Diamond JAR-VLA Flight Manual Download Page 79

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DIAMOND AIRCRAFT

DA 20/100 Flight Manual

Performance

Doc # 202-100-VLA

20 December, 2000

Page

Issue 1

5 - 4

5.3.2. Figure 5.2: Cruising Performance

Engine power in % of maximum continuous power

55% 65%

Pressure

altitude

Standard

Temp.

Fuel Flow

Ft. M

Rpm

X100

In.Hg

L/hr

Gal/hr

Rpm

X100

In.Hg

L/hr

Gal/hr

0 0 15 59 19 24.7

13.6

3.6 20 25.7

15.6

4.1

2000 600 11 52 19 24.0

14.4 3.8 20 24.7 16.0 4.2

4000 1200  7  45  19  23.3 15.6 4.1  21  23.3 16.8  4.4
6000 1800  3  38  20  22.0 16.8 4.4  22  22.7 19.6  5.2
8000 2400 -1  31  21  21.0 18.0 4.8  22  21.7 21.2  5.6

10000 3000 -5

22 19.7 19.2 5.1 22.6 20.3* 22.4* 5.9*

12000 3600 -8

17 22.6 18.0* 20.4* 5.4*

13000 4000 -11 12 22.6 17.0* 21.5* 5.7*

75% 85%

Pressure

altitude

Standard

Temp.

Fuel Flow

Ft. M

Rpm

X100

In.Hg

L/hr

Gal/hr

Rpm

X100

In.Hg

L/hr

Gal/hr

0 0 15 59 21 27.0

18.0

4.8

22.6

27.7

22.0

5.8

2000 600 11 52 22 25.7

18.4 4.9 22.6 26.7 22.4 5.9

4000 1200 7 45 22.6 24.3 19.6 5.2 22.6 25.7* 25.2* 6.7*
6000 1800 3 38 22.6 23.3 23.2 6.1

8000 2400 -1 31 22.6 22.0*

23.6* 6.2*

Maximum Continuous

Power

Maximum Take-Off Power

Pressure

altitude

Standard

Temp.

Fuel Flow

Ft. M

Rpm

X100

In.Hg

L/hr

Gal/hr

Rpm

X100

In.Hg

L/hr

Gal/hr

0 0 15 59 22.6

28.3

26.0

6.9 23.8

29.7*

30.0 7.9*

2000 600 11 52 22.6

27.7*

26.8*

7.1*

4000 1200 7 45 22.6 25.7*

25.2* 6.7*

6000

1800

Fuel flow is given in US-gal.

Data labelled * give a basis for interpolation. These values may not be attained at the stated altitude.

To maintain constant performance at non standard temperature gradient:

Raise manifold pressure by 0.7 in.Hg at ISA + 18° F (10° C)

Lower manifold pressure by 0.7 in.Hg at ISA - 18° F (10° C)

NOTE

To keep engine wear to a minimum, engine operation below 1900 RPM is not recommended.

Summary of Contents for JAR-VLA

Page 1: ...ed in the aircraft at all times Scope and revision status can be found in the List of Effective Pages and in the Record of Revisions The pages identified as DOT appr in the List of Effective Pages are approved by Signature William Jupp Authority Chief Flight test For Director Aircraft Certification Transport Canada Date of approval 20 December 2000 This airplane is to be operated in compliance wit...

Page 2: ...me to familiarize yourself with your KATANA airplane We ask that you carefully read this Flight Manual and pay special attention to the recommendations given A careful study of the manual will reward you with many hours of trouble free flight operation of your KATANA airplane All rights reserved Reproduction of this manual or any portion thereof by any means without the express written permission ...

Page 3: ...Issue 1 0 3 TABLE OF CONTENTS Chapter GENERAL 1 OPERATING LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL OPERATING PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7 HANDLING PREVENTIVE AND CORRECTIVE MAINTENANCE 8 SUPPLEMENTS 9 ...

Page 4: ...c 2000 1 8 22 Aug 2006 DOT appr 3 18 20 Dec 2000 1 9 09 Mar 2001 1 10 20 Dec 2000 4 DOT appr 4 1 20 Dec 2000 1 11 20 Dec 2000 DOT appr 4 2 20 Dec 2000 1 12 20 Dec 2000 DOT appr 4 3 20 Dec 2000 1 13 20 Dec 2000 DOT appr 4 4 20 Dec 2000 1 14 20 Dec 2000 DOT appr 4 5 20 Dec 2000 DOT appr 4 6 20 Dec 2000 2 DOT appr 2 1 20 Dec 2000 DOT appr 4 7 20 Dec 2000 DOT appr 2 2 20 Dec 2000 DOT appr 4 8 20 Dec 2...

Page 5: ...h 19 2004 9 9 1 20 Dec 2000 DOT appr 5 13 March 19 2004 9 2 20 Dec 2000 DOT appr 5 14 March 19 2004 DOT appr 5 15 March 19 2004 Supp 1 S1 1 20 Dec 2000 S1 2 20 Dec 2000 6 DOT appr 6 1 20 Dec 2000 S1 3 20 Dec 2000 DOT appr 6 2 20 Dec 2000 DOT appr 6 3 20 Dec 2000 DOT appr 6 4 20 Dec 2000 6 5 20 Dec 2000 6 6 20 Dec 2000 DOT appr 6 7 20 Dec 2000 DOT appr 6 8 09 Mar 2001 DOT appr 6 9 09 Mar 2001 DOT a...

Page 6: ......

Page 7: ...DIAMOND AIRCRAFT DA 20 100 Flight Manual Doc DA202 100 VLA 20 December 2000 Page Issue 1 0 7 INTENTIONALLY LEFT BLANK ...

Page 8: ...manual The affected pages of any revision as well as the Record of Revisions must be inserted into the manual upon receipt The pages superseded by the revision must be removed and destroyed The Revision Log should be updated by hand Changes are identified on those pages affected by a revision bar Rev No Date Issued Inserted On Inserted By Issue 1 20 Dec 2000 20 Dec 2000 Diamond Aircraft ...

Page 9: ...ww diamond air at Phone Fax 519 457 4041 519 457 4045 Phone Fax 011 43 2622 26700 011 43 2622 26780 2 Rotax 912 Engine related manuals and publications North America Rotech Research Canada LTD 6235 Okanagan Landing Road Vernon British Columbia Canada V1H 1M5 www rotec com HB FLUGTECHNIK GES M B H Dr Adolf Scharf Str 44 A 4053HAID www rotax bombardier com Phone Fax 250 260 6299 250 260 6269 Phone F...

Page 10: ...plane Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this airplane This Manual includes the material required by JAR VLA including amendment VLA 92 1 It also contains supplemental data supplied by the airplane manufacturer that can be useful to the pilot The Flight Manual conforms to a standard equipped DA 20 100 KATANA An...

Page 11: ...r 516 b FAA Part 36 c LBA LSL Chapter X of 1 01 1991 For others refer to the national type certificate data sheets as applicable 1 3 WARNINGS CAUTIONS AND NOTES The following definitions apply to warnings cautions and notes used in the Flight Manual WARNING means that the non observation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION mean...

Page 12: ...DIAMOND AIRCRAFT DA 20 100 Flight Manual General Doc DA202 100 VLA 9 March 2001 Page Revision 1 1 3 1 4 THREE VIEW DRAWING OF AIRPLANE ...

