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JS-MD 3

Aircraft Flight Manual

MD10-AFM-00-001
Issue: 01

Rev. 00

Rev. Date: 14-Feb-20

Page 7-21

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. The water tanks are integral
to  the  wings.  Each  inboard  wing  tank  holds  approximately  78 litres  of
water. Each 18 m wingtip holds approximately 17 litres of water.  The 15
m outboard wings have no integral water tanks.

There are two tail tanks to enable the pilot to set the optimum CG position
for flight:

•

The expendable ballast tail tank is positioned in the front area of
the vertical fin with a capacity of approximately 5.8 litres.

•

The  non-expendable  ballast  tail  tank  is  positioned  in  the  rear
area  of  the  vertical  fin  and  has  a  capacity  of  approximately
8.9 litres.  This  tank  is  used  to  optimize  the  un-ballasted  CG
position.    (The  non-expendable  ballast  tank  is  divided  into  two
tanks from SN 80.)

The water in the non-expendable ballast tank can be drained after flight
by removing the tape over the holes on the left-hand side of the fin.

The dump valve control is situated on the right-hand side of the cockpit.
Pushing the lever forward opens both the wing tank valves and the
expendable tail tank valve.

Moving the dump valve control in the full forward position opens also
the 18m outboard wing tank valves.

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Содержание JS-MD 3

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Страница 3: ...ber Document number MD10 AFM 00 001 Title JS MD 3 Aircraft Flight Manual Issue 01 Date of issue 14 Feb 20 Responsible for content S ren Pedersen HOA The technical content of this document is approved...

Страница 4: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page ii Intentionally left blank...

Страница 5: ...Placard replaced Fig 4 4 1 Pre flight and pre take off placard amended Fig 4 5 4 Vne Chart placard amended Section 4 5 6 Park brake caution added Table 5 3 1 Polar coefficients added Section 6 2 updat...

Страница 6: ...ons Section 7 8 2 1 7 8 2 2 7 8 3 1 7 8 3 2 Heading added Caution note added in section Section 7 8 3 18m tip figure updated Sections 7 8 4 1 7 8 4 2 added Section 7 11 electrical system and battery d...

Страница 7: ...tive sections Section Revision Date Number of Pages Reference 0 00 14 02 2020 8 1 00 14 02 2020 6 2 00 14 02 2020 20 3 00 14 02 2020 14 4 00 14 02 2020 32 5 00 14 02 2020 6 6 00 14 02 2020 18 7 00 14...

Страница 8: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 0 4 Record of amendments Date of Issue Revision Date of Insertion Signature...

Страница 9: ...s 0 5 1 General 1 1 Introduction 1 1 Certification basis 1 1 Warnings cautions and notes 1 2 Descriptive data 1 3 Technical data 1 4 Three view drawing 1 5 2 Limitations 2 1 Introduction 2 1 Airspeed...

Страница 10: ...l dive recovery 3 5 Excessive sideslip recovery 3 6 Engine failure Jet turbine 3 7 Engine Fire 3 7 Electrical fire 3 8 Other emergencies 3 9 4 Normal operating procedures 4 1 Introduction 4 1 Rigging...

Страница 11: ...16 Pneumatic system 7 17 Airbrake system 7 19 Baggage compartment 7 20 Water ballast system 7 21 Power plant 7 30 Fuel system 7 30 Electrical system 7 31 Miscellaneous equipment 7 36 8 Handling and m...

Страница 12: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 0 8 Manufacturer Maintenance 12 1...

Страница 13: ...iner Even though it possesses excellent performance and handling qualities it can only be flown by a skilled pilot who complies with the limitations and recommendations set out in this manual If a Jet...

Страница 14: ...Flight Manual WARNING Means that the non observation of the corresponding procedure leads to an immediate or important degradation in flight safety CAUTION Means that the non observation of the corre...

