AIRPLANE FLIGHT MANUAL for the Powered Sailplane HK 36 TC with ROTAX 912 S Engine

7-14 09 Jan 2002 7- 15 09 Jan 2002 7- 16 09 Jan 2002 7-17 09 Jan 2002 7-1 8 09 Jan 2002 7-1 9 09 Jan 2002 7-20 09 Jan 2002 7-21 09 Jan 2002 8-1 09 Jan 2002 8-2 09 Jan 2002 8 8-3 09 Jan 2002 9-1 09 Jan 2002 9-2 09 Jan 2002 9-3 09 Jan 2002 9 I Page 0 - 5 I 09 Jan 2002 I Doc . No. 3.01 .12 -E 1__R_e_v_._o ---l.... _ HK 36 TC-100 AFM • DiamondAIR CRAFT Introduction 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) 1 OPERATING LIMITATIONS (an approved chapter) 2 EMERGENCY PROCEDURES (an approved chapter) " . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 NORMAL PROCEDURES (an approved chapter) 4 PERFO RMAN CE (a partly app roved chapter) 5 MASS (W EIGHT) AND BALANCE (a non -approved chapter) 6 POWERED SAILPLANE AND SYSTEMS DESCRIPTION (a non-approved chapter) 7 POWERED SAILPLANE HA NDLI NG , CARE AND MAINTE NANCE (a non-approved chapter) 8 SUPP LEMENTS (a partly approved chapter) 9 09 Jan 2002I Doc . No . 3.01.12-E 1__R_e_v_ .o 1 pageo-s i HK 36 TC -100 AFM General CHAPTER 1 GENERAL Page 1.1 INTRODUCT ION . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . 1-2 1.2 CERTIFI CATI ON BASIS 1-2 1.3 W ARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . . .. 1-3 1.4 EXPLANATIO NS AND ABBR EVIATIONS 1-4 1.5 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 1-6 1.6 DESCRIPT IVE DATA 1-7 1.7 THREE- VIEW DRAWI NGS 1-8 09 Jan 2002 ___.1..--- [ Page 1 -1 II Doc. No. 3.01.12-E I Rev. 0 HK 36 TC-100 AFM General 1.1 INTRODUCTION This Powered Sailplane Airplane Flight Manual has been prepared to pro vide pilots and instructors with all the information that is necessary for the safe and efficient ope ration of the powered sailplane. Th is manual includes the material requ ired to be furnished to the pilot by JAR-22 . It also conta ins supplementary data supplied by the powered sailplane manufacturer. Th is Flight Manual conforms to the current version of the customer's airplane. How- ever , any optional equipment (COM, NAV, etc.) is not considered. For their operat ion, the operation manuals of the respective manufacturers must be followed . Th is must always be kept onboard the airplane. 1.2 CERTIFICATION BASIS The HK 36 TC powered sailplane with Rotax 912 S engine has been type certified by Austro Control GmbH (ACG) in accordance with Change 5 of JAR-22 for sailplanes and powered sailplanes as a derivative of the HK 36 TC. The Type Certificate Data Sheet No. SF 3/82 has been amended . Category of Airworthiness: Utility. 09 Jan 2002 Rev. 0 ___.1....--- , Page 1 - 2 II Doc. No. 3.01.12-E I HK 36 TC-100 AFM • DiamondAIRCRAFT General 1.3 WARNINGS , CAUTIONS AND NOTES The foll owing def initions apply to warnings , cautions and notes used in the Airplane Flight Manual. WARNING Means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety . CAUTION Means that the non-observation of the correspond ing procedure leads to a minor or to a more or less long-term degradation in flight safety . NOTE Draws the attent ion on any special item not directly related to safety but which is important or unusual. 09 Jan 2002 Rev. 0 1.----__...1.--- 1 Page 1 - 3 I I Doc. No. 3.01.12-E I HK 36 TC-100 AFM General 1.4 EXPLANATIONS AND ABBR EVIATIONS a) Airspeeds lAS Indicated Airspeed. Airspeed read on airspeed indicator without any correct ion of erro rs. CAS Ca librated A irspeed . Indicated airspeed, corrected for installa- tion and instrument errors. TAS True Airspeed. The speed of the airp lane re lative to the air. TAS is CAS corrected for errors due to alt itude and temperature . b) Meteorolog ical terms Pressure altitude Altitude indicated by the al timeter when the subscale is set to 10 13.25 hPa or 29 .92 inHg. c) Flight performance Take-off roll Distance between the start of the take-off run and the lift-off po int . Take-off distance Distance between the sta rt of the take-off run and the point above wh ich the airplane is ab le to clear a 15 m (50 ft) ob-stacle. Service ce iling Maximum altitude that can be reached with a climb rate of at lea st 0.5 m/s (100 fpm ). 09 Jan 200 2 Rev. 0 ___.1....--- 1 Page 1 - 4 I I Doc. No. 3.01 .12-E I HK 36 TC-100 AFM • DiamondAIRCRAFT General c) Mass and balance Non-lifting parts Fuse lage, rudder, horizonta l tail surfaces and use ful load Useful load Occupa nts, baggage and fuel d) Misce llaneo us ACL Ant i Coll ision Light (Strobe Light) AGL Above Ground Level CG Center of Gravity ELT Emergency Locator Trans mitter GFRP Glass fiber reinforce d plastic CFRP Carbo n fiber reinforced plastic ACG Austro Contro l GmbH (formerly Bundesamt t ur Zivilluftfa hrt, BAZ) MAM Mandatory Des ign Cha nge Advisory OAM Opt ional Design Change Adv isory I Page 1 - 5 I 09 Jan 2002 Rev. 0 [ Doc. No. 3.01.12-E 1 -'-- _ HK 36 TC-100 AFM • DiamondAIRCRA FT General 1.5 UNITS OF MEASUREMENT Dimensi on SI Units US Units Convers ions Length [mm] millimeters [in] inches [mm] I 25.4 =[in] [m] meters [ft] feet [m] I 0.3048 = [ft] [km] kilometers [NM] nautical miles [km] I 1.852 =[NM] Volume [I] liters [US gal] US gallons [I] I 3.7854 =[US gal] [qts] US quarts [I] I 0.9464 =[qts] Speed [km/h] kilometers [kts] knots [km/h] I 1.852 =[kts] per hour [mph] miles per hour [km/h] I 1.609 =[mph] [m/s] meters per [fpm] feet per minute [m/s] x 196 .85 =[fpm] second Speed of [RPM] revolutions per minute -- rotation Mass [kg] kilograms [Ib] pounds [kg] x 2.2046 =[Ib] Force , we ight [N] newtons [Ibf] pounds force [N] x 0.2248 =[Ibf] Pressure [hPa] hecto- [inHg] inches of [hPa] =[mbar] pascal mercury [hPa] I 33.86 =[inHg] [mbar] millibar [psi] pounds per [bar] x 14.504 =[psi] [bar] bar square inch Temperature [ 0C] degrees [ OF] degrees [°C]x1.8 + 32 =[ OF] Celsius Fahrenheit WF] - 32 )/1 .8 =[ 0C] Intens ity of [A] amperes -- electric current Electric [Ah] ampere-hours charg e -- (battery capac ity) Electric [V] volts potential -- 09 Jan 2002 Rev . 0 1...---__...1..--- 1 Page 1 -6 I I Doc. No. 3.01 .12-E I HK 36 TC-100 AFM • DiamondAIRCRA FT General 1.6 DESCRIPTIVE DATA The HK 36 TC is a two-seated powered sailplane in fiber-composite structure, de- signed in compl iance with JAR-22 ; Category of Airworthiness : Utility. It is a low wing airplane with T-tail, side-by-side seating configuration, tricycle landing gear and Schempp -Hirth type air brakes in the upper surface of the wings. In order to enable a fast disassembly and a space -saving storage the airplane can be furn ished with a wing fold ing mechanism. The power plant is a Rotax R 912 S3 engine with an mt-Propeller hydro-mechanically variable pitch prope ller, type MTV-21-A-C-F/CF 175-05. Span (with winglets) 16.33 m 53 ft 7 in Length 7.28 m 23 ft 11 in Height 1.78 m 5 ft 10 in MAC 1.004 m 3 ft 31/ 2 in Wing area 15.30 m2 165 sq.ft Max. wing load ing 50.30 kg/m2 10.3 Ib/sq .ft Aspect ratio 17 .1 1 Airfoil Wortmann FX 63-137 09 Jan 2002 Rev. 0 I Doc. No.3 .01 .12-E 1 1 pa ge1- 7j HK 36 TC-100 AFM General 1.7 THREE-VIEW DRAW INGS Dimens ions in mil limeters . For convers ion to inches, refer to Section 1.5. I \ I \ I \ I \1 I II II II !J I o II I ~I II II II II I 09 Jan 2002 I Page 1 - 8 I ----------'-------------- I Doc . No. 3.01.12-E I Rev . 0 HK 36 TC-100 AFM General II IJ II I 1 J II II II I o I-- -~ - 't- I Page 1 - g I 09 Jan 2002 Doc . No. 3.01 .12-E 1__R_ev_,_o ---I.- _ HK 36 TC-100 AFM • DiamondAIRCRAFT Operating Limitat ions CHAPTER 2 OPERATING LIMITATIONS Page 2 .1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.2 AIRSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 2.2 .1 AIRSPEED LIMITATIONS 2-3 2.2.2 MISCELLANEOUS AIRSPEEDS 2-5 2.3 AIRSPEED INDICATOR MARKINGS 2-6 2.4 POWER -PLANT 2-7 2.4 .1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7 2.4 .2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 2.5 POWER -PLANT INSTRUMENT MARKINGS 2-9 2.6 MASS (W EIGHT) 2-10 2.7 CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 2- 11 2.8 APPROVED MANEUVERS . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11 2.9 MANEUVERING LOAD FACTORS 2-12 2.10 FLIGHT CREW 2-12 2.11 KINDS OF OPERATION 2-12 2.12 MINIMUM EQUIPMENT LIST 2-13 2 .1 3 FUEL 2-14 2.14 AEROTOW, WINCH UNO AUTO-TOW LAUNCHING 2-14 2.15 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 2.16 LIMITATION PLACARDS 2-15 09 Jan 2002I Doc. No. 3.01.12-E 1_ _ R_e_v_. o 1 Page2 -1 I HK 36 TC-100 AFM Operating Limitations 2 .1 INTRODUCTION Chapter 2 includes operating limitations, instrument markings, and bas ic placards necessary for the safe operation of the powered sailplane, its engine, standard systems and standard equipment. The limitations included in this chapter and in Chapter 9 have been approved by Austro Control GmbH (ACG). WARNING All operation values must be kept within the limits stated herein during flight. 09 Jan 2002 Rev. 0 I Doc. No.3.01 .12-E 1 1 pa ge2-2! HK 36 TC-100 AFM • DiamondAIRCRAFT Operating Limitations 2.2 AIRSPEED NOTE The airspeeds shown below must be understood as lAS. 2.2.1 AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown below: Remarks Airspeed VNE Never exceed 261 141 162 Do not exceed this speed in any speed operation and do not use more than 1/3 of control deflection. vRA Rough air 210 113 130 Do not exceed this speed except speed in smooth air, and then only with caution . Examples of rough air are lee-wave rotors , thunderclouds, etc. VA Maneuvering 176 95 109 Do not make full or abrupt control speed movements above this speed , as the powered sailplane structure could be overstressed by full con- trol movement. VABF Maximum ad- 150 81 93 Above this speed the air brakes missible speed can be extended inadvertently with air brakes over the half-extended pos ition by fixed in half-ex- aerodynamic forces . tended pos ition I : The WARNINGS on the follow ing page must be compl ied with. 09 Jan 2002 Rev. 0I Doc. No .3 .01.12-E 1 1 pa ge2- 3 1 HK 36 TC-100 AFM • DiamondAIRCRAFT WARNING Operating Limitations In order to ensure the flutter safety of the airplane, the never exceed speed V NE (lAS) is reduced at pressure alt i- tudes above 2000 meters or 6500 ft (see Paragraph 4.5.7 HIGH ALT ITUDE FLIGHT). WARNING At speeds beyond the rough air speed vRA the airplane may be overstressed by heavy gusts (lee-wave rotors , thunder- clouds , whirlwinds and turbulence at close range to moun- tain ridge s). WARNING The maneuvering speed stated on the previous page ap- plies to the maximum TIO mass of 770 kg (1698 Ib). At lower flight masses, the following limits must be complied with: TIC mass Maneuvering speed vA kg Ib kmlh kts mph 700 1543 168 91 104 650 1433 162 87 101 600 1323 155 84 96 WARNING These speeds are not marked on the airspeed indicator. Simultaneous full deflection of elevator and rudder can overstress the airplane even at speeds below the maneu- vering speed v A- Rev. 0 09 Jan 2002 HK 36 TC-100 AFM • DiamondAIRCRAFT Operating Limitations 2.2.2 MISCELLANEOUS AIRSPEEDS Remark s Airspeed At this airspeed, the airplane climbs with the maximum possible rate of Best rate-of- 110 59 68 climb . vy climb speed Th is airspeed is marked on the air- speed indicator with a blue radial line. At this airspeed, the airplane climbs with the maximum possible angle of Best angle-of- 95 51 59 climb . Vx climb speed This airspeed is not marked on the airspeed indicator. Recommended lowest ap- 105 57 65 See NOTE below. proach speed NOTE Cond itions such as strong headwind , danger of wind shear, turbulence, or wet wings require a higher approach speed. Stalling speeds see Paragraph 5.2.2 STALLING SPEEDS . 