Page 13: ... 125 sq ft 11 6 m2 Mean Aerodynamic Chord MAC 3 ft 6 9 in 1 09 m Aspect Ratio 10 0 Dihedral 4 nominal Sweep of Leading Edge 1 nominal 1 5 3 Horizontal Stabilizer Angle of Incidence 2 5 0 5 Span 8 ft 8 in 2 65 m 1 5 4 Landing Gear Track 6 ft 3 in 1 90 m Wheel Base 5 ft 9 in 1 75 m Tire Size Nose 4 00 4 TOST 5 00 4 GOODYEAR Main 15 x 6 00 5 GOODYEAR or 5 00 x 5 6 Ply TSO C62 Tire Pressure Nose 26 ps...

Page 14: ...der heads air cooled cylinders Propeller drive via integrated reduction gear Reduction Ratio 2 43 1 Displacement 82 5 cu in 1 352 liters Output Power 100 hp 73 5 kW at 2385 RPM 1 7 PROPELLER Two bladed variable pitch propeller manufactured by HOFFMANN Constant speed hydraulic pitch control model HO V352F 170FQ OR model HO V352F C170FQ Range of Pitch Angle 10 35 Diameter 5 ft 6 9 in 1 70 m ...

Page 15: ...gal 2 liters CAUTION Use of automotive gasoline containing alcohol e g methanol or ethanol other than specified in the above listed specifications is not permitted NOTE Petroleum suppliers provide automotive gasoline of varying volatilities depending on the season and climatic zone Fuels with higher volatility cold weather grade fuels are more susceptible to fuel vapour formation than fuels with l...

Page 16: ...s in the reduction gears a 4 stroke motorcycle oil of a registered brand with gear additives that meets API classification SF or SG are highly recommended The viscosity should be selected according to the various climatic conditions using the following table CAUTION Do not use aviation lubricant When operating with AVGAS100LL fuel do not use synthetic oil Oil Capacity Minimum 3 0 liters 3 2 US qt ...

Page 17: ...ant manufacturer s data for change replacement usage and operation are to be observed a Coolant Capacity Minimum 2 5 US qt 2 4 liters Maximum 2 6 US qt 2 5 liters b Reservoir Capacity Minimum 0 11 US qt 0 1 liters Maximum 0 21 US qt 0 2 liters NOTE The level in the reservoir can be checked using the coolant dipstick Excessive overfilling of the reservoir can result in overflow during operation In ...

Page 18: ... Take off Weight 750 kg 1653 lbs Maximum Landing Weight 750 kg 1653 lbs Empty Weight See Chapter 6 Maximum Weight in Baggage Compartment 20 kg 44 lbs only if restraining devices available Wing Loading At Maximum Take off Weight 64 61 kg m 2 13 23 lbs sq ft Performance Load at Max Take off Weight 7 50 kg hp 16 53 lbs hp ...

Page 19: ...irplane relative to the ground TAS True airspeed Speed of the airplane relative to air TAS is CAS corrected for altitude and temperature errors vA Maneuvering speed Maximum speed at which the airplane is not overstressed at full deflection of control surfaces vFE Maximum speed with flaps extended vNE Speed which must never be exceeded in any operation vNO Maximum structural cruising speed which sh...

Page 20: ...ude Altitude reading with altimeter set to 1013 25 mbar 29 92 inHg air pressure Pressure Altitude Altitude measured at standard pressure at MSL 1013 25 mbar 29 92 inHg using a barometric altimeter Pressure altitude is the indicated altitude corrected for installation and instrument errors Within this manual the instrument errors are assumed to be zero Aerodrome Airport Pressure Actual atmospheric ...

Page 21: ...ane from which all horizontal distances for the center of gravity calculations are measured It is the plane through the leading edge of the wing root rib perpendicular to the longitudinal axis of the airplane Station A defined point along the longitudinal axis which is generally presented as a specific distance from the reference datum Lever Arm The horizontal distance from the reference datum to ...

Page 22: ...ation Unusable Fuel The amount of fuel remaining in the tank which cannot be safely used in flight Empty Weight Weight of the airplane including unusable fuel all operating fluids and maximum oil amount Useful Load The difference between take off weight and empty weight Maximum Take off Weight Maximum weight permissible for take off 1 11 6 Equipment ACL Anti collision light 1 11 7 Miscellaneous GF...

Page 23: ... 14 1 12 CONVERSION FACTORS 1 12 1 Length or Altitude 1 ft 0 3048 m 1 in 25 4 mm 1 12 2 Speed 1 kts 1 852 km h 1 mph 1 609 km h 1 12 3 Pressure 1 hPa 100 N m2 1 mbar 1 in Hg 33 865 hPa 1 psi 68 97 mbar 1 12 4 Weight 1 lbs 0 454 kg 1 12 5 Volume 1 US gallon 3 785 liters 1 Imperial gallon 4 546 liters ...

Page 24: ...ENGER SEATING 2 8 2 12 FLIGHT CREW 2 8 2 13 KINDS OF OPERATION 2 8 2 14 FUEL 2 9 2 15 PLACARDS 2 9 2 16 DEMONSTRATED CROSSWIND COMPONENT 2 17 2 17 TEMPERATURE LIMITS 2 17 2 1 INTRODUCTION Chapter 2 of this Flight Manual comprises the operating limitations instrument markings airspeed indicator markings and the limitation placards which are necessary for the safe operation of the airplane its engin...

Page 25: ...t exceed this speed with flaps extended vNO Maximum Structural Cruising Speed 118 135 218 Do not exceed this speed except in smooth air and then only with caution vNE Never Exceed Speed 161 185 298 Do not exceed this speed in any operation 2 3 AIRSPEED INDICATOR MARKINGS IAS Marking kts mph km h Explanation White Arc 37 81 43 93 69 150 Operating range with extended flaps Green Arc 41 118 47 135 76...

Page 26: ...eller speed For that reason all speed references within this manual contrary to the engine manual are propeller speeds c Engine Operating Limitations Max T O Power 5 min 100 hp 73 5 kW Max Permissible T O RPM 2385 RPM Max Continuous Power 93 hp 69 kW Max Permissible Continuous RPM 2260 RPM d Oil Pressure Minimum Normal 12 psi 8 bar Below 1440 RPM 29 psi 73 psi 2 0 5 0 bar Above 1440 RPM Max in cas...

Page 27: ...cle oil of a registered brand with gear additives that meets or exceedes API classification SF or SG are highly recommended also see Page 1 7 for additional information on the selection of suitable lubricants 2 4 2 Propeller a Propeller Manufacturer Hoffmann Propeller Rosenheim Germany b Propeller Type HO V352F 170FQ OR HO V352F C170FQ c Propeller Diameter 5 ft 6 9 in 1 70 m d Propeller Pitch at 3...

Page 28: ...ter 600 2260 RPM 2260 2385 RPM 2385 RPM Oil Temperature Indicator 122 F 50 C 122 266 F 50 130 C 266 F 130 C Cylinder Head Temperature Indicator 275 F 135 C Oil Pressure Indicator 12 psi 0 8 bar 29 73 psi 2 5 bar ABOVE 1440 RPM 12 29 psi 0 8 2 bar BELOW 1440 RPM 73 102 psi 5 7 bar 102 psi 7 bar Recommended nominal idle speed 950 RPM 2 6 MISCELLANEOUS INSTRUMENT MARKINGS Instrument Red Line Lower Li...

Page 29: ...8 CENTER OF GRAVITY The reference datum RD for the center of gravity CG calculation is tangent to the leading edge of the wing at the root rib This plane is vertical when the fuselage is horizontal Procedures for horizontal alignment as well as particulars with regard to the empty weight center of gravity refer to Chapter 6 Most forward CG all weights 250 mm 9 84 in aft of RD Most rearward CG all ...

