DV20 with Rotax 912 S

Transcription

1 AIRPLANE FLIGHT MANUAL DV20 with Rotax 912 S Category of Airworthiness Applicable Airworthiness Requirements Serial No. Registration Date of Issue Document No. : Normal : JAR-VLA including Amendment VLAl92/1 : 20 Aug 1999 : E This manual is part of the airplane DV 20 Katana 100 and must be carried on board 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 "ACG-appr." in the List of Effective Pages are approved by: Signature Authority Stamp Date of approval 12. Okt This airplane is to be operated in compliance with the information and limitations contained herein. DIAMOND INDUSTRIES GMBH N.A. OTTO-STR. 5 A-2700 WR. NEUSTADT AUSTRIA Page O..{)

2 Intra PREFACE Congratulations on your choice of the DV 20 KATANA 100. Safe handling of an airplane increases and ensures your safety and provides you with many hours of enjoyment. For this reason you should take the time to familiarize yourself with your new KATANA 100 airplane. We ask that you carefully read this Airplane Flight Manual and to 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 100 airplane. All rights reserved. Reproduction of this manual or any portion thereof by any means without the express written permission of DIAMOND Austria is prohibited. Copyright by DIAMOND Austria, Wr. Neustadt. Doc. # E 20 Aug 1999 Page 0-1

3 Intro TABLE OF CONTENTS Chapter GENERAL 1 OPERATING LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL OPERATING PROCEDURES 4 PERFORMANCE 5 MASS (WEIGHT) AND BALANCE I EQUIPMENT LIST 6 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7 HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE 8 SUPPLEMENTS 9 I Doc. # E I 20 Aug 1999 Page 0-2

4 Intro LIST OF EFFECTIVE PAGES Chap- Page Date Chap- Page Date ter ter Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Nov 2001 ACG-appr Aug Nov 2001 ACG-appr Aug Nov 2001 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug Aug Aug Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug 1999 ACG-appr Aug Aug Aug Aug 1999 ACG-appr Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug 1999 ACG-appr Aug Aug 1999 ACG-appr Aug Aug 1999 Doc. # E Rev Nov 2001 MSB20-39 Page 0-3

5 Intro Chap- Page Date Chap- Page Date ter ter Aug Aug Aug Aug 1999 ACG-appr Aug Aug Aug Aug Aug Aug Aug Aug Aug 1999 ACG-appr Aug Aug Aug Aug Aug Aug 1999 ACG-appr Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Nov Aug Aug Aug Aug Aug Aug Aug Aug Aug 1999 Doc. # E Rev Nov 2001 MSB20-39 Page 0-4

6 .Diam,.~!'J! Intro RECORD OF REVISIONS Any revisions to the present manual, with the exception of actual weighing data, must be recorded in the following table. Revisions of approved sections must be endorsed by the responsible airworthiness authority. The new or amended text will be indicated by a bold black vertical line in the left hand margin of a revised page. Revision No. and reference will be shown on the bottom of the page. The airplane may only be operated if the Flight Manual is up to date. Rev. Chap- Pages Date of Approval Date of Date Inserted Signature I No. ter Amendment Remarks Approval by Initials &"'HOl~ <>.\\''"- ~ Ihru 0-5 :>,lit. ~~- ~) Authority ~~.. 'l~~\ 1 12 Nov 2001 ~,~,\, ~ No" ZOD( ~ \ ~, / 1h,iNJV> ~""~ Doc. # E Rev Nov 2001 MSB20-39 Page 0-5

7 Oiamond Intra Rev. No. Chapter Pages Date of Approval Date of Date of Signature I Initials Amendment Remarks Approval by Issue Authority Doc. # E 20 Aug 1999 Page 0-6

8 Diamoncl General CHAPTER 1 GENERAL INTRODUCTION CERTIFICATION BASIS WARNINGS, CAUTIONS, AND NOTES THREE-VIEW-DRAWING OF AIRPLANE DIMENSIONS ENGINE PROPELLER FUEL LUBRICANT AND COOLANT MASS (WEIGHT) LIST OF ABBREVIATIONS CONVERSION FACTORS I Doc. # E I 20 Aug

9 General 1.1. INTRODUCTION The Airplane 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 to be furnished to the pilot by JAR-VLA. It also contains supplemental data supplied by the airplane manufacturer which can be useful to the pilot. The Flight Manual conforms to the actual version of the customer's airplane. Any optional equipment installed on request of the customer (COM, NAV, etc.) is not considered. For the operation of optional equipment the Operation Manual of the respective vendor must be used. For permissible accessories refer to the equipment list, Section CERTIFICATION BASIS The basic version of the DV 20 had been approved by the Austrian Federal Office for Civil Aviation (BAZ, now ACG) in accordance with the Joint Aviation Requirements for Very Light Airplane (JAR-VLA), issued April 26, 1990, including Amendment VLN92/1. (Type Certificate No. FZ 1/93). The alteration to the DV 20 KATANA 100, with Rotax 912 S3 engine, has been approved by Austro Control GmbH (ACG) on basis of the JAR-VLA, issue April 26, 1990, according to CRI A-1. Category of Airworthiness Noise Certification Basis : Normal a) FAR 36, Appendix G b) ZLZV 738/ (1) (Austrian requirements) I Doc.# E I 20 Aug

10 General 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 means that the non-observation of the corresponding procedure leads to a minor or to a more or less long term degradation of flight safety. NOTE draws the attention to any special item not directly related to safety but which is important or unusual. Doc. # E I 20 Aug

11 General 1.4. THREE-VIEW-DRAWING OF AIRPLANE 23 ft in. I I ~~~ I I I I /.5 ft. 8.9 in. / I I I I I I 3.2 in 6 ft. 2.8 in. 35 ft. 4.3 in. I Doc. # E I 20 Aug

12 General 1.5. DIMENSIONS OVERALL DIMENSIONS Span without ACL Span with ACL Length Width m (35 ft 4.3 in) m (35 ft 6.7 in) 7.28 m (23 ft 10.6 in) 1.76 m (5 ft 9.3 in) WINGS Airfoil Wing area Mean aerodynamic chord (MAC) Aspect Ratio Dihedral Sweep of Leading Edge Wortmann FX /20 HOAC 11.6 m 2 (124.8 sq.ft.) 1.09 m (3 ft 6.9 in) AILERON Area m 2 (7.08 sq. ft.) FLAPS Area m 2 (13.30 sq.ft.) HORIZONTAL STABILIZER Area Elevator Area Angle of incidence m 2 (18.21 sq.ft.) m 2 (4.75 sq.ft.) 2 VERTICAL STABILIZER Area Rudder Area m 2 (12.21 sq.ft.) m 2 (4.59 sq.ft.) LANDING GEAR Track Wheelbase Nose wheel Main wheel 1.90 m (6 ft 2.8 in) 1.75 m (5 ft 8.9 in) 300*100/ *150/15* I Doc. # E I 20 Aug