09 Jan 2002 Rev. 0I Doc. No. 3.01.12-E 1 1 Page 2 - 5 I HK 36 TC-100 AFM • DiamondAIRCRAFT Operating Limitations 2.3 AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color-code significance are shown below: Value or Range (lAS) Mark ing Significance km/h kts mph Normal operating range . green 86 - 210 46 - 113 53 - 130 Lower limit is 1 .1 VS 1 at max. flight arc mass and most forward CG. Upper limit is rough air speed v RA- Caution range , rough air speed VRA yellow 210 - 261 113 -141 130 - 162 to never exceed speed V NE. arc Maneuvers must be conducted with caution and only in smooth air. red line 261 141 162 Maximum speed for all operations, never exceed speed V NE. blue line 110 59 68 Best rate-of-climb speed vy. yellow 105 57 65 Approach speed at max. flight triangle mass. 09 Jan 2002 Rev. 0 I Doc .No .3 .01.12-E 1 1 pa ge2- 6 1 HK 36 TC-100 AFM • DiamondAIRCRAFT Operating Limitat ions 2.4 POWER-PLANT 2.4.1 ENGINE Engine manufacturer Bombardier Rotax, Gunskirchen, Austria Engine Rotax 912 83 NOTE The engine drives the prope ller through a speed-reducing gear with a gear ratio of 2.43 :1. The RPM indicator of the airplane indicates the propeller RPM. Consequently, all RPM's given in this manual are propeller RPM's (in con- trast to the engine manual). Max. TI O power (5 minutes) 73.5 kW 1100 DIN-hp Max. TI O RPM 2385 RPM Max. continuous power 69 kW 194 DIN-hp Max. continuous RPM . . . . . . . . . . . .. 2260 RPM Idle RPM . . . . . . . . . . . . . . . . . . . . . . . 600 - 800 RPM Power check RPM 2330 ± 50 RPM Maximum Cylinder Head Temperature . . . . . . . . . . . . . . . . . . .. 135 °C Minimum Oil Temperature 50 °C Maximum Oil Temperature 130 °C 09 Jan 2002 Rev. 0 ___-'-- 1 pa ge2- 7 1 I Doc. No. 3.01.12-E 1 HK 36 TC-100 AFM • DiamondA IRCRAFT Operating Limitations Minimum oil pressure . . . . . . . . . . . .. 0.8 bar Maximum oil pressure. . . . . . . . . . . . . 7 bar (short-term, in the event of cold start) Normal oil pressure range 2 to 5 bar Oil grade: Use only motorcycle oils of a registered brand with gear additives and with API classification "SF" or "SG". The viscosity should be selected according to the follow ing table: Klima Mehrbereichs-Ole climatic °C ,. OF multi-grade oils conditions 40 f.lV~ tropisch 30 (trop ical) 1-80 Q Q It) "'t 20 ~ s: Q Q Q Q It) "'t 60 N N I W W s: s: Q <t <t It) It) "'t Q Q 10 tI) tI) ..... ..... s: It) "'t w W Q I gemaBigt 40 oct oct ..... s: s: (tempe rate) tI) tI) w It) It) <t w w O· tI) <t oct tI) tI) 20 10 ~ o 20 arktisch (arct ic) I-- '2 0 0 0 CAUTION Do not use Aviation Grade oil! 09 Jan 2002 Rev. 0I Doc. No. 3.01.12-E 1 1 Page2 -8 HK 36 TC-100 AFM • DiamondAIRCRA FT Ope rating Limitations Minimum oil quantity 2.0 liters (2.1 US qts ) Max imum oil quantity 3.0 liters (3.2 US qts) 2.4.2 PROPELLER Propeller manufacturer . . . . . . . . . . . . mt-Propeller , Straubing, Germany Propeller . . . . . . . . . . . . . . . . . . . . . .. hydro-mechan ically var iable pitch prope ller MTV-21-A-C-F/CF1 75-05 , pitch angles see Sect ion 7.9 POWER PLANT. 2.5 POWER-PLANT INSTRUMENT MARKINGS Power-plant instrument markings and the ir color-code signification are shown below: Instrument Red Line Green Arc Yello w Arc Red Line = = = = Minimum Normal Caution Range Maximum Limit Operating Limit Range RPM indicator - 600 -2260 RPM 2260-2385 RPM 2385 RPM Oil temperature 50°C 50-130 °C - 130 °C indicator Cylinder head temperature - - - 135 °C indicator Oil pressure 0.8 bar 2 - 5 bar 0.8 - 2 bar , 7 bar indicator 5 - 7 bar Fuel quantity - - - -indicator 09 Jan 2002 Rev. 0 ___.1..--- 1 Page 2 - 9 II Doc. No. 3.01.12-E I HK 36 TC-100 AFM • DiamondA IRCR AFT Operating Limitat ions 2.6 MASS (WEIGHT) Maximum take-off mass Maximum land ing mass 770 kg (1698 Ib) 770 kg (1698 Ib) Maximum mass of all non-lifting parts 610 kg (1345 Ib) Maximum mass in baggage compartment . . . . . . . . . . . . . . . . . . . . 12 kg (26 Ib) Maximum useful load (including fue l) . see Mass & Balance Form, page 6-5 f Maximum useful load on right seat . . . 110 kg (243 Ib) Maximum useful load on left seat . . .. 110 kg (243 Ib) WARNING Any exceed ing of the mass limits can lead to overstressing of the airplane and to a degradation of fly ing characte ristics and flight performance. 09 Jan 2002 Rev. 0I Doc . No. 3.01.12-E 1 1 Page 2 - 10 1 HK 36 TC-100 AFM • DiamondA IRCRAFT Operating Limitations 2.7 CENTER OF GRAVITY The datum plane for the cente r of grav ity (CG) specifications lies perpendicular to the center axis of the conical fuse lage tube . It contacts the wing lead ing edge at the root rib to define its pos ition in longitudin al direct ion. Proced ures fo r a horizontal alignment and empty mass CG specifications can be found in the Airplane Maintenance Manual (Doc. No. 3.02.21 ), Section 4. The perm issible fl ight CG range is: Maximum forward CG 318 mm (12.52 in) aft of datu m plane Maximum rearward CG 430 mm (16.93 in) aft of datum plane WARNING A fl ight CG which lies outside the permissible range deteri - orates the controllability and stab ility of the airplane. The procedure for determining the CG position is included in Chapter 6. 2.8 APPROVED MANEUVERS This powered sailplane is certified in the Utility category. NOTE Aerobatics and spinning are forbidden ! 09 Jan 2002 Rev. 0 I Page 2 - 11 I'--- ...L..- _ I Doc. No. 3.01 .12-E I HK 36 TC-100 AFM • DiamondA IRCRAFT Operating Limitations 2.9 MANEUVERING LOAD FACTORS Table of maximum permissible load factors : at V NE w ith a ir brak es ex tende d pos itive 5.30 4.00 3.50 negative -2.65 -1 .50 0.00 WARNING Exceed ing the maximum permissible load factors can over- stress the airplane . 2.10 FLIGHT CREW Solo flights must be cond ucte d from the left seat. 2.11 KINDS OF OPERATION The powered sailplane is cert ified for DAY-VFR operation. Night VFR operation, if perm itted by the competent authority, requ ires add itional equ ipment in accordance with nat ional regulations. IFR, fl ights in clouds , fl ights into known icing cond itions and aerobatics are forbidden. 09 Jan 2002 Rev. 0I Doc .N o. 3.01.12-E 1 1 Page 2 -12 I HK 36 TC-100 AFM • DiamondAIRCRA FT Operating Limitat ions 2.12 MINIMUM EQUIPMENT LIST Minimum equipment (VFR operation) 1 Altimeter 1 Airspeed indicator 1 Magnetic compass 1 Deviation table 1 RPM indicator 1 Running time meter 1 Manifold pressure indicator 1 Oil pressure indicator 1 Oil temperature indicator 1 Cylinder head temperature indicator 1 Fuel quant ity indicator 1 Ammeter 1 Fuel pressure warning light NOTE A current list of installed equipment (minimum and addi - tional equipment) is provided in the Equipment Inventory which is filed in the Airplane Maintenance Log. I Doc. No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 2 - 13 1 HK 36 TC-100 AFM 2.13 FUEL Fuel capac ity • DiamondAIRCRA FT Operat ing Limitat ions Standard tank 55 liters (1 4.5 US gal) Long range tank 79 liters (20.9 US gal ) Usable fue l Standard tank 54 liters (14.3 US gal) Long range tank . . . . . . . . . . . . . . . .. 77 liters (20.3 US gal ) Approved fue l grades a) AVGAS 100 LL b) Automot ive fuel, min. RON 95: EN 228 Super, EN 228 Super Plus NOTE Due to its high lead concentration, AVGAS causes in- creased wear of the va lve seats and produces more resi- due in the combustion chambers . It should therefore only be used at high ambient temperatures (to prevent vapor lock ) or when other fuel grades are not available. 2.14 AEROTOW, WINCH UND AUTO-TOW LAUNCHING The powered sailp lane is designed for self-take-off only . I Doc. No. 3 .01 .12-E I Rev. 0 09 Jan 2002 I Page 2 - 14 1 HK 36 TC- 100 AFM Operating Limitations 2.15 OTHER LIMITATIONS Limitations for soar ing when using a battery with a capac ity of 18 ampere-hours The capacity of the lead accumulator is highly depe ndent on the temperature. There- fore , the duration of continuous soar ing at low ambient tempe ratu res is restricted to: 4 hou rs at 0 °C (32 OF) and 2 hours at -10 °C (14 OF), good maintenance cond ition and cha rge of the battery provided . A ve rage current requirement: 0.3 amperes . Limitat ions with 30 ampere-hours battery No limitations. 2.16 LIMITATION PLACARDS Placard Location Remark Maneuvering speed at max. gross weight VA = 176 km/h Min. useful load on the seats , -full tank , no baggage if airspeed indi- - instrument pane l cator is cali - Min. usefu l load on the seats , or LH canopy full tank, 12 kg (26 Ib) baggage brated in [kts]: - frame Maximum permiss ible usefu l load VA =95 kts WARN ING Use air brake fixture (hands off) only up to 150 km/h! if airspeed indi-Al B may extend beyond fixture at higher speeds. cator is cali- instrument panel brated in [kts]: 81 kts or LH canopy frame I Page 2 - 15 1 09 Jan 2002 Rev. 0 I Doc. No. 3.01.12-E 1 -'--- _ HK 36 TC -100 AFM • DiamondAIRCRAFT Operating Limitations Placard Location Remark Altitude V NE (lAS) [m] [ttl [km/h] [kts] [mph] - 2000 - 6500 261 141 162 instrument pane l - 3000 - 9800 246 133 153 or LH canopy - 4000 - 13100 233 126 145 frame - 5000 - 16400 221 119 137 - 6000 - 19600 210 113 130 Aerobatics and Spin instrum ent pane l are forbidden ! or LH canopy frame GPS not approved for primary navigat ion. I instrum ent panel opt ional Landing Light and Position Lights may only be used for instrument pane l opt iona l 10 % of engine operating time. I No smok ing I instrument pane l Tie baggage down, rearward side of max. 12 kg (26 Ib). baggage com- partment I Page 2 - 16 1 09 Jan 2002 Rev. 0 I Doc . No. 3.01 .12-E I J..-. _ HK 36 TC-100 AFM • DiamondAIRCRAFT Emergency Proced ures CHAPTER 3 EMERGENCY PROCEDURES Page 3.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2 3.2 CANOPY JETTISON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 3-2 3.3 BAILING OUT 3-2 3.4 STALL RECOVERY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 3-3 3.5 SPIN RECOVERY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4 3.6 SPIRAL DIVE RECOVERY 3-4 3.7 ENGINE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 3-5 3.7 .1 ENGINE FAILURE DURING TAKE-OFF. . . . . . . . . . . . . . . . . . 3-5 3.7.2 ENGINE RESTART WITH A DISCHARGED BAITERY (DURING FLIGHT) 3-6 3.7.3 PROPELLER REMAINS IN FEATHERED POSITION . . . . . . . . 3-7 3.7.4 ENGINE FAILURE DURING CRUISE . . . . . . . . . . . . . . . . . . . . 3-9 3.7.5 CARBURETOR ICING 3-10 3.8 FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 3.8 .1 CARBURETOR FIRE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 3-11 3.8.2 ELECTRICAL FIRE . ... . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 3- 11 3.9 OTHER EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 3.9 .1 MALFUNCTION OR FAILURE OF PROPELLER SPEED CONTROL . . . . . . . . . . . . . . . . . . . . . . 