Hoffman DIMONA H 36 Скачать руководство пользователя | Manualshive

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33.1

Hoffmann

4

H 36 DIMONA

Slip

4.17

Slip:

4.17.1

Entry and Recovery:

Slip is practicable from 80 km/h (43 kt) (50 mph) to 120 km/h (65 kt) (75 mph).

—

Throttle idle

—

Apply aileron control in direction of intended slip.

—

Apply opposite rudder simultaneous.

—

To maintain desired airspeed apply aft stick.

—

Use airbrakes additionally if required.

Recover:
—

Reset controls in neutral position.

4.17.2

Characteristics:

Yaw up to 35* and bank up to 10* are practicable with full rudder and suitable aileron control. High
yaw angels require extensive elevator deflections up to the rear stop of the stick.

NOTE

Stall is not possible in the slip. At rear C.G. positions, nose pitches down slowly. Speed after recovery is
not less than 80 km/h (43 kt) (50 mph).

Rates of descent from 3 m/s (600 ft/mm) to 8 m/s (1600 ft/mm) are attainable dependent on airspeed
and yaw.

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Содержание DIMONA H 36

Страница 1: ... for U S registered gliders in accordance with the provisions of 14 CFR Section 21 29 and is required by FAA Type Certification Data Sheet No Reg No Ser No Owner Austrian edition of operating instructions is approved under 33 ZLLV Bundesgesetzblatt 415 Aug 17 1983 Published Nov 15 1985 BAZ approved on Nov 22 1985 Approval of translation has been done by best knowledge and judgment In any case the ...

Страница 2: ...ision Number and Date Revised Pages Description of Revision All manuals for the Hoffmann H 36 can be ordered from Hoffmann Aircraft Richard Neutra Gasse 5 P O Box 100 A 1214 Vienna Austria WARN ING This handbook should not be used for operational purpose unless it is maintained in a current status 0 1 ...

Страница 3: ...ections in the order shown below Section 0 Revisions Section 1 General Section 2 Limitations Section 3 Emergency Procedures Section 4 Normal Procedures Section 5 Performance data Section 6 Weight and Balance Equipment List Section 7 Motor Glider and Systems Descriptions Section 8 Aircraft Handling Service Maintenance Section 9 Supplements 1 1 ...

Страница 4: ... Section 1 General Paragraph Page 1 1 Introduction 4 1 2 Three view drawings 4 1 3 Description 5 1 4 Engine 5 1 5 Propeller 5 1 6 Approved Fuels 5 1 7 Approved Lubricants 6 1 8 Maximum Certified Weights 6 1 9 Symbols Abbreviations and Terminology 6 1 2 ...

Страница 5: ... handbook contains material required to be furnished to the pilot by JAR 22 It also contains supplemental data supplied by the airframe manufacturer Each section is divided by tab markers with Emergency Procedures tabbed in red 1 2 Three View Drawings 1 3 ...

Страница 6: ...r fixed landing gear with steerable tail wheel All three wheels are covered with fairings Seating arrangement is side by side Air brakes are provided in the wings upper surface The aircraft is certified in accordance with JAR 22 in the UTILITY CATEGORY 1 4 Engine Limbach L 2ooo EB 1 C Four cylinders opposed air cooled direct drive The engine produces 59 KW 80 Hp at 3 400 RPM 1 5 Propeller Hoffmann...

Страница 7: ...Weights The maximum allowable take off weight is 770kg 1698 lbs Maximum weight for non lifting parts is 560 kg 12361bs 1 9 Symbols Abbreviations and Terminology Liters Ltr Ki1ogramms Kg Indicated airspeed IAS Indicated airspeed in Knots KIAS Maneuvering Speed Va Max speed in rough air Vb Stalling Speed Vso Airbrakes retracted Max speed not to be exceeded Vne calm air Max speed with flaps extended ...

Страница 8: ...s 8 2 3 Minimum Equipment 8 2 4 Engine Limitations 9 2 5 Oil Pressure 9 2 6 Oil Temperature 9 2 7 Cylinder Head Temperature 9 2 8 Voltmeter 9 2 9 Airspeed Limitations and Load Factor Limits 10 11 2 10 Airspeed Indicator Markings 12 2 11 Crew Requirements 12 2 12 Weights 12 2 13 Center of Gravity Limitations 13 2 14 Placards and Markings 14 17 2 1 ...