13 General 1.6. ENGINE Rotax 912 S3, 4 Cylinder, 4 Stroke-Engine, horizontally opposed, liquid cooled cylinder heads, air-cooled cylinders. Propeller drive via integrated reduction gear. REDUCTION RATIO: DISPLACEMENT: T/O POWER AT: 2.43 : liters (82.5 cu. in.) 73.5 kw (100 HP) 5800 RPM (engine RPM) 1.7. PROPELLER Two-bladed variable pitch propeller, manufactured by HOFFMANN, model HO- V352F/170FQ or model HO-V352F/C170FQ Constant speed, hydraulic pitch control RANGE OF PITCH ANGLE: DIAMETER: m (5 ft 6.9 in) 1.8. FUEL Approved fuel grades: See Chapter 2.4.i TOTAL CAPACITY: USABLE CAPACITY: 79 liters (20.9 US gal.) 77 liters (20.3 US gal.) I Doc. # E I 20 Aug

14 General 1.9. LUBRICANT AND COOLANT LUBRICANT Use only motorcycle oil of a registered brand with gear additives. Use only oil with API-classification "SF" or "SG". CAUTION Do not use aviation lubricant! Due to high stress in the reduction gears, oils with gear additives such as high performance motor cycle oils are required. Because of the incorporated friction clutch, oils with friction modifier additives are unsuitable as this could result in a slipping clutch during normal operation. Heavy duty 4-stroke motor cycle oils meet all the requirements. These oils are usually no mineral oils but semi- or fully-synthetic oils. Oils primarily used for Diesel engines are generally unsuitable due to insufficient hightemperature properties and additives which favour clutch-slipping. CAUTION If the engine is run on AVGAS 100 LL, the following maintenance work is required every 50 hours of operation: oil filter change oil change oil level check Furthermore avoid continuous use of carburetor heat and avoid running engine on idle longer than necessary. Oil Capacity: Minimum Maximum : 2.0 liters (2.1 US qt.) : 3.0 liters (3.2 US qt.) Doc. # E 20 Aug

15 General Oil viscosity should be selected according to the prevailing climatic conditions using the following table. Avoid using single grade oils. climatic 0C,.. OF multi-grade oils conditions 40 J'" tropical 30 temperate f II) I "'t ~ ~ 0 0 II) N N I "'t W W 0 oq. ««~ ~ I U) U) ;: w w 0 Ir! "'t 1-40 ««... U) U) w ~ ~ «w w 0 U) ««U) U) ~o- 0 arctic - ~tj I Doc. # E I 20 Aug

16 General COOLANT Ensure that only automotive antifreeze solution designed for aluminum engines is used (e.g. BASF Glysantin Antikorrosion). CAUTION Use of low quality coolants may result in sediments within the cooling system and partial occlusion of lines, degrading the efficiency of the cooling system. Mixing ratio: SO to 60% antifreeze concentrate with additives against corrosion mixed with 40 to SO% pure water shall be used, or alternatively an equivalently premixed coolant. NOTE If problems are encountered with boiling after engine stop gradually increase the percentage of antifreeze concentrate. At temperatures below -1S C (S OF) a mix1ure of approximately 20% pure water to 80% antifreeze concentrate should be used to attain a very low freezing point. In all cases the mixing ratio has to comply with the manufacturer's recommendations. Coolant Capacity: Minimum Maximum : 2.4 liters (2.S US qt.) : 2.S liters (2.6 US qt.) Equalizing Reservoir Capacity: Minimum Maximum : 0.1 liters (0.11 US qt.) : 0.2 liters (0.21 US qt.) Doc. # E 20 Aug

17 "Diamond ~ General MASS (WEIGHT) Maximum take-off mass (weight) Maximum landing mass (weight) Empty mass (weight) Maximum mass (weight) in baggage compartment Maximum useful load (including fuel) : 730 kg (1609 Ibs) : 730 kg (1609 Ibs) : See Chapter 6 : 20 kg (44 Ibs) : See Chapter 6 WING LOADING At maximum take-off mass (weight) Perfonmance load at max take-off mass (weight) : kg/m2 (3.92 Ibs/sq.ft.) : 9.91 kg/kw (16.1 Ibs/hp) I Doc. # E I 20 Aug

18 General LIST OF ABBREVIATIONS a) Speed CAS: Calibrated airspeed; Indicated speed corrected for installation and instrument errors. CAS is equal to T AS at standard atmospheric conditions at MSL. KCAS: CAS in knots. las: Indicated airspeed as shown on the airspeed indicator. KIAS: las indicated in knots. GS: Ground Speed. Speed of the airplane 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. V FE : Maximum speed with flaps extended. V NE : Speed which must never be exceeded in any operation. VNO: Maximum structural cruising speed which should only be exceeded in calm air. and then only with caution. vs: The power-off stall speed with the airplane in its current configuration. vso: The power-off stall speed with the airplane in landing configuration. vx: Best angle-of-climb speed. Vy: Best rate-of-climb speed. Doc. # E 20 Aug

19 "Diamond ~ A IRCRAFT General b) Meteorological Terms ISA: Intemational Standard Atmosphere at which air is identified as dry gas. The temperature at mean sea level is 15 C (59 OF), the air pressure at sea level is mbar (29.92 inhg), the temperature gradient up to the altitude at which the temperature reaches C (-67.9 OF) is C/m ( F/tt) and 0 C/m (0 F/tt) above. OAT: Outside air temperature. Indicated Pressure Altitude: Altitude reading with altimeter set to mbar (29.92 inhg) air pressure. Pressure Altitude: Altitude measured at standard pressure at MSL ( mbar / 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 Pressure: Actual atmospheric pressure at the aerodrome altitude. Wind: The wind speeds used in the diagrams in this manual should be referred to as headwind or tail wind components of the measured wind. Doc. # E 20 Aug

20 General c) Powerplant Take-off Power: Maximum engine power for take-off. Maximum Continuous Power: Maximum permissible continuous engine output power during flight. d) Flight Performance and Flight Planning Demonstrated crosswind component: The max. speed of the crosswind component at which the maneuverability of the airplane during take-off and landing has been demonstrated during type certification test flights. Service ceiling: The altitude at which the maximum rate of climb is 0.5 m/s (100 ftlmin). e) Mass and Center of Gravity Reference Datum (RD): An imaginary vertical plane 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 the center of gravity (of a component). Moment: The mass (weight) of a component multiplied by its lever arm. Doc. # E 20 Aug

21 General Center of Gravity: Point of equilibrium for the airplane mass. Center of Gravity Arm (CG position): Distance from the reference datum to the CG. It is determined by dividing the total moment (sum of the individual moments) by the total mass (weight). Center of Gravity Limits: The CG range which an airplane with a given mass must be operated within. Usable Fuel: The amount of fuel available for the flight plan calculation. Unusable Fuel: The amount of fuel remaining in the tank, determined in accordance with to the requirements of the certification specifications. Empty Mass (Weight): Mass (Weight) of the airplane including unusable fuel, ali operating fluids and maximum oil amount. Useful Load: The difference between take-off mass (weight) and empty mass (weight). Maximum take-off mass (weight): Maximum mass (weight) permissible for take-off. f) Equipment ACL: Anti Collision Light Doc. # E 20 Aug