Page 30: ... 215 km h Chandelles Entry speed 116 kts 215 km h Steep turns in which the angle of bank does not exceed 60 NOTE Aerobatics are prohibited 2 10 MANEUVERING LOAD FACTORS Table of structural maximum permissible load factors at vA at vNE with fully extended flaps Positive 4 4 4 4 2 0 Negative 2 2 2 2 0 WARNING Exceeding the maximum load factors will result in overstressing of the airplane Simultaneou...

Page 31: ...um Equipment Flight and Navigation Instruments Airspeed Indicator Altimeter Magnetic Compass Minimum Equipment Powerplant Instruments Fuel Quantity Indicator Oil Pressure Indicator Oil Temperature Indicator Manifold Pressure Indicator Cylinder Head Temperature Indicator Tachometer Fuel Pressure Warning Light Voltmeter Ammeter Generator Warning Light Note Additional equipment may be required for co...

Page 32: ... Fuel 0 53 US gal 2 liters 2 15 PLACARDS The following placards must be installed 1 On the instrument panel next to airspeed indicator Effective for all aircraft operated strictly under JAR VLA regulations This airplane is classified as a very light airplane approved for day VFR only in non icing conditions All aerobatic maneuvres including intentional spinning are prohibited See Flight Manual for...

Page 33: ...December 2000 Page DOT Approved 2 10 3 Next to the switches 4 On the flap control 2 On the instrument panel under the airspeed 5 On the dimming switch for trim display flap control and GPS if installed 6 Next to dimming potentiometer for cabin and fuel shut off valve light ...

Page 34: ...0 100 Flight Manual Limitations Doc 202 100 VLA 20 December 2000 Page DOT Approved 2 11 7 On the instrument panel next to the individual circuit breakers Depending on aircraft specific avionic equipment configuration OR OR ...

Page 35: ...Display on top of the instrument panel 15 On the fuel quantity gauge 16 Next to GPS if installed 10 On top the instrument panel within pilot s direct line of vision 11 On DME channeling switch on the RH side of the radio stack optional 12 Above RH air vent on the instrument panel optional 13 Above the OAT indicator 14 Below Microphone jack on LH side of the instrument panel ...

Page 36: ... panel next to the individual knobs 18 On the centre console between throttle and propeller levers 19 On the side of the throttle quadrant next to tension adjustment knob 20 Next to trim switch on the centre console 21 Next to instrument and map light switches on the centre console 22 Next to fuel shut off valve in correct position ...

Page 37: ...14 23 Next to canopy release handles Inside Left partially coloured red Inside Right partially coloured red Outside Left Outside Right 24 Next to ELT if installed to indicate switch position for EBC 102A ELT model for EBC 502 ELT model 25 Next to Headset Jacks on the Back Rest Pilot side LH Co pilot side RH ...

Page 38: ...f baggage compartment 27 On the brake fluid reservoirs rudder pedals 30 On coolant equalizing reservoir 32 Next to fuel filler cap 28 On inside of oil filler door coloured red 29 On oil filler cap 31 On coolant dispatcher vessel Hydraulic Fluid MIL H 5606 DO NOT ADD WATER TO THIS SYSTEM STOP EVANS NPG WATERLESS COOLANT ONLY ...

Page 39: ...age DOT Approved 2 16 33 On fuselage upper skin behind cockpit only if ELT is installed coloured yellow 35 Under each wing and tail skid plate 36 Around Stall Warning Hole in left wing 37 On Nose Landing Gear Strut 38 On Main Landing Gear Strut 34 On fuselage underside belly by left wing ...

Page 40: ...16 DEMONSTRATED CROSSWIND COMPONENT The maximum demonstrated crosswind component is 15 kts 27 km h 2 17 TEMPERATURE LIMITS Limits for outside air temperature and temperature of the structure for the operation of the airplane Maximum T O Temperature 131 F 55 C Structural Temperature limit For Indicator see pg 4 3 ...

Page 41: ... at Full Stop 3 6 3 3 2 Emergency Landing a Emergency Landing with Engine Off 3 7 b Precautionary Landing with Engine Power Available 3 7 3 3 3 Fire a Engine Fire during Start on the Ground 3 9 b Engine Fire during Flight 3 9 c Electrical Fire including Smoke during Flight 3 9 d Electrical Fire including Smoke on the Ground 3 10 e Cabin Fire during Flight 3 10 3 3 4 Icing Unintentional Flight into...

Page 42: ...nd experience of the pilot are essential in rectifying such problems 3 2 AIRSPEEDS DURING EMERGENCY PROCEDURES vIAS kts mph km h Engine failure after take off with flaps in T O position 60 68 110 Manoeuvring Speed 104 120 193 Airspeed for best glide angle Wing Flaps in T O Position 1653 lbs 750 kg 73 84 135 Wing Flaps in T O Position 1322 lbs 600 kg 66 76 121 Precautionary Landing with power and W...

Page 43: ...SUFFICIENT ENGINE POWER 1 Airspeed vIAS 60 kts 68 mph 110 km h 2 Throttle FULL 3 Carburetor Heat ON 4 Choke OFF 5 Fuel Shut off Valve OPEN 6 Ignition Switch BOTH 7 Electric Fuel Pump ON 8 Propeller Speed Control Lever max RPM WARNING If adequate engine performance cannot be restored immediately prepare for an emergency landing If possible land straight ahead avoiding obstacles Shortly before landi...

Page 44: ...nt reduce throttle to minimum required power land as soon as possible II LOSS OF OIL PRESSURE 1 Oil Temperature check 2 If Oil Pressure drops below Green Arc but Oil Temperature is normal land at nearest airfield If Oil Pressure drops below Green Arc and Oil Temperature is rising reduce throttle to minimum required power land as soon as possible Be prepared for engine failure and emergency landing...

Page 45: ...at least 54 kts 62 mph 100 km h the propeller will continue to windmill 1 Airspeed vIAS 70 kts 81 mph 130 km h 2 Wing Flaps T O Position 3 Propeller Speed Control Lever max RPM 4 Fuel Shut off Valve OPEN 5 Ignition Switch BOTH 6 Electric Fuel Pump ON 7 Throttle 3 4 in 2 cm forward If the engine does not start within 10 seconds Cold Start 8 Throttle IDLE 9 Choke ON Pulled 10 Ignition Switch START ...

Page 46: ...ectric Fuel Pump ON 6 Throttle Cold Start Warm Start IDLE 3 4 in 2 cm forward 7 Choke Cold Start Warm Start ON pulled OFF 8 Ignition Switch START NOTE The engine may also be re started by increasing the airspeed by pushing the airplane into a descent and accelerating to approx vIAS 120 kts 138 mph 222 km h A loss of 1000 ft 300 m altitude must be taken into account After successful re start 9 Oil ...

Page 47: ...iving location and intentions 6 Master Switch Battery OFF b Precautionary Landing with Engine Power Available NOTE A precautionary landing would be required if continuing the flight would endanger the aircraft or its occupants Such circumstances could include mechanical defects low fuel quantity or deteriorating weather conditions 1 Search for a suitable place to land Special attention must be giv...

Page 48: ...tches 10 Climb up to 1000 ft AGL if possible 11 Radio Transmit giving location and intentions 12 Final Approach Throttle as required Propeller Speed Control Lever max RPM Carburetor Heat ON Electric Fuel Pump ON Wing Flaps LDG Airspeed vIAS 57 kts 66 mph 106 km h 13 Touch down is to be made with minimum airspeed nose wheel should be kept above ground as long as possible 14 After Touch down Brake a...