Страница 15: ...surface of the wing Boundary layer control is achieved on the main wing bottom surfaces the horizontal stabilizer and vertical fin All control surface hinge gaps are sealed with Mylar strips and Teflo...

Страница 16: ...270 kg 595 lbs 282 kg 622 lbs Empty weight minimum options with engine 286 kg 631 lbs 298 kg 657 lbs Maximum weight without water ballast 415 kg 916 lbs 430 kg 948 lbs Wing load min 70kg pilot 40 0 kg...

Страница 17: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 1 5 Three view drawing JS 3 15 m Figure 1 6 1 JS 3 15 m...

Страница 18: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 1 6 JS 3 18 m Figure 1 6 2 JS 3 18 m...

Страница 19: ...1 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 sta...

Страница 20: ...o not make full or abrupt control movements above this speed because under certain conditions the aircraft may be overstressed by full control movement VFE Maximum flap extended speed See Table 2 2 2...

Страница 21: ...h 151 kts 2 0 3 5 230 km h 124 kts 4 13 5 165 km h 89 kts 5 16 6 165 km h 89 kts L 20 160 km h 86 kts Table 2 2 2 Airspeeds for flap settings The maximum allowable airspeeds for each flap setting are...

Страница 22: ...s Normal Operating Range Lower limit is 1 1 VS1 at maximum weight and most forward CG with flaps neutral Upper limit is rough air speed Yellow Arc 207 to 280 km h 112 to 151 kts Manoeuvres must be con...

Страница 23: ...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 Supp...

Страница 24: ...Off Mass 525 kg 1157 lbs 600 kg 1323 lbs Maximum Take Off Mass without water ballast 415 kg 915 lbs 430 kg 948 lbs Maximum Take Off Mass for winch launching 525 kg 1157 lbs 600 kg 1323 lbs Maximum Tak...

Страница 25: ...288 kg 635 lbs 234 kg 516 lbs 400 kg 882 lbs 305 kg 672 lbs 257 kg 567 lbs 425 kg 937 lbs 310 kg 683 lbs 280 kg 617 lbs 450 kg 992 lbs 314 kg 692 lbs 302 kg 666 lbs MTOM 320 kg 705 lbs 313 kg 690 lbs...

Страница 26: ...to 400 kg 270 mm 10 63 in 270 mm 10 63 in Most forward CG location at MTOM 305 mm 12 01 in 315 mm 12 40 in Most aft CG location 390 mm 15 35 in 398 mm 15 67 in Table 2 6 1 Allowable CG range The datu...

Страница 27: ...26 6 in 26 3 in 26 7 in 270 596 660 mm 660 mm 660 mm 668 mm 26 0 in 26 0 in 26 0 in 26 3 in 280 618 646 mm 646 mm 649 mm 659 mm 25 4 in 25 4 in 25 5 in 25 9 in 290 640 637 mm 633 mm 640 mm 650 mm 25 1...

Страница 28: ...roved 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 Positive loop...

Страница 29: ...on IAS Load factor 15 m 18 m Maximum positive manoeuvre 207 km h 112 kts 5 3 Maximum negative manoeuvre 207 km h 112 kts 2 65 Maximum positive manoeuvre 280 km h 151 kts 4 0 Maximum negative manoeuvre...

Страница 30: ...ured empty CG is not within the normal empty mass CG range the minimum and maximum cockpit mass must be calculated and the cockpit placard values must be corrected accordingly Pilots with a weight bel...

Страница 31: ...or 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 liste...

Страница 32: ...nce with Section 2 2 of this manual Altimeter 4 Point symmetrical seat harness Fixed Operating placards or Placard Booklet Control surface gap seals Mylar seals on all control surfaces Additional inst...

Страница 33: ...d Maximum speed Maximum weak link rating Winch or ground launch 150 km h 81 kts 750 daN E g Tost weak link 3 Red Aerotow 180 km h 97 kts 600 daN E g Tost weak link 4 Blue Table 2 12 1 Aerotow and winc...