22 General CONVERSION FACTORS LENGTH OR ALTITUDE 1 [ft.] = [m] 1 [in.] = 25.4 [mm] SPEED 1 [kts.] = [km/h] 1 [mph] = [km/h] PRESSURE 1 [hpa] = 100 [N/m' ] = 1 [mbar] 1 [in. Hg] = [hpa] 1 [psi] = [mbar] I Doc. # E I 20 Aug

23 Limitations A IRCRAFT CHAPTER 2 OPERATING LIMITATIONS INTRODUCTION AIRSPEED LIMITATIONS AIRSPEED INDICATOR MARKINGS POWERPLANT LIMITATIONS POWERPLANT INSTRUMENT MARKINGS MISCELLANEOUS INSTRUMENT MARKINGS MASS (WEIGHT) CENTER OF GRAVITY PERMISSIBLE MANEUVERS MANEUVERING LOAD FACTORS OPERATING ALTITUDE FLIGHT CREW KINDS OF OPERATION FUEL LIMITATION PLACARDS DEMONSTRATED CROSSWIND COMPONENT Doc. # E I 20 Aug 1999 Page 2-1

24 A IRCRAFT Limitations 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 engine, and standard systems and equipment. The operating limitations in this Chapter and Chapter 9 have been approved by Austro Control GmbH (ACG), the former Federal Office for Civil Aviation (BAZ). WARNING These limitations must be complied with for all operations AIRSPEED LIMITATIONS las Speed kts mph km/h Remarks VA Do not make full or abnupt control Maneuvering speed movement above this speed, because under certain conditions the airplane may be overstressed by full control movement. V FE Do not exceed this speed with flaps Maximum Flap extended Extended speed VNO Do not exceed this speed except in Maximum stnuctural smooth air, and then only with caution cnuisinq speed V NE Do not exceed this speed in any Never exceed operation speed Doc. # E 20 Aug 1999 Page 2-2

25 A IRCRAFT Limitations 2.3. AIRSPEED INDICATOR MARKINGS las Marking kts. mph km/h Explanation White Arc Operating range with extended flaps Green Arc Normal Operating Range Yellow Arc Maneuvers must be conducted with caution and only in smooth air. Red Line Maximum permissible speed for all operating modes Doc. # E 20 Aug 1999 Page 2-3

26 Limitations 2.4. POWER PLANT LIMITATIONS a) Engine manufacturer b) Engine type designation : Bombardier Rotax, Gunskirchen/Austria : NOTE The propeller is driven by the engine via a reduction gear with a ratio of 2.43: 1. The RPM indicator indicates the propeller speed. For that reason, all speed references within this manual - contrary to the engine manual - are propeller speeds. c) Engine Operating Limitations Max TIO power (5 min.) Max. permissible TIO RPM : 73.5 kw 1100 hp : 2385 RPM Max. continuous power Max. permissible continuous RPM : 69 kw 194 hp : 2260 RPM d) Oil Pressure Minimum Normal Maximum Max. in case of cold-start (short-term) : 0.8 bar (12 psi) below 1450 RPM : 2-5 bar (29-73psi) above 1450 RPM : 5.0 bar (73 psi) : 7.0 bar (102 psi) f) Oil Temperature Minimum Maximum : 50 C (122 OF) : 130 C (266 OF) g) Cylinder Head Temperature Maximum : 135 C (275 OF) Doc. # E 20 Aug 1999 Page 2-4

27 Limitations h) Oustside Air Temperature at Starting Engine Maximum : 50 C (122 OF) Minimum :-25 C (-13 F) The engine must be preheated at Outside Air Temperatures below -25 C (-13 F). i) Fuel Specifications: Approved Fuel Grades AVGAS 100LL Automotive Fuel, ROZ minimum 95 octane,leaded or unleaded EN 228 Super EN 228 Super Plus MOGAS according to BAl-Regulation ZI /16-83 j) Oil Grades : Name-Brand Motorcycle Oil (see also Chapter 1-6) k) Propeller Manufacturer : Hoffmann Propeller, Rosenheim/Germany I) Propeller Type : HO-V352F/170FQ HO-V352F/C170FQ m) Propeller Diameter : 1.70 m (5 ft6.9 in) n) Propeller Pitch (at 0.75*R) : 15 _35 0) Propeller Speed Limitations max TIO RPM (max. 5 min.) Max. Continuous RPM : 2385 RPM : 2260 RPM Doc. # E 20 Aug 1999 Page 2-5

28 Limitations 2.5. POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown below: Green Arc Instrument Red Line = Normal Yellow Arc Red Line = Lower Operating = Caution Range = Upper Limit Range Limit Tachometer RPM RPM 2385 RPM Oil temperature 50 C C C indicator (122 OF) ( OF} (266 OF) Cylinder head C temperature (275 OF) indicator Oil Pressure 0.8 bar 2-5 bar bar (12-29 psi) 7 bar Indicator (12 psi) (29-73 psi) 5-7 bar (73-102psit (102 psi) Fuel Quantity Indicator Manifold Pressure Indicator 2.6. MISCELLANEOUS INSTRUMENT MARKINGS [None.] Doc. # E I 20 Aug 1999 Page 2-6

29 Limitations 2.7. MASS (WEIGHT) Maximum permissible take-off mass (weight) Maximum permissible landing mass (weight) Maximum permissible mass (weight) in the baggage compartment Maximum useful load (incl. fuel) Maximum useful load on the left seat Maximum useful load on the right seat : 730 kg (1609 Ibs) : 730 kg (1609 Ibs) : 20 kg (44 Ibs) only permissible with baggage harness : see weighing report (Ch. 6-4 f) : 110 kg (242 Ibs) : 110 kg (242 Ibs) WARNING Exceeding the mass (weight) limitations may lead to overloading of the airplane, as well as degrading of the handling characteristics and flight performance 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 mass center of gravity, refer to Chapter 6. Most forward CG Most rearward CG : 250 mm (9.84 in) aft of RD : 390 mm (15.35 in) aft of RD WARNING Exceeding the center of gravity limitations reduces the maneuverability and stability of the airplane. The procedure used to determine the center of gravity is described in Chapter 6. Doc. # E 20 Aug 1999 Page 2-7

30 Limitations 2.9. APPROVED MANEUVERS This airplane is certified in the Normal Category in accordance with JAR-VLA. Permissible Maneuvers: a) All normal flight maneuvers b) Stalls (except dynamic stalls) c) Lazy Eights Entry speed : 116 kts (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 as well as flight maneuvers with bank angles of more than 60 are prohibited MANEUVERING LOAD FACTORS Table of structural maximum permissible load factors: Positive Negative at VA: at V NE : with fully extended flaps WARNING Any exceeding of the maximum load factors will result in overstressing of the airplane. Simultaneous full deflection of more than one control surface will result in overstressing of the structure, even at speeds below the maneuvering speed. Doc. # E 20 Aug 1999 Page 2-8

