Diamond Aircraft HK 36 TS Flight Manual Download Page 87

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D IAMOND AIRCRAFT

HK 3 6 TS

FLIGHT MANUAL

Systems Description

7. POWERED SAILPLANE AND SYSTEMS

7 . 1
7 . 2

7 . 3

7 . 4
7 . 5

7 . 6
7 . 7
7 . 8

7 . 9

7 . 1 0

7 . 11
7 . 12
7 . 13

7 . 14

INTRODUCTION

AIRFRAME

7 . 2 . 1 Wings

7 . 2 . 2

Fuselage .

7 . 2 . 3 Tail plane

FLIGHT CONTROLS

DESCRIPTION

7 . 3 . 1 Primary controls

7 . 3 . 2 Elevator trim sys t em

7 . 3 . 3 Rudder pedal adj ust

AIR BRAKE SYSTEM

. . . .

LANDING GEAR SYSTEM

7 . 5 . 1 General

7 . 5 . 2

Wheel brake

7 . 5 . 3

Parking brake

SEATS AND SAFETY HARNESSES

BAGGAGE COMPARTMENT . . .

COCKPIT

7 . 8 . 1 Mode select switch

7 . 8 . 2 Instruments

7 . 8 . 3

Cabin heat and cabin air

7 . 8 . 4

Canopy . . . .

POWER- PLANT

7 . 9 . 1 Engine . . . . . . .

7 . 9 . 2

Power plant control s

7 . 9 . 3

Cowl flap

. . . . .

7 . 9 . 4

Propeller

Governor

7 . 9 . 5

Propeller speed control

FUEL SYSTEM

7 . 1 0 . 1 General . . . . . . . .

7 . 1 0 . 2 Fuel shut -off valve . .

7 . 10 . 3 Tank drain

7 . 1 0 . 4 Fuel quantity indicator

ELECTRICAL SYSTEM . .

P ITOT AND STATIC SYSTEM

MISCELLANEOUS EQUIPMENT

PLACARDS I INSCRIPTIONS

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Summary of Contents for HK 36 TS

Page 1: ..._ni_rc_ h g _ s_ c_l _1____ Original date of approval 0 no ve f 8SG This powered sailplane is to be operated in compliance with the information and limitations contained herein Prior to operating the...

Page 2: ...and prov ide you with hours of enj oyment Therefore you should take the time to get familiar with your new HK 3 6 TS We ask you to read this manual thoroughly and to pay attention to the recommendati...

Page 3: ...iness authority The new or amended text in the revised page will be indicated by a black vertical line in the left hand margin and the Revision No and the date will be shown on the bottom left hand of...

Page 4: ...4 24 6 6 4 7 7 5 7 11 0 cover II through IV 2 2 14 I J 2 J 2 4 4 J 4 4 4 22 5 5 5 6 7 7 14 0 II through IV J 7 7 11 Revision No_ Date 3 2 8 Oct JUN 1997 25 AUG 1997 28 ocr 1998 1 OOLG i o 0 0 t v p ii...

Page 5: ...6 1997 1996 1996 1996 1996 1996 1997 1996 1996 1996 1997 1997 1996 1996 1996 1997 1996 1997 1996 1996 1996 1996 1996 1996 1996 1996 1996 1996 1997 1997 1996 1996 1996 1997 1996 Revision No Date Source...

Page 6: ...AN 1996 7 5 JUN 1997 7 6 JAN 1996 7 7 JAN 1996 7 8 JAN 1996 7 9 JAN 1996 7 1 0 JAN 1996 7 11 2 8 OCT 1998 7 12 JAN 1996 7 13 JAN 1996 7 14 2 5 AUG 1997 7 15 JAN 1996 7 16 JAN 1996 8 8 1 JAN 1996 8 2 J...

Page 7: ...roved section PERFORMANCE a partly approved section MASS WEIGHT AND BALANCE I EQUIPMENT LIST a non approved section POWERED SAILPLANE AND SYSTEMS DESCRIPTION a non approved section POWERED SAILPLANE H...