3-11 3.9.2 ICiNG . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . 3-11 3.9.3 WAR NING LIGHT FOR FUEL PRESSURE ILLUMINATES . . 3-12 3.9.4 CAUTION LIGHT FOR COOLANT LEVEL ILLUMINATES 3-12 3.9.5 EMERGENCY LANDING ON WATER 3-13 I Page 3 - 1 I 09 Jan 2002 I Doc. No. 3.01.12-E 1__R_e_v ._o --'-- -----J HK 36 TC-100 AFM • DiamondAIRCRAFT Emergency Procedures 3 .1 INTRODUCTION This chapter provides checklists and recommended procedures for coping with emergencies that may occur. Since it is impossible to foresee all kinds of emergencies and consider them in the Airplane Flight Manual , it is absolutely necessary for the pilot to know the airplane and to have knowledge and experience in solving problems that may occur. 3.2 CANOPY JETTISON 1. Red canopy locks (LH and RH) . . . . . swing 180 0 rearward 2. Canopy . . . . . . . . . . . . . . . . . . . .. . . push up and rearward with both hands 3.3 BAILING OUT 1. Canopy jettison 2. Seat harness . . . . . . . . . . . . . . . . . . . . . .. release 3. Evacuate airplane CAUTION When using a manual parachute , wait two seconds after exit ing the airp lane before pulling the release cord . 09 Jan 2002 Rev. 0 I Doc. NO .3 .01.12-E 1 1 pa ge3 - 2 1 HK 36 TC-100 AFM • DiamondA IRCRAFT Emergency Procedu res 3.4 STALL RECOVERY Behav ior with power off Under all loading conditions , air brakes extended or retracted , in straight and level or in banked flight, the airplane enters a horizonta l stall, during which the ailerons remain effective, even with maximum elevator deflection. A partial loss of positive control in the stick and pedals , buffet ing, and a pitch angle of 20° to 30° occur during this condition. NOTE During the horizontal stall , the airspeed indication rises to approximately 85 km/h (46 kts / 53 mph). Behav ior with power on See behav ior with power off. Excep tion: at 50 % to 100 % power, stra ight and level fl ight, and maximum rearward center of gravity, the airplane may perform a stall dive over the left or right wing after entering the horizonta l stall if the control stick is pulled even further. Recovery The horizontal stall can be terminated immediately by relaxing the force on the elevator contro l. NOTE If the airplane performs a stall dive, immediately relax the force on the elevator control and pull out the airplane smoothly. If the stick is pulled further, the airplane may start to spin. Altitude loss resulting from stationary horizontal stall de- scr ibed above : approx. 10 - 20 m (33 - 65 ft). Altitude loss resulting from stall dive over a wing: approx . 40 m (1 30 ft). I Page 3 - 3 09 Jan 2002 Rev. 0 Doc. No. 3.01.12-E 1 ---'- _ HK 36 TC-1 00 AFM • DiamondAIRCRA F T Emergency Proced ures 3.5 SPIN RECOVERY 1. Rudder apply fu lly opposite to sp in direction Elevator . . . . . . . . . . . . . . . . . . . . . . . . . . . control stick forward A ilerons . . . . . . . . . . . . . . . . . . . . . . . . . . . neutral After spin movement has terminated: 2. Bring rudder in neutral position , pull airp lane out smoothly 3.6 SPIRAL DIVE RECOVERY There is no tendency to a sp ira l dive . The standard recovery procedure is: 1. Rudde r . . . . . . . . . . . . . . . . . . . . . . . . . . . . app ly fully oppos ite to sp iral dive rotation 2. A ilerons apply fu lly oppos ite to sp ira l dive rotation 3. Pull airplane out smooth ly 09 Jan 2002 Rev. 0 I Doc . No. 3.01 .12-E 1 1 Page 3 - 4 1 HK 36 TC-100 AFM Emergen cy Procedures 3.7 ENGINE FAILURE 3.7.1 ENGINE FAILURE DURING TAKE-OFF 1. Fuel valve check OPEN 2. Electric fuel pump check ON 3. Propeller speed control TAKE-OFF 4. Ignition switch BOTH 5. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF WARNING If the symptoms cannot be eliminated immediately and the eng ine refuses to deliver enough power, then a stra ight-in land ing must be performed if below 80 m (260 ft ) AGL. before touchdown : Fuel valve CLOSED Ignition switch OFF Master switch . . . . . . . . . . . . . . . . . . OFF 09 Jan 2002 Rev. 0 I Page 3 - 5 I_______--..1. _ I Doc. No. 3.01 .12-E I HK 36 TC-100 AFM Emergency Procedures 3.7 .2 ENGINE RESTART WITH A DISCHARGED BATTERY (DURING FLIGHT) 1. Electrical equipment OFF 2. Fuel valve OPEN 3. Master sw itch. . . . . . . . . . . . . . . . . . . . . . . ON 4. Mode select switch POWER FLIGHT 5. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required 6. Thrott le control IDLE 7. Ignition switch BOTH 8. Airspeed increase to 160 to 180 km/h (86 to 97 kts / 99 t01 12 mph) 9. Prope ller speed cont rol . . . . . . . . . . . . . . . slowly move from FEATHER to TA KE-OFF 10. Oil pressu re must be ava ilable within 10 seconds 11. Choke as requ ired 12. RPM and throttle as requ ired CAUTION After prolonged soaring per iods, adequate altitude reserve must be ensured for eng ine warm-up . 13. Electrical equ ipment as required 14. Continue flight normally 15. Determine reason for battery discha rge CAUTION The eng ine is started due to windmilling . Because of the high airspeed requ ired for this process , an altitude loss of up to 300 m (1000 ft) must be expected . The airspeed limitations must not be exceeded . I Page 3 - 6 I 09 Jan 2002 Rev. 0 1 Doc . No. 3.01.12-E 1 -'-- _ HK 36 TC-100 AFM Emergency Procedures 3.7.3 PROPELLER REMAINS IN FEATHERED POSITION NOTE The propeller requ ires hydraulic pressure for pitch reduc- tion . The hydraul ic pressure is suppl ied by a pressure ac- cumulator. If this accumulator is empty, pressure must be built up by the oil pump of the engine. The engine is started w ith the propeller in feathered pitch and the throttle control in IDLE pos ition . 1. Electrical equ ipment OFF 2 . Fuel valve OPE N 3. Master switch . . . . . . . . . . . . . . . . . . . . . . . ON 4. Mode select switch POWER FLIGHT 5. Caution light for coolant level illuminates for approximately 3 seconds and ext inguishes 6 . Electric fuel pump ON ; Check whether the red warning light extinguishes after build-up of fuel pressure 7. Choke . . . . . . .. . . . . . . . . . . . . . . . . . . . . as required 8. Throttle control IDLE 9. Ign ition switch BOTH 10 . Propeller speed control . . . . . . . . . . . . . . . TAKE-OFF 11. Ignition switch turn clockwise to start engine unt il propeller is in the working position 09 Jan 2002 Rev . 0I Doc . No .3 .01 .12-E 1 1 Page 3-7 I HK 36 TC-100 AFM • DiamondAIRCRAF T CAUTION Emergency Procedures It is possible to start the engine with the propeller in the feathered position , this however increases eng ine wear. 12. Oil pressure . . . . . . . . . . . . . . . . . . . . . . .. must be available w ithin 10 seconds 13. Choke. . . .. . . .. . . . . . . . . . . . . . . . . . . . as required 14. RPM and throttle as requ ired 15. Electric fuel pump OFF 16. Electrical equipment as required 17. Cont inue flight norma lly 18. After landing, determine the reason for the loss of pressure in the oil pressure accumulator and correct the fau lt. I Doc. No. 3.01 .12-E I Rev. 0 09 Jan 2002 I Page 3 - 8 I HK 36 TC -100 AFM • DiamondA IRCRA FT Eme rgency Proce dure s 3.7.4 ENGINE FAILURE DURING CRUISE Fuel va lve check OPEN Electric fuel pump ON C hoke check OFF 1. 2 . 3. 4. 5. 6. Carburetor heat Ign ition switch . Fue l qua nt ity indi cator . ON at outs ide te mperature s below 10 °C (50 OF) check BOTH c hec k NOTE If the sympto ms cann ot be eliminated and the eng ine re- fuses to del iver enough power , proceed as fol lows: 1. Throttle control IDLE 2. Ign ition sw itch OFF 3. P ropeller speed control FEATHER 4. Fuel valve CLOSED 5. Master sw itch OFF 6 . A irspeed fo r best gl ide rat io (105 km/h ) (57 kts /6 5 mph ) 7. Look fo r a suitable lan ding field 8. Cowl flap C LOSED 09 Jan 200 2 Rev. 0I Doc .No .3 .01.12-E 1 1 Page 3 -g I HK 36 TC-100 AFM 3.7.5 CARBURETOR ICING • DiamondA IRCRAFT NOTE Emergency Procedures Carburetor icing can be recognized by a drop in the engine RPM and/or loss of man ifold pressure and/or irregular running of the eng ine without a change in the throttle con - tro l pos ition, the choke pos ition , the prope ller sett ing , the airspeed, or the altitude. 1. Carburetor heat . . . . . . . . . . . . . . . . . . . .. ON NOTE The eng ine out put wi ll slight ly drop, due to the intake air heat ing, and fue l consumption will slightly increase. 2. Carburetor heat . . . . . . . . . . . . . . . . . . . . . OFF as requ ired I Doc. No . 3.01.12-E I Rev. 0 09 Jan 2002 I Page 3 - 10 I HK 36 TC-100 AFM • DiamondAIRCRAFT Emergency Procedures 3.8 FIRE 3.8.1 CARBURETOR FIRE 1. Fuel valve CLOSED 2. Throttle control FULL POWER 3. Cabin air and cab in heat . . . . . . . . . . . . . . switch off 3.8.2 ELECTRICAL FIRE 1. Master switch . . . . . . . . . . . . . . . . . . . . . . . OFF 3.9 OTHER EMERGENCIES 3.9.1 MALFUNCTION OR FAILURE OF PROP ELLER SPEED CONTROL 1. Throttle control keep RPM in admissible range 2. A irspeed reduce 3.9.2 ICING 1. Leave icing area 2. Constantly move the controls to prevent the m from be ing locked by ice If ice accumulates on canopy: 3. Weather w indow open 4. Cab in heat . . . . . . . . . . . . . . . . . . . . . . . . . ON 09 Jan 2002 Rev. 0 L..--..-__--l.-- 1 Page 3 - 11 II Doc. No. 3.01 .12-E I HK 36 T C-100 AFM • DiamondA IRCRA FT Emergency Procedures 3.9.3 WARNING LIGHT FOR FUEL PRESSURE ILLUMINATES 1. Electric fue l pump ON if the light extinguishes: * Land on nearest suitab le airfield and determine reason for illumination. if the light does not extinguish : * Lack of fue l pressure may result in engine failure. See NOTE in 3.7.4 ENGINE FAILURE DURING CRUISE (page 3-9 ). 3.9.4 CAUTION LIGHT FOR COOLAN T LEVEL ILLUMINATES If poss ible , turn off eng ine and land on nearest suitab le airfield without eng ine power . If turning off the engine is impossible, continue flight with reduced power and land on nea rest suitable airfield. WARNING Monitor eng ine temperatures ! I Page 3 - 12 1 09 Jan 2002 Rev. 0 I Doc . No. 3.01.12-E I -'- -----J HK 36 TC-100 AFM • DiamondA IRCRAFT Emergency Procedures 3.9.5 EMERGENCY LANDING ON WATER Emergency land ings on water should be performed in extreme emergency situations on ly. It must be assumed, from trials with sailplanes, that the airplane will submerge imme diately after touching the water and then surface again . 1. Parachute harness open 2. Seat harness . . . . . . . . . . . . . . . . . . . . . . . tigh ten 3. Approach speed normal 4. Touchdown with minimum speed and air brakes retracted NOTE Conditions such as strong headwind , danger of wind shear, turbul ence or wet wings require a higher approach speed. WARNING On touchdown protect your face with one arm! 5. Seat harness . . . . . . . . . . . . . . . . . . . . . .. release 6 . Red canopy locks (LH and RH ) swing 1800 rearward , push canopy away 7. Evacuate airplane as fast as poss ible I Doc . No. 3.01 .12-E I Rev. 0 09 Jan 2002 I Page 3 - 13 1 HK 36 TC-100 AFM • DiamondAIRCRAFT Normal Procedu res CHAPTER 4 NORMAL PROCEDURES Page 4 .1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2 4.2 RIGGING AND DE-RIGGING 4-2 4.3 DAILY INSPECTION . . . . . . . . . 