thereof. A detailed technical description of the systems with drawings can be found in the JS-MD 3 Aircraft Maintenance Manual.
Page 110 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual The wheel brake is activated by squeezing a trigger on the control stick illustrated in Figure 7.2-1. Figure 7.2-1 Rudder The rudder is controlled by the rudder pedals in the front section of the fuselage.
Page 111 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Flap The flap control (Figure 7.2-2) is via a black handle located on the left- hand side of the cockpit. The flap handle can be freed from its detent by rotating it slightly clockwise as seen from the rear. Flap Lever Figure 7.2-2...
Page 112 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Release system The nose and CG hooks are operated simultaneously when the release handle is pulled towards the pilot. The release handle is a yellow handle positioned on the left-hand cockpit side in front of the flap handle (Figure 7.2-4). Release handle Figure 7.2-4...
Page 113 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Trim The trim of the aircraft is adjusted with a green knob located on the left side of the cockpit below the airbrake lever. The trim can be adjusted when the trim knob is pressed downwards. Moving the trim knob has the following effect on the elevator control: •...
Page 114 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Ergonomic control The ergonomic control panel provides the controls for the following subsystems: • Rudder pedals adjustment • Cockpit ventilation • Demisting ventilation • Seatback upper adjustment (not yet implemented) • Seatback lower adjustment (not yet implemented) The auxiliary electrical system controller panel is situated on the right side of the cockpit behind the eyeball air vent.
Page 115 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual The selector knob is a 6-way rotary switch at 30-degree intervals, used to select the appropriate system to be adjusted. Rudder Pedals Cockpit Ventilation Demisting Ventilation Seat Upper Adjustment Seat Lower Adjustment Figure 7.2-7: Selector knob layout The adjuster switch is a momentary ON-OFF-ON toggle switch, used to adjust the selected sub-system.
Page 116 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 7.2.6.1 Rudder pedal adjustment For aircrafts equipped with the ergonomic control system, rotate the selector switch to “Rudder pedal” position. See Figure 7.2-6 and Figure 7.2-7. Adjust the pedal position using the control switch as follows: •...
Page 117 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Adjust the pedal position using the control switch as follows: • Forward: Moves the rudder pedals away from the pilot • Backward: Moves the rudder pedals closer to the pilot 7.2.6.2 Seatback adjustment (Electrical option) The bottom of the seatback can be moved forwards and rearwards by removing two thumb screw knobs on the seatback pivot point and setting the seatback to the desired position.
Page 118 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual WARNING: Ensure that both thumbscrews and the adjuster locking pins are engaged before flying to prevent the pilot from shifting backwards. This could result in loss of aircraft control. 7.2.6.3 De-misting control (Manual option) For aircraft without the ergonomic control system, the cabin and demisting ventilation system is manually adjustable via an organ stop on the instrument panel.
Page 119 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Organ stop in Figure 7.2-12: De-misting valve closed The eyeball vent positioned on the right-hand cockpit sidewall is manually adjustable to direct the airflow as desired. Closing the eye ball with the ventilation open will still allow air to flow over the instrument binnacle.
Page 120 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 7.2.6.5 Cabin ventilation control (Manual option) For aircraft without the ergonomic control system, the eye ball vent positioned on the right-hand cockpit sidewall is used to direct the airflow as desired, and to regulate the airflow rate (Figure 7.2-13). Figure 7.2-13: Cockpit ventilation 7.2.6.6 Cabin ventilation control (Electrical option)
Page 121 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual NOTE Both the cabin and demisting ventilation system open and close reasonably fast. Only short clicks on the control switch are needed when either fully opened or fully closed is required. 7.2.6.7 Heated boots Heated boots can be plugged into an optional USB port located on the bottom of the instrument console.
Page 122 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Description Chart (Figure 4.5-4) (replaceable by Placard Booklet) Circuit breakers Battery selector switches (Figure 7.11-2) Master switch arrangement (Figure 7.11-1) Figure 7.2-14: Custom instrument panel layout Rev. 00 Rev. Date: 14-Feb-20 Page 7-14...
Page 123: Landing Gear System
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Landing gear system The landing gear handle is located on the right-hand side of the cockpit and labelled as illustrated in Figure 7.3-1. Pulling the handle backwards retracts the landing gear and pushing it forward extends the landing gear. The handle is rotated firmly clockwise to lock the landing gear in the extended and retracted position.