Page 49: ...e Airplane immediately b Engine Fire during Flight 1 Fuel Shut off Valve CLOSED 2 Airspeed vIAS 70 kts 81 mph 130 km h 3 Flaps T O 4 Throttle FULL 5 Electric Fuel Pump OFF 6 Cabin Heat CLOSED 7 Perform emergency landing with engine off according to paragraph 3 3 2 c Electrical Fire including Smoke during Flight 1 Master Switch Battery OFF 2 Cabin Air OPEN 3 Fire Extinguisher use only if smoke deve...

Page 50: ...N 7 Avionics Master Switch ON 8 Radio ON 9 Land as soon as possible d Electrical Fire including Smoke on the Ground 1 Master Switch Battery OFF If engine running 2 Throttle IDLE 3 Fuel Shut off Valve CLOSED 4 Ignition Switch OFF 5 Canopy open 6 Fire Extinguisher deploy as required e Cabin Fire during Flight 1 Master Switch Battery OFF 2 Cabin Air OPEN 3 Cabin Heat CLOSED 4 Fire Extinguisher deploy...

Page 51: ...opeller blades observe maximum RPM 5 Cabin Heat OPEN CAUTION In case of icing on the leading edge of the wing the stall speed will increase CAUTION In case of icing on wing leading edge erroneous indicating of the airspeed altimeter rate of climb and stall warning should be expected 3 3 5 Recovery from Unintentional Spin 1 Throttle IDLE 2 Rudder fully applied opposite to direction of spin 3 Contro...

Page 52: ... the side with the defective tire to compensate for change in direction which is to be expected during final rolling 3 Land with wing slightly tipped in the direction of the non defective tire To increase the maneuvrability during rolling the nose wheel should be brought to the ground as soon as possible after touch down 4 To ease the load on the defective tire the aileron should be fully applied ...

Page 53: ... head wind by 2296 ft 0 7 km 3 3 9 Electrical Power Failure a Total Electrical Power Failure 1 Battery Circuit Breaker If tripped reset 2 Master Switch Generator Battery check ON 3 If Unsuccessful Land at nearest suitable airport b Generator Failure GEN Annunciator Illuminated 1 Master Switch Generator Cycle Generator Master Switch OFF ON 2 Generator Circuit Breaker If tripped reset 3 Generator CO...

Page 54: ...d the ammeter is indicating to the left of centre discharge Discontinue any planned flight activity II LOW VOLTAGE INDICATION NEEDLE IN YELLOW ARC DURING FLIGHT 1 All non flight essential electrical consumers Switch OFF 2 If needle is remaining in the yellow arc and the ammeter is indicating to the left of centre discharge Generator Failure Refer to paragraph 3 3 9 b III LOW VOLTAGE INDICATION NEE...

Page 55: ...check all positions of the flap toggle switch flap stops are fail safe modify approach and landing as follows only UP available raise approach speed by 5 kts throttle as required flat approach angle only T O available normal approach speed throttle as required flat approach angle only LDG available normal landing 3 3 11 Starter Failure Starter does not disengage after starting the engine continuou...

Page 56: ...pull avionic master control circuit breaker and land at nearest suitable airport Radio System Operative no reception 1 Microphone Key check for stuck Microphone Key on transceiver display 2 Headphones check deactivate SQUELCH for a few moments if SQUELCH not heard check headset connection Radio System Operative transmitting not possible 1 Selected Frequency check if correct 2 Microphone check if a...

Page 57: ... NOTE Full range of travel is available for elevator but expect forces up to 20 lbs on control stick 3 Land at nearest suitable airport Runaway of Trim 1 Control Stick Grip stick and maintain control of airplane 2 Trim motor circuit breaker Pull circuit breaker 3 Rocker Switch Check if depressed If reason for runaway condition is obvious and has been resolved push in engage circuit breaker NOTE Fu...

Page 58: ... failure Use Flashlight Ref 3 3 9 3 3 15 Tachometer failure Operation at T O 5 minute power 1 Airspeed Do not exceed 110 KIAS Operation at maximum continuous power 1 Propeller Speed Control Lever Ensure lever is at least inch 10mm measured at slot aft of full forward position Engine will now be operating at or below maximum continuous power NOTE With propeller speed control lever at least inch 10m...

Page 59: ... 3 4 4 NORMAL OPERATION CHECKLIST 4 5 4 4 1 Preflight Inspection I In Cabin Check 4 5 II Walk Around Check 4 6 4 4 2 Before Starting Engine 4 9 4 4 3 Starting Engine 4 10 4 4 4 Before Taxiing 4 11 4 4 5 Taxiing 4 11 4 4 6 Before Take off Engine Run up 4 12 4 4 7 Take off 4 13 4 4 8 Climb 4 14 4 4 9 Cruise 4 14 4 4 10 Descent 4 15 4 4 11 Landing Approach 4 15 4 4 12 Balked Landing 4 16 4 4 13 After...

Page 60: ...r lower flight weights vIAS TAKE OFF kts mph km h Climb Speed during normal take off for 15 m 50 ft obstacle 57 66 106 Best Rate of Climb speed at sea level vy Wing Flaps T O 65 75 120 Best Angle of Climb speed at sea level vx Wing Flaps T O 57 66 106 vIAS LANDING kts mph km h Approach speed for normal landing Wing Flaps in landing position 57 66 106 Balked landing climb speed Wing Flaps in landin...

Page 61: ...dicator is visible through the cut out in the seat shell backs ref fig 2 At temperatures below the 55 C 131 F limit the indicator appears all red with a faint indication of 55 C At temperatures exceeding the 55 C 131 F limit the indicator displays a clearly contrasting red 55 C on a black background ref fig 1 NOTE At temperatures approaching the limit the background will progressively darken prior...

Page 62: ...DIAMOND AIRCRAFT DA 20 100 Flight Manual Normal Operating Procedures Doc 202 100 VLA 20 December 2000 Page DOT Approved 4 4 INTENTIONALLY LEFT BLANK ...

Page 63: ...free 10 Throttle free IDLE 11 Propeller Speed Control Lever free max RPM 12 Master Switch Battery ON 13 Warning Lights Gen Fuel Press and Canopy illuminated 14 Fuel Quantity sufficient 15 Engine Gauges Ammeter and Voltmeter check 16 Circuit Breakers pressed in 17 Map Light operational 18 Instrument Lights operational and dimmable 19 Trim NEUTRAL 20 Wing Flaps Indicator and Flap Actuation check ext...

Page 64: ...DIAMOND AIRCRAFT DA 20 100 Flight Manual Normal Operating Procedures Doc 202 100 VLA 20 December 2000 Page DOT Approved 4 6 II Walk Around Check and Visual Inspection ...

Page 65: ...eel Fairing visual inspection c Tire Pressure 33 psi 2 3 bar check d Tire Wheel Brake visual inspection e Wheel Chocks remove 2 Left Wing a Entire Wing visual inspection b Stall Warning check suck on opening c Pitot Static Probe clean holes open d Tie down remove e Taxi and Landing Lights visual inspection f Wing Tip Position Lights and Strobe visual inspection g Aileron Balancing Weight visual in...

Page 66: ... Main Landing Gear a Landing Gear Strut visual inspection b Wheel Fairing visual inspection c Tire Pressure 33 psi 2 3 bar check d Tire Wheel Brake visual inspection e Wheel Chocks remove 7 Nose a Oil check level by using dip stick min max range is indicated by flat area of stick Coolant Level must be between dip stick markings refill if required b Cowling visual inspection c Air Intakes five free...