4-7 4.4 PREFLIGHT INSPECTION 4-14 4.5 NORMAL PROCEDURES AND RECOMMENDED SPEEDS 4-15 4.5.1 STARTING ENGINE, RUN UP & TAXIING PROCEDURES 4-1 5 4.5.2 TAKE-OFF AND CLIMB 4-19 4.5.3 FLIGHT (INCLUDING IN-FLIGHT ENGINE STOP/START PROCEDURES) 4-20 4.5.4 DESCENT . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 4-23 4.5.5 APPROACH AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . 4-23 4.5.6 (omitted) 4.5.7 HIGH ALTITUDE FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . 4-28 4.5.8 FLIGHT IN RAIN 4-29 4.5.9 AEROBATICS 4-29 4.5.10 ENGINE SHUT-DOWN . . . . . . . . . . . . . . . . . . . . . . 4-29 4.5 .1 1 PARKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-30 09 Jan 2002I Doc. No .3 .01 .12-E 1__R_e_v._o 1 Page4 - 1 I HK 36 TC-100 AFM Normal Procedures 4.1 INTRODUCTION Chapter 4 contains checklists and a description of the normal operating procedures wh ich is based on the results of flight tests . Normal procedures associated with opt iona l systems can be found in Chapter 9. 4.2 RIGGING AND DE-RIGGING General Each wing is connected to the fuselage by three bolts. The two main bolts are located at the center of the spar tunne l. They are accessible between the backrests and can be inserted fro m the front side. A spr ing loaded hook is placed over the bolt handles to secure the bolts. The A- and B-bolts are fixed to the fuselage at the wing root. The A -bolt is placed in front of the spar tunnel and the B-bolt lies near the trailing edge . Self locking units are screwed onto the B-bolts, which are accessible th rough handholes on the upper surface of the wing . Locking rings are integrated in the B-bolt lock ing units, which therefore do not requ ire any furthe r safetying . The hor izontal stabilizer is attached to the vertica l stab ilizer by means of three bolts . Th e two bolt s at the rear are fixed to the mount in the vertical stabilizer. The threaded bolt located at the front is fitted with a hexagonal socket. When screwed in, it is automatically secured by means of a locking ring integrated into the hori zont al stab i- lizer. I Page 4 - 2 I 09 Jan 2002 Rev. 0 I Doc . No . 3.01.12-E 1 .1.....- ----J HK 36 TC -100 AFM No rma l Procedures W ing insta llation w ithout wing folding mechan ism 1. Clea n all bo lts and bushe s and the B-bolt locking unit and app ly a light coat of grease . 2. Lift one wing (two persons at the root rib, one at the wing tip) and insert spa r stump into spar tunne l. Ensure the smooth insertion of the A - and B-bo lts. Co nnect pos ition ligh ts (optional) and AC L (= strobe light, optional ) wh en the gap between fuselage and w ing is just wide enough to reach the w ires. 3. Insert main bolt wh ile mov ing the wing tip in small circles. The aileron and air brake control systems are automat ica lly connected . Do not release the win g befo re the main bo lt has been inserted comp letely. The w ide track of the landi ng gear supports the attached wi ng ; no support of the wing tip is req uired . 4. Screw the B-bolt lock ing unit onto the B-bolt and tighten it by hand . 5. Insta ll the other wing in a similar manner. 6 . Tighten both B-bolt lock ing un its w ith a wrench (size 17 mm), app lying moder - ate ha nd torque (approximately 6 Nm (4.5 ft.l b)). 7. Secure ma in bolts with spr ing loaded hook. 8. Apply water res istant adhes ive tape to the gap between fuse lage and wing and to the covers on the access holes. 09 Jan 2002 Rev . 0 I Doc. No. 3.01 .12-E 1 1 Page 4 - 3 I HK 36 TC -100 AFM Normal Procedures W ing install ati on wi th win g fo lding mech an ism 1. Clean all bo lts and bushes and the B-bo lt lock ing un it and app ly a light coat of grease , remove co ver fro m B-bo lt ha ndhole. 2 . Un hoo k one win g from its han ging mount on the sta bilize r, pull it re arw ard to the stop. A second person should stand between th e wing and fuse lage and relieve the load on the telescopic tube by lifti ng the w ing at the spar stump. 3. Wal k forward until the wing is 90° from line of fl ight ; rotate the wing unt il the root ribs are para llel ; keep wing in its co rrect pos ition . 4. Introduce spa r stump into spa r tunne l whil e en sur ing the smooth insertion of A- and B-bolts. Connect pos ition lights (optional) and ACL (= strobe light, op- t iona l) when the gap between fuse lage and win g is just w ide enough to reach the wi res. 5. Inse rt ma in bo lt whi le movin g the win g tip in smal l circles. The aileron and air brake control systems are automatically connected . Do not release the w ing befo re the main bo lt has bee n inserted complete ly. The wide track of the landi ng gear supports the attached wing ; no support of the wing tip is requ ired . 6. Screw the B-bo lt locking unit onto the B-bolt and tighten it by ha nd . 7. Insta ll the ot her w ing in a similar man ner . 8. Tighten both B-bolt locking units w ith a wrench (size 17 mm), applying moder- ate hand torque (approximatel y 6 Nm (4.5 fU b)). 09 Jan 2002 Rev. 0 I Doc .No .3 .01.12-E 1 1 pa ge4- 4 1 HK 36 TC-100 AFM • DiamondA IRCRAFT Normal Procedures 9. Secure main bolts with spring loaded hook. 10. Apply water resistant adhes ive tape to the gap between fuse lage and wing and to the covers on the access holes . W ing removal To remove the wing s reverse the above procedure. NOTE When installing or removing the wings, ensure that the airplane will not drop onto its nose wheel or tail skid as the center of gravity shifts. Winglet installation 1. Clean the bolts and bushes if necessary. CAUTION Do not lubricate the bolt threads ! 2. Install wing let with washers and self locking nuts. 3. Tighten self locking nuts with moderate hand torque (approxi mately 6 Nm (4.5 fUb )). 4. Apply water resistant adhesive tape to the gap. Winglet removal To remove the wing let reverse the above procedure. I Doc. No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 4 - 5 I HK 36 TC -100 A FM Normal Procedures Hor izontal stab ilizer install ation 1. Clean all bushes and bolts and apply a light coat of grease. 2. Move trim knob to full NOSE DOWN pos ition . 3. Remove the Pitot tube . 4. Positi on the horizontal stabilizer over the stabil izer mount; the elevator push- rod must be connected by a second person. WARNING The elevator control system is not connected automatica lly ! 5. Slip the hor izontal stabilizer onto both rearward bolts. 6. Screw in the fasten ing bolt to the stop with an 8 mm hexagon key , app lying moderate hand torque (approximately 6 Nm (4.5 ftlb)) . 7 . Check the horizontal stabilizer for insecure attachment and inspect load trans - miss ion of elevator control system. 8. Install the Pitot tube. 9. Apply wat er resistant adhesive tape to the gap between the horizontal stab ilizer and the vert ical stabilizer. Horizontal stab ilize r removal To rem ove the horizontal stab ilizer reverse the above procedure. I Page 4 - 6 I 09 Jan 2002 Rev. 0 I Doc . No . 3.01.12-E 1 -'-- _ HK 36 TC-100 AFM • Diamond. AIRCRAFT Normal Procedures 4.3 DAILY INSPECTION WARNING Master switch OFF, ignition switch OFF ! 1. Fuel tank drain check: on the drain port (see Section 7.10 FUEL SYSTEM), drain off about 1/8 liter (approx. 1/8 US qt) of fuel using a transparent drain cup . Check for dirt or water. NOTE In order to prevent the water depos ited in the tanks from dispers ing, the airplane should not be agitated prior to the dra in check. 2. Ensure completeness of the onboard documents and ensure that the remaining operating time before the next scheduled inspection (100, 200 or 600 hrs.) allows for the intended flight. 3. Check left fuselage skin for damage and cracks . 4. Inspection of vertical stabilizer: - Check skin for damage or cracks . - Check rudder for improper or insecure mounting . - Check for excessive play. - Check rudder control system for improper connect ion and interference. - Remove Pitot tube cover. - Check Pitot tube for improper mounting and blockage of bores . I Doc. No . 3.01.12-E I Rev. 0 09 Jan 2002 I Page 4 - 7 I HK 36 TC-100 AFM • DiamondA IR CRAFT Normal Procedures 5. Inspection of hor izontal stabilizer: Check horizontal stabilizer and tips for improper mounting and insecure attachment, and check skin for damage and cracks. - Check ele vator for improper mount ing, play , damage and cracks . - Check elevator control system for improper connection , lack of load transm is- sion and interference. 6. Check right fuselage skin for damage and cracks . 7. Inspection of right wing : - Check wing , aileron and winglet for improper or insecure mounting, exces- sive play , damage, and cracks . - Check aileron control system for improper connection, lack of load transm is- sion and interference. - Check air brakes for incomplete retraction ; ensure flushness with the wing surface. 8. Inspection of right main landing gear: - Check landing gear strut for damage and cracks. - Check wheel fairing for damage and looseness. - Visually check tires and brakes. - Ensure correct inflation (2.3 bar (33 psi)) . 9. Inspection of propeller: - Check pro peller blades for damage, cracks and excessive play . - Check spinner for damage and insecure mounting. 10. Inspection of nose land ing gear: - Check nose wheel strut for damage and cracks. - Check wheel fairing for damage and looseness. - Visually check tire. - Ensure correct inflation (1.8 bar (26 psi )). 09 Jan 2002 Rev. 0 '----__-'--- 1 pag e4-s lI Doc. No . 3.01.12 -E I HK 36 TC-100 AFM • DiamondA IRCRAFT Normal Procedures 11. Oil and coo lan t check: - Chec k oil level. NOTE The oil consumption is minor. Refill engine oil only when the oil level reaches or falls below the minimum marking . - Ensure coolant level in equalizing reservo ir is more than 1/3. NOTE The coo lant equa lizing rese rvo ir shou ld not be more tha n 2/3 fu ll. - Check eng ine compart ment for obvious defects. - Check coo lers for obs truct ion . 12. Inspection of left main landing gear: - Check landing gear strut for damage and cracks. - Check wheel fa iring for damage and looseness. - Visually check tires and brakes. - Ensure correct inflation (2.3 bar (33 psi)). 13. Inspection of left wing : - Check wing , aileron and wing let for improper or insecure mount ing, exces- sive play, damage , and cracks . - Check aileron control system for improper con nection, lack of load transmis- sion and interference. - Check air brakes for incomplete retraction; ensure flushness with the wing surface. 09 Jan 2002 Rev. 0I Doc. No. 3.01.12 -E 1 1 Page 4 - 9 I HK 36 TC-100 AFM Norma l Procedures 14. Check in the cabin : - Verify that loading is admissible (refer to Chapte r 6). NOTE Ensure compl iance with load ing restr ictions by chang ing and/or rearranging the useful load. - Master switch . . . . . . . . . . . . . . . . . . . . . ON - Mode select switch . . . . . . . . . . . . . . . . . POWE R FLIGHT - Caution light for coo lant leve l. . . . . . . . . check , illuminates for approx. 