Page 8: ...TION BASIS 1 3 WARNINGS CAUTIONS AND NOTES 1 4 EXPLANATIONS 1 4 1 Abbreviations 1 4 2 Physical units 1 4 3 Special terms 1 5 DESCRIPTIVE DATA 1 6 THREE VIEW DRAWINGS Revision No Date Source Doc No 3 0...

Page 9: ...orms to the actual version of the customer s airplane However any optional equipment COM NAV etc is not considered For their operation the operation manual of the respective manufacturer must be follo...

Page 10: ...rresponding procedure leads to an immediate or important degradation of the f light safety CAUT I ON Means that the non observation of the corresponding procedure leads to a minor or to a more or less...

Page 11: ...out any correction of errors TAS True Airspeed lAS corrected by errors due to instrument system altitude and temperature 1 4 2 Physical units hPa Hectopascal inHg inches mercury column psi pounds per...

Page 12: ...1013 25 mbar or 1013 25 hPa Maximum altitude that can be reached with a climb rate of at least 0 5 mls approx 100 ft min Distance between the start of the take off run and the lift of f point Distance...

Page 13: ...able a fast disassembly and a space saving storage the airplane can be furnished with a wing folding mechanism The power plant is a Rotax R 9 1 2 A3 engine with an mt propel l er MTV 2 1 A C F CF175 0...

Page 14: ...DIAMOND AIRCRAFT 1 6 THREE VIEW DRAWINGS HK 3 6 TS FLIGHT MANUAL a 1 I I II II t II II I I _ TI _ f J _ I r L Revision No Date Source Doc No Issue 3 0 1 0 6 Jan 1996 General Page No 1 7...

Page 15: ...RAFT I I 1I I I I I It if t inJ IU I II II II II I I I I Revision No Date HK 3 6 TS FLIGHT MANUAL o N o o S Z5 II g I I I Source Doc No 3 0l 0 6 General II II II II I III I II I I II I I ssue Page No...

Page 16: ...WEIGHT 2 7 CENTER OF GRAVITY 2 8 APPROVED MANEUVERS 2 9 MANEUVERING LOAD FACTORS 2 10 FLIGHT CREW 2 11 KINDS OF OPERATION 2 12 FUEL 2 13 AEROTOW WINCH AND AUTOTOW LAUNCHING 2 14 OTHER LIMITATIONS 2 15...

Page 17: ...y for safe operation of the powered sailplane its engine standard systems and standard equipment The limitations included in this section and in Section 9 have been approved by Austro Control GmbH ACG...

Page 18: ...han 1 3 of control deflection Do not use more than 1 3 of the travel between position of the controls for unacce lerated f light and deflec tion to stop Do not exceed this speed except in smooth air a...

Page 19: ...y the never exceed speed vNE is limited at altitudes above 2000 meters 6500 ft see sub paragraph 4 5 7 WARNING The maneuvering speed stated on the previous page appli es to the maximum T O mass max T...

Page 20: ...with the maximum possible rate of climb Best angle of climb speed Vx 95 km h 5 1 kts 59 mph This airspeed is not marked on the airspeed indicator At this airspeed the airplane climbs with the maximum...

Page 21: ...ts mph 8 6 210 4 6 113 53 1 3 0 Significance Normal Operating Range Lower limit is max mass weight 1 1 vS1 at most forward c g with air brakes retracted Upper limit is rough air speed 210 261 Maneuver...

Page 22: ...opeller speed Consequently all speeds given in this manual are propel ler speeds in contrast to the engine manual Max T O power 5 minutes Max T O RPM Max continuous power Max continuous RPM Idle RPM P...

Page 23: ...chart The lubricant quality rating according to the API system must be SF or SG climatic single grade oils multi grade oils tropical temperate arctic CAUTION Under no circumstances should Aviation Gra...