Page 67: ...DLE 10 Propeller Speed Control Lever max RPM 11 Friction Device of Throttle Quadrant adjust 12 Avionics Master Switch OFF 13 Master Switch Battery Generator ON 14 Generator Warning Light illuminated 15 Fuel Pressure Warning Light illuminated 16 Exterior Lights as required 17 Instrument Panel Lighting as required 18 Canopy Close and Secure 19 Canopy Locking Warning Light OFF NOTE Under certain circ...

Page 68: ...hoke Cold Start Warm Engine ON fully pulled and hold OFF 5 Toe Brakes Hold 6 Propeller Area Clear WARNING Ensure that propeller area is clear 7 Ignition Key START NOTE During extreme cold weather starts hold the choke on until the engine starts to warm up 8 Choke OFF 9 Throttle maximum 1500 RPM 10 Oil Pressure within green range after maximum of 10 seconds CAUTION If Oil Pressure is below 12 psi 0...

Page 69: ...e green arc Increase RPM to achieve or turn OFF non flight essential electrical consumers 5 Warning Lights Gen Fuel Press Canopy push to test 6 Parking Brake release CAUTION Warm up engine to a minimum Oil Temperature of 122 F 50 C at 1100 to 1500 RPM also possible during taxi 4 4 5 Taxiing 1 Brake check 2 Direction Control check 3 Flight Instruments and Avionics check 4 Compass check CAUTION At h...

Page 70: ...nd flight should not be initiated 5 Fuel Shut off Valve check OPEN 6 Fuel Quantity Indicator check 7 Engine Gauges within green range 8 Trim NEUTRAL 9 Controls free 10 Throttle 1700 1800 RPM 11 Propeller Speed Control Lever Cycle 3 times RPM drop 50 250 RPM 12 Ignition Switch Cycle L BOTH R BOTH Max RPM drop 150 RPM Max RPM difference L R 50 RPM Min RPM difference L R none but RPM drop must be not...

Page 71: ...der NOTE In crosswind conditions directional control can be enhanced by using the single wheel brakes Note that using the brakes for directional control increases the take off roll distance 10 Rotate vIAS 51 kts 59 mph 95 km h 11 Climb Speed vIAS 57 kts 66 mph 106 km h CAUTION For the shortest possible take off distance to clear a 15 m 50 ft obstacle Lift off Speed vIAS 54 kts 62 mph 100 km h Clim...

Page 72: ...f climb speed decreases with increasing altitude NOTE Electric fuel pump ON above 13000 ft Speeds vIAS Altitude flaps T O flaps UP feet kts mph km h kts mph km h 0 4000 65 75 120 69 79 128 4000 7000 63 73 117 65 75 120 7000 10000 62 71 115 above 10000 59 68 110 4 4 9 Cruise 1 Throttle as required 2 Propeller Speed Control Lever 1700 2260 RPM NOTE For favorable manifold pressure RPM combinations re...

Page 73: ...arburetor Heat ON NOTE If RPM drops and then rises suspect carburetor icing and leave Carb Heat ON Otherwise turn Carb Heat OFF Wing Flaps UP Airspeed 118 kts 135 mph 218 km h 4 4 11 Landing Approach 1 Seat Belts fastened 2 Electric Fuel Pump ON 3 Lights as required 4 Master Switch Battery Generator check ON 5 Ignition Switch check BOTH 6 Carburetor Heat ON NOTE If RPM drops and then rises suspect...

Page 74: ...should be selected 4 4 12 Balked Landing 1 Propeller Speed Control Lever max RPM 2 Throttle FULL 3 Carburetor Heat OFF 4 Wing Flaps T O 5 Airspeed 57 kts 66 mph 106 km h 4 4 13 After Landing 1 Throttle as required 2 Wing Flaps UP 3 Carburetor Heat OFF 4 Exterior Lights as required 5 Electric Fuel Pump OFF 4 4 14 Engine Shut down 1 Throttle IDLE 2 Parking Brake set 3 ELT Check by listening to 121 5...

Page 75: ... due to hot weather conditions the ignition should be switched on choke pulled and after approximately 3 seconds ignition should be turned off again 4 4 15 Flight in Rain NOTE Flight performance might be reduced especially for the T O distance and the maximum horizontal air speed The influence on flight characteristics of the airplane is negligible Flights through heavy rain should be avoided due ...

Page 76: ...alibration 5 3 5 3 2 Figure 5 2 Cruising Performance 5 4 5 3 3 Figure 5 3 Stall Speeds 5 5 5 3 4 Figure 5 4 Wind Data 5 6 5 3 5 Figure 5 5 Take Off Distances 5 7 5 3 6 Figure 5 6 Climb Performance Service Ceiling 5 9 5 3 7 INTENTIONALLY LEFT BLANK 5 10 5 3 8 Figure 5 8 Cruising Speed True Airspeed 5 11 5 3 9 Figure 5 9 Maximum Flight Duration 5 12 5 3 10 Figure 5 10 Climb Performance during Balked...

Page 77: ...ated procedures are followed and the airplane is in good maintenance condition Note that the flight duration data does not include a fuel reserve The fuel consumption during cruise is based on propeller RPM and manifold pressure settings Some undefined variables such as the operating condition of the engine contamination of the aircrafts surface or turbulence could have influences on flight distan...

Page 78: ...age DOT Approved 5 3 5 3 PERFORMANCE TABLE AND DIAGRAMS 5 3 1 Figure 5 1 Airspeed System Calibration Assumes zero indicator error Example vIAS 93 kts equals vCAS 95 kts 160 110 40 50 60 70 80 90 100 120 130 140 150 40 50 60 70 80 90 100 110 120 130 140 150 160 T O LDG UP VIAS kts VCAS kts ...

Page 79: ...Hg L hr Gal hr Rpm X100 MP In Hg L hr Gal hr 0 0 15 59 21 27 0 18 0 4 8 22 6 27 7 22 0 5 8 2000 600 11 52 22 25 7 18 4 4 9 22 6 26 7 22 4 5 9 4000 1200 7 45 22 6 24 3 19 6 5 2 22 6 25 7 25 2 6 7 6000 1800 3 38 22 6 23 3 23 2 6 1 8000 2400 1 31 22 6 22 0 23 6 6 2 Maximum Continuous Power Maximum Take Off Power Pressure altitude Standard Temp Fuel Flow Fuel Flow Ft M C F Rpm X100 MP In Hg L hr Gal h...

Page 80: ...e Flaps 0 30 45 60 IAS CAS IAS CAS IAS CAS IAS CAS UP 41 50 46 53 55 59 69 70 T O 39 46 44 49 51 54 63 65 LDG 37 44 41 47 49 52 59 62 Stall speeds in mph Bank Angle Flaps 0 30 45 60 IAS CAS IAS CAS IAS CAS IAS CAS UP 47 57 53 62 63 68 79 81 T O 45 52 51 56 59 62 72 75 LDG 43 50 47 54 56 60 68 72 Stall speeds in km h Bank Angle Flaps 0 30 45 60 IAS CAS IAS CAS IAS CAS IAS CAS UP 76 93 85 99 101 109...

Page 81: ...mber 2000 Page DOT Approved 5 6 5 3 4 Figure 5 4 Wind Components Maximum demonstrated crosswind component 15 kts 27 km h Example Wind speed 11 kts 20 km h Angle between wind direction and flight direction 30 Headwind component 9 5 kts 18 km h Crosswind component 5 5 kts 10 km h ...

