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JS-MD 1C Aircraft Flight Manual

MD01-AFM-00-001
Issue: 02

Rev. 00

Rev. Date: 14.09.2017

Page 3–4

3.5 Spin recovery

Spin recovery is performed using the standard recovery procedures:

1. Apply rudder opposite direction to the spin rotation

2. Simultaneously release the elevator back pressure by moving

the stick forward to the neutral position

3. Centralize the rudder when the rotation stops

4. Gently pull out of the resulting dive

NOTE

:

Ailerons  should  be  kept  neutral  during  the  recovery
process.  (However,  full  aileron  deflection  in  either
direction does not  have a  significant influence on the
recovery behaviour.

CAUTION

:

Move flaps to Position 3 during the pull-out if the spin
was commenced in flap Position 4, 5 or L to avoid
exceeding V

FE

(Maximum Flap Extended Speed).

CAUTION

:

Do not use airbrakes during spin recovery procedure.

WARNING

:

Intentional spins with water ballast are prohibited.

WARNING:

Intentional spins in 21 m configuration are prohibited.

Altitude  loss during recovery is  between 100 m and  150 m (330 ft to
500 ft)  without  water  ballast  and  up  to  220  m  (720  ft)  at  maximum
weight.  The  spin  rotation  speed  is  relatively  low,  typically  five  to  six
seconds per rotation.

If the spin is entered with a high incident angle, the nose will oscillate in
pitch during the first two rotations. After approximately one rotation, the
nose will (with very aft CG positions) rise above the horizon before
stabilizing in a nose down spin attitude. Pitch oscillation may continue
during the spin, especially with aft CG positions.

3.6 Spiral dive recovery

A spiral dive may occur when:

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Содержание JS-MD 1C 2017

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Страница 3: ...MD 1C Aircraft Flight Manual Issue 02 Date of issue 14 September 2017 Responsible for content Issue 02 of this JS MD 1C Aircraft Flight Manual is approved under the authority of APDOA EASA AP175 Secti...

Страница 4: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page ii Intentionally left blank...

Страница 5: ...MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 0 1 0 Document Management 0 1 List of Issues Issue Date Reason for Change 01 15 05 2017 Initial Issue 02 14 09 2017 Editorial Changes Section...

Страница 6: ...ist of effective sections Section Revision Date Number of Pages Reference 0 00 14 09 2017 6 1 00 14 09 2017 6 2 00 14 09 2017 18 3 00 14 09 2017 14 4 00 14 09 2017 32 5 00 14 09 2017 8 6 00 14 09 2017...

Страница 7: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 0 3 0 3 Record of Amendments Date of Issue Revision Date of Insertion Signature...

Страница 8: ...and notes 1 2 1 4 Descriptive data 1 3 1 5 Technical data 1 4 1 6 Three view drawings 1 5 2 Limitations 2 1 2 1 Introduction 2 1 2 2 Airspeed limits 2 2 2 3 Airspeed indicator marking 2 4 2 4 Mass 2...

Страница 9: ...1 5 2 Approved data 5 1 5 3 Non approved information 5 5 6 Weight and balance 6 1 6 1 Introduction 6 1 6 2 Weight and balance record 6 1 6 3 Permitted payload range and CG envelope 6 3 6 4 Optimisati...

Страница 10: ...2 Rev 00 Rev Date 14 09 2017 Page 0 6 8 2 Ground handling 8 3 8 3 Cleaning and care 8 5 8 4 Long term storage 8 9 9 Supplements 9 1 9 1 Introduction 9 1 9 2 List of ancillary equipment 9 1 10 Service...

Страница 11: ...of the JS MD 1C All the data that is required by the Airworthiness Requirement CS 22 to furnish the pilot is contained in this manual It also contains supplementary data supplied by the sailplane manu...

Страница 12: ...of airworthiness is U Utility 1 3 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 co...

Страница 13: ...ith two main pins The airbrakes are a triple blade design on the upper surface of the wing Boundary layer control is achieved on the main wing bottom surfaces the horizontal stabilizer and vertical fi...