Страница 9: ...ed for VFR flights Day Flights into known icing conditions are prohibited Approved aerobatic maneuvers are All aerobatic maneuvers inclusive spin and flights in clouds are forbidden 2 3 Minimum Equipment 1 Airspeed indicator 1 Altimeter 1 RPM counter with hour meter 1 Oil pressure indicator 1 Oil temperature indicator 1 Voltmeter 1 Fuel quantity indicator 1 Magnetic compass 1 Cylinder head tempera...

Страница 10: ...erating RPM Green Arc 700 3 000 RPM CAUTION Avoid RPM during cruise below 2300 min 1 2 5 Oil Pressure Maximum Oil Pressure red line 4 bar 55 8 psi Minimum Oil Pressure red line 1 bar 13 9 psi Operating Range green arc 1 4 bar 13 9 55 8 psi 2 6 Oil Temperature Maximum Oil Temperature red line 120 C 248 F Operating Range green arc 50 120 C 122 248 F Minimum Temperature red line 50 C 122 F 2 7 Cylind...

Страница 11: ... with airbrakes extended Vsl 70 km h 38 kts 44 mph Stall speed with airbrakes retracted Vso 70 km h 38 kts 44 mph Load Limit Factors The following accelerations may not be exceeded airbrakes retracted normal maneuvers At Maneuvering speed 5 3 2 65 At Maximum speed Vne 4 0 1 5 CAUTION When flying in areas where turbulent weather may be encountered i e thunder clouds wind rotors standing waves and m...

Страница 12: ...e km h 275 kts 149 259 140 246 133 233 126 221 119 NOTE Maneuvering speed Va is the maximum speed at which application of full available aerodynamic control will not overstress the airplane Increasing altitude increases True Air Speed TAS Indicated Airspeed Errors The following table illustrates airspeed errors IAS due to positioning of the pitot pressure and pitot static sources Pitot and Static ...

Страница 13: ...irspeed for the best climb Ratio is 85 km h 46 kts 53 mph 2 11 Crew Minimum Crew One Person min weight 70 kg 155 lbs CAUTION Solo flights may be conducted from the left seat only 2 12 Weights Empty Weight refer to section 6 3 Weighing report Max Gross Weight 770 kg 1698 lbs Min Wt in pilots seat incl parachute 70 kg 135 lbs Max Wt in each seat incl parachute 110 kg 243 lbs Max Wt in baggage compar...

Страница 14: ...rd 270 mm aft of leading edge wing root rib Aft Up to 740kg 385 mm aft of leading edge wing root rib At 770kg 370 mm aft of leading edge wing root rib Between 740 and 770 kg linear run between 370 and 385 mm For more detailed Center of Gravity information refer to section 6 Weight and Balance Equipment list 2 7 ...

Страница 15: ...auf Full throttle idle Brandhahn Fuel shut off valve auf zu open closed ein aus on off Luftung Cabin Air Heizung Cabin Heat Zundung Ignition Kraftstoffpumpe Fuel pump Hauptsicherung Main fuse Kopflastig Trimmung Nose down trim Schwanzlastig nose up Haubennotabwurf Canopy emergency jettison Parkbremse Parking brake Choke Choke Text and position of placards in English language see following pages 2 ...

Страница 16: ...NE 275 149 170 Rough Air Vb 210 113 130 Maneuvering Va 176 95 109 max Gross Weight 770 kg 1698 lbs min Payload in pilot seat 70 kg 154 lbs max Payload in any seat 110 kg 245 lbs Baggage Maximum 12 kg 26 5 lbs max Payload see Flight manual page 43 Below Canopy Frame Left side Altitude in ft 0 6500 Vne KIAS 149 10 000 140 13 000 133 16 500 126 20 000 119 Below Canopy Frame Left Side Labels on operat...

Страница 17: ...16 Hoffmann 2 H 36 DIMONA Limitations 2 10 ...

Страница 18: ...2 1 0 17 Hoffmann 2 H 36 DIMONA Limitations 2 11 ...

Страница 19: ...on 10 3 2 Stalls Power off 19 3 3 Spin Recovery 19 3 4 Engine failure during Take Off 20 3 5 Engine failure in flight 21 3 6 Emergency Landing 21 3 7 Icing 21 3 8 Carburetor Icing 21 3 9 Water Landings 21 3 l0 Engine fire during flight 22 3 11 Electrical fire during flight 22 3 12 Canopy Jettison Aircraft exiting during flight 22 3 1 ...

Страница 20: ...ng stall warning is buffeting as with power on however the aircraft will not roll on a wing and can be held level with aileron and rudder control The aircraft will sink vertically at a rate of 700 fpm Stall recovery in this mode is to relax back pressure on the stick 3 3 Spin Recovery Reduce power and push control stick full forward Apply fu11 rudder opposite to spin rotation Recover smoothly from...