Page 82: ...ind C om ponent knot O b s tac le H e ig ht fe e t 0 5 1 0 1 5 O b s tac le He ig ht m 0 1 6 3 3 4 9 500 700 900 1100 1300 1500 1700 1900 2100 2300 2500 2700 2900 3100 3300 3500 152 252 352 452 552 652 752 852 952 1052 Takeoff Distance feet m feet m Example Pressure altitude 3000 ft Outside temperature 15 C 59 F Weight 1598 lbs 725 kg Headwind 10 kts Result Take off roll distance 1025ft 312 4 m Ta...

Page 83: ...deep 15 increase in take off roll distance Grass deeper than 10cm 4in 25 increase in take off roll distance On wet soft grass covered runways with grass deeper than 10cm 4in the take off roll distance might be increased by as much as 40 This information is provided for guidance purposes only and has not been demonstrated The dashed lines in the above diagram wind component represent tailwind ...

Page 84: ...5 10 5 0 5 10 15 20 25 30 TEMPERATURE C PRESSURE ALTITUDE FEET 4 5 14 23 32 41 50 59 68 77 86 TEMPERATURE F 0 2000 4000 6000 8000 10000 12000 14000 16000 100 200 300 400 500 600 700 800 900 1000 ROC ft m in 0 5 1 0 1 5 2 0 2 5 3 0 3 6 4 1 4 6 5 1 m sec 1433 lbs 650 kg 1543 lbs 700 kg 1609 lbs 730 kg 1653 lbs 750 kg Standard Temperature Example Pressure Altitude 5000 ft 1524 m OAT 46 F 8 C Weight 1...

Page 85: ...DIAMOND AIRCRAFT DA 20 100 Flight Manual Performance Doc DA202 100 VLA March 19 2004 Page Revision 3 5 10 5 3 7 INTENTIONALLY LEFT BLANK INTENTIONALLY LEFT BLANK ...

Page 86: ...peed TAS calculation at selected power level Flight mass 750 kg 1653 lbs and Flaps UP Temperature F 4 14 32 50 68 86 Temperature C True Airspeed knots Example Pressure altitude 9500 ft Temperature 57 F 14 C power setting 55 Result True airspeed TAS 116 kts 215 km h CAUTION In case of operation without wheel fairings the maximum cruising speed is reduced by approximately 5 ...

Page 87: ...1800 m 6000 ft 1 8 0 0 m 6 0 0 0 f t 1200 m 4000 ft 600 m 2000 ft 0 10 20 30 40 50 60 70 80 0 1 2 3 4 5 6 Flight Time hour no reserve Fuel Quantity litres 0 2 4 6 8 10 12 14 16 18 20 3 4 1 4 1 1 4 2 1 4 3 1 4 4 1 4 5 1 4 Flight Time hour 45 minute reserve Fuel Quantity US Gal 55 75 95 Example Fuel quantity 13 2 US gal 50 liters Pressure Altitude 6000 ft Power Setting 75 Result Possible flight time...

Page 88: ...lbs most forward center of gravity max take off power 0 100 200 300 400 500 600 700 800 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 ROC ft min 0 00 0 51 1 02 1 52 2 03 2 54 3 05 3 56 4 06 ROC m sec Hp ft Hp m Example Pressure altitude 2250 ft 685 m Outside temperature 59 F 15 C Result Climb performance during balked landing 320 ft min 1 63 m sec CAUTION In case of operation without wheel ...

Page 89: ...g Roll Distance ft m 790 241 813 248 837 255 862 263 889 271 916 279 NOTE Poor maintenance condition of the airplane deviation from the given procedures as well as unfavourable outside conditions high temperature rain unfavourable wind conditions including cross wind could increase the landing distance considerably For landings on dry short cut grass covered runways the following corrections must ...

Page 90: ...nce Doc DA202 100 VLA March 19 2004 Page Revision 3 5 15 5 4 NOISE DATA a Noise limit according to FAR 36 Appendix G 75 0 dB A Noise value measured 63 8 dB A b Noise limit according to ICAO Annex 16 Chapter 10 79 1 dB A Noise value measured 71 7 dB A ...

Page 91: ...eighing Report 6 4 6 3 WEIGHT AND BALANCE REPORT 6 5 Figure 6 2 Weight Balance Report 6 6 6 4 FLIGHT WEIGHT AND CENTER OF GRAVITY 6 7 Figure 6 3 Weight Balance Diagram 6 8 Figure 6 4 Calculation of Loading Condition 6 9 Figure 6 5 Permissible Center of Gravity Range and permissible Flight Weight Moment 6 10 6 5 EQUIPMENT LIST 6 11 AIRCRAFT SPECIFIC WEIGHT AND BALANCE DOCUMENTS ENCLOSED AT THE END ...

Page 92: ...ighed in accordance with applicable air regulations Empty weight and the center of gravity are recorded in a Weighing Report and Weight and Balance Report as illustrated in the samples in figure 6 1 and 6 2 The actual report for the aircraft is at the end of this chapter In case of equipment changes the new weight and empty weight CG position must be determined by calculation or by weighing and mu...

Page 93: ...t see figure 6 1 With the airplane correctly positioned a plumb line is dropped from the leading edge of each wing at the root rib to the floor join these two points to determine the reference datum RD From this line use a suspended plumb line aligned with each landing gear to measure the distances DN nose gear DL left main gear and DR right main gear The following formulas apply Empty Weight WT W...

Page 94: ...uding brake fluid lubricant coolant and unusable fuel 3 31 lbs 1 5 kg Equipment List dated Support Gross lbs kg Tare lbs kg Net Weight lbs kg Lever Arm in m Nose WN DN Main Left WL DL Main Right WR DR Empty Weight WT WN WL WR lbs kg Empty Weight Moment M WN x DN WL x DL WR x DR _________________ in lbs m kg Empty Weight CG Position Empty Weight Moment Empty Weight M WT _________________ in m Posit...

Page 95: ... the Weight and Balance Report Each change of the installed equipment as well as each repair affecting the empty weight the CG position of the empty weight or the empty weight moment must be entered in the Weight and Balance Report at the end of this chapter The following Sample Weight and Balance Report figure 6 2 is for reference only Ensure that you are using the latest weight and balance infor...

Page 96: ...end of this chapter Date Description Changes of Weight Actual Signature of Part or Addition Subtraction Empty Weight IN OUT Modification Weight Arm Moment Weight Arm Moment Weight Arm Moment lbs in in lbs lbs in in lbs lbs in in lbs kg m kg m kg m kg m kg m kg m Original Issue Date Registration Aircraft Serial No Model DA20 A1 100 KATANA Aircraft Specific Weight and Balance Report ...

Page 97: ...light weight and the center of gravity as follows 1 The empty weight and the empty weight moment of the airplane should be taken from the weighing report or from the weight balance report and entered into the form Calculation of Loading Condition figure 6 4 in the columns identified with Your DA 20 2 Using the Weight Balance Diagram see figure 6 3 determine the moment for each part to be loaded an...

Page 98: ...Figure 6 3 Weight Balance Diagram Example Pilot and Passenger 380 lbs 172 kg Fuel 19 5 US gal 74 liters 117 lbs 53 kg 6 01 lbs per US gal 0 72 kg per liter Baggage 11lbs 5 kg Result Moment of Pilot and Passenger 2139 in lbs 24 60 kgm Moment of Fuel 3796 in lbs 43 76 kgm Moment of Baggage 357 in lbs 4 12 kgm ...