Страница 14: ...m JS MD 1C 21 m Empty Weight without Engine 310 kg 683 lbs 330 kg 728 lbs Maximum Weight 600 kg 1323 lbs 720 kg 1587 lbs Wing Loading min 70 kg pilot 34 1 kg m 6 98 lb ft2 32 6 kg m 6 68 lb ft2 Wing...

Страница 15: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 1 5 1 6 Three view drawings JS MD 1C 18 m Figure 1 6 1 1...

Страница 16: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 1 6 JS MD 1C 21 m Figure 1 6 2 1...

Страница 17: ...imitations 2 1 Introduction Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the aircraft standard systems and standard equipment The lim...

Страница 18: ...ouds etc VA Manoeuvring speed 203 km h 110 kts Do not make full or abrupt control movement above this speed because under certain conditions the sailplane may be overstressed by full control movement...

Страница 19: ...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 0 2 The maximum allowable airspeeds for each flap setting are indicated on the airspeed indicator AS...

Страница 20: ...2 at maximum weight and most forward c g with flaps neutral Upper limit is rough air speed Yellow Arc 203 to 270 km h 110 to 146 kts Manoeuvres must be conducted with caution and only in smooth air Re...

Страница 21: ...tion 500 kg 1102 lbs Maximum Mass of non lifting parts 350 kg 772 lbs 325 kg 717 lbs Maximum Mass in baggage compartment 1 kg 2 2 lbs Table 2 4 0 1 WARNING Only soft items such as canopy covers and ja...

Страница 22: ...Most forward CG location 244 mm 9 61 in 269 mm 10 59 in Most aft CG location 375 mm 14 76 in 375 mm 14 76 in Table 2 5 0 1 The datum is defined as the wing leading edge at the wing root rib i e on the...

Страница 23: ...21 m 18 m 21 m 320 705 558 mm 22 0 in 593 mm 23 4 in 597 mm 23 5 in 330 727 553 mm 21 8 in 587 mm 23 1 in 593 mm 23 4 in 340 749 548 mm 21 6 in 582 mm 22 9 in 590 mm 23 2 in 350 771 543 mm 21 4 in 577...

Страница 24: ...s certified in the Utility category U The following aerobatic manoeuvres are permitted in the 18 m configuration only Lazy Eight Chandelle Steep turns Positive loops Stall turns Spins Refer to Section...

Страница 25: ...uvring loads are given in the Table 2 7 0 1 below Condition IAS Load factor 18 m 21 m Maximum positive manoeuvre 203 km h 110 kts 5 3 Maximum negative manoeuvre 203 km h 110 kts 2 65 Maximum positive...

Страница 26: ...easured empty CG is not within the normal empty mass CG range the minimum and maximum cockpit loads must be calculated and the cockpit placard values corrected accordingly Pilots below the minimum wei...

Страница 27: ...VFR day Cloud flying only in 18 m configuration without water ballast where national regulations permit NOTE For Cloud flying the take off mass must not exceed the Maximum Take Off Mass without Water...

Страница 28: ...to 350 km h 27 to 189 kts colour markings in accordance with Section 2 3 Altimeter 4 point symmetrical seat harness Operating placards Control surface gap seals Mylar seals on all control surfaces Ad...

Страница 29: ...imum Speed 18 m Maximum Speed 21 m Recommended Weak link Winch or ground launch 150 km h 81 kts 140 km h 76 kts 750 daN E g Tost weak link 3 Red Aerotow 180 km h 97 kts 600 daN Tost weak link 4 Blue T...

Страница 30: ...flying is not permitted when flying with water ballast Temperature restrictions without water ballast Flights in conditions below 30 C are prohibited When the outside air temperature is less than 30...

Страница 31: ...rently no additives e g anti freeze are approved to lower the water freezing point Limitations while dumping water ballast Dumping water ballast takes approximately five minutes While dumping the fuse...

Страница 32: ...ent conditions the Rough Airspeed VRA should not be exceeded Decelerate to 180 km h or 97 kts before closing airbrakes Airbrake forces above 200 km h are very high WARNING The deceleration associated...