Page 124: Seats And Safety Harness
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Seats and safety harness The safety harness is a four-point system. The lower straps pass through the seat pan and are anchored to the fuselage skin. The shoulder straps pass through the seatback and are attached to the structure behind the pilot’s shoulders.
Page 125: Pneumatic System
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Pneumatic system The aircraft pneumatic system consists of: • Static (P ) piping for the ASI and altimeter STAT • Dynamic (P ) piping for the ASI • Static piping for the variometer from fin probe •...
Page 126 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Static ports on fuselage Figure 7.5-1 Figure 7.5-2 Rev. 00 Rev. Date: 14-Feb-20 Page 7-18...
Page 127: Airbrake System
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Airbrake system The airbrakes are actuated by the blue handle on the left-hand side of the cockpit (Figure 7.6-1). Airbrake Lever Figure 7.6-1 Airbrake Lever The airbrakes are operated as follows: • Pull the handle backwards to open the airbrakes.
Page 128: Baggage Compartment
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual The airbrakes are locked by moving the airbrake handle fully forward, over the over-centre lock. A force of approximately 15 to 20 kg is required to lock the airbrakes. A damper restricts the rate of opening to reduce high loads on the aircraft if the airbrakes are opened at high speed.
Page 129: Water Ballast System
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Water ballast system General The water ballast system allows the weight of the aircraft to be increased to a maximum of 525 kg (1157 lbs) in the 15 m configuration and to 600 kg (1323 lbs) in the 18 m configuration.
Page 130 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Forward Position Middle Position Rear Position Figure 7.8-1 CAUTION: When dumping water, first dump water in the main tanks before dumping the tip tanks. An optional fuselage ballast tank can be installed instead of an engine system.
Page 131 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Main tanks The main tanks are integrated in the D-box area of the main wings (inboard section), spanning the entire leading edge of the wing. A smaller tank, connected to the leading edge tank, is located inboard of the airbrake box behind the spar, as illustrated in Figure 7.8-2.
Page 132 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 7.8.2.1 Filling the main tanks The filling holes are positioned on the top of the inboard wing section near the tip junction. Filling is done through the top filling holes. The filling holes are closed by screwing the filler caps into position using the universal rigging tool.
Page 133 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 18 m Tip tanks In the 18 m configuration water is also carried in the outboard wings. Each outboard wing additionally carries approximately 17 litres of water. ① ② ④ ③ ① ④...
Page 134 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 7.8.3.1 Filling the tip tanks Filling is done through the dump valve of the 18 m tips using the water filling tool. Figure 7.8-5: 18 m Outboard filling tool CAUTION: The filling pipe diameter should preferably not exceed 12mm (0.5”) if the filling is done through the top filling holes.
Page 135 MD10-AFM-00-001 JS-MD 3 Aircraft Flight Manual Issue: 01 7.8.3.2 Draining the tip tanks Water can be dumped from the tip tanks by moving the dump valve control in the full forward position. Approximately 200 ml of water remains in the tank after dumping. This water must be drained after flight.
Page 136 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Water tanks in fin There are two water types of ballast trim tanks in the fin of the JS-3, an expendable tank ahead of the shear web and non-expendable tank(s) behind the shear web. Ventilation Filling Expendable...
Page 137 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Draining the tail tank is done by moving the single water dump lever to the centre or forward position. 7.8.4.2 Non-Expendable water ballast The non-expendable water ballast tanks are located behind the shear web in the fin are not expendable and is used to trim the CG position for pilot weight.
Page 138 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual filled to reach total capacity. Both tanks must be drained by removing sealing vinyl stickers from the bottom hole(s) Filling hole (Left) Vent hole (Right) Non-expendable water ballast (Upper) Filling hole (Left) Vent hole (Right) Non-expendable water ballast (Lower)
Page 139: Power Plant
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Power plant Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement. Fuel system Refer to JS-MD 3 Jet Sustainer Flight Manual Supplement Section 7.1.4. Rev. 00 Rev. Date: 14-Feb-20 Page 7-31...
Page 140: Electrical System
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Electrical system The electrical power of the aircraft is supplied by maintenance-free dry- gel type or LiFePO-4 12V batteries. Two main batteries are fitted in the luggage compartment and an optional backup battery can be installed behind the seatback.
Page 141 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual The entire system can be switched off using the master avionics switch. However, the ERGO and bug wiper systems can be switched off independently using the master electric switch. 7.11.1.2 Power source selection Battery selection is performed by selecting Battery 1, Battery 2 or Auxiliary Battery for bus 1, bus 2 and the electric bus.