31 Limitations OPERATING ALTITUDE The airplane has a maximum demonstrated operating altitude of 4000 meters (13120 ft.) FLIGHT CREW Minimum flight crew: 1 Pilot. Solo flights have to be performed from the left seat only KINDS OF OPERATION Flights are only permissible in accordance with visual flight rules and during day-time (DAY-VFR). Minimum 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 Low-Voltage caution light Generator warning light Control Light for Coolant Quantity FUEL Fuel Capacity Total fuel quantity: : 79 liters (20.9 US gal) Usable Fuel: : 77 liters (20.3 US gal) For approved fuel grades refer to 2.4.i. of this Chapter. Doc. # E 20 Aug 1999 Page 2-9

32 Diamoncl Limitations LIMITATION PLACARDS The following limitation placards must be installed: (a) At the top of the left instrument panel: Maneuvering speed: VA = 104 kts. This airplane is classified as a very light airplane approved for day VFR only. in non-icing conditions. All aerobatjc maneuvers including intentional spinning are prohibited. See Flight Manual for other limitations. I No smoking! (b) In the baggage compartment: Baggage. max. 20 kg (44 Ibs.). only with baggage harness NOTE For further placards refer to the Maintenance Manual, Doc. No DEMONSTRATED CROSSWIND COMPONENT The maximum demonstrated crosswind component is 15 kts. (27 km/h) FURTHER LIMITATIONS Electrical consumers The landing light and the position lights (optional equipment) may only be used during 10 % of the engine operating time. Otherwise, adequate battery charging cannot be guaranteed. Doc. # E I 20 Aug 1999 I Page2-10 I

33 Oiamond Emergency Procedures CHAPTER 3 EMERGENCY PROCEDURES INTRODUCTION AIRSPEEDS DURING EMERGENCY PROCEDURES EMERGENCY PROCEDURES - CHECKLISTS Engine Failures (a) Engine Failure During Take-off Run (b) Engine Failure After Take-off I. Insufficient Engine Power II. Engine Inoperative (c) Engine Failure During Flight I. Engine Running Roughly II. Loss Of Oil Pressure III. Loss Of Fuel Pressure IV. Restarting The Engine With Propeller Windmilling V. Restarting The Engine With Propeller At Full Stop Emergency Landing (a) Emergency Landing With Engine Off (b) Precautionary Landing Fire (a) Fire On Ground (b) Fire During Take-Off (c) Fire In Flight Icing (a) Unintentional Flight Into Icing Area Recovery From Unintentional Spin Landing With Defective Tire On Main Landing Gear Landing With Defec1ive Wheel Brakes Gliding Electrical Power Failure (a) Generator Warning Light Illuminated With Engine Running (b) Low Voltage Caution Light (LoN-Caution Light) Flap System Failure Starter Failure Avionics System Failure Doc. # E 20 Aug 1999 Page 3-1

34 Emergency Procedures 3.1. INTRODUCTION The following chapter contains check-lists as well as descriptions of the recommended procedures in case of an emergency. However, engine failure or other airplane related emergency situations will most likely never occur if the mandatory preflight check and maintenance are performed properly. In the event that an emergency situation does appear, the procedures presented in this manual should be used to rectify such problems. Since it is impossible to present in the Flight Manual all emergency situations which may occur, knowledge of the airplane and experience of the pilot are essential in rectifying such problems AIRSPEEDS DURING EMERGENCY PROCEDURES V IAS kts mph km/h Engine failure after take-off with flaps in T/O position Maneuvering Speed Airspeed for best glide ratio 730 kg (1609 Ibs) (Flaps T/O for all flight masses/weights) 600 kg (1323 Ibs.) Precautionary Landing (with power and flaps in LDG configuration) Emergency landing with engine off (flaps as required) Doc. # E 20 Aug 1999 Page 3-2

35 Emergency Procedures 3.3. EMERGENCY PROCEDURES - CHECKLISTS Engine Failures (a) ENGINE FAILURE DURING TAKE-OFF RUN Throttle Brakes IDLE as required (b) ENGINE FAILURE AFTER TAKE-OFF I. INSUFFICIENT ENGINE POWER Airspeed (V,AS) Throttle Carburetor Heat Choke Fuel Shut-off Valve Ignition Switch Electric Fuel Pump Propeller Speed Control Lever 59 kts. 168 mph kml h FULL OFF OFF OPEN BOTH ON max. RPM WARNING If the engine performance cannot be restored immediately. the airplane should be landed. Shortly before landing: Fuel Shut-off Valve Ignition Switch Master Switch CLOSED OFF OFF Doc. # E 20 Aug 1999 Page 3-3

36 Emergency Procedures II. ENGINE INOPERATIVE Perform emergency landing according to paragraph (c) ENGINE FAILURE DURING FLIGHT I. ENGINE RUNNING ROUGHLY 1. Carburetor Heat 2. Electric Fuel Pump 3. Magnetos 4. Throttle 5. No Improvement ON ON check BOTH at present position reduce throttle to minimum required power, land as soon as possible. II. LOSS OF OIL PRESSURE 1. Oil Temperature 2. If oil pressure drops below green arc but oil temperature is normal If oil pressure drops below green arc and oil temperature is rising check land at nearest airfield reduce throttle to minimum required power; land as soon as possible. Be prepared for engine failure and emergency landing III. LOSS OF FUEL PRESSURE 1. Electric Fuel Pump 2. If Fuel Pressure Warning Light does not extinguish ON Land as soon as possible. Be prepared for engine failure and emergency landing. Doc. # E 20 Aug 1999 Page 3-4

37 Diamoncl Emergency Procedures IV. RESTARTING THE ENGINE WITH PROPELLER WINDMILLING As long as the airspeed (V,AS) is at least 54 kts mph km/h, the propeller will continue to windmill. 1. Airspeed (V,AS) 2. Wing Flaps 3. Propeller Speed Control Lever 4. Electric Fuel Pump 5. Ignition switch 6. Fuel Shut-off Valve 7. Throttle 70 kts mph km/h T/O Position max. RPM ON BOTH OPEN 2 cm (3/4 in) forward If the engine does not start within 10 seconds: Cold Start 8. Throttle 9. Choke 10. Ignition Switch IDLE ON (Pulled) START Doc. # E 20 Aug 1999 Page 3-5

38 Emergency Procedures V. RESTARTING THE ENGINE WITH PROPELLER AT FULL STOP 1. Electric Consumers OFF 2. Master Switch (Battery) ON 3. Propeller Speed Control Lever max. RPM 4. Electric Fuel Pump ON 5. Throttle Cold Start: IDLE Warm Start: 2 cm (3/4 in) forward 6. Choke Cold Start: ON (pulled) Warm Start: OFF 7. 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. 108 kts (124 mph 1200 km/h). A loss of 1000 ft 1300 m altitude must be taken into account. After successful re-start: 8. Oil Pressure 9. Choke 10. Electric Consumers 11. Oil Temperature check OFF ON if required check Doc. # E 20 Aug 1999 Page 3-6