Страница 34: ...permitted when flying with water ballast Temperature restrictions without water ballast Flights conducted in conditions below 30 C are prohibited When the outside air temperature is less than 30 C a d...

Страница 35: ...ts at outside temperature well above the freezing point CAUTION Currently no additives e g anti freeze are approved to lower the water freezing point Limitations while dumping water ballast Dumping th...

Страница 36: ...When the airbrakes are extended in possible turbulent conditions the Rough Airspeed VRA should not be exceeded Decelerate to 200 km h 108 kts before closing the airbrakes The forces acting on the airb...

Страница 37: ...and contains the most important mass and speed limitations Figure 2 14 1 Limitation placard The placard given in Figure 2 14 1 must list the same units as the airspeed indicator Refer to the MD10 AMM...

Страница 38: ...h 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 NO...

Страница 39: ...ison To jettison the canopy pull both left and right canopy jettison latches as far as possible and push the canopy upward with the latches The jettison latches are labelled or engraved as shown in th...

Страница 40: ...he 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 4 Deploy the parachute in accordance with...

Страница 41: ...re on the control stick and move it towards the neutral position CAUTION During stalled flight if the angle of attack is increased by further pulling back on the stick a wing drop may occur This asymm...

Страница 42: ...ing the pull out if the spin was commenced in flap Position 4 5 or L to avoid exceeding VFE Maximum Flap Extended Speed CAUTION Do not use airbrakes during the pull out of the dive WARNING Intentional...

Страница 43: ...e slip angles with full rudder deflection Indications of a spiral dive are a high bank angle increasing airspeed and a high G load Spiral dive recovery is performed by 1 Apply the aileron co ordinated...

Страница 44: ...tion of the yaw 2 When balanced flight is restored neutralize both aileron and rudder WARNING If an excessive slip angle is not corrected with opposite rudder input the secondary effect of yaw may cau...

Страница 45: ...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...

Страница 46: ...tch supplying the circuits 2 If a circuit breaker pops reset only once This is most likely due to a faulty circuit 3 Land as soon as possible Cockpit fire on the ground The most likely cause of a cock...

Страница 47: ...the cable 3 Only after adequate flying speed has been regained Extend the airbrakes and land straight ahead provided sufficient runway is available OR Use an abbreviated circuit and carry out a landin...

Страница 48: ...p the wings level When a developing asymmetry is observed perform the following to prevent full asymmetry developing 1 If a lateral asymmetry is detected but no water was dumped during the flight ther...

Страница 49: ...approach speed by 10 km h or 5 kts 3 Avoid any operation near stall speeds 4 Avoid turns in the landing flap configuration with the airbrakes extended 5 Keep the heavy wing as high as possible during...

Страница 50: ...imately 20 below the horizon To recover from a spin towards the heavy wing use the following procedure 1 Apply full rudder opposite to the spin rotation 2 Simultaneously release the elevator back pres...

Страница 51: ...a is too short to stop safely before the end a ground loop may be initiated 1 Apply maximum wheel brake to reduce energy as much as possible 2 Initiate a ground loop at least 50 m or 165 ft before the...

Страница 52: ...gear 4 Undo the parachute harness during the downwind leg 5 Ensure that the safety straps are tight 6 Try to land parallel to the shore and against the wind 7 Close the water dump valves before touchd...

Страница 53: ...eparation 1 Roll the fuselage from the trailer onto the assembly ramp if assembly from trailer 2 Ensure there is adequate ground clearance to extend the main landing gear 3 Lift the tail off the groun...

Страница 54: ...e are installed 8 Insert the right spar end into the fuselage with the flaperon in the neutral position and the dihedral angle approximately correct 9 Insert the left spar end into the fuselage also w...

Страница 55: ...s 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 WARNING Failure to ensure that the red ru...

Страница 56: ...care not to over tighten the tailplane front attachment bolt Hand tight only maximum 1 Nm torque Install auxiliary items 1 Insert the batteries into position in the luggage compartment behind the sea...