3 seconds and extinguishes CAUTION If the caut ion light for the coo lant level does not extinguish, coo lant must replenished (dispatcher vessel, located c en- trally on the eng ine). The upper cowling must be removed for replen ishing . WARNING The pressure cap on the dispatcher vessel must snap in the 'closed' position . Ensure a tight fit! - All circuit breakers presse d in - Fue l quantity check using fuel qua ntity indicator and log boo k entries ; refuel if nec- essary NOTE Usab le fue l and approved fue l grades: see Section 2.13 FUEL. Rev. 0 09 Jan 2002 HK 36 TC-100 AFM • DiamondAIRCRAFT Normal Procedures - Master switch OFF - Fore ign bodies and loose items check - Canopy check for dirt and damage - Cowl flap check for improper operation - Main bolts . . . . . . . . . . . . . . . . . . . . . . . . secured 15. Check of propeller FEATHER pos ition : - Rudder pedals . . . . . . . . . .. adjust Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . closed & locked Fuel valve . . . . . . . . . . . . . . . . . . . . . . . . OPEN Park ing brake . . . . . . . . . . . . . . . . . . . . . set Electrical equipment . . . . . . . . . . . . . . .. OFF Master switch ON - Mode select switch . . . . . . . . . . . . . . . . . POWER FLIGHT - Caut ion light for coola nt level illuminates for approx. 3 seconds and extingu ishes - Propeller speed contro l TAKE-OFF - Cowl flap OPEN - Electric fue l pump ON; verify that red warn ing light extinguishes after build-up of fuel pressure - Throttle control IDLE - Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . ON if engine is cold I Page 4 - 11 I 09 Jan 200 2 Rev. 0 I Doc . No. 3.01.12-E 1 -'-- _ HK 36 TC-100 AFM • Diamond. AIRCRAFT Normal Procedures WARNING People must stay clear of the prope ller danger zone ! - Ignition switch . . . . . . . . . . . . . . . . . . . . . turn clockwise to start eng ine - Throttle control . . . . . . . . . . . . . . . . . . . . adjust 1000 RPM - Oil pressure . . . . . . . . . . . . . . . . . . . . . . must reach operating range within 10 seconds CAUTION If oil pressure is too low, turn off engine immediately ! NOTE When the powered sailplane has been parked for long per iods, or the hydraulic pressu re accumu lator is emptied for any other reason, a loss of oil pressure may occur after oil pressure build-up in the area of the oil pressure sensor. The reason for this is the filling process of the accumulator. The oil pressure indicator may drop to zero for a maximum of 15 seconds. - Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . push forward as requ ired - Electric fuel pump OFF I Page 4 - 12 1 09 Jan 2002 Rev. 0 I Doc. No. 3.01.12-E 1 ---'- _ HK 36 TC-100 AFM Normal Procedures - At increased idle speed (approximately 1000 RPM) turn off ignition and simultaneously pull propeller speed contro l all the way back to the FEATHER pos ition. NOTE Unless the propeller speed control is actuated simulta - neously with the ignition switch, the propeller will remain in the take-off position. Propeller feathering is only possible at 500 RPM or above (see Section 7.9 POWE R-PLANT). - Propeller speed control TAKE- OFF NOTE If the prope ller remains in the feathered position, apply the emergency procedure described in Paragraph 3.7.3 PRO- PELLER REMAINS IN FEATHERED POSITI ON. - Master switch . . . . . . . . . . . . . . . . . . . . . OFF - Mode select switch SOARING 09 Jan 2002 Rev. aI Doc. No. 3.01.12-E 1 1 Page 4 - 13 1 HK 36 TC-1 00 AFM • DiamondAIRCRAFT Normal Procedures 4.4 PREFLIGHT INSPECTION The following checklist placard with the most important items is placed where it is well visible for both pilots: START CHECK 1. Mass & Balance checked 2. Main bolts secured 3. Fuel valve OPEN 4. Fuel quant ity checked 5. Canopy locked 6. Seat harness on & s ec ur e 7. Propeller check 8. Magneto check 9. Carburetor heat OFF 10. Controls f ree 11. Tr im checked 12. Parking brake released 13. Air brakes locked 14. Fuel pump ON I Doc. No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 4 - 14 1 HK 36 TC-100 AFM Normal Procedures 4.5 NORMAL PROCEDURES AND RECOMMENDED SPEEDS 4.5.1 STARTING ENGINE, RUN UP & TAXIING PROCEDUR ES 1. Rudder pedals . . . . . . . . . . . . . . . . . . . . . . adjust 2. Seat harnesses . . . . . . . . . . . . . . . . . . . . . fasten 3. Canopy . . . . . . . . . . . . . . . . . . . . . . . . . . . closed & lock ed 4. Fuel valve OPE N 5. Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . free 6 . Air brakes check operation ; lock 7. Parking brake set 8. Electrical equipment OFF 9. Master switch ON 10. Mode se lect switch POWER FLIGHT 11. Caution light for coolant level illuminates for approx . 3 seconds and ext ingu ishes 12 . Propeller speed control TAKE-OFF 13 . Fuel quantity ind icator . . . . . . . . . . . . . . . . check 14. Cowl flap OPEN 15. Electric fuel pump ON ; verify that red warn ing light ext inguishes after bu ild-up of fuel pressure 16. Throttle contro l IOLE 17. Choke ON if engine is co ld I Page 4 - 15 1 09 Jan 2002 Rev . 0 1 Doc . No. 3.01 .12-E 1 ----1- _ HK 36 TC-100 AFM • DiamondA IRCRAFT WARNING People must stay clear of the propeller danger zone! Normal Procedures 18. Ignition switch turn clockwise to start eng ine 19. Throttle control adjust 1000 RPM 20. Oil pressure . . . . . . . . . . . . . . . . . . . . . . .. must reach operating range within 10 seconds CAUTION If oil pressure is too low, turn off engine immediately! NOTE Whe n the powere d sailplane has been parked for long periods, or the hydrau lic pressure accumulator is emptied for any other reason , a loss of oil pressure may occur after oil pressure build-up in the area of the oil pressure sensor. The reason for this is the filling process of the accumulator. The oil pressure indicator may drop to zero for a maximum of 15 seconds . 21. Choke push forward as requ ired WARNING If the engine is warm, the activated choke will considerably reduce the eng ine output ! I Doc. No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 4 - 16 1 HK 36 TC-100 AFM Normal Procedures 22. Electrical equipment as required 23. Altimeter set 24. Oil temperature check CAUTION Before loading the engine, allow the oil temperature to rise to 50 °C with the cowl flap open at 1000 to 1500 RPM (also possible during taxiing). 25. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 26. Check ignition circuits at 1700 RPM . .. . . RPM drop . . . . . . 50 to 150 RPM difference LH/RH . max. 50 RPM CAUTION If RPM drop is too high at low ambient temperatures, re- peat check with the carburetor heat ON. 27. Check carburetor heat at 1700 RPM .. . . . RPM drop . ... . approx. 20 RPM 09 Jan 2002 Rev. 01 Doc. No .3 .01.12-E 1 1 pa ge4-1 7! HK 36 TC-100 AFM • DiamondAIRCRAFT Normal Procedures 28. Propeller check: - Throttle control . . . . . . . . . . . . . . . . . . . . adjust 2000 RPM - Pull prope ller speed control back to the cam in front of the SOARING posi- tion, wait until propeller speed drops to approximately 1800 RPM. Reset to TAKE-OFF position. Carry out this procedure at least three times. CAUTION Unless this procedure is carried out several times, it is not ensured that the pitch change mechanism is operative . 29. Power check: - Ignition switch BOTH - Throttle control . . . . . . . . . . . . . . . . . . . . FULL; check 2330 ± 50 RPM 30. Power-plant instruments all indicators in green range 09 Jan 2002 Rev. 0I Doc.No .3 .01.12-E 1 1 page4-1 s l HK 36 TC-100 AFM • DiamondA IRCRAFT Normal Procedures 4.5.2 TAKE-OFF AND CLIMB 1. Cowl flap OPEN 2. Electric fuel pump ON 3. Propeller speed control .. . . . . . . . . . . . . . TAKE-OFF 4. Throttle control FULL THROTTLE 5. RPM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check 2330 ± 50 RPM 6. Start take-off run with elevator neutral, keep direction with rudde r. 7. Lift nose wheel at approximately 80 km/h (43 kts I 50 mph). Airplane will lift off by itself at approximately 90 km/h (49 kts I 56 mph). 8. Perform climb with at least 95 km/h (51 kts I 59 mph). Monitor oil pressure , oil temperature and cylinder head tempe rature which all must stay within the green range. at a height of 100 m (330 tt) AGL: 9. Electric fuel pump OFF If the fuel system is intact, the red warning light must not illuminate, because the engine-driven pump maintains the fuel pressure. For best angle of climb adjust airspeed to 95 km/h (51 kts I 59 mph), for best rate of climb to 110 km/h (59 kts 16 8 mph). Figures apply to maximum T/O mass (max. gross weight). 09 Jan 2002 Rev. 0I Doc. No .3 .01.12-E 1 1 Page4-191 HK 36 TC -100 AFM • DiamondAIRCRAFT Nor mal Procedures 4.5.3 FLIGHT (INCLUDING IN-FLIGHT ENGINE STOP/START PROCEDURES) NOTE Econom ic power settings can be found in Paragraph 5.3.7 FUEL CONSUMPTION , CRUISING SPEED , ENDUR - A NCE , RANGE . In-f light eng ine stop 1. Throttle control IDLE 2. Electrical equ ipment OFF WARNING Sta rting the engine with the electric starte r can become impossible: - after prolonged soar ing with severa l elect rical consumers switched ON (mis-operation of mode select switch ); - in extreme co ld (see Sec tion 2.15 OTHER LIMITA- TI ONS); - if the battery is in a poorly mainta ined cond ition or barely cha rged . I Page 4 - 20 I 09 Jan 2002 Rev. 0 I Doc. No . 3.01 .12- E 1 --'-- _ HK 36 TC -100 AFM • DiamondAIRCRAFT Normal Procedures 3. Ignition switch OFF 4. Propeller speed control FEATHER (pull all the way back over the cam) 5. Mode select switch SOARING NOTE The propeller will continue to rotate after ignition shut-off due to w indm ill ing . Feathering will occur with the propeller rotating . 6 . Cowl flap CLOSE In-flight engine start NOTE Starting the eng ine is poss ible up to a density alt itude of at least 5000 meters (16400 ft). 1. Electrical equipment OFF 2. Master switch . . . . . . . . . . . . . . . . . . . . . . . ON 3. Mode select switch POWER FLIGHT 4. Caution light for coolant level illuminates for approx. 3 seconds and ext inguishes 5. Propeller speed control . . . . . . . . . . . . . . . TAKE-OFF 6. Cowl flap OPE N 7. Choke ON if eng ine is cold 8. Electric fuel pump ON 9. Throttle control IDLE 10. Ignition switch start engine; BOTH 09 Jan 2002 Rev . 0I Doc .No .3 .01.12-E 1 1 Page4-21 HK 36 TC -100 AFM • DiamondAIRCRAFT Normal Procedures 11. Oil pressure check NOTE The hydraulic pressure accumulator is no longer full after the prope ller pitch change. After pressure build-up, there might be a loss of oil pressure in the area of the oil pres- sure sensor. The reason for this is the filling process of the pressure accumulator. The oil pressure indicator may drop to zero for a maximum of 15 seconds. 12. Choke . . . . . . . . . . . . . . . . . . . . . . . . . . . . push forward as required 13. Electr ical equipment as requ ired 14. Oi l temperature check 15. Propeller check : - Throttle contro l . . . . . . . . . . . . . . . . . . . . adjust 2000 RPM - Pull prope ller speed control back to the cam in front of the SOARING posi- tion, wait until propeller speed drops to approximately 1800 RPM . Reset to TAKE-OFF position . Carry out this procedure at least three times . CAUTION Unless this procedure is carried out several times , it is not ensured that the pitch cha nge mechanism is operative. I Page 4 - 22 1 09 Jan 2002 Rev. a1 Doc . No. 3.01.12-E 1 ---1.... _ HK 36 TC -100 AFM Normal Procedures 4.5.4 DESCENT 1. Power " . .. . ... .... reduce as required 2. Carbu reto r heat ON if required 3. Tr im . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required 4 . Air brakes " . . . ... . .. . . as required 4.5.5 APPROACH AND LANDING Land ing with eng ine power 1. Propeller speed control TAKE-OFF 2. Elect ric fuel pump ON 3. Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . reduce 4. Carburetor heat " ON 5. Cowl flap OPEN 6. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as required 7. Air brakes " " " " as required NOTE The air brake lever is arrested when the air brakes are extended half way. W ith slightly increased force , this pos i- tion can be overtraveled in either direction. W ith the air brakes locked in the half-extended pos ition, it is poss ible to control the glide path with the throttle contro l. The maxi- mum airspeed for air brakes fixed in the half-extended pos ition (VABF) must not be exceeded . I Page 4 - 23 1 09 Jan 2002 Rev. 0 I Doc . No. 3.01 .12-E I J...- ---J HK 36 TC-100 AFM • DiamondA IRCRAFT Normal Procedures 8. Sideslip possible but not necessary NOTE The speed range in which sideslips can be performed de- pends on the strength of the pilot , since significant rudder control forces are requ ired at higher airspeeds. Usually, the upper limit is approximately 150 km/h (81 kts / 93 mph) . A control force reversal can occur when the rudder is fu lly def lected and the ailerons are deflected oppos ite to the rudder. To recover, either release the aileron control or apply approximately 30 N (7 Ibf) to the rudder pedal to overcome the control force reversal. 9. Approach speed 105 km/h (57 kts / 65 mph ) during final approach NOTE Cond itions such as strong headwind , danger of wind shear, turbu lence, or wet wings requ ire a higher approach speed. I Page 4 - 24 1 09 Jan 2002 Rev. 0 I Doc . No. 3.0 1.12-E 1 -'--- _ HK 36 TC-100 AFM Normal Procedures 10. Touchdown . . . . . . . . . . . . .. . . . . . . . . . . on main landing gear 11. Wheel brakes . . . . . . . . . . . . . . . . . . . . . . . apply as required using toe-brakes CAUTION The wheels have a differential braking system. Apply toe brakes symmetrically to avo id skidding. 12. Electric fuel pump OFF I Doc . No. 3.01 .12-E I Rev . 0 09 Jan 2002 I Page 4 - 25 1 HK 36 TC -100 AFM • DiamondAIRCRAFT Normal Procedures Balked landing with eng ine power 1. Air brakes retract 2. Power sett ing fu ll power WARNING When approach ing with the air brakes fixed in the half- extended pos ition, one hand on the control stick and the other on the thrott le control , first select fu ll throttle and then retract the air bra kes. NOTE Climbing is poss ible with the air brakes fixed in the ha lf- extended pos ition . 3. Perform climb with at least 95 km/h (51 kts / 59 mph) . Mon itor oil pressure, oil temperature and cyl inder head temperature which all must stay within the green range. at a height of 100 m (330 fl) AGL: 4. Electric fuel pump OFF If the fuel system is intact, the red warn ing light must not illuminate, because the engine-driven pump mainta ins the fuel pressure. 09 Jan 2002 Rev. 0I Doc . No . 3.01.12 -E 1 1 Page 4 - 26 1 HK 36 TC-100 AFM • DiamondAIRCRAF T Norma l Procedures Land ing without eng ine power NOTE If the propeller is feathe red, sufficient height must be al- lowed on approach to ensure that the landing field is reached safely. Starting the engine takes too much time during final approach. 1. Trim . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . as requ ired 2. Air brakes as required NOTE The air brake lever is arrested when the air brakes are extended half way. W ith slightly increased force , this pos i- tion can be overtraveled in either direction. 3. Approach speed 105 km/h (57 kts / 65 mph) dur ing final approach NOTE Conditions such as strong headwind, danger of wind shear, turbulence , or wet wings require a higher approach speed . 4. Touchdown on main landing gear i Doc . No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 4 - 27 i HK 36 T C-1 00 AFM • DiamondA IRCRAFT Normal Procedures 5. Wheel brake s . . . . . . . . . . . . . . . . . . . . . . . apply as required using toe-brakes CAUTION The wheels have a differential braking system . Apply toe brake s symmetr ically to avoid skidding . 4.5.6 (omitted) 4.5.7 HIGH ALTITUDE FLIGHT The never exceed speed V NE is reduced at pressure altitudes above 2000 meters (6500 ft), as shown in the fo llowing table . Pressure alt itude Never exceed speed (V NE) meters feet km/h kts mph oto 2000 oto 6500 261 141 162 2000 to 3000 6500 to 9800 246 133 153 3000 to 4000 9800 to 13100 233 126 145 4000 to 5000 13100 to 16400 221 119 137 5000 to 6000 16400 to 19600 210 113 130 09 Jan 2002 Rev. 0I Doc .No .3 .01 .12-E 1 1 pa ge4 -2sl HK 36 TC-100 AFM Norma l Procedures 4.5.8 FLIG HT IN RAIN NOTE Flight performance deteriorates in rain . The impact on the fly ing characteristics is minor. Flight in very heavy ra in should be avo ided because of the reduced visibil ity. CAUTION The airplane has no lightn ing protection system. 4.5 .9 AEROBATICS CAUTION Aerobatics and sp inning are not perm itted . 4.5.10 ENGINE SHUT-DOWN 1. Propeller speed contro l . . . . . . . . . . . . . . . TA KE-OFF 2. T hrottl e control IDLE 3. Parking brake set 4. Electric fuel pump OFF 5 . Electrical equ ipment OFF 1 Page 4 - 29 1 09 Jan 2002 Rev. 0 1 Doc. No. 3.01 .12-E 1 .1....-.. _ HK 36 TC-100 AFM • DiamondAIRCRAFT Normal Procedures 6. Ignition switch OFF 7. Master switch OFF 8. Mode select switch SOARING 9. Air brakes lock 4.5.11 PARKING When parking for a short time , the airplane should be oriented in headwind direction with the parking brake set and the air brakes fixed in the half-extended pos ition. In case of longer unattended parking or in unpredictable wind cond itions , the airplane should be moored or stored in a hangar. It is also advisable to cover the Pitot tube . CAUTION Avo id outdoor parking for prolonged per iods of time. NOTE The powered sailplane shou ld not be parked with the pro- peller in the feathered pitch pos ition . With an empty oil pressure accumulator, the propeller blades cannot move to the take-off position. Starting the eng ine with the propeller in feathered pitch is poss ible, but significantly increases engine wear. I Doc. No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 4 - 30 I HK 36 TC-1 00 AFM • Diam ondAIRCRAFT Performance CHAPTER 5 PERFORMANCE Page 5 .1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2 5.2 ACG-APPROVED DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3 5.2 .1 AIRSPEED INDICATOR SYSTEM CALIBRATION 5-3 5.2.2 STALLING SPEEDS 5-4 5.2.3 TAKE -OFF PERFORMANCE 5-5 5.3 ADDITIONAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-6 5.3 .1 DEMONSTRATED CROSSWIND PERFORMANCE . . . . . . . . . 5-6 5.3.2 GLIDE PERFORMANCE AND FLIGHT POLAR 5-6 5.3.3 TAKE -OFF CHARTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7 5.3.4 NOISE DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9 5.3.5 CLIMB PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9 5.3.6 SERVICE CEILING 5-9 5.3.7 FUEL CONSUMPTION , CRUISING SPEED , ENDURANCE, RANGE 5-10 I Page 5 - 1 I 09 Jan 2002 I Doc. No. 3.01.12-E 1_ _ R_e_v_ .o ---L. _ HK 36 TC -100 AFM • DiamondAIRCRAFT Performance 5 .1 INTRODUCTION Chapter 5 prov ides ACG approved data for airspeed calibration , stall ing speeds and take-off performance, as well as additional information wh ich does not require ap- proval. The data in the charts has been determined on the basis of fl ight tests with the powered sailplane and power-plant in good cond ition , with the wheel fairings installed and using average piloting techniques. The specified airspeeds must be understood as lAS. The performance data has been evaluated using the normal procedures described in Chapter 4. NOTE A poor maintenance condition of the airplane as well as unfavorable external factors (high temperature , rain ) can considerably deteriorate the specified performance values . I Page 5 - 2 I 09 Jan 2002 Rev . 0 I Doc . No. 3.01.12-E 1 -'- _ HK 36 TC-100 AFM • Diam ondAIRCRAFT Performance 5.2 ACG-APPROVED DATA 5.2.1 AIRSPEED INDICATOR SYSTEM CALIBRATION kmf h f h ~ / v/ .I ~ ~ . V/ / ~ ~ . V/ ~ ~ . V V V· V / 1 / / V V VBO KXJ 120 140 I 160 1£K) 200 220 240 260 80 120 140 160 100 180 200 60 70 40 50 80 90 INDICA TED AIRSPEED (lAS) kts. km 140 260 130 240 120 220 110 100 I I I I I I I I I I I kts. 40 50 60 70 80 90 100 110 120 130 140 CAL/BRA TED AIRSPEED (CAS) Doc. No. 3.01. 12-E I Rev. 0 09 Jan 2002 I Page 5 - 3 I HK 36 TC -100 AFM Performance 5.2.2 STALLING SPEEDS Stalling speeds at different bank angles in km/h : IAir brakes Bank angle retracted vso 78 km/h 84 km/h 93 km/h 110 km/h extended V S1 81 km/h 87 km/h 96 km/h 115 km/h Stall speeds at different bank angles in kts: IA ir brakes Bank angle --3-0-0 --1--4-5-0 - --.-- - - ----1 retracted vso 42 kts 45 kts 50 kts 60 kts extended VS1 44 kts 47 kts 52 kts 62 kts Bank angle -----.---3-0-0 - - '- - 4-5-0 -- retracted vso 48 mph 52 mph 58 mph 69 mph extended V S1 50 mph 54 mph 60 mph 71 mph Stalling speeds at different bank angles in mph: I A ir brakes NOTE Conditions such as turbulence, wet wings , or high load factors increase the stall ing speeds. I Doc. No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 5 - 4 I HK 36 TC-100 AFM Performance 5.2.3 TAKE-OFF PERFORMANCE Conditions: - Outside Air Temperature 15 DC (59 OF) - Atmospheric pressure 1013 hPa (29.92 inHg) - Calm - Full throttle - Maximum flight mass - Propeller setting TAKE -OFF (full forward ) - Rotation speed appr o80 km/h (43 kts 150 mph) - Lift-off speed appr o90 km/h (49 kts I 56 mph) - Climb-out speed ap pro 95 km/h (51 kts I 59 mph) - Runway . . . . . . . . . . . . . . . . . . . . . . . . . . . level , asphal t surface Take-off roll 193 m 633 ft Take-off distance to clear 308 m 1010 ft a 15 m (50 ft) obstacle NOTE For take-off distances under conditions which are different from those described above , refer to the charts in Para- graph 5.3.3. NOTE Poor maintenance condition of the airplane, deviation from the procedures prescribed in this manual and unfavorable external factors (high temperature , rain , unfavorable wind and , in particular, long grass) can considerably extend the take-off distance . 09 Jan 2002 Rev. 0 l-__..I...-- I PageS-S II Doc. No. 3.01.12-E I HK 36 TC-100 AFM • DiamondAIRCRAF T Performa nce 5.3 ADDITIONAL INFORMATION 5.3.1 DEMONSTRATED CROSSWIND PERFORMANCE Take -off I 30 km/h I 16 kts Landing 30 km/h 16 kts 5.3.2 GLIDE PERFORMANCE AND FLIGHT POLAR Minimum rate of descent 1.18 m/s (232 fpm) at 97 km/h (52 kts /60 mph) Maximum lift drag rat io 27 at 105 km/h (57 kts / 65 mph) NOTE These figures as well as the graph below are valid for max- imum flight mass with winglets , wheel fairings and spinner installed and the propeller feathered . AIRSPEED 140 kts. I 250 k /h 120 I 200 100 I 80 I 150 60 I 100 40 I 50 -Av m ( ~ <, <.-, I\. -, Flight polar o 0 200 1 400 2 600 3 800 4 1000 5 1200 6 t.p.m. m/s RA TE OF DESCENT I Doc. NO. 3.01.12-E Rev. 0 09 Jan 2002 I Page 5 - 6 I HK 36 TC-100 AFM • DiamondA IRCRA FT Perfo rmance 5.3.3 TAKE -OFF CHARTS Cond itions : - Full throttle - Maximum flight mass - Propeller setting 0 0 0 0 0 0 0 0 0 0 • • • • • • • 0 0 0 TAKE-OFF - Rotation speed . 