39 Emergency Procedures Emergency Landing (a) EMERGENCY LANDING WITH ENGINE OFF 1. Airspeed (vias) 59 kts. 168 mph km/h (Flaps as required) 2. Fuel Shut-off Valve CLOSED 3. Ignition Switch OFF 4. Master Switch (Battery) OFF (b) PRECAUTIONARY LANDING NOTE Such a landing would only be required if reasonable suspicion of a defect of the airplane or its systems or bad weather raises dou bts that the destination airfield can be reached without endangering the airplane or its occupants Search for a suitable place to land. Special attention must be given to wind direction and obstacles in the approach path Initiate Descent Throttle Trim Wing Flaps (observe permissible speed) as required as required as required Doc. # E 20 Aug 1999 Page 3-7

40 Emergency Procedures 6. Low pass over flight (not below 350 ft 1100 m above ground) over selected landing area to observe any possible obstacles such as cables, fences, ditches, etc. 7. Final Approach. 8. Throttle 9. Propeller Speed Control Lever 10. Carburetor Heat 11. Electric Fuel Pump 12. Wing Flaps 13. Airspeed (VIAS) 14. Touch-down is to be made with minimum airspeed, nose wheel should be kept above ground as long as possible 15. After touch-down: Fuel Shut-off Valve Ignition Switch Master Switch (Battery) as required max RPM ON ON LDG 59 kts 168 mph 1110 kmlh CLOSED OFF OFF NOTE If no suitable level landing area can be found, an up-hill landing should be preferred, if possible. Doc. # E 20 Aug 1999 Page 3-8

41 AJRCRAFT Emergency Procedures Fire (a) FIRE ON GROUND I. ENGINE FIRE AT STARTING ENGINE 1. Fuel Shut-off Valve CLOSED 2. Throttle FULL 3. Master Switch (Battery) OFF 4. Ignition Switch OFF 5. Evacuate Airplane immediately II. ELECTRICAL FIRE INCLUDING SMOKE ON THE GROUND 1. Master Switch OFF If engine is running: 2. Throttle 3. Fuel Shutt-off Valve 4. Ignition Switch 5. Canopy 6. Fire Extinguisher IDLE CLOSED OFF open use as required Doc. # E 20 Aug 1999 Page 3-9

42 Emergency Procedures (b) FIRE DURING TAKE-OFF I. SUFFICIENT RUNWAY LENGTH AVAILABLE FOR STRAIGHT-AHEAD LANDING Throttle Brakes At standstill IDLE use as much braking action as possible - bring airplane to standstill. take further action as in (a) FIRE ON GROUND II. NO SUFFICIENT RUNWAY LENGTH AVAILABLE FOR NORMAL LANDING 1. Look for a suitable field 2. Airspeed (las) 59 kts 168 mph 1110 kmlh 3. Flaps TIO 4. Fuel Shut-off Valve CLOSED 5. Throttle FULL 6. Electric Fuel Pump OFF 7. Cabin heat CLOSED 8. Master Switch (Battery) OFF 9. Perform emergency landing Doc. # E 20 Aug 1999 Page 3-10 I

43 4aDiamond ~ Emergency Procedures (c) FIRE IN FLIGHT I. ENGINE FIRE IN FLIGHT 1. Airspeed (V,AS) 70 kts. /81 mph 1130 kmlh 2. Flaps TIO 3. Fuel Shut-off Valve CLOSED 4. Throttle FULL 5. Electric Fuel Pump OFF 6. Cabin Heat CLOSED 7. Master Switch (Battery) OFF 8. Perform emergency landing II. ELECTRICAL FIRE INCLUDING SMOKE IN FLIGHT Master Switch (Battery) Cabin Heat Cabin Air Fire Extinguisher OFF CLOSED OPEN use only if smoke development continues. CAUTION While fire extinguisher is being used, the cabin must be aerated. In case the fire is extinguished and electric power is required for continuation of the flight: 5. Avionics Master Switch OFF 6. Electric Consumers OFF 7. Master Switch (Battery) ON 8. Avionics Master Switch ON 9. Radio ON 10. Land as soon as possible. Doc. # E 20 Aug 1999 Page 3-11

44 Emergency Procedures II. CABIN FIRE IN FLIGHT 1. Master Switch (Battery) OFF 2. Cabin Air OPEN 3. Cabin Heat CLOSED 4. Fire Extinguisher use as required 5. Land as soon as possible Doc. # E 20 Aug 1999 Page 3-12

45 Emergency Procedures Icing (a) UNINTENTIONAL FLIGHT INTO ICING AREA 1. Leave icing area (through change of altitude or change of flight direction to reach area with higher outside air temperature). 2. Continue to move control surfaces to maintain their movability. 3. Carburetor Heat 4. Increase RPM to avoid icing of propeller blades (observe maximum RPM) 5. Cabin Heat ON OPEN CAUTION In case of icing on the leading edge of the wing, the stall speed may increase. Doc. # E 20 Aug 1999

46 Emergency Procedures Recovery From Unintentional Spin Throttle Rudder Control Stick Rudder Wing Flaps Elevator IDLE fully engaged opposite to direction of spin neutral neutral UP pull cautiously Bring airplane from descent into level flight position. Do not exceed maximum permissible speed (V NE ) NOTE Due to the excellent low-speed- and stability characteristics of the airplane, unintentional spin is unduly to occur during climb, level flight, descent, or during banking as long as the airspeed does not drop below the minimum permissible speed and the center of gravity is within its limits. Doc. # E 20 Aug 1999 Page 3-14

47 Emergency Procedures Landing With Defective Tire On Main Landing Gear 1. Final approach with wing flaps in landing position. 2. Land airplane on the side of runway opposite to 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 maneuverability 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 engaged in the direction of the non-defective tire Landing With Defective Wheel Brakes In general, a landing on grass is recommended in order to reduce the landing roll distance due to the greater friction. After touch-down: Ignition Switch Master Switch (Battery) OFF OFF Doc. # E 20 Aug 1999 Page3-15

48 Emergency Procedures 3.3.S. Gliding 1. Wing Flaps 2. Airspeed at 730 kg (16091bs) at 600 kg (1323 Ibs) 3. Glide ratio 14, which means at 1000 ft I 305m above ground, and with no wind the distance of glide is 4.3 km (2.5 NM). T/O (VIAs) 70 kts/ 81 mph/ 130 km/h (vias) 64 ktsl 73 mphl 118 Km/h NOTE The glide distance from 1000 tt altitude increases for each 10 kts tail wind by 0.6 km (1968 tt). The glide distance from 1000 tt altitude decreases for each 10 kts head wind by 0.7 km (2296 tt) Electrical Power Failure (a) GENERATOR WARNING LIGHT ILLUMINATED WITH ENGINE RUNNING 1. Ammeter If needle on indicator is on lett side of O-marking (-): check Switch off all equipment not required for a safe flight Land on nearest available airfield NOTE With average battery condition, safe operation of the radio and the extending of the landing flaps is possible for at least one hour. Doc. # E 20 Aug 1999