Страница 33: ...ixed to the wall of the cockpit in the field of view of the pilot preferably the left side and contain the most important mass and speed limitations Figure 2 13 0 1 Figure 2 13 0 2 The placard given i...

Страница 34: ...acard as illustrated in Fig 2 13 0 3 and must correlate with the values in the mass and balance report Figure 2 13 0 3 The nose ballast placard Figure 2 13 0 4 is located underneath the Control panel...

Страница 35: ...the canopy pull both left and right canopy jettison latches labelled or engraved as in the picture below as far as possible and push the canopy upward with the latches The Roeger hook will act as a pi...

Страница 36: ...ness 4 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 5 Deploy the p...

Страница 37: ...se the back pressure 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 ma...

Страница 38: ...nced in flap Position 4 5 or L to avoid exceeding VFE Maximum Flap Extended Speed CAUTION Do not use airbrakes during spin recovery procedure WARNING Intentional spins with water ballast are prohibite...

Страница 39: ...ll rudder deflection Indications of a spiral dive are high bank angle increasing airspeed and a high G loading Spiral dive recovery is performed by 1 Apply aileron co ordinated with rudder gently agai...

Страница 40: ...e direction 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...

Страница 41: ...upplying the circuits 2 If a circuit breaker pops reset once only This is most probably the faulty circuit 3 9 Land as soon as possible Cockpit fire on the ground The most likely cause of a cockpit fi...

Страница 42: ...2 Release cable 3 Only once adequate flying speed has been regained Extend airbrakes and land straight ahead provided sufficient runway is available OR Use an abbreviated circuit and carry out a land...

Страница 43: ...wings level When a developing asymmetry is observed take the following action to prevent full asymmetry developing 1 If a lateral asymmetry is detected but no water was dumped during the flight there...

Страница 44: ...rease approach speed by 10 km h or 5 kts Avoid any operation near stall speeds Avoid turns in landing flap with airbrakes extended Keep the heavy wing as high as possible during the ground run Change...

Страница 45: ...on Position 1 5 Apply aileron into the turn 6 Centralize the controls when the rotation stops 7 Gently pull out of the resulting dive A spin entry towards the lighter wing is unlikely and recovery is...

Страница 46: ...d a ground loop may be initiated 1 Apply maximum wheel brake to reduce energy as much as possible 2 Initiate ground loop at least 50 m or 165 ft before the end of the landing area 3 Lower the into win...

Страница 47: ...that aircraft fuselage can submerge completely The following procedure is recommended for an emergency landing on water 1 Dump all ballast 2 Make a radio call 3 Extend the landing gear 4 Undo the par...

Страница 48: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 3 14 Intentionally left blank...

Страница 49: ...02 Rev 00 Rev Date 14 09 2017 Page 4 1 4 Normal operating procedures 4 1 Introduction Section 4 provides checklist and amplified procedures for the conduct of normal operations Normal operations assoc...

Страница 50: ...osition 3 and the control stick to the centre position 6 If bug wipers are fitted release both wipers by approximately 1 5 meters and place them in a safe place while rigging the sailplane This allows...

Страница 51: ...lever forward and ensure it locks positively by pushing the lever over centre 14 Check if the 21 m tip rubber water drain plugs where inserted during wing rigging only for 21 m wing tips CAUTION The f...

Страница 52: ...plane onto the fin Take care that the elevators are sliding into the elevator auto coupler 3 Make sure the Mylar edge on the tailplane does not snag on the fin 4 Screw the tailplane main bolt into pos...

Страница 53: ...uit breakers on the battery connector boxes 3 Install the total energy tube and temporary equipment logger etc 4 Seal the wing fuselage junctions wing wingtip junctions and the fin tailplane junctions...

Страница 54: ...junction and tailplane fin junction Retracting the undercarriage 1 Roll the aircraft into the fuselage dolly The gear doors should be approximately 5 cm 2 inches from the ramp end 2 Lift the ramp unti...