0 •• • •• ••• •••• ••• ••• 0 appr. 80 km/h (43 kts 1 50 mph) - Lift-off speed .. 0 • • 0 • • • • • • • • • • 0 • • • • • • appro 90 km/h (49 kts 156 mph) - Climb-out speed 0 0 • • •• • •• • • • •• • • • 0 • 0 appr o95 km/h (51 kts 159 mph) - Runway . . 0 0 0 0 • 0 0 0 0 0 0 0 0 0 0 0 0 • 0 • 0 • • •• level , aspha lt surface S1 0" Take-off roll S2 .. 0 Take-off distance to clear a 15 m (50 ft) obstacle Pressure altitude above MSL QFE Head- w ind OAT Om /Oft 400 m 11310 ft 800 m 12620 ft 1200 m 1 3940 ft comp, [0C] 1013 hPa 966 hPa 921 hPa 877 hPa [kts] S 1 S2 S1 S 2 S 1 S2 S1 S 2 [m] [m] [m] [m] [m] [m] [m] [m] 0 163 262 187 294 217 332 251 378 0 15 190 299 219 367 255 383 298 437 30 222 339 257 385 301 440 354 498 0 128 216 147 243 170 275 199 312 5 15 150 247 174 279 202 31 7 237 362 30 175 281 204 319 239 364 283 413 0 96 175 112 197 130 224 153 255 10 15 114 200 133 227 156 258 184 295 30 134 229 157 260 185 298 220 337 09 Jan 2002 ___""-- 1 PageS -? I I Doc. No. 3.01 .12-E I Rev. 0 HK 36 TC-100 AFM • DiamondAIRCRAFT Performance s, Take-off roll S 2 Take-off distance to clear a 15 m (50 ft) obstacle Pressure altitude above MSL QFE Head- wind OAT Om /Oft 400 m 11310 ft 800 m / 2620 ft 1200 m 13940 ft comp, [OF] 29.9 inHg 28.5 inHg 27.2 inHg 25.9 inHg [kts] 5 1 5 2 5 1 5 2 5 1 5 2 5 1 5 2 [ft] [tt] [ft] [tt] [tt] [tt] [tt] [tt] 32 535 860 614 965 712 1089 823 1240 0 59 623 981 719 1204 837 1257 978 1434 86 728 1112 843 1263 988 1444 1161 1634 32 420 709 482 797 558 902 653 1024 5 59 492 810 571 915 663 1040 778 1188 86 574 922 669 1047 784 1194 928 1355 32 315 574 367 646 427 735 502 837 10 59 374 656 436 745 512 846 604 968 86 440 751 515 853 607 978 722 1106 WARNING A grass runway will extend the take-off roll by at least 20 % , depend ing on the characteristics of the ground (soft- ness, grass he ight) . 09 Jan 2002I Doc. No.3 .01 .12-E 1__R_e_v_ .o 1 PageS-a I HK 36 TC-100 AFM • DiamondAIRCRAFT Performance 5.3.4 NOISE DATA The evaluation of noise emissi on was carried out according to the Noise Regulations of ICA O, Annex 16. According to Chapte r 10: 61 .8 dB(A) According to Chapter 6 (for Austr ia only): 62 .3 dB(A); for bas ic tra ining and tow ing flight (Austrian Federal Law Gazette, 29 Oct 1993, 738th Decree) 5.3.5 CLIMB PERFORMANCE Cond itions : - Sea level - Full throttle - Max. fl ight mass - Airspeed v y =110 km/h (59 kts / 68 mph) - Propeller RPM . . . . . . . . . . . . . . . . . . . . . . 2260 RPM Max. clim b rate : 4.9 m/s (965 fpm) 5.3.6 SERVICE CEILING The service ceiling is above 5000 m (16400 ft) . 09 Jan 2002 Rev. 0 I Doc .No .3 .01 .12-E 1 1 pages-9 1 HK 36 TC -100 A FM • Diam ondAIRCRAFT Performance 5.3.7 FUEL CONSUMPTION, CRUISING SPEED, ENDURANCE, RANGE NOTE The specifications for endurance and range app ly to a full tank and do not include any reserve . The range spec ifica- tions apply to fli ght in still air with a well-maint ain ed and correctly adjusted airplane. Cond itions: - Pressure alt itude 1800 m (5900 ft) Prop . Manif. Fuel flow Cruising speed Endur- Range Fuel tank speed press. ance capacity lit.t US stat. US RPM inHg hr gall kmth kts mph h:mm km NM miles liters gal hr 2000 22 16.8 4.4 170 92 106 3:10 545 295 335 55 14.5 4:35 775 420 480 79 20 .9 220 0 22 .7 19.6 5.2 180 97 112 2:45 495 265 305 55 14.5 3:55 705 380 435 79 20 .9 2260 23 .3 23 .2 6 .1 190 103 118 2:15 440 235 270 55 14.5 3:15 630 340 390 79 20 .9 09 Jan 2002 Rev . 0 '---__---'---- 1 Page 5 -10 II Doc. No . 3.01 .12-E I HK 36 TC-100 AFM • DiamondAIRCRAFT Performance NOTE It is generally recommended for a fast cruise to select a propeller speed of 2250 RPM and a manifold pressure which is at least 0.7 inHg under the maximum obta inable. This reduces the fuel consumption cons iderably whilst hard ly affecting the cruis ing speed . For an economical crui se it is recommended to set the propeller speed between 2150 and 2050 RPM and the manifold pressure 1 to 2 inHg under the maximum obtain- able . Deviation from this recommendation will result in a fuel flow which is significant ly higher than that shown in the table above . 09 Jan 2002 Rev. 0I Doc. No. 3.01 .12-E 1 1 Page 5 - 11 I HK 36 TC-100 AFM • DiamondA IRCRAFT Mass and Balance CHAPTER 6 MASS (WEIGHT) AND BALANCE Page 6.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2 6.2 WEIGHING PROCEDURE 6-2 6.3 WEIGHING REPORT 6-3 6.4 BASIC EMPTY MASS AND MOMEN T . . . . . . . . . . . . . . . . . . . . . . . . . 6-4 6.5 MASS OF ALL NON-LIFTING PARTS . . . . . . . . . . . . . . . . . . . . . . . . . 6-4 6.6 MASS AND BALANCE FORM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 6-5 6.7 USEFUL LOAD 6-7 6.7.1 MAX IMUM USEFUL LOAD 6-7 6.7.2 USEFUL LOAD ON THE SEATS 6-7 6.7.3 USEFUL LOAD IN BAGGAG E COMPARTMENT 6-8 6.7.4 FUEL LOAD 6-9 6.8 MASS I CG ENVELOPES 6-9 I Page 6 - 1 I 09 Jan 2002 I Doc. No. 3.01.12-E 1__R_e_v._o --J...- _ HK 36 TC-100 AFM • DiamondA IRCRAFT Mass and Balance 6 .1 INTRODUCTION Chapter 6 describes the range of loading in wh ich the HK 36 TC be operated safely. Descriptions of the weighing procedure, the dete rmination of the adm iss ible empty mass CG range and a list of the equipment that must be present in the airplane dur ing the weighing process are included in the Airplane Maintenance Manual (Doc. No. 3.02.21) , Section 4. WARNING Exceed ing the maximum fl ight mass (maximum gross weight ) can lead to overst ress ing of the airplane . Falling short of the minimum usefu l load on the seats w ill lead to reduced controllability and stability of the airplane. 6.2 WEIGHING PROCEDURE The weigh ing procedure is described in the Airplane Maintenance Manual , Paragraph 4.2. The purpose of weigh ing the airplane is to determine the empty mass (empty weight) and the correspond ing CG lever arm (i.e., the CG pos ition). It may be carried out by aut horized personnel only. I Page 6 - 2 I 09 Jan 2002 Rev . 0 I Doc. No. 3.01.12-E 1 -'- _ HK 36 TC-100 AFM • DiamondAIRCRAFT Mass and Balance 6.3 WEIGHING REPORT The Weigh ing Report shows the current empty mass (empty weight) and the corre - sponding CG posit ion. The Weighing Report is filed in the Airplane Maintenance Log. NOTE After equipment changes , repair work , repainting , etc., the new empty mass (empty weight) and the corresponding CG position must be determined by an authorized person in compliance with the Airplane Maintenance Manual. The results must be recorded in the Mass and Balance Form, and the new limits must be drawn on a new Mass and Bal- ance Diagram. 09 Jan 2002 Rev. 0 I Page 6 - 3 IL..- ---.L.. _ [ Doc. No. 3.01.12-E I HK 36 TC-100 AFM • DiamondA IRCRAFT Mass and Balance 6.4 BASIC EMPTY MASS AND MOMENT The empty mass CG limitations are defined in the Airplane Maintenance Manual , Section 4. These limitations guarantee that solo-pilots with a mass (weight) of at least 70 kg (154Ib) will not overstep the maximum rearward CG when flying with a full tank and no baggage. The CG will not exceed the maximum forward position if not more than 220 kg (485 Ib) of useful load on the seats and 10 kg (22 Ib) of fuel for a half hour flight are aboard. 6.5 MASS OF ALL NON-LIFTING PARTS The maximum mass (weight) of all non-lifting parts is 610 kg (1345 Ib). A list of all non-lifting parts is included in the Airplane Maintenance Manual, Paragraph 4.6. NOTE Due to the design of the HK 36 TC, the maximum mass (weight) of all non-lifting parts will not be exceeded as long as the maximum flight mass (max. gross weight) of 770 kg (1698 Ib) is complied with. 09 Jan 2002 Rev. 0I Doc .No .3 .01.12-E 1 1 pa gee -4 1 HK 36 TC-100 AFM • DiamondA IRCRAFT Mass and Balance 6.6 MASS AND BALANCE FORM The Mass and Balance Form on the next page shows the fo llow ing va lues : current empty mass current empty mass CG pos ition current maximum useful load including parachute, seat cushions, fue l, and baggage minimum useful load on seats for solo flights with full tank and no baggage minimum useful load on seats for solo flights with fu ll tank and maximum baggage mass (12 kg or 26 Ib) Add itiona lly, the Mass and Balance Form is a record of all we ighings . The Mass and Balance Form must be updated by an authorized person us ing the data recorded in the currently effective Weighing Report . The corresponding instructions can be found in the Airplane Mainte nance Manua l, Paragraph 4.7. In add ition to the Mass and Balance Form , a new Mass and Balance Diagram is filled out upon each weighing . The corresponding instructions are given in the Airplane Ma intenance Manual , Paragraph 4.8. NOTE The airplane is weighed with the equipment shown in the Equipment Inventory installed. Airp lane operation withou t win glets, spinner or wheel fairings is permissibl e in excep - tional cases. The influence on the empty mass (weight) and the corresponding CG pos ition is neg ligible. 09 Jan 2002 Rev. 0 I Doc. No . 3.01.12-E 1 1 Page 6 - 5 1 HK 36 TC-100 AFM • DiamondA IRCRA F T Mass and Balance MASS AND BALANCE FORM SERIAL NO.: _ CALL SIGN: _ Minimum useful load Date Empty Empty Max. on seats of mass mass useful with full fuel tank A.M.E. weighing (weight) CG pas . load no 12 kg baggage baggage [kg] [mm aft [kg] [kg] [kg] of datum] 09 Jan 2002 '------__-'--- 1 Page 6 -6 I I Doc. NO.3 . 01 .12-E I Rev. 0 HK 36 TC-100 AFM • DiamondA IRCRAFT Mass and Balance 6.7 USEFUL LOAD The useful load cons ists of the masses (weights) of occupants (including parachutes ), baggage and fuel. 6.7.1 MAXIMUM USEFUL LOAD The maximum permissible useful load is shown in the Mass and Balance Form , in the Mass and Balance Diagram, and on the placard in the cockpit. 6.7.2 USEFUL LOAD ON THE SEATS Minimum useful load on the seats The Mass and Balance Form and the limitations placard in the cockp it show the follow ing data : * Minimum useful load on the seats for solo flights with a full tank and no bag- gage; * Minimum useful load on the seats for solo flights with a full tank and maximum baggage mass (12 kg or 26 Ib) The minimum usefu l load on the seats is in no case less than 55 kg (121 Ib). NOTE Pilots with a mass (a weight) between 55 kg (121 Ib) and the minimum usefu l load on the seats must install a trim we ight in the case of solo flights . 09 Jan 2002 Rev. 0 ___l....-- I pag ee-7 1 1 Doc. No. 3.01 .12-E I HK 36 TC-1 00 AFM • DiamondA IRC RAFT Mass and Balance Trim weights If the minimum useful load on the seats is above 55 kg (121 Ib), then a trim weight fixture can be installed on the cente r console 400 mm (15.75 in) aft of the firewal l. A deficit in useful load on the seats should be equal ized using the following table : Deficit in useful load on the seats Trim mass (weight) [kg] [Ib] [kg] [Ib] 5 11 1.7 3.75 10 22 3.4 7.5 15 33 5.1 11.25 Maximum usefu l load on the seats The useful load on one seat must not exceed 110 kg (243 Ib). Lever arm of useful load on the seats A lever arm of 143 mm (5.63 in) aft of datum plane is assumed for al l CG calculations. 