Страница 57: ...sealing tape on the wing fuselage junction wing wing tip junctions and tailplane fin junction Retracting the undercarriage 1 Lock the tail wheel in the down position by inserting the optional locking...

Страница 58: ...on 3 and move the control stick to the centre position 3 Pull the wingtip locking lever fully back and the slide wing wingtips out of the inboard section Secure the wingtips in the trailer 4 Insert th...

Страница 59: ...gged 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...

Страница 60: ...fety Figure 4 3 1 Forward fuselage Check the functionality of the nose release hook Cockpit 1 Ensure that the canopy is clean 2 Check the canopy emergency release mechanism pull back both jettison lat...

Страница 61: ...to check the rudder cables for signs of fraying kinks and wear especially near the S tube exits Perform a visual check on the rudder pedal retention nuts by checking that they are securely in place E...

Страница 62: ...rt or mud may lead to improper functioning of the release hook 7 Check that the water drain orifice behind the landing gear box is clear Wings 1 General condition Check for evidence of damage to the s...

Страница 63: ...erating correctly Check the dump rate of the main tanks with the filler caps installed Ensure that the dump rates of the left and right wings are equal and that the dump rate is faster than that of th...

Страница 64: ...ed 5 Check the vertical tail tank valve operation Check that the dump rate of the tail tank exceeds 1 litre per minute 6 Check that the tank vent holes on the left hand side of the fin are unobstructe...

Страница 65: ...ted Ensure that there are no leaks from the root rib drain plugs and on the 18m tips at the junction drain plugs after filling the aircraft with ballast Mass and balance Trim weight water ballast tail...

Страница 66: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 4 14 Figure 4 4 1 Pre flight and pre take off check placard...

Страница 67: ...ain wheel and tail wheel just touching As the speed builds up gently rotate into the full climbing attitude Change to flap setting 4 when the aircraft is established in the full climbing attitude Winc...

Страница 68: ...ed maximum loads WARNING With the CG in the aft position and a fast acceleration the aircraft will automatically rotate into the climb WARNING Downwind winch launches jeopardise the safety of the laun...

Страница 69: ...he flap to the setting indicated in Table 4 5 3 Aerotow speed table Flap setting Airspeed km h kts Recommended aerotow speed No water ballast 4 130 km h 70 kts Recommended aerotow speed MTOM 4 140 km...

Страница 70: ...ment Section 2 7 2 4 5 3 2 Self launch The Jet Sustainer fitted is not approved for self launching operations Flight The JS 3 offers exceptionally good flying characteristics handling and manoeuvrabil...

Страница 71: ...weight Flap settings 4 3 2 1 Deflection 13 5 5 0 3 Configuration With no water ballast 90 110 km h 49 59 kts 110 120 km h 59 65 kts 120 180 km h 65 97 kts 180 km h VNE 97 kts VNE With max water balla...

Страница 72: ...g 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 Due to high aerodynamic forces the flaps may not be extended...

Страница 73: ...135 km h 73 kts Strong crosswind flap setting 3 full airbrakes 120 km h 65 kts 135 km h 73 kts Table 4 5 5 At maximum take off mass with the airbrakes fully extended and at 117 km h 63 kts the approac...

Страница 74: ...radient may become negative i e the rudder will be aerodynamically pushed against the rudder stop This can be corrected by applying opposite rudder Refer to Section 3 7 for the excessive sideslip reco...

Страница 75: ...ear on the tip skid wheel and reduces the risk of damaging the flaperons Safe landing in cross winds up to 30 km h 16 kts is possible due to the polyhedral wing shape allowing high bank angles during...

Страница 76: ...78x2 litres Wing tips 0 litres 17x2 litres Expendable tank capacity 5 8 litres Non expendable tank s 8 9 litres Fuselage tank if fitted 35 litres Total expendable water capacity no fuselage tank 162 l...