49 "Diamond ""'0/ Emergency Procedures (b) LOW VOLTAGE CAUTION LIGHT (LON-CAUTION LIGHT) This caution light illuminates if the on-board voltage (13.75V) drops below the threshold of 12.5 Volts. Possible reason for voltage drop: - Defective Power Supply - RPM too low - Operation of too many electrical consumers (equipment) I. LON-CAUTION LIGHT ILLUMINATED WHILE AIRPLANE ON GROUND 1. RPM 1200 RPM 2. Landing Lights OFF 3. Position Lights OFF 4. Ammeter check 5. If the LoN-caution light continues to be illuminated, and the ammeter is in the left side field (-) discontinue any planned flight activity. II. LON-CAUTION LIGHT ILLUMINATED IN FLIGHT: 1. Landing Lights 2. Ammeter 3. If the LoN-caution light continues to be illuminated, and the ammeter is in the left side field (-): Defective Generator OFF check Refer to paragraph (a) III. LON-CAUTION LIGHT ILLUMINATED DURING LANDING: 1. After Landing proceed in accordance with paragraph (b)1. Doc. # E 20 Aug 1999 Page 3-171

50 Oiamond Emergency Procedures Flap System Failure Failure of Position Indication or Function visual check of the flap position select airspeed within the range of the white arc marked on the airspeed indicator check all positions of the flap toggle switch (flap stops are fail-safe) adapt approaching procedure to available flap position: only UP available: only TIO available: raise approach speed by 5 kts. throttle as required - flat approach angle normal approach speed throttle as required - flat approach angle only LOG available: - normal landing Starter Failure Starter does not disengage after starting the engine Throttle Ignition Switch IDLE OFF discontinue any planned flight Doc. # E 20 Aug 1999 Page 3-18

51 A IRCRAFT Emergency Procedures Avionics System Failure Radio system operative, no reception: Microphone Key Speaker check for sticking check, deactivate SQUELCH for a few moments, use headsets if available Radio system operative, transmitting not possible: Selected Frequency Microphone check if correct check, if available use different one (headset) Problem cannot be resolved: switch transponder (if available) to "COMM FAILURE" code if required by the situation and permitted by applicable national regulations. Doc. # E 20 Aug 1999 Page 3-19

52 Normal Procedures CHAPTER 4 NORMAL OPERATING PROCEDURES 4.1. INTRODUCTION AIRSPEEDS FOR NORMAL FLIGHT OPERATION [INTENTIONALLY LEFT BLANK] NORMAL OPERATION CHECKLIST Preflight Inspection I. In-Cabin Check 4-5 II. Walk-Around Check Before Starting Engine Starting Engine Before Taxiing Taxiing Before Take-off Take-off Climb Cruise Descent Landing Approach Balked Landing After Landing Engine Shut-down After-Flight Check Flight in Rain 4-18 Doc. # E 20 Aug 1999 Page 4-1

53 Normal Procedures 4.1. INTRODUCTION Chapter 4 provides checklists and procedures for the normal operation. For normal procedures and supplementary information associated with optional systems refer to Chapter AIRSPEEDS FOR NORMAL FLIGHT OPERATION Unless stated otherwise, the following table contains the applicable airspeeds for maximum take-off and landing mass (weight). The airspeeds may also be used for lower flight masses. V IAS TAKE-OFF kts mph kmlh Climb Speed du ring normal take-off for 15 m (50 tt) obstacle Best Rate-of-Climb speed at sea level v, (flaps T/O) Best Angle-of-Climb speed at sea level v, (flaps T/O) LANDING kts mph kml h Approach speed for normal landing. Flaps in landing position Minimum speed for balked landing. Flaps in take-off or landing Maximum demonstrated crosswind speed during take-off and landing V IAS CRUISE kts mph kml h Maximum permissible speed in rough air v NO Maximum permissible speed with full control surface deflections Maximum permissible speed with wing flaps extended v Fe V IAS Doc. # E 20 Aug 1999 Page 4-2

54 Normal Procedures INTENTIONALLY LEFT BLANK Doc. # E 20 Aug 1999 Page 4-3

55 Normal Procedures INTENTIONALLY LEFT BLANK Doc. # E 20 Aug 1999 Page 4-4

56 Normal Procedures 4.4. NORMAL OPERATION CHECKLIST PREFLIGHT INSPECTION I. (a) (b) (c) (d) (e) (f) (g) (h) In-Cabin Check Airplane Documents Check List Parking Brake Ignition Key Canopy Circuit Breakers Master Switch (Battery) Control Light for Coolant Quantity check present set removed clean, undamaged pressed in ON illuminates for about 3 seconds and terminates illumination if the quantity of coolant in the dispatcher vessel is sufficient NOTE In case the control light for coolant quantity does not terminate illumination, coolant in the dispatcher vessel (on top of the engine) has to be replenished. The upper cowling has to be removed to gain access to the dispatcher vessel. WARNING When closing the dispatcher vessel push down the pressure cap firmly in order to allow it to be held by its safety catch. Verify dispatcher vessel is securely closed! (i) G> (k) (I) (m) (n) (0) (p) (q) Fuel Quantity Master Switch (Battery) Throttle Propeller Speed Control Lever Carburetor Heat Foreign Object Inspection Emergency Locator Transmitter (EL T) Main Bolts (see page 7-2) Baggage sufficient OFF IDLE max RPM OFF done AUTO secured stowed, baggage hamess attached Doc. # E 20 Aug 1999 Page 4-5

57 "Diamond ~ Normal Procedures II. WALK AROUND CHECK AND VISUAL INSPECTION I 1 I G) CAUTION Visual Inspection is defined as check for defects, cracks, delaminations, excessive play, insecure or improper mounting; inspection of general condition. verification of freedom of movement of control surfaces. Doc. # E 20 Aug 1999 Page 4-6

58 Normal Procedures 1. Left Main Landing Gear a) Landing Gear Strut visual inspection b) Wheel Fairing visual inspection c) Tire Pressure (2.3 bar 133 psi) check d) Tire, Wheel, Brake visual inspection e) Skid Marks visual inspection 2. Left Wing a) Entire Wing visual inspection b) Stall Warning check (suck on opening) c) Pitot-Static Probe clean, hole open d) Wing Tip, Balancing Mass visual inspection e) Position Light visual inspection f) Mooring Harness on Wing Tip release g) Aileron visual inspection h) Wing Flap visual inspection 3. Fuselage a) Skin visual inspection b) Tank Vent check c) Tank drain drain water d) Fuel Quantity check with fuel pipette 4. Empennage a) Fins and control surfaces visual inspection b) Mooring Harness on Tail Fin release c) Trim Tab visual inspection Doc. # E 20 Aug 1999 Page 4-7

59 A IRCRAFT Normal Procedures 5. Right Wing a) Entire Wing visual inspection b) Wing Flap visual inspection c) Aileron visual inspection d) Mooring Hamess on Wing Tip release e) Wing Tip, Balancing Mass visual inspection f) Position Light visual inspection 6. Right Main Landing Gear a) Landing Gear Strut visual inspection b) Wheel Fairing visual inspection c) Tire Pressure (2.3 bar I 33 psi) check d) Tire, Wheel, Brake visual inspection e) Skid Marks visual inspection Doc. # E 20 Aug 1999 Page 4-8