6.7.3 USEFUL LOAD IN BAGGAGE COMPARTMENT Maximum useful load in the baggage compartment The maximum useful load in the baggage compartment is 12 kg (26 Ib). NOTE When load ing baggage, make sure not to exceed the maxi- mum perm iss ible useful load. Lever arm of usefu l load in the baggage compartment The CG enve lope assumes that the baggage pieces have the same CG position as the fuel load, i.e. 727 mm (28.62 in) aft of datu m for the standa rd tank , and 824 mm (32.44 in) aft of dat um plane for the long range tank . I Page 6 - 8 I 09 Jan 2002 Rev. 0 [ Doc. No. 3.01.12-E 1 ...1....- _ HK 36 TC-100 AFM • DiamondAIRCRAFT Mass and Balance 6.7.4 FUEL LOAD The fuel capacity is given in Section 2.13 FUEL. NOTE When refuell ing, make sure not to exceed the maximum permissible useful load. Lever arm of the fuel tank The load calcu lations are based on the following CG positions for the fue l load : Standard tank (55 1/14 .5 US gal) : 727 mm (28.62 in) aft of datum plane Long range tank (79 1/ 20.9 US gal) : 824 mm (32.44 in) aft of datum plane 6.8 MASS I CG ENVELOPES The Mass and Balance Diagram is a supplement to the Mass and Balance Form. It gives the pilot the information whether a loading is permissible, tak ing maximum permissible useful load and minimum useful load on the seats into account. It shows the permissible mass (weight) of fuel and baggage for a given useful load on the seats. The diagram appl ies to one specif ic airplane. It is redrawn by an authorized person upon each determinat ion of the empty mass (weight) and the correspond ing CG position. Limits are drawn on the diagram using the broken subsidiary lines and the data prov ided by the Mass and Balance Form. The correspond ing instructions are laid down in the Airplane Maintenance Manual , Paragraph 4.8. 09 Jan 2002 Rev. 0I Doc. No. 3.01.12-E 1 1 pagee-gl HK 36 TC-100 AFM • DiamondA IRCR AFT Mass and Balance Use of the Mass and Balance Diagram The prohibited combinations of useful load on the seats and total mass (weight) of fue l and baggage are represented by the hatching. Beside the diagram there is a scale for the convers ion of the fuel quant ity in liters or US gallons to the fuel mass (weight) in kilograms or pounds . The following sample problems show how to use the Mass and Balance Diagram. Example A: Pilot 70 kg (154 Ib), copilot 82 kg (181 Ib), total 152 kg (335 Ib). Long range tank , ful l (60 kg 11 32 Ib); no baggage . The corresponding point in the diagram does not touch any boundary, hence the loading is permissible. Example B: Pilot 65 kg (143 Ib), solo-flight. Long range tank, full (60 kg I 132 Ib); baggage 12 kg (26 Ib), total mass of fuel and baggage 72 kg (159 Ib). The loading oversteps the maximum rearward CG position. The pilot must remove 15 kg (33 Ib) or 20 liters (5.3 US gal) of fuel. Example C: Pilot 92 kg (203 Ib), passenger 105 kg (231 Ib), total 197 kg (434 Ib). Standard tank. In case they do not take any baggage aboard , they may take off with 27 kg (60 Ib) or 36 liters (9.5 US gal) of fuel. Example 0 : Pilot 57 kg (126 Ib), no cop ilot. Standard tank, full (42 kg I 93 Ib); bag- gage: 12 kg (26 Ib), total mass of fuel and baggage 54 kg (119 Ib). Since the maximum rearward CG position is not effective in sample airplane "b" (empty mass CG position 426 mm or 16.77 in), the pilot may use the entire maximum mass (weight) of fuel plus baggage , which amounts to 54 kg (1 19 Ib). 09 Jan 2002 Rev. 0I Doc. NO .3 .01.12-E 1 1 Page 6 - 10 I HK 36 TC -1 00 AFM • DiamondAIRCRAFT Mass and Balance ! .M .f: . : - _ "'<"~.f!R~ ~ __ - ... . M.E . , _ 130 I I I/O 90 70 I 150 170 190 S eat Pay l oad ----< Mass and Balance O(agram Lon 9 Ran geT a n k (79 liters) I 55 E a p t y Mo~ .s s~ r I 01 nVll b or l _ _~~ ,::,-p_~1. f: ~ :. _~·~':__ C e ll 5Ion: OL ~ J<..>:.~~ _ O o t.o o f " o l g ll r n g : z ../-' E j_'~ _ Do t. e o t R op /oo o lllon l: _ {kg} q) Ol 0 Ol Ol 72 0 llJ 70 "0 60 c 0 50 -q) ;) 40 IJ... ... 30 0 2 0 III III 10 0 ~ 0 ...0 t- Examples 3° 1 ~ :: ' 0 . z 55 Fve l Qvantl i y 0 10{I(1;;1 tn 10 1 0 1 20 20 { . 3 0 2 10 [ k g) 19 0 (' Ri.~ ~ . "" f.£ . t _ :..~ _ .... /J.E'. : _ 110 90 70 55 130 15 0 17 0 S eat Pa y lo a d - --- --- Mass and Balance DI agra m S ian dar d Tan k (55 liters) So r ra' n v .. bO,. '_!~e. ~_ E'£,,_~ _ ~ (~_~ _ Co li 51 ; n:--2£:---3.'::1:.'- - --1-- - - -- - - o: J '" ~ '" Oo l ~ 0 / ... lg ll l nQ' __ I -{_ _ .. _ D o t & o t R tlIp loo •• e n l: _ {kg} -o ...o t- 09 Jan 2002 Rev . 0 ___--l.....-- I Page6-11 II Doc. No. 3.01.12-E Mass and Balance Diagram Useful Load on Seats Long-Range-Tank r I I I I I r I TTT' j I I I I I I I I I I I I I I I I I I I I I I I J I I 110 ..so 12 1 150 200 250 300 350 'f00 -180 [Ibs] »I"Tl ::" S: W (j) --I oI -" o o • om· p 3 ~ g ~ Q. 4 e 8 I • 10 12 I II 20 eo .0 80 ' 0 0 Ie 12 0 -+ ' 20 I :5:Q) l a z ...J... 2 /.1 en en Q) ::J 0- rnQ) Q) ::J o CD 10 20 30 40 110 7 0 "0 80 40 50 :z Fuel Quant ity 0 :r: o 0:r: o [k g] I[ t] [lb !iUu. g,L] 10 20 30 T""l [kg] ............ I "........ "...." r 210 ........ " I ".... " I . 19 0 ............ ... ".... I 170 ............ " ..... "........ A.M.E. A.M.E. ........ " 150 ........ " 130 ................ ~ .... .... .... .>J .... .... ....... .... .... .... " .... " .... " .... .... ,...." " " " " .... " " " " " .... I.... " .... .... " .... .... .... .... " .... " .... .... .... " .... .... .... .... , I' I' .... .... ,.... .... .... .... " .... "" " " .... " .... /10 Empty Mass .$"6> .$"..:. .$"~ .$".$" .$",. .$"~ o+~ o+~ 0+"" 0+... 0+"" 0+"" 90 '"........ I I I I I I • " I I I I I I I I I I I I I I I I I 5 5 70 SERIAL NUMBER CALL SIGN DATE OF WEIGHING DATE OF REPLACE MENT fibs] -- =2 - 70 [kg] 20 40 ! 0 0 0 Z 0 w 0 -" -" N I m :::0 CD < 0 0 CD c:.... Q) ~ N 0 0 N "'U Q) <0 CD (j) I -" N HK 36 TC-100 AFM Powered Sailplane Description CHAPTER 7 POWERED SAILPLANE AND SYSTEMS DESCRIPTION Page 7 .1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 7.2 AIR FRAME 7-2 7.3 FLIGHT CONTRO LS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 7.4 AIR BRAKE SYSTEM 7-4 7.5 LANDING GEAR SYSTEM 7-5 7.6 SEATS AND SAFETY HARNESSES . . . . . . . . . . . . . . . . . . . . . . . . . . 7-6 7.7 BAGGAGE COMPARTMENT 7-6 7.8 COCKPiT 7-7 7.9 POWER-PLANT 7-9 7.10 FUE L SYSTEM 7-14 7 .1 1 ELECTRICAL SYSTEM 7-15 7.12 PITOT AND STATIC SYSTEM 7-15 7.13 MISCELLANEOUS EQUIPME NT 7-16 7 .1 4 PLACARDS / INSCRIPTIONS 7-16 7.14 .1 LIMITATION PLACARDS 7-16 7.14.2 PLACARDS FOR COCKPIT CONTROLS " 7-16 7.14.3 PLACARDS FOR ELECTRICAL EQUIPMENT 7-18 7.14.4 MISCELLANEOUS PLACARDS 7-20 [ Doc . No. 3.01.12-E I Rev. 0 09 Jan 2002 I Page 7 -1 I HK 36 TC-1 00 AFM • DiamondAIRCRAF T Powered Sailp lane Description 7 .1 INTRODUCTION Chapter 7 prov ides a descr iption of the powered sailplane and its systems along with information on the ir operation. Refer to Chapter 9, Supplements, for deta ils of opt iona l systems and equipment. 7.2 AIRFRAME Wings The GFRP/CFRP wings are manufact ured in semi-monocoque sandwich construction . The ailerons are made of CFRP and are attached to the wing by means of five hinges, also made of CFRP . Schempp-H irth type air brakes are prov ided on the upper surface of the wi ngs. They may be extended at all speeds up to VNE. The air brakes have oil dampers but must be locked. This is performed by pushing the lever to the forward stop overcom ing the resistance occurring afte r the air brake is retracted. The air brake lever catches when the air brakes are extended half way. The wings are connected to the fuselage with three bolts each . The winglets are manufactured from CFRP and are attached to the wings with two threaded bolts each . Fuselage The GFRP fuse lage is manufactured in semi-monocoque const ruct ion . A spec ial fire-res istant fabric sheet is sandwiched betwee n a sta inless steel barrier and the firewa ll. The main bulkhead is made of CFRP /GFRP . The instrument pane l is made of GFRP . The maximum permissible mass (weight) of the instrument pane l including the instruments installed is 17 kg (37.5 Ib). [ Page 7 - 2 1 09 Jan 2002 Rev. 0 1 Doc. No. 3.01 .12-E 1 "'- ---' HK 36 TC-100 AFM • DiamondAI RCRAF T Powered Sailplane Description Ta il plane The rudder, elevator and hor izontal stabilizer are manufactured in semi-monocoque sandw ich construct ion. The folded-top COM antenna and the Pitot tube mount are located in the vertical stabilizer . The horizonta l tail surfaces are attached with two bolts and a fastening screw . 7.3 FLIGHT CONTROLS Primary control system The ailerons and elevator are driven by push-rods and the rudder is driven by control cables. Elevator control forces can be compensated by means of a spring trim system . The aileron and air brake control systems are automat ically connected when the wing is installed. However, the ACL (= strobe lights , optional ) and position lights (optional) must be connected manually . The elevator control syste m is not connected automati- cally. Elevator trim system The trim lever with a green knob is located on the center console behind the throttle quadrant. To trim the airplane, unlock the knob by pulling it upwards , then move it to the desired position. The knob is spring-l oaded and locks when it is released. Knob forward =NOSE DOWN I Page 7 - 3 1 09 Jan 2002 Rev. 0 1 Doc. No. 3.01 .12-E I .l......- _ HK 36 TC-100 AFM • DiamondAIRCRAFT Powered Sailplane Description Rudder peda l adjustment CAUTION The rudder pedals must be adjusted on the ground. The pedals are unlocked by pulling the black T-grip in front of the control stick. Move forward: Push peda ls forward with your heels while pull ing the grip. Release the grip and allow the pedals to lock perceptibly . Move rearward: Pull pedals rearward with the grip. Release the grip, use your feet to push the peda ls forward until they lock. 7.4 AIR BRAKE SYSTEM There is a blue air brake lever on either side pane l. By pulling the lever rearward the air brakes are unlocked and extended . The air brake lever catches when the air brakes are extended half way . This position can be overtraveled in either direction with slightly increased force. To lock the air brakes the lever must be pushed to the forward stop overcoming the resistance occurring after the air brake is retracted . WARN ING When exceeding the maximum admissible speed with the air brakes fixed in the half-extended position , v ABF' the air brakes can become extended by aerodynamic forces. I Page 7 - 4 I 09 Jan 2002 Rev. 0 I Doc. No. 3.01.12-E 1 -'-- _ HK 36 TC -100 AFM Powered Sa ilplane Descript ion 7.5 LANDING GEAR SYSTEM The landing gear consists of a res ilient main gear with spr ing steel struts, and a res ilient castering nose wheel. An elastomer damper prov ides suspens ion for the nose wheel. Wheel brake The main wheels are equ ipped with hydraulically actuated disc brakes wh ich are individually operated through toe pedals. Parking brake The draw -button is located on the center console beh ind the trim lever . The parking brake is released when the button is in the inserted pos ition . To set the parking brake , draw the button to the stop and actuate the bra ke peda ls