Страница 21: ...immediately Fuel valve ON position Fuel pump ON position If these are not the cause of engine failure and the altitude is less than 300ft land straight ahead If more than 300 ft altitude are available a 180 turn in the glider mode can be made The propeller should be feathered to reduce drag 3 3 ...

Страница 22: ...chdown all switches OFF Should engine power still be available the selected landing site should be surveyed while airborne to see if obstacles exist After landing Throttle Closed all switches OFF 3 7 Icing Attempt to leave the icing area as soon as possible If necessary change altitude to escape icing layer Continue to move controls to prohibit lockage from ice When the canopy is iced over the wea...

Страница 23: ...tch OFF Circuit breakers PULL OFF The engine will continue to run Land as soon as practical or at the next airfield 3 12 Canopy Jettison Aircraft exiting during flight With engine running Throttle CLOSED Ignition OFF With engine stopped Prop feathered Turn prop feather handle to START Red Canopy locks left and right swing AFT Place both hands above your head against canopy PUSH Release safety harn...

Страница 24: ...r Console Layout 26 4 4 Preflight Inspection 26 27 4 5 Preflight Inspection walk around Guide 28 4 6 Before starting Engine 28 4 7 Starting Engine 29 4 8 Before Take Off check 30 4 9 Take Off and Climb 30 4 10 Cruise 31 4 11 Engine Shut Down and Restart in flight 31 4 12 Soaring 31 4 13 Permitted Aerobatic Maneuvers 32 4 14 Descent and Approach 33 4 16 Engine Shut Down 33 4 1 ...

Страница 25: ...2 1 0 4 Hoffmann Normal procedures H 36 DIMONA Cockpit Layout 4 2 ...

Страница 26: ...lve 7 parking brake 8 Rudder pedal adjustment 9 cabin air l0 cabin heat 11 choke 12 Propeller lever 13 Ignition switch 14 Starter button 15 main switch 4 2 Instrument Console Layout 16 airspeed indicator 17 altimeter 18 climb speed indicator 19 COM AVIONIC 2o cylinder head temp 21 oil temp 22 oil press 23 voltmeter 24 fuel 25 RPM indicator hour meter 4 3 ...

Страница 27: ... of engine controls Engine and engine parts for security and damage Foreign objects in engine compartment Close engine cowling 3 Main Landing Gear CHECK For excessive wear cuts abrasions Wheel fairings for condition and security Tire Pressure 2 1 bar 30 psi 4 Right Wing CHECK Fibre Glass Skin for damage or cracks Ailerons and push pull tubes for security and condition Air Brakes and torque tube fo...

Страница 28: ...racks Excessive play in mounting tugs Rudder connected Remove Pitot tube covert 8 Tailwheel assembly CHECK Fairing for condition Tire pressure 2 1 bar 30 psi 9 Left wing CHECK Perform same check as right wing 10 Fuel Tank Drain CHECK Drain for two seconds Inspect for dirt or water 11 Cockpit CHECK Wing quick disconnects LOCKED Controls for freedom of movement Required documents 12 Latching hook CH...

Страница 29: ...ine 1 Canopy LOCKED 2 Rudder Pedals ADJUSTED 3 Fuel Shutoff Valve OPEN 4 Controls FREE 5 Airbrake Extend Retract 6 Parking Brake ON 7 Prop Control MOVE ONE CYCLE 8 Altimeter SET 9 Master Switch ON 10 Fuel Quantity CHECK 11 Baggage SECURE 12 Seat Harness ON and LOCKED 13 Canopy RECHECK LOCKED 4 6 ...

Страница 30: ...engine starts release starter button Adjust throttle to 1000 RPM When engine is running smoothly close the choke 8 Oil Pressure CHECK Oil pressure should be in Green Range in 10 seconds 9 Voltmeter CHECK for 14 VDC 10 Radio and Nav Equipment ON after Engine runs Allow engine to run for two minutes at 1000 RPM then increase RPM to 1500 until the oil temperature indicates 50 C The 1500 RPM phase can...

Страница 31: ...M 2700 2900 CAUTION If the RPM setting is not obtained repeat steps 5 and 6 If a take off is attempted with the propeller in cruise position a significantly longer take off roll will result 4 9 Take Off and Climb 1 Parking brake release 2 Fuel pump on 3 Line up in Position 4 Trim SET 5 Throttle FULL POWER Not less than 2700 RPM 6 Control Stick Light forward pressure steer with rudder at about 80 k...