Страница 55: ...otate Rotate the wing pins out of the locked position while pulling back the lock pin 7 Remove the main pins CAUTION Do not lower the wings after the main pins have been removed The fuselage shell may...

Страница 56: ...een 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 Forward fuselage 1...

Страница 57: ...ace Ensure pedals lock positively in the desired setting under load 6 Ensure the operation of the water system main and tail tank valves 7 Ensure that charged batteries are correctly installed and con...

Страница 58: ...hat the outer wing panel is properly locked without play 5 Check that the flaperons move freely with no hinge play Perform a positive control check on the inboard and outboard flap 6 Check that wing t...

Страница 59: ...arks and cracks 2 Check that the Total energy multi probe receptacle is clear Drain all possible water from the receptacle if the probe was left in position during rain by removing the multi probe and...

Страница 60: ...ertical tail fin water ballast tank is correct in relation to wing water ballast and cockpit load 8 Check that the horizontal stabilizer is properly installed without free play 9 Check that the contro...

Страница 61: ...er Ballast System Check operation and proper sealing of valves and vents unobstructed Weight and Balance Trim weight water ballast tail and wing tanks minimum and maximum cockpit load within calculate...

Страница 62: ...htly forward Allow the aircraft to get airborne in the 2 point position main wheel and tail wheel just touching As the speed builds up gently rotate into the full climbing attitude Change to flap sett...

Страница 63: ...ecommended as this may cause overruns on the winch drum WARNING Downwind winch launches jeopardise the safety of the launch significantly and should be avoided WARNING Winch launch with water ballast...

Страница 64: ...ble 4 5 1 2 Aerotow speed table Flap setting Airspeed km h kts 18 m 21 m Recommended aerotow speed ranges 3 4 115 to 140 km h 62 to 76 kts Minimum safe aerotow speed No water ballast calm conditions 3...

Страница 65: ...hermalling is Position 4 or 5 Flap setting 4 is the normal thermalling flap setting The optimum thermal speed at maximum loading is 105 to 115 km h 57 to 62 kts When the thermals are very rough it is...

Страница 66: ...weight combination there is an optimum flap setting for maximising the glide angle The following table gives the optimum flap setting as a function of speed and weight Flap settings 4 3 2 1 deflection...

Страница 67: ...nual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 4 19 Lightning The JS MD 1C is not approved for flight where lightning strikes may occur WARNING Flights in conditions conducive to lightn...

Страница 68: ...hen the cockpit handle is moved to the forward position Table 4 5 3 1 gives the recommended airspeeds for the approach Minimum Recommended Approach Speeds Various Approach Types Loading configuration...

Страница 69: ...mended as this 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 flyin...

Страница 70: ...when braking hard reduces the chances of damaging the flaperon trailing edges on uneven surfaces and improves aileron control at slow speeds Whilst slowing down and it is no longer possible to keep th...

Страница 71: ...lves and will dump simultaneously with the inboard main tanks This tank can be used to offset the centre of gravity change due to the water ballast in the main inboard wing tanks To offset the forward...

Страница 72: ...NOTE As a conservative approximation add 1 litre of water in the bottom tail tank for every 25 litres of water in the main inboard wing tanks WARNING The tail tank should always be filled based on th...

Страница 73: ...xpendable tail tank is empty by following the procedure given in the daily inspection check list 4 Close the dump valve in the cockpit 5 Fill the 21 mtips if fitted Filling can be done through the dum...

Страница 74: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 4 26 Add water ballast using the top filling port top one on the right hand side of the fin...

Страница 75: ...ion 4 If progressively increased aileron deflection is required to maintain bank angle while dumping water the water is probably dumping unevenly Refer to Section 3 10 2 for details on asymmetrical fl...

Страница 76: ...must finish dumping before the main wing tanks to ensure safe shifting of CG WARNING The wing tips must be filled with water ballast if the main tanks or fuselage tanks are filled even partially fille...

Страница 77: ...an that the colour markings on the Air Speed Indicator are not correct at high density altitude As flutter depends upon true airspeed the maximum allowable airspeed must be reduced at high altitudes F...