Page 24: ...off mass max TIO weight 770 kg Maximum landing mass Maximum mass of all non lifting parts Serial numbers below 36 517 Serial number 36 517 and subsequent Maximum mass in baggage compartment Maximum us...

Page 25: ...e Manual Section 4 The permissible flight CG range is Maximum forward CG Maximum rearward CG 318 mm 12 52 in aft of reference datum 430 mm 16 93 in aft of reference datum WAR N I NG A flight CG which...

Page 26: ...ess the airplane 2 10 FLIGHT CREW Solo flights must be conducted from the left seat 2 11 KINDS OF OPERATION The HK 3 6 TS is certified for DAY VFR operation Night VFR operation if permitted by the com...

Page 27: ...ers liters liters liters 14 5 US gal 2 0 9 US gal 14 3 US gal 2 0 3 US gal Aviation Grade 100 LL MOGAS leaded min octane rating 96 ROZ Limitations Automotive Super min octane rating 95 ROZ leaded or u...

Page 28: ...very much dependent on the temperature Therefore the length of a continuous soaring at low temperatures is restricted to 4 hours at o C 3 2 OF 2 hours at 10 C 14 OF good maintenance condition and char...

Page 29: ...FACTOR 176 km h 95 kts 1 109 mph 770 kg 1698 lbs 5 3 2 65 No acrobatic maneuvers including spin approved Altitude loss in a stall recovery 20 m 65 ft Flight into known icing conditions prohibited Thi...

Page 30: ...7 1 Engine failure during take off 3 4 3 7 2 starting the engine with a discharged battery 3 5 3 7 3 Propeller stuck in feathered position 3 6 3 7 4 Engine failure during cruise 3 7 3 7 5 Carburetor i...

Page 31: ...know the airplane and to have knowledge and experience in solving problems that may occur 3 2 CANOPY JETTISON 1 Strongly swing red canopy locks left and right 180 rearward 2 Place both hands above you...

Page 32: ...nly at 5 0 to 1 0 0 power wings level flight and maximum rearward center of gravity the airplane may perform a stall dive over the left or right wing after entering the horizontal stall if the control...

Page 33: ...e to spiral dive rotation 2 Apply full aileron opposite to spiral dive rotation 3 Pull out the airplane smoothly 3 7 ENGINE FAILURE carburetor icing 3 7 1 Engine failure during take off 1 Fuel valve c...

Page 34: ...TAKE OFF 1 0 oil pressure should be avai lable within 1 0 seconds 1 1 Choke re adjust if required 1 2 RPM and throttle as required to continue flight CAUTION Ensure adequate altitude reserve for engi...

Page 35: ...g light extinguishes after build up of fuel pressure 6 Choke as required 7 Throttle control IDLE 8 Ignition switch BOTH 9 Propeller speed control TAKE OFF 10 Ignition switch turn clockwise to start en...

Page 36: ...f switch i s in BOTH position 6 Fuel quantity check N OTE If you cannot eliminate the troubles and the engine refuses to deliver enough power proceed as follows 1 Throttle control IDLE 2 Ignition OFF...

Page 37: ...ning of the engine without a change in the throttle control position the choke position the propeller setting the airspeed or the altitude 1 Carburetor heat ON NOTE The engine output will slightly dro...

Page 38: ...ster switch OFF 3 9 OTHER EMERGENCIES 3 9 1 Malfunction or failure of vroveller sveed control 1 RPM Keep in admissible range with throttle control 2 Airspeed reduce 3 9 2 Icing 1 Leave icing area 2 Co...

Page 39: ...extreme emergency situations Due to trials with sailplanes it is assumed that the airplane will submerge immediately after touching the water and then surface again 1 Parachute harness open 2 Seat har...

Page 40: ...abilizer removal DAILY INSPECTION PREFLIGHT INSPECTION 4 5 NORMAL PROCEDURES AND RECOMMENDED SPEEDS 4 5 1 Launch engine starting run up taxiing procedures 4 5 2 Take off and climb 4 5 3 Flight includi...