Страница 77: ...he tail tank should always be filled based on the CG calculation as described in Section 6 Under no circumstances is it permitted to fly with the CG aft of the rear limit CAUTION The filler caps must...

Страница 78: ...n in the daily inspection check list 4 Close the dump valve in the cockpit 5 Fill the 18 m tips if fitted Filling can be done through the dump valve using filling equipment allowing a maximum of 0 1 b...

Страница 79: ...t only partially the inboard wings must be dumped first This is achieved by moving the damp valve lever to the centre position 4 If progressively increased aileron deflection is required to maintain b...

Страница 80: ...opping on take off WARNING Check for the correct dumping sequence The tail tank must finish dumping before the main wing tanks to ensure safe shifting of the CG WARNING The wing tips must be filled wi...

Страница 81: ...peed 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 As flutte...

Страница 82: ...e indicated airspeed to compensate for the effect of high altitude Flight in rain When flying in rain a decrease in glide performance is expected The airfoil is specially designed not to have any loss...

Страница 83: ...intained between 100 km h and 120 km h 54 kts and 65 kts The aircraft should be flown without excessive slipping or skidding 3 If the wings are allowed to get too contaminated the wiper might get stuc...

Страница 84: ...7 below Aerobatic entry speed Flap setting Entry speed G load Lazy Eight 3 180 km h 97 kts 3 Chandelle 3 150 km h 81 kts 2 Steep turn 3 150 km h 81 kts 3 Positive loop 3 200 km h 108 kts 3 5 Stall tu...

Страница 85: ...from actual flight tests with the aircraft in good conditions and using average piloting techniques Approved data Airspeed indicator calibration During airspeed calibration tests the airspeed indicati...

Страница 86: ...vable speed IAS CG fwd Minimum achievable speed IAS CG fwd L 20 78 km h 42 kts 86 km h 46 kts 5 16 6 79 km h 43 kts 88 km h 48 kts 3 5 87 km h 47 kts 95 km h 51 kts 1 3 91 km h 49 kts 98 km h 53 kts T...

Страница 87: ...ining aircraft Additional information 5 2 4 1 Turbulators On the lower surface of the flaperons there is a line of blow holes supplying air by NACA ducts It is necessary to keep these holes and ducts...

Страница 88: ...acteristics 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 During winch launch 25 km h 14 k...

Страница 89: ...light Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 5 5 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 c...

Страница 90: ...ference mass Configuration 15m 18m Reference mass 450 kg 992 lbs 500 kg 1102 lbs Polar coefficients a 0 9847 0 9233 b 1 8498 1 6595 c 1 4745 1 2658 Table 5 3 1 NOTE The calculated flight polar can be...

Страница 91: ...ulas Calculation of minimum and maximum cockpit loads Weight and balance record The weight and balance record summarizes the results of weight and balance calculations and gives the maximum and minimu...

Страница 92: ...nk s empty Non Expendable fin tank s full Approval Name Signature Min Max Min Max 15 18 15 18 15 18 15 18 15 18 15 18 15 18 Table 6 2 1 NOTE When a fuselage water tank is installed instead of a Jet Sy...

Страница 93: ...n Water ballast Expendable tail tank Non expendable tail tank Baggage O2 bottle Fuselage water ballast Fin ballast Adjustment possibilities such as cockpit ballast lead tail ballast and water in the n...

Страница 94: ...S MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 6 4 expendable fin tank The moment arms are measured from the datum with the following sign convention Figure 6 3...

Страница 95: ...156 344 247 9 7 6 MWingT Water ballast tip 18 m 36 79 480 18 9 7 MFusT Fuel tank top 5 6 12 3 500 19 7 8 MFusB Fuel tank bottom 12 7 28 853 33 6 9 MTail1 Expendable tail tank 5 8 13 4285 168 7 10 MTai...