60 "Diamond ~ Normal Procedures 7. Nose WARNING Carry out pre-flight checks on the cold or luke warm engine only! Otherwise there are Risks of burnings and scaldsl WARNING Befor cranking propeller by hand: Turn Ignition OFF and anchor the aircraft. Have cockpit occupied by a cornpetent person. NOTE Prior to the oil check turn propeller by hand several times to pump oil from the engine into the oil tank; the process is completed if air is being pumped into the oil tank - a hissing noise can be heard from the open oil tank. a) - Oil check level by using dip-stick NOTE Consumption of oil and coolant is very low under normal operating conditions. Therefore topping up is necessary and senseful only if the quantities are below the minimum markings of oil dip-stick or coolant equalizing reservoir. - Level of coolant in equalizing reservoir Level must be between dip-stick b) Cowling c) Air Intakes (six) d) Propeller Ground Clearance minimum: e) Spinner f) Nose Gear g) Tire and Wheel h) Wheel Fairing i) Tire Pressure (1.8 bar 126 psi) markings, refill coolant if needed visual inspection free visual inspection approx. 25 cm (10 in). visual inspection visual inspection visual inspection visual inspection check Doc. # E 20 Aug 1999 Page 4-9

61 Normal Procedures BEFORE STARTING ENGINE Preflight Inspection Pedals Safety Belts Canopy Parking Brake Controls Fuel Shut-off Valve Trim Throttle Prop. Speed Control Lever Carburetor Heat Friction Device of Throttle Quadrant Avionics Master Switch Master Switch (Battery) Generator Warning Light Low Voltage Caution Light Fuel Pressure Warning Light performed adjust, lock fasten close and secure set FREE in Movement OPEN NEUTRAL free, IDLE free, max RPM free, OFF Adjust OFF ON Illuminated Illuminated Illuminated NOTE Under certain circumstances, activation of the fuel pressure waming light might take as long as 10 minutes after shutting down the engine or switching off the electric fuel pump. Doc. # E 20 Aug 1999

62 Normal Procedures STARTING ENGINE Electric Fuel Pump ON (noise of pump audible) Fuel Pressure Warning Light OFF Throttle - Cold Start IDLE - Warm Engine approximately 2 cm (3/4 in) forward Choke - Cold Start ON, fully pulled - Warm Engine OFF WARNING Ensure people are clear of the propeller danger zone! Ignition Key Throttle Oil Pressure START maximum 1500 RPM within green range after maximum of 10 seconds CAUTION If oil pressure is below 0.8 bar (12 psi) shut down engine immediately! (10 seconds maximum delay) Generator Warning Light Low Voltage Caution Light Electric Fuel Pump Fuel Pressure Waming Light Electric Fuel Pump OFF OFF OFF Shall not illuminate (wait for 10 sec.) ( = check if main fuel pump keeps up pressure) ON Doc. # E 20 Aug 1999 I Page 4-11

63 Normal Procedures BEFORE TAXIING Electric Consumers Powerplant Instruments W ing Flaps (Indicator- and Flap Actuation) Avionics Master Switch Flight Instruments and Avionics Parking Brake ON as required check check. extend and retract fully ON set release CAUTION Warm-up engine to a minimum oil temperature of 50 C (122 OF) at 1000 to 1400 RPM (also possible during taxiing) TAXIING Brake Direction Control Flight Instruments and Avionics check check check Doc. # E 20 Aug 1999

64 .Oia'"9!!!! Normal Procedures BEFORE T AKE-OFF 1. Parking Brake set 2. Safety Hamesses fastened 3. Canopy closed and locked 4. Fuel Shut-off Valve check, OPEN 5. Powerplant Instruments within green range 6, Fuel Quantity Indicator check 7, Wing Flaps TIO 8, Trim NEUTRAL 9, Controls free 10, Throttle 1700 RPM 11, Propeller Speed Control Lever Pull completely 3 times RPM drop: RPM 12, Ignition Switch L-BOTH-R-BOTH Max RPM drop on one magneto: 150 RPM Max difference (UR): 50 RPM 13, Carburetor Heat OFF - ON RPM drop: 30 RPM ; OFF 14, Throttle FULL for 5 sec" check RPM: 2300 ± 80 RPM back to IDLE; 15, Parking Brake release Doc, # 4,01,20-E 20 Aug 1999

65 Normal Procedures TAKE-OFF Electric Fuel Pump Propeller Speed Control Lever Throttle Elevator - at beginning of rolling Control direction check, ON max. RPM FULL (2300 ± 80 RPM) NEUTRAL using rudder 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. VIAS 6. Lift Nose wheel 51 kts. 59 mph 95 km/h 7. Climb Speed 65 kts. 75 mph 120 km/h CAUTION For the shortest possible take-off distance to clear a 15 m (50 ft) obstacle: Liftoff speed 57 kts 165 mph km/h. Climb Speed 58 kts 167 mph km/h Prop. Speed Control Lever Electric Fuel Pump 2260 RPM (after reaching a safe altitude) OFF NOTE In order to avoid excessive noise, the prop speed should be reduced to 2260 RPM as soon as a safe flight altitude has been reached. Doc. # E 20 Aug 1999

66 A IRCRAFT Normal Procedures CLIMB Propeller speed control lever Throttle Powerplant Instruments Flaps Airspeed 2260 RPM FULL Within green range T/O (UP) 65 kts I 75 mph I 120 km/h NOTE The best rate of climb speed decreases with increasing altitude. Flaps T/O (Flaps UP) kts mph km/h Kts mph km/h ft ft ft ft Trim Adjust CRUISE Wing flaps Throttle Propeller Speed Control Lever UP as required RPM NOTE For favorable manifold pressure/rpm combinations refer to Chapter Trim as required CAUTION Max operating time of position lights: 50 % of flight time. Doc. # E 20 Aug 1999

67 Normal Procedures DESCENT 1. Altimeter Adjust 2. Throttle as required 3. Prop Speed Control Lever RPM 4. Carburetor Heat as required CAUTION To achieve a fast descent: Prop Speed Control Lever Throttle Carburetor Heat Wing Flaps Airspeed 2260 RPM IDLE ON UP 117 kts.l135 mph/217 km/h LANDING APPROACH Airspeed Wing Flaps Trim Throttle Prop Speed Control Lever Carburetor Heat Electric Fuel Pump Wing Flaps Approach Speed max. 81 kts 193 mph I 150 km/h TIO as required as required maximum RPM ON ON LOG 60 kts 168 mph 1110 km/h CAUTION Maximum operating time of landing light: 10 % of flying time, but no longer than 5 minutes. NOTE Under conditions such as strong headwind, danger of wind-shear or turbulence, a higher approach speed should be selected. Doc. # E 20 Aug 1999

68 A IRCRAFT Normal Procedures BALKED LANDING Prop Speed Control Lever Throttle Carburetor Heat W ing Flaps Airspeed max RPM FULL OFF T/O, set with caution 58 kts I 67 mph I 108 km/h AFTER LANDING Throttle Wing Flaps Carburetor Heat Landing Light IDLE UP OFF OFF ENGINE SHUT-DOWN Throttle Parking Brake Electric Fuel Pump Avionics Master Switch Ignition Switch Master Switch (Battery) IDLE set OFF OFF OFF OFF NOTE In case of post ignition due to hot weather conditions and the use of MOGAS, the ignition should be switched on, choke pulled and after approximately 3 seconds, ignition should be tumed off again. Doc. # E 20 Aug 1999