Page 41: ...ts are f ixed to the fuselage at the wing root The A bolt is placed in front of the spar tunnel the B bolt l ies near the trailing edge Self locking units are screwed onto the B bol t s which are acce...

Page 42: ...he wing tip in small circles The aileron and air brake control systems are automatically connected Do not release the wing before the main bolt has been completely inserted The wide track of the landi...

Page 43: ...A and B bolts Connect position and strobe lights optional when the gap between the fuselage and wing is just wide enough to reach the wires 5 Insert main bolt The aileron and a ir brake control syste...

Page 44: ...ply water resistant adhesive tape to the gap 4 2 6 Winglet removal TO remove the winglet reverse the procedure 4 2 7 Horizontal stabilizer installation appr 6 Nm 1 Clean all bushes and bolt s and appl...

Page 45: ...nt adhesive tape to the gap between the horizontal stabilizer and the vertical stabilizer 4 2 8 Horizontal stabilizer removal To remove the horizontal stabilizer reverse the procedure 4 3 DAILY INSPEC...

Page 46: ...rizontal stabilizer Check horizontal stabili zer and tips for improper mounting insecure attachment and inspect skin for damage and cracks Check elevator for improper mounting play damage and cracks C...

Page 47: ...and excessive play Check spinner for damage and insecure mounting 11 oil and coolant check Check oil level Ensure coolant level in equal i zing reservoir is more than 1 3 Check engine compartment for...

Page 48: ...loading is admissible refer to Section 6 NOTE Ensure observation of loading restrictions by changing and or rearranging the useful load Master switch ON Mode select switch POWER FLIGHT All circuit bre...

Page 49: ...ople must stay clear of the propel ler danger zone Ignition switch press and turn clockwise to start engine Propel l er speed adjust to approximately 1 0 0 0 RPM oil pressure must reach green range wi...

Page 50: ...ously with the ignition switch the propeller will remain in TAKE OFF position Propel ler feathering is only possible at RPMs above 5 0 0 see sub paragraph 7 9 5 Propel ler Speed control Propell er spe...

Page 51: ...leased 13 Air brakes locked 4 5 NORMAL PROCEDURES AND RECOMMENDED SPEEDS 4 5 1 Launch engine starting run up taxiing procedures 1 Rudder pedals 2 Seat harnesses 3 Canopy 4 Fuel valve 5 Controls 6 Park...

Page 52: ...ny reason a loss of oil pressure may occur after oil pressure build up in the area of the o i l pressure sensor The reason for this is the filling process of the accumulator The oil pressure indicator...

Page 53: ...ntil speed drops to approx 1 8 0 0 RPM Then reset to TAKE OFF position Repeat at least three times CAUTION Without repeating the procedure it is not ensured that the pitch change mechanism is operativ...

Page 54: ...the fuel system is intact the red warning lamp must not i lluminate since the engine driven pump maintains the fuel pressure For best angle of climb adjust airspeed to 9 5 kmjh 51 l ts j 5 9 mph for b...

Page 55: ...tched on mis operation of mode select switch In extreme cold see page 2 13 I f the battery is in a poorly maintained condition or barely charged 3 Ignition 4 Propeller 5 Mode select switch OFF FEATHER...

Page 56: ...o i l pressure sensor The reason for this is the filling process of the pressure accumulator The o i l pressure indicator may drop to zero for a maximum of 15 seconds 1 1 Choke 1 2 Electrical consume...

Page 57: ...kts 9 3 mph A control force reversal can appear when the rudder is ful l y deflected and the ailerons are deflected opposite to the rudder To recover ei ther release the aileron control or apply appro...

Page 58: ...brakes fixed in the hal f extended position vABf must not be exceeded 8 Sideslip 9 Approach speed possible but not necessary 1 0 5 kmjh 57 kts j 65 mph during final approach NOTE Conditions such as s...