Страница 32: ...ent not needed OFF 3 Ignition OFF 4 Propeller control PULL TURN LEFT The propeller is now feathered and the wind milling effect on the engine will cease RESTART 1 Choke with cold engine PULL 2 Ignition ON 3 Propeller Control TURN TO START POSITION The wind milling effect should cause the engine to start Should the speed not produce the wind milling use the starter to effect RPM 4 Throttle IDLE unt...

Страница 33: ...2 1 0 32 Hoffmann 4 H 36 DIMONA Normal Procedures 4 13 Permitted Aerobatic Maneuvers ALL AEROBATIC MANEUVERS INCLUSIVE SPIN AND FLIGHTS IN CLOUDS ARE FORBIDDEN 4 10 ...

Страница 34: ...duce Airbrakes as required Throttle Closed Touchdown Back pressure on stick to produce 3 point attitude CAUTION Do not apply full airbrake at touchdown The coupling with the brake system will result in landing with blocked wheels 4 16 Engine Shut Down Parking Brake As required Throttle Closed idle engine for 2 minutes for cooling Radios and NAV Equipment Off Electrical Switches Off Ignition Off Ma...

Страница 35: ...lly if required Recover Reset controls in neutral position 4 17 2 Characteristics Yaw up to 35 and bank up to 10 are practicable with full rudder and suitable aileron control High yaw angels require extensive elevator deflections up to the rear stop of the stick NOTE Stall is not possible in the slip At rear C G positions nose pitches down slowly Speed after recovery is not less than 80 km h 43 kt...

Страница 36: ...l without assistance NOTE Bank angels above 10 cause a turn in slip direction Airspeeds above 120 km h 65 kt 75 mph cause the same effect CAUTION Due to high rates of descent recover from slip at least 20 m 60 ft above ground level 4 17 3 Indicated Airspeed Errors At yaw angels below 25 indicated airspeed error does not exceed 12 of CAS At higher yaw angels airspeed indication is no longer interpr...

Страница 37: ...Performance Data Table of Contents Section 5 PERFORMANCE DATA Paragraph Page 5 1 Take Off Distances 35 5 2 Landing Distances 36 5 3 Rate of Climb 36 5 4 Cruise Speed 36 5 5 Range 36 5 6 Fuel Consumption 36 5 7 Maximum Altitude 37 5 1 ...

Страница 38: ...il lift off mtr 0 ft 0 m 185 ft 607 196 643 207 679 218 715 250 810 m 191 ft 267 202 663 213 699 224 735 500 1625 m 197 ft 646 208 682 220 722 231 758 750 2438 m 203 ft 666 215 705 227 745 238 781 1000 3250 m 299 ft 686 221 725 234 768 246 807 Take off distance to 0 0 m 305 ft 1001 333 1043 361 1184 389 1276 Clear 15 mtr 50 ft obstacle 250 810 m 320 ft 1050 348 1142 375 1230 403 1322 500 1625 m 33...

Страница 39: ...pm Rate of climb propeller in CRUISE position 120 km h 75 mph IAS 2 0 m s 394 fpm 5 4 Cruise speed At maximum continuous RPM 3000 RPM Straight and Level Flight 190 km h 118 mph 5 5 Range At a cruise speed of 180 km h the range is 960 km with no reserve Wind factor is not considered At a cruise speed of 150 km h at an altitude of 1 500 mtr 5000 ft the range is 1000 km with no reserve Wind factor is...

Страница 40: ...2 1 0 37 Hoffmann 5 H 36 DIMONA Performance Data 5 7 Maximum Altitude Aircraft weight 770 kg ICAO standard atmosphere The DIMONA has demonstrated the ability to climb to5 500 m NN 18 045ft 5 4 ...

Страница 41: ... list Table of contents Section 6 WEIGHT AND BALANCE EQUIPMENT LIST Paragraphs Page 6 1 Empty Weight 39 6 2 Reference Datum Line and CG Limits 39 42 6 3 Weight Report 43 6 4 Minimum Equipment List incl in fleet weight 44 6 5 Additional Equipment list 44 6 1 ...

Страница 42: ...e reweighed to adjust the weight report accordingly After removing or adding equipment a sample weight balance problem should always be performed to insure the CG limits have not been exceeded 6 2 Reference Datum Line RDL and CG Limits The reference datum line RDL is the leading edge of the wing at the wing root rib The aircraft leveling point is the underside of the wing mid chord The CG Limits a...