Page 142 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 3. Electrical systems • Rudder pedal controller or SCC (optionally installed) • Bug wiper system • Heated boots • 5V power supply • Warning systems (if fitted) Dividing the avionics and electrical system in separate systems allows the pilot to supply power from separate batteries or from the same source.
Page 143 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Recommended battery types The batteries used in the aircraft must be of the dry sealed type, as no battery that vents any gas is allowed in the aircraft according the airworthiness requirements of CS-22. Left &...
Page 144 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Figure 7.11-3 Master switch arrangement Rev. 00 Rev. Date: 14-Feb-20 Page 7-36...
Page 145: Miscellaneous Equipment
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Miscellaneous equipment Microphone and antenna The plugs for microphone and antenna from the canopy frame are behind the instrument panel. CAUTION: The radio microphone is located on the canopy frame. Take care when removing the canopy from the instrument panel.
Page 146 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Bug wiper system The bug wiper controls can be found on the left side of the cockpit in front of the trim lever. If the bug wiper system is installed, perform the following checks before each flight: •...
Page 147: Handling And Maintenance
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 8 Handling and maintenance Certain inspections and maintenance procedures to maintain aircraft performance and reliability are included in this section. It is advisable to follow a regular schedule of lubrication and preventive maintenance, consistent with the usage, climatic and flying conditions encountered.
Page 148: Aircraft Inspection Periods
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Aircraft inspection periods The aircraft shall be subjected to an annual airworthiness inspection. A more detailed inspection schedule can be found in the JS-MD 3 Aircraft Maintenance Manual. • Airworthiness inspections must be performed in accordance with the relevant laws of the country in which the aircraft is registered.
Page 149: Ground Handling
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Ground handling Ground towing Either use a rope or other non-metallic cable from the nose hook with someone walking with the wing tip, or Use a tow bar connected to the tail dolly and a ‘wing walker’ with a sprung wheel (or someone walking with the wingtip).
Page 150 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Tie down The aircraft can be tied down using the holes in the wingtip skids. It is preferable to position wing stands under the wings inboard of the tip junction adjacent to the tie down ropes. A tie down rope across the rear fuselage boom in front of the fin should also be used to prevent the tail from lifting.
Page 151: Cleaning And Care
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Cleaning and care General The JS-3 is manufactured from a composite of glass, carbon and aramid fibres in an epoxy matrix. The gel coat surface layer is finished with a polyurethane acrylic 2K paint topcoat. There is no composite material available that is impervious to moisture absorption or to UV (ultra-violet) rays.
Page 152 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual CAUTION: Never use any of the following products on the aircraft: • Trichloroethylene • Carbon tetrachloride or similar hydrocarbon chlorides • Any product containing silicon Canopy The canopy must be protected from scratches. Always wash off dust by using liberal amounts of water with a soft chamois, taking care not to allow dust to get between the chamois and the canopy surface.
Page 153 MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Pins, bushes and control systems All bare metal surfaces that are not protected with paint must be protected with a thin film of grease. Seat belt harness The seat belt harness must be checked regularly for frayed of edges, mildew and wear.
Page 154: Long-Term Storage
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual Long-term storage To store the aircraft for periods exceeding 12 months, the following is recommended: 1. Remove the instruments and store separately. 2. Close the external pressure ports and inner tube end. 3.
Page 155: Supplements
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 9 Supplements Introduction This section includes additional information on the safe operation of the aircraft if fitted with ancillary equipment not included as standard in the aircraft. List of ancillary equipment Oxygen system Provision is made for an oxygen bottle with a maximum diameter of 86 mm (3.4”).
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Page 157: Service Bulletins
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 10 Service bulletins This section starts with an overview table of all optional SB’s, in which the owner or operator should mark which SB’s he voluntary implemented and which not. All implemented optional SB’s have to be printed and added to this section by the owner or operator.
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Page 159: Stcs And Minor Change Approvals
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 11 STCs and minor change approvals Reference No. Rev. Date Description Rev. 00 Rev. Date: 06.02.2019 Page 11-1...
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Page 161: Contact
MD10-AFM-00-001 JS-MD 3 Issue: 01 Aircraft Flight Manual 12 Contact Type Certificate Holder M&D Flugzeugbau GmbH & Co. KG Streeker Straße 5b 26446 Friedeburg Germany  +49 (0) 4465 / 97878 – 11 Mail: info@md-flugzeugbau.de Manufacturer / Maintenance M&D Flugzeugbau GmbH & Co. KG Streeker Straße 5b 26446 Friedeburg Germany...
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