Page 99: ...0 148 40 2 Pilot and Passenger Lever Arm 0 143 m 5 63 in 380 172 2139 24 60 3 Baggage Lever Arm 0 824 m 32 44 in 11 5 357 4 12 4 Total Weight and Total Moment with empty fuel tank sum of 1 3 1536 697 15376 177 12 5 Usable Fuel Load 6 01 lbs per US gal 0 72 kg per liter Lever Arm 32 44 in 0 824 m 117 53 3796 43 76 6 Total Weight and Total Moment taking fuel into account sum of 4 and 5 1653 750 1917...

Page 100: ... m 1235 1285 1335 1385 1435 1485 1535 1585 1635 12100 13428 14756 16084 17412 18740 20068 21396 22724 24052 25380 Flight Weight lbs 560 585 610 635 660 685 710 735 Flight Weight kg 1653 750 Figure 6 5 Permissible Center of Gravity Range and permissible Flight Weight Moment Permissible Center of Gravity Range mm in Permissable Flight Weight Moment DA 20 Example of page 6 9 Changes during flight due...

Page 101: ...quipment group and a sequential number Abbreviations A Avionics I Instruments M Miscellaneous any equipment other than avionics or instruments Weight and lever arm of the equipment items are shown in the columns Weight and Arm NOTE Additional installation of equipment must be carried out in compliance with the specifications in the Maintenance Manual The columns Weight and Arm show the weight and ...

Page 102: ...tenna King KA91 0 6 0 27 16 0 0 407 A 8 Marker Beacon Antenna King KA26 0 50 0 23 59 0 1 499 A 9 Transponder Antenna Bendix King KA60 0 20 0 09 18 0 0 457 A 10 VHF AM Antenna Comant CI122 0 50 0 23 43 5 1 105 A 11 Audio Panel King KMA24 1 7 0 772 20 5 0 521 A 12 Audio Panel Terra TMA350D 1 7 0 772 20 5 0 521 A 13 Diplexer Comant CI1125 0 25 0 11 18 0 0 457 A 14 Diplexer Comant CI505 0 20 0 09 18 0...

Page 103: ...ng KX125 3 88 1 76 A29 Nav Com 1 King KX155 4 94 2 24 A30 Nav Com 2 King KX155 4 94 2 24 A31 Remote Switch NAT RS16 0 44 0 20 A32 Transponder Bendix King KT76A 3 00 1 36 A33 GPS Garmin GPS150 2 14 0 97 A34 Chronometer Davtron M800B 0 24 0 11 A35 Audio Panel King KA134 TSO d 0 8 0 36 A36 GPS King KLN 35A 2 07 0 94 A37 Emergency Locator Transmitter EBC 502 2 75 1 25 A38 Emergency Locator Transmitter...

Page 104: ... Pressure Indicator Uma 7 100 20 0 29 0 13 16 35 0 415 I9 Oil Pressure Indicator VDO 20 3910 20 03 0 31 0 14 16 35 0 415 I10 Oil Temperature Indicator VDO 20 3910 20 02 0 31 0 14 16 35 0 415 I11 Directional Gyro R C Allen RCA15AK 2 2 45 1 11 16 35 0 415 I12 Artificial Horizon R C Allen RCA26AK 1 2 43 1 10 16 35 0 415 I13 Airspeed Indicator United 8000 0 66 0 30 16 35 0 415 I14 Turn and Slip Indica...

Page 105: ...ng Nose Gear DIAMOND 2 65 1 20 M3 Seat Cushion standard DIAMOND 2 pieces 4 50 2 05 M4 Seat Cushion leather DIAMOND 2 pieces 5 63 2 55 M5 Fire Extinguisher AMEREX A 620 2 25 1 02 M6 Tire 5 00x5 6Ply Main Gear TSOC62 including inner tube 4 51 2 05 M7 Tire 15 x 6 00 5 Main Gear Goodyear including inner tube 7 70 3 49 Not approved for use in all countries check national regulations Refer to the Aircra...

Page 106: ...YSTEMS 7 1 INTRODUCTION 7 2 7 2 AIRFRAME 7 2 7 3 FLIGHT CONTROLS 7 3 7 4 INSTRUMENT PANEL 7 5 7 5 LANDING GEAR SYSTEM 7 7 7 6 SEATS AND SAFETY BELTS 7 8 7 7 BAGGAGE COMPARTMENT 7 8 7 8 CANOPY 7 9 7 9 POWERPLANT 7 10 7 10 FUEL SYSTEM 7 13 7 11 ELECTRICAL SYSTEM 7 14 7 12 PITOT AND STATIC PRESSURE SYSTEMS 7 17 7 13 STALL WARNING 7 17 7 14 AVIONICS 7 18 ...

Page 107: ...ch construction and contain a CFRP spar The ailerons and flaps are made from CFRP and are attached to the wings using aluminum hinges The wing fuselage connection is made with three bolts each The so called A and B bolts are fixed to the fuselage s root rib The A bolt is placed in front of the spar tunnel the B bolt lies near the trailing edge The two main bolts are placed in the middle of the spa...

Page 108: ... circuit breaker panel and can also be triggered manually switch forward nose down 7 3 2 Flaps The flaps are driven by an electric motor The flaps are controlled by a three position flap operating switch on the instrument panel The three positions of the switch correspond to the position of the flaps where the top position of the switch is used during cruise flight When the switch is moved to a di...

Page 109: ...ls forward with your feet while pulling the T grip Backward adjustment Pull pedals backward to desired position by pulling on T grip NOTE After the T grip is released push the pedals forward with your feet until they lock in place 7 3 5 Flight Control Lock A flight control lock P N 20 1000 01 00 is provided with each aircraft and should be installed whenever the aircraft is parked NOTE Failure to ...

Page 110: ...Control Stick s leather boot to expose the Control Stick tube and push the Control Stick forward against the Control Lock 5 Loop the straps around the Control Stick as shown and push forward on the Control Stick 6 Clip the straps into the left and right buckle receptacles located under the instrument panel 7 Adjust the straps as required Straps should be tight to secure the controls properly 8 TO ...

Page 111: ...ob 5 Altimeter 20 Master Switch 35 Oil Temp Ind 48 Choke Knob 6 CDI 21 Ignition Switch 36 Voltmeter 49 Cabin Heat Knob 7 Stall Warning Horn 22 Flap Control 37 Cylinder Head Temp 50 Parking Brake Knob 8 Turn and Bank Ind 23 Compass Card Indicator 51 Power Lever 9 Directional Gyro 24 Trim Indicator 38 Ammeter 52 Propeller RPM Lever 10 Vertical Speed Ind 25 Annunciator Lights 39 Fuel Indicator 53 Lev...

Page 112: ...SYSTEM The landing gear system consists of the two main landing gear wheels mounted to a self spring steel strut and a free castering nose wheel The suspension of the nose wheel is handled by an elastomer package The landing gear wheel fairings are removable During flight operations without wheel fairings partially reduced flight performance must be taken into account see Chapter 5 7 5 1 Wheel Bra...

Page 113: ...to foul the controls The seats are equipped with removable cushions Manually triggered seat type parachutes may be used instead of cushions For automatically triggered parachutes it is possible to install suitable fastening loops on the A bolts under the seats Every seat is equipped with four point safety belt The locking of the safety belt occurs by slipping the lap belt through the shoulder belt...

Page 114: ... locking handles backwards A canopy locking warning light located in the upper center section of the instrument panel indicates the status of the canopy s locking mechanism If the canopy locking warning light is illuminated the canopy is not locked properly In an emergency situation the canopy can be opened from the outside LH side by sliding the locking handle backward and pulling the emergency r...