Страница 96: ...parate non expendable fin tanks fitted from SN 080 and onwards Figure 6 3 2 Moment Load point Max Mass Moment arm kg lbs mm inch 10 1 MTail2 Non expendable tail tank bottom 5 0 11 0 4495 177 0 10 2 MT...

Страница 97: ...Moment Mass x Moment arm 4 Add the mass of the applicable loads 5 Add the moments of the applicable loads 6 Plot the mass against the moment on the JS 3 Envelope diagram Figure 6 3 3 7 The Flying CG...

Страница 98: ...ble tail tank 5 8 4285 24 9 5 Non expendable tail tank 8 9 4510 40 1 8 O2 bottle AL248 2 0 0 0 Totals 524 7 172 6 Table 6 3 3 The plot on the diagram illustrated in Figure 6 3 3 demonstrates that the...

Страница 99: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 6 9 Figure 6 3 3 illustrates the envelope for the 15 m configuration Figure 6 3 3...

Страница 100: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 6 10 Figure 6 3 4 illustrates the envelope for the 18 m configuration Figure 6 3 4...

Страница 101: ...lained in the JS MD 3 Maintenance Manual Update the cockpit loads placard or Placard Booklet Figure 2 14 2 Update the weight and balance record Table 6 2 1 o Add remove the removable ballast to change...

Страница 102: ...lbs mm inch MTAIL1 Expendable tail tank 5 8 13 4240 167 Table 6 4 1 To offset the forward CG change due to water in the main wing tanks the expendable tail tank must be filled according to the Table...

Страница 103: ...imum cockpit weight is therefore higher when water is added to the fuselage tanks The table below indicates the maximum weight and moment arm of the fuselage tank Load point Mass Moment arm kg lbs mm...

Страница 104: ...below indicates the maximum weight and moment arm of the fuselage tanks Load point Mass Moment arm kg lbs mm inch MFTTop Fuel tank top 5 6 12 3 500 19 7 MFTBot Fuel tank bottom 12 7 28 853 33 6 Table...

Страница 105: ...tank Table 6 4 5 indicates the maximum weight and moment arm of the non expendable ballast tank Load point Mass Moment arm kg lbs mm inch MTail2 Non expendable tail tank 8 9 19 6 4510 177 6 Table 6 4...

Страница 106: ...5 3 2 7 0 2 2 3 4 9 7 4 67 5 8 3 2 0 7 1 8 4 3 6 9 69 6 3 3 8 1 2 1 3 3 8 6 4 71 6 8 4 3 1 7 0 8 3 3 5 9 73 7 3 4 8 2 2 0 3 2 8 5 4 75 7 8 5 3 2 7 0 2 2 3 4 9 77 8 3 5 8 3 2 0 7 1 8 4 3 79 8 8 6 3 3 8...

Страница 107: ...ient to reach the optimum CG position Refer to the CG calculator to ensure the forward CG limit is not violated CAUTION Flying on the aft limit is not recommended Winch launching with the CG in the ca...

Страница 108: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 6 18 Intentionally left blank...

Страница 109: ...he controls their labels and layout in the aircraft Cockpit controls Elevator and aileron The elevator and ailerons are controlled conventionally by the control stick Forward aft movement deflects the...

Страница 110: ...hing either pedal deflects the rudder in the desired direction The rudder pedals fore and aft position is adjustable to accommodate different size pilots The ergonomic controller on the right hand sid...

Страница 111: ...t The flap handle can be freed from its detent by rotating it slightly clockwise as seen from the rear Figure 7 2 2 The flap setting is indicated on the flap indicator plate Figure 7 2 3 positioned ju...

Страница 112: ...20 Page 7 4 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 cock...

Страница 113: ...b 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 contro...

Страница 114: ...tion 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...

Страница 115: ...ary switch at 30 degree intervals used to select the appropriate system to be adjusted Figure 7 2 7 Selector knob layout The adjuster switch is a momentary ON OFF ON toggle switch used to adjust the s...