Страница 78: ...to compensate for the effect of high altitude Flight in rain When flying in rain it can be expect that there will be a decrease in glide performance The airfoil is specially designed not to have any l...

Страница 79: ...he winders Cleaning can be performed in level flight or during climbing as long as airspeed between 90 km h and 120 km h 49 kts and 65 kts is maintained The aircraft should be flown without excessive...

Страница 80: ...lap setting Entry speed km h kts G loading 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 turns 3 200 km h 108 k...

Страница 81: ...approved further information The data in the charts has been computed from actual flight tests with the sailplane in good condition and using average piloting techniques 5 2 Approved data Airspeed ind...

Страница 82: ...8 kts 82 km h 44 kts 5 16 6 75 km h 40 kts 84 km h 45 kts 3 5 79 km h 43 kts 86 km h 46 kts 1 3 85 km h 46 kts 99 km h 53 kts Table 5 2 2 1 Table 5 2 2 2 gives the stall speeds for the JS MD 1C 18 m c...

Страница 83: ...82 km h 44 kts 94 km h 51 kts 1 3 86 km h 46 kts 101 km h 55 kts Table 5 2 2 3 With the flying centre of gravity in the forward positions the elevator is not able to produce a sufficiently high angle...

Страница 84: ...e boundary layer transition from laminar flow to turbulent flow in flap setting 1 and 2 If the boundary layer control is not working properly a whistling sound can be heard when changing to flap setti...

Страница 85: ...MD 1C has very good crosswind handling characteristic due to its polyhedral wing shape allowing high bank angles during touch down The maximum demonstrated crosswind components are During aerotow 25 k...

Страница 86: ...t Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 5 6 Flight polar Figure 5 3 2 1 shows the calculated polar for the JS MD 1C in the 21 mfor two wing loading cases Figure 5 3 2...

Страница 87: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 5 7 Noise data Not applicable to the pure sailplane...

Страница 88: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 5 8 Intentionally left blank...

Страница 89: ...s CG calculation formulas Calculation of minimum and maximum cockpit loads 6 2 Weight and balance record The Weight and Balance Record summarizes the results of weight and balance calculations and giv...

Страница 90: ...PTY Empty CG position XCG Permitted pilot weights S N Without tail battery With ___ kg Tail Battery Approved Min Max Min Max Date Signed Table 6 2 0 1 For the calculation of the permitted maximum and...

Страница 91: ...Non expendable tail tank Tail battery Baggage O2 bottle Fuselage Water ballast top bottom tanks To allow the pilot to achieve the desired CG position adjustment possibilities are the nose ballast the...

Страница 92: ...last main 180 396 8 200 7 9 4 MTail1 Expendable tail tank 7 5 16 5 4570 179 9 5 MTail2 Non expendable tail tank 4 5 9 9 4630 182 3 6 MTailB Tail battery 2 7 6 0 4520 178 7 MBag Baggage compartment 1 2...

Страница 93: ...ion To determine if a selected loading falls within the CG envelope as illustrated in Fig 6 3 0 2 the following procedure can be used 1 List all the loads in table format as illustrated in Table 6 3 0...

Страница 94: ...n in metric units only Loading point Mass kg Arm mm Moment kg m Mass x Arm 1000 Empty aircraft 312 622 194 1 1 Pilot and parachute 90 575 51 8 3 Water ballast main 180 200 36 4 Expendable tail tank 7...

Страница 95: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 6 7 Figure 6 3 0 2 Figure 6 3 0 3 gives the envelope for the 21 m configuration...

Страница 96: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 6 8 Figure 6 3 0 3...

Страница 97: ...ntenance Manual o Update the Cockpit loads placard Fig 2 13 0 3 o Update the weight and balance record Table 6 2 0 1 Add remove removable ballast to change the empty no water ballast centre of gravity...

Страница 98: ...Expendable tail tank 7 5 16 5 4630 182 3 Table 6 4 1 1a To offset the forward centre of gravity change due to water in the main wing tanks the expendable tail tank must be filled according to the Tabl...