69 Normal Procedures AFTER-FLIGHT CHECK 1. ElT check if triggered 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 to the reduced visibility. Doc. # E 20 Aug 1999

70 DiainJ!c':.'!! Performance CHAPTERS PERFORMANCE INTRODUCTION USE OF PERFORMANCE TABLES AND DIAGRAMS PERFORMANCE TABLES AND DIAGRAMS Figure 5.1: Airspeed Calibration Figure 5.2: Cruising Performance Figure 5.3: Pressure Altitude - Density Altitude Figure 5.4: Stall Speeds Figure 5.5: Wind Data Figure 5.6: Take-Off Distances Figure 5.7: Climb Performance I Cruising Altitudes [Intentionally left blank.] Figure 5.9: Cruising Speed (True Airspeed) Figure 5.10: Maximum Flight Duration Figure 5.11 : Climb performance during Balked Landing Landing Distances Doc. # E 20 Aug 1999 Page 5-1

71 Diain 9l!!! Performance 5.1. INTRODUCTION The performance tables and diagrams on the following pages have been prepared to illustrate the performance you may expect from your airplane as well as to enable you to conduct precise flight planning. The data presented in these tables and diagrams has been derived from testflights using an airplane and engine in good operating condition, and was corrected to standard atmospheric conditions (las = 15 C (59 OF) and mbar (29.92 in. Hg) at sea level). The performance tables do not take into account the expertise of the pilot or the maintenance condition of the airplane. The performance illustrated in the tables can be achieved if the indicated procedures are followed and the airplane is in good maintenance condition. Note that the range and flight duration data in each diagram includes a 30 minute fuel reserve for the indicated power level. 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, or turbulence could have influences on flight distance and flight duration. For this reason, it is of utmost importance that all available data is used when calculating the required amount of fuel for a flight. For flight operation without wheel fairings the resulting performance variations is given in % USE OF PERFORMANCE TABLES AND DIAGRAMS The performance data is shown in the form of tables and diagrams to illustrate the influence of the different variables. These tables contain sufficiently detailed information to plan any flight with the necessary precision and safety on the conservative side. Doc. # E 20 Aug 1999 Page 5-2

72 .DiainJ!c'!!! Performance 5.3. PERFORMANCE TABLES AND DIAGRAMS FIGURE 5.1: Airspeed Indicator System Calibration (assuming zero instrument error) 150." ~ "' en ('j 90.0 > / / / t;/'/, /. ~ UP - / / 87 k ' TfO. LOG ~. [.. V V [7 / // /.:/ / // o M I,. / o III o '" o '" V,AS [kts.] Example: V,AS = 93 kts. equals V eas = 95 kts. 1 Doc. # Aug 1999 Page 5-3

73 Diainond Performance FIGURE 5. 2'. Cruisina Performance Engine power in % of max. continuous power. Pressure Standard 55% 65 % 75 % Altitude Temp. RPM MP Fuel Flow RPM MP Fuel Flow RPM MP Fuel Flow ft. m "C OF 1>100 in. Hg. Vh gallhr 1*100 in. Hg I/h. gallhr 1*100 in. Hg I/h IgaIhlf ' 23.6' 6.2' ' 22.4' 5.9' " 20.4' 5.4' 85 % 95% 105 % Pressure.. Standard Altitude Temp. RPM MP Fuel Flow RPM MP Fuel Flow RPM MP Fuel Flow ft. m C OF 1*100 in. Hg I/h galjhr 1*100 in. Hg Uh gallhr 100 in. Hg IIh gaiiilt ' 30.0' 7.9' ' 26.8' 7.1' ' 25.2' 6.7' Fuel flow is given in US-gal. Data labelled ' give a basis for interpolation. Eventually, values may not be reached at the stated altitude. Correction of chart under non-standard conditions: At ISA + 15 C (ISA + 2]0 F) engine power in % of max. continuous power is approximately 5% lower than given. Fuel consumption is approx. 3% lower than given At ISA - 15 C (ISA - 27 F) engine power in % of max. continuous power is approximately 5% higher than given. Fuel consumption is approx. 3% higher than given. See also Notes on the following page. Doc. # E 20 Aug 1999 Page 5-4

74 Performance NOTE The above chart shows the combinations of RPM and MP which result in the lowest fuel consumption at a selected power and altitude. In general it is recommendable for a fast cruise to select 2200 RPM and an MP that is at least 0.7 inhg below the maximum possible MP at the respective cruising altitude. This measure reduces fuel consumption significantly while hardly affecting the cruising speed. For an economical cruise, it is recommendable to select a propeller speed between 2100 and 1900 RPM and an MP that is 1-2 inhg below the maximum possible MP at the respective cruising altitude. NOTE To keep engine wear to a minimum, engine operation below 1700 RPM is not recommended. Doc. # E 20 Aug 1999 Page 5-5

75 Performance FIGURE 5.3: Pressure Altitude - Density Altitude Conversion from Pressure Altitude to Density Altitude E 5000 ~ w w 0 0 ~ I. 500 :J I <{ <{ ~ 4000 W ~ :J :J en ~ fz 3 SO 0 w ~ ~ ~<.p'. ; ~ ~ 0 --' 6000 't, ~ 4000 ~. C- t 000 ~ r ,, Tempe-.. tur C '",.20 ~ w 0 :J I-- 5 <{ E w 0 :J I-- 5 <{ >- >- I-- I-- iii iii z z w w sao :::: " 2 000, I do Example: 1. Set Altimeter to mbar (29.9 inhg) and read the pressure altitude (900 ft.) 2. Determine outside air temperature (+21 C 170 OF) 3. Read density altitude (1800 ft.) Result The effective altitude with respect to performance is 1800 ft. 1 Doc. # ,,1 20 Aug 1999 Page 5-6

76 Performance FIGURE 5.4: Stall Speeds Configuration: Idle, most forward center of gravity, max. mass (weight) (this is the most adverse configuration) Stall speeds in km/h " 'BankAngle. Flaps oa «30 " I,ee 45". las CAS las CAS las CAS UP "., ," TIC LOG. " I ",. 60 las CAS Stall speeds in kts. F FI!1ps l Ban!tAngle 0" '''", 30C' A5",. I '. las CAS las CAS las CAS UP , -- TfO ' LOG. ' 'i'"., 60 0, " las CAS Doc. # E 20 Aug 1999 Page 5-7

77 Performance FIGURE 5.5: Wind Components Demonstrated crosswind component: FLIGHT DIRECTION t 20 o 10' 15 kts. (27 km/h) VI ~ o f Z l!j Z o ~5 o u o z ~ 0 L1i :r: 5 f- ~...J 0 z ~ (/) (/) 0 c:: u 1/0' o ' 10' Example: In. Wind speed: 170'160150' ' o CROSSWIND COMPONENT kts I I I o 10 20kM/h 30 Angle between wind direction and flight direction: Headwind component: Crosswind component: kts (20 km/h) kts (18 km/h) 5.5 kts (10 km/h) I Doc. # Aug 1999 Page 5-8