Page 59: ...s NOTE Climbing is possible with the air brakes fixed in the half extended position 3 Perform climb with at l east 9 5 km h 51 kts 5 9 mph Monitor oil pressure oil temperatur e and cylinder head tempe...

Page 60: ...NOTE conditions such as strong headwind danger of wind shear turbulence or wet wings require a higher approach speed 4 Touchdown in three point position CAUTION In case of airplanes wi thout toe brake...

Page 61: ...0 0 1 3 1 0 0 to 164 0 0 5 0 0 0 to 6 0 0 0 16 4 0 0 to 1 9 60 0 4 5 8 Flight in rain of altitude the following must be observed v E km h ts mph 2 6 1 14 1 1 6 2 2 4 6 1 3 3 1 5 3 2 3 3 126 1 4 5 221...

Page 62: ...ake 4 Electric fuel pump 5 Electrical consumers 6 Ignition TAKE OFF IDLE set OFF OFF OFF NOTE In case of post ignition in hot weather conditions and when using MOGAS fuel switch on ignition again pul...

Page 63: ...nditions the airplane should be moored or stored in a hangar CAUTION Avoid outdoor parking for long periods of time NOTE The powered sailplane should not be parked with the propeller in the feathered...

Page 64: ...2 3 Take off performance 5 5 5 3 ADDITIONAL INFORMATION 5 3 1 Demonstrated crosswind performance 5 6 5 3 2 Glide performance and flight polar 5 6 5 3 3 Take off charts 5 7 5 3 4 Noise data 5 9 5 3 5 C...

Page 65: ...sailplane and engine in good condition wheel fairings installed and using average piloting techniques The specified airspeeds must be understood as lAS The performance data has been evaluated applyin...

Page 66: ...icator system calibration INDIGATED AIRSPEED lAS kts km Ih 140 260 l7 k f SO V 100 V 1 120 140 f 160 180 200 40 50 60 70 80 90 100 1 10 V 7 220 24 GAL BRATED AIRSPEED GAS Revision No Date Source Doc N...

Page 67: ...les i n kts Air Bank angle Brakes 0 3 0 45 retracted vSO 42 45 50 extended vS 1 44 47 52 Stall speeds at different bank angles in mph Air Bank angle Brakes 0 3 0 4 5 retracted vso 4 8 52 5 8 extended...

Page 68: ...t surface Take off roll 161 m 5 2 8 ft Take off distance to clear a 15 m 5 0 ft obstacle 3 0 6 m 1004 ft NOTE For take off distances under circumstances different from those described above refer to t...

Page 69: ...maximum flight mass max gross weight Minimum rate of descent 1 14 m s 22 4 ft min at 9 5 km h 51 kts 5 9 mph Maximum l ift drag ratio 2 8 at 1 0 5 km h 57 kts 65 mph Flight polar Condition propeller...

Page 70: ...a mbar m 0 1013 400 966 800 921 1200 877 Headwind component OAT sl s2 sl s2 sl s2 sl s2 kts C m m m m m m m m 0 142 275 160 3 02 179 3 3 5 201 3 7 1 0 15 161 3 0 6 182 3 3 8 204 375 229 417 3 0 1 82 3...

Page 71: ...6 8 597 1115 673 1237 755 1375 853 1529 374 7 6 1 420 840 472 935 531 1040 427 846 482 945 541 1050 6 14 1171 482 951 545 1060 620 1178 699 13 16 2 89 6 3 6 3 2 8 7 0 2 3 7 1 7 8 4 423 876 3 3 1 712 3...

Page 72: ...apter 10 Noise emission 6 1 4 dB A 5 3 5 Climb performance Maximum rate of climb Conditions Sea level Full throttle Max flight mass max gross weight v Vy 105 km h 5 7 kts I 6 5 mph Propeller speed 242...