Страница 99: ...moment arm of the fin battery Loading point Mass Moment arm kg lbs Mm inch MTailB Tail battery 2 7 6 0 4520 178 Table 6 4 2 1a Refer to the minimum cockpit weights placard LH side of cockpit or Table...

Страница 100: ...ge tanks The table below indicates the maximum weight and moment arm of the fuselage tanks Loading point Mass Moment arm kg lbs mm inch MFTTop Fuselage tank top 12 26 5 435 17 1 MFTBot Fuselage tank b...

Страница 101: ...4 4 1a Table 6 4 4 1b indicates the required loading litres of water in the non expendable ballast tail tank to achieve the optimum centre of gravity position Non expendable tail tank loading require...

Страница 102: ...NoseB Nose ballast 11 24 3 1800 70 9 Table 6 4 5 1a Table 6 4 5 1b indicates the required removable nose trimming weights in kilogram to move the CG into a permissible range Nose trimming weight requi...

Страница 103: ...section gives a description of the aircraft systems together with instruction on the use of it A detailed technical description of the systems with drawings can be found in the MD01 AMM 00 001 JS MD 1...

Страница 104: ...on are controlled conventionally by the control stick Various stick grip options are available with integrated instrument control buttons or just the radio transmit button press to talk A leather boot...

Страница 105: ...ckpit below the airbrake lever Slider trim system If the slider trim system is installed the trim can be adjusted when the trim knob is pressed downwards Moving the trim knob has the following effect...

Страница 106: ...and to accommodate different size pilots The rudder pedal adjuster handle is built into the side of the centre console The adjuster is pulled to disengage the lock The pedals can be moved away from t...

Страница 107: ...cockpit The flap handle can be unlocked by twisting it slightly clockwise as seen from the rear Figure 7 2 4 1a The flap setting is indicated on the flap indicator plate Figure 7 2 4 1b positioned ju...

Страница 108: ...ev Date 14 09 2017 Page 7 6 Release system The nose and CG hooks are operated simultaneously when the release handle is pulled The release handle is the yellow handle positioned on the left hand cockp...

Страница 109: ...e cockpit ventilation is controlled with two air vents 1 The Adjustable Ball type vent installed in the right cockpit console Figure 7 2 6 1 2 The Scoop window fitted on the sliding window optional Th...

Страница 110: ...out is built to the owner s requirements and approved by the manufacturer There are various options that the customer can choose from Some of the stickers that are being used on the instrument panel a...

Страница 111: ...rding to the owner s requirements and language 7 5 Microphone and antenna The plugs for microphone and antenna from the canopy frame are behind the instrument panel CAUTION The radio microphone is loc...

Страница 112: ...landing gear handle is located on the right hand side of the cockpit and labelled as illustrated in Figure 7 5 0 1 Pulling the handle backwards retracts the wheel and pushing it forward extends the w...

Страница 113: ...6 0 1 2 The top of the seatback can be adjusted between an upright or reclined position by moving the seatback adjuster located behind the seatback in or out The seat back adjuster is unlocked by squ...

Страница 114: ...the pilot s shoulders CAUTION Shorter 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 suffi...

Страница 115: ...I and Altimeter Blue Dynamic piping for ASI Green Static for electronic flight Computer from multi probe Transparent White Total Energy piping from fin probe Red Mechanical variometer capacity Yellow...

Страница 116: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 7 14 Figure 7 7 0 1...

Страница 117: ...of the cockpit Figure 7 8 0 1 The airbrakes are operated in the conventional manner Pull the handle backwards to open the airbrakes Figure 7 8 0 2 illustrates the cockpit label for the open airbrake p...

Страница 118: ...orward over the over centre lock A force of approximately 15 to 20 kg is required to lock the airbrakes The last 20 of rearward movement actuates the wheel brake Do not land with the airbrake handle p...

Страница 119: ...s 1 kg This should only be used for soft items that will not injure the pilot in the event of a hard or crash landing Make sure that the batteries that are carried in this area are secured with the ba...