Страница 116: ...ser to the pilot Multiple safety features in the rudder pedal adjustment include Built in limit switches at both ends of travel Overload shutoff switch this prevents pedal adjustment if pressure is ap...

Страница 117: ...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 Figure 7 2 9 Figure 7 2 9 Seatback lower adj...

Страница 118: ...ircraft 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 in...

Страница 119: ...lation open will still allow air to flow over the instrument binnacle 7 2 6 4 De misting control Electrical option For aircraft equipped with the ergonomic control system the cabin ventilation system...

Страница 120: ...7 2 6 6 Cabin ventilation control Electrical option For aircraft equipped with the ergonomic control system the cabin ventilation system is electrically adjustable via the ergonomic control panel To a...

Страница 121: ...sed to supply power to any 12V 2A device Instrument panel The instrument panel is integral with the canopy and lifts to facilitate entering and exiting from the aircraft The canopy can be removed from...

Страница 122: ...1 Rev 00 Rev Date 14 Feb 20 Page 7 14 Description 1 VNE Chart Figure 4 5 4 replaceable by Placard Booklet 2 Circuit breakers 3 Battery selector switches Figure 7 11 2 4 Master switch arrangement Figur...

Страница 123: ...d 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...

Страница 124: ...er pilots should add firm cushions preferably energy absorbing cushions on the seat pan to raise the body position in the cockpit The cushion height should be sufficient to ensure that the shoulder st...

Страница 125: ...r Static for the ASI and Altimeter Blue Dynamic for the ASI Green Static for the electronic flight computer from the multi probe Transparent White Total energy from the fin probe Red Mechanical variom...

Страница 126: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 7 18 Figure 7 5 1 Figure 7 5 2 Static ports on fuselage...

Страница 127: ...operated as follows Pull the handle backwards to open the airbrakes Figure 7 6 2 illustrates the cockpit label for the open airbrake position Push the airbrake lever forward to close the airbrakes Fig...

Страница 128: ...approximately 20mm Avoid prolonged airbrake settings where the caps are oscillating WARNING When closing the airbrakes ensure the airbrake lever is fully forward and locked over centred The first dete...

Страница 129: ...The expendable ballast tail tank is positioned in the front area of the vertical fin with a capacity of approximately 5 8 litres The non expendable ballast tail tank is positioned in the rear area of...

Страница 130: ...ional fuselage ballast tank can be installed instead of an engine system This tank is accessible via the engine bay doors This tank can be either non expendable or as an option fitted with an electric...

Страница 131: ...ection 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 Figure 7 8 2...

Страница 132: ...ust be fitted the one way valves CAUTION The filling pipe diameter should preferably not exceed 12mm 0 5 Water tanks may burst under high water pressure if the filling pipe is left unguarded in the fi...

Страница 133: ...Each outboard wing additionally carries approximately 17 litres of water Description 1 Dump valve bottom of wing 2 Vent hole or vent filling plug optional top of wing 3 Drain plug optional bottom of w...

Страница 134: ...h water pressure if the filling pipe is left unguarded in the filling hole without sufficient venting area around the pipe If a vent filling plug is fitted instead as an alternative to the vent hole f...

Страница 135: ...the 18m outboard tip and subsequently remove the red drain plug from the root Lift the tip of wing panel with the leading edge facing downwards and allow all the water to drain If a drain plug is inst...

Страница 136: ...s behind the shear web Figure 7 8 6 SN003 079 7 8 4 1 Expendable water ballast The expendable water ballast in front of the fin shear web is used to offset the CG change due to the water ballast in t...

Страница 137: ...filling hole on the left side of the fin These must be filled according to the procedure provided in Paragraph 4 5 7 1 Draining is done by removing sealing vinyl stickers from the bottom hole on left...

Страница 138: ...30 filled to reach total capacity Both tanks must be drained by removing sealing vinyl stickers from the bottom hole s Figure 7 8 7 SN080 and onwards Filling hole Left Vent hole Right Non expendable...