Page 73: ...h per h r km h kts mph h mi n km mi 1 es mi 1 es 15 4 0 170 92 106 3 36 612 330 380 55 1 5 08 873 471 542 13 3 4 160 86 99 4 09 665 359 413 5 55 948 512 589 NOTE It is generally recommended for a fast...

Page 74: ...Y MASS AND MOMENT 6 5 MASS OF ALL NON LIFTING PARTS 6 6 MASS WEIGHT AND BALANCE FORM 6 7 USEFUL LOADS 6 7 l Maximum useful load 6 7 2 Seat payload 6 7 3 Useful load in baggage compartment 6 7 4 Fuel l...

Page 75: ...G range and a list of the equipment that must be present in the airplane during the weighing process are included in the Main tenance Manual Section 4 W ARN I NG Exceeding the maximum mass maximum gro...

Page 76: ...g Report shows the current empty mass empty weight and the corresponding CG position The Weighing Report is preserved in the Aircraft Maintenance Log NOTE After equipment changes repairs repainting et...

Page 77: ...5 Ibs s eat payload and 10 kg 22 Ibs of fuel for a half hour fl ight are aboard 6 5 MASS OF ALL NON LIFTING PARTS Maximum mass weight of all non lifting parts serial numbers below 3 6 517 serial numbe...

Page 78: ...out The Mass and Balance Form must be updated by an authorized person in compliance with the currently effective Weighing Report The corresponding instructions can be found in the Maintenance Manual...

Page 79: ...AL NO __ __ __ __ __ __ __ __ CALL S IGN Min seat payload with full tank Empty Maximum Baggage A M E s Empty mass useful No 12 kg Signa Date mass CG load Baggage 2 6 lbs ture kg mm kg kg kg lbs in lbs...

Page 80: ...yload for solo flights with a full tank and no baggage Minimum seat payload for solo flights with a full tank and maximum baggage mass 12 kg 2 6 Ibs The minimum seat payload is never less than 55 kg 1...

Page 81: ...f the baggage was assumed to be equal to the lever arm of the fuel tank i e 7 2 7 mm or 2 8 62 in for the standard tank 824 mm or 3 2 44 in for the long range tank NOTE When taking baggage aboard do n...

Page 82: ...seful load and minimum seat account It and baggage for a given shows the permissible seat payload mass weight of fuel The diagram applies to one specific airplane It is based on the data provided by t...

Page 83: ...g is permissible Example B Pilot 6 5 kg 143 Ibs solo flight Long range tank full 6 0 kg 132 Ibs baggage 12 kg 2 6 Ibs total 72 kg 159 Ibs The loading oversteps the maximum rearward CG position The pil...

Page 84: ...n g e T a n k 791 5 0 nU b N_f e _eL _ k_ ____ CO II sllln __2 L _EY ____r_______ Octe of w lflhln __i _te _ l _______ 1I t e _ ____ Dot o t Repl l nl _____________ M E _________________ lIpty M Mass...

Page 85: ...0 0 0 0 0 0 I I I I 1 1 0 0 0 0 I X I 1 0 S o 0 4 4 4 U 0 1 1 1 S 0 d 5 0 SSDW 1 1 dIJJ3 I I II I _I I I I I a a a co l a a a Cl N e f5 0 0 0 0 g p U D e n J O S S D W l D r Ol Dl r a N a 0 a 1 a l a...

Page 86: ...pressure indicator 1 Oil temperature indicator 1 Cylinder head temperature indicator 1 Fuel quantity indicator 1 Ammeter 1 Deviation table 1 Fuel pressure warning lamp Additional equipment Mass Balanc...

Page 87: ...BAGGAGE COMPARTMENT COCKPIT 7 8 1 Mode select switch 7 8 2 Instruments 7 8 3 Cabin heat and cabin air 7 8 4 Canopy POWER PLANT 7 9 1 Engine 7 9 2 Power plant controls 7 9 3 Cowl flap 7 9 4 Propeller G...