Страница 120: ...tail tank is positioned in the bottom area of the vertical fin with a capacity of approximately 7 5 litres The non expendable ballast tail tank is positioned above the expendable tail tank in the vert...

Страница 121: ...g tool The main tanks are vented through the vent holes in the filler caps Optionally vent caps fitted with specially designed valves can be fitted These valves will reduce water spillage through the...

Страница 122: ...lt into the sailplane from each battery to the instrument panel via the channel on the right hand side of the cockpit Each main battery is equipped with circuit breaker box fitted on top of the batter...

Страница 123: ...battery 15 A Tail backup battery 12 V Sealed Lead Acid or LiFePO4 battery Dimensions 178 mm x 34 mm x 60 mm Fuse required at battery 10 A WARNING Only use the batteries supplied with the aircraft or s...

Страница 124: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 7 22 1...

Страница 125: ...hts Provision can be made for trim weights to be fitted in the nose of the sailplane adjacent to the nose release hook bulkhead as indicated in Figure 7 12 1 1 The nose ballast can be made up with com...

Страница 126: ...ired in the remaining slots 6 Insert the bottom and top locking pins and secure with R pin 7 Insert the slider locking pin Removal of the 7 kg weight plate 1 Remove slider locking pin by removing the...

Страница 127: ...weight plates 1 Remove the bottom locking pin 2 Remove the top locking nut 3 Remove the weights by lifting the weights one by one from the slider Oxygen Provision is made for an oxygen bottle at the...

Страница 128: ...m the winglet Check that both wipers seat correctly in their garages when retrieved Check the condition of the wiping cable and retrieve cable Check that the stabilizing leg of the wiper opens between...

Страница 129: ...en approaching head on NOTE The sailplane is not certified for night flying regardless if a strobe light is fitted The strobe light is connected either directly to the battery or if a LX Flarm ACL is...

Страница 130: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 7 28 Intentionally left blank...

Страница 131: ...advisable 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 t...

Страница 132: ...cockpit checks as specified in Section 7 The manufacturer recommends performing additional inspections in certain circumstances such as hard landings or ground loops as explained in the MD01 AMM 00 00...

Страница 133: ...or pull on the wingtips Supporting area for road transport Fuselage o Tail skid or tail wheel with tail wheel faring removed o Main wheel o Shell in front of landing gear minimum length of support 300...

Страница 134: ...nboard 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 rest...

Страница 135: ...paint topcoat There is no composite material available that is impervious to moisture absorption or to UV ultra violet rays UV rays will break down the epoxy matrix cross links and moisture absorptio...

Страница 136: ...ure This will shows as cracks and yellowing The gel coat can be protected by refinishing the aircraft with a Polyurethane Acrylic 2K paint system factory finish process Applying hard wax will not prev...

Страница 137: ...nks The sailplane should always be stored with the wing tanks open to ventilate It is also a good idea to put a small electrical fan on top of the wing surface over the water filler hole to force vent...

Страница 138: ...maintenance instructions Tow release Clean the nose and CG hooks regularly by means of pressured air and lubricate with spray oil Also refer to the MD01 AMM 00 001 JS MD 1C Aircraft Maintenance Manua...

Страница 139: ...event small animals from entering 5 Drain all water tanks and force ventilate water tanks until insides of the tanks are dry Remove water filler caps and keep valves open during storage 6 Leave the ai...

Страница 140: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 8 10 Intentionally left blank...

Страница 141: ...gen equipment installed a must be approved b must be free from hazards in itself in its method of operation and its effect upon other components c must have means to allow the pilot to readily determi...

Страница 142: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 9 2 Intentionally left blank...

Страница 143: ...an overview table of all optional SBs in which the owner or operator should mark which SBs he voluntary implemented and which not All implemented optional SBs have to be printed and added to this sec...

Страница 144: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 10 2 Intentionally left blank...

Страница 145: ...JS MD 1C Aircraft Flight Manual MD01 AFM 00 001 Issue 02 Rev 00 Rev Date 14 09 2017 Page 11 1 11 STCs and Minor Change Approvals Reference No Rev Date Description...

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