Page 115: ...tarter is operated by further turning against spring load to the right position START The engine is shut off by the ignition switch Due to the backlash in the reduction gear the propeller can be easily turned approximately 30 by hand Sudden throttle movements should be avoided to prevent impact load in the gearbox 7 9 2 Carburetor Heat Throttle Propeller Pitch Control Lever The Throttle and Propel...

Page 116: ...7 9 5 Propeller Governor Woodward A 210786 7 9 6 Propeller Pitch Adjustment Propeller pitch adjustments are made with the propeller pitch control lever located on the center console throttle quadrant to the right of the throttle Pulling the lever backwards causes a reduction in RPM The governor keeps the selected RPM constant regardless of airspeed or throttle setting If the engine power level sel...

Page 117: ...F OPERATION The process is finished when crankcase air can be heard being forced back to the oil tank The sound will be noticed as a gurgle coming from the oil tank with the oil cap removed The sound verifies that the crankcase has been purged of residual oil Remove the oil dip stick clean and reinsert Let the oil dip stick sit for a few seconds then remove verifying the oil level is in the middle...

Page 118: ...terior of the airplane A finger filter is installed at the bottom of the tank From there the fuel is fed to the electric fuel pump and from there through the middle tunnel to the fuel shut off valve From the fuel shut off valve it is fed to the firewall breach and further to the mechanical fuel pump From there the fuel reaches the distribution manifold and finally the float chambers of both carbur...

Page 119: ...osed engine failure is possible 7 10 2 Tank Drain To drain the tank sump activate the spring loaded drain by pushing the brass tube in with a drain container The brass tube protrudes approx 1 1 6 in 30 mm from the fuselage contour and is located on the left side of the fuselage approximately at the same station as the fuel filler cap 7 10 3 Fuel Pipette A fuel pipette P N 20 1200 02 00 is supplied...

Page 120: ...g light is activated by the voltage regulator monitoring circuit and illuminates when the generator is not charging the battery 7 11 2 Ignition System The engine is provided with two independent ignition systems The two magnetos are independent from the power supply system and are in operation as soon as the propeller RPM is greater than 100 This ensures safe engine operation even in case of an el...

Page 121: ...t is marked numerically from 8 16 volts in divisions of 2 The scale is divided into three colored arcs to indicate the seriousness of the bus condition These arcs are Red for 8 0 11 0 volts Yellow for 11 0 12 5 volts Green for 12 5 16 0 volts Redline at 16 1 volts 7 11 5 Ammeter The ammeter indicates the charging and discharging of the battery It consists of a dial which is marked numerically from...

Page 122: ...ndicator are also protected together by one circuit breaker 7 11 9 Internal Lighting The internal lighting of the DA 20 100 KATANA is provided by a lighting module located aft of the Pilot s head and on the center line of the aircraft Included in this module are two panel illumination lights and one map light The switches for the lights are located on the center console aft of the Trim control swi...

Page 123: ...Use only the factory supplied pitot static probe cover P N G 659 200 with the Remove before Flight flag attached 7 13 STALL WARNING SYSTEM When the airspeed drops below 1 1 times the stall speed a horn sounds in the left instrument panel The horn grows louder as the speed approaches the stall speed The horn is activated by suction on a hose that leads from a hole in the leading edge of the left wi...

Page 124: ... 2 8 1 AIRPLANE INSPECTION PERIODS 8 2 8 1 AIRPLANE ALTERATIONS OR REPAIRS 8 2 8 1 GROUND HANDLING ROAD TRANSPORT 8 1 1 Ground Handling 8 3 8 1 2 Parking 8 4 8 1 3 Mooring 8 4 8 1 4 Jacking 8 4 8 1 5 Road Transport 8 5 8 1 CLEANING AND CARE 8 1 1 Painted Exterior Surfaces 8 6 8 1 2 Canopy 8 6 8 1 3 Propeller 8 7 8 1 4 Engine 8 7 8 1 5 Interior Surfaces Seats and Carpets 8 7 ...

Page 125: ...low a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered 8 2 AIRPLANE INSPECTION PERIOD Inspection intervals are every 100 hrs 200 hrs 1000 hrs and 6000 hrs of flight time The respective maintenance procedure can be found in the Airplane Maintenance Manual 8 3 AIRPLANE ALTERATIONS OR REPAIRS It is essential that the responsible airworthin...

Page 126: ...e moved forward by pushing at the trailing edge of the wing tips II Moving Backward By following a simple procedure it is very easy to move the Katana backward around the ramp This is accomplished by pushing down with one hand on the aft section of the fuselage near the vertical stabilizer to lift the nose wheel while pushing back on the leading edge of the horizontal stabilizer close to its cente...

Page 127: ...e ground or placed in a hangar When parking the airplane the flight controls lock P N 20 1000 01 00 must be installed and pitot static probe cover and stall warning plug should be fitted ref Chapter 7 Aircraft Description Parking in a hangar is recommended 8 4 3 Mooring The tail fin of the airplane has a hole which can be used to tie down the airplane to the ground Tie down rings are also installe...

Page 128: ...o it cannot be damaged in case the fuselage should move b Wings For transportation both wings must be removed from the fuselage To avoid any damage the wings are stored in upright position on the leading edge with the root rib area positioned on an upholstered profiled surface of at least 1 ft 4 in 400 mm width The outside wing area approximately 10 ft 3 m from the root rib area is placed on an up...

Page 129: ...remove Approximately once a year the surface of the airplane should be treated and buffed using a silicon free automotive polish CAUTION DO NOT use any cleaning agents containing silicon based materials 8 5 2 Canopy The DA 20 100 KATANA offers excellent vision through a large plexiglass canopy It is essential that care will be taken while cleaning the canopy as it is easily scratched If scratched ...

Page 130: ...8 5 4 Engine See Operator s Manual for the Rotax 912 aircraft engine 8 5 5 Interior Surfaces Seats and Carpets The interior should be cleaned using a vacuum cleaner All loose items pens bags etc should be properly stored and secured All instruments can be cleaned using a soft dry cloth plastic surfaces should be wiped clean using a damp cloth without any cleaning agents ...

Page 131: ... SUPPLEMENTS 9 2 9 1 GENERAL This Chapter contains information regarding optional equipment which may be installed in your airplane Individual supplements address each optional equipment installation It is only necessary to maintain those supplements which pertain to your specific airplane s configuration ...

Page 132: ...Doc 202 100 VLA 20 December 2000 Page DOT Approved 9 2 9 2 INDEX OF SUPPLEMENTS Supplement No Title Pages Revision 1 Winterization Kit 3 Issue 1 ...

Page 133: ...lement 1 Doc 202 100 VLA 20 December 2000 Page DOT Approved S1 1 CHAPTER 9 SUPPLEMENT 1 WINTERIZATION KIT 1 GENERAL S1 1 2 OPERATING LIMITATIONS S1 2 3 EMERGENCY PROCEDURES S1 2 4 NORMAL PROCEDURES S1 2 5 PERFORMANCE S1 3 6 WEIGHT AND BALANCE S1 3 ...

Page 134: ...olant temperatures 2 OPERATING LIMITATIONS Maximum T O temperature with baffles installed is 10 C 50 F The following placard must be located in two places one immediately forward of the oil cooler inlet the other upon the radiator inlet baffle 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the winterization kit is installed 4 NORMAL PROCEDURES Preflight Inspect...

Page 135: ...nt 1 Doc 202 100 VLA 20 December 2000 Page DOT Approved S1 3 5 PERFORMANCE There is no change in airplane performance when the winterization kit is installed 6 WEIGHT AND BALANCE The effect of the winterization kit on weight and balance is negligible ...

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