Page 88: ...coming the resistance occurring after the air brake is retracted The air brake l ever catches when the air brakes are extended half way The wings are connected to the fuselage with three bolts each Th...

Page 89: ...h control cables Elevator control forces can be compensated by means of a spring trim system The aileron and air brake control systems are automatically connected when the wing is installed However th...

Page 90: ...air brakes are unlocked and extended The air brake lever catches when the air brakes are extended half way This position can be over travelled in either direction with slightly increased force By pus...

Page 91: ...which are individually operated through toe pedals 7 5 3 Parking brake Wheel braking system without toe brakes The main wheels are equipped with hydraulically actuated disk brakes The wheel brake syst...

Page 92: ...elease Therefore these parachutes cannot be used Each seat is provided with a four part harness To fasten the harness the end pieces must be inserted into the lock To open the harness turn the twist h...

Page 93: ...DICATOR I ANIFOLD PRESSURE INDICA TOR J t CYLINDER HEAD TEMPERA TURE IND PRESSURE IND o COMMJNAV TRANSPONDER IGNITION STARTER SWITCH CABIN GPS BREAKERS FUEL QUANTITY INDICA TOR TI1ROTTLE fl COWL FLAP...

Page 94: ...hand section of the instrument panel The power plant instruments are installed in the right hand section 7 8 3 Cabin heat and cabin air The draw button for the cabin heat is located on the center con...

Page 95: ...swinging the red levers 1 8 0 0 rearward the canopy is disconnected from the brackets Then the pilot must place both hands above his head against the canopy and push it away in upward direction 7 9 PO...

Page 96: ...in a unit on the center console Throttle control Carburetor heat Propeller speed control Large round lever Lever full forward Small rectangular l ever Lever full rearward FULL THROTTLE CARBURETOR HEAT...

Page 97: ...l temperature below 80 C 1 7 6 O F NOTE Continuous operation with oil temperatures below 80 C 1 7 6 O F may lead to increased accumulation of condensation which can be recognized by white foam in the...

Page 98: ...control is not sufficient to maintain the selected RPM the propeller blades will move to the lowest possible pitch maximum RPM at this power setting I f the propeller speed control is moved full rear...

Page 99: ...t two minutes without oil being supplied by the engine As soon as the oil pressure in the pressure accumulator is used up the propeller blades will move into the feathered pitch position CAUT I ON The...

Page 100: ...finally to the float chambers of the two carburetors 7 1 0 2 Fuel shut off valve The fuel shut off valve is located on the left side of the center console near the pilot s feet Tap in flight directio...

Page 101: ...h is in POWER FLIGHT position In SOARING position all current consumers except for the COM equipment and the e lectric vertical speed indicator optional are currentless The NAV and COM equipment is lo...

Page 102: ...he mount The lowest spot of the Pitot and static lines is bridged by means of bypass l ines Water that might have entered the system can accumulate there Removal of water must be done during scheduled...

Page 103: ...D MAINTENANCE 8 1 INTRODUCTION 8 2 POWERED SAILPLANE INSPECTION PERIODS 8 3 POWERED SAILPLANE ALTERATIONS OR REPAIRS 8 4 GROUND HANDLING ROAD TRANSPORT 8 5 CLEANING AND CARE Revision No Date Source Do...

Page 104: ...ing conditions encountered 8 2 POWERED SAILPLANE INSPECTION PERIODS Inspections are scheduled every 100 2 0 0 and 600 hours The respective inspection checklists are prescribed in the Maintenance Manua...

Page 105: ...dable to remove insects with water and sponge after the day s flying is ended CAUT I ON Extreme dirt accumulation deteriorates flight performance Refer to the Maintenance Manual paragraph 1 4 for furt...

Page 106: ...MENTS At this t ime the following supplements are available Supplement 1 Use as a Tow Plane Supplement 2 Differential Braking System Supplement 3 Electrical Power Outlet for Additional Equipment Revis...

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