Страница 139: ...ht Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 7 31 Power plant Refer to JS MD 3 Jet Sustainer Flight Manual Supplement Fuel system Refer to JS MD 3 Jet Sustainer Flight Manual Supp...

Страница 140: ...th a battery master switch arrangement and battery selection switches CAUTION Overload protection is provided for each electrical system by circuit breakers The rating for each system must comply with...

Страница 141: ...attery 2 or Auxiliary Battery for bus 1 bus 2 and the electric bus Power to the different systems can be selected from the appropriate battery shown in Table 7 11 1 Battery BAT 1 Left BAT 2 R AUX BAT...

Страница 142: ...s and electrical systems are on a separate switch arrangement allowing selection between the Battery 1 L Battery 2 R and centre C and or the auxiliary battery C if installed Figure 7 11 2 NOTE The swi...

Страница 143: ...x 30 mm Fuse required for Avionics 15 A Electrical provision is made for a third battery behind the seat back Installation and type of additional batteries must comply with CS STAN SC034a NOTE Only t...

Страница 144: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 7 36 Figure 7 11 3 Master switch arrangement...

Страница 145: ...e instrument panel CAUTION The radio microphone is located on the canopy frame Take care when removing the canopy from the instrument panel The microphone plug should be carefully unplugged to avoid d...

Страница 146: ...the wipers are set to wipe not closer than 500 mm from the winglet Check that both wipers sit correctly in their garages when retrieved Check the condition of the wiping cable and retrieve cable Check...

Страница 147: ...dvisable to follow a regular schedule of lubrication and preventive maintenance consistent with the usage climatic and flying conditions encountered For service and information not contained within th...

Страница 148: ...cks as specified in Section 4 The manufacturer recommends performing additional inspections in certain circumstances such as hard landings or ground loops as explained in the JS MD 3 Aircraft Maintena...

Страница 149: ...r pull on the wingtips Supporting area for road transport 1 Fuselage Tail skid or tail wheel with tail wheel faring removed Main wheel Shell in front of landing gear minimum length of support 300 mm 2...

Страница 150: ...oard 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 It is advisable to restra...

Страница 151: ...outer surface finish is to present a good aerodynamic surface to the air when flying but also to protect the structure from the environment The main enemy for the structure is UV rays and moisture UV...

Страница 152: ...act an M D representative for recommended canopy polishes Cockpit interior The inside of the cockpit can be cleaned with mild soap and water Water tanks The aircraft should always be stored with the w...

Страница 153: ...for corrosion and proper functioning Also refer to the seat belt harness manufacturer s maintenance instructions Tow release Clean the nose and CG hooks regularly by means of pressured air and lubrica...

Страница 154: ...to prevent small animals from entering 5 Drain all water tanks and force ventilate the water tanks until the inner surfaces of the tanks are dry Remove the water filler caps and keep the valves open...

Страница 155: ...an oxygen bottle with a maximum diameter of 86 mm 3 4 The oxygen bottle tube is installed through the bulkhead on the left hand side of the wheel box The oxygen bottle must be correctly secured with...

Страница 156: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 9 2 Intentionally left blank...

Страница 157: ...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 sec...

Страница 158: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 10 2 Intentionally left blank...

Страница 159: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 06 02 2019 Page 11 1 11 STCs and minor change approvals Reference No Rev Date Description...

Страница 160: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 06 02 2019 Page 11 2 Intentionally left blank...

Страница 161: ...Contact Type Certificate Holder M D Flugzeugbau GmbH Co KG Streeker Stra e 5b 26446 Friedeburg Germany 49 0 4465 97878 11 Mail info md flugzeugbau de Manufacturer Maintenance M D Flugzeugbau GmbH Co...

Страница 162: ...JS MD 3 Aircraft Flight Manual MD10 AFM 00 001 Issue 01 Rev 00 Rev Date 14 Feb 20 Page 12 2 Intentionally left blank...

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