Страница 43: ...Weight 340 520 176 800 1 Pilot 143 80 11 440 2 Pilot 143 100 14 300 Baggage 834 10 8 340 Fuel 834 57 6 48 038 767 6 258 918 The result of the above problem places the CG at 337 3 mm which is within the allowable range An additional problem may be calculated for example that all the fuel is consumed and the aircraft will continue to fly and land as a glider By removing the 57 6 kg of fuel and the m...

Страница 44: ...6 DIMONA Equipment list 6 2 cont Empty weight CG limits With a min weight of 70 kg 155 lbs in pilot s seat the CG will be within the allowable range if the empty weight CG is within the limits shown below Empty weight CG mm aft of RDL 6 4 ...

Страница 45: ...nce 6 H 36 DIMONA Equipment list 6 2 cont Determination of empty weight CG position Put x1 and x2 with their absolute value in mm into the formula where X L is the empty weight CG position in mm aft of RDL reference datum line 6 5 ...

Страница 46: ...3 Weighing Report Date of weighing carried out by Equipment first used for weigh date Empty weight kg lbs Empty C of G behind datum mm in Empty weight moment Max Payload kg lbs Sign The empty weight momentum is necessary to calculate the CG for flight load table 6 6 ...

Страница 47: ...irspeed indicator 2 Altimeter 3 RPM indicator with hour meter 4 Oil Pressure Indicator 5 Oil Temperature Indicator 6 Cylinder Head Temperature Gauge 7 Fuel Quantity Indicator 8 Voltmeter 9 Standby Compass 10 Two seats restraint harness 11 Loading Plan 12 Data Plate 13 Flight Handbook 6 5 Additional Equipment List Item Arm mm weight kg Moment kg mm 1 2 3 4 5 6 7 8 9 l0 11 6 7 ...

Страница 48: ...djusting handle forward of the control stick and pushing with the feet against the pedals permits forward adjustment To move pedals aft pull handle and let pedals snap into the desired rear position 5 Cockpit Heat Pulling the knob permits heat entry thru the cabin heat duct 6 Choke The choke knob closes butterfly valves in both carburetors thru cables It must not be used to shut down the engine an...

Страница 49: ...canopy push shut with the black grips located on the canopy frame then turn the red levers to lock the canopy To open the canopy reverse the sequence 10 Emergency jettison The red levers are located left and right on the canopy frame use review Emergency Procedures Par 3 12 11 Propeller Control The propeller control lever is on the upper middle console For use review Normal Operations Par 4 8 12 F...

Страница 50: ...aft Handling and Servicing Table of Contents Section 8 AIRCRAFT HANDLING AND SERVICING Paragraph Page 8 1 Aircraft Assembly 48 49 8 2 Aircraft Disassembly 50 8 3 Transporting the Aircraft 50 8 4 Storage 51 8 5 Cleaning the Aircraft 51 8 1 ...

Страница 51: ...rying tube 5 Then walk forward until the wing is 90 from line of flight 6 Rotate the wing until the root ribs are parallel and push wing into fuselage An assistant at the wing trailing edge should observe the smooth insertion of the two shear bolts Let latching hooks snap into links 7 Move the wing tip up and down lightly while the assistant locks the main mounting bolt by pushing up on the mounti...

Страница 52: ...ion Fin above Vertical Fin 2 Raise Elevator slightly and firmly push fin aft against the stop 3 As you push the fin aft guide the elevator drive fork into the elevator lug 4 Lock safety pin FINAL ASSEMBLY 1 Plug in compensation nozzle if desired 2 Apply tape if desired to gap between wing and fuselage CAUTION Check elevator control for proper connection and inspect elevator actuator inserted in dr...

Страница 53: ...cked to insure enough clearance in the trailer 3 The wings do not have to be removed for road transportation The wing remains attached to the fuselage by the telescopic tube When folded the wing should be cushioned by a 400 mm wide profile cushion under the butt rib This will prevent the telescopic tube from damage An additional profile cushion should be placed about 4 in 13 ft outboard of the but...

Страница 54: ...ft should not be placed in open or unprotected storage for long periods of time Dirt insects etc can be removed by washing using warm water and a mild detergent For stubborn spots an automotive paint cleaner can be used For best result the aircraft should be cleaned after the day s flying is ended The lower fuselage surfaces should be inspected for oil and exhaust stains These can be removed with ...

Страница 55: ...2 1 0 52 9 Hoffmann Supplements H 36 DIMONA Table of Contents Section 9 SUPPLEMENTS Paragraph Page 9 1 ...

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